28 20 8239 https://digitalprojects.uah.edu/files/original/20/977/spc_stnv_000030.pdf 907a19de79b9e4a1422476b62c823081 PDF Text Text rb $3 -! ,/- t c; --J 'A &"r- A=!-. iw A BIBLIOGRAPHY OF WERNHER VON BRAUN ,+ 1965 - -: .'g . ,, '=3, \ X -* U 7 q-3 ; ! -I e b , - - !;I: - a ) , Lc-z . cc;s ,,,,-- .- 3;c. "About Comets and Meteors, " Popular Science, 184, No. 4 (April 1964) , 95. 3 = ' 2 !;7 , a - - -- 9 i+3. ,t . 3 -- -- -- ! "The Acid Test, National Strategy in an Age of Revolutions, ed. G. B. de Huszer. New York: Frederick A. Praeger Publishers, 1959, 64. ilp'"i d4 ??qF 1 , Chemical and Engineering News, 36, No .9 (March 3, 1958) , 52. , Signal (Journal of the Armed Forces Communications and Electronics Association) , 12, do. 7 (March 1958) , 5. , Space Journal, , Vital , V. 1, No. 3 (Summer 1958), 31. Speeches, 24, No. 14 (May I,1958), 433. F. W. Magazine, 46, No. 7 (March 1959), 12. Across the Space Frontier (with J. Kaplan, H. Haber, W. Ley, and 0. Schachtek, F. L. Whipple) , ed. 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"Space Station Status Report, " Challenge (General Electric Co. ) , 2, No. 4 (Winter 1964) , 2. "Space Superiority," Ordnance, Vol. 37, No. 197 (March-April 1953), 770. "Space Travel, Best Articles and Stories, 2, No. 6 (June-July 1958) , I . , Foreign Service Journal, 35, No. 4 (April 1958) , 20. "Space Travel and Our Technological Revolution, No. 7 (July 1957), 75. " Missiles and Rockets, 2, "Space Travel, When It Is Coming, What It Will Be Like" (Interview) , U. S. News and World Report, 43, No. 16 (October 18, 1957) , 36 "Space Travel Sooner Than You Think" ( Interview) , U. S. News and World Report, 4 3 , No. 16 (September 9 , 1955), 62. �"Space Vehicles, " (with Frederick I. Ordway , 111) , The Encyclopedia Americana, Vol. 25, 1962 ed. New York: Americana Corp. , 1962, 320. "The Strange World of Zero Gravity, " Popular Science, 186, No. 6 , (June 1965) , 68. Start in den Weltraum; ein Buch iiber Raketen, Satelliten und Raumfahrzenge (With W. Ley) ~rankfurt/Main: S. Fischer , 1958. . "Station in Space, " The Complete Book of Outer Space, ed. J . Logan. New York: Maco Magazine Corp. , 1953, 16. (Reprinted in 2nd ed. , 1957, together with "A Plea for a Coordinated Space Program. ") Station in Weltraum. Frankfurt/Main: S. Fischer , 1953. by Heinz Gartmann of Across the Space Frontier. ) (German translation "Status Report on the Saturn Space C a r r i e r Vehicle and Its Potential Applications, I' Astronautica Acta, 7 , No. 2-3 (1961), 92. "The Story Behind the Explorers, " This Week Magazine, April 13, 1958, 8. "Sulla Luna con il mio Saturno, " I1 Giorno , August 24, 1965, 5. "Survey of Development of Liquid Rockets in Germany and Their Future Prospects, " Journal of the British Interplanetary Society, 10, No. 2 (March 1951) , 75. "Teamwork: Key to Success in Guided Missiles, No. I (October 1956), 38. " Missiles and Rockets, 1, "The Time for Space Exploration, " IEEE Spectrum, 2 , No. 12 (December 1965) , 44. "The Timing of Satellite and Space Probe Launchings, ' I Physics and Medicine of the Atmosphere and Space, ed. 0. 0. Benson, Jr. , and H. Strughold. New York: John Wiley and Sons, Inc., 1960, 259. "Tiniest Computers Steer Mightiest Rockets; Popular Science, 187, No. 4 (October 1965), 94. "To get to the Moon, Yale Daily News, C a r r e e r Opportunities in Research and Development Supplement, October 1963, 2. �&. nr Stockholm: Gebers F&lag, 1961. F i r s t Men on the Moon). Tur -Retur Manen. Oslo: Nosjanalfarlaget , 1961. F i r s t Men on the Moon). (Swedish translation of ( Norwegian translation of "The United States Space C a r r i e r Vehicle Program, I ' Proceedings of the Eleventh International Astronautical Congress, Vol. 1 , Stockholm, 1960. Vienna: Springer-Verlag, 1961, 638. "Un Bambino per la Luna , (Interview) LIEuropeo, January 19, 1964, 34. "U. S. Can Be F i r s t On Moon, I ' New York World Telegram, April 23, 1962, 30. U. S. Patent 2,967,393, January 10, 1961. "Rocket-propelled Missile." "Visit with a Prophet of the Space Age" (Interview) , The New York Times Magazine, October 20, 1957, 14. "Von Braun a t Marshall Tells of NASA Booster Plans, " DATA 9 , No. 1 (January 1964), 15. "Von Braun en la Argentina, " (Interview) , Revista Nacional Aeronautica y Espacial, 23, No. 259 (December 1963) , 5. "Von Braun Offers Plan for Station in.Space, I ' Aviation Age, 18, No. 6 (December 1952) , 15. "Von Braun Vous Fait Vivre l e Premier Voyage dans l a Lune," P a r i s Match, No. 532 (June 20, 1959) , 57. "Von Braun Reveals Progress in Space-Age Race, I' Honolulu Star Bulletin, January 27, 1961, 18. "Von Braun S w s Key to Space Tempo is: Change," Chicago's American, (Sect. 7) , April 7 , 1963, 2. "Von Braun says 'Your Ain't Seen Nothing, April 29, 1962, 31. '" Nashville Tennessean, "Vortwort, " Die Rakete zu den Planetenraum, H. Oberth. Verlag , 1960. Niirnberg: Uni- �, Roald Amundsen-Der Letzte Wikinger , E. Calis. Diisseldorf : Hoch-Verlag , 1960. , Vortstoss in den Weltraum, E. Dolezai. Solothurn, Switzerland: Schweizer Jugend-Verlag, 1964, 5. "Warum Raumfahrt ?" Arbeits -und Forschungsgemeinschaft "Graf Zeppelin1' Stuttgarter Gespraeche, June 1959, 26. "We Land on the Moon, '' This Week Magazine, October 12, 1958, ( P a r t 2 of F i r s t Men on the Moon. ) "Weltraumfahrt, eine Aufgabe fiir die internationale wissenschaftliche zusammenarbeit ,l 1 Probleme aus d e r Astronautisc hen Grundlagen forschung, ed. H. H. Koelle. Stuttgart: Gesellschaft fiir Weltraum forschung, 1952, 246. "We Need a Coordinated Space Program;" Space-Flight Problems (P'roceedings of the IV International Astronautical Congress, Zurich, 1953). BielBienne, Switzerland: 1954, 206. , The Yale Scientific Magazine, 31, No. 4 (January 1957), 40. "We Need to Know More About the Sun, l 1 Popular Science, 184, No. 3 (March 1964), 14. "Wernher von Braun, l1 Mitteilungen, 12, No. 44 (March 1959) , 5. (Reply to an e a r l i e r article in this publication that criticized Hermann Oberth. ) 'Wernher von Braun Answers Your Questions, " Popular Science, 182, No. I (January 1963) , 92. (Monthly column beginning with this issue and having various titles. ) "Wernher von Braun antwortet, l 1 Alfa, Zeitschrift fiir Technik und Fortbildung, I , No. I (1960) , 24. "Wernher von Braun Explores Seven Mysteries of Space'' (Interview), This Week Magazine, September 13, 1959, 18. 'Wernher von Braun on the Creative Artist ," School A r t s , 59, No. 2 (October 1959), 17. �I'What a n Astronaut will w e a r on the Moon, 1965), 87. Popular Science, 186, No. 4 (April "Whatever Happened to t h e Manned Space Station, " Popular Science, 186, No. 2 ( F e b r u a r y 1 9 6 5 ) , 88. "What I Believe, " Space World, I, No. 4 (November 1960) , 20. "What is a n Optimum P r o g r a m , '' Astronautics, 5 , No. 11 (November 1960) , 24. "What It Takes t o Survive i n Space, I ' Popular Science, 183, No. 6 (December 1963), 12. "What's Happening in the Race t o the Moon" (Interview), U. S. News and World Report, 56, No. 22 ( J u n e 1, 1964), 154. "What is Space All About?" Explorers J o u r n a l , 41, No. I ( M a r c h 1963) , 35. "What Space Control Means to U. S. , " U. S. News and World Report, 43, No. 126 (December 27, 1957) , 43. ( Excerpts f r o m testimony before senate committee) . "When Will We Land on Mars?'! Popular Science, 186, No. 3 ( M a r c h 1965) , 86. "Where A r e We Going?" Space Journal, 1 , No. 1 (Summer 1957), 10. "Where A r e We in Space?'' This Week Magazine, January 1 , 196 1, 1. "Where We Stand and Where We A r e Going, " ( I n t e r v i e w ) , E r i k Bergaust, This Week Magazine, September 30, 1962 , 4. "Why and How of the Countdown, ' I Popular Science, 186, No. 1 (January 1965) , 66. "Why a Satellite Stays Up, " Popular Science, 183, No. 4 (October 1963) , 16. "Why I Believe, I ' This Week, ( J u l y 18, 1965) , 2. "Why I Believe i n Immortality, " The Third Book of Words to Live By, ed. W. Nichols. New York: Simon and Schuster, 1962, 119. "Why I Chose America, " A m e r i c a n Map-azine, 154, No. 1 (July 1952), 15. "Why Must We Conquer Space, ' I Alabama School Journal, 78, No. 7 ( F e b r u a r y , 1961), 14. �, Virginia Journal of Education, 54, No. 4 (December 1962), 11. "Why Rockets Have Fins, " Popular Science, 185, No. 3 (September 1964) , 68. "Why Should America Conquer Space?ll This Week Magazine, March 20, 1960, 8. I7WhyShould I Be a Space Scientist?" Phamphlet published and distributed by the New York Life Insurance Co. , 1963. "Why the Challenge Must be Met, " Insulation Magazine, 8 , No. 2 ( February 1962) , 37. "Will Astronauts 'Fly' Rocket Boosters?" Popular Science, 184, No. 2 (June 1964), 72. "You Can't Duck the Space Age," The Emory Magazine, 41, No. 4 (July 1965), 10. "Your Most Important Problem, '' Hi Way, (November 1959) , 3 . "Zum amerikanischen Raumfahrtprogramm , " Starten und Fliegen, ed. H. -J. Luz. Stuttgart: Deutsche Verlags-Anstalt, 1959, 366. � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000030 Title A name given to the resource "A Bibliography of Wernher von Braun, 1965." Creator An entity primarily responsible for making the resource Sharpe, Mitchell R. Date A point or period of time associated with an event in the lifecycle of the resource 1965-12 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) Von Braun, Wernher, 1912-1977 Type The nature or genre of the resource Bibliographies Text Source A related resource from which the described resource is derived Saturn V Collection Box 15, Folder 38 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050 https://digitalprojects.uah.edu/files/original/20/978/spc_stnv_000031.pdf c9eb0a707b5e24890270eb392ebe82b8 PDF Text Text - '- '"T )I j GEORGE C. MARSHALL SPACE FLIGHT CENTER HUNTSVILLE, ALABAMA Memorandum TO Distribution FROM H i s t o r i c a l O f f i c e , A&TS-MS-H DATE S$,Tl.,i':.l ~i!Sy.?,.?:Gy DCCUPIENT (./rij~ci;it.Y $.lzk,~maR,?-:cs!.ch Institute History of Science& 'rec',r:clogy Group SUBJECT T r a n s m i t t a l o f D r a f t ---------- -------- Date DOC. NO. The a t t a c h e d m a t e r i a l i s a d r a f t of t h e o f f i c i a l 1966 Chronology o f MSFC, t o be p u b l i s h e d s o o n . We i n v i t e you t o r e a d t h i s c h r o n o l o g y , make t h e changes o r a d d i t i o n s you c o n s i d e r n e c e s s a r y , and r e t u r n t h e copy t o u s a t a n e a r l y d a t e . I f you appove o f t h e m a t e r i a l a s i t i s , p l e a s e i n i t i a l y o u r a p p r o v a l on t h i s t r a n s m i t t a l l e t t e r and r e t u r n t o u s , s o we may keep y o u r c o n c u r r e n c e on f i l e . Your c o o p e r a t i o n w i l l h e l p X s s u r e p r o d u c t i o n o f an a c c u r a t e c h r o n o l o g y o f t h e C e n t e r ' s 1966 o p e r a t i o n . You a r e on d i s t r i b u t i o n f o r a copy of t h e completed c h r o n o l o g y . L. L . ~ o n q $ Historian ' Distribution: S&E-DIR, H. Weidner S&E-CSE, W . Haeussermann S&E-ASTR, B . Moore S&E-QUAL, D. Grau S&E-AERO, E . G e i s s l e r S&E-ASTN, K . Heimburg S&E-ME, M. S i e b e l PD-DIR, W . Lucas PD-SA, W . Huber PD-DO, E. Goerner PD-AP, H. Becker PM-DIR, E . O'Connor PM-COY 0 . H i r s c h PM-EP, W . Brown PM-SAT, L. James PM-MA, G . Constan F'M-MT, J . Balch PM-AA, L . Belew PM-MU, F. S p e e r A&TS-DIR, D. Newby A&TS-FAC, C . Huth A&TS-FIN, T. Hardeman A&TS-MA, P . S t y l e s A&TS-PR, G . Buckner A&TS-TS , D . Foxwor t h y S , J . Murphy PA, F. Haley CC, W . G u i l i a n IS-CAS-5, J . Cobb NASA Hq. EH, E . Ernme �J A N U A R Y JANUARY 1: 1 9 6 6 MSFC e x e r c i s e d t h e o p t i o n t o e x t e n d t h e Mason-Rust s u p p o r t c o n t r a c t a t Michoud Assembly F a c i l i t y (MAF) f o r one y e a r . 1 s i o n i n c r e a s e d t h e c o n t r a c t v a l u e by $ 1 3 . 1 m i l l i o n . The e x t e n - - Program o f f i c i a l s f o r m a l l y r e d e s i g n a t e d S-11-T, t h e a l l - s y s t e m s t e s t s t a g e , a s S-11-T/D, t h e a l l - s y s t e m s t e s t l d y n a m i c t e s t s t a g e . 2 - MSFC D i r e c t o r Wernher von Braun named D r . J . C . McCall t o o r g a n i z e and manage t h e E x p e r i m e n t s and A p p l i c a t i o n s O f f i c e , which would manage MSFC1s p o r t i o n o f t h e A p o l l o A p p l i c a t i o n s Program. 3 JANUARY 3 : MSFC awarded t o Lockheed M i s s i l e s and Space Company a MIMOSA ( m i s s i o n modes and s y s t e m a n a l y s i s ) s t u d y c o n t r a c t . Purpose o f t h e s t u d y was t o d e f i n e and a n a l y z e p o t e n t i a l s y s t e m c o n c e p t s and programs a p p l i c a b l e t o b o t h l u n a r e x p l o r a t i o n and s c i e n t i f i c m i s s i o n s f o r 4 experiments. - NASA announced n e g o t i a t i o n of two nine-month s t u d y c o n t r a c t s i n v o l v i n g an improved and s i m p l i f i e d 5-2 e n g i n e f o r S a t u r n V 1 s S - I 1 and S-IVB stages. North American A v i a t i o n , I n c . (NAA), r e c e i v e d a $148,000 c o n t r a c t and Douglas A i r c r a f t Company a $225,000 m o d i f i c a t i o n t o a n existing contract.5 JANUARY 4: MSFC awarded two s t u d y c o n t r a c t s f o r a manned r e u s a b l e s p a c e t r a n s p o r t system. $237,000. Lockheed - C a l i f o r n i a Company r e c e i v e d one f o r The o t h e r c o n t r a c t , f o r $51,000, went t o M a r t i n M a r i e t t a Corporation. 6 - MSFC announced award of f i v e s t u d y c o n t r a c t s t o S a t u r n s t a g e c o n t r a c t o r s . S t u d i e s i n c l u d e d e i g h t v a r i a t i o n s of improved S a t u r n V v e h i c l e s and s i x proposed S a t u r n I B c o n f i g u r a t i o n s . The Boeing Company r e c e i v e d �one c o n t r a c t , North American A v i a t i o n o n e , Douglas two, and C h r y s l e r Corporation one. 7 JANUARY 5: NASA and Radio C o r p o r a t i o n of American (RCA) o f f i c i a l s s i g n e d a l o g i s t i c s and maintenance c o n t r a c t , NAS8-15496, c o v e r i n g t h e RCA l l O A computer program f o r S a t u r n I B and S a t u r n V v e h i c l e s . Amount of t h e two-year c o n t r a c t was $7.8 m i l l i o n . The l o g i s t i c s u p p o r t c o n t r a c t covered s e r v i c e s on t h e RCA computer used t o check S a t u r n I B and S a t u r n V l a u n c h v e h i c l e systems a u t o m a t i c a l l y d u r i n g m a n u f a c t u r e and l a u n c h . 8 JANUARY 6: Boeing workmen a t Michoud Assembly F a c i l i t y (MAF) completed i n t e g r a t e d t e s t i n g on t h e S-IC-F s t a g e and t r a n s f e r r e d i t t o a t e s t 9 c e l l f o r w e i g h i n g and p r e p a r a t i o n f o r shipment. - D o r t e c h , I n c . , completed S-IC T r a n s p o r t e r No. 107 a t Tampa, F l o r i d a , and s h i p p e d t h e t r a n s p o r t e r t o MSFC aboard t h e NASA b a r g e L i t t l e 10 Lake. JANUARY 8: The S-IVB b a t t l e s h i p from Sacramento T e s t C e n t e r , C a l i f o r n i a (SACTO), a r r i v e d by b a r g e a t South P i t t s b u r g , T e n n e s s e e , e n r o u t e t o Arnold E n g i n e e r i n g Development C e n t e r a t Tullahoma f o r f u r t h e r t e s t i n g .I1 JANUARY 10: Douglas s h i p p e d t h e S-IVB-204 s t a g e , j u s t completed a t i t s H u n t i n g t o n Beach, C a l i f o r n i a , assembly p l a n t , from S e a l Beach, 12 C a l i f o r n i a , t o SACTO a b o a r d t h e b a r g e O r i o n . - Workmen a t Huntington Beach completed i n s t a l l a t i o n of t h e 5 - 2 e n g i n e 13 on S-IVB-205 s t a g e . �JANUARY 12: North American A v i a t i o n p e r s o n n e l conducted a f u l l - d u r a t i o n s t a t i c f i r i n g of t h e S - I 1 s t a g e b a t t l e s h i p a t S a n t a Susana F i e l d L a b o r a t o r y , C a l i f o r n i a (SSFL). The f i r i n g had t o be t e r m i n a t e d m a n u a l l y a t 354 seconds b e c a u s e a n a u t o m a t i c LOX l o w - l e v e l s i g n a l 14 c u t o f f did n o t occur. JANUARY 13: MSFC announced t h e award of a $ 4 . 1 m i l l i o n m o d i f i c a t i o n of i t s c o n t r a c t w i t h I n t e r n a t i o n a l Business Machines C o r p o r a t i o n (IBM) f o r m a n u f a c t u r e of 78 a d d i t i o n a l r e d u n d a n t s w i t c h s e l e c t o r s f o r S a t u r n V and S a t u r n I B v e h i c l e . 15 - MSFC workmen moved t h e S-IC-D dynamic t e s t s t a g e from M a n u f a c t u r i n g E n g i n e e r i n g (ME) L a b o r a t o r y b u i l d i n g and h o i s t e d i t i n t o t h e S a t u r n V 16 Dynamic T e s t S t a n a . - P o s t - m a n u f a c t u r i n g c h e c k o u t of t h e "minimum c o n f i g u r a t i o n " S-IC-F s t a g e ended a t MAF. T h i s p r o c e d u r e e s t a b l i s h e d t h e s t a g e ' s w e i g h t and c e n t e r of g r a v i t y . 17 - During a p r e s s u r e t e s t a t SACTO t h e S-IVB common bulkhead t e s t a r t i c l e 18 f a i l e d , completely s e v e r i n g t h e bulkhead. JANUARY 14: Boeing p e r s o n n e l a t MAF l o a d e d S-IC-F, the Saturn V f a c i l i t i e s b o o s t e r , a b o a r d t h e b a r g e Poseidon f o r i t s journey t o Kennedy Space 19 C e n t e r , F l o r i d a (KSC). - S-IVB-204 f l i g h t s t a g e a r r i v e d a t SACTO and was i n s t a l l e d i n Beta 3 20 Test Stand. - The S-11-1, f i r s t S - I 1 f l i g h t s t a g e , completed t h e f i r s t f u l l - s t a g e h y d r o s t a t i c p r o o f t e s t i n g a t t h e S e a l Beach, C a l i f o r n i a , assembly p l a n t of North American A v i a t i o n ' s Space and I n f o r m a t i o n Systems 21 D i v i s i o n (S&ID). �With S-IVB-202 s t a g e p o s t - f i r i n g a c t i v i t i e s c o m p l e t e a t 22 SACTO, Douglas s h i p p e d t h e s t a g e t o KSC. JAhrLTARY 15: - The b a r g e P o s e i d o n l e f t MAE w i t h S-IC-F, - S-IC-1 p o s t - m a n u f a c t u r i n g c h e c k o u t ended a t MSFC. 2 4 JANUARY 17: e n r o u t e t o KSC. 23 P e r s o n n e l a t MSFC completed t h e h o r i z o n t a l assembly of S-IC-2 and moved t h e s t a g e t o Q u a l i t y and R e l i a b i l i t y Assurance ( Q u a l i t y ) L a b o r a t o r y f o r p o s t - m a n u f a c t u r i n g c h e c k o u t . 25 - C h r y s l e r p e r s o n n e l a t H u n t s v i l l e f i r e d t h e S-IB-4 s t a g e f o r 35.23 s e c o n d s a s s c h e d u l e d . 26 - Douglas p e r s o n n e l a t SACTO began p r o p u l s i o n subsystem c h e c k o u t of t h e A t e s t a c c i d e n t damaged t h e r e c i r c u l a t i o n pump and n e c e s s i t a t e d i t s r e p l a c e m e n t . 2 7 S-IVB-203 s t a g e . - Wyle L a b o r a t o r i e s a t H u n t s v i l l e s u c c e s s f u i l y completed v i b r a t i o n t e s t i n g o f t h e G e n e r a l Dynamics S-IU-500V, f o r t h e S a t u r n V program. 2 8 JANUARY 19: a vibration t e s t instrument u n i t The S-IC-F a r r i v e d a t KSC aboard t h e Poseidon f o r u s e i n c h e c k i n g o u t Launch Complex 39 (LC-39). 2 9 - MSFC t e s t - f i r e d t h e S-IVB B a t t l e s h i p s t a g e a t H u n t s v i l l e f o r 7 . 3 s e c o n d s . 30 JAhWARY 20: NASA and Rocketdyne D i v i s i o n of NAA announced c o m p l e t i o n of J-2 engine q u a l i f i c a t i o n t e s t s . I n t h e t e s t program a t S a n t a Susana, Rocketdyne f i r e d a s i n g l e e n g i n e s u c c e s s f u l l y 30 s e p a r a t e t i m e s f o r a t o t a l f i r i n g time of 3,774 s e c o n d s .3 1 �JANUARY 20: Workmen removed S-IC-T from t h e S t a t i c T e s t S t a n d a t MSFC and moved i t t o ME Lab f o r s t o r a g e pending t h e s t a g e ' s c o n v e r s i o n 32 t o t h e S-IC-4 c o n f i g u r a t i o n . - A t MAE Boeing workmen completed i n t e r t a n k assembly o f t h e S-IC-4 f o l l o w i n g c o m p l e t i o n of t h e s t a g e ' s t h r u s t s t r u c t u r e on J a n u a r y 10. 33 JANUARY 21: D r . von Braun a p p o i n t e d D r . W i l l i a m R . Lucas d i r e c t o r of t h e P r o p u l s i o n and V e h i c l e E n g i n e e r i n g (P&VE) L a b o r a t o r y , e f f e c t i v e March 1, 1966. He succeeded F. B. C l i n e , who r e s i g n e d . 34 - MSFC n e g o t i a t e d and s i g n e d w i t h Bendix C o r p o r a t i o n a c o n t r a c t f o r a m o b i l i t y e v a l u a t i o n and comparisons s t u d y c o n c e r n i n g l u n a r s u r f a c e v e h i c l e s . 35 - The f o u r t h S a t u r n I B f l i g h t b o o s t e r , S-IB-4, underwent a f u l l - d u r a t i o n 36 f i r i n g o f 2% m i n u t e s a t MSFC/Huntsville. JANUARY 24: S-IC-1, MSFC t e c h n i c i a n s moved t h e f i r s t S a t u r n V f l i g h t b o o s t e r , t o t h e S-IC S t a t i c T e s t S t a n d and mounted i t i n t h e s t a n d . - An S-IVB B a t t l e s h i p f i r i n g a t MSFC l a s t e d f o r 100.46 s e c o n d s . - Damping t e s t s began a t MSFC on t h e S-IC-D s t a g e . JANUARY 26: 3'7 38 39 MSFC p e r s o n n e l s u c c e s s f u l l y f i r e d f o r t h e f i r s t time a t s i m u l a t e d a l t i t u d e t h e S-IVB s t a g e a u x i l i a r y p r o p u l s i o n s y s t e m (APS). The t e s t , c o n d u c t e d i n t h e a l t i t u d e t e s t c e l l a t MSFC, v e r i f i e d t h e 40 i n t e g r i t y of t h e Apollo r e g u l a t o r i n t h e APS. - T e c h n i c i a n s . a t MSFC t e s t - f i r e d t h e S-IVB B a t t l e s h i p s t a g e f o r 438 41 seconds, achieving a l l major t e s t o b j e c t i v e s . �JANUARY 28: S t r u c t u r a l f a b r i c a t i o n and assembly of t h e S-IU-501 was 42 completed a t MSFC, and component assembly was s t a r t e d . - P o s t - m a n u f a c t u r i n g c h e c k o u t of S-IVB-501, the f i r s t f l i g h t Saturn V 43 t h i r d s t a g e , ended a t Douglas' Huntington Beach f a c i l i t y . JANUARY 29: The f o u r t h f l i g h t S a t u r n I B b o o s t e r s t a g e , S-IB-4, left MSFC/Huntsville a b o a r d t h e b a r g e Palaemon f o r MAF where i t would u n d e r g o p o s t - f i r i n g c h e c k o u t . 44 JANUARY 31: S-11-F s t a g e moved t o a s t a t i o n a t S e a l Beach f o r s y s t e m c h e c k o u t , p a i n t i n g , f i n a l c l o s e o u t , and packaging f o r shipment. 45 I N JANUARY: T e s t p e r s o n n e l moved t h e S-IC-S o x i d i z e r t a n k assembly i n t o t h e V e r t i c a l Assembly B u i l d i n g (VAB) a t MSFC f o r i n s t a l l a t i o n o f i n s t r u m e n t a t i o n i n p r e p a r a t i o n of t e s t s i n t h e Load T e s t Annex. 4 6 - S-11-5 s t a g e f i n a l assembly began a t S e a l Beach. 47 �F E B R U A R Y 1 9 6 6 FEBRUARY 1: S-IB-2 s t a g e , t h e second S a t u r n I B f l i g h t b o o s t e r , d e p a r t e d 1 MAF f o r KSC. FEBRUARY 2: The S-IU-200S/500S-I1 s t r u c t u r a l t e s t u n i t f a i l e d a t MSFC w h i l e b e i n g s u b j e c t e d t o 140 p e r c e n t o f s i m u l a t e d maximum p r e s s u r e l i m i t loads. T h i s t e s t completed q u a l i f i c a t i o n o f t h e i n s t r u m e n t u n i t s t r u c t u r e f o r Saturn I B missions .2 FEBRUARY 3: James E . Kingsbury would s u c c e e d D r . W. R. Lucas a s Chief o f t h e M a t e r i a l s D i v i s i o n , P r o p u l s i o n and V e h i c l e E n g i n e e r i n g L a b o r a t o r y , t h e MSFC D i r e c t o r announced. t o r o f t h e P&VE Lab. - D r . Lucas was named e a r l i e r t o b e D i r e c - 3 Both a p p o i n t m e n t s were t o be e f f e c t i v e March 1. The a t t e m p t e d f u l l - d u r a t i o n f i r i n g o f t h e S - I 1 S t a g e B a t t l e s h i p a t S a n t a Susana F i e l d L a b o r a t o r y t e r m i n a t e d a f t e r 14 s e c o n d s o f mains t a g e o p e r a t i o n because of a gas g e n e r a t o r over-temperature s i g n a l r e s u l t i n g from a f a u l t y c o n n e c t o r . - 4 Power was a p p l i e d t o S-IC-2 a t Q u a l i t y L a b o r a t o r y f o l l o w i n g c o m p l e t i o n o f s t a g e s t a t u s c h e c k on F e b r u a r y 1 d u r i n g p o s t - m a n u f a c t u r i n g c h e c k out. 5 FEBRUARY 4: A l l e n g i n e and s t a g e p a r a m e t e r s a p p e a r e d normal d u r i n g t h e MSFC S-IVB B a t t l e s h i p s t a t i c f i r i n g which l a s t e d 445 s e c o n d s . 6 FEBRUARY 7 : Workmen a t KSC moved t h e S-IC-F s t a g e i n t o t h e low bay o f 7 t h e VAB i n p r e p a r a t i o n f o r s t a c k i n g . - The S - I 1 B a t t l e s h i p a t SSFL f i r e d f o r 336 s e c o n d s . Cutoff occurred when t h e augmented s p a r k i g n i t e r on e n g i n e 4 r u p t u r e d , c a u s i n g a �f i r e . The f i r s t S - I 1 B a t t l e s h i p p r o p e l l a n t u t i l i z a t i o n t e s t was s u c c e s s f u l l y completed. 8 FEBRUARY 8 : Completed a t M i s s i s s i p p i T e s t F a c i l i t y (MTF) and r e l e a s e d by t h e c o n t r a c t o r was t h e H i g h - P r e s s u r e Water F a c i l i t y , i n c l u d i n g t h r e e d e e p w e l l s and a 6 0 - m i l l i o n - g a l l o n r e s e r v o i r . 9 FEBRUARY 11-18: S-IC-D s u s p e n s i o n s y s t e m and damping t e s t s c o n t i n u e d i n t h e S a t u r n V Dynamic T e s t F a c i l i t y a t MSFC." FEBRUARY 11: S-IVB-203 s t a g e p r e - a c c e p t a n c e f i r i n g a c t i v i t i e s ended a t SACTO'S Beta 1 T e s t S t a n d w i t h i n i t i a t i o n o f t h e s i m u l a t e d s t a t i c 11 firing test. FEBRUARY 14: MSFC Q u a l i t y Lab p e r s o n n e l completed c h e c k o u t o f t h e S-IU- 500FS ( f l i g h t s y s t e m s t e s t u n i t ) .I2 FEBRUARY 17: The f i r s t t e s t f i r i n g of S-IC-1 o c c u r r e d ahead o f s c h e d u l e a t MSFC. - A l l main t e s t o b j e c t i v e s were met i n t h e 40.7-second t e s t . 13 NASA announced t h e award o f f o u r l u n a r e x p l o r a t i o n s t u d y c o n t r a c t s v a l u e d a t a b o u t $1.8 m i l l i o n , which would be managed by MSFC. Lock- heed M i s s i l e s and Space Company r e c e i v e d a n $897,000 c o n t r a c t f o r a comprehensive A p o l l o A p p l i c a t i o n s s t u d y known a s MIMOSA ( m i s s i o n modes and s y s t e m s a n a l y s i s ) . S u p p o r t i n g s t u d i e s went t o Bendix, f o r $500,000; t o NAA, f o r $200,000; and t o A i r e s e a r c h M a n u f a c t u r i n g Company, f o r $200,000. 1 4 FEBRUARY 17-19: Workmen a t S e a l Beach l o a d e d and t i e d down t h e S-11-F s t a g e a b o a r d t h e P o i n t Barrow i n p r e p a r a t i o n f o r s h i p p i n g t h e s t a g e 15 t o KSC. �FEBRUARY 20: S-IVB-502 assembly ended w i t h j o i n i n g of t h e a f t s k i r t , forward s k i r t , and t h r u s t s t r u c t u r e ; Douglas workmen moved t h e s t a g e 16 i n t o t h e c h e c k o u t tower a t Huntington Beach. A 40.19-second 17 o c c u r r e d a t MSFC. FEBRUARY 21: - t e s t f i r i n g of t h e S-IVB B a t t l e s h i p s t a g e MSFC t e c h n i c i a n s completed d i s a s s e m b l y o f S-IU-500V components i n p r e p a r a t i o n f o r r e a s s e m b l y i n t o t h e S-IU-500V-I1 s t r u c t u r e . General Dynamics p r o v i d e d t h e S-IU-500V s t r u c t u r e and NAA t h e s t r u c t u r e of 18 t h e S-IU-500V-11. An S - I 1 B a t t l e s h i p f i r i n g a t S a n t a Susana ended a f t e r 19 69 s e c o n d s . FEBRUARY 22: FEBRUARY 24: A f t e r s e v e r a l a t t e m p t s a t a f u l l - d u r a t i o n t e s t , S&ID p e r - s o n n e l a t SSFL conducted a 365-second f i r i n g of t h e S - I 1 B a t t l e s h i p stage. FEBRUARY 25: A l l primary t e s t o b j e c t i v e s were s a t i s f i e d . 2 0 I n i t s second s t a t i c t e s t , s c h e d u l e d f o r 125 s e c o n d s , S-IC-1 f i r e d 8 3 . 2 s e c o n d s ; an o b s e r v e r t e r m i n a t e d t h e t e s t a f t e r r e c e i v i n g a n i n c o r r e c t r e a d i n g from a f a u l t y t r a n s d u c e r . O f f i c i a l s decided t h a t no f u r t h e r f i r i n g was r e q u i r e d . 2 1 - The S-IU-500F, r e d e s i g n a t e d and m o d i f i e d w i t h components from t h e S-IU-200Fl500F which was damaged a t KSC l a t e i n 1965, was completed at ~ s ~ c . 2 2 - The S - I 1 B a t t l e s h i p a t S a n t a Susana f i r e d f o r 361 s e c o n d s and c u t o f f 23 a u t o m a t i c a l l y upon LOX d e p l e t i o n . �FEBRUARY 26: AS-201, t h e f i r s t S a t u r n I B f l i g h t v e h i c l e , was s u c c e s s f u l l y l a u n c h e d from LC-34 a t Cape Kennedy a t 11:12 a.m. EST. Unmanned A p o l l o s p a c e c r a f t 009 was b o o s t e d i n t o s u b o r b i t a l f l i g h t by S a t u r n I B l a u n c h v e h i c l e SA-201 t o q u a l i f y t h e Command Module (CM) h e a t s h i e l d i n g , t h e S e r v i c e Module (SM) p r o p u l s i o n s y s t e m , m a j o r s p a c e c r a f t s y s t e m s , and t h e launch v e h i c l e - s p a c e c r a f t combination. were normal. L i f t o f f and powered f l i g h t F o l l o w i n g a seven-minute b u r n o f t h e S-IVB s t a g e , t h i s second s t a g e and i n s t r u m e n t u n i t s e p a r a t e d from t h e s p a c e c r a f t . s p a c e c r a f t r e a c h e d a l t i t u d e o f 310 m i l e s . The The d e s c e n d i n g SM performed a n u l l a g e maneuver, f i r i n g t h e r e a c t i o n c o n t r o l s y s t e m r o c k e t s f o r 3 0 seconds t o i n c r e a s e t h e s p a c e c r a f t ' s r e e n t r y speed. propulsion engine f i r e d twice--for The SM's main 100 s e c o n d s and f o r 1 0 s e c o n d s . The SM was j e t t i s o n e d , and t h e CM r e e n t e r e d t h e e a r t h ' s atmosphere a t a b o u t 27,000 f e e t p e r second. The s p a c e c r a f t ' s h e a t s h i e l d w i t h s t o o d r e e n t r y h e a t of about 4,000 degrees F a h r e n h e i t . The t h r e e main p a r a c h u t e s d e p l o y e d a t 1 2 , 0 0 0 f e e t a l t i t u d e , and t h e CM s p l a s h e d i n t o t h e A t l a n t i c a t 1 1 : 5 1 a.m. EST w i t h i n 35 m i l e s o f t h e t a r g e t . A h e l i c o p t e r from t h e USS Boxer r e c o v e r e d t h e s p a c e c r a f t ; i t was i n "good" c o n d i t i o n . o f f i c i a l s c a l l e d t h e m i s s i o n "a c o m p l e t e s u c c e s s . 1, 24 - NASA P e r s o n n e l a t SACTO s u c c e s s f u l l y accomplished t h e S-IVB-203 s t a g e a c c e p t a n c e f i r i n g a f t e r u n s u c c e s s f u l a t t e m p t s F e b r u a r y 1 8 and 22. The s i n g l e 5-2 e n g i n e had a m a i n s t a g e f i r i n g o f 284.9 s e c o n d s f o l lowed by a s i m u l a t e d t w o - o r b i t c o a s t p e r i o d w i t h e n g i n e r e s t a r t cond i t i o n p r e p a r a t i o n s a f t e r e a c h o r b i t . 25 - Workmen a t S e a l Beach completed t h e S-11-3 a f t s k i r t l t h r u s t s t r u c t u r e a s s e m b l y . 26 FEBRUARY 28: S t a g e c h e c k o u t o f S-IVB-502 began a t Douglas' H u n t i n g t o n Beach f a c i l i t y f o l l o w i n g t h e F e b r u a r y 17 i n s t a l l a t i o n o f t h e s t a g e ' s 5-2 e n g i n e . 27 �FEBRUARY 28: The S-IB-5 s t a g e , which had a r r i v e d a t MSFC on t h e b a r g e Palaemon F e b r u a r y 27, was i n s t a l l e d i n t h e S t a t i c T e s t Tower E a s t f o r f i r i n g . 28 - V e r t i c a l assembly o f S-IC-4 began a t MAF; Boeing p e r s o n n e l had comp l e t e d forward s k i r t assembly on F e b r u a r y 8 and h y d r o s t a t i c t e s t o f t h e f u e l t a n k on F e b r u a r y 1 0 . 29 I N FEBRUARY: V e r t i c a l b u i l d u p o f t h e S-11-2 commenced f o l l o w i n g c o m p l e t i o n o f forward s k i r t and a f t LOX bulkhead a s s e m b l i e s a t S e a l Beach. 3 0 �MARCH 1: The AS-203 v e h i c l e ' s n o s e c o n e , which was manufactured a t MSFC, was s h i p p e d t o KSC. 1 - - ME L a b o r a t o r y p e r s o n n e l completed f i n a l c h e c k o u t of t h e bonding a u t o 2 c l a v e i n B u i l d i n g 4707. MSFC awarded a o n e - y e a r $1.6 m i l l i o n c o n t r a c t t o L i n g Temco V o u g h t ' s Range Systems D i v i s i o n t o f u r n i s h t e c h n i c i a n s t o o p e r a t e computers a t MAF'S Computer O p e r a t i o n s , S l i d e l l , L o u i s i a n a . 3 - A 412.44-second f i r i n g o f t h e S-IVB B a t t l e s h i p a t MSFC ended w i t h a c u t o f f c a u s e d by f u e l d e p l e t i o n . - 4 The b a r g e P o s e i d o n d e p a r t e d MSFC/Huntsville c a r r y i n g t o KSC t h r e e S a t u r n V s e r v i c e arms p l u s t h e S-IU-500F and t h e n o s e cone f o r t h e 5 LH2 e x p e r i m e n t v e h i c l e , AS-203. - Boeing p e r s o n n e l a t MSFC completed c i r c u i t checks and ground equipment t e s t s e t c h e c k s o f e l e c t r i c a l s u p p o r t equipment on t h e S a t u r n V Systems Development F a c i l i t y (SDF). 6 MARCH 4: The S - I 1 s t a g e B a t t l e s h i p a t SSFL f i r e d f o r a planned 360 seconds 7 o f m a i n s t a g e o p e r a t i o n . C u t o f f came w i t h LH2 d e p l e t i o n . - NASA announced c o n v e r s i o n o f t h e Boeing S-IC s t a g e prime c o n t r a c t from a f i x e d - f e e t o a n i n c e n t i v e - f e e t y p e of c o n t r a c t . S a t u r n s t a g e c o n t r a c t t o be s o c o n v e r t e d . 8 c o n v e r s i o n was $850.1 m i l l i o n . I t was t h e f i r s t The c o n t r a c t ' s v a l u e upon �MARCH 4: The S-11-F s t a g e and i t s i n t e r s t a g e on t h e P o i n t Barrow a r r i v e d a t P o r t C a n a v e r a l , F l o r i d a , 12 days a f t e r d e p a r t i n g t h e assembly p l a n t a t Sea1 Beach on F e b r u a r y 20. 9 MARCH 6: Workmen a t KSC'S LC-39 moved t h e S-11-F s t a g e and i n t e r s t a g e i n t o t h e VAB low bay i n p r e p a r a t i o n f o r s , t a c k i n g a s p a r t o f t h e S a t u r n V f a c i l i t y c h e c k o u t v e h i c l e , SA-SOOF. 1 0 MARCH 7: MSFC announced t h a t a l l p r i m a r y m i s s i o n o b j e c t i v e s of t h e AS-201 m i s s i o n F e b r u a r y 26 were a c h i e v e d and t h a t t h e f l i g h t was v e r y s a t i s f a c t o r y a c c o r d i n g t o i n i t i a l e v a l u a t i o n of t e s t r e s u l t s . Guid- a n c e and c o n t r o l s y s t e m s performed w e l l , b o t h S-IB and S-IVB s t a g e t r a j e c t o r i e s and v e l o c i t i e s were n o r m a l , and no s t r u c t u r a l problems w e r e found i n e i t h e r s t a g e o r t h e i n s t r u m e n t u n i t . The q u a l i t y of d a t a r e c e i v e d a t ground s t a t i o n s was " e x c e l l e n t , " and few l o s s e s o c c u r r e d i n t h e e x p e c t e d 1300 measurements t h a t were t e l e m e t e r e d . 11 - C o n s t r u c t i o n began a t S e a l Beach on t h e new S - I 1 s t a g e subassembly 12 b u i l d i n g f o r which t h e c o n t r a c t was awarded March 2 . - S&ID t e c h n i c i a n s f i n i s h e d i n s t a l l i n g t h e f i v e 5-2 e n g i n e s on t h e S-11-1 s t a g e a t S e a l Beach f o l l o w i n g c o m p l e t i o n o f s t a g e assembly on 13 February 27. Boeing p e r s o n n e l p l a c e d t h e S-IC-3 s t a g e i n t h e S t a g e Checkout B u i l d i n g a t MAF f o r p o s t - m a n u f a c t u r i n g c h e c k o u t . 1 4 MARCH 9: - A s t a t i c f i r i n g of t h e MSFC S-IVB B a t t l e s h i p ended a f t e r 2.15 s e c o n d s 15 when t e r m i n a t e d by a g a s g e n e r a t o r o v e r - t e m p e r a t u r e d e v i c e . MARCH 10: S t r u c t u r a l t e s t p e r s o n n e l a t MSFC t e s t e d t h e S-IC q u a r t e r - s c a l e i n t e r t a n k t o t h e p o i n t of f a i l u r e . The t e s t specimen f a i l e d a t �1 5 0 p e r c e n t of combined a x i a l l o a d , bending moment, and s h e a r i n 16 a cryogenic environment, MARCH 10: The S-IU-500FS was flown from H u n t s v i l l e t o t h e Douglas H u n t i n g t o n Beach p l a n t aboard t h e Super Guppy a i r c r a f t i n p r e p 17 a r a t i o n f o r t h e S-IVBIIU t e s t program t h e r e . NASA H e a d q u a r t e r s approved t h e Boeing procurement p l a n f o r 18 s t a g e s S-IC-11 t h r o u g h S-IC-15. MARCH 11: - Douglas s h i p p e d t h e S-IVB-501 s t a g e from Huntington Beach t o SACTO 19 f o r acceptance f i r i n g s . MARCH 14: S-IC-1 was removed from t h e t e s t s t a n d a t MSFC and p l a c e d i n ME L a b ' s new h a n g a r ( B u i l d i n g 4755) f o r r e f u r b i s h m e n t p r i o r t o s t a r t 20 o f p o s t - s t a t i c checkout. - Rocketdyne s u c c e s s f u l l y completed t h e r e l i a b i l i t y d e m o n s t r a t i o n program f o r t h e 230,000-pound-thrust 21 engine. MARCH 15: ( 2 3 0 ~ )c o n f i g u r a t i o n of t h e 5-2 KSC workmen i n s t a l l e d S-IC-F i n Launch U m b i l i c a l Tower No. 1 (LUT-1) a t LC-39. 2 2 - An S - I 1 B a t t l e s h i p t e s t f i r i n g a t SSFL l a s t e d f o r 349 seconds m a i n s t a g e o p e r a t i o n , u n t i l d e p l e t i o n of LH2. A t h i r d t e s t s c h e d u l e d f o r March was c a n c e l l e d , c o m p l e t i n g t h e B a t t l e s h i p t e s t i n g - s e r i e s f o r t h e 23 current schedule. MARCH 18: S-IVB-204 s t a g e a c c e p t a n c e f i r i n g was s u c c e s s f u l l y performed on t h e f i r s t a t t e m p t a t SACTO's Beta 3 T e s t S t a n d . 24 d u r a t i o n was 451.2 s e c o n d s . The m a i n s t a g e �MARCH 19: Douglas p e r s o n n e l a t Huntington Beach completed f a c t o r y check- o u t of t h e S-IVB-500ST, 25 S a t u r n V program. - t h e MSFC t h i r d s t a g e s i m u l a t o r f o r t h e Assembly of S-IC-3 a t MAF proceeded s l o w l y because of hardware s h o r t a g e s and d e s i g n c h a n g e s . t h e s y s tems t e s t a r e a . 2 6 - Workmen d e l i v e r e d t h e i n c o m p l e t e s t a g e t o Douglas p e r s o n n e l removed S-IVB-203 s t a g e from Beta 1 T e s t S t a n d a t SACTO f o r c o m p l e t i o n of p o s t - s t a t i c c h e c k o u t .27 MARCH 20-24: The S-IVB-D dynamic t e s t s t a g e was l o a d e d a b o a r d t h e Super Guppy a t H u n t s v i l l e f o r a n a i r c r a f t f l i g h t t e s t t o and from t h e Los A l a m i t o s Naval A i r S t a t i o n , C a l i f o r n i a . 28 d e v e l o p e d on t h e f l i g h t . MARCH 21: The S-IVB-501, No s i g n i f i c a n t problems f i r s t S a t u r n V S-IVB f l i g h t s t a g e , was i n s t a l l e d on Beta T e s t S t a n d a t SACTO by Douglas workmen f o l l o w i n g i t s a r r i v a l from t h e Huntington Beach assembly p l a n t March 1 5 . 29 - MTF c l o s e d t o t h r o u g h t r a f f i c t h e s e c t i o n of S t a t e Highway 43 which crossed the f a c i l i t y . A bypass had been completed. The c l o s i n g was i n p r e p a r a t i o n f o r r o c k e t s t a g e s t a t i c t e s t s a t MTF, s c h e d u l e d t o 30 begin s h o r t l y . - S-IVB-205 s t a g e c h e c k o u t ended a t Huntington Beach f o l l o w i n g c o m p l e t i o n of a s s e m b l y . - 31 I n t e g r a t i o n of e l e c t r i c a l s u p p o r t equipment and s t a g e e l e c t r i c a l s i m u l a t o r s was completed on t h e S a t u r n V SDF a t M S F C . ~ ~ �MARC11 23: C h r y s l e r t e s t p e r s o n n e l a t MSFC performed a s h o r t - d u r a t i o n f i r i n g o f 35 s e c o n d s on S-IB-5 s t a g e . A l l s t a g e s y s t e m s performed s a t i s f a c t o r i l y -33 - MSFC T e s t L a b o r a t o r y p e r s o n n e l c o n d u c t e d a f o u r - h o u r t e s t of t h e Saturn MARCH 24: IBIS-IVB APS module. A l l module s y s t e m s o p e r a t e d s a t i s f a c t o r i l y . 3 4 NASA announced t h e d e c i s i o n t o n e g o t i a t e i n c e n t i v e c o n t r a c t s t o t a l i n g $315 m i l l i o n w i t h Boeing and Rocketdyne f o r p r o c u r e m e n t of f i v e a d d i t i o n a l S-IC s t a g e s and 33 F - 1 e n g i n e s f o r t h e S a t u r n V v e h i c l e program. The Boeing c o n t r a c t was f o r $165 m i l l i o n ; t h e 35 Rocketdyne c o n t r a c t , $150 m i l l i o n . - A f l e e t o f n i n e NASA b a r g e s f o r t r a n s p o r t of c r y o g e n i c p r o p e l l a n t s (LOX and LH2) had been p l a c e d i n s e r v i c e on i n l a n d w a t e r w a y s between New O r l e a n s and MTF, a c c o r d i n g t o an announcement by A i r P r o d u c t s and C h e m i c a l s , I n c . (APCI). The d o u b l e w a l l t a n k s , t h r e e c a r r y i n g 2 5 0 , 0 0 0 g a l l o n s e a c h o f h y d r o g e n , and s i x o f 1 0 5 , 0 0 0 - g a l l o n oxygen c a p a c i t y , would p e r m i t pumping o f l i q u i d s d i r e c t l y i n t o r o c k e t 36 t a n k s a t MTF t e s t s t a n d s . MARCH 25: The S-11-F s e c o n d s t a g e of t h e S a t u r n V f a c i l i t i e s c h e c k o u t v e h i c l e was mated w i t h t h e S-IC-F i n t h e VAB a t KSC1s Launch Complex - D u r i n g t h e week p e r s o n n e l a t KSC1s LC-39 c o m p l e t e d i n s t a l l a t i o n o f S a t u r n V o p e r a t i o n a l d i s p l a y s i n Launch C o n t r o l C e n t e r F i r i n g Room 38 No. 1. MARCH 28-29: T e c h n i c i a n s a t KSC s t a c k e d t h e S-IVB-F a t o p t h e S-IC-F and S-11-F t o form t h e S a t u r n V f a c i l i t i e s c h e c k o u t v e h i c l e i n t h e 39 VAB . �MARCH 29: O f f i c i a l s a t KSC p r o v i s i o n a l l y a c c e p t e d t h e d i s c r e t e c o n t r o l systems f o r LC-39's F i r i n g Room No. 1 and Launch U m b i l i c a l Tower No. 1.40 MARCH 30: Douglas completed r e p a i r s on t h e S-IVB-503 LOX t a n k a t H u n t i n g t o n Beach and conducted f i n a l h y d r o s t a t i c t e s t i n g . Tank damage had o c c u r r e d d u r i n g a h y d r o s t a t i c t e s t i n F e b r u a r y 1966. 41 - S t a t i o n v e r i f i c a t i o n t e s t s b e g a n on t h e I n s t r u m e n t U n i t Checkout 42 Station a t I ~ M / ~ u n t s v i l l e . - F o l l o w i n g i n s t a l l a t i o n i n t o Beta 1 T e s t S t a n d a t SACTO March 21, t h e S-IVB-501 underwent c o m p l e t i o n of "hookup" t o t h e f a c i l i t y and 43 ground s u p p o r t equipment; power was t h e n a p p l i e d t o t h e s t a g e . - Douglas A i r c r a f t Company t u r n e d o v e r S-IVB-500ST, t h e MSFC S t a g e s i m u l a t o r f o r t h e S a t u r n V SDF, t o NASA a t C o u r t l a n d , C a l i f o r n i a , f o l l o w i n g c o m p l e t i o n of p o s t - m a n u f a c t u r i n g c h e c k o u t March 1 9 . 44 s i m u l a t o r was t h e n flown t o H u n t s v i l l e by t h e Super Guppy. - The KSC t e c h n i c i a n s mated t h e S-IU-500F t o t h e S-IVB-F on t h e S a t u r n V 45 f a c i l i t i e s c h e c k o u t v e h i c l e a t LC-39. MARCH 31: F i n a l assembly o p e r a t i o n s on t h e S-IC-5 t h r u s t s t r u c t u r e , i n t e r t a n k , and forward s k i r t were on s c h e d u l e a t MAF. 4 6 - C h r y s l e r p e r s o n n e l a t MSFC s t a t i c - f i r e d t h e S-IB-5 s t a g e f o r 2% 47 minutes. I N MARCH: MSFC p e r s o n n e l conducted f i v e s i n g l e F-1 e n g i n e f i r i n g s a t t h e West Area F-1 T e s t S t a n d . The t e s t s i n c l u d e d 40-second f i r i n g s on March 1 8 ( t w o ) , March 21, and March 22, and a t e s t l a s t i n g 9 6 . 8 3 s e c o n d s on March 29. 4 8 �I N MARCH: T e c h n i c i a n s began i n s t a l l i n g v e r t i c a l f i n s , f a i r i n g s , and r e t r o r o c k e t s on t h e S-IC-D dynamic t e s t s t a g e i n t h e MSFC S a t u r n V Dynamic T e s t S t a n d . 49 - . T e c h n i c i a n s a t MSFC completed s t r u c t u r a l t e s t s s t a r t e d i n F e b r u a r y on t h e S-IC-S f u e l t a n k l t h r u s t s t r u c t u r e i n t e r t a n k a s s e m b l y . down o f t h i s t e s t s e t u p was i n p r o g r e s s a t t h e end o f March. - Tear- 50 MSFC c o n t r a c t o r s s t a r t e d c o n s t r u c t i o n and s i t e work f o r c o n v e r t i n g t h e MSFC S-IC S t a t i c T e s t S t a n d t o s u p p o r t t h e S-11-1 s t a g e . MSFC a u t h o r i z e d NAA t o proceed w i t h l o g i s t i c s e f f o r t f o r s t a n d c o n v e r s i o n . L a t e r i n t h e month NASA H e a d q u a r t e r s d i s a p p r o v e d t h e MSFC p r o p o s a l 51 f o r c o n v e r s i o n of t h e s t a n d , and m o d i f i c a t i o n work s t o p p e d . �A P R I L APRIL 1: 1 9 6 6 NASA announced t r a n s f e r o f t h e RLlO hydrogen e n g i n e p r o j e c t from MSFC t o Lewis R e s e a r c h C e n t e r , C l e v e l a n d , Ohio. The RLlO e n g i n e was used t o power t h e second s t a g e of t h e S a t u r n I v e h i c l e and was t h e p r i m a r y p r o p u l s i o n s y s t e m a l s o f o r t h e C e n t a u r s p a c e vehicle. 1 - C h r y s l e r p e r s o n n e l conducted a f u l l - d u r a t i o n 2%-minute f i r i n g of S-IB-5 s t a g e a t H u n t s v i l l e . 2 - MSFC r e c e i v e d a t H u n t s v i l l e t h e S-IVB-500ST s t a g e s i m u l a t o r , t r a n s p o r t e d i t t o t h e S a t u r n V SDF, and began t o p r e p a r e i t f o r e r e c t i o n i n the f a c i l i t y . 3 APRIL 3: S&ID workmen a t S e a l Beach completed assembly of t h e s p e c i a l S - I 1 High F o r c e T h r u s t Complex f o r u s e i n a t e s t i n g program a t Wyle 4 Laboratories, Huntsville. APRIL 4: Douglas p e r s o n n e l s h i p p e d S-IVB-203 t o KSC v i a t h e Super Guppy 5 aircraft . - NASA announced a change i n t h e sequence of t h e n e x t two A p o l l o / S a t u r n I B launches: AS-203 would f l y b e f o r e AS-202, and b o t h l a u n c h e s w e r e s c h e d u l e d f o r t h e t h i r d q u a r t e r of 1966. 6 APRIL 5: Two c r y o g e n i c t a n k b a r g e s a r r i v e d a t MTF c a r r y i n g 196,000 g a l l o n s of LOX f o r t h e upcoming s t a t i c f i r i n g of t h e S-11-T/D 7 stage . - MSFC announced award of c o s t - p l u s - i n c e n t i v e - f e e contracts totaling more t h a n $61 m i l l i o n t o n i n e f i r m s f o r e n g i n e e r i n g , f a b r i c a t i o n , �and i n s t i t u t i o n a l s u p p o r t s e r v i c e s i n t h e S a t u r n l a u n c h v e h i c l e program. R e c e i v i n g one-year r e n e w a l s under o p t i o n s of c o n t r a c t s o r i g i n a l l y awarded i n 1965 were: S p e r r y Rand C o r p o r a t i o n , V i t r o C o r p o r a t i o n , Brown E n g i n e e r i n g Company, Spaco, I n c . , Northrop C o r p o r a t i o n , Hayes I n t e r n a t i o n a l C o r p o r a t i o n , Management S e r v i c e s , Inc., APRIL 5: R u s t E n g i n e e r i n g Company, and RCA S e r v i c e Company. 8 Douglas p e r s o n n e l moved S-IVB-208 s t a g e i n t o t h e i n s u l a t i o n chamber a t Huntington Beach f o r i n s t a l l a t i o n of i n s u l a t i o n . 9 APRIL 6: NASA and Rocketdyne s i g n e d a $7.6 m i l l i o n c o n t r a c t m o d i f i c a t i o n c o v e r i n g procurement o f 22 a d d i t i o n a l H - 1 e n g i n e s f o r t h e S a t u r n I B v e h i c l e program p l u s t h r e e y e a r s of s u p p o r t s e r v i c e s . 1 0 - The Super Guppy a i r c r a f t d e l i v e r e d t h e S-IVB-203 s t a g e from SACTO t o KSC a f t e r a d e l a y e n r o u t e . 11 APRIL 7: - The S-IB-3 s t a g e l e f t MAF by b a r g e f o r KSC. 1 2 A f t e r c o m p l e t i o n of S-IVB-503 h y d r o s t a t i c t e s t i n g i n l a t e March, Douglas moved t h e s t a g e t a n k assembly t o t h e i n s u l a t i o n chamber. - 13 North American A v i a t i o n d e l i v e r e d S-IU-500V-I1 s t r u c t u r e t o Wyle L a b o r a t o r i e s a t H u n t s v i l l e a f t e r c o m p l e t i n g component assembly 14 t h e p r e v i o u s day. V i b r a t i o n t e s t i n g was s c h e d u l e d a t Wyle. APRIL 8: workmen a t S&ID'S S e a l Beach assembly p l a n t completed v e r t i c a l b u i l d u p of t h e S-11-2 f l i g h t s t a g e . 15 APRIL 9-13: Douglas p e r s o n n e l t r a n s p o r t e d t h e S-IVB-205 s t a g e from 16 H u n t i n g t o n Beach t o SACTO by way of t h e NASA b a r g e O r i o n . �APRIL 13: P e r s o n n e l a t t h e MSFC Load T e s t Annex removed t h e S-IC-S f u e l t a n k from t h e f a c i l i t y f o l l o w i n g teardown of t h e f u e l t a n k l t h r u s t s t r u c t u r e l i n t e r t a n k s e t u p . 17 APRIL 14: Workmen completed r e i n s t a l l a t i o n on S-IC-2 s t a g e of a l l f i v e F-1 e n g i n e s which had been removed f o r c l e a n i n g because o f contam18 i n a t i o n of t h e e n g i n e s by h y d r a u l i c f l u i d . - H y d r o s t a t i c t e s t of t h e LOX and LH2 t a n k of S-11-2 ended a t S e a l ~ e a c h . l ~ A f t e r u p d a t i n g S-IU-500ST t o f u n c t i o n a l c o n f i g u r a t i o n , MSFC MID-APRIL: p e r s o n n e l p o s i t i o n e d t h e I U a t o p t h e S-IVB forward s e c t i o n i n t h e 20 S a t u r n V SDF and s t a r t e d s y s tern t e s t s . APRIL 1 7 : Workmen a t MTF completed t h e LH2 t a n k i n g t e s t on t h e S-11-T/D . s t a g e 21 APRIL 18: S&ID completed systems i n s t a l l a t i o n on S-11-1 s t a g e a t 22 S e a l Beach. APRIL 19-21: Nine a s t r o n a u t s v i s i t e d MSFC f o r b r i e f i n g on t h e S a t u r n I B launch v e h i c l e . A t t e n d i n g were V i r g i l I . Grissom, James A. M c D i v i t t , David R . S c o t t , R u s s e l l S c h w e i k a r t , Edward H. White 11, Frank Borman, 23 W a l t e r M. S c h i r r a , J r . , Roger C h a f f e e , and W a l t e r Cunningham. APRIL 20: S&ID t r a n s f e r r e d S-11-1 s t a g e r e s p o n s i b i l i t y from m a n u f a c t u r i n g t o t e s t o p e r a t i o n s a t S e a l Beach, p a v i n g t h e way f o r a u t o m a t i c s t a g e systems checkout i n i t i a t i o n . 2 1 APRIL 21: NASA s i g n e d c o n t r a c t s t h i s week w i t h Douglas, McDonnell A i r c r a f t C o r p o r a t i o n , and Grumman A i r c r a f t E n g i n e e r i n g C o r p o r a t i o n c o v e r i n g d e f i n i t i o n s t u d i e s of t h e S-IVB s p e n t s t a g e e x p e r i m e n t s u p p o r t �module (SSESM). Each of t h e t h r e e 60-day A p o l l o A p p l i c a t i o n s con25 t r a c t s was v a l u e d a t $50,000. S t a t i c f i r i n g of t h e S-11-T/D a l l - s y s t e m s t e s t s t a g e o c c u r r e d a t APRIL 23: MTF. T h i s 15-second t e s t marked t h e f i r s t o p e r a t i o n a l u s e of t h e t e s t s t a n d and t h e f i r s t time a f l i g h t - w e i g h t S - I 1 s t a g e had been fired. APRIL 25: Almost a l l t e s t o b j e c t i v e s were a c h i e v e d . 2 6 S&ID d e l i v e r e d t h e S - I 1 High-Force T h r u s t Complex t o H u n t s v i l l e f o r t e s t i n g a t Wyle L a b o r a t o r i e s . 2 7 - Douglas completed t h e S-IVB-204 s t a g e s i m u l a t e d f l i g h t t e s t a t SACTO. 2 8 - S&ID t e c h n i c i a n s a t S e a l Beach began t h e v e r t i c a l b u i l d u p of S-11-3 29 f o l l o w i n g c o m p l e t i o n of t h e common bulkhead on A p r i l 1 8 . - MSFC ME Lab d e l i v e r e d t o Q u a l i t y Lab t h e S-IC-2 s t a g e f o r post-manu30 f a c t u r i n g checkout. APRIL 28: The t h i r d 200-second s t a t i c f i r i n g d u r i n g A p r i l of t h e S-IVB b a t t l e s h i p o c c u r r e d a t MSFC. stage. APRIL 29: T h i s was t h e 2 1 s t f i r i n g t e s t of t h i s The o t h e r A p r i l t e s t s were on A p r i l 7 and A p r i l 1 3 . 31 A t e s t a c c i d e n t a t MSFCseverely buckled t h e f u e l t a n k upper b u l k h e a d i n t e n d e d f o r t h e S-IC-5 s t a g e . Officials considered the 32 b u l k h e a d n o t r e p a i r a b l e and o r d e r e d t h a t i t be r e p l a c e d . I N APRIL: MSFC p e r s o n n e l completed t h e S-IVB s t a g e APS development 33 firing tests . - F-1 e n g i n e t e s t s i n MSFC's West Area o c c u r r e d f o u r t i m e s . 41.9-second t e s t on A p r i l 7 , a 64.7-second There was a f i r i n g A p r i l 1 9 , a 40.6- second t e s t A p r i l 7 , and a 145.5-second f i r i n g A p r i l 2 8 . 34 �I N APRIL: S-IVB-502 s t a g e c h e c k o u t c o n t i n u e d toward c o m p l e t i o n a t t h e H u n t i n g t o n Beach V e r t i c a l Checkout L a b o r a t o r y . hampered c h e c k o u t a c t i v i t i e s . 35 Parts shortages �M A Y MAY 2: 1 9 6 6 V i b r a t i o n t e s t i n g of S-IU-200V-11, which began on A p r i l 2 5 , e n d e d a t Wyle L a b o r a t o r i e s , H u n t s v i l l e . 1 MAY 2-6: MSFC p e r s o n n e l a t H u n t s v i l l e f i r e d t h e S-IVB B a t t l e s h i p t h r e e times. On May 2 t h e s t a g e f i r e d f o r 1 5 1 s e c o n d s ; t h e t e s t May 4 l a s t e d 200 s e c o n d s ; and t h e May 6 f i r i n g was f o r 323 s e c o n d s . L MAY 3: Douglas p e r s o n n e l r e p e a t e d t h e s i m u l a t e d f l i g h t t e s t o f S-IVB-204 s t a g e and p l a c e d t h e s t a g e i n s t o r a g e a t SACTO u n t i l n e e d e d . 3 MAY 4: NASA announced s e l e c t i o n of ARINC R e s e a r c h C o r p o r a t i o n and ITT/ Federal E l e c t r i c Corporation f o r competitive n e g o t i a t i o n s leading t o a $1.7 m i l l i o n , one-year c o n t r a c t t o provide t e c h n i c a l s u p p o r t f o r t h e S a t u r n l a u n c h v e h i c l e r e l i a b i l i t y program a t MSFC. 4 MAY 4-5: MSFC T e s t L a b o r a t o r y c o n d u c t e d two f i r i n g s of a n F-1 e n g i n e i n t h e W e s ~T e s t A r e a . The May 4 t e s t l a s t e d 1 5 1 . 7 s e c o n d s ; t h e May 5 f i r i n g was f o r 1 5 0 s e c o n d s . MAY 5 : Both t e s t s w e r e s a t i s f a c t o r y . 5 A s m a l l hydrogen-oxygen b u r n i n g e n g i n e o r i g i n a l l y d e v e l o p e d f o r t h e S a t u r n 1 ' s S-IV second s t a g e was b e i n g a d a p t e d f o r u s e i n t h e S a t u r n V ' s S-IVB t h i r d s t a g e , MSFC announced. The s m a l l e n g i n e was b e i n g m o d i f i e d by Douglas a t H u n t i n g t o n Beach t o s e r v e a s a h e a t e r f o r e x p a n d i n g t h e h e l i u m g a s u s e d i n r e p r e s s u r i z i n g t h e S-IVB p r o p e l l a n t tanks i n space. I t s u s e was t o p r o v i d e a n 800-pound p a y l o a d g a i n through weight r e d u c t i o n . 6 a hydrogen-oxygen b u r n e r . MAY 6: The t w o - f o o t - h i g h e n g i n e was c a l l e d MSFC announced s e l e c t i o n o f Computer S c i e n c e s C o r p o r a t i o n and G e n e r a l E l e c t r i c Company's Computer D i v i s i o n f o r c o m p e t i t i v e �n e g o t i a t i o n s l e a d i n g t o a o n e - y e a r , $6 m i l l i o n c o n t r a c t t o p r o v i d e s u p p o r t s e r v i c e s t o t h e Computation L a b o r a t o r y . ' MSFC r e c e i v e d i t s f i r s t u p r a t e d 5-2 r o c k e t e n g i n e f o r s t a t i c MAY 6: firing. Rocketdyne had i n c r e a s e d t h e e n g i n e ' s maximum t h r u s t t o 230,000 pounds f o r u s e i n S a t u r n I B and S a t u r n V upper s t a g e s . 8 - Wyle L a b o r a t o r i e s r e t u r n e d S-IU-500V-I1 o f a v i b r a t i o n t e s t program. 9 - MSFC p r e s e n t e d t o t h e S m i t h s o n i a n I n s t i t u t i o n ' s N a t i o n a l A i r and Space t o MSFC a f t e r c o m p l e t i o n o f Museum two r o c k e t e n g i n e s , a n RLlO and an 11-1. p l a y e d key r o l e s i n t h e U.S. 10 t h e museum. MAY 9 : These e n g i n e s which s p a c e program would be d i s p l a y e d a t I n t e g r a t e d systems c h e c k o u t o f S-IVB-501 ended a t SACTO's Beta 1 T e s t S t a n d i n p r e p a r a t i o n f o r a c c e p t a n c e f i r i n g t e s t s o f t h e s t a g e .ll - S-IVB-502 s t a g e c h e c k o u t ended a t H u n t i n g t o n ~ e a c h . l ~ MAY 10: ME Lab p e r s o n n e l a t MSFC completed work on f u l l - s c a l e Lunar 13 Module mockups. MAY 11: A s t a t i c f i r i n g of S-11-T/D a t MTF ended a t a p p r o x i m a t e l y 46 s e c o n d s b e c a u s e of a f a u l t y i n d i c a t i o n of o v e r - t e m p e r a t u r e i n one e n g i n e Is g a s g e n e r a t o r . l4 MAY 12: ME Lab p e r s o n n e l a t MSFC completed p o s t - f i r i n g r e f u r b i s h m e n t o f S-IC-1 and moved t h e s t a g e t o Q u a l i t y Lab f o r p o s t - s t a t i c c h e c k o u t . 15 - . S -1C-2 completed pos t-manufac t u r i n g c h e c k o u t a t MSFC l6 �MAY 12: A f t e r S-IVB-207 s t a g e j o i n i n g o p e r a t i o n s and i n s t a l l a t i o n s which ended May 1 0 , workmen began f a c t o r y c h e c k o u t of t h e s t a g e a t Huntingt o n Beach ." MAY 13: I n i t i a l a p p l i c a t i o n o f power t o t h e SA-500F f a c i l i t y c h e c k o u t v e h i c l e i n t h e VAB a t KSC o c c u r r e d a s s c h e d u l e d . 1a MAY 15: P o s t - m a n u f a c t u r i n g c h e c k o u t of S-IC-3 was i n t e r r u p t e d a t MAF when a b o u t 50 p e r c e n t c o m p l e t e t o accommodate a planned p e r i o d o f s t a g e m o d i f i c a t i o n . 19 MAY 17: MSFC t e c h n i c i a n s moved S-IC-2 s t a g e t o t h e s t a t i c t e s t s t a n d and 20 placed it i n p o s i t i o n a t Huntsville. - S&ID p e r s o n n e l s u c c e s s f u l l y t e s t - f i r e d t h e S-11-T/D MTF. f o r 150 seconds a t A p r e v i o u s f i r i n g a t t e m p t on May 16 t e r m i n a t e d a f t e r n i n e seconds because of f a u l t y instrumentation. Today's f i r i n g came on t h e t h i r d 21 a n n i v e r s a r y o f ground b r e a k i n g f o r t h e t e s t f a c i l i t y . MAY 18: The 2 7 t h f i r i n g t e s t o f t h e MSFC S-IVB b a t t l e s h i p s t a g e was p e r - formed f o r 11 s e c o n d s . Four p r e v i o u s t e s t s o c c u r r e d d u r i n g May - for 151 s e c o n d s on May 2 , 200 s e c o n d s May 4 , 3 2 3 seconds May 6 , and a n 22 i g n i t i o n t e s t on May 1 6 . MAY 20: MSFC d i r e c t e d S&ID t o c a n c e l t h e s c h e d u l e d m o d i f i c a t i o n of t h e a l l - s y s t e m s / d y n a m i c t e s t s t a g e , S-11-T/D. 23 t h e S-11-T s t a g e . - The s t a g e was r e d e s i g n a t e d The f i r s t f u l l - d u r a t i o n s t a t i c f i r i n g o f S-11-T o c c u r r e d a t MTF. time was 354-.5 s e c o n d s . were a c c o m p l i s h e d . 24 Firing A 1 1 b u t one o f t h e major t e s t o b j e c t i v e s �MAY 20: The f i r s t a t t e m p t a t a c c e p t a n c e f i r i n g o f S-IVB-501 r e s u l t e d i n 25 an a u t o m a t i c c u t o f f a f t e r 50 seconds. MAY 22: The M o b i l e Equipment M a i n t e n a n c e B u i l d i n g a t MTF was c o m p l e t e d 26 and t u r n e d o v e r t o t h e government. 27 MAY 24: Douglas c o m p l e t e d S-IVB-206 s t a g e c h e c k o u t a t H u n t i n g t o n Beach. MAY 25: The SA-500F, S a t u r n V f a c i l i t i e s c h e c k o u t v e h i c l e , r o l l e d o u t of t h e VAB a t KSC's LC-39 f o l l o w i n g c o m p l e t i o n of s y s t e m s t e s t t h e C r a w l e r - T r a n s p o r t e r No. 1 t r a n s p o r t e d t h e v e h i c l e t o 28 T r a n s i t took most of t h e day. previous day. Pad A . - T e c h n i c i a n s a t MTF a t t e m p t e d t h e s e c o n d f u l l - d u r a t i o n f i r i n g o f S-11-T/D. The t e s t ended a f t e r 198 s e c o n d s a s a r e s u l t o f a f i r e on e n g i n e number 5 . 2 9 MAY 25-27: Twenty a s t r o n a u t s t o u r e d MSFC l a b o r a t o r i e s and t e s t f a c i l i t i e s 30 and r e c e i v e d b r i e f i n g s on S a t u r n I B and S a t u r n V l a u n c h v e h i c l e s . MAY 26: The s e c o n d a t t e m p t a t a c c e p t a n c e f i r i n g t h e S-IVB-501 s t a g e was s u c c e s s f u l a t SACTO. The t e s t c o n s i s t e d of a 151-second m a i n s t a g e f i r s t b u r n , a 1 0 6 - m i n u t e s i m u l a t e d o r b i t a l c o a s t p e r i o d , and a 301-second m a i n s t a g e b u r n a f t e r r e s t a r t . 31 accomplished. A l l t e s t o b j e c t i v e s were MAY 26-27: P e r s o n n e l a t t h e S-IC S t a t i c T e s t S t a n d a t MSFC c o n d u c t e d 32 p r o p e l l a n t l o a d t e s t s on S - I C - 2 . MAY 27: NASA announced s e l e c t i o n of two a e r o s p a c e companies f o r n e g o t i a - t i o n of p a r a l l e l one-year study c o n t r a c t s covering i n t e g r a t i o n o f e x p e r i m e n t s and e x p e r i m e n t s s u p p o r t e q u i p m e n t f o r manned �Apollo Applications. Each c o n t r a c t was e s t i m a t e d a t $1 m i l l i o n . The two f i r m s s e l e c t e d were Lockheed M i s s i l e s and Space Company and 33 Mar t i n Company. MAY 28: A t e s t a c c i d e n t a t MTF d e s t r o y e d t h e S-11-T/D s t a g e . LH2 t a n k r u p t u r e d when o v e r - p r e s s u r i z e d . The empty A s e c o n d - s h i f t crew a t t e m p t e d t o p r e s s u r i z e t h e t a n k w i t h g a s e o u s h e l i u m , n o t knowing t h a t a p r e v i o u s work crew had d i s c o n n e c t e d t h e t a n k ' s p r e s s u r e s e n s o r s and s w i t c h e s . - 34 NASA a l l o c a t e d t h e S-11-F t o t h e S a t u r n V dynamic t e s t v e h i c l e program t o r e p l a c e t h e S-11-T/D. The S-11-F would be m o d i f i e d f o r dynamic t e s t i n g a f t e r f u l f i l l i n g i t s m i s s i o n i n t h e SA-500F v e h i c l e a t KSC. 3 5 - The c o n t r a c t o r , Thornton and Hyde C o r p o r a t i o n , t u r n e d o v e r t o MTF t h e c o m p l e t e d r o a d s and p a r k i n g a r e a s of t h e f a c i l i t y . 36 MAY 29: D r . von Braun a p p o i n t e d a board of i n v e s t i g a t i o n f o r t h e May 28 t e s t a c c i d e n t t h a t d e s t r o y e d t h e S-11-T/D s t a g e . 3 7 MAY 30: S-IU-501, the instrument u n i t f o r the f i r s t f l i g h t Saturn V, e n t e r e d t h e c h e c k o u t s t a t i o n a t IBM's H u n t s v i l l e f a c i l i t y . 3 8 MAY 31: P e r s o n n e l a t MSFC's S t a t i c T e s t S t a n d E a s t i n s t a l l e d S-IB-6 i n t h e tower f o r f i r i n g . 39 I N MAY: MSFC performed f i v e s i n g l e F-1 e n g i n e f i r i n g s a t t h e West Area F-1 T e s t S t a n d . F i r i n g d u r a t i o n s ranged from 52 t o 1 5 0 s e c o n d s . The t e s t s o c c u r r e d May 9 ( t w o ) , May 11, and May 1 8 ( t w o f i r i n g s ) . 4 0 - S&ID p e r s o n n e l a t MTF s t a t i c - f i r e d t h e S-11-T s e v e n t i m e s d u r i n g t h e month. Only two f i r i n g s a c h i e v e d planned d u r a t i o n s . 4 1 �S-IVB p r o j e c t o f f i c i a l s d i r e c t e d t h a t t h e S-IVB-503 t a n k assembly be used a s t h e h y d r o s t a t i c t e s t program u n i t and t h a t S-IVB-504 t a n k 42 a g e be a s s i g n e d t o S-IVB-503. S-IVB-501 APS modules 1 and 2 were checked o u t and c o n f i d e n c e - f i r e d a t SACTO. T e c h n i c i a n s f i r e d module 1 May 6 and module 2 May 1 3 . 4 3 MSFC approved Change Order 425 t o e x t e n d t h e S - I 1 B a t t l e s h i p L e s t program on a r e d u c e d l e v e l of e f f o r t t h r o u g h J u l y 31, 1967. This e x t e n s i o n would p e r m i t p e r s o n n e l t o g a i n more e x p e r i e n c e and conf i d e n c e i n t h e MTF A-2 T e s t S t a n d . 44 �J U N E JUN1: - 1 9 6 6 2: D o u g l a s s h i p p e d t h e S-IVB-502 s t a g e t o SACTO f o r a c c e p t a n c e f i r i n g v i a t h e S u p e r Guppy a i r c r a f t . 1 S-IVB-205 s t a g e a c c e p t a n c e f i r i n g was s u c c e s s f u l l y a c c o m p l i s h e d a t 2 SACTO. M a i n s t a g e d u r a t i o n was 4 3 7 . 5 s e c o n d s . JUNE 3: S-IVR-501 was removed from t h e B e t a 1 T e s t S t a n d a t SACTO f o l - lowing completion of a c c e p t a n c e t e s t i n g . D o u g l a s p e r s o n n e l moved t h e s t a g e t o t h e V e r t i c a l Checkout L a b o r a t o r y f o r p o s t - s t a t i c checko u t a n d m o d i f i c a t i o n b e f o r e s h i p m e n t t o KSC.' JUNE 6: P o s t - m a n u f a c t u r i n g c h e c k o u t o f S-IC-3 resumed a t MAF f o l l o w i n g i n c o r p o r a t i o n o f 21 change o r d e r s . - d 4 The f i n a l t e s t o f S - I C s t r u c t u r a l t e s t f i n s a n d e n g i n e f a i r i n g s a t MSFC was a c c o m p l i s h e d . 5 J U N E 7: B e l l A e r o s y s t e m s Company c o m p l e t e d a Manned F l y i n g S y s t e m s ( p o g o s t i c k ) s t u d y m o n i t o r e d by MSFC. 6 - Boeing p e r s o n n e l a c c o m p l i s h e d a s u c c e s s f u l f i r s t f i r i n g o f S-IC-2 a t MSFC. JUNE 8: The t e s t l a s t e d 1 2 6 . 3 s e c o n d s . The S-IU-502 s t r u c t u r e , r e a l l o c a t e d S-IU-200/500S-111, a t MSFC t o r e p l a c e t h e S-IU-203/509S-11, 8 l i m i t load t e s t i n g . - / arrived w h i c h had f a i l e d d u r i n g SA-500F p r o c e s s i n g a n d t e s t a c t i v i t i e s a t LC-39, Pad A , w e r e i n t e r r u p t e d b e c a u s e o f t h e a p p r o a c h o f H u r r i c a n e Alma. KSC p e r s o n n e l moved t h e v e h i c l e b a c k i n t o t h e VAB a s a p r e c a u t i o n . 9 �JUNE 9: Changes i n A p o l l o program n o m e n c l a t u r e were announced by NASA Headquarters. Lunar E x c u r s i o n Module would be known a s Lunar Module; S a t u r n I B v e h i c l e a s u p r a t e d S a t u r n I; and S a t u r n V s t a g e s ( S - I C , S - I 1 and S-IVB) a s f i r s t , s e c o n d , and t h i r d s t a g e s . The " c o n f u s i n g " former d e s i g n a t i o n s would be dropped g r a d u a l l y , e x c e p t i n NASA's i n t e r n a l a z d t e c h n i c a l documents t i o n . l o JUNE 10: With t h e h u r r i c a n e t h r e a t p a s t , p e r s o n n e l a t KSC a g a i n moved SA-500F from t h e VAB t o Pad A a t LC-39. e i g h t h o u r s . 11 - The move r e q u i r e d a b o u t Two i g n i t i o n t e s t s , t h e 2 8 t h and 2 9 t h f i r i n g s o f t h e MSFC S-IVB b a t t l e s h i p , o c c u r r e d a t H u n t s v i l l e . 12 JUNE 16: T e s t p e r s o n n e l a t MSFC removed S-IC-2 from t h e S t a t i c T e s t S t a n d a £ t e r one f i r i n g and moved i t t o ME Lab f o r r e f u r b i s h m e n t . 1 3 - P e r s o n n e l a t M S F C 1 s S t a t i c T e s t S t a n d E a s t performed a p r o p e l l a n t l o a d i n g t e s t on t h e S-IB-6 s t a g e i n p r e p a r a t i o n f o r s t a t i c t e s t . 1 4 JUNE 17: MSFC awarded t o Lockheed M i s s i l e s and Space Company a $30,000 c o n t r a c t c o v e r i n g a Lunar G r a v i t y S i m u l a t o r s t u d y , s c h e d u l e d f o r c o m p l e t i o n November 1 4 , 1966 .I5 JUNE 20: P e r s o n n e l a t S e a l Beach completed i n s t a l l a t i o n o f t h e f i v e 5-2 e n g i n e s on S-11-2 f l i g h t s t a g e . 1 6 - I B M p e r s o n n e l a t t h e H u n t s v i l l e f a c i l i t y completed f a b r i c a t i o n o f S-IU-502. 17 JUNE 22: A f a b r i c a t i o n a c c i d e n t a t S e a l Beach damaged one of t h e b u l k - head g o r e s o f s-11-5 stage. Program o f f i c i a l s d e c i d e d t o c u t o u t and r e p l a c e t h e damaged g o r e . 1 8 �JURE 22: I B M began assembly of S-IU-502, 19 second S a t u r n V v e h i c l e . - the instrument u n i t f o r the MSFC o f f i c i a l s met t o d i s c u s s i d e n t i f i c a t i o n o f some SA-5 o r b i t a l f r a g m e n t s which s u r v i v e d r e e n t r y and l a n d e d i n B r a z i l A p r i l 2 8 , 1966. The p i e c e s , found on May 6 , 1966, w e r e h a n d - c a r r i e d t o MSFC by a NASA H e a d q u a r t e r s r e p r e s e n t a t i v e . 20 MSFC f o r s t u d y and e x h i b i t i o n . The f r a g m e n t s were t o remain a t JUNE 23: C h r y s l e r t e s t p e r s o n n e l a t MSFC s t a t i c - f i r e d S-IB-6 s t a g e f o r 31 a s c h e d u l e d d u r a t i o n o f 35 s e c o n d s . JUNE 24: NASA announced s e l e c t i o n of Computer S c i e n c e s C o r p o r a t i o n t o p r o v i d e s u p p o r t s e r v i c e s f o r MSFC's Computation L a b o r a t o r y . Estimated c o s t of t h e c o n t r a c t f o r t h e f i r s t y e a r was $5.5 m i l l i o n . 2 2 - NASA announced s e l e c t i o n o f Univac D i v i s i o n o f S p e r r y Rand t o p r o v i d e a new ( t h i r d g e n e r a t i o n ) computing s y s t e m a t MSFC. The c o n t r a c t was v a l u e d a t $30 m i l l i o n and e x t e n d e d o v e r a 5 - y e a r p e r i o d . Univac would f u r n i s h a l m o s t c o m p l e t e r e p l a c e m e n t o f t h e C e n t e r ' s computer complex equipment. 2 3 - S&ID p e r s o n n e l completed S-11-1 s t a g e c h e c k o u t o p e r a t i o n s a t S e a l Beach. 2 4 - T e s t p e r s o n n e l a t MSFC completed t h e i n i t i a l p h a s e of S-IC-D v e h i c l e s i t e i n t e g r a t i o n t e s t i n g .25 JUNE 27: NASA announced c o n v e r s i o n of i t s Douglas S-IVB s t a g e prime c o n t r a c t from f i x e d - f e e t o i n c e n t i v e - f e e . c o n t r a c t was $700 m i l l i o n . Estimated c o s t of t h e Under t h e c o n t r a c t , Douglas p r o v i d e d t h e t o p s t a g e s f o r b o t h Uprated S a t u r n I and S a t u r n V l a u n c h v e h i c l e s . 26 �JUNE 27: Boeing t e c h n i c i a n s a t MAF completed i n s t a l l a t i o n of F-1 e n g i n e s on S-IC-4, - the booster stage for the fourth Saturn V f l i g h t vehicle. 27 MSFC a c c e p t e d b e n e f i c i a l occupancy of MTF's S-IC T e s t S t a n d B-2 28 machine s h o p . JUNE 29: S-IB-6, t h e b o o s t e r f o r t h e s i x t h Uprated S a t u r n I f l i g h t v e h i c l e , f i r e d f o r f u l l d u r a t i o n of 145 seconds a t MSFC. 29 t h e f i n a l s t a t i c t e s t of t h e s t a g e . - P e r s o n n e l a t S a n t a Susana s u c c e s s f u l l y t e s t - f i r e d t h e S - I 1 B a t t l e s h i p f o r 382 s e c o n d s . JUNE 30: - I t was A l l t e s t o b j e c t i v e s were accomplished .30 The S-IVB-206 s t a g e a r r i v e d a t SACTO from t h e assembly p l a n t . 3 1 MSFC t e s t p e r s o n n e l i n s t a l l e d a S a t u r n V/S-IVB APS module i n t h e vacuum chamber f o r h o t - f i r i n g t e s t s s c h e d u l e d i n J u l y . 32 - T e s t i n g of t h e S-IU-500FS j o i n e d t o an S-IVB s t a g e a t Huntington Beach, which began June 1, was s u c c e s s f u l l y completed. 3 3 - Workmen had a l m o s t completed r e p a i r s and r e f u r b i s h m e n t of t h e A-2 T e s t S t a n d a t MTF f o l l o w i n g d e s t r u c t i o n of t h e S-11-T s t a g e i n a t e s t May 2 8 . M o d i f i c a t i o n of s t a n d GSE t o t h e S-11-1 c o n f i g u r a t i o n was 5 0 p e r c e n t c o m p l e t e . 34 - SLID i s s u e d a l e t t e r c o n t r a c t t o Thiokol Chemical C o r p o r a t i o n c o v e r i n g a backup u l l a g e motor f o r t h e S - I 1 s t a g e . C o s t of t h e back- up program was e x p e c t e d t o be l e s s t h a n $500,000. S&ID would choose l a t e r between t h e Rocketdyne and t h e Thiokol u l l a g e m o t o r s . 35 �J U N E 30: IBM completed a c t i v a t i o n of t h e S a t u r n V I U Checkout S t a t i o n 36 a t t h e H u n t s v i l l e f a c i l i t y and began t e s t i n g of t h e S-IU-501. S t r u c t u r a l f a b r i c a t i o n of t h e t h i r d S a t u r n V f l i g h t i n s t r u m e n t 37 u n i t , S-IU-503, began a t IBM's H u n t s v i l l e p l a n t . I N JUNE: - P e r s o n n e l d i s c o v e r e d s t r e s s c r a c k s i n t h e m a n i f o l d weld j o i n t s of the f i r s t Saturn V f l i g h t instrument u n i t . a t H u n t s v i l l e c o n t i n u e d . 38 S-IU-501, - Systems t e s t s E n v i r o n m e n t a l t e s t i n g of t h e S-IVB-500FS ( f l i g h t systems t e s t a r t i c l e ) w i t h a n i n s t r u m e n t u n i t began a t t h e I B M Space Systems C e n t e r Simu39 l a t i o n L a b o r a t o r y , H u n t s v i l l e . Four t e s t s were completed. - MSFC t e s t p e r s o n n e l conducted 1 0 F-1 e n g i n e f i r i n g t e s t s t o e v a l u a t e Engine No. F-5038, a q u a l i f i c a t i o n c o n f i g u r a t i o n e n g i n e . o c c u r r e d between J u n e 20 and J u n e 30. 40 seconds each i n d u r a t i o n . Firings S i x t e s t s exceeded 150 �J U L Y JULY 1: 1 9 6 6 P e r s o n n e l a t SACTO completed t h e f i r s t s u c c e s s f u l 4%-hour burn o f t h e S-IVB s t a g e LO~/Hydrogen b u r n e r . 1 t o p e r form t h e t e s t . - T h i s was t h e t h i r d a t t e m p t MSFC c o n t r a c t e d w i t h A e r o j e t - G e n e r a l f o r e x p a n s i o n and e x t e n s i o n of a s t u d y e n t i t l e d "Demonstration of a S o l i d P r o p e l l a n t Motor M a l f u n c t i o n D e t e c t i o n and Combustion System.'' E s t i m a t e d c o s t o f t h e 9-month s t u d y was $214,000. 2 - MSFC awarded a c o n t r a c t t o Lockheed f o r c o n t i n u a t i o n of t h e i n v e s t i g a t i o n and s p e c i f i c a t i o n of n u c l e a r s a f e t y s y s t e m s . E s t i m a t e d c o s t was $103,700 f o r a performance p e r i o d o f s i x months. 3 - MSFC awarded a $182,300 c o n t r a c t t o G e n e r a l E l e c t r i c f o r a m i s s i o n e n g i n e e r i n g s t u d y of e l e c t r i c a l l y p r o p e l l e d manned p l a n e t a r y v e h i c l e s . P e r i o d o f performance was 1 0 months. 4 - S&ID workmen a t S e a l Beach completed t h e S-11-2 s t a g e m e c h a n i c a l and bracket installations f o r the thrust structure. JULY 2: 5 S&ID workmen a t S e a l Beach completed f i n a l p a i n t i n g and marking o f t h e S-11-1 f l i g h t s t a g e . 6 JULY 5 : A p o l l o / S a t u r n v e h i c l e AS-203, t h e second Uprated S a t u r n I f l i g h t v e h i c l e , was s u c c e s s f u l l y launched from Launch Complex 37 a t Cape Kennedy. It was t h e f i r s t e a r t h - o r b i t a l m i s s i o n f o r t h e S-IVB s t a g e . P u r p o s e o f t h e m i s s i o n was t o o b t a i n f l i g h t i n f o r m a t i o n on t h e S-IVB second s t a g e and t h e I n s t r u m e n t U n i t (IU). The t w o - s t a g e v e h i c l e b o o s t e d a n unmanned payload c o n s i s t i n g of t h e S-IVB s t a g e , I U and n o s e cone i n t o a 117-mile-high c i r c u l a r o r b i t . The S-IVB e n g i n e �burned once i n e a r t h ' s atmosphere and s h u t down. Photos of l i q u i d hydrogen f u e l b e h a v i o r were t r a n s m i t t e d t o f o u r ground s t a t i o n s by one t e l e v i s i o n camera. A second TV camera m a l f u n c t i o n e d . During t h e f o u r t h o r b i t , w h i l e performing a p r e s s u r e d i f f e r e n t i a l t e s t of t h e S-IVB s t a g e common bulkhead, i n t e r n a l p r e s s u r e b u i l t u p ' k e l l i n e x c e s s of d e s i g n valuesl'and t h e s t a g e exploded. I n i t i a l evaluation of f l i g h t d a t a i n d i c a t e d t h a t a l l m i s s i o n o b j e c t i v e s were a t t a i n e d . 7 I t was t h e 1 2 t h s u c c e s s f u l S a t u r n f l i g h t . JULY 5: Douglas removed t h e S-IVB-205 s t a g e from Beta I11 T e s t Stand a t SACTO f o r completion of p o s t - s t a t i c checkout. 8 S-IVB-206 s t a g e , which had a r r i v e d a t SACTO J u l y 1, was i n s t a l l e d i n Beta I11 T e s t Stand i n p r e p a r a t i o n f o r a c c e p t a n c e f i r i n g . 9 JULY 6: The S-IC-T a l l - s y s t e m s s t a g e was i n s t a l l e d i n t h e S-IC T e s t Stand 10 a t MSFC f o r a d d i t i o n a l s t a t i c f i r i n g s . JULY 7 : NASA announced e s t a b l i s h m e n t of new program o f f i c e s a t Manned S p a c e c r a f t Center and MSFC. The Saturn/Apollo A p p l i c a t i o n s Program O f f i c e a t MSC's Apollo A p p l i c a t i o m Program O f f i c e would be headed by George M . Low a s a c t i n g manager. 11 MSFC would have Leland F. Belew a s manager. JULY 8: MSFC c r e a t e d a new Experiments O f f i c e i n c o n n e c t i o n w i t h e s t a b l i s h - ment of t h e S a t u r n / A p o l l o Applications Program O f f i c e . D r . William G. Johnson would head t h e o f f i c e , which would o p e r a t e a t s t a f f l e v e l i n Research and Development O p e r a t i o n s . l2 - NASA announced award of a c o n t r a c t t o F e d e r a l E l e c t r i c C o r p o r a t i o n of I n t e r n a t i o n a l Telephone and Telegraph Company f o r t e c h n i c a l s u p p o r t of t h e S a t u r n launch v e h i c l e program a t MSFC. 13 �JL%Y - 8: V e r t i c a l b u i l d u p of t h e S-11-3 s t a g e ended a t S e a l Beach. 14 S&ID completed assembly of t h e f o r w a r d b u I k h e a d f o r S-11-4 f l i g h t s t a g e . a t S e a l ~ e a c h15 - MSFC awarded f o u r c o n t r a c t s c o v e r i n g F i s c a l Year 1967 LOX and LH2 requirementsfor the Center. The awards t o t a l l i n g $3.8 m i l l i o n went t o American Cryogenics, I n c . , A i r Reduction Company, I n c . , Welding 16 Gas P r o d u c t s Company, and Union Carbide Corporation. - . Douglas assembly t e c h n i c i a n s a t Huntington Beach completed S-IVB-209 s t a g e t a n k assembly. 1 7 JULY 13: NASA announced assignment t o MSFC of p r o j e c t management respon- s i b i l i t y f o r t h e Apollo Telescope Mount (ATM) f o r S a t u r n / A p o l l o 18 Applications missions. JULY 15: MSFC awarded p a r a l l e l $1.2 m i l l i o n c o n t r a c t s t o Lockheed and M a r t i n - M a r i e t t a t o conduct p r o j e c t d e f i n i t i o n s t u d i e s f o r Apollo A p p l i c a t i o n s Program (AAP) payload i n t e g r a t i o n . ' E f f e c t i v e d a t e of both 19 c o n t r a c t s was J u l y 8 , w i t h a 12-month p e r i o d of performance. - S t a g e - j o i n i n g o p e r a t i o n s f o r S-IVB-208 s t a g e began a t t h e Douglas 20 assembly f a c i l i t y a t Huntington Beach. JULY 18: MSFC announced award of a $230,000 c o n t r a c t t o Bagby E l e v a t o r and E l e c t r i c Company f o r m o d i f i c a t i o n s t o B wing of t h e f i r s t f l o o r 21 of t h e Computation L a b o r a t o r y , B u i l d i n g 4663. J U L Y 19: MSFC announced t h e award of two p a r a l l e l c o n t r a c t s t o Bendix and Boeing f o r s t u d y of proposed l u n a r s u r f a c e v e h i c l e s . The 6-month, $350,000 c o n t r a c t s extended work done by t h e two f i r m s under c o n t r a c t s 22 awarded i n 1964 and 1965. �JULY 19: Douglas p e r s o n n e l a t Huntington Beach completed on s c h e d u l e t h e s t a g e c h e c k o u t of S-IVB-207 s t a g e . 2 3 JULY 21: MSFC p e r s o n n e l conducted two f i r i n g t e s t s of t h e S-IVB B a t t l e s h i p . The t e s t s l a s t e d 6 and 200.5 s e c o n d s , r e s p e c t i v e l y , t o d u p l i c a t e cond i t i o n s of rough combustion e x p e r i e n c e d w i t h t h e same e n g i n e (5-2048) 24 i n a n e a r l i e r f i r i n g (May 1 8 , 1966). - S-IVB-501 s t a g e p o s t - f i r i n g c h e c k o u t ended s u c c e s s f u l l y w i t h a n a l l s y s t e m s t e s t a t SACTO's V e r t i c a l Checkout L a b o r a t o r y . 25 - MSFC c o n t r a c t e d w i t h Emerson E l e c t r i c Company t o s t u d y t h e p o s s i b i l i t y of r e c o v e r i n g s m a l l m e t a l l i c coupons from t h e wings of t h e Pegasus I11 meteoroid technology s a t e l l i t e . 26 $34,990. - Dr. Value of t h e l o w e e k c o n t r a c t was J . C . McCall, MSFC Deputy D i r e c t o r of Research and Development O p e r a t i o n s , announced he would r e s i g n i n September t o j o i n IBM. 2 7 - With p r e s t a t i c c h e c k o u t c o m p l e t e , S-IVB-502 underwent a s i m u l a t e d 28 s t a t i c t e s t a t SACTO's Beta 1 T e s t S t a n d . JULY 22: A f t e r s e v e r a l a t t e m p t s , S&ID a t S e a l Beach completed S-11-1 s t a g e 29 i n t e g r a t e d systems c h e c k o u t and a c c e p t a n c e . - S - I 1 B a t t l e s h i p T e s t No. 35 was conducted a t S a n t a Susana. D u r a t i o n of t h e t e s t was 300 m i l l i s e c o n d s , w i t h a n a u t o m a t i c c u t o f f caused by 30 miscalibration i n a sensing unit. J U L Y 23: A c o u s t i c t e s t i n g of t h e S - I 1 High Force T h r u s t C o m p l e x / i n t e r s t a g e specimen was completed a t Wyle L a b o r a t o r i e s , H u n t s v i l l e , e i g h t days ahead of s c h e d u l e . 3 1 �JULY 23: Douglas p e r s o n n e l a t SACTO began a s e r i e s of t e s t s ~ i t rhe d e s i g n e d i n j e c t o r s i n an a t t e m p t t o s o l v e t h e i n j e c t o r i c i n g problem i n t h e S - I V ~ / S a t u r nV oxygen-hydrogen b u r n e r . 3 2 JULY 24: MSFC announced award of a $150,000 s t u d y c o n t r a c t t o B a l l Brothers Research Corporation. The seven-month s t u d y concerned a s e r i e s of proposed e x p e r i m e n t s u s i n g a n A p o l l o s p a c e c r a f t t o c a p t u r e , 33 r e p a i r o r r e t r i e v e o b j e c t s from e a r t h o r b i t . JULY 25: Rocketdyne s u c c e s s f u l l y t e s t - f i r e d t h e f i r s t RS-V-602 m o t o r , which was t h e S - I 1 s t a g e u l l a g e motor. Preliminary data indicated s a t i s f a c t o r y performance. 34 JULY 26: MSFC had awarded t h e U n i v e r s i t y of Michigan a $29,930 s t u d y c o n t r a c t t o develop an i n f r a r e d sensing technique t o survey t h e e a r t h ' s n a t u r a l r e s o u r c e s from a i r c r a f t and o r b i t i n g s a t e l l i t e s . - 35 MSFC announced award of a $29,829 s t u d y c o n t r a c t t o Lockheed A i r c r a f t Corporation. The c o n t r a c t c o v e r e d a p r e l i m i n a r y d e s i g n s t u d y of a 36 lunar gravity simulator. JULY 28: Douglas conducted t h e a c c e p t a n c e f i r i n g of t h e S-IVB-502 a t SACTO on t h e f i r s t a t t e m p t . A f t e r a smooth t e s t countdown t h e r e was a f i r s t b u r n of 150.7 s e c o n d s . Following a 91-minute s i m u l a t e d o r b i t a l c o a s t p e r i o d , t h e s t a g e r e s t a r t e d and f i r e d f o r 291.2 37 seconds. - S&ID began work a t t h e S e a l Beach assembly p l a n t on t h e S-11-7 stage by p l a c i n g t h r e e g o r e s of t h e common bulkhead a f t f a c i n g s h e e t on t h e meridian-weld f i x t u r e f o r w e l d i n g o p e r a t i o n s . 38 �J U L Y 28: Checkout of t h e S-11-2 s t a g e s y s t e m s , which began J u l y 23, c o n t i n u e d a t S e a l Beach. P e r s o n n e l completed c o n t r o l r o o m / s t a g e / 39 s t a t i o n i n t e r f a c e c h e c k o u t and a p p l i e d power t o t h e s t a g e . JULY 29: C o n t r a c t s c o v e r i n g f e a s i b i l i t y s t u d i e s f o r P r o j e c t Able were e x e c u t e d t h i s week t o Goodyear Aerospace C o r p o r a t i o n and Boeing. C o n t r a c t v a l u e s were $75,000 and $125,000, r e s p e c t i v e l y . Contractors' s i g n a t u r e s were a w a i t e d on s i m i l a r awards t o Westinghouse and t h e S c h j e l d a h l Company. P r o j e c t Able p e r t a i n e d t o r e f l e c t o r s a t e l l i t e s t o p r o v i d e i l l u m i n a t i o n o v e r l a n d masses a t n i g h t . 40 - R e p a i r of c r a c k s i n t h e S-11-1 LH2 t a n k , which were - With t h e s u c c e s s f u l c o m p l e t i o n of S-IC s t a g e o x i d i z e r t a n k assembly d i s c o v e r e d J u l y 23 d u r i n g i n t e g r a t e d systems c h e c k o u t , were completed a t S e a l Beach. 4 1 t e s t , P&VE Lab p e r s o n n e l a t MSFC's Load T e s t Annex f u l l y q u a l i f i e d f o r m a n - r a t i n g a l l m a j o r s t r u c t u r a l components of t h e S-IC s t a g e (SA-501-503 c o n f i g u r a t i o n ) . The m a n - r a t i n g t e s t s q u a l i f i e d t h e 42 s t a g e components t o a s a f e t y f a c t o r of 1 . 4 . - An S - I 1 B a t t l e s h i p f i r i n g t e s t a t S a n t a Susana ended a f t e r 40 seconds 43 m a i n s t a g e b e c a u s e of a n e r r o n e o u s a u t o m a t i c c u t o f f . - S&ID p e r s o n n e l a t S e a l Beach conducted t h e h y d r o s t a t i c t e s t i n g of S-11-3 s t a g e , and d i s c o v e r e d a l e a k i n a weld j o i n t . 44 JULY 30: The S - I 1 B a t t l e s h i p s t a g e f i r e d f o r 365 seconds i n a t e s t a t . SSFL 45 - Following completion a t S e a l Beach of p o s t - c h e c k o u t r e p a i r s , S&ID 46 workmen p r e p a r e d S-11-1 s t a g e f o r shipment t o MTF. �JULY 31: The S-11-1 f l i g h t s t a g e , which had been loaded aboard t h e AKD P a i n t Barrow J u l y 30, d e p a r t e d S e a l Beach e n r o u t e t o MTF. 4 / I N JULY: MSFC t e s t p e r s o n n e l performed a series of S a t u r n V/S-IVB APS module f i r i n g t e s t s . F i r i n g s o c c u r r e d on J u l y 11, 1 5 , 28, and 29. (The APS module c o n s i s t e d of t h r e e e n g i n e s having 150 pounds of t h r u s t and one e n g i n e of 70 pounds t h r u s t . ) These t e s t s a t s i m u l a t e d a l t i t u d e v e r i f i e d t h e c a p a b i l i t y of t h e APS module t o o p e r a t e i n t h e 48 s p a c e environment. - MSFC awarded t o Bryson C o n s t r u c t i o n Company a $226,000 c o n t r a c t f o r e r e c t i o n of a o n e - s t o r y s t r u c t u r e t o house t h e C e n t e r ' s Research ProjectsOffice. The b ~ i l d i n g ~ p r o v i d i n8,400 g s q u a r e f e e t of f l o o r s p a c e , would be a t t a c h e d t o B u i l d i n g 4481. 49 - S t a g e j o i n i n g o p e r a t i o n s on S-IVB-503 were complete a t Huntington Beach by t h e middle of t h e month.50 - - Boeing workmen a t MAF completed h y d r o s t a t i c t e s t , c l e a n i n g , and p a i n t i n g of t h e S-IC-5 s t a g e . 5 1 S-IC-T was removed from t h e S-IC T e s t Stand a t MSFC w i t h o u t f u r t h e r f i r i n g s i n o r d e r t o e x p e d i t e t r a n s f e r of t h e s t a g e t o MTF f o r s t a n d checkout and l a t e r f i r i n g s . 5 2 �AUGUST 1 9 6 6 NASA announced s i g n i n g of an agreement w i t h C h r y s l e r Corpora- AUGUST 1: t i o n Space D i v i s i o n which c o n v e r t e d t h e Uprated S a t u r n I S-IB s t a g e p r o d u c t i o n c o n t r a c t from a f i x e d - f e e t o an i n c e n t i v e - f e e c o n t r a c t . The agreement, valued a t $339 m i l l i o n , c a l l e d f o r C h r y s l e r t o b u i l d and t e s t 12 S-IB s t a g e s and t o provide r e l a t e d s e r v i c e s , equipment and s u p p o r t . 1 S-IC-4 s t a g e moved i n t o t h e S t a g e Checkout B u i l d i n g a t MAF 2 f o r s t a r t of post-manufacturing checkout. AUGUST 3: - - H y d r o s t a t i c t e s t i n g of t h e S-11-4 s t a g e a f t bulkhead was completed a t 3 S e a l Beach. NASA modified an e x i s t i n g c o n t r a c t w i t h NAA1s Rocketdyne D i v i s i o n f o r . 52 a d d i t i o n a l 5-2 e n g i n e s and s u p p o r t s e r v i c e s e x t e n d i n g through 4 December 1968. The c o n t r a c t e x t e n s i o n c o s t $145.6 m i l l i o n . - MSFC awarded a $400,000 p l a n e t a r y s t u d y c o n t r a c t t o NAA. The one-year c o n t r a c t covered i n v e s t i g a t i o n of methods and hardware f o r manned 5 ~ a r and s Venus f l y b y s u s i n g Apollo/Saturn systems. AUGUST 5: MSFC announced award of a $23.4 m i l l i o n m o d i f i c a t i o n , - t o a n . e x i s t i n g c o n t r a c t w i t h NAA S&ID f o r a d d i t i o n a l s e r v i c e s i n b u i l d i n g and s e r v i c i n g t h e S - I 1 second s t a g e f o r t h e S a t u r n V v e h i c l e . The m o d i f i c a t i o n i n c l u d e d r e d e s i g n of t h e s t a g e u m b i l i c a l system and 6 additional testing. -S-IC-4, w i t h h o r i z o n t a l assembly o p e r a t i o n s completed t h e p r e v i o u s day, moved from manufacturing t o t h e post-manufacturing checkout a r e a of 7 MAF . �S-IVB-204 f l i g h t s t a g e was shipped from SACTO t o KSC f o l l o w i n g completion of s t a g e m o d i f i c a t i o n s . 8 AUGUST 5: AUGUST 8: The b u i l d i n g c o n t r a c t o r completed and t u r n e d over t o t h e government a t MTP t h e S - I 1 S t a g e V e r t i c a l Checkout Building and 9 t h e S-I1 Vehicle Service Building. - S t r u c t u r a l f a b r i c a t i o n of S-IU-503 ended a t IBM/Huntsville. 1 0 AUGUST 9: The i n t e r s t a g e f o r t h e S-11-1 a r r i v e d a t P o r t Canaveral (KSC) on a commercial w a t e r t r a n s p o r t and was t r a n s f e r r e d from t h e barge t o t h e VAB. 11 - P e r s o n n e l a t Huntington Beach completed t h e l a s t of seven scheduled t e s t s i n t h e S-IVB/Instrument U n i t environmental t e s t program, 12 u t i l i z i n g t h e S-IU-500FS f l i g h t systems t e s t u n i t . AUGUST 10: MSFC's Q u a l i t y L a b o r a t o r y completed p o s t - s t a t i c checkout of S-IC-1 and t u r n e d t h e s t a g e over t o ME L a b o r a t o r y t o p r e p a r e f o r 13 shipment t o KSC. - P e r s o n n e l a t SACTO removed S-IVB-502 from t h e t e s t s t a n d f o l l o w i n g comp l e t i o n of i t s a c c e p t a n c e f i r i n g program and p l a c e d . t h e s t a g e i n t h e V e h i c l e Checkout L a b o r a t o r y . 14 - ME L a b o r a t o r y p e r s o n n e l a t MSFC completed r e f u r b i s h m e n t of t h e S-IC-2 s t a g e following i t s s t a t i c f i r i n g . Workmen moved t h e s t a g e t o a Q u a l i t y Lab checkout s t a t i o n f o r commencement of p a s t - s t a t i c checkout.15 - The S-IB-4, b o o s t e r s t a g e f o r t h e Uprated S a t u r n I scheduled t o perform t h e f i r s t manned Apollo m i s s i o n , d e p a r t e d MAF f o r K S C . ~ ~ �AUGUST 11: The SA-202 F l i g h t R e a d i n e s s Review was h e l d a t KSC's LC-34 a s scheduled. l7 - The S-IB-7 s t a g e a r r i v e d a t ~ S ~ C / H u n t s v i l lfrom e MAF on t h e b a r g e P o s e i d o n , and t e c h n i c i a n s i n s t a l l e d i t i n t h e S t a t i c T e s t S t a n d E a s t . 18 - NASA announced t h a t MSFC would b e g i n n e g o t i a t i o n s w i t h C h r y s l e r and Douglas f o r procurement o f l o n g - l e a d - t i m e Uprated Saturn I launch v e h i c l e s . was e s t i m a t e d a t $5 t o $10 m i l l i o n . - items f o r a d d i t i o n a l Cost of t h e advance v e h i c l e i t e m s 19 S-IC-D t h r u s t v e c t o r c o n t r o l (TVC) t e s t s began i n t h e S a t u r n V Dynamic T e s t S t a n d a t MSFC. 20 A 365-second f i r i n g t e s t o f t h e S - I 1 B a t t l e s h i p a t SSFL ended w i t h a n a u t o m a t i c c u t o f f i n i t i a t e d by t h e LH2 low l e v e l c u t o f f system. 2 1 Upon c o m p l e t i o n of t h e a d d i t i o n t o t h e Advanced S a t u r n GSE T e s t F a c i l i t y 22 a t MSFC, f i n a l i n s p e c t i o n of t h e f a c i l i t y was h e l d . AUGUST 12: Douglas t u r n e d o v e r t o NASA and s h i p p e d t o KSC v i a Super Guppy 23 t h e f i r s t S-IVB f l i g h t s t a g e f o r S a t u r n V , t h e S-IVB-501. - T e c h n i c i a n s a t KSC's LC-39 s u c c e s s f u l l y completed f u l l p r e s s u r e t e s t on t h e t a n k a g e of S-11-F,a p a r t of t h e S a t u r n V F a c i l i t i e s Checkout V e h i c l e , s t a n d i n g on Pad AUGUST 13: S-11-1 s t a g e a r r i v e d a t MTF a f t e r t r a n s f e r from t h e AKD P o i n t Barrow t o t h e s h u t t l e b a r g e P e a r l R i v e r a t Michoud Assembly F a c i l i t y . 25 �AUGUST 1 3 : MSFC s h i p p e d t h e S - I 1 s t a g e s i m u l a t o r ( s p a c e r ) from MAF t o KSC v i a t h e P o i n t Barrow f o r temporary u s e i n t h e f i r s t S a t u r n V 26 v e h i c l e , SA-501. AUGUST 1 4 : The S-IVB-501 s t a g e a r r i v e d a t KSC a b o a r d t h e Super Guppy. I t had d e p a r t e d Sacramento August 12 and been d e l a y e d one day b e c a u s e 27 of w e a t h e r . AUGUST 15: The S-IVB-501 s t a g e was moved i n t o t h e low bay o f t h e VAB i n p r e p a r a t i o n f o r " s t a c k i n g " a s a p a r t of t h e SA-501 f l i g h t v e h i c l e . 2 8 - The S-1VBISaturn V h i g h - f o r c e dynamic t e s t program was completed a t t h e Wasatch D i v i s i o n of T h i o k o l Chemical C o r p o r a t i o n , Brigham C i t y , U t a h . 29 - The S-IB-4 s t a g e a r r i v e d a t KSC v i a b a r g e . 3 0 AUGUST 16: - S-IU-204 was s h i p p e d t o KSC by a i r c r a f t . 3 1 MSFC awarded t o NAA a o n e - y e a r , $400,000 c o n t r a c t t o " i n v e s t i g a t e t h e b e s t methods and hardware f o r p e r f o r m i n g manned Mars and Venus f l y b y s w i t h maximum u s e of A p o l l o / S a t u r n systems ...a s a stepping stone t o manned l a n d i n g m i s s i o n s . ,132 - The S - I 1 f i t u p f i x t u r e ( s t a g e s i m u l a t o r ) d e s i g n a t e d H7-17 arrived a t KSC from MTF t o s e r v e a s a "spacer" on t h e SA-501 v e h i c l e u n t i l a r r i v a l o f t h e S-11-1 s t a g e . 3 3 AUGUST 17: I n t h e v e r t i c a l assembly tower a t MAE, Boeing p e r s o n n e l mated t h e S-IC-5 i n t e r t a n k s e c t i o n t o t h e f u e l t a n k , which had been moved i n t o t h e tower w i t h t h e t h r u s t s t r u c t u r e t h e p r e v i o u s d a y . 3 4 �AUGUST 17: During t h e S-IC-F LOX l o a d i n g t e s t a t LC-39, t h e f a c i l i t y LOX s y s t e m f a i l e d , c a u s i n g d e l a y i n t h e S-11-Ft a n k i n g s c h e d u l e . 35 AUGUST 18: S-IU-501 c h e c k o u t ended a t H u n t s v i l l e w i t h a l l t e s t r e q u i r e ments s a t i s f i e d . 36 AUGUST 19: NASA s e l e c t e d McDonnell A i r c r a f t C o r p o r a t i o n f o r n e g o t i a t i o n s on a f i x e d - p r i c e c o n t r a c t t o produce an a i r l o c k f o r an e x p e r i m e n t i n which a s t r o n a u t s would e n t e r t h e empty hydrogen t a n k of a s p e n t Uprated S a t u r n I second s t a g e . 37 million. - E s t i m a t e d c o s t of t h e work was $9 Douglas s u c c e s s f u l l y accomplished a c c e p t a n c e f i r i n g of S-IVB-206 f l i g h t s t a g e a t SACTO's Beta 3 T e s t S t a n d . 38 433.7 s e c o n d s . - M a i n s t a g e d u r a t i o n was "Stackup" of t h e S-IC-5 ended a t MAF's v e r t i c a l assembly tower w i t h 39 m a t i n g of t h e forward s k i r t t o t h e t o p of t h e s t a g e . T e c h n i c i a n s a t MTF i n s t a l l e d t h e S-11-1 s t a g e i n T e s t S t a n d A - 2 a f t e r c o m p l e t i n g r e c e i v i n g i n s p e c t i o n and r e p l a c e m e n t of a n LH2 c y l i n d e r 40 doubler. AUGUST 20: The S-IU-500FS was flown from Huntington Beach t o MSFC aboard t h e Super Guppy f o l l o w i n g t h e S-IVB/IU e n v i r o n m e n t a l t e s t program i n t h e Douglas Space Systems C e n t e r . The S-IU-500FS, reallocated t o t h e S a t u r n V SDF, would be updated t o t h e S-IU-504 c o n f i g u r a t i o n . AUGUST 22: S t a g e c h e c k o u t of S-IVB-208 began i n Tower 5 a t t h e Douglas 42 H u n t i n g t o n Beach f a c i l i t y . 41 �AUGUST 24: Boeing p e r s o n n e l a t MAF s u c c e s s f u l l y completed post-manufac43 t u r i n g c h e c k o u t of S-IC-3. - At LC-39A t h e a u t o m a t i c l o a d i n g of f u e l i n t h e S-IC-F s t a g e of SA-500F, which began on August 1 2 , was s u c c e s s f u l l y completed. 44 AUGUST 25: I B M began s t r u c t u r a l f a b r i c a t i o n of S-IU-504, the instrument u n i t f o r t h e f o u r t h f l i g h t S a t u r n V. - The Super Guppy d e l i v e r e d S-IU-501 t o KSC f o r u s e i n t h e SA-501 l a u n c h v e h i c l e . 46 - NASA s u c c e s s f u l l y l a u n c h e d t h e A p o l l o / S a t u r n AS-202 v e h i c l e from Complex 34 a t 1:16 p.m. EDT. The t h i r d Uprated S a t u r n I f l i g h t v e h i c l e b o o s t e d unmanned A p o l l o s p a c e c r a f t 011 i n t o s u b o r b i t a l f l i g h t . I t was t h e second f l i g h t t e s t of t h e major s p a c e c r a f t s y s t e m s , and t h e second performance check of t h e Command Module (CM) h e a t s h i e l d . Liftoff and powered f l i g h t were normal. t h e 21,500-pound-thrust After spacecraft separation, S e r v i c e Module (SM) p r o p u l s i o n e n g i n e burned 3 m i n u t e s and 35 seconds t o b o o s t t h e s p a c e c r a f t t o 706 m i l e s a l t i tude. The SM e n g i n e i g n i t e d t h r e e more t i m e s t o t e s t r a p i d r e s t a r t c a p a b i l i t i e s , w i t h t h e l a s t burn s e p a r a t i n g t h e SM. The CM e n t e r e d e a r t h ' s atmosphere a t more t h a n 1 9 , 9 0 0 mph, and maximum t e m p e r a t u r e of t h e s p a c e c r a f t ' s s u r f a c e was c a l c u l a t e d t o be a b o u t 2,700 d e g r e e s F. w h i l e i n t e r n a l t e m p e r a t u r e was 70 d e g r e e s . The main p a r a c h u t e s d e p l o y e d a t 23,850 f e e t a l t i t u d e , l o w e r i n g t h e CM t o splashdown i n t h e P a c i f i c Ocean a b o u t 500 m i l e s s o u t h e a s t of Wake I s l a n d and 200 m i l e s from t h e t a r g e t , a t 2:49 p.m. c a r r i e r USS Hornet. EDT. Recovery was by a i r c r a f t The Apollo h e a t s h i e l d had w e l l w i t h s t o o d t h e h i g h h e a t - l o a d t e s t , and t h e s p a c e c r a f t was i n " s t a b l e c o n d i t i o n 1."47 �AUGUST 25-26: The s t e e r i n g committee f o r t h e p r e l i m i n a r y s t u d y o f a NASA manned s p a c e s t a t i o n met a t Manned S p a c e c r a f t C e n t e r , Houston, Texas, t o review space s t a t i o n design approaches, l o g i s t i c system a p p r o a c h e s , and e x p e r i m e n t i n t e g r a t i o n . T h i s committee i n c l u d e d MSFC p e r s o n n e l . 48 AUGUST 26: S-IC-1, t h e f i r s t S a t u r n V f l i g h t b o o s t e r , went a b o a r d t h e b a r g e P o s e i d o n a t H u n t s v i l l e and d e p a r t e d f o r KSC. 49 - Boeing, NASA, and S&ID p e r s o n n e l met a t KSC t o d i s c u s s c o n v e r s i o n of t h e S-11-F s t a g e t o t h e S-11-F/D c o n f i g u r a t i o n . 5 0 - I n p r e p a r a t i o n f o r a c c e p t a n c e f i r i n g of S-11-1 f l i g h t s t a g e , NAA p e r 51 s o n n e l a t MTF a p p l i e d power t o t h e s t a g e on T e s t S t a n d A-2. - MSFC t e s t p e r s o n n e l c o n d u c t e d a f i r i n g t e s t of t h e S a t u r n V/S-IVB APS module. AUGUST 27: 52 Boeing p e r s o n n e l a t MAF completed p o s t m a n u f a c t u r i n g check- o u t o f S-IC-3 s t a g e . 5 3 - MSFC p e r s o n n e l r e i n s t a l l e d a n F-1 e n g i n e i n t h e No. 1 p o s i t i o n on S-IC-2 a f t e r f i r i n g t h e e n g i n e t w i c e t o i d e n t i f y and c o r r e c t a 54 h i g h - t h r u s t problem. AUGUST 30: Douglas workmen a t H u n t i n g t o n Beach s h i p p e d t h e completed 55 S-IVB-207 s t a g e t o SACTO v i a t h e Super Guppy a i r c r a f t . AUGUST 31: Workmen a t S e a l Beach moved S-11-3 s t a g e t o a t e s t s t a t i o n f o r LOX t a n k c l e a n i n g and LH2 t a n k h e l i u m s o a k i n g i n p r e p a r a t i o n f o r s y s t e m s i n s t a l l a t i o n . 56 �S - I 1 B a t t l e s h i p f i r i n g t e s t No. 39 ended a f t e r 233 seconds a t 57 S a n t a Susana. AUGUST 31: I N AUGUST: Douglas workmen a t S a n t a Monica completed t h e common bulkhead 58 f o r S-IVB-505 f l i g h t s t a g e . - S t r u c t u r a l t e s t i n g of t h e S-IC o x i d i z e r t a n k assembly i n t h e S-IC-5 c o n f i g u r a t i o n ended s u c c e s s f u l l y a t M S F C . ~ ~ - S&ID workmen a t S e a l Beach completed ahead of s c h e d u l e t h e a f t bulkhead 60 f o r t h e S-11-4 f l i g h t s t a g e . - MSFC t e s t p e r s o n n e l conducted t h r e e s t a t i c f i r i n g s of t h e S-IVB B a t t l e ship a t Huntsville. There was a 31-second t e s t August 11, a 20-second f i r i n g on August 24, and a t e s t of 279 seconds August 26. The f i r s t S-IVB "hot g i m b a l i n g " program a t MSFC was performed d u r i n g t h e August 26 t e s t a 6 1 - NASA H e a d q u a r t e r s approved m o d i f i c a t i o n of t h e v e s s e l O r i o n , t o be used a s a backup f o r t h e P o i n t Barrow and t h e Poseidon i n w a t e r 62 t r a n s p o r t of S a t u r n s t a g e s . - S-IVB-502 p o s t - s t a t i c c h e c k o u t and s y s t ~ m s t e s t s c o n t i n u e d t h r o u g h o u t t h e morith a t SACTO. 6 3 �S E P T E M B E R SEPTEMBER 1: 1 9 6 6 An i n v e s t i g a t i v e b o a r d named by t h e MSFC D i r e c t o r t o s t u d y s t a g e a c c i d e n t a l d e s t r u c t i o n d u r i n g a t e s t a t MTF on t h e S-11-T/D May 2 8 r e p o r t e d i t s f i n d i n g s and recommendations. The b o a r d found t h a t t h e p r i m a r y f a i l u r e o c c u r r e d n e a r t h e LH2 f i l l - a n d - d r a i n l i n e f i t t i n g - t o - s k i n and was caused by s t r e s s i n d u c e d by poor f i t i n conjunction with the pressure applied. 1 c o n t r o l o v e r MTF t e s t p r o c e d u r e s . - The b o a r d recommended t i g h t e r NASA H e a d q u a r t e r s approved t h e MSFC c o n t r a c t w i t h Computer S c i e n c e s C o r p o r a t i o n f o r m i s s i o n s u p p o r t s e r v i c e s f o r t h e Computation L a b o r a 2 tory. - C h r y s l e r p e r s o n n e l a t MSFC conducted a s u c c e s s f u l s h o r t - d u r a t i o n ( 3 5 second) f i r i n g of t h e S-IB-7 s t a g e . 3 - T e c h n i c i a n s a t SACTO i n s t a l l e d i n Beta 1 T e s t S t a n d t h e S-IVB-207 s t a g e , which had a r r i v e d August 31 from H u n t i n g t o n Beach. - 4 S o l u t i o n of t h e S-IVB s t a g e oxygen-hydrogen b u r n e r i n j e c t o r i c i n g p r o gram was d e m o n s t r a t e d by Douglas a t SACTO i n a s e r i e s of 1 6 performance t e s t s beginning t h i s date.5 SEPTEMBER 2: P o s t - s t a t i c c h e c k o u t a c t i v i t y on t h e S-IVB-502 s t a g e ended 6 a t SACTO. SEPTEMBER 3 : IBM a t H u n t s v i l l e completed assembly of S-IU-502 and made immediate p r e p a r a t i o n s f o r t e s t i n g t h e u n i t . - / I B M p e r s o n n e l completed s t r u c t u r a l f a b r i c a t i o n o f S-IU-207. 8 �SEPTEMBER 3: An open house was h e l d c e l e b r a t i n g t h e opening of t h e MARS Golf and Country Club n e a r M e r i d i a n v i l l e 12 m i l e s n o r t h of H u n t s v i l l e . The newly completed employee r e c r e a t i o n f a c i l i t y was o p e r a t e d f o r MSFC employees .9 SEPTEMBER 6: MSFC announced t h r e e key p e r s o n n e l changes i n t h e C e n t e r ' s Engine Program O f f i c e : S. F. Morea, F-1 Engine p r o j e c t manager, became d e p u t y manager, Engine Program O f f i c e ; F r a n c i s M . S t e w a r t I11 s u c c e e d e d Morea i n t h e F-1 Engine O f f i c e ; and A . J . Burks, J r . , a s s i s t a n t manager, Engine Program O f f i c e , assumed a d d i t i o n a l d u t i e s 10 a s a c t i n g c h i e f , Program C o n t r o l O f f i c e . SEPTEMBER 6-7: A s t r o n a u t Alan Bean v i s i t e d MSFC and s i m u l a t e d S-IVB Workshop a c t i v i t i e s i n t h e n e u t r a l buoyancy Zero G s i m u l a t o r t a n k , w e a r i n g t h e Arrowhead Mark I V p r e s s u r e s u i t . He a l s o worked w i t h 11 S-IVB Workshop 209 e x p e r i m e n t s i n t h e ME L a b ' s mockup a r e a . SEPTEMBER 7: The b a r g e Poseidon c a r r y i n g t h e S-IC-1 s t a g e resumed i t s voyage from MSFC t o KSC a f t e r b e i n g d e l a y e d s e v e r a l days a t New O r l e a n s 12 by a towing s t r i k e . P e r s o n n e l a t SACTO completed p o s t - f i r i n g c h e c k o u t of 13 S-IVB-502 s t a g e w i t h a n a l l - s y s t e m s t e s t . SEPTEMBER 12: - The S-IC-1 s t a g e , b o o s t e r f o r t h e f i r s t S a t u r n V f l i g h t v e h i c l e , a r r i v e d a t KSC from MSFC t o b e g i n t h e b u i l d u ? of f l i g h t v e h i c l e SA-501. men unloaded t h e s t a g e , moved i t t o t h e LC-39 VAB, and i n i t i a t e d 14 receiving inspection. - V e r t i c a l assembly of S-IC-5 was completed a t MAF. 15 Work- �SEPTEMBER 13: A f u l l - d u r a t i o n s t a t i c f i r i n g of S-IB-7 s t a g e o c c u r r e d a t . MSFC l6 SEPTEMBER 14: Douglas p e r s o n n e l a t SACTO s u c c e s s f u l l y f i r e d t h e S-IVB-206 s t a g e f o r a m a i n s t a g e d u r a t i o n of 66.7 s e c o n d s . This f i r i n g v e r i f i e d performance of a n e n g i n e f o l l o w i n g r e p l a c e m e n t of t h e LOX turbopump 17 assembly. SEPTEMBER 15: MSFC p e r s o n n e l completed t h e s t r u c t u r a l t e s t program of t h e S-IU-200S/500S-111. In the f i n a l t e s t condition the u n i t successfully w i t h s t o o d 1 4 0 p e r c e n t l i m i t l o a d i n g s and was c o n s i d e r e d q u a l i f i e d f o r 18 b o t h manned and unmanned U p r a t e d S a t u r n I and S a t u r n V v e h i c l e s . SEPTEMBER 20: MSFC/Huntsville s h i p p e d t h e S-IB-7 s t a g e back t o MAF f o r p o s t - s t a t i c t e s t s f o l l o w i n g t h e f u l l - d u r a t i o n s t a t i c t e s t September 1 3 . 20 - Manual LOX l o a d i n g t e s t s a t KSC were completed f o r S-IC-F s t a g e . - S&ID t e c h n i c i a n s began t h e v e r t i c a l b u i l d u p of t h e S-11-5 f l i g h t s t a g e a t S e a l Beach w i t h t h e weld j o i n i n g of t a n k c y l i n d e r s . 21 problems h i n d e r e d t h e b u i l d u p . Welding - IBM/Huntsville completed c h e c k o u t of S-IU-205 b u t r e t a i n e d t h e u n i t f o r 22 i n s t a l l a t i o n of m o d i f i c a t i o n k i t s p r i o r t o s h i p p i n g t o KSC. - The RCA l l O A computer was i n s t a l l e d i n Launch C o n t r o l C e n t e r F i r i n g 23 Room 2 a t LC-39, KSC. SEPTEMBER 23: MAF r e t u r n e d t o H u n t s v i l l e t h e S-IB-D/F ( d y n a m i c / f a c i l i t i e s ) The s t a g e was s c h e d u l e d f o r 24 d i s p l a y a t t h e MSFC Space O r i e n t a t i o n C e n t e r . s t a g e which had been i n s t o r a g e a t MAF. 19 �SEPTEMBER 23: KSC t e c h n i c i a n s a t LC-39A s u c c e s s f u l l y completed t h e S-11-F LOX and LH2 manual l o a d i n g t e s t . 25 were accomplished. - Most major t e s t o b j e c t i v e s The S-IC-3 s t a g e , f i r s t S a t u r n V f l i g h t b o o s t e r m a n u f a c t u r e d by Boeing, d e p a r t e d MAF by b a r g e e n r o u t e t o MSFC/Huntsville f o r s t a t i c t e s t i n g . 2 6 SEPTEMBER 24: Checkout of t h e S-11-2 s t a g e s y s t e m s , which proceeded much more smoothly t h a n had checkout of S-11-1, SEPTEMBER 26: ended a t S e a l Beach. 2 7 S&ID p e r s o n n e l a t S e a l Beach s u c c e s s f u l l y conducted t h e t h i r d p n e u m o s t a t i c t e s t of S-11-3 f l i g h t s t a g e . 2 8 - C h r y s l e r p e r s o n n e l a t MAF began p o s t - s t a t i c m o d i f i c a t i o n s and r e p a i r s 29 on S-IB-7 s t a g e . SEPTEMBER 27: A t MTF t h e c o n s t r u c t i o n c o n t r a c t o r completed t h e S - I 1 V e h i c l e S e r v i c e and V e r t i c a l Checkout B u i l d i n g . 30 i n s t a l l a t i o n continued. SEPTEMBER 28: T e c h n i c a l systems With assembly of t h e S-11-4 f l i g h t s t a g e a l m o s t complete a t S e a l Beach, o f f i c i a l s r e f u s e d t o a c c e p t t h e f a u l t y " g i r t h weld" o f t h e a f t b u l k h e a d ; a review board d e c i d e d t o c u t t h e weld a p a r t and t o r e p l a c e t h e bulkhead w i t h t h e S-11-5 a f t bulkhead. 3 1 - The AKD P o i n t Barrow a r r i v e d a t S e a l Beach c a r r y i n g t h e a f t s e c t i o n of t h e S-11-T/D, SEPTEMBER 29: which was s c h e d u l e d f o r m i n u t e e x a m i n a t i o n . 3 2 MSFC announced award of t h r e e new s t u d y c o n t r a c t s i n v o l v i n g manned p l a n e t a r y f l y b y s . M i s s i o n s i n t h e 1975-82 p e r i o d would be s t u d i e d by NAA S&ID and Douglas, e a c h w i t h $100,000 c o n t r a c t s . Systems, I n c . , r e c e i v e d a $200,000 c o n t r a c t t o s t u d y a l t e r n a t i v e 33 m i s s i o n modes f o r o r b i t a l and l a n d i n g m i s s i o n s . TRF! �SEPTEMBER 30: Technicians a t Huntington Beach i n s t a l l e d a 5-2 e n g i n e on S-IVB-504 s t a g e d u r i n g v e r t i c a l assembly and systems i n s t a l l a t i o n of 34 the stage. I N SEPTEMBER: S&ID p e r s o n n e l a t SSFL began major m o d i f i c a t i o n s t o t h e B a t t l e s h i p T e s t Stand upon completion of T e s t F i r i n g No. 39. c a t i o n s were i n p r e p a r a t i o n f o r b o a t t a i l environmental t e s t s . Modifi- 35 �O C T O B E R OCTOBER 1: 1 9 6 6 S-IC-3 s t a g e a r r i v e d a t H u n t s v i l l e by b a r g e from MAF.' OCTOBER 2: S-11-2 s t a g e systems c h e c k o u t , i n p r o g r e s s s i n c e J u l y 23, 2 ended a t S&ID1s S e a l Beach f a c i l i t y . OCTOBER 3 : S-IC-D f i n and f a i r i n g t e s t s t h a t began September 29 were completed a t MSFC. 3 - - S-IC-F a u t o m a t i c LOX l o a d i n g ended a t LC-39A, KSC. 4 Workmen a t MSFC/Huntsville unloaded S-IC-3 and p l a c e d i t i n t h e S-IC T e s t Stand i n p r e p a r a t i o n f o r acceptance f i r i n g . 5 Douglas workmen a t Huntington Beach f i n i s h e d p a i n t i n g t h e S-IVB-503 s t a g e f o l l o w i n g September 1 4 c o m p l e t i o n of a l l f a c t o r y c h e c k o u t t e s t s . - The RCA l l O A computer f o r Launch U m b i l i c a l Tower (LUT) No. 2 a t LC-39 7 was i n s t a l l e d fol.lowing d e l i v e r y t o KSC on September 30. OCTOBER 5: 8 ity. F a c t o r y c h e c k o u t of S-IU-206 began a t I B M ' s H u n t s v i l l e f a c i l - OCTOBER 7: G e n e r a l Dynamics C o r p o r a t i o n r e c e i v e d a n e i g h t - m o n t h $275,000 c o n t r a c t f o r a study of very l a r g e space s t r u c t u r e s . The f i r m would a n a l y z e s t r u c t u r a l c o n c e p t s p r o v i d e d by MSFC and a l s o d e v e l o p a d d i t i o n a l concepts. G e n e r a l Dynamics would t h e n s e l e c t t h r e e s t r u c t u r e s t h a t c o u l d f l y a s A p o l l o A p p l i c a t i o n s payloads on S a t u r n l a u n c h 9 vehicles. Workmen a t Huntington Beach performed h y d r o s t a t i c t e s t i n g of 10 t h e S-IVB-505 t a n k a g e . OCTOBER 10: 6 �OCTOBER 1 0 : P e r s o n n e l a t SSFL began S - I 1 B a t t l e s h i p s t a g e b o a t t a i l environmental t e s t i n g . These t e s t s were s c h e d u l e d t o c o n t i n u e t h r o u g h December t o e v a l u a t e t h e S - I 1 s t a g e LOX r e c i r c u l a t i o n s y s t e m . l l C h r y s l e r p e r s o n n e l a t MAF completed p o s t - s t a t i c c h e c k o u t o f OCTOBER 11: S-IB-6 and began t o p r e p a r e t h e s t a g e f o r shipment t o KSC. 12 - S-IVB-503 t r a v e l l e d v i a Super Guppy from H u n t i n g t o n Beach t o SACTO f o r c h e c k o u t and a c c e p t a n c e f i r i n g t e s t s . 1 3 MSFC completed d e l i v e r y t o KSC o f t h e q u a l i f i e d s e r v i c e arms OCTOBER 1 2 : and t a i l s e r v i c e m a s t s f o r LUT No. 1.1 4 - Douglas workmen a t H u n t i n g t o n Beach completed f a c t o r y c h e c k o u t o f S-IVB208 s t a g e . 15 - Shipment o f S-IVB-503 s t a g e by a i r from t h e Douglas assembly p l a n t t o 16 SACTO f o r t e s t i n g o c c u r r e d . - SA-500F v e h i c l e a u t o m a t i c LOX and LH2 l o a d i n g was s a t i s f a c t o r i l y a c c o m p l i s h e d a t KSC LC-39A. 17 NASA awarded t h e I B M F e d e r a l Systems D i v i s i o n a $51 m i l l i o n OCTOBER 1 4 : sole-source c o n t r a c t t o provide Saturn instrument u n i t launch support 18 s e r v i c e s a t KSC t h r o u g h J u n e 3 0 , 1970. - R o l l b a c k o f t h e SA-500F v e h i c l e from LC-39A t o t h e VAB was accomplished a t KSC, f o l l o w i n g c o m p l e t i o n of f a c i l i t y / v e h i c l e c h e c k o u t and n e c e s s a r y 19 testing . OCTOBER 15: MSFC u n v e i l e d t o t h e p u b l i c f o r t h e f i r s t t i m e a mockup of a n U p r a t e d S a t u r n I upper (S-IVB) s t a g e c o n v e r t e d i n t o a s p a c e �workshop. 20 event. OCTOBER 17: The mockup was shown d u r i n g t h e C e n t e r ' s open house S&ID p e r s o n n e l a t KSC s t a r t e d work t o modify t h e S-11-F s t a g e t o t h e S-11-D c o n f i g u r a t i o n f o r t h e S a t u r n V dynamic t e s t program a t MSFC . 2 1 - On T e s t S t a n d A-2 a t MTF S&ID p e r s o n n e l s u c c e s s f u l l y accomplished t h e LN2/LH2 t a n k i n g t e s t of t h e S-11-1 s t a g e p r e p a r a t o r y t o s t a t i c - f i r i n g 22 the stage. - S t a g e b a l l a s t i n g of S-IC-D was completed and l o n g i t u d i n a l t e s t i n g on 23 t h e s t a g e began a t MSFC's S a t u r n V Dynamic T e s t S t a n d . - Douglas p e r s o n n e l a t Huntington Beach completed S-IVB-206 s t a g e p o s t 24 f i r i n g checkout. - A f t e r u p d a t i n g t h e S-IC-T t o t h e S-IC-4 c o n f i g u r a t i o n , MSFC/Huntsville 25 p e r s o n n e l s h i p p e d t h e s t a g e t o MTF v i a t h e Poseidon. OCTOBER 19: MSFC awarded t h e M a r t i n Company a one-year $100,000 c o n t r a c t f o r a d e s i g n f e a s i b i l i t y s t u d y of a 2 , 0 0 0 - w a t t n u c l e a r power s y s t e m c o n s i s t i n g of f o u r Snap-29 r a d i o i s o t o p e g e n e r a t o r s f o r p o s s i b l e u s e on l o n g - d u r a t i o n p o s t - A p o l l o m i s s i o n s . 2 6 - Douglas s u c c e s s f u l l y accomplished a c c e p t a n c e f i r i n g of S-IVB-207 s t a g e a t SACTO i n Beta 1 T e s t S t a n d . OCTOBER 21: M a i n s t a g e d u r a t i o n was 445.6 s e c o n d s . 27 Wyle L a b o r a t o r i e s f o r m a l l y opened i t s High-Force V i b r a t i o n T e s t i n g F a c i l i t y a t H u n t s v i l l e f o r t h e S - I 1 s t a g e and o t h e r components 28 of t h e S a t u r n V v e h i c l e . �OCTOBER 21: KSC t e c h n i c i a n s completed d e - e r e c t i o n of SA-500F i n t h e VAB a t LC-39. The d e - e r e c t i o n p r o c e s s began October 1 5 w i t h t h e Command and S e r v i c e Modules and I n s t r u m e n t U n i t , c o n t i n u e d October 16 w i t h t h e S-IVB and S - I 1 s t a g e s , and concluded w i t h t h e S-IC s t a g e . 2 9 OCTOBER 23: The S-IC-T s t a g e , s h i p p e d from H u n t s v i l l e October 1 7 , a r r i v e d a t MTF and was s t o r e d pending c o m p l e t i o n of t h e B-2 T e s t S t a n d . 3 0 OCTOBER 24: During e r e c t i o n of SA-501 on LUT No. 1 t h e LC-39 VAB, work- men completed removal and r e p l a c e m e n t of a l l b u t f o u r of t h e n e c e s s a r y swing arms. 31 OCTOBER 25: T e c h n i c i a n s c o n v e r t i n g S-11-F s t a g e t o S-11-D c o n f i g u r a t i o n o u t of t h e bay a t KSC. 3 2 completed t h e work and r o l l e d t h e S-11-F/D - MSFC announced award of a $679,101 c o n t r a c t t o t h e U n i v e r s i t y of Wisconsin t o d e v e l o p s e n s o r s f o r a g a l a c t i c X-ray mapping e x p e r i m e n t 33 t o be flown on a n Uprated S a t u r n I l a u n c h v e h i c l e . - The S-IB-8 s t a g e a r r i v e d a t MSFC/Huntsville from MAF f o r ground t e s t operations .34 OCTOBER 26: S-IC-3 p r o p e l l a n t l o a d t e s t , which began October 2 5 , was 35 s u c c e s s f u l l y completed a t MSFC. - NASA awarded NAA a $37 m i l l i o n supplementary c o n t r a c t c o v e r i n g l a u n c h p r e p a r a t i o n and c h e c k o u t of t e n S - I 1 s t a g e s of t h e S a t u r n V v e h i c l e .36 - S&ID p e r s o n n e l a t S e a l Beach completed assembly of t h e S-11-5 s t a g e a f t bulkhead. The bulkhead t h e n was r e d e s i g n a t e d t o t h e S-11-4 s t a g e . 37 �OCTOBER 27: LC-39. vehicle. OCTOBER 28: KSC p e r s o n n e l e r e c t e d S-IC-1 on LUT No. 1 i n t h e VAB a t S-IC-E was t h e f i r s t s t a g e of t h e f i r s t S a t u r n V f l i g h t 38 NASA awarded a $4.5 m i l l i o n c o n t r a c t m o d i f i c a t i o n c a l l i n g f o r Boeing t o assume d e s i g n and procurement r e s p o n s i b i l i t i e s f o r c e r t a i n S-IC s t a g e s t r u c t u r a l components and i n s t r u m e n t a t i o n p r e 39 v i o u s l y p r o v i d e d by t h e government. The S-11-F/D s t a g e was l o a d e d a b o a r d a b a r g e a t KSC and 40 s h i p p e d t o MSFC/Huntsville. OCTOBER 29: OCTOBER 31: The S - I 1 s p a c e r , a s u b s t i t u t e f o r S-11-1 s t a g e of t h e SA-501 l a u n c h v e h i c l e , was e r e c t e d a t o p t h e S-IC-1 i n t h e VAB a t . KSC 41 I N OCTOBER: During t h e l a s t week of t h e month c o n t r a c t o r s i n v o l v e d i n t h e FY-1965 S a t u r n Improvement S t u d i e s gave t h e i r f i n a l p r e s e n t a t i o n s t o MSFC. The s t u d i e s , i n v o l v i n g s i x c o n t r a c t o r s and $1.6 m i l l i o n , w e r e aimed a t u p r a t i n g S a t u r n I B , S a t u r n V , and a c l a s s between t h e s e two c a l l e d " i n t e r m e d i a t e S a t u r n . ,142 - F o l l o w i n g d e - e r e c t i o n of t h e SA-5OOF v e h i c l e a t KSC t h i s month, p e r s o n n e l s t o r e d t h e S-IU-F and S-IVB-F a t KSC; c o n v e r t e d t h e S-11-F t o t h e S-11-D c o n f i g u r a t i o n and s h i p p e d i t t o MSFC; and p r e p a r e d t o 43 s h i p S-IC-F t o MAE f o r s t o r a g e . �NOVEMBER NOVEMBER 1: With p o s t - s t a t i c m o d i f i c a t i o n s and r e p a i r c o m p l e t e , C h r y s l e r p e r s o n n e l a t MAF began p o s t - s t a t i c c h e c k o u t o f t h e S-IB-7 s t a g e . I NOVEMBER 2: NASA announced e x t e n s i o n f o r a n a d d i t i o n a l 1 2 months of t h e o p e r a t i o n a l l i f e t i m e s o f t h e t h r e e Pegasus m e t e o r o i d d e t e c t i o n s a t e l l i t e s b e c a u s e of t h e i r s u c c e s s f u l o p e r a t i o n . The s a t e l l i t e s w e r e l a u n c h e d by S a t u r n I v e h i c l e s on F e b r u a r y 1 6 , May 27, and J u l y 30, 1965. A l l had been s c h e d u l e d t o o p e r a t e 1 8 months. 2 - The S-IU-501 was e r e c t e d i n t h e VAB, one day a f t e r s t a c k i n g of t h e 3 S-IVB-501 a s p a r t of t h e SA-501 v e h i c l e . ~ ~ ~ / H u n t s v i pl el res o n n e l s t a r t e d s t r u c t u r a l f a b r i c a t i o n of S-IU-208. NOVEMBER 5: 4 A b l a s t o c c u r r e d i n t h e LH2 v e n t l i n e a t MTF T e s t S t a n d A-2 where S-11-1 s t a g e was b e i n g p r e p a r e d f o r a c c e p t a n c e f i r i n g t e s t s . The e x p l o s i o n d e s t r o y e d a b o u t 8 0 f e e t of t h e 2 4 - i n c h v e n t l i n e and 5 f o r c e d f o r e i g n m a t e r i a l i n t o t h e LH2 t a n k of t h e s t a g e . NOVEMBER 7: NASA f o r m a l l y a c c e p t e d S-IU-502 from t h e m a n u f a c t u r e r , I B M , 6 f o l l o w i n g s a t i s f a c t o r y c o m p l e t i o n of c h e c k o u t on November 3 . NOVEMBER 8: KSC p e r s o n n e l a t LC-39 a p p l i e d power t o t h e S-IC-1 s t a g e s t a c k e d i n t h e VAB. 7 - I n t h e Beta 3 T e s t S t a n d a t SACTO undergoing m o d i f i c a t i o n work and p a r t s i n s t a l l a t i o n s i n c e October 1 4 , t h e S-IVB-503 had performance v e r i f i c a t i o n completed and power t u r n e d on f o r subsystem c h e c k o u t 8 and p r e p a r a t i o n f o r f i r i n g t e s t s . �NOVEMBER 1 0 : G e n e r a l E L e c t r i c Company's M i s s r l e and Space D i v i s i o n had r e c e i v e d a 1 ~ - m u x i t h , $14 .884 c o n t r a c t f-om MSFC t o s t u d y e l e c t r i c p r o p u l s i o n c o n ~ e p t sf o r system. - low a c c e l e r a t i o n s p a c e t r a n s p o r t a t i o n 9 The S-11-F/D, which was s h i p p e d from KSC on O c t o b e r 29 f o l l o w i n g com- p l e t i o n o f SA-500F c h e c k o u t , a r r i v e d a t MSFC f o r t e s t i n g i n t h e 10 S a t u r n V Dynamic T e s t S t a n d . NOVEMBER 1 2 : MAE was h o s t t o a p p r o x i m a t e l y 1 8 , 0 0 0 v i s i t o r s a t t h e a n n u a l 11 NASA-contractor open h o u s e e v e n t . - P e r s o n n e l a t t h e MSFC S a t u r n V Dynamic T e s t S t a n d c o m p l e t e d l o n g i t u d 12 i n a l t e s t i n g o f t h e S-IC-D s t a g e . NOVEMBER 15: Boeing p e r s o n n e l a t MSFC/Huntsville s u c c e s s f u l l y f i r e d t h e S-IC-3 s t a g e f o r 121.5 s e c o n d s . A l l s y s t e m s f u n c t i o n e d w e l l and no major problems were encountered. T h i s was t h e l a s t p l a n n e d f i r i n g 13 o f a n S-IC s t a g e a t H u n t s v i l l e . NOVEMBER 16: A s h o r t - d u r a t i o n f i r i n g ( 3 5 s e c o n d s ) o f S-IB-8 o c c u r r e d a t MSFC, a p p r o x i m a t e l y f o u r weeks a h e a d of s c h e d u l e . 1 4 NOVEMBER 1 7 : S-11-1 s t a g e LH2 t a n k c l e a n u p a n d c l o s e o u t ended a t MTF T e s t S t a n d A-2, where a n e x p l o s i o n November 5 c a u s e d c o n t a m i n a t i o n 15 of t h e t a n k . NOVEMBER 1 7 : NASA announced s e v e r a l c h a n g e s i n t h e A p o l l o I S a t u r n manned s p a c e f l i g h t s c h e d u l e , b e c a u s e of l a u n c h v e h i c l e and s p a c e c r a f t development problems. c r a f t (AS-205), date set. The second manned f l i g h t of a n A p o l l o s p a c e - s c h e d u l e d f o r s p r i n g 1 9 6 7 , was p o s t p o n e d and n o new The AS-205 prime c r e w - - W a l t e r M . S c h i r r a , Donn F . E i s e l e �and Walter Cunningham--became the backup crew for the AS-204 mission. AS-204, the first manned ApoPlo flight, was scheduled for the first 16 quarter of 9967. NOVEMBER 18: Boeing personnel completed installation the S-IC-5 F-1 engines; this task had been in progress since October 18 at MAF. 17 NOVEMBER 19: 18 IBM completed checkout of S-IU-206 at Huntsville. NOVEMBER 21: MSFC announced it had ordered 30 additional F-1 engines and related services from Rocketdyne Division of North American. The order completed the requirements for the 15 scheduled Saturn V boosters. Cost was estimated at $141 million. ,FJ1engines purchased 19 to date totalled 106. - S-IC-3 was removed from the MSFC S-IC Test Stand for return to MAF. 20 - MSFC presented to NASA Headquarters a summary of information from the FY-1965 Saturn Improvement Studies. These studies were performed by United Technology Corporation, NAA, Boeing, Douglas, Chrysler, and Aerojet-General.21 NOVEMBER 21-22: Boeing personnel at Huntsville stacked the S-11-F/D stage on the S-IC-D stage in the Saturn V Dynamic Test Facility without major problems. 22 November 19. S-11-F/D had been moved to the facility NOVEMBER 22: Vehicle "power on" was accomplished during checkout of SA-501 in the VAB at KSC'S LC-39.23 - The IU structural subcontractor delivered to IBM the structural seg24 ments of S-IU-209. �NOVEMBER 22: A t a NASA b i d d e r s ' c o n f e r e n c e a t MAF today r e p r e s e n t a t i v e s of 17 s h i p b u i l d i n g f i r m s i n s p e c t e d t h e b a r g e Orion w i t h a view t o m o d i f y i n g t h e v e s s e l t o accommodate S a t u r n V s t a g e s . 25 NOVEMBER 23: NASA had a u t h o r i z e d Perkin-Elmer C o r p o r a t i o n and C h r y s l e r t o c o n t i n u e f o r n i n e a d d i t i o n a l months t h e i r s t u d i e s o f o p t i c a l technology f o r f u t u r e extended Apollo f l i g h t s . 26 t h e p a r a l l e l $250,000 c o n t r a c t e x t e n s i o n s . NOVEMBER 25: MSFC would manage MSFC o b t a i n e d b e n e f i c i a l occupancy of t h e S a t u r n S u p p o r t T e s t Area h i g h - p r e s s u r e g a s and p r o p e l l a n t s s y s t e m . 27 c o m p l e t e e x c e p t f o r minor d e f i c i e n c e s . NOVEMBER 27: The j o b was The S-IC-3, which was s h i p p e d on t h e Poseidon from MSFCI H u n t s v i l l e on November 22 a f t e r a c c e p t a n c e f i r i n g , a r r i v e d a t MAF 28 f o r r e f u r b i s h m e n t and p o s t - s t a t i c c h e c k o u t . NOVEMBER 28: NASA awarded f o u r c o n t r a c t s t o t a l l i n g $825,000 f o r s t u d i e s of methods t o e x p l o r e t h e p l a n e t s and t o d e s i g n advanced l a u n c h vehicles. R e c e i v i n g c o n t r a c t s were: Lockheed M i s s i l e s and Space Company, $200,000; Boeing Company, $150,000; L o c k h e e d - C a l i f o r n i a Company, $250,000; and NAA, $225,000. 29 manage t h e c o n t r a c t s . - NASA H e a d q u a r t e r s would NASA announced t h a t i t would n e g o t i a t e a c o n t r a c t w i t h Bendix f o r development and p r o d u c t i o n of a p o i n t i n g c o n t r o l s y s t e m f o r t h e A p o l l o T e l e s c o p e Mount. Bendix would produce t h r e e u n i t s under d i r e c t i o n of MSFC a t a c o s t of a b o u t $6.9 m i l l i o n . 3 0 NOVEMBER 29: The forward bulkhead of t h e S-11-3 s t a g e ' s LH2 t a n k was damaged when a l a d d e r f e l l w h i l e t h e s t a g e was i n a h o r i z o n t a l 31 p o s i t i o n f o r i n - t a n k systems i n s t a l l a t i o n a t S e a l Beach. �NOVEMBER 29: C h r y s l e r p e r s o n n e l a t MSFC s u c c e s s f u l l y s t a t i c - f i r e d f o r 145 s e c o n d s t h e S-IB-8 s t a g e . The S-IB-8 was t o f l y a s t h e b o o s t e r o f t h e e i g h t h Uprated S a t u r n I l a u n c h v e h i c l e . 32 NOVEMBER 30: - The S-IVB-207 s t a g e a c c e p t a n c e m e e t i n g was h e l d a t SACTO. 3 3 P e r s o n n e l a t MSFC s a t i s f a c t o r i l y performed a t e c h n i c a l d e m o n s t r a t i o n of t h e h y d r a u l i c l o a d s i m u l a t o r s on t h e S a t u r n V SDF a f t e r s t a r t i n g 34 f u n c t i o n a l c h e c k o u t of t h e s i m u l a t o r s on O c t o b e r . 2 6 . I N NOVEMBER: MSFC D i r e c t o r Wernher von Braun announced management o r g a n i z a t i o n t o d i r e c t t h e Apollo T e l e s c o p e Mount ( A m ) p r o j e c t : L e l a n d Belew, Program Manager; Rein I s e , P r o j e c t Manager; W i l l i a m K e a t h l e y , P r o j e c t Experiments D i r e c t o r ; E . B . C r a i g , C o n t r a c t i n g Officer; D r . Ernst Stuhlinger, Project Scientist. The MSFC A s t r i o n i c s L a b o r a t o r y would be r e s p o n s i b l e f o r o v e r a l l t e c h n i c a l a s p e c t s of t h e 35 ATM development. �D E C E M B E R DECEMBER 1: 1 9 6 6 Boeing p e r s o n n e l a t Michoud s u c c e s s f u l l y completed p o s t - m a n u f a c t u r i n g c h e c k o u t of S-IC-4 b e f o r e s t o r i n g t h e s t a g e . - 1 The S - I 1 common bulkhead t e s t t a n k (CBTT) a t S a n t a Susana f a i l e d d u r i n g an u l t i m a t e h y d r o s t a t i c p r e s s u r e t e s t . The LH2 t a n k b u l k - head and w a l l c o l l a p s e d , l e a v i n g i n t a c t t h e LOX t a n k and common bulkhead p o r t i o n of t h e t e s t a r t i c l e . An i n v e s t i g a t i o n concluded t h a t t h e f a i l u r e began w i t h a p r i o r c r a c k a t a f i t t i n g on t h e LH2 tank wall. - F o l l o w i n g c o m p l e t i o n of S-11-1 p r e s t a t i c c h e c k o u t and m o d i f i c a t i o n e f f o r t s , workmen a t MTF performed a f u l l - d u r a t i o n f i r i n g l a s t i n g 384 s e c o n d s . 3 - NASA e x t e n d e d f o r one y e a r a n a i r t r a n s p o r t c o n t r a c t between Aero S p a c e l i n e s and MSFC. The c o n t r a c t , w i t h e s t i m a t e d v a l u e of $2.5 m i l l i o n , c o n t i n u e d t h e s e r v i c e s of t h e Super Guppy and P r e g n a n t Guppy a i r p l a n e s f o r t r a n s p o r t i n g major S a t u r n hardware. 4 - F i n a l d e l i v e r y of SA-501 t e s t program t a p e s from t h e S a t u r n V SDF a t MSFC t o KSC o c c u r r e d . ' DECEMBER 3: Assembly c o m p l e t i o n of t h e SA-500D dynamic t e s t v e h i c l e a t MSFC o c c u r r e d w i t h s t a c k i n g of t h e A p o l l o Command Module, S e r v i c e Module, and Launch Escape System. S-IVB-D s t a g e s t a c k i n g had ended November 30, and assembly of o t h e r s p a c e c r a f t components on Decem6 b e r 1. DECEMBER 4: S-IVB-208 s t a g e a r r i v e d a t SACTO f o r a c c e p t a n c e t e s t i n g . ' �Workmen a t SACTO i n s t a l l e d S-IVB-208 s t a g e i n Beta 1 T e s t 8 Stand f o r a c c e p t a n c e t e s t i n g . DECEMBER 5: - - Post-manufacturing checkout of S-IC-4 s t a g e ended a t MAF w i t h o u t major 9 problems. I n s t a l l a t i o n of i n s u l a t i o n , which had been i n p r o g r e s s on S-IVB-505 tankage throughout November, ended a t Douglas' Huntington Beach 10 plant. DECEMBER 7: Under an eight-month NASA c o n t r a c t Douglas would develop d e s i g n r e q u i r e m e n t s f o r a s m a l l modular space l a b o r a t o r y . The proposed l a b o r a t o r y would r e p l a c e t h e d e s c e n t s t a g e of t h e Apollo Lunar Module. MSFC. DECEMBER 8: - The $344,000 s t u d y c o n t r a c t would be managed by 11 I B M s t a r t e d s t r u c t u r a l assembly of S-IU-8. 12 MSFC shipped t h e S-IB-8 s t a g e t o MAF f o l l o w i n g completion of s t a t i c firing. 13 - I B M p e r s o n n e l a t H u n t s v i l l e completed f a b r i c a t i o n of S-IU-208 and 14 began component assembly. NASA e x e r c i s e d a one-year renewal o p t i o n w i t h Ling-Temco-Vought p r o v i d e computer s u p p o r t s e r v i c e s f o r MAF. 15 c o s t $2.7 m i l l i o n . DECEMBER 9: F a c t o r y checkout of S-IVB-504, Beach October 4 , ended s u c c e s s f u l l y . 16 to The c o n t r a c t e x t e n s i o n which began a t Huntington �The S-IC-F a r r i v e d a t MAF aboard t h e b a r g e Poseidon from KSC t o be s t o r e d pending f u r t h e r need. 1 7 DECEMBER 10: DECEMBER 12: MSFC t e c h n i c i a n s completed t h e l o n g - d e l a y e d p o s t - s t a t i c c h e c k o u t of S-IC-2, d i s c o n n e c t e d t h e s t a g e from power, and t u r n e d i t o v e r t o ME L a b o r a t o r y f o r i n c o r p o r a t i o n o f changes and m o d i f i c a 18 tions. DECEMBER 13: f o r KSC. - - The S-IB-6 s t a g e l e f t MAF a b o a r d t h e b a r g e Palaemon bound 19 S-IB-8 a r r i v e d a t MAF from H u n t s v i l l e f o r p o s t - s t a t i c m o d i f i c a t i o n s 20 and c h e c k o u t . Douglas s h i p p e d t h e S-IVB-206 s t a g e t o KSC f o l l o w i n g c o m p l e t i o n of 21 p o s t - f i r i n g c h e c k o u t and m o d i f i c a t i o n s a t Huntington Beach. DECEMBER 14: Boeing d e d i c a t e d i t s I n d u s t r i a l R e s e a r c h C e n t e r a t F e a t u r e d s p e a k e r was D r . Edward C . Welsh, E x e c u t i v e S e c r e t a r y o f t h e N a t i o n a l A e r o n a u t i c s and Space C o u n c i l . 2 2 Huntsville. DECEMBER 14: - S-IVB-206 s t a g e a r r i v e d a t KSC. 2 3 I B M completed assembly of S-IU-207. DECEMBER 15: 24 The S - I 1 i n t e r s t a g e p o r t i o n of t h e S-IC/S-I1 i n t e r f a c e t e s t specimen f a i l e d a t MSFC's Load T e s t Annex d u r i n g d e s i g n l i m i t 25 l o a d i n g a t 127 p e r c e n t d e s i g n l i m i t l o a d . - Checkout of S-IU-207 began a t I B M ' s Huntsville plant. 26 �Boeing moved t h e S-IC-4 s t a g e a t MAF i n t o s t o r a g e f o l l o w i n g DECEMBER 16: c o m p l e t i o n of p o s t - m a n u f a c t u r i n g c h e c k o u t and i n c o r p o r a t i o n of 27 changes. - With assembly of S-IC-5 c o m p l e t e d , Boeing p e r s o n n e l a t MAF moved t h e s t a g e i n t o t h e Checkout B u i l d i n g f o r p o s t - m a n u f a c t u r i n g c h e c k o u t . 2 8 - F a c t o r y c h e c k o u t of S-IVB-504 s t a g e , which began October 1 0 a t Hunt29 i n g t o n Beach, was completed a s p l a n n e d . - The Super Guppy a i r c r a f t d e l i v e r e d S-IU-206 t o KSC, t h r e e d a y s ahead 30 of s c h e d u l e . - SLID completed a s e r i e s of 159 b o a t t a i l e n v i r o n m e n t a l t e s t s on t h e S - I 1 B a t t l e s h i p a t S a n t a Susana. These t e s t s d e t e r m i n e d t h e con- d i t i o n s under which t h e LOX system would remain s u b c o o l e d from p r e l a u n c h t h r o u g h S - I 1 e n g i n e s t a r t . 31 DECEMBER 17: T e c h n i c i a n s a t MTF removed t h e S-IC-T a l l - s y s t e m s t e s t s t a g e from s t o r a g e and p l a c e d i t i n S-IC S t a g e T e s t P o s i t i o n B-2 f o r s t a t i c f i r i n g t e s t preparations. P e r s o n n e l began e l e c t r i c a l and m e c h a n i c a l hookup of t h e s t a g e . 32 DECEMBER 1 8 : The S-IB-6 s t a g e a r r i v e d a t KSC from MAF a b o a r d t h e b a r g e Palaemon. 3 3 A s p e c i a l s e m i - t o r o i d a l t a n k , f a b r i c a t e d by ME Lab a s a n DECEMBER 19: e x p e r i m e n t a l c o n f i g u r a t i o n , was d e l i v e r e d t o P&VE Lab f o r s t r u c t u r a l 34 testing . DECEMBER 20: NASA announced a c o n t r a c t m o d i f i c a t i o n w i t h C h r y s l e r c o v e r - i n g l o n g - l e a d - t i m e i t e m s f o r a d d i t i o n a l Uprated S a t u r n I b o o s t e r s �(S-IB s t a g e s ) . The $ 7 . 2 m i l l i o n supplemental agreement t o C h r y s l e r ' s b a s i c c o n t r a c t a u t h o r i z e d t h e c o n t r a c t o r t o provide m a t e r i a l s , components and e n g i n e e r i n g s u p p o r t n e c e s s a r y t o m a i n t a i n i t s c a p a b i l i t y t o assemble f o u r S-IB s t a g e s a y e a r f o l l o w i n g completion of t h e 12 scheduled v e h i c l e s . 35 DECEMBER 20: The l a s t of 1 3 t e s t f i r i n g s s i n c e J u l y 1 of t h e S-IVB B a t t l e s h i p s t a g e a t MSFC was performed. was 281.14 seconds. F i r i n g time f o r t h i s t e s t O f f i c i a l s noted achievement of a number of major t e s t o b j e c t i v e s i n t h e six-month p e r i o d . 3 6 DECEMBER 21: With a p p r o v a l from MSFC, S&ID p e r s o n n e l a t SSFL began t h e S - I 1 B a t t l e s h i p m o d i f i c a t i o n s n e c e s s a r y t o p r e p a r e f o r a new s e r i e s 37 of s t a t i c - f i r i n g t e s t s . - Post-manufacturing checkout of S-IC-5 began i n t h e S t a g e T e s t . B u i l d i n g a t MAF. 38 DECEMBER 22: The countdown f o r t h e scheduled second f u l l - d u r a t i o n s t a t i c t e s t of S-11-1 began a t MTF. A t 1 0 p.m. a l l e n g i n e s s t a r t e d b u t a u t o m a t i c c u t o f f came immediately. 1.5 seconds. 39 DECEMBER 23: The u n s u c c e s s f u l t e s t l a s t e d MSFC r e c e i v e d t h e N a t i o n a l S a f e t y C o u n c i l ' s Award of Honor f o r having worked over 5 m i l l i o n man-hours w i t h o u t a d i s a b l i n g 40 i njury. - NASA had awarded General E l e c t r i c a c o n t r a c t e x t e n s i o n of $22.3 million t o continue i n i t s fourth year as general support contractor f o r MTF. The GE s u p p o r t c o n t r a c t a t MTF began i n June 1963. new c o n t r a c t covered t h e p e r i o d November 1966 t o J u l y 1967. 41 The �DECEMBER 27: Boeing p e r s o n n e l a t MAF a p p l i e d power t o t h e S-IC-5 s t a g e t o commence post-manufacturing checkout. 42 DECEMBER 28: NASA announced m o d i f i c a t i o n of t h e Douglas S-IVB s t a g e c o n t r a c t t o p r o v i d e long-lead-time hardware f o r a d d i t i o n a l S a t u r n I B v e h i c l e s . The $6.3 m i l l i o n c o n t r a c t r e v i s i o n would extend through June 1967. The a c t i o n would permit MSFC t o o r d e r a d d i t i o n a l S-IVB s t a g e s w i t h o u t d e l a y i f f u r t h e r v e h i c l e m i s s i o n s were a s s i g n e d a f t e r t h e 12 v e h i c l e s c u r r e n t l y scheduled. 4 3 - With S-IU-503 component assembly o p e r a t i o n s complete, I B M moved t h e u n i t t o t h e checkout s t a n d f o r l e a k t e s t of t h e environmental c o n t r o l system and t h e gaseous n i t r o g e n system. 44 DECEMBER 29: Douglas t e c h n i c i a n s a t Huntington Beach completed h i g h p r e s s u r e l e a k checks of t h e S-IVB-504 s t a g e and moved t h e s t a g e t o a n o t h e r assembly tower f o r f i n a l i n s t a l l a t i o n s . 45 DECEMBER 30: MSFC awarded Douglas A i r c r a f t Company a $300,000 nine-month c o n t r a c t t o a n a l y z e t h e needs of an o r b i t a l s u p p o r t f a c i l i t y f o r f u t u r e a s t r o n o m i c a l r e s e a r c h from s p a c e . R e s u l t s of t h e s t u d y c o u l d be used f o r s p a c e programs f o l l o w i n g t h e Apollo Telescope Mount (ATPI) 46 program. - S t a t u s of S-IC-6 s t a g e assembly a t MAF: V e r t i c a l assembly was com- p l e t e and t h e h a n d l i n g r i n g was undergoing t e s t i n p r e p a r a t i o n f o r s t a g e "lay-down" e a r l y i n 1967. 4 7 - S-11-1 s t a g e underwent i t s second s u c c e s s f u l f u l l - d u r a t i o n a c c e p t a n c e t e s t a t MTF, t h u s completing t h e a c c e p t a n c e t e s t program. 48 �IN DECEMBER: Wyle Laboratories, Huntsville, completed several tests in the S-I1 Stage high-force test program. Following completion of the thrust complex first-axis lateral testing on November 30, Wyle personnel completed second-axis lateral testing on December 6 and third-axis testing December 21. Vibration testing of the forward skirt ended December 15.49 - MSFC accepted beneficial occupancy of the S-IC Test Position B-2 at MTF. GSE installation was nearly complete.50 �J A N U A R Y 1. Michoud Assembly F a c i l i t y , H i s t o r i c a l R e p o r t , J a n u a r y 1, 1966 December 3 1 , 1966, p. 42. - 2 . North American A v i a t i o n , I n c . , Space and I n f o r m a t i o n Systems D i v i s i o n , S a t u r n S - I 1 S t a g e Monthly P r o g r e s s R e p o r t , J a n u a r y 1966, p. 2 . 3. MSFC P u b l i c A f f a i r s O f f i c e , P r e s s R e l e a s e 65-307, December 1 7 , 1965. 4 . MSFC P r o p u s l i o n and V e h i c l e E n g i n e e r i n g L a b o r a t o r y , Monthly P r o g r e s s R e p o r t f o r P e r i o d J a n u a r y 1, 1966, Through J a n u a r y 31, 1966, p. 6 . 5. PAO, P r e s s R e l e a s e 66-1, J a n . 3 , 1966. 6. PA0,'Press R e l e a s e 66-2, J a n . 4 , 1966. 7. PAO, P r e s s R e l e a s e 66-3, J a n . 4 , 1966. 8. MSFC S a t u r n V Program O f f i c e , Q u a r t e r l y P r o g r e s s R e p o r t f o r J a n u a r y 1-March 31, 1966, p . 42. 9. S a t . V Prog. O f f . , S a t V QPR, J a n . 1 - Mar. 31, 1966, p. 8. 1 0 . MSFC T e s t L a b o r a t o r y , P r o g r e s s R e p o r t , December 1 2 , 1965--January 1 2 , 1966, p. 25. 11. H. Memo, Davis E. Foxworthy, C h i e f , T e c h n i c a l S e r v i c e s O f f i c e , t o H. Gorman, Deputy D i r e c t o r , A d m i n i s t r a t i v e , s u b j . , "Flash R e p o r t , " J a n . 1 4 , 1966. 12. Douglas A i r c r a f t Company, S a t u r n S-IVB Monthly T e c h n i c a l P r o g r e s s R e p o r t , J a n u a r y 1966, p. 49. 13. Ibid., pp. 49-50. 14. NAA, 15. PAO, P r e s s R e l e a s e 66-16, J a n . 1 3 , 1966. 16. S a t . V Prog. O f f . , S a t . V QPR, J a n . 1 17. I b i d . , p. 8 . 18. I b i d . , p. 22. S - I 1 MPR, J a n . 1966, p. 45. - 1 9 . PAO, P r e s s R e l e a s e 66-18, J a n . 1 4 , 1966. Mar. 31, 1966, p. 8. �January (Cont'd) 20. DAC, S-IVB MTPR, J a n . 1 9 6 6 , p . 1. 21. S a t . V Prog. Off., 22. DAC, S-IVB MTPR, J a n . 1 9 6 6 , p . 1. 23. S a t . V Prog. Off., 24. Ibid., 25. I b i d . , p. 1 2 . 26. T e s t L a b . MPR f o r J a n . 1 2 27. Ibid., 28. S a t . V Prog. Off., 29. Ibid., 30. I b i d . , p . 22. 31. PAO, P r e s s R e l e a s e 6 6 - 2 3 , J a n . 2 0 , 1 9 6 6 . 32. S a t . V Prog. Off., 33. I b i d . , p. 1 3 . S a t V QPR, J a n . 1 - Mar. 3 1 , 1 9 6 6 , p . 18. S a t V QPR, J a n . 1 - Mar. 3 1 , 1 9 6 6 , p . 1 0 . p . 11. - Feb. 1 2 , 1 9 6 6 , p . 1. p p . 26-27. S a t V QPR, J a n . . l - Mar. 31, 1 9 6 6 , p . 38. p. 10. S a t V QPR, J a n . 1 - Mar. 3 1 , 1 9 6 6 , p. 38. 3 4 . PAO, P r e s s R e l e a s e 66-24, J a n . 2 1 , 1 9 6 6 ; a n d Memo, D r . Wernher von B r a u n , D i r e c t o r , MSFC, t o D i s t r i b u t i o n , s u b j . " P e r s o n n e l A p p o i n t m e n t s , P&VE L a b o r a t o r y , " J a n . 2 1 , 1 9 6 6 . 35. P&VE L a b . , MPR f o r J a n . 1 9 6 6 , p . 5 . 36. PAO, P r e s s R e l e a s e 66-25, J a n . 24, 1 9 6 6 . 37. S a t . V Prog. Off., 38. Ibid., 39. I b i d . , p. 8 . 40. P&VE L a b . , MPR f o r J a n . 1 9 6 6 , p . 28. 41. S a t . V Prog. Off., S a t V QPR, J a n . 1 - Mar..31, - Mar. 3 1 , 1 9 6 6 , p . 2 3 . 1 9 6 6 , p . 11. p. 22. S a t V QPR, J a n . 1 �January (Cont'd) 42. Ibid., p . 39. 43. I b i d . , p . 25. 44. PAO, P r e s s R e l e a s e 6 6 - 2 7 , J a n . 2 8 , 1 9 6 6 . 45. NAA, S - I 1 MPR, J a n . 1 9 6 6 , p . 2 5 . 46. S a t . V Prog. O f f . , 47. Ibid., p. 19. S a t V QPR, J a n . 1 - Mar. 31, 1 9 6 6 , p. 11. �F E B R U A R Y 1. MAF, H i s t . R p t . 1 9 6 6 , p . 2 . 2. S a t . V Prog. Off., 3. PAO, P r e s s R e l e a s e 66-32, Feb. 3 , 1966. 4. P&VE L a b . , MPR f o r F e b r u a r y 1 9 6 6 , p . 34. 5. S a t . V Prog. Off., S a t . V QPR, J a n . 1 S a t V QPR, J a n . 1 - - Mar, 31. 1 9 6 6 , p. 36 Mar. 3 1 , 1 9 6 6 , p . 1 2 . 7. Memo, B i l l H. S n e e d , C h i e f , S a t u r n V Program C o n t r o l O f f i c e , MSFC, t o C h i e f , A p o l l o Program P l a n n i n g , NASA, s u b j . , " S a t u r n V Weekly R e p o r t No. 5 7 , " Feb. 7 , 1966. 8. P&VE L a b . , MPR f o r Feb. 1966, p . 34. 9. M i s s i s s i p p i T e s t F a c i l i t y , H i s t o r y o f t h e Year 1 9 6 6 , p . 1 4 . S a t V QPR, J a n . 1 - Mar. 3 1 , 1 9 6 6 , p. 8. 10. Sat. 11. DAC, S-IVB MTPR, Feb. 1 9 6 6 , p . 35. 12. Sat. V 13. w.,p . 14. PAO, P r e s s R e l e a s e 66-42, Feb. 1 7 , 1966. 15. T e s t L a b . , MPR f o r Feb. 12 16. S a t . V Prog. Off., 17. w.,p . 19. T e s t Lab., MPR f o r Feb. 1 2 20. NAA, S - I 1 MPR f o r Feb. 1 9 6 6 , p. 38. 21. S a t . V Prog. Off., 22. w.,p . V Prog. Off., P r o g . O f f . , S a t . V QPR, J a n . 1 - Mar. 3 1 , 1 9 6 6 , p. 38. 11. - Mar. 1 2 , 1 9 6 6 , p . 25. S a t . V QPR, J a n . 1 - Mar. 31, 1 9 6 6 , p. 27. 23. 36. - Mar. 1 2 , 1 9 6 6 , p . 26. S a t . V QPR, J a n . 1 - Mar. 31, 1 9 6 6 , p . 11. �February (Cont'd) 23. T e s t L a b . , MPR f o r Feb. 1 2 - Mar. 1 2 , 1 9 6 6 , p . 2 6 . 2 4 . NASA S P - 4 0 0 7 , A s t r o n a u t i c s and A e r o n a u t i c s , 1966, Chronology on S c i e n c e , T e c h n o l o p y , and P o l i c y , p . 67; and MSFC PAO, M a r s h a l l S t a r , Mar. 2 , 1 9 6 6 , p . 1. 25. DAC, S-IVB MTPR, Feb. 1 9 6 6 , pp. 1 & 35. 26. S a t . V Prog. O f f . , 27. DAC, S-IVB MTPR, Feb. 1 9 6 6 , p. 5 0 . 28. T e s t L a b . , MPR f o r F e b . 1 2 29. S a t . V Prog. O f f . , 30. Ibid., p. 19. S a t . V QPR, J a n . 1 - - Mar. 3 1 , 1 9 6 6 , p. 1 9 . Mar. 1 2 , 1 9 6 6 , p. 1. S a t . V QPR, J a n 1 - Mar. 3 1 , 1 9 6 6 , p. 1 3 . �M A R C H 1. MSFC M a n u f a c t u r i n g E n g i n e e r i n g Lab., ME L a b o r a t o r y H i s t o r i c a l Q u a r t e r l y R e p o r t , J a n u a r y - March 1966 ( d r a f t ) . 2. Ibid. - 3. MAF, H i s t . Rpt. 1966, p. 2 , 4. S a t . V Prog. O f f . , 5. T e s t L a b . , MPR f o r Feb. 12 6. S a t . V Prog. O f f . , S a t . V QPR, J a n . 1 7. NAA, S - I 1 MPR, Mar. 1966, p. 2. 8. PAO, P r e s s R e l e a s e 66-49, Mar. 4 , 1966; and MAF, H i s t . Rpt. 1966, - S a t . V QPR, J a n . 1 - Mar. Mar. 31, 1966, p. 2 3 . 1 2 , 1966, p. 25. - Mar. 31, 1966, p. 43. p . 2. - S a t . V Prog. O f f . , S a t . V QPR, J a n . 1 Mar. 31, 1966, p. 1 6 . 10. NAA,, S - I 1 MPR f o r Mar. 1966, p. 2 7 . 11. NASA, A s t r o n a u t i c s and A e r o n a u t i c s , 1966, p. 88. 12. NAA, S - I 1 MPR f o r Mar. 1966, p. 5 . 13. S a t . V Prog. O f f . , 14. MAF, H i s t . Rpt. 1966, p . 31. S a t V QPR,Jan. 1 - S a t . V Prog. O f f . , S a t . V QPR, J a n . 1 16. P&VE Lab., MPR f o r Mar. 1966, p. 40. 17. S a t . V Prog. O f f . , S a t V QPR,Jan. 18. MAF, H i s t . Rpt. 1966, p. 61. 19. S a t . V Prog. O f f . , S a t V QPR,Jan. Mar. 31, 1966, p . 18. - Mar. 31, 1966, p. 23. 1 - Mar. 31, 1966, p. 38. 1 - Mar. 31, 1966, p. 25. 21. MSFC Engine Program O f f i c e , Semiannual P r o g r e s s R e p o r t , F-1, H - 1 , 5-2 and C - 1 E n g i n e s , J a n . 1, 1966 - June 30, 1966, p. 11. �March ( C o n t ' d ) - Mar. 31, 1966, p . 10. - Mar. 31, 1966, p . 12. 22. S a t . V Prog. O f f . , S a t . V QPR, J a n . 1 23. NAA, 24. DAC, S-IVB MTPR, Mar. 1966, p . 35. 25. I b i d . , p. 58. 26. S a t . V Prog. Off., 27. T e s t Lab., MPR f o r Mar. 12 28. S a t . V Prog. O f f . , S a t . V QPR, J a n . 1 29. DAC, S - I V B MTPR, Mar. 1966, p . 35. 30. PAO, M a r s h a l l S t a r , Mar. 9 , 1966, p. LO. 31. DAC, S-IVB MTPR, Mar. 1966, p. 49. 32. S a t . V Prog. O f f . , S a t . V QPR, J a n . 1 33. T e s t Lab., MPR f o r Mar. 12 34. I b i d . , p. 11. S - I 1 MPR f o r Mar. 1966, p . 2. S a t . V QPR, J a n . 1 - - Apr. 1 2 , 1966, p . 29. - - Mar. 31, 1966, p. 23. Mar. 31, 1966, p. 43. Apr. 1 2 , 1966, p. 1. 35. MAF, H i s t . Rpt. 1966, p . 3; and NASA, A s t r o n a u t i c s a n d . A e r o n a u t i c s , 1966, p. 115. NASA, A s t r o n a u t i c s and A e r o n a u t i c s , 1965, p . 114. S a t . V Prog. Off., S a t V QPR, J a n . 1 - Mar. 31, 1966, p . 10. I b i d . , p. 42. Ibid ., p . Ibid., 16. p. 42. DAC, S-IVB MTPR, Mar. 1966, p. 50. S a t . V Prog. O f f . , S a t . V QPR, J a n . 1 - Mar. 31, 1966, p . 44. Ibid., p . 25. �March ( C o n t ' d ) Ibid ., p . 25; a n d DAC, S-IVB MTPR, Mar. 1 9 6 6 , p. 37. S a t . V Prog. O f f . , S a t . V QPR, J a n . 1 - Mar. 3 1 , 1 9 6 6 , p . 23. I b i d . , p. 1 3 . PAO, P r e s s R e l e a s e 66-69, Apr. 1, 1 9 6 6 . T e s t L a b . , MPR f o r Mar. 1 2 S a t . V Prog. Off., Ibid., - Apr. 1 2 , 1 9 6 6 , p . 6 . S a t . V QPR, J a n . 1 p. 10. NAA, S - I 1 MPR, Mar. 1 9 6 6 , p p . 1 2 & 1 6 . - Mar. 3 1 , 1 9 6 6 , p . 8 . �P r e s s R e l e a s e 6 6 - 6 8 , A p r . 1, 1 9 6 6 . L. l'liO, 2. PAO, P r e s s R e l e a s e 6 6 - 6 9 , Apr. 1, 1 9 6 6 . 3. S a t . V Prog. Off., I. NAA, S - I 1 MPR, A p r . 1 9 6 6 , p. 1. 5. T e s t Lab., 6. PAO, P r e s s R e l e a s e 6 6 - 7 1 , Apr. 4 , 1 9 6 6 . 7. MTF, H i s t . o f Year 1 9 6 6 , p. 3 . 8. PAO, P r e s s R e l e a s e 6 6 - 7 4 , Apr. 5 , 1 9 6 6 . 9. DAC, S-IVB MTPR, Apr. S a t V QPR, A p r . 1 MPR f o r Mar, 1 2 - - June 30, 1966, p . 28. A p r . 1 2 , 1 9 6 6 , p.. 29. 1 9 6 6 , p. 4 6 . Jan. - 10. MAF, H i s t . R p t . , 11. DAC, S-IVB MTPR, A p r , 12. MAF, H i s t . R p t . , 13. DAC, S-IVB MTPR, Apr. 1 9 6 6 , p. 46. 14. S a t . V Prog. O f f . , 15. w.,p. 16. DAC, S-IVB MTPR, Apr. 1 9 6 6 , p. 30. 17. S a t . V Prog. O f f . , 18. I b i d . , P. 1 2 . 19. Ibid., p. 2 1 . 20. Ibid., p. 41. 21. Memo, Sneed t o NASA Hq., 22. Ibid. Jan. Dec. 1 9 6 6 , p. 3 . 1 9 6 6 , p. 30. - Dec. 1 9 6 6 , p. 3 . S a t V QPR, Apr. 1 - J u n e 3 0 , 1 9 6 6 , p. 4 0 . 21. S a t . V QPR, Apr. 1 - June 30, 1966, p. 10. " S a t . V Wkly R p t . No. 6 7 , " Apr. 1 8 , 1966 �April (Cont'd) 23. PAO, P r e s s R e l e a s e 6 6 - 7 9 , A p r . 1 9 , 1 9 6 6 . 24. S a t . V Prog. O f f . , 25. PAO, P r e s s R e l e a s e 66-83, Apr. 2 1 , 1966. 26. NAA, S - I 1 MPR, Apr. 1 9 6 6 , p. 1. 27. Ibid. 28. DAC, S-IVB MTPR, Apr. 1 9 6 6 , p . 3 3 . 29. S a t . V Prog. O f f . , 30. ME L a b . , S a t . V QPR, Apr. 1 S a t . V QPR, Apr. 1 H i s t . Qtrly. Rpt., Apr. - - - J u n e 3 0 , 1 9 6 6 , p. 2 1 . June 30, 1966, p. 23. June 1966, ( d r a f t ) . 3 1 . S a t . V F r o g . O f f . , S a t . V QPR, Apr. 1 - J u n e 30, 1 9 6 6 , p . 2 6 ; a n d T e s t L a b . , MPR f o r Mar. 1 2 - Apr. 1 2 , 1 9 6 6 , p. 7 , a n d A p r . 1 2 - May 1 2 , 1 9 6 6 , p. 4 . 32. P&VE L a b , MPR f o r A p r . 1 9 6 6 , p. 2 4 . 33. P&VE L a b , S u p p l e m e n t t o MPR f o r A p r . 1 9 6 6 , p. 9 . 3 4 . T e s t L a b , MPR f o r Mar. 12 - Apr. 1 2 , 1 9 6 6 , p . 6 ; a n d Apr. 1 2 May 1 2 , 1 9 6 6 , p . 3 . 35. S a t . V Prog. O f f . , S a t . V QPR, Apr. 1 - J u n e 3 0 , 1 9 6 6 , p . 31. - �1. xemo, Sneed t o NASA Hq., "Sat. V Wkly-Rpt. NO. 69,"May - 2. T e s t L a b . , MPR f o r Apr. 1 2 3. DAC, S-IVB MTPR, May 1 9 6 6 , p . 1. 4. NASA, A s t r o n a u t i c s and A e r o n a u t i c s , 1 9 6 6 , pp. 165-166. 5. T e s t L a b . , MPR f o r Apr. 1 2 6. PAO, P r e s s R e l e a s e No. 66-92, May 5 , 1 9 6 6 . 7. PAO, P r e s s R e l e a s e So. 6 6 - 9 6 , May 6 , 1 9 6 6 . 8. PAO, P r e s s R e l e a s e No. 6 6 - 9 1 , May 6 , 1 9 6 6 . 9. S a t . V Prog. Off., - May 1 2 , 1 9 6 6 , p . 4 . May 1 2 , 1 9 6 6 , p . 4. S a t . V QPR, A p r . 1 - 10. PAO, P r e s s R e l e a s e 6 6 - 9 5 , May 6 , 1 9 6 6 . 11. S a t . V Prog. O f f . , 12. DAC, S-IVB MTPR, May 1 9 6 6 , p. 2 . 13. ME L a b . , 14. Memo, Sneed t o NASA H q . , 15. S a t . V Prog. Off., 16. Ibid 17. DAC, S-IVB MTPR, May 1 9 6 6 , p . 2 . 18. NAA, S - I 1 MPR, May 1 9 6 6 , p . 23. 19. S a t . V Prog. Off., 20. w. 21. Ibid., 22. S a t . V Prog. Off., 23. NAA, S - I 1 MPR, May 1 9 6 6 , p . 1. ., S a t . V QPR, Apr. 1 H i s t . Q t r l y . Rpt., 2 , 1966. Apr. - J u n e 3 0 , 1 9 6 6 , p . 40. - J u n e 30, 1 9 6 6 , p. 2 9 . J u n e 1966 ( d r a f t ) . " S a t . V Wkly. R p t . No. 7 1 , " May 1 6 , 1 9 6 6 . S a t . V QPR, Apr. 1 - June 30, 1966, p. 12. - June 30, 1966, p. 14. p. 12. p..19; S a t . V QPR, Apr. 1 a n d MTF, H i s t . o f Year 1 9 6 6 , p . 3. S a t . V QPR, Apr. 1 - J u n e 30, 1966, p. 27. �May ( C o n t ' d ) - June 30, 1966, p . 1 9 . - J u n e 30, 1 9 6 6 , p p . 4 & 6 . 2%. S a t . V P r o g . O f f . , S a t . V QPR, A p r . 1 25. I b i d . , p . 29. 26. MTF, H i s t . o f Year 1 9 6 6 , p . 1 4 . 27. DAC, S-IVB MTPR, May 1 9 6 6 , p . 2 . 28. S a t . V P r o g . O f f . , S a t . V QPR, A p r . 1 29. Ibid., 30. PAO, P r e s s R e l e a s e 66-119, May 2 5 , 1 9 6 6 . 31. S a t . V Prog. Off., 32. Ibid., 33. PAO, P r e s s R e l e a s e 66-122, May 2 7 , 1966. 34. S a t . V P r o g . O f f . , S a t . V QPR, A p r . 1 35. Ibid. - 36. MTF, H i s t . o f Year 1 9 6 6 , p . 1 4 . 37. I b i d . , p . 4. 38. Memo, Sneed t o NASA Hq., " S a t . V Wkly. R p t . No. 6 9 , " May 2 , 1 9 6 6 . 39. T e s t L a b . , MPR f o r May 1 2 40. Lbid., - 41. NAA, S - I 1 MPR, May 1 9 6 6 , p . 1. 42. S a t . V Prog. O f f . , 43. DAC, S-IVB MTPR, May 1 9 6 6 , p . 4 1 . p . 19. S a t V QPR, Apr. 1 - J u n e 3 0 , 1 9 6 6 , p. 2 9 . p . 14. - - June 30, 1966, p . 19. J u n e 1 2 : 1 9 6 6 , p . 1. pp. 3 & 4 . S a t . V QPR, A p r . 1 - J u n e 30, 1 9 6 6 , p . 31. 4 4 . NAA, S - I 1 MPR, May 1 9 6 6 , p . 2 ; and S a t . V P r o g . O f f . , S a t . V QPR, Apr. 1 - J u n e 30, 1966, p . 18. �1. DAC, S-IVB MTPR, J u n e 1 9 6 6 , p . 40. 2. I b i d . , p . 43. 3. S a t . V Prog. Off., 4. Ibid 5. I b i d . , P. 11. 6. PhVE L a b . , MPR f o r J u n e 1 9 6 6 , p . 3 . 7. S a t . V Prog. O f f . , 8. I b i d . , p . 40. 9. Ibid., ., S a t . V QPR, Apr. 1 - J u n e 3 0 , 1 9 6 6 , p . 29. P. 1 4 . Sat.V QPR, A p r . 1 - J u n e 3 0 , 1 9 6 6 , p . 1 4 . p . 6. 10. NASA, A s t r o n u a t i c s a n d A e r o n a u t i c s , 1 9 6 6 , p . 213. 11. S a t . V P r o g . O f f . , S a t . V QPR, Apr. 1 - J u n e 3 0 , 1 9 6 6 , p . 6 . 12. I b i d . , p. 27. 13. I b i d . , p. 14. 14. T e s t L a b . , MPR f o r J u n e 1 2 - J u l y 1 2 , 1 9 6 6 , p . 1. 15. P&VE L a b . , MPR f o r J u n e 1 9 6 6 , p . 4 . 16. NAA, S - I 1 MPR, J u n e 1 9 6 6 , p . 8 . 17. S a t . V Prog. Off., 18. NAA, S - I 1 MPR, J u n e 1 9 6 6 , p . 2 1 . 19. Memo, Sneed t o NASA H q . , S a t . V QPR, A p r . 1 J u n e 3 0 , 1 9 6 6 , p . 4 3 . " S a t . V Wkly. K p t . No. 7 7 , " J u n e 2 7 , 1 9 6 6 . 2 0 . MSFC A e r o - A s t r o d y n a m i c s L a b . , M o n t h l y P r o g r e s s R e p o r t , J u l y 7 , 1 9 6 6 , p. 4. 2 1 . . T e s t L a b . , MPR f o r J u n e 1 2 - J u l y 1 2 , 1 9 6 6 , p . 1. 22. PAO, P r e s s R e l e a s e 66-138, J u n e 2 4 , 1 9 6 6 . �June ( C o n t ' d ) PAO, P r e s s R e l e a s e 66-139, J u n e 2 4 , 1 9 6 6 . Memo, Sneed t o NASA Hq., S a t . V Prog. Off., " S a t . V Wkly. R p t . No. 7 8 , " J u l y 5 , 1 9 6 6 . S a t . V QPR, Apr. 1 - J u n e 3 0 , 1 9 6 6 , p . 1 0 . PAO, P r e s s R e l e a s e 66-141, J u n e 2 7 , 1 9 6 6 . S a t . V Prog. O f f . , Ibid., - S a t . V QPR, A p r . 1 - J u n e 30, 1 9 6 6 , p . 1 4 . p , 54. PAO, P r e s s R e l e a s e 66-142, J u n e 3 0 , 1 9 6 6 . S a t . V Prog. Off., S a t . V QPR, Apr. 1 - June 30, 1966, p . 18. DAC, S-IVB MTPR, J u n e 1 9 6 6 , p . 4 3 . T e s t L a b . , MPR f o r J u n e 1 2 - J u l y 1 2 , 1 9 6 6 , p. 1 0 . S a t . V P r o g . O f f . , S a t . V QPR, Apr. 1 - J u n e 30, 1 9 6 6 , p . 4 1 . -.I b i d 9 p. 5 3 . Memo, Sneed t o NASA Hq., S a t . V Prog. Off., I b i d . , p. Ibid., p. I b i d ., p . " S a t . V Wkly. R p t . No. 8 0 , " J u l y 1 8 , 1966 S a t . V QPR, Apr. 1 - J u n e 3 0 , 1 9 6 6 , p . 4 9 . 43. 41. 29. T e s t L a b . , MPR f o r J u n e 1 2 - J u l y 1 2 , 1966, p. 4. �1. P&VE L a b . , MPR f o r J u l y 1 9 6 6 , p. 3 0 . 2 . Memo, G . G . B u c k n e r , C h i e f , P u r c h a s i n g O f f i c e , t o H. H. Gorman, Deputy D i r e c t o r , A d m i n i s t r a t i v e , s u b j . , 'Weekly A c t i v i t y R e p o r t , " J u l y 1, 1966. 3. Ibid. 4. Ibid. - 5 . S a t u r n V Program O f f i c e , S a t u r n V Semi-Annual P r o g r e s s R e p o r t , J u l y 1 December 3 1 , 1 9 6 6 , p . 4 1 . 6. Ibid., p..36. 7. SASA, A s t r o n a u t i c s and A e r o n a u t i c s , 1 9 6 6 , p. 233. 8. T e s t L a b . , MPR f o r J u n e 12 - J u l y 1 2 , 1 9 6 6 , p . 2 8 . 9. Ibid. S a t . V S-APK, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 2 5 . 10. S a t . V Prog. Off., 11. PAO, P r e s s R e l e a s e , 66-149, J u l y 7 , 1 9 6 6 . 1 2 . PAO, P r e s s R e l e a s e , 66-151, J u l y 8 , 1 9 6 6 ; and Memo, von Braun t o A d d r e s s e e s , s u b j . , "Creation of Experiments O f f i c e , " J u l y 7, 1966. 13. PAO, P r e s s R e l e a s e , 66-152, J u l y 8 , 1 9 6 6 . 14. S a t . V Prog. Off., 15. NAA, S - I 1 MPR, J u l y 1 9 6 6 , p . 1 4 . 16. Memo, Buckner t o Gorman, s u b j . , 17. DAC, S-IVB MTPR, J u l y 1 9 6 6 , p . 4 0 . 18. PAO, P r e s s R e l e a s e 66-156, 19. Memo. Buckner 20. DAC, S-IVB MTPR, J u l y 1 9 6 6 , p . 39. 21. PAO, P r e s s R e l e a s e 66-158, J u l y 1 8 , 1 9 6 6 . S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 4 2 . "Wkly.Act. R p t . , " J u l y 8 , 1966. J u l y 1 3 , 1966. t o Gorman, s u b j . , 'Wkly. A c t . R p t . , " J u l y 1 5 , 1966. �J u l y (Cont'd) 22. PAO, P r e s s R e l e a s e 6 6 - 1 5 ? > J u l y 1 9 , 1 9 6 6 . 23. DAC, S-IVB MTPR, J u l y 1 9 6 6 , p . 3 9 . 24. T e s t L a b . , MPR f o r J u l y 1 2 25. DAC, S-IVB MTPR, J u l y 1 9 6 6 , p . 4 3 . 26. PAO, P r e s s R e l e a s e 66-162, J u l y 2 1 , 1 9 6 6 . 27. PAO, P r e s s R e l e a s e 6 6 - 1 6 1 , J u l y 2 1 , 1 9 6 6 . 28. S a t . V P r o g . O f f . , S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 5 6 . 29. I b i d . , p p . 36-37. 30. I b i d . , p . 35. 31. NAA, S - I 1 MPR, J u l y 1 9 6 6 , p . 1. 32. DAC, S-IVB 33. PAO, P r e s s R e l e a s e 6 6 - 1 6 4 , J u l y 24, 1 9 6 6 . 34. P&VE L a b . , MPR f o r J u l y 1 9 6 6 , p . 2 9 . 35. PAO, P r e s s S e l e a s e 66-167, J u l y 2 6 , 1 9 6 6 . 36. PAO, P r e s s R e l e a s e 66-168, J u l y 2 6 , 1 9 6 6 . - Aug. 1 2 , 1 9 6 6 , p . 3 . MTPR, J u l y 1 9 6 6 , p . 4 7 . 3 7 . S a t . V P r o g . O f f . , S a t . V S-APR, J u l y 1 - Dec. 31, 1 9 6 6 , p . 56; a n d PAO, P r e s s R e l e a s e 66-173, J u l y 2 9 , 1 9 6 6 . 38. NAA, S - I 1 MPR, J u l y 1 9 6 6 , p . 1 8 . 39. S a t . V P r o g . O f f . S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 4 1 . 40. Memo, Buckner t o Gorman, s u b j . , 41. S a t . V P r o g . O f f . , S a t . V S-APR, J u l y 1 42. P&VE L a b . , MPR f o r Aug. 1 9 6 6 , p . 40. 43. S a t . V P r o g . O f f . , S a t . V S-APR, J u l y 1 "Wkly. A c t . R p t . , " J u l y 2 9 , 1 9 6 6 . - Dec. 3 1 , 1 9 6 6 , p . 37. - Dec. 3 1 , 1 9 6 6 , p . 3 5 . �J u l y (Cont Id) NAA, S - I 1 MPR, J u l y 1 9 6 6 , p . 1 2 . S a t . V Prog. Off., S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 35. RAA, S - I 1 MPR, J u l y 1 9 6 6 , p . 9 . S a t . V Prog. Off., S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 37. T e s t L a b . , MPR f o r J u l y 1 2 Birmingham P o s t - H e r a l d , S a t . V Prog. Off., Ibid., p. 3 1 . I b i d . , p. 25. - Aug. 1 2 , 1 9 6 6 , p . 8 . J u l y 8, 1966, p. 5 . S a t . V S-APR, J u l y I - Dec. 3 1 , 1 9 6 6 , p . 5 6 . �A U G U S T 1. PAO, P r e s s R e l e a s e 6 6 - 1 7 4 , Aug. 1 , 1 9 6 6 . 2. MAE, H i s t . R p t . , J a n . - Dec. 1 9 6 6 , p . 31. 3. NAA, 4. NASA, A s t r o n a u t i c s a n d A e r o n a u t i c s , 1 9 6 6 , p . 257. 5. A e r o L a b . , MPR, Aug. 9 , 1 9 6 6 , p . 4 . 6. PAO, P r e s s R e l e a s e 6 6 - 1 8 1 , Aug. 5 , 1 9 6 6 . 7. Sat.V P r o g . O f f . , 8. DAC, S-IVB QTPR, S e p t . 1 9 6 6 , p . 2 9 . 9. MTF, H i s t . o f Year 1 9 6 6 , p . 1 4 . S - I 1 MPR, Aug. 1 9 6 6 , p . 9 . S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p. 3 1 . 10. S a t . V P r o g . O f f . , S a t V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 7 4 . 11. NAA, 12. S a t . V P r o g . O f f . , S a t . V S-APR, J u l y 1 13. I b i d . , p. 26. 14. I b i d . , p. 56. 15. I b i d . , p . 26. 16. MAF, H i s t . R p t . , J a n . - Dec. 1 9 6 6 , p . 4 . S - I 1 MPR, Aug. 1 9 66, p . 30. - Dec. 3 1 , 1 9 6 6 , p . 7 0 . 1 7 . T e l e t y p e , M e l v i n J o h n s o n , C h i e f , Program C o n t r o l O f f i c e , S a t u r n I / I B P r o g r a m O f f i c e , MSFC, t o D i r e c t o r , A p o l l o Program C o n t r o l , NASA, s u b j . , " S a t u r n I B Weekly Notes 3 3 - 6 6 , " Aug. 1 6 , 1 9 6 6 . 18. T e s t L a b . , MPR f o r J u l y 12 - Aug. 1 2 , 1 9 6 6 , p . 1. 19. PAO, P r e s s R e l e a s e 6 6 - 1 8 3 , Aug. 11, 1 9 6 6 . 20. S a t . V Prog. Off., 21. Ibid., p..35. 32. I b i d . , p . 86 S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 6 �August ( C o n t Id) DAC, S-IVB QTPR, S e p t . 1 9 6 6 , p . 3 0 . S a t . V Prog. O f f . , S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 1 2 . I b i d . , p p . 37-38 Hemo, Sneed t o NASA Hq., S a t . V Prog. O f f . , " S a t . V Wkly. R p t . No. 8 4 , " Aug. 1 5 , 1 9 6 6 . S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 5 4 . I b i d . , p. 17. DAC, S-IVB QTPR, S e p t . 1 9 6 6 , p . 5 . TWX, Johnson t o NASA H q . , " S a t . I B Wkly. N o t e s 3 3 - 6 6 , " Aug. 1 6 , 1 9 6 6 . Ibid. PAO, P r e s s R e l e a s e 6 6 - 1 8 7 , Aug. 1 6 , 1 9 6 6 . S a t . V P r o g . O f f . , S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 1 7 . I b i d . , p. 31. Ibid ., p. 12. I b i d . , p . 72. PAO, P r e s s R e l e a s e 6 6 - 1 8 9 , Aug. 1 9 , 1 9 6 6 . DAC, S-IVB QTPR, S e p t . 1 9 6 6 , p . 2 9 . S a t . V P r o g . O f f . , S a t . V S-APR, J u l y 1 Ibid., - Dec. 3 1 , 1 9 6 6 , p . 3 1 . p . 39. I b i d . , p p . 70 & 7 1 . DAC, S-IVB QTPR, S e p t . 1 9 6 6 , p. 2 4 . S a t . V P r o g . O f f . , S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 28. Ibid . Y Pa 11. I b i d . , p . 76. �August ( C o n t ' d ) 46. Memo, Sneed t o NASA Hq., 47. NASA, A s t r o n a u t i c s and A e r o n a u t i c s , 1 9 6 6 , p . 2 7 4 . 48. P&VE L a b . , MPR f o r A u g u s t 1 9 6 6 , p . 8 . 49. S a t . V Prog. O f f . , 50. NAA, S - I 1 MPR, A u s . 1 9 6 6 , p . 3 1 . 51. Ibid., 52. T e s t Lab.,MPR p. " S a t . V Wkly. R p t . No. 8 6 , " Aug. 3 1 , 1 9 6 6 . S a t . V S-APR, J u l y 1 - Dec. 31, 1 9 6 6 , p . 2 6 . 23. MAF, H i s t . R p t . , f o r Aug. 12 - Sept. 12,'1966, p. 9. J a n . - Dec. 1 9 6 6 , p. 31. S a t . V P r o g . O f f . , S a t . V S-APR, J u l y 1 - Dec, 3 1 , 1 9 6 6 , p . 2 6 . DAC, S-IVB QTPR, S e p t . 1 9 6 6 , p . 2 4 . S a t . V P r o g . O f f . , S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 4 3 . I b i d . , p. 35. I b i d . , p . 60. I b i d . , p . 22. NAA, S - I 1 MPR, Aug. 1 9 6 6 , pp. 1 & 9 . T e s t L a b . , MPR f o r Aug. 12 Memo, Sneed t o NASA Hq., S a t . V Prog. O f f . , - S e p t . 1 2 , 1966, p. 4. " S a t . V Wkly. R p t . No. 8 5 , " Aug. 2 4 , 1966 S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 5 6 6 , p . 5 6 . �S E P T M B E R 1. PAO, P r e s s R e l e a s e 66-196, S e p t . 1 , 1 9 6 6 . 2. Memo, Buckner t o Gorman, "kly. 3. TWX, J o h n s o n t o NASA Hq,llSat. I B Wkly. N o t e s 3 6 - 6 6 , " S e p t . 8 , 1 9 6 6 . 4. DAC, S-IVB QTPR, S e p t . 1 9 6 6 , p . 30. 5. Ibid., - 6. S a t . V Prog. Off., 7. I b i d . , p . 72. 8. TWX, Johnson t o NASA Hq., " S a t . I B Wkly. Notes 3 6 - 6 6 , " S e p t . 8 , 1 9 6 6 . 9. PAO, P r e s s R e l e a s e 66-197, S e p t . 1, 1 9 6 6 . 10. Act. R p t . , " S e p t . 9 , 1 9 6 6 . p . 34. S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 5 6 . PAO, P r e s s R e l e a s e 6 6 - 2 0 0 , S e p t . 6 , 1 9 6 6 . 11. Memo, W. R. K u e r s , D i r e c t o r , ME L a b . , t o D. S . Akens, C h i e f , H i s t o r i c a l O f f i c e , MSFC, s u b j . , " H i s t o r i c a l D a t a , J u l y - September 1 9 6 6 , " December 2 7 , 1 9 6 6 . S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 2 6 . 12. S a t . V Prog. O f f . , 13. DAC, S-IVR QTPR, S e p t . 1 9 6 6 , p . 3 0 . 14. S a t . V Prog. Off., 15. I b i d . , p . 31. 16. TWX, 17. Ibid. 18. S a t . V Prog. Off., 19. PAO, P r e s s R e l e a s e 66-210, S e p t . 1 9 , 1 9 6 6 . 20. S a t . V Prog. Off., 21. I b i d . , p. 48. 22. TWX, Johnson t o NASA H q . , S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p p . 1 7 & 2 6 . Johnson t o NASA Hq., "Sat. I B Wkly. Notes 3 8 - 6 6 , ' ' S e p t . 1 9 , 1 9 6 6 . S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 71. S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 1 2 . "Sat. I B Wkly. Notes 3 9 - 6 6 , ' ' S e p t . 2 7 , 1 9 6 6 . �September ( C o n t ' d ) S a t . V Prog. O f f . , MAF, H i s t . R p t . , S a t . V S-APR, J u l y 1 Jan. S a t . V Prog. Off., - - Dec. 3 1 , 1966, p . 8 1 . Dec. 1 9 6 6 , p . 1 2 . S a t . V S-APR, J u l y I - Dec. 3 1 , 1 9 6 6 , p . 1 3 . I b i d ., p . 25. NAA, S - I 1 MPR, S e p t . 1 9 6 6 , p . 5 . I b i d . , p. 7. TWX, Johnson t o NASA H q . , S a t . V Prog. Off., "Sat. I B Wkly. Notes 40-66,'' S a t . V S-APR, J u l y 1 - Oct. 3 , 1966. Dec. 3 1 , 1 9 6 6 , p p . 87-88. I b i d . , p . 47. NAA, S - I 1 MPR, S e p t . 1 9 6 6 , p . 26. PAO, P r e s s R e l e a s e 66-223, S e p t . 2 9 , 1 9 6 6 . S a t . V P r o g . O f f . , S a t . V S-APR, J u l y 1 Ibid a ? P o 36. - Dec. 3 1 , 1 9 6 6 , p . 5 9 . �O C T O B E R S a t . V P r o g . O f f . , S a t . V S-APR, J u l y 1 - Dee. 3 1 , 1 9 6 6 , p . 28. I b i d . , p . 42. I b i d . , p. 6 . I b i d . , p. 12. I b i d . , p . 28. I b i d . , p. 58. I b i d . , p. 81. TWX, 9. J o h n s o n t o NASA H q . , "Sat. I B Wkly. Notes 4 1 - 6 6 , " O c t . 1 0 , 1966. PAO, P r e s s R e l e a s e 66-245, O c t . 7 , 1 9 6 6 . S a t . V S-APR, J u l y 1 - 10. S a t . V Prog. Off., 11. I b i d . , p . 36. 12. TWX, J o h n s o n t o NASA H q . , 13. S a t . V P r o g . O f f . , S a t . V S-APR, J u l y 1 14. I b i d . , p. 83. 15. DAC, S-IVB QTPR, Dec. 1 9 6 6 , p . 2 9 . 16. I b i d . , p . 30. 17. S a t . V Prog. Off., 18. NASA, A s t r o n a t u i c s and A e r o n a u t i c s , 1 9 6 6 , p . 321. 19. S a t . V P r o g . O f f . , S a t . V S-APR, J u l y 1 20. PAO, P r e s s R e l e a s e 66-246, O c t . 11, 1 9 6 6 . 21. NAA, S - I 1 QPR, 4 t h Qtr. 1 9 6 6 , p . IV-3. 22. Ibid., p . 111-1. "Sat. Dec. 3 1 , 1 9 6 6 , p . 60. I B Wkly. Notes 4 2 - 6 6 , " O c t . 1 8 , 1 9 6 6 . - Dec. 3 1 , 1 9 6 6 , p . 5 3 . S a t . V S-APR, J u l y 1 - Dec. 31, 1 9 6 6 . p . 1 4 . - Dec. 3 1 , 1 9 6 6 , p . 1 5 . �October (Cont'd) S a t . V Prog. O f f . , S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p. 7 . DAC, S-IVB QTPR, Dec. 1 9 6 6 , p . 3 3 . S a t . V P r o g . O f f . , S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 2 5 . NASA, A s t r o n a u t i c s and A e r o n a u t i c s , 1 9 6 6 , p . 325. DAC, S-IVB QTPR, Dec. 1 9 6 6 , pp.33 & 34. The H u n t s v i l l e Times, O c t . 2 3 , 1 9 6 6 . S a t . V Prog. Off., S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 1 5 . I b i d . , p. 25. Ibid . 7 P - 18. NAP., S - I 1 QPR, 4 t h Qtr. 1 9 6 6 , p . IV-4. PAO, P r e s s R e l e a s e 66-258, O c t . 2 5 , 1966. PAO, P r e s s R e l e a s e 66-261, O c t . 2 5 , 1 9 6 6 . S a t . V Prog. Off., S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 3 0 . NASA, A s t r o n a u t i c s and A e r o n a u t i c s , 1 9 6 6 , p . 3 3 0 . NAA, S - I 1 QPR, 4 t h Qtr. 1 9 6 6 , p . 1 1 - 1 4 . S a t . V Prog. Off., MAE, H i s t . R p t . , S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 1 8 . J a n . - Dec. 1 9 6 6 , p . 5 . NAA S - I 1 QPR, 4 t h Qtr. 1 9 6 6 , p . IV-4. S a t . V Prog. Off., Aero. L a b . , S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 1 8 . Bimonthly P r o g . R p t . Dec. 1 2 , 1 9 6 6 , p . 1 3 . S a t . V P r o g . O f f . , S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 1 5 . �N O V E M B E R 1. TWX, J o h n s o n t o NASA Hq., 2. PAO, P r e s s R e l e a s e 66-264, Nov. 2 , 1 9 6 6 . 3. S a t . V P r o g . O f f . , S a t . V S-APR, J u l y 1 4. TWX, J o h n s o n t o NASA Hq., 5. NAA, S - I 1 QPR, 4 t h Q t r . 1 9 6 6 , p . 1 1 1 - 2 . 6. S a t . V Prog. Off., 7. Memo, Sneed t o NASA Hq., 8. S a t . V P r o g . O f f . , S a t . V S-APR, J u l y 1 9. PAO, P r e s s R e l e a s e 66-271, Nov. 1 0 , 1 9 6 6 . " S a t . I B Wkly. N o t e s 4 4 - 6 6 , " "Sat. Dec. 3 1 , 1 9 6 6 , p. 1 8 . I B Wkly. N o t e s 4 4 - 6 6 , " S a t . V S-APR, J u l y 1 "Sat. - V Nov. 7 , 1 9 6 6 . - Nov. 7 , 1 9 6 6 . Dec. 3 1 , 1 9 6 6 , p . 74. Wkly. R p t . No. 9 6 , " Nov. 1 5 , 1966. - Dec. 3 1 , 1 9 6 6 , p . 5 8 . 10. S a t . V P r o g . O f f . , S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , pp. 7 & 1 5 . 11. PAO, M a r s h a l l S t a r , Nov. 1 6 , 1 9 6 6 , p. 1 0 . 12. S a t . V Prog. Off., 13. Ibid., - 14. TWX, J o h n s o n t o NASA Hq., 15. NAA, S - I 1 QPR, 4 t h Qtr. 1 9 6 6 , p . 1 1 1 - 2 . 16. PAO, P r e s s R e l e a s e 66-276, Nov. 1 7 , 1 9 6 6 . 17. S a t . V Prog. Off., 18. TWX, J o h n s o n t o NASA H q . , 19. PAO, P r e s s R e l e a s e 66-278, Nov. 2 1 , 1966. 20. S a t . V Prog. Off., 21. A e r o . L a b . , Bimonthly P r o g . R p t . , S a t . V S-APR, J u l y 1 - Dec. 3 1 , 1 9 6 6 , p . 7 . p . 30. "Sat. I B Wkly,Notes, 4 6 - 6 6 , " S a t . V S-APR, J u l y 1 "Sat. - Nov. 2 2 , 1 9 6 6 . Dec. 3 1 , 1 9 6 6 , p . 3 1 . I B Wkly. N o t e s 47-66," Nov. 2 9 , 1 9 6 6 . S a t . V S-APR, J u l y 1 - Dec. 31, 1 9 6 6 , p. 3 0 . Dec. 1 2 , 1 9 6 6 , p . 1 3 . 2 2 . S a t . V P r o g . O f f . , S a t . V S-APR, J u l y 1 NAA, S - I 1 QPR, 4 t h Q t r . 1 9 6 6 , p . I V - 4 . - Dec. 3 1 , 1 9 6 6 , p. 7 ; and �November (Cont'd) Sat. V Prog. Off., Sat. V S-APR, July 1 Dec. 31, 1966, p . 18. TWX, Johnson to NASA Hq., "Sat. IB Wkly. Notes 51-66,!' Dec. 27, 1966. PAO, Press Release 66-281, Nov. 22, 1966. PAO, Press Release 66-282, Nov. 23, 1966. Sat. V Prog. Off., Sat. V S-APR, July 1 - Dec. 31, 1966, p p . 86-87. Ibid., p . 30. NASA, Astronautics and Aeronautics, 1966, p . 356. PAO, Press Release 66-284, Nov. 28, 1966. Sat. V Prog. Off., Sat. V S-APR, July 1 - Dec. 31, 1966, p p . 44 & 46. PAO, Press Release 66-288, Nov. 30, 1966. TWX, Johnson to NASA Hq., "Sat. IB Wkly. Notes 48-66," Dec. 5, 1966. Sat. V Prog. Off., Sat. V S-APR, July 1 - Dec. 31, 1966, p p . 81 & 8 3 . NASA, Astronautics and Aeronautics, 1966, p. 360-361. �D E C E M B E R - 1. S a t . V Prog. O f f . , 2. Ibid 3. I b i d . , p . 39. 4. PAO, P r e s s R e l e a s e 66-279, Nov. 22, 1966. 5. S a t . V Prog. O f f . , 6. I b i d . , p . 7. 7. TWX, Johnson t o NASA Hq., "Sat. I B Wkly. Notes 48-66," Dec. 5 , 1966. 8. DAC, S-IVB QTPR, Dec. 1966, p . 34. 9. MAF, H i s t . R p t . , J a n . - 9 S a t . V S-APR, J u l y 1 Dec. 31, 1966, p . 31. P . 34. S a t . V S-APR, J u l y 1 - - Dec. 31, 1966, p . 83. Dec. 1966, p . 31. S a t . V S-APR, J u l y 1 - Dec. 31, 1966, p . 60. 10. S a t . V Prog. O f f . , 11. PAO, M a r s h a l l S t a r , Dec. 7 , 1966, p . 7. 12. TWX, Johnson t o NASA Hq., "Sat. 13. TWX, Johnson t o NASA Hq., "Sat. I B Wkly. Notes 49-66," Dec. 1 3 , 1966. 14. TWX, Johnson t o NASA Hq., 15. PAO, P r e s s R e l e a s e 66-292, Dec. 8 , 1966. 16. S a t . V Prog. O f f . , 17. Ibid 18. I b i d . , p . 28. 19. PAO, P r e s s R e l e a s e 66-294, 20. TWX, Johnson t o NASA Hq., 21. DAC, S-IVB QTPR, Dec. 1966, p . 33. 22. NASA, A s t r o n a u t i c s and A e r o n a u t i c s , 1966, p . 373. ., p. "Sat. 1 3 Wkly Notes 52-67," J a n . 3 , 1967. I B Wkly. Notes 50-66," Dec. 30, 1966. S a t . V S-APR, J u l y 1 - Dec. 31, 1966, p . 5 9 . 15. Dec. 1 3 , 1966. "Sat. I B Wkly. Notes 49-66," Dec. 1 3 , 1966. �December ( C o n t ' d ) 23. TWX, Johnson t o NASA Hq., 24. Ibid. 25. S a t . V Prog. O f f . , S a t . V S-APR, J u l y 1 26. TWX, Johnson t o NASA Hq., 27. MAF, H i s t . Rpt., Jan. - "Sat. I B Wkly. Notes 50-66," Dec. 2 0 , 1966. - Dec. 31, 1966, p . 24. "Sat. I B Wklp.Notes 50-66," Dec. 20, 1966. Dec. 1966, p. 27. 2 8 . . I b i d . , p . 32. 29. DAC, S-IVB QTPR, Dec. 1966, p . 30. 30. TWX, Johnson t o NASA Hq., 31. NAA, 32. S a t . V Prog. O f f . , S a t . V S-APR, J u l y 1 33. TWX, Johnson t o NASA Hq., 34. Memo, Kuers t o Akens, " H i s t . 35. PAO, P r e s s R e l e a s e 66-295, Dec. 20, 1966. 36. S a t . V Prog. O f f . , 37. NAA, S - I 1 QPR, 4 t h Q t r . 1966, p.VI-74. 38. S a t . V Prog. O f f . , S a t . V S-APR, J u l y 1 39. NAA, S - I 1 QPR, 4 t h Q t r . 1966, p. 111-5. 40. PAO, M a r s h a l l S t a r , J a n . 4 , 1967, p. 7 . 41. PAO, P r e s s R e l e a s e 66-298, Dec. 2 3 , 1966. 42. MAF, H i s t . R p t . , J a n . 43. PAO, P r e s s R e l e a s e 66-301, Dec. 2 8 , 1966. 44. S a t . V Prog. O f f . , 45. I b i d . , p . 59. "Sat. I B Wkly. Notes 50-66," Dec. 2 0 , 1966. S - I 1 QPR, 4 t h Qtr. 1966, p. 1-1. Dec. 31, 1966, p . 9 0 . "Sat. I B Wkly. Notes 50-66," Dec. 2 0 , 1966. D a t a , Oct. S a t . V S-APR, J u l y 1 - - - Dec. 1966." - Dec. 31, 1966, p p . 50-52. - Dec. 31, 1966, p . 31. Dec. 1966, p. 27. S a t . V S-APR, J u l y 1 - Dec. 31, 1966, p . 74. �December ( C o n t ' d ) 46. PAO, P r e s s R e l e a s e 66-302, Dec. 30, 1966. 47. MAF, K i s t . R p t . , 48. S a t . V P r o g . Off'., S a t . V S-APR, J u l y 1 49. NAA, S - I 1 QPR, 4 t h Q t r . 1966, p . 1-1. 50. S a t . V Prog. O f f . , Jan. - Dec. 1966, p . 28. S a t . V S-APR, J u l y 1 - Dec. 31, 1966, p . 41. - Dec. 3 1 , 1966, pp. 89-90. � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000031 Title A name given to the resource 1966 Chronology of Marshall Space Flight Center. Description An account of the resource This draft copy of the chronology includes a memorandum from Marshall Historian L. L. Jones of the Historical Office. Creator An entity primarily responsible for making the resource Jones, L. L. George C. Marshall Space Flight Center Date A point or period of time associated with an event in the lifecycle of the resource 1967-01-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) George C. Marshall Space Flight Center Type The nature or genre of the resource Chronologies (list) Text Source A related resource from which the described resource is derived Saturn V Collection Box 20, Folder 14 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050 https://digitalprojects.uah.edu/files/original/20/979/spc_stnv_000032.pdf 1a9cd09f530ad95abeb931027f66440d PDF Text Text A C T I V E Z3XTFr1CTS T S : ULXISG L A Z S L X X Y PROP-LSZON AND V E H I C L Z EKG--YT' ,A P r e p a r e d by I n d u s t r i a l R e s o u r c e s Grou? R e s o u r c e s Yunagement O f f i c e �AiResearch Yanufacturing Brown Engineering Company MS8-;'1%2i Development and Hanufacture of Trotective Clothing for Use in Hazardous Environments Design, Development, Fabrication, and Delivery of Saturn V instrument Unit Umbilical Connector Assemblies T Brown Engineering Cornpany DesLgn, Development, Documentation, Fabrication, and Testing of Saturn V Simulator Instrument Unit Disconnect Carrier Assembly Kits 3rown Engineering Company ViSration Testing of Saturn -,nstrument Unit Hounting Con?onents Brown Engineering Company Verification of Criticality Data Denison Ecgineering Div. American Brake Shoe CO. Qnaiification Test Program for -7. h i g h Pressure lump Used in the S-IC Ground Hydraulic Supply & C'neckout Douglas Aircraft Company Suman Engineering Design Criteria Study �~s~-',i673 Greer Kydraulics, I n c . yL h - -0 ~ ~ ; ~ p i ~ - S?are P a r t s r o r , o g i s t i c ~ l ~S ~ y p ~p o r tof S - I C H y d r a u l i c S u p p o r t and Checkout U n i t s G r e e r Eiydraulics, I n c . iSAS8-54-74 C z s i g n , Devclop:~$znt, iilznuf a c z u r i n g , aild D e l i v e r y o f Five Ground S u p p o r t H y d r a u l i c Systems and Checkout U n i t s I d a l t e r E d d e and Co., Inc. XAS8-,1550 C e s l g n , 3~5:-ica:5on, T e s t i n g , an? D e l i v e r y o; . i v e Xach S-IC I n e r t ??refill U n r t s W a l t e r R i d d e and Co., Inc, i\;:S8-+;357 F e s l g n , Usvelopment, F a b r l c a E i o n , Assembly, and T e s t i n tJ - of a Truck-Mounted F l u s h and ? u r g e Ground Sup?ort S e r v i c i n g System - Hayes I n t e r n a t i o n a l Corp. A i r Bearing Supply Distribucion and Konitoring System Hayes I n t e r n a t i o n a l Corp. Design, Develop, F a b r i c a t e , T e s t , and D e l i v e r y o f Two Mobile S e r v i c e Truck U n i t s ( M - 1 and Sodiun N i t r i t e ) �J e t Research Cezter, Inc. COITLETE %S8-li484 - im?act o f S 2 n s l t l v l z y o f V a r i o u s Typzs and S i z e s o f L i n e a r Shaped Charges V i b r z t i o n iind F a t i g u e l e s t i n g of Bolted Y f r t i n - M a r i e t t a Corp. ?7 Separable Connectors - Design, 3sve:o?rnent, zaSr:cation, Testing, a z d C o c u m ~ n e a t i o no f m-, L , a, L , s p o r t s b i e Ground Su??ort Cooling U n i t s P a l l Corporation P ic a tinny Arsenal U. S . A m y M u n i t i o n s Command Ff-7i5135 7 e z s l b i ; L t y Study o f t h e Use of L i q u i d Z x p i o s i v e e c d A s s o c i a t e d Components �cO:,T",',."" --"---,-,> . :_; - -:T T:I\,iXSZi-jX LL~L.; CON'~~L~cTOR Souttwestern I c d u s t r i c s , Inc. -,7y> d: , - L L . c<,A - .- - ~,.L,?L,L?. S,:~SC-,5-/,73 ~;;ss-~~~;~~ Spaco, I n c o r p o r a t e d U n i t e d A i r c r a f t Corp ? ,-( . U n i v e r s a l >latch Corp. (continued) .-.,-- -';,, : u .,. I\. C3 CONTXP-CT .. r c.,2 , (15j 'I'h,-. . <- ,- ,u,~ OK ?x-essure Z~L:cl;g of ?\esearch and Z ~ v e l o p z c n t i n the F i e l d oE T h y s i c a l 3 e t e r i i ; i n a t i o n f o r ?/ass Properties Des:gn, Developne;~t, F a b ~ T c a t i o n ,and Testing of S-IVB APS ? r o p e l l a n t Servicing Units 33s?.gn, D s v e l o p e n t , ;?'&b.-,;cation, and Q u a l i f i c a t i o n i e s t i n g o f a Xemote C o n t r o l S a l e t y and Arming D e v i c e "7 Wyle Laboratories Cor~ponent Znvironrnental Q ~ a l L f i c z c i o nT e s t i n g i n S u p 2 o r t of S s t u r n Wyle L a b o r a t o r i e s 3nvLron?.1e2tal T e s ~ i n go f t:% s-" , ~ u r a 2 3 and V in strum en^^ Units �Aerojet-General Corp . M S 8 - 11043 C0317YET ZD Aerojet-General Corp. COmLETE NAS8-11063 Study of Detonation in Solid Propellznt by Liquid Propellant Explosion Study of the Phenomena Associated with Mixing of Cryogenic Fluids Aeronca Manufacturing Corp. NAS8-5445 Cevelopment of Eizh S t r e n r s k h , >raz~dL!,Luminqm,Woneycornb S~ndwichComposites Adapzable ?or Both Elevated and Cryogenic Temperature Applications University of Alabama NAS8-5059. Development of Shell Xolding Technique for Producing Prototype Launch Vehicle Castings University of Alabama NAS8-2571 Physico-Chemlcal and Thermodynamic Considerations on Launch Vehicle Ylterials Aluminum Co. of America NASS-5340 Investigation of Stress Corrosion of High Strength Aluminum Alloys Aluminum Co. of America NASS-5452 Development of a High Strength Aluminum Alloy, Readily Yeldable in Plate Thicknesses, and Suitable for Application at -4230F (-253OC) Aluminum Co. of America NAS8-11226 Development of Improved Conversion Coatings for Aluminum Alloys American Machine 6: Foundry NASS-11168 Development of Lightweight Magnesium Alloys for Low Temperature Applications Army Missile Support Command H-61510 Blast Hazard Test Arnold Engineering Development H-71461 Center Atlantic Research Corp. Air Reduction Co. Inc. .- K4S8-11044 CC~~?LCTE~ ?r;vestigation o£ the Effects of vd~uum - on Liquid Hydrogen and Other Cryogens used on Launch Vehicles ~7.- XASS-23078 Investigation of the Beactivity of Tiraniurn and Other Yaterials with Liquid Oxygen and Xitrogen Tetroside NAS8-20099 TOFLOX Synthesizer Study - Air Reduction Co. Inc. ~nvestigationof Addition Polp,erization of Self Sealants -r �CONTMCT LISTING - ;vI DIVISION (continued) COXTRACTOR AVCO Corporation NAS8-11872 Design, Development, Assembly, and Delivery of Differentially Pumped Remotely Adjusted Orifice System AVCO Corporation NAS8-11866 Cp~icalSystem for Coupling an Evacuated Integrating Sphere to 2 Spectrophotometer Battelle Hemorial Institute NASB-11851 Battelle Memorial Institute NAS8-li837 3cvelopncnt of Techniques for Measuring Thermai Diffusivity Process Development and Pilot Plant Production of Silane Polymers and Diols Battelle Memorial Institute NAS8-11452 Development of Improved Thermoelectr5.c Yaterials for Spacecraft Applications Battelle Memorial Institute NAS8-5265 CONPLETED Development of Magnesium-Lithium Alloys for Structural Applications Beckman Instruments Inc. X4S8-11510 Development of Techniques and Instrumentation for Detection of Rydrogen Gas The Boeing Company NAS8- 11307 Research Study for Development of Techniques for Joining of Disslnilar Xetals Borden Chemical Company P.LiS8-ilSlS Dcvelopment of Improved Adhesives for Use at Cryogenic Temperatures to -423'~ Browii Engineering CO. COMPLETE KiS8-SLSG Fabrication and Related Services . KtS8-11187 COMPLETE NAS8-20156 Contract for Fabrication Services NAS8-20529 Development of a MicromeferoidSimulation Device Study of Detonations of Mixtures of Gaseous Hydrogen and Oxygen Brqwn Engineering Co Boeing Company Canadian Commercial Corp . University of California MS8-2634 CTL, Division of Studebaker Corporation M S 8 - 11036 -.. .. Study of Dissimilar Metal Joining by Solid State Welding Development of an Analytical Technique for Predicting Properties of Composite Materials - �B a t t e l l e Memorial I n s t i t u t e R. W . Benson & A s s o c i a t e s ,-Inc C O N T M C T hT;J?SEII NA;"IE O F CONTRACT NAS8-20029 Study of Hydrogen E m b r i t t l e ment of V a r i o u s A l l o y s . NAS8-20208 Development of Non-Des t r u c t i v e Methods f o r D e t e r m i n i n g Residual Stress & Fatigue Damage i n M e t a l s �CONTRACT LISTING CONTRACTOR - M DIVISION (continued) CONTRACT NUMBER Denton Vacuum, Inc. NAS8-11836 COMPLETE WME: OF CONTRACT Design, Fabricate, Assemble, and Deliver a Vapor Coating System Edwards Air Force Base Study of Blast Hazards of Rocket Propellants University of Florida NAS8-1523 Change to NAS8-20247 Study of age Deterioration of Gasket Materials Installed in Simulated Launch Vehicie Hardware Frankford Arsenal H-71508 Development of Magnesium -.Lithium Alloy Casting Program General Dynamics Corporation MS8-2450 Investigation of Combined Effects of Radiation &Vacuum on Engineering Paterials General Electric Company NAS8-2442 Coatings for Conductors Goodyear Aircraft Company NAS8-2564 Research and Development of YTterials for Saturn Heat Shield Curtains Goodyear Aircraft Company NAS8-11070 Evaluation of Structural Reinforced Plastics at Cryogenic Temperatures Goodyear Aerospace Company NAS8-11747 Development of Materials and Materials Application Concepts for Joint Use as Cryogenic Insulation and Micrometeorite Bumpers Goodyear Aerospace Company NAS8-11761 Development of a Lightweight Cryogenic Insulating System �CONTRACT LISTING - M DIVISION CONTRACT N W E R CONTRACTOR Harvey Aluminum, Inc. NAS8-11508 NNm OF CONTRACT Development of Ultrahigh Strength, Low Density, Alumi~umPlate Composites Hughes Aircraft Company Development of Organic Sealants Hughes Aircraft Company Services Required for Research and Development of an Improved Heat Sterilizable Potting Compound Hughes Aircraft Company Development of Dielectric Windows Protective Cover Materials for Spacecraft Antennas Hughes Aircraft Company Development of Structural Foams For Cryogenic Applications Hughes Aircraft Company An Investigation of Adhesion and Cohesion in Vacuum " Illinois Institute of Technology Investigation of the Combined Effects of Space Environmental Parameters, etc. Study, Research, and Development of Analytical Methods and Fabrication of Test Equipment for Determination of Hydrocarbon Contamination Illinois Institute of Technology Development and Validation of a Method for Predicting Neutron Induced Activation in Materials Illinois Institute of Technology Develop Materials for Slip Ring Assemblies Illinois Institute of Technology Research Study on Development of Lightweight Thermal Insulation Materials for Rigid Heat Shields Hughes Aircraft Intermountain Research and Engineering Co , Inc. . NAS8-5318 Investigation and Determination of the Shock Overpressure Required for Initiation of Titanium-LOX and Aluminum-LOX Reactions . ' �CONTRACT LISTING - I4 DIVISION (continued) CONTRACT NUMIjER CONTRACTOR NAME OF CONTMCT Ipsen Industries, Inc. NAS8-11048 Investigation of Foamed Metals for P+plications on Space Capsules Lockheed Aircraft Corp. NAS8-11448 COMPLETED Evaluation of BE-38% Aluminum Alloy Manlab's, Inc. , NAS8-11091 Development of Stress Relief Treatments for High Strength Aluminum Alloys Martin-Marietta Corporation MS8-2531 COMPLETED Test Program for Determination of Low-Temperature Fatigue Properties of Aluminum and Titanium Alloys Nartin-Marietta Corporation NAS8-11300 Test Program for Determination of Low Temperature Fatigue Properties of Aluminum and Titanium Alloys Melpar, Incorporated NAS8-11322 Investigation of the Effects of Mechanical Stress on the Permeability of Engineering Ykiterials to Liquid Hydrogen and Other Propellants Used in Launch Vehicles Midwest Research Corporation NAS8-1540 Conduct Research on Bearing for Use in High Vacuum Midwest Research Corporation NAS8-11338 Synthesis and Evaluation of New High Temperature Polymerslfor Cbating Applications Bureau of Mines Department of Interior H-76708 Determination of Flammability of Specific Propellant Combinations Under Varying Environmental Conditions D .- - . 9 �CONTRACT LISTING CONTRACTOR DIVISION (continued CONTRACT NT31SER Monsanto Research Corp. Monsanto Research Corp. - M - NP.1E OF CONTRACT NAS8-11371 Develoynent of Improved Semiorganic Structural Adhesives for Elevated Temperstures Applications NAS8-11373 Development of Improved Plastic Foam Generating Agents and Techniques for Saturn Applications , Whittaker Corporation ( Narmco Research & Development) NAS8-11068 Whittaker Corporation (~armcoResearch & ~evelopment) NAS8-5053 National Bureau of Standards H-2151A Development of Structural Adhesive Systems Suitable for Use with Liquid k y g en Research and Development of Improved Gasket Materials for Cryogenic Application in Space Investigation of the Directional I Effects in the Stress Corrosion of Aluminum Alloys Program North AmericanAviation Study of Methods for the Design and Analysis of Sensitivity Experiments North American Aviation Development of High Strength, Low Density Composite Materials for Saturn Applications North American Aviation Development of Nondestructive Testing Techniques for Honeycomb Heat Shields Peninsular Chemresearch, Inc. NAS8-5352 Development of Vulcanizable Elastomers Suitable for Use in Contact with Liquid Oxygen Southern Research, Inc. KAS8-2 0 i 9 0 Study of Polymers Containing Silicon-Nitrogen Bonds .- . �CONTRACT LISTIKG CONTRACTOR - M DIVISION (continued) CONTRACT r&BZR Southern Research Institute NAS8-1510 N L I OF CONTXJCT Study of Polymers NAS8-1529 Southern Research Institute Change to NAS8-20160 Development of Welding Techniques and Filler Metals for High Strength Aluminum Alloys Spaco, Incorporated NAS8-5315 COMPLETED Research and Development Fabrication Services Spaco, Incorporated NAS8-11186 Contract for Fabrication Services Standard Pressed Steel Co. NAS8-11125 Evaluation of Fasteners and Fastener YTterials for Space Vehicles National Bureau of Standards H-92120 Behavior of Polymeric Yfterials at Cryogenic Temperatures National Bureau of Standards H-7679.7 Cryogenic Propellant Fluid Properties Data Evaluation Program National Bureau of Standards H-41982 Syracuse University NAS8-11345 Collection of Platerial Property Data and Presentation of Said Data in the Form of Material Data Wandbooks NAS8-1532 COMPLETED Research and Development of High Tenperature Resistant, Polymeric Film Fo-ming Tecumseh Products Co. NAS8-11075 Development of Improved Thermlelectric ~Naterialsfor Spacecraft Applications Stanford Research Institute NAS8-20220 Investigation of Reactivity of Launch Vehicle Materials with Liquid Oxygen United Aircraft Corporation NAS8-11537 Research and Development of Ylterials for Use as Lubricants in a Liquid Hydrogen Environment United Aircraft Corporation NAS8-20089 Development of Alkali Metal Peroxide and Superoxide Blown Ceramic Forms Stauffer Chemical Company -.- . . -investigation of the Stress-Corrosion Cracking Stainless Steel �CONTRACT LISTING CONTRACTOR Whittaker Corporation - M DIVISION ( c o n t i n u e d ) CONTRACT KLTBER NAS8-11958 NP.KE OF CONTRACT O p t i m i z a t i o n of t h e P e r f o r m a n c e o f a P o l y u r e t h a n e A d h e s i v e System o v e r t h e Temperature Range of -4230F t o +2000F - Whittaker Corporation (Narmco R e s e a r c h & Development) NAS8-11068 Development o f S t r u c t u r a l A d h e s i v e Systems S u i t a b l e f o r Use w i t h L i q u i d Oxygen Whittaker Corporation (Narmco R e s e a r c h & Development) NAS8-5053 R e s e a r c h and Development o f Improved Gasket M a t e r i a l s f o r Cryogenic A p p l i c a t i o n i n Space ,. �CONTRACT LISTING - P DIVISTGN ( ~ ~ p70 0 LS i CONTRACTOR CONTRACT L W E R F!iQE Advanced Technology Labs. NAS8-5323 Theoretical Studies to Establish Design Parameters for Accurate Calorimeters " OF CONTRACT Aerodyne Controls Corp . NAS8-11777 Design, Development, Manufacture, and Preflight Certification Testing or Regulator Assembly. Pressure, Gas D r a r l n g Gas Supply System Aerodyne Controls Corp . NAS8-11792 Design, Manufacture, and Qualification Testing of First Stage, WaterlMethanoi Pressure Regulator NAS8-510 COMPLETED Design and Development of Expiosive Bridge Eire (E3W Ignition System for Aerojet General 2KS 36250 Rocket Motors) NAS8-12906 COMPLETE NAS8-11741 Initiator Aerojet-General Corp . Aerojet-General Corp. Aerojet-General Corp. . Fabricate Necessary Hardware and Perform Studies to Determine the Rocket Combustion Dynamic Behavior of the Hydrogen-Oxygen Propellant Combination at High Chamber Pressure NAS8-5467 COWLETE Initiator-Ignitor Compatibility Program for the S-1 Retro Motor Ignition System Aerojet-General Corp. NAS8-11374 Determination of Abort SystemMission Effects for Saturn Ciass Vehicles Aerojet-General Corp. (Classified Confidential) NAS8-li575 COMPLETE Development of a Multifunctional Auxiliary Propulsion Module Aerojet-General Corp - Aerojet-General Corp . NAS8-20068 "POGO" Analysis of the SATURN Propulsion Systems Aero jet-General Corp . NAS8-20219 Demonstration of a Solid Propellant Motor Malfunction Detection 4 Combus tion Termination System �- P DIVISION (continued) CONTRACT F J ~ E R MAKE, OF COhTIIACT CONTRACT LISTING CONTRACTOR Aeroquip Corporation NAS8-11336 Test Plan for Evaluation of Mounting Methods and Distance for Brazed Tubing Assemblies AiResearch Manufacturing Co. NAS8-5107 Development of Fuel and LOX Prevalves Airtek Dynamics, Inc. NAS8-11751 Design, Manufacture, and Qualification TestLng of Certain Gaseous Nitrogen SL. orage Bottles University of Alabama NAS8-5217 Study of Transient Heat Transfer Problems University of Alabama NAS8-5262 Study to Establish a System of Propulsion Component Design Simplicity ' University of Alabama NAS8-11341 Study of the Stability of the S-IC Open Loop 2ropellantHydraulic System Allison Division (General Motors) NAS8-5045 2OMPLETE Development of a Flight Test Program to Demonstrate the Concept of a Rocket Thrust Vector Control System American Brake Shoe Co. NAS8-11172 Repair and Maintenance Services of Fiydraulic Pumps Army Missile Command H-71466 Conduct Hazard Classification Program Arrowhead Products NAS8-5097 Design, Development, Fabrication, Testing, and Documentation of Six Items of Ducting for the Saturn S-IC Auburn University NAS8-11234 Environmental Effects ori Multiphase Genesis Astro-Space Laboratories NAS8-20536 .- . ~ r n o l dEngineering Development H-2105A Center Design, Development, Fabrication and ?ref light Certification Testing of an Absolute-Type Pressure Switch Testing of Five Full-Scale Centaur/ S-IB Retro Rockets with Simulated Vehicle Structure �CONTRACT LISTING - P DIVISION (Continued) CONTRACTOR CONTMCT NUMBER NAME OF CONTRACT Arnold E n g i n e e r i n g Development C e n t e r H-2174A Approximately 235 h o u r s of Vacuum T e s t Time f o r t h e I U Sublimator �CONTRACT LISTILG CONTRACTOR - - P DIVISION (continued) CONTRACT NUMBER W E OF CONTRACT AVCO Corporation NAS8-11870 Optimization of the Saturn IB and V Mounting Thermal Conditioning Panels AVCO Corpora.tion COMPLETED NAS8-14008 Fabrication, Testing, and Delivery of a Quality Mounting and Thermal Conditioning Panels The Bendix Corp. NAS8-20532 Design, Development and Fabrication of an Absolute-Type Pressure Switch Bourns, Inc. NAS8-20501 Design, DeveJopment and Fabrication of an Absolute-Type Pressure Switch Barber-Colman Co. NAS8-5140 COMPLETED Fabrication, Qualification Testing, and Delivery of Various Components Beech Aircraft Corp. NAS8-5331 Conducting Liquid Hydrogen Pressurization Tests Bell Aerosystems Co. NAS8-5491 COMPLETE Bell Aerosystems Co. NAS8-11364 Propellant Droplet Study Under Combustion Conditions Bendix Corporation NAS8-11644 Design, Development, and Delivery of Optical Sensor Systems Bendix Corporation COMPLETED NAS8-11709 Design, Development, and Delivery of One Optimized High Pressure Accumulator Lnstrumentation Development, Fabrication, and Furnishing Techniques to Measure Vehicle Engine Performance V Bell Aerosystems Co. Low Thrust Throtteable Engine Performance Evaluation The Boeing Company Conducting a Comprehensive Review on the Application of Large Solid Fators on Assist Take-Off Devices, Boosters and Building Blocks for Vehicles now in Operation on in the Study Phase �CONTRACT,LISTING - P DIVISION (continued) CONTRACTOR CONTRACT h 7 ~ NAIE~ OF CONTRACT ~ ~ The Boeing Company NAS8-11321 COMPLETED Recoverable Launch Vehicle Thermal Design with Consideration of Arbitrary Wall Temperature The Boeingl Company NAS8-11722 Development and Testing of a Low Temperature Hydraulic System The Boeing Company WS8-14002 Space Propulsion System Project Brown Engineering Company NAS8-11166 COMPLETED Research and Development Engineering Services in Support of the Saturn I and Saturn V Program Cad illac Gage Company NAS8-1662 Engineering and Manufacturing Services University of California NAS8-11468 Study of Heating by Radiation from Exhaust Gases Cryonetics Corporation NAS8-11734 COMPLETED Cryogenic Liquid Level Sensing System Ensign-Bickford Company NAS8-11703 Confined Detonating Fuze (CDF) V Fairchild Stratos Corporation NAS8-11730 Design, Development, Fabrication, and Qualification Testing of Calibratable Solid Stage Electronic Pressure Switches Fairchild Stratos Corporation Design, Development, Manufacturing and Testing of Saturn Mounting and Thermal Conditioning Panels . NAS8-5437 �CONTRACT LISTING CONTRACTOR - P CONTRACT KTIPfBER h DIVISICN (continued) NhW OF CONTRACT Fairchild Stratos Corporation NAS8-11538 Furnishing Services for Design, Development, Manufacturing, Testing, and Delivery of Four Prototype Units of a Boiler, Water, T h e m 1 Conditioning System Flexonics Division Design, Development, Manufacture, and Testing of Outboard LOX and Fuel Pressure Volume Compensator Ducting Flexonics Division Manufacture of Tooling and S-IC LOX and Fuel Pressure Volume Compensating Ducting Franklin Institute NAS8-5382 COMPLETE Frebank Company Study of Contamination Generation of Hydraulic Components Design, Development, Fabrication, and Preflight Certification Testing of Saturn V, S-IC Pressure Switch General Dynamics Corp. NAS8-20146 Study of Zero-Gravity, VaporLiquid Separators . NAS8-11161 Research on Thermal Protection Systems for Cryogenic Propellants,,etc General Dynamics Corporation NAS8-11405 Zydrogen-Oxygen Reaction 'Studies General Dynamics Corporation NAS8-11324 Study on Hydraulic Pressure Surges General ~lectricCompany NAS8-11523 Investigation, Research and Development Materials and their Application to Achieve Zero Leakage for Duct and Tube Connections General Electric Company NAS8-4012 Design Criteria of Zero Leakage Connectors for Launch Vehicles General Electric Company NAS8-11422 Investigation of the Nature of, Cryogenic Fluid Flow Instabilities in Heat Exchangers General Electric Company NAS8-20000 Cavitation Noise Analysis General Dynamics Corp �CONTRACT LISTIKG - P GIVZSlON (continued) CONTRACTOR G e n e r a l Dynamics Corp, NAS8-'20167 LEI2 S u c t i o n L i n e I n s u l a t i o n R e s e a r c h and Development G e n e r a l Dynamics Corp. KASb- 23i65 Development o f A n a l y t i c a l Methods f o r P r e d i c t i n g R e s i d u a l Cryogenic P r o p e l l a n t Behavior i n O r b i t a l V e h i c l e s �CONTiL4CT LIS'I'IYG - P DIVISION (continued) CONTRACTOR CONTFU4CT NL'hBER E-ME OF CONTRACT General Precision, Inc. X4S8-12901 General Precision, Inc. . NAS8-llk72 COEPLETE Initiators improvement of Ignition System for Simultaneous Ignition of Groups of Retro and Ullage Motor on Saturn V NAS8-11770 Design, Fabrication and Testing of Two Pressure Switch Toggle Actuators . NAS8-11311 Determination of Propellant Mass in a Storage Tank by Application ~2 Nucleonic or Light Radiation Technique Giannini Controls Corp. NAS8-11814 Evaluate the Effectiveness of Cryogenic Propellant Tank Vent System Operating Under or Near Zero Gravity Conditions" Georgia Technical Research Institute Giannini Controls Corp Greer Hydraulics, Inc. Design, Development, Fabrication, Delivery, and Installation of a Fluid Power Package Gulton Industries, Inc. NAS8-11672 Design, Development, Fabrication, and Testing of a Piezoelectric Crystal Temperature Sensing System to Measure Mean Temperature of Bulk Iropeilants Hamilton Standard, a Division of United Aircraft NAS8-11615 Saturn IB and Saturn V Instrument Unit Heat Exchanger Hamilton Std. Division of United Aircraft Corporation NAS8-11541 Design, Development, Y ~ n uacturing, f Testing, and Delivery of Four Prototype Units of a Boiler, Water, Thermal Conditioning System , �CONTRACT LISTING CONTRACTOR - P DIVISION (continued) CONTRACT hTTJX3ER Hercules Powder Company N f i E OF CONTMCT NAS8-11598 Solid Propellant Gas Valve Scale-Up Program NAS8-5264 Design, Development, and >fanufacture of Two Prototype Saturn S-IC Hydraulic Transformers Hydro-Aire Division NAS8-11512 Design, Develop, Manufacture, and Test a LOX Conditioning System Pump Hydro-Aire Division NAS8-20524 Design, Development, Fabrication & Documentation for Oile G??i and One 100 GPN Hydraulic Intensifier n Illinois Institute of Technology NAS8-11014 Feasibility Study of Techniques to Protect Mechanisms 9erations in Space from Malfunction MS8-11698 Design, Development, Fabrication, and Testing and Low Temperature Solenoid Valves Wallace 0 . Leonard, Inc. NAS8-11572 rYlodification, Qualification Tesring and Delivery Air Bearing Air Supply and Heater Assemblies Arthur D. Little, Inc. MS8-12818 COMPLETE Design, Fabrication, and Delivery of One Insulation Calorimeter Arthur D. Little, Inc. NAS8-11642 Research and Development of High Flow Hydraulic Filters Hydro-Aire Division W. M. Lanagan Company - \ Lockheed Aircraft Corp. Study of Fundamentals of Pressurant Distribution Design �CONTRACT LISTING CONTRACTOR - P DIVISION (continued) CONTRACT hTPiEII NtI?.'E OF CONTRACT Lockheed Aircraft Corp. NAS8-11347 CO>PLETED Oeveloprnent of Installation and Design Concepts for High Performance Insulation Applied to Cryogenic Space Vehicle Tanks Lockheed Aircraft Corp. NAS8-11525 Develo-,ment of Zero "G" Heat Transfer Modes Marotta Valve Corporation LVAS~-I;SS~ Fabrication, Asse~biy,and Preflight Certification of the Two Position, Kornally Open, Solenoid Operated Water Shut-Off Valve Assembly NAS8--,223 Cryogenic Liquid Experiments in Orbit Martin-Marietta Corp . Study of Mechanics of Geysering Martin-Marietta Corp. COMPLETE NAS8-5418 (Changed to U S 8 -20231)of Cryogenics Martin-Marietta Corp. NAS8-11337 COrnLETE Study of Contamination of LOX by GN2 Martin-Marietta Corp. NAS8-5208 Study of Cryogenic Propellants, Stratification Reduction NAS8-2G231 InvestigatFon of LH2 Recirculation Sysrem Vapor Entraimenr Marquardt Corporation NAS8-5298 Hydrogen Logistics Investigations Marquardt Corporation CONPLETED NAS8-11250 Feasibility Study of Oxygen/ Hydrogen Powdered Metal Ignition Massachusetts Institute of Technology NAS8-20013 Study of Bubble Formation and Growth Metrophysics, Incorporated N-4S8-11625 COEE'LETE Design, Fabrication, and Testing of Solid-state Thermostats Martin-Marietta Corp . Marotta Valve Corporation NAS8-11834 Certification Testing of 'a Solenoid Operated (Gas Bearing) Normally Closed Valve Assembly �CONTRACT LISTIXG - P DfVISION (continued) CONTMCTOR CONTRACT NLTBSR University of Michigan Change Mississippi State University NAS8-825 NAS8-23228 NAS8-11334 Investigation and Study of Aransient Heac Transfer F? Research S"iuci:- for Determination of Liquid Surface Profile in a Cryogenic Tank During C2s Injection Scudy of Prcosurc Losses in Tubing and Fittings McCormick Selph NAS8-11939 National Research Corporation NAS8-11042 Develop and Establish the Feasibility of Processing and $fixing Technique of Very Large Quantities of Propellants for Solld Propellant Motors Bureau of Naval Weapons Bureau of Naval Weapons Design', Development, Fabrication G Testing of 2 Type E, Xigh TeinperaCure, Confined DetonatLng Fuse Assembly , Tee and Ordnance Manifold Development,of Techniques and Hardware for Insulation Wrappings of Cryogenic Containers H-61447 COFPLETED Start-Stop-Restart Capabilities in Solid Propellant Rocket Motors Program North American Aviation, Inc. NAS8-4013 Feasibility Evaluation of Toroidal Hoop Combustion Chamber North American Aviation, Inc. NAS8-2654 Aerodynamic Nozzle Investigation North American Aviation, Inc. NAS8-4000 COMPLETE NL4S8-4010 CGMPLZTE Multi-Chamber Engines North American Aviation, Inc. Change NAS8-4011;k NAS8-20225 Investigation of Cooling Problems at High Chamber Pressures North American Aviation, Inc. NAS8-11745 Five S-I1 Ullage Motors North Aierican Aviation, Inc. %g~s8-4010- Complete High Pressure Pumping Technology �CONTRACT LISTIXG CONTRACTOR - P CONTRACT E W E R DIVISION ( c o n t i n u e d ) :'L'SZ OF CGYTL-CT North American A v i a t i o n Incorporated NAS8-20237 System A n a l y s i s of Plug Multi-Chamber C o n f i g u r a t i o n North American A v i a t i o n Incorporated NAS8-20143 S t u d y of Pump D i s c h a r g e Pressure Oscillations North American A v i a t i o n Incorporated NAS8-20289 S t u d y of Impact on S - I 1 S t a g e of Improved 5-2 Engine �CONTRACT LISTING CONTUCTOR - T DIVISICN (continued) CONTRACT kUX3XR ;<&hha OF CONTR4CT North Arnerican Aviation, Inc. MS8-11325 lnvestlgation of Positive Type Shaft Seals North American Aviation, Inc. EAS8-iL367 Study of Boiling Transfer with LOX, LH2, and LN2 North American Aviation, Inc. NAS8-$001 Unconventional Injector Feasibility Investigation North American Aviation, Inc. XAS5-LL402 Toroidal System Analysis North American Aviation, Inc. GAS8-11407 CCmLETE 7 kngineericg Xethod to Predict Saturn V Vehicle and Launch Complex Envlroaments due to Rocket Jet Impingement berations Research, Inc. MS8-5321 Compurational and Analytical Support Services Oklahoma State University NAS8 -11009 Study of Fil~rarionMechanics and Sampling Techniques Oklahoma State University NAS8-11302 Skudy the Effects of Acceleration sad Vibrating Forces in Cryogenic and RP-1 Fluids of Filled Conduit with and without Component Parker Aircraft Company Design, Development, Fabrication, Assembly, and Preflight Certification Testing of a Helium Flow Control Xegulator Assembly Parker Aircraft Company Design, Development, and Manufacture of LOX and Fuel Prevalves Parker Aircraft Company DesLgn, Develop, ?-lanufacture,and Perform Qualification Testing-on Saturn I GGX Flow Control Valve Parker Aircraft Company Parker Aircraft Company -.- - 5 NAS8-11595 COXPLETED Develo~mentof Seals for Use in the LOX, Fuel and Helium Systecs of Space Vehicles Design, Develop, and Test 10" LOX Vent and Relief Valve �CONTRACT LISTING CONTRACTOR - I? DIVISION (continued) CONTRACT hTi2BER N K . 2 OF C O K T U C T Parker Hannifin Company NASS-11694 Design, Development, Manufacturing, and Preflight Certification Testing on a Submerged LH2 Shut Off Valve Purdue Research Foundation USE-20222 Improved Fluid Dynzmics Similarity, Analysis and Verification Princeton University MS8- 11216 Pressure Transducers Development and Zvaluation Purolator Products, Inc. XASS-11720 Design, Development, >%mufacture, and Preflight Certification Testing of quick Disconnect Couplings Resistoflex Corporation NASC-11933 Flexible Hose kssenbly Se-rvomechanisms, Incorporated NAS8-5375 Cryogenic Oscillation Dampers Servomechanisms, Incorporated NAS8-11504 Five LOX Containers Relief Switches Solar, A Division of International Harvester NASS-11303 A Study of Liquid Hydrogen Solar, A Division of International Harvester NASS-~ ' ~ 3 4 3 A Study to Advance the State-of-the- Southwestern Industries, Inc. WSS-5333 CONPLZTED Design, Development, Fabrication and Testing of Various Relief and 2ressurizing Switches for the Saturn Vehicle Southwest Research Institute NAS8-11045 Study of Nonlinear Gynamic . Behavior of Liquids in'cylindrical Elastic Containers Technology Flexible Ducting Arc in the Design of Vacuum Jacketed Ducts, Lines and Bellows �CONTRACTOR Initiator Space Equipment Corp. . Spaco, I n c . NAS8-11565 CO$IPLETXD Xodify One Each Flulti-Degree of Freedom O s c i l l a t o r T e a s i b i l i t y I n v e s t i g a t i o n of Rocket 3 n g i n e A n z l y z e r and D e c i s i o n Znsrrumenta:ion f o r S a t u r n V V e h i c l e S p e r r y Gyroscope Company D i v i s i o n o f S p e r r y Rand Corp. NAS8-11290 COMPLETED Sperry h n d Corporation S p e r r y Gyroscope Co. D i v i s i o n NAS8-11229 hocket Engine A n a l y z e r and Cecision lnstrurnentatioc N a t i o n a l Bureau of S t a n d a r d s H-71442 Cryogenic P r o p e l l a n t V e n t i n g Under Conditions Low "essure 7 Design, Development, and Q u a l i f i c a t i o n Testing of Pressure Switches f o r Saturn V Instrument Unit Tavco, I n c o r p o r a t e d NAS8-20152 Study o f Bubble Growth i n a n Oscillating Pressure Field T h i o k o l Chemical C o r p o r a t i o n MS8-11034 Completed Survey o f E x i s t i n g S o l i d P r o p e i l a n t Data T h i o k o l Chemical C o r p o r a t i o n NAS8-11622 COiKPLETE Design, Development, T e s t i n g , and D e l i v e r y of F i v e A c c e l e r o m s t e r Assemblies T h i o k o l Chemical C o r p o r a t i o n NAS8-12396 Com2le~e T h i o k o l Chemical C o r p o r a t l o n NAS8-lTr5-5> COXPLE 2, 3.2velopment of a S t a n d a r d I n i t i a t o r Zozparison T e s t I r o c e d u r e MS8-li3:O X e l i a b i l L t y Improvement and Weight Reduction of t h e S-IC S t a g e R e t r o Kozor NAS8-2i:5v55 COK2LsTZ2 F i v e TX 143-25 S o l i d P r o p e l l a n t Eocket N o t o r s Univ. of T e n n e s s e e L T h i o k o l Chemical C o r p o r a t i o n T h i o k o l Chemical Corp . �CONTUACT LISTTTNG - CONTRACT L C 312 COhiTWCTOR Titeflex A Divtsion of Atlas Corp. MS8-ll;3 , 7 EIVIS'iON (continued) IJJ,:.T GP CONTRACT -. . >es;gn, Development, %nu£ acture 2nd Preflight Certiflcacion Test llexible Hose Assembiies Thompson Ramo Woolridge, Inc, tirilS8-5 - - 3 COM2LEZ.7 TAPCO Division =?sign, Developnent and Fabrication of a Frototype Xydraulic TurEne Pump Combination Thompson Ramo Woolridge, Inc, NAS8-11578 TRW Electromechanical Division Instrument Unit Coolant Tumps X4S8-20248 Low Thrust Throtteable Engine Performance Evaluation United Aircraft Corporation NAS8-li714 Design, Fabricate, and Test Breadboard Liquid Hydrogen Pump United Aircraft Corporation NAS8-5442 Investigation of Pressure Prediction Xethods for Radial Flow Impellers United Aircraft Corporation NAS8-1164.1 Development of an Aerodynamic Rot Gas Valve for Tnrust Vector Control United Alrcraft Corporation NAS8-5370 CONPLETD Use of Hydrogen as a Secondary ~njectantfor T h r u s ~Vector Control United Aircraft Corporation NAS8-11038 A Survey of the Suppression of TRW Space Laboratories Thompson Ramo Woolridge, Inc. - Combustion OsFllatLons with Mechanical Damping Devices L'esign, Fabrication, Testing, and 3elivery of a Kigh Temperature Gas Generator United Aircraft Corporation NAS8-ll752 United Aircraft Corporation NAS8-11024 COWLETZ investigation of Combustion Stability with Liquid Hydrogen/Cold Hydrogen Gas and Liquid Oxygen United Aircraft Corporation NASS-11427 Design Study of an Engine Systeq for Upper Stages of Uprated Saturn United Aircraft Corporation WS8-il436 S ~ u d yfor Evaluation of the Plug ::ultiChamber United Aircraft Corporation NAS8-11438 Determination of Abort System Mission Effects for Saturn Class Vehicles -.- ... United Aircraft Corp . NAS8-20540 -. szquid Gxygen Turbopump Study �COXTMCT LISTING - P DIVISION (continued) CONTRACTOR United Control Corporation WS8-li759 Design, Development, Fabrication, Assembly and Preflight Certification ~estingof a Temperature Control Systen rn United Technology Center Division of United Aircraft NAS8-11380 COXPLZTS Cevelopment of Pelletized Propellants Vickers, Incorporated Aerospace Division Division of Sperry Rand Corp. NAS8-11281 Repair and Iiintenance Services of Kydrauiic Puir,ps Westinghouse Electric Corp. XAS8-11697 CON1LXTE Whittaker Controls and Guidance Division of NAS8-5104 Telecomputing Corporation Wiancko Engineering MS8-11520 n besign, Fabrication, Testing, and Delivery of Three ?rototype Uprated S - 1 Electrical Mozors Development of Fuel and LOX Prevalves Five Helium Bottle Filling Ok Fressure Switches �CONTRACTOR AVCO C o r p o r a t i o n l l e v e l o p e n t of T y p i c a l Mars Landing Capsule S t e r i i i z a t i o n Container �CONTV-L"- CONTKLICTOII P 'I L -- -- -- . >-?. Aeronca Manufacturing Corp. bLAS8-1~739 Aircraft Armaments, fnc. ~:*sa-:;:3 Bell Aerosystems Company KAS8-11215 - Sev2loprnen t of ix2roved Keat Shic1dl;lg pesslbility Study for Full Scale Saturn V Struczural Response to Rocliet Sled Snvironnents Study of Effects of Local Pressure Transients on the Stress Fields in Cylindrical Pressure Vessels University of Alabama Study of the Stability of Reinforced Cylindrical and Conical Shells Subjected to Vzrious Types and Combinations of Loads University of Alabama A Theoretican and Experimental investigation of Shear Lag, etc. Liquid-Solid Systen Integration Study, YLV-SAT-V-4( s ) The Boeing Company The Boeing Company CesLgn Study of the XS-IC Scage for che Kodified Launch Vehicle Sa-iurn V The Boeing Company Study of Resource RequiremenEs for ILV-SAT-V-4(s) Liquid-Solid System Integration Brown Engineering Co . c7 iest Equi~mentfor the Integrated Cynamic Study for Model and Full Scale Vehicles Bolt, Beranek and Newman incorporated Calkfornie Institute of Technology Study of Structural Response to Inflight Acoustic Environment K4S8-24.51 Xesesrch on Failure of zquipment when Subject to Vibration �KiS8- Li332 Columbia U n i v e r s i t y Study of A j s o q t i o n o f Low Fzequency A c o u s t i c Energy i n t h e Atmospheric KedLa Errvironmental D e f i n i t i o n of S e l e c t e d A e r o s p a c e Cargo During A i r T r a n s p o r t a t i c Datacraft, Inc. D a ~ a c r a f t , Incorporated NAS8-li760 A c o u s t i c and V i b r a t i o n Mezsuring Program f o r S o l i d P r o p e l l a n t Booster -~ ~ v e l o ? m e aoft Douglas A i r c r a f t Company Cptinum Design 3 0 c e d u r s s f o r E a n d l l n g Space Vehicle Vibration Douglas A i r c r a f t Company Design S t u d y of t h e XS-PV3 S t a g e f o r t h e X o d i f i e d Laucch V e h i c l e Saturn V Douglas A i r c r a f t Company U S "s- 2 0 5 4 9 Development of Vibration Design Procedures f o r Representztive S t r u c t u r a l Types U n i v e r s i t y of F l o r i d a hLkS8-5199 R e s e e ~ c hI n v e s t i g a t i o n s of Sull&.ead C y l i n d r i c a l J u n c t i o n s Z x ~ o s e dt o Combined Load, Cryogenic T e q e r z t u r e s U n i v e r s i t y of F l o r i d a NAS8-5324 E x p l o r a t o z y S t u d i e s 2nd A n a l y s i s of t h e TroSlein o f Buclciing of C y l L n d r i c a i S h e l l s wi;h I n c P i n e d Stiffeners Elastic Behavior of Sandwich Shells U n i v e r s i t y of F l o r i d a G e n e r a l Dynamics Corp -.- .. A . �CONTMCT LTSTIKG CONTRACT - S G I V X S Z C N (continued) ijr.-?zE?. Generai American Transportation Corporation WiS8-11451 Transportation Design Criteria General Dynamics Corporation KkS&-i.;4L9 Czvelo?ncnt of AnalysLs for Structural Panel instabilities General Electric Company NAS8-11372 Cesign Criteria for Tlaneeary Sp~cecraftto be Sterilized Sy Seating General Dynamics Corp. NAS8-11943 Eevelo;:cent of Heavy Gage Bonded r,uL;eycorr.b r T r _ K4S8-;1C39 CO;\:?LZTXZ Georgia Technical Research institute Goodyear Aerospace Corp . NkS8-11553 -. . -zsign, Subscale Test, Fabricate Scale Model and Test a Full Sczle Nodel of the designed -aoneycoxb Sonded Sandwich Structure of Satura V Inrertank Cyiindrical Structure L. 7 u l l Goodyear Aerospace Corp. Flexlble Vacuum Jacket Bevelopnent Holioman Air Force Base Bcasfbility Study for Full Scale Saturn V Structural Response to Locket Sled Envirornents in Accordance w i t h Scope of Work Herein Illinois Institute of Technology Xeiiabiilty of Structures and Components Subjected to A%ndorn Dynamlc Loading Illinois Institute of Technology "udy .of VibratFons Induced La T>in-Walled pipes. by Fluid Flow lllinois Institute of Technology U Theore~icalAnalysis for DerLving ?.lathematical Yass-Spring Kodels. of Various ?artiaiiy 3ilied Pro~eilant Tanks �CONTRACT LISTIXG - S CIVISION ( c o n i i n u e d ) CONTRACTOR Ling-Tenco-Vought, Inc. &G8-11797 Desigr., 3 ~ v e i o p m e n t , S a b r l c a ~ i o n , ani i4sscably o f a V i L r & t i o n Power T r e i l e r w i t h Electzo2ynmFc Shakers and Associated Components Lockheed A i r c r a f t Corp. WS8-11298 Lockheed A i r c r a f t Corp. ;LSd-li439 - L ~ e s t i g a C i o no f Low Frequency 2 y n a r . L ~Zesponse of O r t h o t r o p i c , Liquid-Ziiled Shells Lockheed A i r c r a f t Corp. N~SS-1147l C?t%m~nS t z t i s ~ i c e lC ~ e r a c t e r L z a t F o n of S a t u r n V i b r a t i o n SaLa Lockheed A i r c r a f t Corp. iYAS8 - 11480 Study of J u n c c u r e S C r e s s F i e l d s -. PecuPlar t o ~ ~ u 1 : i c e l l u l a r l r o p e i l a n t Containers Ling - E l e c t r o n i c s XAS8-il981 S y s t ~ nD e s i g n azd 1ns:a:lation of I 7 i b r a t i o n and A c o u s r i c Equipment Lockheed A i r c r a f t Corp. NAS8-il901 Martin-Narietta Corporation K~58-11323 DesLgn, I l a n u f a c t u r e , T e s ? , Z v a l u a t e & D e l i v e r S2ecirnens f o r Cryogenic 2 u r s r TzsZ ?rograr,l An Inves:igaCion of L o n g i t u d i n a l 3 s c i l : a c i o n I n s t a b i l i t i e s of t h e Satrrrn V LOR V e h i c l e ndighr . : Sgving Through Use o f S e r y l l i u m Aiuainum A l l o y s f o r Sacurn Type V e h i c l e S t r u c t u r e s TT- - M a r t i n - Y m r i e t t a C o r p o r a t i on K~!~S8-11397 ii Sciiay Trogram i n C r y o g e n i c I n s u i a t i o n 2rogram Lockheed A i r c r a f t C o r p o r a t i o n KAS8-15485 Fayload Shrouds S t r u c t u r a l OptirnLzaCion SCudy Y l s s a c h u s e t t s I n s t i t u t e of Technology NAS8- 2594 Establishnent of Guidelines f o r b n d o n arid S l n i l s o i d a l V i b r a t i o n Correlation Measurement A n a l y s i s Corp. ELS8-11154 S e v e l o p ? e n ~o f a Kechod f o r the s L I A L L ~ t iC~a a~ i~ p a r i s oof z ~ n v i r o n n e n t a lData c>,,,-,r.;. "..-.- UL - >9 " .L ?- 5 T7 Keasurement A i a l y s i s Corp. ' \ T - ~ A 2~ g9-~ ~ 2 5 I q r o v e m e n t of Yechnlqaes ? o r t h e C e r i v a t i o n of V i b r a t i o n T e s t SpeciEication KL-SS-20i95 E~-. ,L- l i i i L l l ~ aS l t u d i e s of Cumulative -. . . Kidwest A p p l i e d S c i e n c e Corp. .--:-q-4- Szr;?age �CONTRACT LISTIKG - S GIVISION ( c ~ n t i n u e d ) CeXTTiXCT h-d:bEzFL OT CG?;TxACT ?er:o:icszce of a Rocket S l e d m L Z S C of a S u ? e r i n s u l a t e d Tank Naval Ordnance T e s t S t a t i o n North A m e r i w n A v i a t i o n , I n c . North American A v i a t i o n , I n c , North American A v i a t i o n , I n c $$$% . North American A v i a t i o n , I n c . . . . . cf T,!ehs o f ? a r t F s ? l T e z s i o n ::;:>..iysrs Tie16 Zsaas S c b j e c t e d t o L a t e r a l Pressure L o ~ i i n g s -q'-udy of D e s i g c Tecknlques f o r Srructuce-Cryogenic I n s u l a t i o n Ix-egr&.cion L . .- Axial ?irnsn;ss: a i i i t y C n a r a c ~ e r i s t i c sf o r T y p i c a l 3ocket Vehicie S t r u c t u r e -s z s i g n s - 2 ~ of 6 ~ t h e I\zS-Ii S t a g e - -- tile -X o d i f i e d Launch V e h i c l e Tu, - Saturn V Northrop Corporation Technical Services f o r Sup2ort i n t h e Development o f S t r u c t u r a l A n a l y s i s C r i t e r i a Documents Northrop Corporation Study of E f f e c t on Engine i g n i t i o n on A i r Slow h e r VehLcie Northrcp Norair D i v i s i o n o f Northrop Corp. s s t a b ; i s h m s n t of Zmpe6ance Methods f o r P r e c i L c ~ i n gV i b r a t o r y Xesponses I a V e h i c l e 2nd S p z c e c r a f t S ~ r u c t u r e Northrop Corporation Investigation of Honeycomb S t r u c t u r e 3 e s p o n s 3 t o V i b r a t i o n and A c o u s t i c Zxcltation Northrop C o r p o r a t i o n Norair Division A r x l y t l c z i l end E x p e r i n e i a t a l 3 e t e m i n z c i o n of L o c a l l z e d S t r u c t u r e t o be used i n Laboratory V i b r a t i o n T e s t i n g of S h e l l Structure Mounted Components, S a t u r n V - . 7 �CONTx4C;T LTSZi'G - S North Aiierican A v i a t i o n ~ncorporated NAS8-20509 DTTTISlGN (Continued) DesLgn Z n v e s t i g a t i o n of CyiLndricai S t r u c t u r e s other ,-IEoneycomj L - L L ~ ~ North American .Aviation Incorporated Stu6.y of S h e l l S u ~ p o r c e d Ring Frames w i t h Out-ofPlane Loadings Nor, t h r o p C o r p o r a t i o n j-jec+ UL,n - Study o f :. C m e r a t o r foz :-;I;:: Frequency A c o i l s t i c 2Leld.s f o r L a b o r a t o r y T e s t i n g ~f Flociel S t r u c t u r e North American A v i a t i o n Incorporated NAS8-262,s Study of YCss Loading 3 f f e c t s on LocalLzeu V i b r a t o r y Rocket Vehicie Znvironnents �CONTRACTOR X~2ublicAviation Corp . Republic Aviation Corp. Republic Aviation Corp . Research Triangle Institute Spaco, Incorporated EjAS8-2849 atu urn A:t Fin Flutter M ~ d e l and Bnelysis jQJ-33-1i514- zxBer;n?exts: 3eter;cinz.tion of Syscen 2zr;aeters for ei$n!?ailed Cyilnders uAs3-23522 KLSS-ll3L5 --. ~zvelo2neL~~ of S-cr-dccural ~ese A r t l c lcs f zom Nei~& U~cozve~tiozal, etc 3 2a;lc Be$--rctFrogram in :he Alvanced Studies of Szationary Processes 7 7\:> C'C, , - , -L---..~ ~, h , ~ end G ~ v e l o p ~ e nFzbrica"Lon t L A..,~-11125 2-~;2 ~~~~;Services in %?port or' "ie Saturn V Program Wyle Laboratories, Inc. N A - 0 -l7L. -L,L 7 .-1L3- Wyle Laboratorles, Inc. ATA: - 112 52 Frocedvres azd Tcchnlques for Structures and Siting Criteria 2s Zzfluz~cec2by AcousZics S o ~ n dTraasxlssioa Loss or Strl~ctures -. 226 pzterials ac Low Fr~quencies n . LcsLr--,&, Grouc2 Su13?o;t nesearch Acoustic Tmpeiazce Tes;i=g Szturn Ins2iwment Unit 7, OK Kyle Laboratories, Tnc. y ..;~-5113 "- - -~ .-T-7;- L~.. - .A&d ~nv5rorirnen:~l Li.coustLc Research, Testi~g,and Development Services Wyle Laboratories, Inc. >:---2-53~:& Wyle Laboratories, Inc. >:~;s~-li~2~ h S[~dy to Czterrnine the 3ffects of Clusrering of Solid Engines on Structural Vibration Levels Wyie LaSoratories, Inc. NASS- 11744 Acoustic Research Xodei Study of Acoustic Reverberation Room Planned for Xxperimentai Structures Laboratory . �CONTG,CT L S T I N S Wyle L a b o r a t o r i e s , I n c . - Wyle L a b o r a t o r i e s , ~ n c . - - M S 8 - 11414 1.;.i~;-2;281 " >-- S L.;T ,--... - _.~-L>I (coatinued) Z n v i r o n m e n t a i T e s t s on Su?erLnsuiated S t r u c t u r a l 5;s e c i ~ e n s '" d i b r a t i o n T e s t of SAT3hY T 3 / SX-203 C r y o g e n i c S t o r z g e E o c t l e and Component ;\iounting P l a t e �A r n o l d E n g i n e e r i n g Developmeet C e n t e r Douglas A i r c r a f t Co., I n c . ri-2 1GL'. Crew S e a t i n g acd R e s t r a i n t Sys terns f o r Lvnar Surface Vehlc les KAS8-56 11 Exchange of Advanced Technology on N u c l e a r P r o p u l s i o n and Nuc l e a r S t a g e T? G e n e r a l Dynamics C o r p , Exchange of Advanced Techno logy on Nuc l e a r P r o p u l s i o n and N u c l e a r Stage Goodyear A e r o s p a c e Corp . KAS8-ILS31 COrnLZTS 4 Study i n t h e Nan R a t i n g of S a c u r n Launch Vehic i e S y s terns . NASS-SZS69 A Study i n Lhe Kan X a t i n g of S a t u r n Lsunch , V e h i c l e Systems - Goodyear A e r o s p a c e Cor? �COKTUCTOX Eoneywell, I n c . NAS8-20606 Lockheed M i s s i l e s & S p a c e Co. A K - .- mr a - S y s t e n C ~ L t e r i af o r E x t r a c e r r e s t r i a l Surface Roving Vehlc l e s - ~ n d u trl<--l s FacFlities for Reactnr-In-Flight-Tes t Trogram Lockheed A i r c r a f t Corp. US?-55, - Lockheed A i r c r a f t Corp. NASS-9502 N Advance V e h i c l e Techno l o g y Program Lockheed A i r c r a f t Corp. ITASS-5263 S O?eration;: Xuc l e a r Hazard S t u d y N S e r v i c e s of F i r e De2artnent and S e c u r i t y Badge C l e r i i s i n S u p p o r t o f NASA./U.tSC E f f o r t z t t h e X o f f e t t Hangar Department o f Navy North America2 A v i a t i o n KAS8-202S3 \I A ~ 7 heacror-in-Flight Test Ve;iicle S t a t e (RIFT) Huaan F a c t o r s V i s u a l Simulation Study �S ~ a c eC r a f t , I n c . Space C r a f t , Inc . A CONPLETZ XAS8-ll225 Change XASS-20'53 i S t u j y orL U t < l i 7,?,,+,o' n of S a t u r n I3 I n s t r y ; r ~ e n t ~ t L o n 3nit t o Su??o:L Space ~ -x p c r i r c e n t s 7 In=ec--c-;iu L Lon LA S t u d y of AL of StanZarcl Pay i o a d $:oduies c - 1l; ca o n t h e S z r u r n IE Launch Vehicle U n i t e d A i i c r a f t Corp. KAS8-20?' 5 A ?kin-System ?ask A n a l y s i s f o r Lunar Surface Experiments � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000032 Title A name given to the resource Active contracts list, Propulsion and Vehicle Engineering Laboratory. Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center Date A point or period of time associated with an event in the lifecycle of the resource 1965-12-30 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) United States. National Aeronautics and Space Administration--Procurement Contracts Government contractors--United States Type The nature or genre of the resource Reports Text Source A related resource from which the described resource is derived Saturn V Collection Box 15, Folder 42 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050 https://digitalprojects.uah.edu/files/original/20/980/spc_stnv_000033.pdf ba36783a664d0f0d3d950b9c79b13dd4 PDF Text Text March 24, 1965 Lee: Please accept t h i s as additional script information for Saturn I/IB Rpt. Nr. 19 L. Lucier �FILM NARRATION DISSOLVE. TO : . A t P r a t t & Whitney A i r c r a f t ' s SCENE -- Connecticut Operations, f a b r i c a t i o n and 0-1329 assembly of the RLlOA-3-1 s e r i e s engines L.S. is continuing. of P r a t t & Whitney Aircraft building a t East Hartford, Conn. The A-3-1 configuration i s e s s e n t i a l l y CUT TO: SCENE -- an RLlOA-3 engine designed f o r improved d u r a b i l i t y and performance LS, shot of Mae West Section . of RL~OA-3-1;.tilt down. Four of these engines have been delivered CUT TO; SCENE -- t o P&Wfs Research and Development Center MS, man places gimbal A t west Palm Beach, Florida, f o r acceptance on engine-follow up with t e s t i n g p r i o r t o delivery, t o NASA. MS of man checking turbopump. Improved solenoid valves have been CUT TO: SCENE -- LS,.transducer encloseure area. on engine, showing two t r a n s - incorporated i n t o both t h e RLlOA-3 . The improved solenoids arid A-3-1 engines. ". reduce v a r i a t i o n i n cuto6f impulse, o f f e r i n g ,* ducer boxes--follow up with MS of both r i g h t and l e f t solenoids. f u r t h e r increase in' payload c a p a b i l i t i e s . �FILM NARRATION CDT TO: To f a c i l i t a t e t h e s t u d y of p r o p e l l a n t -- SCENE supply systems f o r advanced space MS, 3 i m p e l l e r s , used i n v e h i c l e s , a newly designed inducer has inducer i n h o t water. been designed and i s undergoing t e s t i n g loop t e s t i n a h o t water loop, CUT TO: SCENE In t h e t e s t , t h e behavior of cryogenic . -- p r o p e l l a n t s is s i s u l a t e d by u s i n g h o t CU, .impeller i n r i g , water which provides an a c c u r a t e s i m u l a t i o n spinning--follow up of.cavitation characteristfcs. w i t h MS, of man a t c o n t r o l s and CU of impeller spinning. CUT TO: SCENE P r a t t & Whitney w i l l continue t h e t e s t -- program t o determine t h e f e a s i b i l i t y of LS , v a r i a b l e t h r u s t eggine developing t h e v a r i a b l e t h r u s t c a p a b i l i t y i n s t a l l e d i n #E-7 t e s t s t a n d , of t h e RLlO engin:. follow up w i t h LS, e i i n~e i n s t a n d during v a r i a b l e t h r u s t run. � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000033 Title A name given to the resource Additional script information for Saturn I/IB Report no. 19. Creator An entity primarily responsible for making the resource Lucier, L. George C. Marshall Space Flight Center Date A point or period of time associated with an event in the lifecycle of the resource 1965-03-24 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) Saturn launch vehicles--Testing Saturn 1 launch vehicles Saturn 1B launch vehicles Space vehicles--Design and construction Type The nature or genre of the resource Correspondence Text Source A related resource from which the described resource is derived Saturn V Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Is Part Of A related resource in which the described resource is physically or logically included. Uprated Saturn IB Quarterly film report and related materials #19, 20, 21, 22, 23, 24, 25, 26 Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050 https://digitalprojects.uah.edu/files/original/20/981/spc_stnv_000034.pdf 69f79604363ff3e971b9fd365d1f7444 PDF Text Text // *' A DISCUSSION OF THE LUNAR LANDING PROBLEM F r e d E, Digesu As trionic s Division Marshall Space Flight Center, NASA Huntsville , Alabama To be presented at the AIAA Guidance % Control Conference Massachusetts Institute of Technoi-3gy Cambridge, Massachusetts f ~ u ~ u s12 t - 14, 1963\ �A DISCUSSION OF THE LUNAR LANDING P R O B L E M Serious talk concerning placing srsrnet5ing 01-1 the moo2 beg2.n same s i x to eight years ago with an A", F a r c e 71hqrdlanding" project b a s e d u p o n a Thur missile f i r s t stage. The landing g e a r of this probe w a s a metal spike which was to be driven E ~ t ot 5 e lunar surface, and t b e designation "hardlanding" was qu'L',e ~ppro7rtatefop t h e anticipated impact shock of s e v e r a l hundred g - a v f t i ~ s . B e c a u s e of limited payload capability the concept was, of nsceseity, v e r y simple. A direct ascent ballistic injection w a s envisaged with the yayloa d stage spun u p to stabilize it in an inertially -fixed o m - i e ~ t a t b immediately n after injection. The inertial direction wa,z ',?ken such that t%e spike would be parallel to the lunar local vertical at !mpzct. SEiortly before impact, a retrorocket, ignited by timer, wag to remove the major portion of t h e descent velocity. Error ana.lyse:le 2,nd assessment of the probability of impact with no possibility for midcour a e correction showed that "fly-by" would be the mere e x r e d i e ~ method t of e x p r e s s k g the mission abj ectives. Indeed, similar p - o y o s z !..+ by t h e Army based upon a Jupiter missile first stage claimed cnly E near miss possibility. T h e s e studies and proposals bore f r u i t in the Pir.dqeer s e r i e s of lunar probes, which, despite their enfcrc ed adberenc e ?r>simplicity and thus its inherent high reliability, met with ratlcer lirnLted success. W e are still talking about landing on t h e mcc-I and while the overwhelming concensus is that it is well within the state of the art, somehow we haven't quite a.ccomplished the f.12 t a5 y e t . So when I say "state of the a r t " wkat. E r e a ily mean t s lT3tateof the study'? since we have yet to demonr;t;ra.te f r n ,=.!.l ity f! with a piece of hardware, �Studies now exist, t o varying d e g r e e s of depth, for many modes of l u n a r landing. A s i d e from the Atlas -Agena boosted Ranger and the A t l a s -Centaur boosted S u r v e y o r , the interest in these s t u d i e s seems to be centered around the Saturn boosted class of vehicles, the Apollo mission, and the various unrna.nraed Ixnders ~ ~ o p o s easd s u p p o r t of and to augment such landings. Thus w e a r e begicr~ingt o look at lunar payload capabilities of t 5 e 3 t o 4 thousznd Ibs of t h e Saturn I B , the L E M t r u c k capability of from 6 to 8 thousand I b s . , and the Saturn V Lunar Logistic vehicle capability of 2rour.d 31! t:"louse.ndr: Ibs . on the rncon. Of course, landed pa ylo2.d weight w o u l d ~ r c b a b l ynot be a fzix way to d e s c r i b e the lunar excursion modu1.e in t\r! Ano!lo mode, but the total L E M weight of around 2 5 t;housand pound..; is typical of tl?e class of landers with which these s t u d i ~ zd e a l . . H e r e then, i s the real break-through. W e a y e coming to the paint where we have the weight lifting capability for the i n s t r u m e n t a tion and the power supplies needed f o r a somewIlat m o r e cornfortable design margin f o r the mission r e q u i r e m e n t s . The c e e d f o r microminiturizatiwn and minute power r,or,sumptiox is no longer acute and can he traded far r e l i a b i l i t y , longer rar_g.=,arid firwif.~ra c r u r ? , ry, Of c o u r s e , this pre-supposes the d e v ~ l o p m e z tof fuel rel1.s t o s u p ~ l y this power and it could well be s a i d t5at this is a pzcing item. Parenf.hetical2y I might mention that the developmert of radio-isotope power supplies ma.y well be the pacing item for int;e-t.::;~.nzt;.,sy m i s . s i a n ~ . It is difficult to place the l a n d e ~ r 3into b:::,?s: cat cgcries other than the obvious one of manned and u n r n a n ~ e d . However, suSdivi5ions caxl be made under these two categories Z.-i a ~ a u g h l y~ a . r z 1 3ed manner, These subdivisions would be along the I l s e : ~c f tk:e c.;"+rationa,l requirements a ~ the d apriori knowledge as signed t o tv:e i n ~ . f ~ u m e ntion.. ta W h i l e no s i n g l e factor in itself determiner, t17e c~ve?x!I system, its components a n d degree of complexity c8.n 5 e nl-rlwn t n be influenced s t r o n g l y by: a.) The proposed flight profile b) The location at whickr the nzvig~.bir>nalfunction is ~ e r f o r r n e d (an bozr d or on ground) �c J The constraints upon the vehicle velocity at lunar touchdowa d ) The d e s i r e d versatility in landing site selection 3 ) The d e s i r e d location accuracy in t h e landing It will be found that g e n e r a l l y the manned missions wi1.1 contain the m o r e complete and extensive s e t of equipments. T h i s a t e m s from the fact that I ) Man has a g r e a t e r capability f o r reliability using a larger variety of ins trnrnentation, and 2 ) The tendency is to l e a n tow2rd making ths manned vehicle a:$ self sufficient as is possible. In pursuing these points, consider the block diagram of F i g u r e 1 which is general enough t o apply to any mission. Indeed, it contains the elements for any form of guidance since it is capable of either dead-r eckoning o r of positioning navigation. The trade -off in the various subdivisions cited previously will determine the degree of completeness of the block diagram f o a3y ~ specffic mission, .7.s w e l l a.s the componexlt complexity and charact~,r!~t:,cs. First consider the flight profile. At earth's end, it is customary to use a parking orbit of f r o m up t o several o r b i t s far A70110 d o w n t~ one o r b i t or less f o x unmanned miasions such a s R a n g e r , Surveyor, cr t h Saturn ~ V Lunar Logistic vehicle. P u r e i n e r t i d injection h a s b e e n shown to be well within the midcourse ca~rection'vel.ocitybudget for t h e one orbit or l e s s c a s e s , I whereas updating of the inertial system by nnboard or ground bxs ed tracking may ba r e q u i r e d fox the longer orbital stay times. At t h e lunar end, the approach to the landing s i t e can be either direct as in the Ranger and the Surveyor, or through ~ p ' S ? i3.3 t in the A20110 a.nd the Lunar Logistic vehicle, In reviewing the implementation of these missions profiles, it b e c o m e s clear that the key factor in t h e design of the guidance equipment is location (on the vehicle or on t h e ground) of the t h r e e guidance functions of: �1. Navigation (that is, the determination of the vehicle positionvelocity state vector) 2 . Computation of the r e q u i r e d maneuver to r e a c h the desired final state vector 3. Supervision and measurement of the c5enge in the vehicle state vector throughout the maneuver. The time in which each of t h e s e functions must be performed is a f o u r t h and heavily influencing factor upon the guidasce hardware. It is with the midcourse phase of t h e lunar t r n n s i - t that we begin clur review since this paper is concerned with t h e guidance problems confronting the spacecraft. For a ground-based navigational s y s t e m , items 1 and 2 a r e e a r t h based while i t e m 3 remains as an onboard function. A functional diagram of such a system i s illustrated in Figure 2 . Two angles, rela.tive range and/cr rznge rzte, a r e measured t o t h e spacecraft. Computations on these measured qulintities determine s p x e c r a f t position and velocity. Prediction of t 5 e future s t a t e of the vehicle is obtained by solving the equations of motion. Computations of the required maneuver to meet d e s i r e d end conditions of velocity and position a r e m a d e and t r a n s m i t t e d t o t h e spacecraft f o r execution. Onboard i n e r t i a l equipment super-vises and measures the maneuver. This concept I e a d s to the greatest simplificatien of t h e onboard system. It is only necessary that t h e r e be a. kcown m i e n t a t i o n of the guidance coordinates aboard the vehicle. S h r t t e r m (in the o r d e r of minutes or hours) stabilization of these a x ~ siz don- by gyroscppes; however, since gyroscopes a r e subject to random d r i f t s (to a g r e a t e r or l e s s e r d e g r e e , depending u p n the quality of the g y r o ) , long t e r m (in the order of days) stabilizatioxl of the guidiance coordinate a x i s is done by optical means. The optical devices deptcted in the block diag r a m of Figure 1 s e r v e t o supervise the a l i g n m e ~ tof the inertia.] j.nstrumentation, but this is a unique function f o r tSe ground-bas ed �navigation s c h e m e we are discussing. The onboard computer in such a system can be a relatively simple device, consisting of little m o r e than a program s e q u e n c e r , Most c e r t a i n l y capable of doing the e a r t h - b a s e d tracking and cavigation 505 a r e thq stations of the Deep Space I ~ ~ t r u m e n f - , z t i o a Facility of the J e t P r o p u l s i o n ~ a b o r a t o r ~ . 'Tte6e a r e ins?zl!ations located at 120 d e g r e e i n t e r v a l s a r o u n d the w o ~ l din Goldstone, California, Woomera, Australia, and Johanneahurg, Sout? Africa; each ,s ta,tion t ~ a c kwith an 85-foot dish antenna an4 wit;$ a quoted a n g l e t r a c k i n g accuracy of 0.01. to 0.02 d e g r e e s , a ?Erg? r a t e accuracy in the o r d e r of 0.2 m/s, and a ranging a c c u r a c y cf f30 m e t e r s , when incas-porated. * The concept of onboard navigation places a much stiffer r e q u i r e ment upon the guidance Instrumentation. Along with supervising t ? ~ mientation of the i n e r t i a l measur ernent unit, the optical devices must p e r f o r m the additional duties of mea.surtng a n g l q s and distances cf c e l e s t i a l bodies. The guidance computer m u s t r e r f o r m the f u q c tions of computing position from th.-s e rnea.:.rilred q u a z t i t i e s , ~ r e d i c t i n g t h e l a t e r s t a t e vector, and calculating t h mar?.t?uver r e q u i r e d to meet d e s i r e d end conditions, F o r the m i d c o u r s e phase, the m e a s u r e r n e n t ~a r e all angular measurements ( d i s t a n c e must be taken by a tadinmetric measurernenta since u s e of onboard radar ranging is prohib;.ttve in power r e q u i r e d ) , and the long distances involved a c t t o give l a r g e po3ition uncertainties £ O P even small angular measurement e r r or. HQWever, a rriitigxting c i r c u m s t a n c e is that the times i ~ v o l v e dare 30r4 6 0 that a. n u m b e r nf measurements can be made and the data i r ~ m t h e s e can be at?-tistical ly pxoces s e d ("'smoothed") to give smaller pos it!.on uncertain tie^ T h e r e a r e mamy smoothing techniques d i s c u s s e d in t % e 1litera.ture, s u c h as c u r v e fitting by least squares, weighted l e a s t squares, minimum variance, a n d the Schmidt- Kalrnan technique3 nf o?tirnal f i l t e r i n g . . 4. This l a t t e r technique with work by Batti?, w'here he d e r i v e s the optimum plane in which to make the measurement and where each �can be a single m e a s u r e m e n t , is the onboard midcourse navigation s c h e m e planned for Apollo. To e a s e t h e load on the airborne computer, l i n e a r i z e d forms of t h e nonlinear motion equations and the measurem e n t c o o r d i n a t e s are i m p l e m e n t e d by using the first order terms of a Taylor series expansion about a reference t r a j e c t c z - y . - - For example,'the equations used f o r predicting future state, f r o m present s t a t +e , ,I:[ takes t h e form: 5 A4 W h e r e t h e Ai are 3 x 3 s u b m a t r i c e s of partial derivatives evaluated along t h e r e f e r e n c e t r a j e c t o r y . At lunar end, the planned a p p r o a c h e s t o the landing s i t e ( d i r e c t o r through o r b i t l , the t h r u s t t o weight r a t i o of the spacecraft, a n d the accuracy with which the end points m u s t be met influence the system characteristics. M e a s u r e m e n t s from t h e spacecraft t o the lunar target become mandatory t o determine it:, relative position and velocity t o within a c c u r a . e i e s r e q u i r e d by cons t r a i n t s upon t h e t r a j e c t o r y endpoints. F o r the Ranger d i r e c t c a s e , where a h a r d landing is permissible, w h e r e t h e direction of t h e velocity vector at touchdown is allowed to deviate 5 y 4 5 degrees f r o m the vertical, and w h e r e no specification SF; made ur,on t h e l o c a t i o n of the landing s i t e , the landing s e n s o r is a radar p r o x i m i t y fuse. H o w e v e r , even in this case, the dispersion volume a t r e t s o ignition r e q u i r e s that a.t least one m i d c o u r s e guidance c o ~ r e c t i o nbe made. For t h e soft landing Surveyor, the c o n s t r a i n t upon t h e direction of the velocity v e c t o r at touchdown r e q u i r e s determina.tion of all cornponerzta of t h e velccity vector relative to t h e lunar s u r f a x e as an additinna.1 meaqurement. The flight profile for the landing t l r o u g h lunar orbit is shown in F i g u r e 3 . F i r s t t h e r e is t h e brake t o lunar. orbit, then a d e s c e n t kick, an approach braking, a v e r n i e r , a hover (for FL manned Apollo L F M ) , and the touchdown. �The brake to lunar orbit will usually be a long burn during which pitch s t e e r i n g according t o some guidance law m u s t be performed. Studies show6 that it is possible t o control the plane of the lunar orbit b y choice of the trans it injection parameters at e a r t h end; thus a large plane change will probably not be 2. requirement on the lu3ar o r b i t b r a k e maneuver. Prior t o the braking burn, alignment of the onboard i n e r t i a l equipment f o r supervising the maneuver m u s t be done with reference t o a lunar -fixed coordinate s y s t e m . This can be done directly with a lunar horizon s e n s o r o r indirectly with a s u n and stzr s e n s o r and a knowledge of the reIative position of the spacecraft and moon. The accuracy with which the brake lo lunar orbit must be accomplished is dictated by the altitude at which this orbit is to be established. Navigational and execution inaccuracies will c a u s e a decrease in peris elenurn altitude. The accuracy required of the xlavigztional s y s t e m can be inferred from the fact that initial condition e r r o r s at the beginning of the brake of 1 m/s in velocity, or of 0. 1 5 d e g r e e s i n the velocity direction, o r of 1 km in altitude would each lead t o an ellipse with a n altitude error of 5 k m at periselenurn over a desired 185 krn c i r c u l a r orbit. O n c e the spacecraft is in orbit, naviga.tior_ must be done to establ i s h its ephemeris relative to the lunar coordinate s y s t e m . The s a m e techniques u s e d for midcourse can be used h e r e , with the same implications in the hardware. Descent from lunar o r b i t is accomplished i2 a n u m b e r of ways. T h e r e v a r y from a descent kick which puts the ~ p a . c e c r a f into t a Hohrnann t r a n s f e r , with approach braking initiated at p e r i a p s i . ~ ,t o t h e Apollo L E M descent kick into the equi-period ell i p s e , with approach braking a l s o initiated a t periapsis, to a conti~.uousburr:. down f r o m the parking orbit. In Figure 4 are plotted some representative landing t,rajectories f o r the Saturn V Lunar Logistic vehicle and f o r the Apclllo L E M , t h e 1ower altitudes being the periaps e s of the previously mentioned descent ellipses. It is well t o note h o w initial thrust to weight r a t i o , F/WQ, affects the r e q u i r e d m e a s u r i n g range (the lower the F / w ~ ,the g r e a t e r the distance of the ignition paint). �The F/WO and t h e altitude can combine s o that the landing point is out of sight below the horizon at ignition. If this is the case the ignition point m u s t be determined by navigational methods which have been discussed previously, but which s u f f e r from the fact that t h e vehicle state vector r e l a t i v e to the landing site must b e a r r i v e d at through indirect measurements and eornputation~. The i ~ a u h e e r e i z whether: a ) The landing m u s t be a soft one on a smooth a r e a within a relatively small radius of a specific loca.ticrx, or b ) The landing m u s t be a soft one cn a smooth area but the touchdown location is relatively immat.eria1. The first case is a two point bounda.ry value ~ r o b l e mthat has a unique solution for the case of minimum fuel. Errors in knowledge of the initial conditions l e a d t o w a r d over expenditure of fuel. Since surface d i s t a n c e t r a v e l e d is not a dependent quaqtity in t h e second c a s e , the requirement upon the na.vigation syn tern is c o y r e ~ p o n d i n g l yeased. In Figure 5 a r e plotted s o m e of t h e n a . v i g a t i o ~ a lstate parameters of the vehicle relative to a specific landing point f o the ~ a9prnaeh braking trajectories g i v e n in F i g u r e 4. Methcds for Implementing these measurements range from radar tracking of a beacon a t the t o doppler aided television or optical sightings of point in the landing point from the vehicle, Once the components of the vehicle relative s t a t e vector are determined, the guidance function of computation of the t h r u s t m a n euver t o meet desired end points must be done. Here a.gain we czn find a wealth of material on the ~ u b j e a t p ,in t h e l i t e s a t u r e . This i~ called the "guidance logic" and u s u a l l y takes the fcrm of a functional r e l a t i o n s h i p t o be maintained between t h e vehicle s t a t e v e c t o r a n d t%e direction a n d magnitude of the t h r u s t vector. TI-:<;. guidxnc.e logic relationship i s usually derived from the p o i n t of view of constraining the vehicle to some "minimum energy" p-7 th for t h e d e s c e n t . The computational p r o c e s s e s r e q u i r e d r ~ x ~ g from e exylic:t solutfon cf the equations of motion (sometimes in linearized farm) t o a. simple comparison and enforcement of the measured t ~ z j e l = t o r ydata t o conf o r m to p r e e t o r e d data for a precomjmted standikrd descent. �The type and processing of the m e a s u r e d data., the computer carnplexity, and the fuel expenditure in reaching desired end conditians from perturbed initial conditions all enter into the arguments in the implementation of this phase of the trajectory. The v e r n i e r , h o v e r , and touchdown part of the lazding profile will now be b r i e f l y discussed. The purpose of these phase^ ir; t o in:iure ;i ,;oft and stable landing on a smooth l u n a r surface. The definiticn of "emcrotEaM is usually obtained after a lively discussion between the vehicle: de,<i g n e r , the propulsion people, and the guidance sy3tem e n ~ i n n e r ,with ~ e r h a p sa l u n a r surface "expert" included to make t h e s u b j e c t e v e n more interesting. It is readily apparent-that the sinking velocity a t touchdown directly influences the a i z : ~ of the landing gear. Engine throttle ability becomes a requirement for a very soft toucFldown or % hover capability, the throttle range being a function of the velocity d i p i ~ e r ~ i o r ,at :3 vern?er altitude, the v e r n i e r guidance fogir, ar.d the 3p7i;lir a f t ma 3 5 touch-. down. It is found, however, that vehicle staSi1:ty (i. e . , r e s i s t a n c e to toppling) i s a c r i t i c a l factor for t h e l a r g e r s > a c e c r ?3. Tho stability cf the vehicle a t lunar touchdown is a functia? of t h e lzgding p e a r s p r e a d and the induced ti2ping moment. Thi,q t i p ~ i n gmoment resuZ t s from su?fa,:e roughne 5 rj (toul d e r a, craters, e t c . ), the slope of the r u r f a r e , the :lur-E7s.c-e friction, a n d the vehicle l a t e r a l velocity at touchdown. Loweriag the vehicle center of gravity increa.3 e s vehicle stability, but unfortunately t5is a l o has the effect of decreasing the engine swivel con,rcl ziomer,t a r m . T h e r e i s thus a definite lower limit f o r the c m t e r of gravity position. Increasing the landing g:ay s ~ r e a bd. ~ ' , n p?; on packaging, manipulation (extens ion, e tc. 1, a ~ weigkt d ~ ? c t ? e m ; : : . Deer ea,sing the landing l a t e r a l velocity dispersion ircrea:>e z the dernaad;.; upon the m e a s u r e m e n t of this quantity. 7 �A proposed solution to this m e a s u r e m e n t p r o b l e m is the u s e of a 3 b e a m doppler radar velocity sensor a s shown i n F i g u r e 6. An unknown in t h i s solution is the lunar dust effect. T h e altitude at which the dust cloud r a i s e d by the engine begins to render radar ineffective is open t o c o n t r o v e r s y , but certainly it i.5 sornet:eLing ot3.e;. th3.n z e r o . Thus the actual landing will be done on i ~ e r t i a m l e m o r y with initial conditions s e t into the i n e r t i a l equipment from the last r ~ . d a rfix. R a d a r e r r o r s enter a s initial condition e r r c r s into the i n e r t i a l equipment. Since these e r r o r s thus become time function:, the higher the East radar fix, the m o r e the dead recknnicg e r r c : a c c r u e m e n t , and the greater the touchdown dispe-rsion. Obstacle identification and avoidance during d e s c e n t b e c o m e s a requirement if a landing at s o m e unexplored location :s d e s i r e d . Inclusion of television in the guidance is offered E;- a s o l u t i n n t o t5is problem. The television loop could be c l o ~ e deit5er directly on the vehicle o r through an earth cornrnunicationa link. Consideration of l u n a r ascent z ~ l de r t h z e t u r n i ? , for the moment, of i n t e r e s t only in t h e m a a n ~ dl u n a r l i + ~ A i n g. = w e ,tlzrzt i,;, i n t h e Apollo m i s s i o n . H e r e the additional functiors cf lunar o-Sit rendezvous and earth r e -entry m u s t be d e s i g n e e into the gutda.nce system. Earth return from l u n a r landing is e a s i l y a, subject f o r another paper and will not be t r e a t e d h e r e . �REFERENCES 1. N e i g h b o r s , A l i c e K . ; Cole, John W . : a n d D a n i ~ 1 ,Fred: ' E r r o r Analysis of Saturn Guidance Hardware a x Applied to a Lunar Mission, " N A S A ( M S F C ) MTP-ASTR-A-63 - 4 , M a r c h 13, 1963. ( C ) 2. Noton, Cutting, and Barnes: "Analysis of Ra:"io C o m m a n d MidC o u r s e Guidance, J P L Technical Memo N o . 32 -25. September 8, 1960. 3. S m i t h , G e r a l d L . , Schmidt, Stanley F., and M c C e e , L e o n a r d A . : tlApplication of S t a t i s t i c a l Filter Theory t o t h e Optimal Es timation of P o s i t i o n and Velocity qn Board a Circumlunar Vehicle, ' I NASA TR R-135, October 9 , 1962. 4. B a t t i n , Richard H. : "A Statistical Optimizing Navigation P r o c e dure for Space Flight, I ' Massachusetts f ~ s t i t u t eof Technology, ARS NO. 2461 - 6 2 . 5. McLean, John D. , S c h m i d t , Stanley F . , and McGee, Leonard A . : "Optimal F i l t e r i n g and Linear P r e d i c t i o n Applied to a Midcour s e Navigation S y s t e m for the Circumlunar M i ; q ~ i o n", NASA T N D- 12C8, M a r c h 15. 1962. 6. Hoelker, R . F. and B r a u d , N. J. : "Survey and Classification of E a r t h - M o o n T r a j e c t o r i e s Based on Newly Dtqcovered P r c p e r t i e ~ ", NASA (MSFC) MTP-AERO-63-39, M a y 2 0 , 1963. 7. Marshall Space F l i g h t Center: " L u n a r Logistic System, (MSFC) MTP-M-63-1, March 15, 1963. NASA �.,, ,.,..- . _ . .- = , . ._ ,.,...:. ...* . I . : . ., ., . , ,, , ,- . , . , . , ,, I , ., ������ Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000034 Title A name given to the resource "A Discussion of the Lunar Landing Problem." Description An account of the resource Digesu worked in the Astrionics Division of MSFC. This paper was presented at the AIAA Guidance & Control Conference, Massachusetts Institute of Technology, Cambridge, Massachusetts, August 12-14, 1963. Creator An entity primarily responsible for making the resource Digesu, Fred E. George C. Marshall Space Flight Center Date A point or period of time associated with an event in the lifecycle of the resource 1963-08-12 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) Space flight to the moon Lunar landing Type The nature or genre of the resource Reports Text Source A related resource from which the described resource is derived Saturn V Collection Box 9, Folder 25 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050 https://digitalprojects.uah.edu/files/original/20/982/spc_stnv_000035.pdf 52b477f7878cd332cdc51071cfab7976 PDF Text Text A p r i l 28, 1960 ADMINISTltATORgS STATEMENT ON THE, SELECTIOEJ OF A COIJTR-21.CTOR FOR THE SATURN S-IV STAGE On A p r i l 19, 2960, t h e Source E v a l u a t i o n Board appointed t o evaluate t h e c o n t r a c t o r ' s proposals f o r t h e S a t u r n S-TV s t a g e made a p r e s e n t a t i o n t o me i n c l u d i n g t h e chronological s t e p s taken i n t h e evaluation process, t h e t e c h n i c a l and b u s i n e s s e v a l u a t i o n d a t a i n g r e a t det a i l , and t h e Board" a n a l y s i s of t h a t d a t a . T h e r e a f t e r I s e l e c t e d t h e Douglas A i r c r a f t Company, I n c . , a s t h e c o n t r a c t o r w i t h which t o n e g o t i a t e a c o n t r a c t f o r t h e development of t h e S a t u r n S - I V s t a g e . Among t h e cons i d e r a t i o n s i n f l u e n c i n g my c h o i c e of a c o n t r a c t o r , t h e f o l l o w i n g r e a s o n s seemed t o me c o n t r o l l i n g : I. The r e p o r t of t h e Source E v a l u a t i o n Board, i n c l u d i n g t h e back-up m a t e r i a l provided by t h e T e c h n i c a l and B u s i n e s s A d m i n i s t r a t i o n Committees, showed t h e t e c h n i c a l competence of t h e two o r g a n i z a t i o n s -- Gonvair and Douglas -- t o b e n e a r l y t h e same a s r e v e a l e d i n t h e i r p r o p o s a l s , A sliqht edge g i v e n t o Convair d i d n o t seem t o me t o b e c o n t r o l l i n g . The Douglas p r o p o s a l , i n some ways, seemed more i m a g i n a t i v e . Conversely, t h e r a t h e r lower r a t i n g g i v e n t o Convair by t h e Business Administ r a t i o n Committee would seem t o i n d i c a t e o n l y t h a t a t t e n t i o n t o c e r t a i n of t h e d e t a i l s of o r g a n i z a t i o n was l a c k i n g . I n t h e c o u r s e o f n e g o t i a t i o n of t h e c o n t r a c t , e i t h e r o f t h e s e shortcomings would b e c o r r e c t e d , i n a l l probability. C o n v a i r ' s work on Centaur undoubtedly gave them a s l i g h t edge i n t h e t e c h n i c a l compet.ition. 3- I 2. C o n s i d e r a b l e importance must be g i v e n t o a cons i d e r a t i o n o f t h e d e s i r a b i l i t y of a t l e a s t l i m i t e d comp e t i t i o n a s we s t a r t o f f t h i s new technology. Should a l l work b e c e n t e r e d i n one company, it might w e l l b e t h e c a s e t h a t subsequent c o m p e t i t i o n s f o r t h e o t h e r s t a g e s of S a t u r n would become q u i t e one-sided. A monopol i s t i c p o s i t i o n i n t h i s f i e l d seems p o s s i b l e and should b e avoided u n l e s s s u b s t > a n t i a l l yi n c r e a s e d c o s t s would 4at 1 i �be i n v o l v e d o r u n n e c e s s a r i l y complicated management, arrangements r e s u l t . An examination of t h e s e f a c t o r s produces a n e g a t i v e r e s u l t -- t h a t i s , no inzportant c o s t o r management problems a r e expected t o a r i s e i f a second a i n d u s t r i a l o r g a n i z a t i o n e n t e r s t h e f i e l d . Indeed, some b e n e f i t s m a y w e l l a c c r u e . Broadening t h e i n d u s t r i a l b a s e i n hydrogen v e h i c l e technology i s i n t h e b e s t national interest, 3 , S i n c e b o t h p r e f e r r e d p r o p o s e r s a r e primary A i r Force c o n t r a c t o r s , a review of p o s s i b l e i n t e r f e r e n c e s w i t h on-going o r planned A i r Force programs by t h e i n i t i a t i o n o f S a t u r n SV was i n s t i t u t e d . Assurances were had from t h e A i r Force t h a t c a p a c i t y was a v a i l a b l e i n b o t h o r g a n i z a t i o n s -- p e r h a p s a b i t more completely i n Dougl a s , b u t a d e q u a t e l y a v a i l a b l e i n Convair . Q 4 . C o n v a i r k c o n t i n u a t i o n w i t h Centaur (S-V) i n s u r e s a Larger s h a r e of p r o d u c t i o n b u s i n e s s f o r t h a t company s i n c e S-V w i l l 'be used b o t h w i t h S a t u r n and A t l a s -- i n f a c t , may w e l l become one of t h e "work h o r s e s " of t h e s p a c e program i n b o t h m i l i t a r y and nonm i l i t a r y a c t i v i t i e s , Thus, l o s s of t h e S-IV c o n t r a c t has more p o s i t i v e f e a t u r e s i n t h e i n i t i a t i o n of comp e t i t i o n than disturbing features i n t h e possible l o s s o f s i g n i f i c a n t amounts of on-going b u s i n e s s . Both ope r a t i o n s w i l l c o n t i n u e t o b e h e a l t h y -- n o t u n n e c e s s a r i l y starved t o achieve competition. nn an tor � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000035 Title A name given to the resource "Administrator's Statement on the Selection of a Contractor for the Saturn S-IV Stage." Creator An entity primarily responsible for making the resource Glennan, Thomas Keith, 1905-1995 United States. National Aeronautics and Space Administration Date A point or period of time associated with an event in the lifecycle of the resource 1960-04-28 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) United States. National Aeronautics and Space Administration--Procurement Government contractors--United States Saturn S-4 stage Type The nature or genre of the resource Administrative reports Text Source A related resource from which the described resource is derived Saturn V Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Is Part Of A related resource in which the described resource is physically or logically included. NASA HQ Miscellaneous Correspondence August 1968 Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050 https://digitalprojects.uah.edu/files/original/20/983/spc_stnv_000036.pdf 6eb3c8813129aea297f81174b1a84f4f PDF Text Text rnANCES IN PIWrnG TErnOLOGY AM) ROCKET EXGI?ii TlTRBOmMP APPLICATIONS C h m l e s A. MacGregor Supervie or Advanced Turbomachinery D~~~ ---------- Doc. No. -------- Rocke tdyne A D i v i s i o n of Korth American A v i a t i o n , Inc. Canoga Park, C a l i f o r n i a Royce Hall, Roam a p a r t o f t h e NASA- on t h e Transformat i o n of Knowledge and I t s U t i l i z a t i o n . �rnT1LYcES m PUMPING TECHNOLOGY AND R O m E N G m TURBOPUMP APPLICATIONS Charles A. MacGregor Superv ie o r Advanced Turbomachinery Bocke tdgne A Division of North American Aviation, Ina. Canoga Park, C a l i f omia INTRODUCTION This r e p o r t i s divided i n t o two general p a r t a . The f i r s t p a r t ir a d e s c r i p t i o n 6f turbopumps f o r l i q u i d r o c k e t enginee m they e x i s t today. For campletenesa and understanding, same background i a f o r m a t i a a is included on why turbopumps have evolved t o t h e i r preeent configarationm. The second p a r t suggest portion8 of t h i s e f f o r t t h a t may have some a p p l i c a b i l i t y t o t h e general ecanomy. TURBOPUMP FOR LIQUID BOCIiET E N G I N S The turbopump hae t h e d i e t i n c t i o n of being one of t h e moat im,partmt Its f u n c t i o n in an engine h t s l l a t i o n i s t o receive propellante from t h e tanka and d e l i v e r them t o tha components in a l i q u i d rocket engine. �t h r u s t chamber a t design pressure l e v e l s and f l o w r a t e s s o t h a t the engine can develop deaign t h r u s t a t the required chamber pressure. . The turbopump i s r o t a t i n g machinery assembly , which cone ia t s of a 'pump ( o r pumps) for i n c r e a s i n g the pressure l e v e l of the propellant(s). The power t o d r i v e 'the p ~ p ( s i)n t h i s assembly is aupplied by a t u r b i n e , which u t i l i z e . working f l u i d s supplied by the engine system gas generator. Tut%opump design configurations can vary depending on t h e engine combustion p r o c e r r , t h e i n s t a l l a t i o n requirements, and the p r o p e l l a n t s being pumped. Detailed d e e c r i p t i o n s of turbopump configurations w i l l be presented in the following text. F l u i d s and F l u i d P r o p e r t i e s The major f a c t o r influencing the t ~ p eof turbopump d e s i g n chosen for any a p p l i c a t i o n is the d e n a i t y of the propellants t o be pumped. Variaticmm i n o x i d i z e r and f u e l d e n s i t y requires the i n d i v i d u a l pumps t o be operated a t speeds capable of obtaining respective pump head and volume flows. A t a b u l a t i o n of p r o p e l l a n t p r o p e r t i e s , which shows t h e v a r i a t i o n in propell a n t d e n s i t i e s , appear. in Table 1 . For turbopumps pumping p r o p e l l a n t combineti o m t h a t have s i m i l a r d e n s i t i e r , both pumps can be run a t the same speed. In cases where a g r e a t v a r i a t i o n i n p r o p e l l a n t d e n s i t y e x i s t s between the oxidizer and f u e l , an i n the l i q u i d oxygen ( ~ O X ) / l i ~ u i hydrogen d (5) cmbination, each pump i a driven at i t s b e s t design speed t o most e f f i c i e n t l y meet i n d i v i d u a l head requirementr . �Data a t NormalTemperature, Liquid *2*1 60 Vapor Pressure, psia 11.1 Density, lb/cu it Viscosity ~107. lb-scc/sq in. 90.88 0.657 60 0.152 63.25 1-49 60 0 255 62.37 1-65 RP- 1 60 0.01 50.45 5-51 EthylAlcohol (95 percent5 percent) 60 0.652 50.44 2.247 UDMH 60 1.89 49.71 0.815 UX* -297.5 14.6 71.39 0.277 llFL -305 16.0 93.77 0 W2 -315 20.70 49.50 NX N2H4 H2° J F Conditions A 338 0 ,0206 -425 4.42* 10.62 I=2 *Density a t 14.7 psi. +wXormal conditions do n o t necessarily imply standard conditionr, i f tank pressures have been applied. A �Operating Rauge Figure 1 i s a p l o t showing t h e range of o p e r a t i o n f o r t y p i c a l p r o p e l l a n t pumps i n terms of pump head and flow. This curve demonstrates how t h e head requirements f o r t h e l e s s dense p r o p e l l a n t , l i q u i d hydrogen, are much ' The p l o t g r e a t e r t h a n t h o s e r e q u i r e d by e i t h e r l i q u i d oxygen o r RP-1. shown in F i g . 2 i s t h e o p e r a t i o n envelope of c u r r e n t turbopump t u r b i n e d e s i g n s based on power and speed requirements. Turbine working f l u i d mass f l o w r a t e depends on the p r o p e r t i e s of t h e s e f l u i d s , t h e power # development r e q u i r e m e n t s , amount of energy from t h e s e f l u i d s made a v a i l a b l e t o t h e t u r b i n e t o c o n v e r t i n t o work, and t h e t u r b i n e d e s i g n and t p e r a t i n g parameters. A l i s t of working f l u i d p r o p e r t i e s f o r canmon p r o p e l l a n t combinations appears i n T a b l e 2. As power requirement8 f o r a s p e c i f i c d e s i g n o p e r a t i n g p o i n t i n c r e a s e , t h e r a t i o of t u r b i n e maar f l o w r a t e t o Cngine flow i n c r e a s e s . I f chamber p r e s s u r e is i n c r e a s e d f o r a f i x e d thrust c o n d i t i o n , t h e t u r b i n e power requirements t o d e v e l o p t h e needed pump heads become g r e a t e r . A p l o t of t u r b i n e t o engine weight flow r a t i o v s chamber p r e s a u r e , f o r a gas g e n e r a t o r i n s t a l l a t i o n , i s shown in F i g . 3. . The curves f o r b o t h LOX/RP-1 and LOX!LH~ c l e a r l y shmr t h a t , as d e s i g n chamber p r e s s u r e i s i n c r e a s e d , t h e t u r b i n e t o engirie weight f l o v r a t i o i n c r e a s i n g l y i n f l u e n c e s engine performance. The e f f e c t of chamber p r e s s u r e on turbopump weight i s a l s o an important d e s i g n c o n s i d e r a t i o n ; t o meet t h e i n c r e a s e d power requirements f o r h i g h e r chamber p r e e s u r e a , t h e turbopump assembly weight becomes h e a v i e r . A p l o t ahowing t h e e f f e c t of chamber p r e s s u r e on t h e turbopump t o e n g i n e weight r a t i o i. s h a m in Fig. 4. ���TABLE 2 PROPERTIES Inlet' Temperature, Fluid IAX/RP- 1 N20 4 / ~ ~ 3 (-1 lox/% L F Y ft lb/lb F Mixture Ratio, o/f 1.097 1.100 43.3 45.1 0.93 0.320 1.106 47.1 0.337 C P' ~ t u / l bF n, 1100 0 635 1150 1200 0.639 0.643 1250 0.646 1.111 58.6 0 354 1300 0.648 50.4 0.372 1350 1400 0.651 1.115 1.119 51.8 0.390 0 653 1.124 53.6 0.408 1450 0 655 1.128 0.425 1500 0 657 1.132 55-4 58.0 1550 1600 0.659 0.660 1.137 59.0 0.460 1.140 60 7 0.478 1650 0.661 1.144 62.4 1700 0.662 1.148 64.0 0,497 0,516 1400 0.380 1.42 0.11 1500 1.42 1600 0.398 0.416 87.5 91.6 1.42 95.7 0.22 1700 0.434 1.42 99.9 0,274 1800 0.452 1.42 104.0 0.328 1900 0.470 1.42 108.2 0.382 1000 2.05 1.374 434 0.785 1200 1.94 1.364 403 0 1400 1.86 1.354 378 1.025; 1600 1.80 1 343 358 1. ir3 1800 1.73 1.69 1 333 1.322 3% 1.273 320 1.410 2000 0.443 0.165 903 . ���TURBOPUMP DESIGN PROCESS 3 The process of designing a turboppp is shown graphically in Fig. 5. The influence of the various quantities that must be considered and determined are shown so that the turboplmp can be specified graphically and analytically. It is through this process and by considering these items that the various turbopump designs have evolved. Turbopump Design Criteria In selecting a turbopump design geometry, it is necessary to have a set of criteria by whihh to establish the desirability of a configuration. The criteria used for this selection are classified as keliabjlity, flexibility, ease of development, weight, and performance. The most important single criterion is that of turbopump reliability; it defines the expected successful performance of the turbopump in meeting the requirements of the design. Experience has shown that good reliability is a function of using design principles and techniques that are simple and provide a sound basis for performing the mechanical function for which at is designed. In addition to simplicity of design, the reliability of a machine depends on utilizing as few detail parts aa necessary t o perform the job intended by the design. A turbopump design must incorporate the characterietic of flexibility toward operating under a wide variety of conditions. This flexibility must include thie ability t o deviate from the design operating point, eaae of the unit to prwide a base from which it can be uprated to prwida a higher level of performance, and also the provision of changing individual pump operating points to facilitate adjustments in engine mixture r a t i o . , �+ I THRUST SlZE PROPELLANTS IMR) CHAMBER PRESSURE I APPLICATION ENGINE DESIGN POINT EQUIVALENT WGT ENGINE CYCLE T/C COOLING METHOO I d T/P DESIGN POINT 1 + POWER TURBINE INLET. O~SCH AND WORKING FLUID CONDITIONS T/P INSTALLATION T/P MOUNTING GIMBALLING DUCT SIZES DUCT LOADS (FLEX JOINTS) J 1 I THROTTLING RANGE W REOUIREMENTS STARTING METHOD RESTARTING REOUIREMENT CALIBRATION AND DESIGN POINT DEVIATIONS L STATE-OF-THE-ART LIMITATIONS 64 L b + I I DESIGN PROBLEMS FLOW STABILITY COMPONENT EFFICIENCY AXIAL AND RADIAL FORCES TEMPERATURE GRADENTS TORQUE TRANSMlSS#HI CRITKAL SPEED FABRICATKN( PROCESSES MATERIAL SELECTION STATK DEFLECTKH(S WORKING STRESS LEVELS H K ~ N PRESSURE FLANGE A OFF-DESIGN REQUIREMENTS RELIABILITY FLEXIBILITY DEVELOPMENT * . CAVITATION BEARINGS TIP SPEEDS SEAL LIMITS STAGE LOADINGS T/P CONFIGdRATlON PUMP TYPE AND SIZE TURBINE TYPE AND SIZE k + T/P DESIGN LAYOUT WEIGHT T/P PERFORMANCE OEVELOPMENT EFFORT h Figure 5. Turbomachinery Design Process �The c r i t e r i a t h a t provide f o r e a s e of a e - ~ r l o p i n e n tf o r a turbopump c o n f i g u r a t i o n a r e of major importance. 2 e s e include t h e o r g a n i z a t i o n t r experience and a b i l i t y t o f a b r i c a t e and s ~ c c e s s f u l l yt e s t a new t u r b o pump d e s i g n , t h e e x i s t e n c e of knowledge r s p e r f o m t h e program, and a b i l i t y t o p r e d i c t t h e magnitude and time of t h e development program. Another important c o n s i d e r a t i o n a f f e c t - e a s e of development is t h e a b i l i t y t o p r e d i c t performance; t h i s c a p e 5 i l i t y p r o v i d e s f o r a p r o t o t y p e d e s i g n t h a t r e q u i r e s a minimum of m o d i f i c e t i o n s and o b t a i m t h e d e e i r e d program o b j e c t i v e s i n a s h o r t e r d e v e l o p n c n t time period. The p r e d i c t i o n of turbopump d r y weight FS.~ performance can be combined I in terms of e q u i v a l e n t weight, i. e . , t h e rurbopump dry w e i g h t i s added t o t h e weight r e p r e s e n t i n g t h e e q u i v a l e n z p r o p e l l a n t weight conaumed b y t h e turbopump, expressed in terms of i n i r i a l m i s s i l e payload w e i g h t . This c r i t e r i a i s t h e l e a s t d i f f i c u l t t o i r e d i c t a n a l y t i c a l l y f o r a new design application. Turbopump D e s i Requirements ~ To s a t i s f a c t o r i l y meet t h e requirements c f a s p e c i f i c e n g i n e a p p l i c a t i o n , t h e turbopumps in many of t h e new engine c',esigns, i n a d d i t i o n t o o p e r a t i n g a t s t e a d y - s t a t e c o n d i t i o n s , must have t h e c a p a b i l i t y of t h r o t t l i n g e n g i n e t h r u s t t o meet s p e c i f i c mission r e q u i r e c e 3 t s . t h e f l e x i b i l i t y t o be used w i t h differer;: The d e s i g n a l s o mst have engine s t a r t i n g methods; t h i r can v a r y from uee of p r o p e l l a n t tank head t o start t h e pumping of p r o p e l l a n t s t o t h e t h r u s t chamber, o r perhaps a t u r b i n e s p i n start from an auxiliary power source. With any start nequence, t h e pumps m e t smoothly develop r e q u i r e d heads and f l w e w i t h o u t c a v i t a t i n g o r transmitting p r e s e u r e p u l s e e through t h e p r o p e l l a n t s z p p l y eyetem. Additional �requirements that may be imposed on a turbopump are those of providing engine restarts in flight, or varying engine mixture ratio in flight operation so that all the propellants in the tanks can be utilized during the flight mission. Design Problems and Solutione Turbopump experience has shown that there are baeic design problem which must be considered and solved before a new configuration will eatisfactorily meet required operating specificatio~. The individual pumps will be required to demonstrate stable performance characteristics for the full operating range of the turbopump without having tendencies of cavitating, transmittiag pressure pulses to the propellant feed aptem, or going into a region of stall. Development tests are conducted with both air and water, using pump detail inducers, impellers, and puxp subassemblies at a pump component test facility to ascertain that the pumps will perform satisfactorily before being used in a turbopump assembly. Comparable tests are conducted with the turbine a b a turbine test facility. \ Attaining the individual efficiencies of components used in the turbopump can. be a trouble source in qualifying a new turbopump design. To emure that the units are operating at required performance levels, all components are fully developed for the full range of operation in component test facilities prior to their use ae turbopump production configurations. Loads arising from axial and radial forces can reach proportions capable of causing internal damage because of rubbing of rotating parts; in . �extreme cases, complete failure of the turbopump by explosion can be experienced if the propellant being pumped has the properties of liquid oxygen. To eliminate auc= problems, the pumps are designed with balance pistons, and with provisioas to evenly distribute pressures within the pumps. The work with be&-ings capable of withstanding larger radial and axial loads is aimed st helping to minimize this type of problelh. Considerable work has bee3 done to eliminate problems caused by temperature grediente within the pump. With a cryogenic turbopump deaign, it is possible to have a pump c2eratin.g at a temperature less than -300 to 400 F mounted adjacent to a tur3ine operating with working fluid temperatures ranging from 1200 to 170C F. This environment and temperature gradient presents problem with differential contraction and expansion, lubrication, and sealing. Cryogeaic turbopump design and development experience has established techniques for cooling and allowing far thermal growth between adjacent components. Problems associated with fabrication processes for new turbopump design configurations are dealt with by two approaches. Primary considerations are given to the design of a component to establish if the complexity of the unit could be simplified and still perf o m in the same manner. If the design is committed t o fabrication, the individual casting, forging, and machining processes a=d techniques are improved or developed so that parts can be produced with consistent quality. In some difficult instances, either the mode of fabrication or material is changed. Casting processes for new pump volutes are often developed so that the volute casting will be of acceptable quality. Experience with selecting materials for fabricating new turbopump hardware has shown that newly developed alloy8 with propertiee suitable far turbopump service often preeent machining problems. In most cases, all much �problems were e l i m i n a t e d as machining experience w i t h t h e new a l l o y was accumulated. h l e n s e l e c t i n g m a t e r i a l s f o r f a b r i c a t i n g a new component, those comon m a t e r i a l a t h a t have been worked w i t h p r e v i o u s l y a r e i n v e s t i g a t e d f i r s t , r a t h e r than u s i n g a new e x o t i c type w i t h p r o p e r t i e 8 t h a t far exceed t h e maximum requirements f o r t h e a p p l i c a t i o n . There have been i n s t a n c e s when problems a s s o c i a t e d w i t h t o r q u e t r a n s m i a s i o n and c r i t i c a l speed have had t o be s o l v e d i n turbopump development programs. On& method of minimizing t h e problems of t r a n s m i t t i n g t o r q u e ( f o r example, frum t h e t u r b i n e t o t h e pumps)has been t o u t i l i z e c u r v i c c o u p l i n g s in t h e designs. They have proved v e r y s a t i s f a c t o r y in s e r v i c e . In c h e c k i n g new turbopump d e s i g n s , t h e c r i t i c a l epeed i n bending i s analyzed f o r the r o t a t i n g assembly. For d e s i g n s t h a t o p e r a t e above t h e f i r e t c r i t i c a l , t h e c a l c u l a t e d f i r e t c r i t i c a l should be no more than 85 p e r c e n t of t h e d e e i p speed. For t h e c a s e of o p e r a t i o n below t o e f i r s t c r i t i c a l , the c a l c u l a t e d f i r s t c r i t i c a l should be no l e s s t h a n 150 p e r c e n t if t h e d e s i g n epeed. Turbopump s t a t e - o f - t h e - a r t l i m i t a t i o n s r e p r e s e n t t h e e x i s t i n g boundaries t o man's knowledge concerning turbopumps. Exceeding any one of t h e s e l i m i t a t i o n s w i l l r e s u l t i n a turbopump t h a t i e e i t h e r u n r e l i a b l e o r inefficient. Rocket engine turbopumps a r e designed a t t h e maximum a l l o w a b l e r o t a t i o n a l epeed because of weight c o n s i d e r a t i o n s . Figure 6 demonstrates t h i r r e l a t i o m h i p between turbopump weight and r o t a t i o n a l apeed. ' ��Each s t a g e cf a r o c k e t engine pump d e i i v e r s a s much work as t h o s t r u c t u r a l a d hydrodynamic l i m i t a t i o n s w i l l a l l o w , because t h e number of r e q u i r e d s t a g e s i s i n v e r s e l y p r o p o r t i o n a l t o t h e work d e l i v e r e d per stage. This minimizes t h e pump w e i g h t , because pump weight ' i n c r e a s e r w i t % t h e number of r e q u i r e d s t a g e s . The f o l l o w i n g hydrodynamic and s t r u c t u r a l phenomena p l a c e an upper limit on r o t a t i o n a l speed and a lower l i m i t on t h e number of pump s t a g e e . Cavitation . C a v i t a t i o n w i t h i n a pump i s t h e passage of t h e pump flow from t h e l i q u i d phase t o t h e v a p o r phase. This s e v e r e l y r e s t r i c t s t h e weight flow d e l i v e r e d by t h e pump, because of two i n t e r a c t i n g r e a s o n s : (1) t h e volume f l o w r a t e d e l i v e r e d by a pump is c o n s t a n t , and (2) a vapor occupies a much l a r g e r volume t h a n t h e c o r r e s p o n d i n g l i q u i d . C a v i t a t i o n a l s o w i l l cause s e v e r e e r o s i o n of t h e flow passages i n a pump t h a t o p e r a t e s f o r l o n g p e r i o d s of time, because t h e v a p o r c a v i t y c o l l a p s e s v i o l e n t l y when it p a s s e s i n t o a higher pressure region. This e r o s i o n i s a minor c o n s i d e r a t i o n i n r o c k e t engine pumps, because t h e s e pumps have a v e r y s h o r t o p e r a t i n g d u r a t i o n . These a d v e r s e e f f e c t s of c a v i t a t i o n a r e minimized by a t t a c h i n g an i n d u c e r upstream of t h e main i m p e l l e r i n l e t . This inducer r a i s e s t h e p r e s s u r e of t h e pump f l o w t o a l e v e l a t which t h e f l a w w i l l n o t c a v i t a t e w i t h i n the impeller. I I I �An inducer will operate satisfactorily rrt low pressures because it is designed to avoid low-pressure regions within the flaw passing through it. Figure 7 is a photograph of a typical inducer. It is a small axial stage with a large inlet area and a small number of vexy thin, low-cambered blades. This type of design avoids low-presaure regiom by minimizing the relative velocity of the f l m as it passes over the blader. Bearings The speed limit of rolling contact bearings is expressed by the parameter DN. This parameter is directly proportional to the tangential velocity of the shaft OD, and is the product of the diameter (in millimeters) of the shaft that passes through the bearing, and the shaft rotational speed =pap- Depending on the lubricant, the DN limit for rolling contact bearings im in excess of one million (I'ig. 8 ). Operation at higher DN values will cause contact fatigue in the outer race and excessive heat generation. These modes of failure are caused by high centrifugal forces and nonrolling phenomena, respectively. Rocket engine turbopump bearings are lubricated by the propellant being pumped. This eliminates a separate lubrication system and reduces sealing problem. Explosions can occur if separate lubricants are used, and they mix with the ~ropellants. �ma-11/19/61-1 P i p e 7. Typical Turbopump Inducer ��Seale The f u n c t i o n of a s e a l is t o minimize or p r e v e n t t h e leakage of a c o n t a i n e d f l u i d by p r e s e n t i n g a high r e s i a t e n c e t o flow along any p o t e n t i a l leakage path. This is accomplished i n r o t a t i n g machinery by mechanically f o r c i n g t h e s e a l f a c e a g a i n s t t h e s u r f a c e of t h e r o t a t i n g element. The v e l o c i t y a t which t h e s e a l f a c e rubs a g a i n s t t h e r o t a t i n g element has an upper limit (depending on t h e l i q u i d being s e a l e d ) i n excees of 300 f p s ( ~ i g . 9 ) Operation a t h i g h e r v e l o c i t i e s w i l l g e n e r a t e e x c e e s i v e h e a t , which w i l l reduce t h e c o o l i n g c a p a c i t y of t h e surrounding l i q u i d by v a p o r i z i n g it. The r e s u l t of such o p e r a t i o n i s a r a p i d t e m p e r a t u r e r i s e f o l l o w e d by f a i l u r e . Structural Limitations The c e n t r i f u g a l s t r e s s a t t h e r o o t of t h e t u r b i n e b l a d e s can l i m i t t h e turbopump r o t a t i o n a l speed. This s t r e s s i s p r o p o r t i o n a l t o t h e pr8duct of t h e m a x i m t u r b i n e annulus a r e a and t h e square of t h e speed. Theref o r e , t h e m a x i m speed allowed by t h i s l i m i t a t i o n i s s e t i f t h e t u r b i n e f l o w r a t e , i n l e t c o n d i t i o n s , and h o r s e p m e r a r e e p e c i f i e d , becauee t h e s e parameters s e t t h e annulus a r e a . The amount of head r i s e p e r ahrouded c e n t r i f u g a l s t a g e i s l i m i t e d by a maximum a l l o w a b l e t i p speed of 2200 f p s i f t h e i m p e l l e r i s made of titanium. Higher t i p epeeds w i l l cause y i e l d i n g in t h e i m p e l l e r , becaure t h e c e n t r i f u g a l s t r e e s e e w i l l be exceeaive. Unshrouded c e n t r i f u g a l i m p e l l e r s c a n o p e r a t e a t h i g h e r t i p speeds, b u t have l m e r e f f i c i e n c i e r and e x c e a e i v e axial f o r c e r . ��Hydrodynamic Limi t a t iona The b l a d e s of an a x i a l pump s t a g e should t u r n t h e flow aa much as p o s s i b l e , because t h i s maximizes t h e amount of work p u t i n t o t h e f l u i d per stage. This minimizes t h e pump l e n g t h by minimizing t h e number of st a g e s . The The t u r n i n g i s l i m i t e d by t h e maximum allowable d i f f u s i o n f a c t o r . r o t o r d i f f u s i o n f a c t o r is d e f i n e d a s f o l l o w s ( r e f e r r i n g t o Fig.10 ): where The s t a t o r d i f f u s i o n f a c t o r should be e i m i l a r , because e f f i c i e n c y c o n s i d e r a t i o n s make 50-percent r e a c t i o n a t a g i n g d e s i r a b l e . B l a d i n g w i t h a d i f f u s i o n f a c t o r of 0.7 w i l l p e r f o m w e l l . demonstrated by experimental t e s t i n g at Rocketdyne. This has been Loading i n excesa of t h i s v a l u e , however, can r e s u l t i n low pump e f f i c i e n c y from flow s e p a r a t i o n w i t h i n t h e b l a d e row. D i f f u s i o n problems w i t h i n c e n t r i f u g a l i m p e l l e r s can be a l l e v i a t e d by u s i n g backward curved vanes. Thin w i l l reduce t h e d i f f u s i o n w i t h i n t h e i m p e l l e r p a s s a g e , because t h e t i p r e l a t i v e v e l o c i t y w i l l have a backward t a n g e n t i a l component a s w e l l as a r a d i a l cmpontnt. ��r n W E N C E OF THE LlMITS The i n f l u e n c e of t h e s e l i m i t s on turbopump r o t a t i o n a l speed is demonstrated i n Fig. 11. The s p e c i f i c speed l i m i t i n d i c a t e s t h e maximum epeed a t which a c e n t r i f u g a l pump can be operated. Axial pumps must be used i f thin l i m i t a t i o n is t o be exceeded, because t h i s l i m i t a t i o n i n d i c a t e s t h a t the t i m p e l l e r i n l e t diameter i a almoet equal t o the impeller t i p diameter. Seal speed and b e a r i n g DN l i m i t s are evaluated f o r s h a f t s that a r e e i e e d by c r i t i c a l speed c o n s i d e r a t i o n s and by t h e t o r a i o n a l s t r e e s l i m i t . TCTRBOPWP CONFIGURATIONS Turbopumps can be designed i n t o a number of d i f f e r e n t c o n f i g u r a t i o n s and arrangements. The f i n a l s e l e c t i o n depends ?n the d e e i r e d speed r a t i o between pumps, t h e arrangement of components, and the energy source of t h e t u r b i n e working f l u i d . There a r e t h r e e b a s i c turbopump d e s i g n t y p e s : 1. Geared turbopump 2. S i n g l e - s h a f t turbopump 3. Dual-ahaft turbopump Geared Turbopump The geared turbopump d e s i g n c o n f i g u r a t i o n u t i l i z e e a gear box w i t h which t o d r i v e t h e f u e l and o x i d i z e r pump a t d i f f e r e n t epeeds w i t h a a i n g l e t u r b i n e d r i v e aesembly. Figure 12 containrr a cutaway photograph of a LOX/RP-~ g e a r turbopump c o n f i g u r a t i o n t h a t i s c u r r e n t l y i n s e r v i c e i n a 150,000pound-thrust b o o e t e r engine. �PUMP FLOW RATE Figure 11. - GPM Maxhmm rotational speeds allowed by varioas limite. �Figure 12. Geared Twbopwp. �Single-Shaft Turbopumg The turbopump photographs shown in Fig. l3and 14 are of single-shaft turbopump configurations. In this type design, both the oxidizer and fuel pumps a r e driven on one shaft by a single turbine. The turbopump shown in Fig.13 is for an engine rated at 70,000 pound8 thrust. The single-shaft turbopump assembly shown in Fig. 14 is being used in LWRP-1, 1,500,000-pound-thrust engine. Dual-Shaft Turbopump The dual-shaft turbopump configuration utilizes separate shafts to drive the oxidizer and fuel pump8 st the best speed to meet the head and flow ia driven requirement of the propellanta that are being pumped. Each p~ by its uwn turbine; pump speeds heads and flows can be adjusted independently with this type pump installation. Dual-shaft configurations are used for pumping propellant combinations that have large differences in density; one such propellant combination is ~0../4. Photos shown in Fig. 15. and b are of dual-shaft, LOX and turbopumps respectively, for a 200,000- 3 pound-thrust engine application. In dual-shaft installation, the turbine8 can be installed either in series or in parallel to one anothar. �Figure 13. S i q l e @aft'Porboprrmp Fop P d Thrast Engine. 70,000 �Figare 14. Tarbopa~~g For 130UK Tbnuf Engine. ��TCRBOPUP DE%'I%OF?.IATSAPPLICABLE TO TIIE GEX3XA.L ECONOMY Items presented in this section have been developed in connection with turbopumps and may have some applicability to the general econoqy. The turbopump, in configuration, is simply constituted. It ie made up of two p m p s and a single turbine variouly mounted on a single shaft or, in the past, a gear box has been used to transmit power from t h e turbine. Both roller and ball bearings which will take radial and a n a l loade impoaed on the rotating assembly have been used. Dynamic seals are ueed at the impeller and on the shaft to control leakage and thruet, and are placed to prevent mixing of the propellants. Positive static seals are need in the stationary assembly to prevent the hazard8 of external leakage, The remaining major components are the paup volute, turbine manifold and the shaft, the former of b%ich must contain either high-preseure or hightemperature fluid within a sound structure, and the latter must transmit torque through spline or curvic couplinge. These components will suffer and withstand deflections, temperature gradients, miaalipenta, etc. Figure 16 ahows a cavitating-type inducer mounted on the shaft with the pump impeller. k d e r cond'ition of low inlet Xet Positive Sbction Head the inducer operates in a cavitating condition but provides a head rise sufficient to suppress cavitation in the main impeller and thua permit8 it to work satisfactorily. High-speed pumps can, therefore, be operated at a much lower inlet head than conventional pumps, and the net gain i r very much lighter and smaller turbomachinery. Figure 17 shows the weight ��Figare 17. Turbopump weight/turbine nhaft horaepowar vereus tarbopnmp rotational apeed. �reduction obtained by increased turbopump rotational speed. Moet of Thir these gains have been made possible by improvements to the inducer. weight saving is critical in flight hardiiare and is also~importantfor commercial machinery because lower weight and smaller size often result8 An important parameter for an inducer is the suction specific speed at which it is able, to operate and develop head. The* improvement in suction performance obtained by utilizing a low flow coin reduced costs. efficient inducer is illustrated in Fig. 18. Conventional pump8 are limited by head loss from cavitation to a suction apecific speed from 5000 to 8000, whereas rocket engine pumps as a result of inteneive develop- ment efforts over the years have been improved to 40,000 in water. r The important design parameters for an inducer giving approximately 35,000 suction specific speed in water are shown in Table 3. It is important to note that cavitation performance is poorest in cold water and other liquids having similar thermodynamic properties. The described inducer will give in excess of 40,000 suction specific speed in liquids (such as liquid oxygen) that are being pumped near their boiling point. In liquid hydrogen, the auction specific speed attainable ie over 70,000. The blades of the inducer at design conditions operate under cavitating conditions with consequent wear to the inducer and surrounding case. Thir is of only minor consideration in short life rocket engine pumps, but i m a aerious limitation in commercial p m p s that require long-operating life. It has limited the application of these inducers,but prewhirl offer. possible means of alleviating this problem. r ���A great deal of this cavitation can be suppressed and possibly eliminated if a technique known as prewhirl is used. Figure19 illustrate6 the application of preb-hirl to the inlet of a cavitating inducer, centrifugal . pump combination. Prebhirl consists of bjpaseing a small quantity ot high-pressure pump discharge flow to the inducer inlet. This secondary flow of high-energy fluid swirls around the inlet pipe outside a ~ u l u s and suppresses inducer backflow and cavitation. Fig. 20 a and b . This is illustrated in This first photograph indicates the inducer cavitat- ing during normal pump operation, The second photo shows the same inducer with prewhirl in operation. Notice the great reduction in backflow and mvitation and the general smoothing of the flow. There is also a large . reduction in pump discharge pressure oscillationsbas illustrated in Fig.21 Prewhirl will also increase the suction specific speed of an inducer. The prewhirl is in the direction of rotation and can thus reduce the N e r head of the pump. This is an aid in broadening the operating range, as the stall range can be extended and efficient operation achieved at low-flow conditions. Depending on requirements, from 2 to 15 percent of the p m p flow is bjpaseed for prewhirl. Bypassing lower head fluid from the inducer discharge rather than from the pump diecharge offere a means of reducing the loss associated with the process because of the improved ejectory efficiency of lover momentum bypass fluid, . ���Figure 21. Iduaer osoillation reduotion. �SEALS A great deal of development work has been done on rocket engine turbopump shaft seals. While particular emphasis has been on cryogenics, the reaults are applicable to seale in other extreme environments. The basic seal tj-pes are shorn in Fig.22 . In the past, comercia1 machinery hae ex- tensively used the packing box seal. This seal alwaya ha8 Borne leakage and historically haa been a very troublesome device. The requirement. of reduced lehkage, higher shaft speeds, and improved reliability have resulted in the development of the mechanical aeal. Normally, an elaetomer such,as a rubber O-ring has been used on the secondary seal that seals along the path of the axial movement of the nosepiece carrier. Severe operating regimes of both very low and high temperatures have led to the development of k liptype secondary seal for rocket engine applications. Dynamic shaft seal developments during the past 2 or 3 years have pointed out the advantages of using metal bellows-type face seals (Fig.23 ) for the severe applications of the aerospace industry. The extreme temperatare requirements, often from as low as -423 F to as high as +lo00 F, have directed most of the face-type seal test effort toward the bellows. The all-metal construction allowa the seal to operate at temperature6 which are only 1imited.b~the capability of the metal inatead of this usual elastomer secondary seal that is used in moat standard applications. A properly deeigned bellows seal ie capable of withstanding ertremely high fluid pressure throughout large temperature ranges for long periods of time without the worry of elaatomer deterioration and cure date expiration. For this reaeon, the bellows-type seal hae many potential applica- tione for industrial usage. At the present time, t h e bellows eeal is more ��Figure 23. Bellm Seal. �expensive than the conventional elastoner t y p e ; however, as the rate of usage increases and the bellows are fabricated in volume, it is reasonable to expect that the costa may be comparable. Actually, &en replacement costs are considered, the bellows seal may be leas expensive in the long run, even at present prices. Mechanical seals operating in a lubricating media auch as oil can have practically no leakage. Such is not the case, however, when sealing a nonlubricant like gaseoue nitrogen. In this caae, the leakage rates can have an acceptably low value of 6 scim of gas sealing against 30 pounds pressure, at 8000 fpm seal surface speed for a 2-inch-diameter seal. HIGH-LOAD , HIGH-SPEED BEARINGS Ekperimental investigations conducted for space development programs have been effective in breaking down barriers and extending previously accepted limitations of speed, loading, and cooling of the rolling contact bearings. Prior to 1955, 1,000,000 DN (bore in millimeters multiplied by speed in rpm) was considered to be extremely fast for ball and roller bearings. Because of the advances in bearing geometry and lubrication techniques required for turbomachinery applications, bearings operating at 1,500,000 DN are fairly commonplace, and have proved to be reliable. It was found, for instance, that highly loaded roller bearings equipped with inner-land riding cages are quite difficult to lubricate properly at altitudes of 100,000 feet and more; similar bearings equipped with outer-land riding cages, providing easy lubricant entry, experienced no difficulty d e r vacuum environmentr. \ �It has been found that the maximum compressive stresa existing between races and rolling elements can be extended almost to the plastic flav range if proper lubrication techniques are employed. It ie paramount to maintain a heat balance in which heat is removed from the bearing at the rate it is generated at a temperature low enough to maintain proper materiala properties. Bearings may be made to accept high loads and speeds with proper lubrication by conventional lubricants such as oils. However, an advantage c a n be obtained by using process fluid as the tearing coolant/lubricant. Fkperimental investigations have shown that with proper material selection, such fluids as RP-1, LH2, N 0 LRFNA, and X2 can cool high-speed 2 4' (1,000,000 DN) ball bearings. In another investigation, it was s h w n that by careful attention to detail design of ball bearings, the operating speeds and loads can be elrtended A ball bearing cooled by 3 has been operated for short periods at speeds to 4,000,000 DN, and for useful duration8 at 3,000,000 DN. using coolants with little or no lubricity. . In summary, it might be stated that experimental programs aimed at development of rocket engine turbomachinery have freed users of rolling contact bearings from some of the limitations in apeed, load, and lubricants formerly accepted by induatry in general. �RECEUT ADVAhCES IN MECMICAL GEARING TRANSMISSIONS Between 1958 and 1964 there has been a slow but steady advancement in the load carrying capacity on aerospace and rocket engine gearing. There have been no major breakthroughs but the combination of empirical metallurgy and better quality control has resulted in gearing with 1-1/2 to 2 times its previous load carrying ability. Quality assurance begins with the'rigid control of the alloy composition and is almost continuous during the pouring, forging, cutting, and heattreating operations. * Most of the material for aerospace gears is produked by the double vacuum melted proceqs using consumable electrodes. Ektreme cleanliness is a must and carbon content of the alloy is controlled in some instances within 0.02 percent. Heat-treatment cycles are specified and then rigiqly controlled. are stress relieved in dual cycles of +3OO to -100 F. Parts The latest carburiz- ing furnaces are of the stainless-steel retort type with infrared analysis and control of the carburizing atmosphere. Sample slugs and sample parts are subjected to the identical heat-treating process as the production parts. The samples must'be acceptable by metallurgical evaluation before the parts are purchaeed. Sample parts are then run at conditions equal or greater than actual operating conditiona. Failure of a mandacturerls parts to pass these quafificetion tests means disqualification of the manufacturer aa a supplier. . �Improvements in the accuracy of measilriug devices have made it possible to tighten tolerances and still maintain the ability to measure with repeatability. Ten years ago, some manufacturers talked in terms of 0.0001 of an inch and were able to measure to 0.0002 to 0.0005 inch. Today, the same people talk in terms of millionths of an inch and measure repeatedly in a range of 0.0001 to 0.00005 inch and as low as 5 microinchea. To accomplish this, the measuring instruments and parts are kept in socalled white rooms where temperature, humidity, and dirt levels are rigidly controlled. Surface finishes are now measured as to finish, lay, and waviness. * It has been found that these factors have a ,reat influence on scoring resietence of the gear surface. Shot peening of gears used in the past, as a corrective measure, is now part of the original design to induce beneficial compressive stresses and relieve discontinuities in gear roots, webs, and rims. Increases of up to 50 percent improvements in fatigue life have been obtained in some instances. The same peening procedures are used on splines and couplings with similar results. Improvements have been made in design theory. Profile modifications used , to be a matter of experience. Today, detailed profile measurements, deflectione, and calculations are made all along the line of action. &tire profile modification8,art calculated before a gear is run, thus decreasing scoring, finding, and compressive failure#. �Root stresses are now calculated with much greater accuracy and loads of 1-112 to 2 times those of a few years ago are being used. Unit loads of 40,000 t9 45,000 and bending stresses of 80,000 psi are common practice An index of the compressive strength of a gear is the K factor. ?reduction gears are running today with K for life cycles up to 10,000,000. values of over 2000, whereas high. I( values of 900 used to be conaidered as Metallurgy and a dimensional accuracy have been the moet important contributing factor.. Ten years ago, a pitch-line relocity of 20,000 ft/min was considered a maximum to prevent scoring failures. Today, the ability to more accurately control gear-face surface conditions and the use of lubricant additives hare relieved the scoring problem to the extent that pitch line velocities of 50,000 ft,/min are obtainable. The greatest area of improvement occurred in lubrication of aerospace gearing. For example, kerosene by itself can carry only 500 lb/in. of face loading. By the addition of 3 percent by volume of extreme pressure additives, load carrying capacity of over 6000 lb/in. of face has been demonstrated. Gears pretested with an extreme pressure film of millionths of an inch thickness can later be operated in kerosene only at loads up to 4000 lb/in. It appears it may be feasible to pretreat gears and bearings with extreme pressure films before putting them in actual service and then nm them in any reasonable coolant. # This theory has been demonstrated under controlled laboratory conditions; howdver, additional research must be done before it can be applied to comerical transmissions. The use of dry-film lubricants is more prevalent and offers a potential future especially for rpliner. �Special nitrited surface gears have been run at extremely high temperatures (600 F) and bearings and couplings have been operated at -300 and -420 F in gases and liquids of pure oxygen and hydrogen. LoaQs have aot.been extremely high on 'gears,but they can carry significant loads (500 to 1000 1b;in.) for short timee. Present gears can carry approximately 40 horeepover for every pound of gear box and with a reliability of as high aa 0.9996.It is felt that the procedures, controls, and experience described could be applied to everyday industrial applications, resulting in lighter, more efficient, more reliable industrial products. a DEVELOEENT OF ALUMINUM ALLOY CASTINGS In the early fifties, design values for ultimate strength and yield strengkh of castable aluminum alloys were approximately 23,000 and 15,000 psi, respectively. As a result of considerable research and development work in the aerospace industries in recent years, one can now confidently use values of over 45,000 psi ultimate and 56,000 yield. One of the most widely used general purpose castable aluminum alloys has been 356-T6. of the Imparities like iron, however, limit the heat treatability 356 alloy. The iron forms needle-shaped crystala that are brittle and it is, therefore, not possible to heat treat the alloy f d l y without serious damage to ductility. �The alloy Tens-50 developed at Rocketdyne overcame this defect in 356 by modifying the shape of the brittle iron crystals to harmless modules through a beryllium addition. A further improvement was also made by increasing the heat treatable hardening constituents (magnesium and silicon) resulting in a higher heat treatable etrength. The composition of 356 and Tens-50 is compared in Table 4. Succeseful reeults in minimizing casting porosity because of gas or shrinkage have been achieved by the combined effect of controlled melting techniques and extensive me af chills in the mold design. Normal melting precautions such as control of purity of furnace charges, proper degassing procedures, and controlled holding and pouring t e m p ,eratures are important in the production of porosity-free aluminum caatinga. 3 Statistical analysis shows, however, that these precautions do not guarantee consistantly sound castings. When good melting add pouring techniques are combined,with the extensive use of Leary chills in the mold design, a real improvement is achieved because of the extremely rapid solidification. AB an example of the properties achieved in an actual caeting, a Tens 50T60 aluminum alloy sand casting of a turbopump volute was metallurgically analyzed. This test is part of the routine metallurgical evaluations that are performed on all Rocketdpe castings. Fifty-two r o d (0,250 inch diameter) teat bars were machined from the casting. Table 5 shows the results. Ultimate strength as high as 49,800 psi, yield etrength am high as 38,100 psi and elongations of a maximum of 8.5 percent were obtained. �TABLE 4 - b EIE?Ell"rS i Tens-50 356 w 5 si 6.5 % 0.25 - 7.5 7.6 -8.6 0.15 - - @.LO 0.ho Be C 0.10 0.55 0.30 - 0.20 Ti 0.20 Fax ~a 0.13 Cn 0.10 Fax 0.10 Max m 0.50 F2x 0.20 Fax Zn 0.05 :?ax 0.20 Max Al Reminder Renainder - 0.30 0.30 Max n �, f.2 ----. -- . z'€ -- 6.5. 0 0 1 ' H CoQ'w2 - OW' lb 006 'st, 002 'Lt7 006'sC S'P S'S 9 C . 2 o w ' 9~ tr 000 '9c ---- 008'SC 0.c cozg9€ 4 'L - C.9 - 001'PC --00%' Sf - ooB'6t7 -.. 00 b'btr 009 ' 6 000'5~ -- . I. -- - -.- PJ!fl I ~ y J- uj O n l I!J3 ~=ra .capu!iAa ( ~ I Y I sI~llnO Iw!4!J3'U0N 'kern a(n10~ p~epuets I*!+!'3 c 2 '31t11"5 - . I ~ a ( t ! l d -s ~ b 3 p6 ~ 1 1 ~ ~ 1 1 SJb(t!ldS )o J b ( u 8 3 z J@!l!ldS . bu!peal I ~ J ! ) ! J ~ I ~a((!lds'-a6pa € c c. a)+ ~ F ~ ~ I -.on A J lm! I!J3'"91 -- I*? l!'3 2 PJWU~S 9 €. 9 s'8 0:L .--- 9 t, ----. -- --__. .---. L'c -.-. QVO'l3 i \Pa!\!'J I=!f!Ja --- . 15d-0131~ --. . zanhol anhuq- -- - a)p3 bu!pes) NOILV307 3 0 ~ ~ 3 - - - - .. �Individual test bare machined from the most significant arear of the caeting were analyzed microscopically and the resulta are shown in Fig.24 . �PHOTOMICROGRAPHIC STUDY AND MECHANICA PROPERTIES OF F-1 FUEL VOLUTE TENS 50-160 ALUMINUM ALLOY SAND CASTING. WEIGHT OF CASTING: 400 POUNDS 3.0% ELONG 39.300 PSI 2.0%ELONO 49.200 PSI 43,700 tL( 36.206 PSI 4.0% ELOW 6.0%ELOW Figure 24. Photomicrographic etudy and mechanical propertier o f P-1 Fnel Volute Tern 5 0 - ~ 6 0Alnminnm Alloy Sand cmting. Weight of casting: 400 pound.. 55 � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000036 Title A name given to the resource "Advances in Pumping Technology and Rocket Engine Turbopump Applications." Description An account of the resource Presented by Charles A. MacGregor, Supervisor, Advanced Turbomachinery during Workshop D, Royce Hall, Room 160 at UCLA on 2 June 1964, as a part of the NASA-UCLA Symposium and Workshop on the Transformation of Knowledge and Its Utilization. The introduction notes, "This report is divided into two general parts. The first part is a description of turbopumps for liquid rocket engines as they exist today. For completeness and understanding, some background information is included on why turbopumps have evolved to their present configurations. The second part suggest portions of this effort that may have some applicability to the general economy." Creator An entity primarily responsible for making the resource MacGregor, Charles A. North American Aviation. Rocketdyne Division Date A point or period of time associated with an event in the lifecycle of the resource 1964-06-02 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) Liquid propellant rockets Turbine pumps Turbomachinery Type The nature or genre of the resource Reports Text Source A related resource from which the described resource is derived Saturn V Collection Box 11, Folder 33 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050 https://digitalprojects.uah.edu/files/original/20/984/spc_stnv_000037.pdf 6b33c94ae60e6739061576b52392f6fb PDF Text Text ADVANCED ASTRIONICS PROJECT REVIEW IBM NO. 68-KO5-0001 30 JANUARY 1968 c I �PROJECT REVIEW ADVANCED ASTRIONICS IRAD TECHNICAL SEMINAR GAITHERSBURG, NLARYLAND JANUARY 30, 1968 F. L. PUGH PRINCIPAL INVESTIGATOR E. C. CALDWELL ADVANCED IU SYSTEMS IBM HUNTSVILLE �TASK SYNOPSIS a NEED IU FOLLOW -ON PROGRAh4 a OBJECTIVES O F ADVANCED ASTRIONICS P R O J E C T a a - DEFINITION O F FUTURE SYSTEMS - IDENTIFICATION O F APPLICATIONS - DEVELOP SYSTEM DESIGNS AND HARDWARE - DEVELOP, A T LEAST, 1 OFF-THE-SHELF PRODUCT IN EACH SUBSYSTEM AREA 1968 APPROACH - ANALYTICAL STUDIES (REQUIREMENTS AND TECHNOLOGY) - LAB T E S T (IU -S IVB SEPARATION) - PRELIMINARY DESIGN FOR PRINCIPAL APPLICATIONS 1969 APPROACH - LAB TESTS - BREADBOARD HARDWARE - COMPUTER AIDS T O DESIGN a CONTINUING CUSTOMER CONTACT a EVENTUAL SUBCONTRACTOR INVOLVEMENT �SUMMARY O F PREVIOUS AND CURRENT E F F O R T S e 1967 : REQUIREMENTS AND TECHNOLOGY STUDIES Q, 1968 e - CONTINUE - START LAB TESTS (IU - S-IVB SEPARATION) - PRELIMINARY REQUIREMENTS/TECHNOLOGY REPORT B Y 3/1/68 E F F O R T S SUMMARIZED IN SUBSEQUENT TECHNICAL DATA - ANALYTICAL - LAB T E S T �ANALYTICAL RESULTS �MISSIONS (1970 - '85) PROFILES EARTH ORBITAL Q - LUNAR - PLANETARY VEHICLE TESTS OMECTIVES - SPACE SCIENCES (ASTRONOMY, BIOMEDICINE, ASTROPHYSICS, ETC .) NASA APPLICATIONS COMMUNICATIONS METEOROLOGY RESOURCES NAVIGATION GEODESY DEVELOPMENT (VEHICLES, RESCUE, INDUSTRY) - MILITARY RECON COMMUNICATIONS NAVIGATION - ~OMMAND/CONTROL/COMMUNIC ATION MANNEDPLANETARYEXPLORATION �MISSION 9 (1970 - '85) PLANETARY (SCIENCE AND EXPLORATION) NASA - a PREMISE - UNMANNED (SOLAR PROBES, FLYBY, ORBITERS, ETC. ) 0 . 1 TO 5.6 AU - SOFT LANDINGS IN ' 80'S LUNAR NASA - LIMITED MANNED SURFACE - LUNAR ORBITAL SUPPORT, E. G., COMMUNICATIONS SEVERAL WEEKS - MONTH EARTH ORBITAL (SCIENCES, APPLICATIONS, ENGINEERING DEVELOP. ) NASA AND USAF - DEVELOP MANNED PLANETARY CAPABILITY - ASTRONOMICAL SCIENCES - EARTH RESOURCES SURVEY / APPLICATIONS MANNED /UNMANNED MILITARY RECON, COMM. AND NAVIGATION SATELLITES LAUNCH AND SPACE VEHICLE DEVELOPMENT �TRENDS I N UNMANNED MISSIONS F Y 1969 START I I I 1 I NOW TYP I ; LEAD I I I I 1 I I J t I I TIME I I I NUMBER OF MISSIONS \ I CALENDAR YEAR PLANNED IN F Y 1968 BUDGET �EXAMPLE SPACE SCIENCE APPLICATIONS PLAN - COMMUNICATIONS (BASIS FOR FLIGHT PLAN) 0 11 (COMMON CARRIER) - TV SYNCOM - VOICE - RELAY - TECHNOLOGY SERIES APPLICATIONS SATELLITES TV STUDIES DIRECT COMMUNITY AAP EXP. e SYNC ORBIT EXP COMM. SATS. LUNAR COMM. SATS (ABANDONED MODULES) ATS-C SERIES NIMBUS E - INTERROGATE - RECORD - LOCATE o ORBITING RELAY * RELAY O F BALLOON COLLECTED DATA 7 �MSFC PROVIDED SPACE DEVELOPMENT PLAN "SATURN UTILIZATION STUDY" - LANDING - RENDEZVOUS - UNMANNED LOGISTICS e SURFACE & ORBITAL - LAUNCH/RENDEZVOUS - MANNED OPS e SCIENCE - DAY/NITE OPS - SUB -SURFACE - ASTRONOMY - SOIL SAMPLES - SAMPLING MAN - SUBSYSTEMS (b MAN - SYNC ORBIT e NUCLEAR PLANETARY - STAGE DEV. - PROP. CLUSTERTNG e HIGH S P E E D REENTRY a SPACE a MANNED PLANETARY ENCOUNTER e DEV. D E E P SPACE DEV. 1OOK LBS T O EARTH ORBIT e DEV. 400K LBS EARTH ORBIT 8 �EARTH ORBITAL FLIGHT PLAN / * s FLJGHTS SCHEDULE TO BE DETERMINED a PRELIMINARY ESTIMATE FOR NUMBER OF LAUNCH VEHICLES - - 20 INTERMEDIATES NEW) 57 TITANS (USAF) 7 ATLAS -AGENAS a 221 LAUNCH VEHICLES THROUGH 1985 A Lunar Module (LM) V 0 0 0 8 t) Command and Service Module (CSM) LM/CSM Scientific & Earth Resources Experiments Orbital Workshop - Spent Stage Orbital Solar Observatory Orbiting Astronomical Observatory (OAO) a Apollo Telescope Mount (ATM ) One Year Module - Ground Fitted 8 Applications Technology Satellites D Orbiting Telescope - Man Tended (D Orbiting Geophysical Laboratory (OGO) BB Scientific Satellite - Atmosphere, Ionosphere & Magnetosphere (GSFC) 0 �LUNARANDINTERPLAMETARYFLIGHTPLAN / / UNMANNED SURFACE JUPITER & NEPTUNE # b 7 @ 0 Lunar ~odule/Command& Service Mbdule Lunar Flying Vehicle ) (LFV) I Local Scientific Survey Module ( L S S ~ Lunar Module Shelter Surveyor 8 Mars Q enu us Mercury �NASA / OMSF MISSION PROSPECTUS TOTAL : 50 TO 103 FLIGHTS ? (MAX : 81 FLIGHTS) , 2 1 EARTH ORBITAL FTATIONS I J 6 RESUPPLY TO 7 10 0 19 CALENDAR YEARS �MSFC SUPPLIED FLIGHT PLAN - OPTIMISTIC ("SATURN UTILIZATION STUDY") BALANCED - BUDGET CONSTRA (NED NMED SAT V IN -21 10 SM V I N -a o UN,%C~UNDSAT v I M -m V MANNED SAIURRV V UUMC\tJMD SATURN V R4TEi) SAT V UtMNNED TOTAL LAUNCH VEHICLES : 116 ��PAYLOAD WEIGHT REQUIREMENT TRENDS (PRELIMINARY) *IWEO - INITIAL #EIGHT EARTH ORBIT (SPENT BOOSTER + PAYLOAD) CALENDAR YEAR �WEIGHT REQUIREMENTS - LUNAR LANDED ASTRIONICS OPTIMISTIC P R O J E *INCLUDES A L L SUPPORTING SUBSYSTEMS 15 �PAYLOAD-VELOCITY REQUIREMENTS VS. - TECHNOLOGY 100 NM ORBIT LUNAR INJECTION SYNC ORBIT VESTA JUPITER FLYBY FLYBY *4 F-1 ENGINES ON S-IC 4.68 G'S MAX. ASCENT �LAUNCH VEHICLE PAYLOAD GROWTH CAPABILITY - WEIGHT IN 100 NM EARTH ORBIT CALENDAR YEAR �LAUNCH VEHICLE OPTIONS (100K LBS) PAYLOADS T O 100 NM FROM E T R (LBS) A SAT V SIB DEFUVATIVE: DERIVATIVE: INTERMEDIATE -20 MS -260 3I 3 DERIVATIVE: MS-I56 \ PRESSURE FED STORABLE TITAN I I IG �ASTRIONIC FUNCTIONS I Astrionic Subsvstem I Payload Checkout Prelaunch - - - - - - - - - - - - - - - - - - - - - - - - & Booster Boost I I I I i Phase (GNC) Reuse I I Maneuvers (GNC) I P o s t Boost Injection Rendezvous & Phase Orbital A s s y / A C ~ Attitude Control Data Eva1 & Transm. Midcourse @ Support 0 0 @ (GNC & Support Role) Payload Subsystem Functions Unmanned Satellite Experiment Carrier Landing Interim Exp. Module Piggyback Sensor Dev. OWS Support 0 9 Month Lifetime Completely Integrated Astrionic Subsystem Space Station Exp. Module 6-9 Man 1 -1/2 year lifetime Lunar and Interplanetary I �ASTRIONIC SUBSYSTEM �SYSTEMS ANALYSIS METHODOLOGY (1968 EFFORT) I SCIENCE DEV. PLANS MISSION ANALYSIS I I FLIGHT PLANS AND PROFILES I I VEHICLES LAUNCH/SPAC ECRAFT OVERALL ASTFUONICS I - - - - - - - SUBSYSTEMS C=J TECHNOLOGY \ - - - - - HAIDWARE DESIGN I IREQUIREMENTS I PROJ. APPLICATIONS AND COMMONALITY I �ASTRIONIC SUBSYSTEM PARAMETERS i SUBSYSTEMS, PARAMETERS I LV GNCS IC S EPS ECS LIFETIME (HOURS) X X X WEIGHT (POUNDS) X X X VOLUME (CUBIC F E E T ) X X PRIME POWER (WATTS) X THERMAL POWER DISSIPATED (WATTS) VELOCITY ACCURACY (FT/SEC) X I X X X X �PROJECTED ASTHONIC CONFIGURATIONS a 0 BLOCKIIIU - MODERATE UPDATES IN TECHNOLOGY - 1968 - '75 ADVANCED ASTRIONICS - 1975 - '85 - ALL NEW TECHNOLOGY �EVOLUTION OF ADVANCED ASTRIOM CS BLOCKI.1 IU I m 1968-71 o II 4 R I I I ADVANCED ASTFUONICS 4 I 4 1971-75 I 4 P 0 EXTENDED LIFE I U SYNC ORBIT 4 15 e m m 6 HI 1U B- e 4 R u n ADVANCED I U I 4 I E I SYNC ORBIT 24-36 HI I U 4 I I D 4 4 4 B II n0 I 4 n I PRESENT I U e a a a a 6.5 H;1 MISSION LAUNCH ORBIT CHECKOUT EXPERIMENT CRRRIER a a EXPERIMENT MODULES a AAP-A (2 WK IU) LASER SYSTEM COMMUNICATION EXPERIMENT (LSCE) CLUSTER UNMANNED SATELLITE 4 EXPERIMENT MODULES I : a a a I 4 I AAP-B (1-3 M O IU) LSCE CLUSTER DATA PROCESSING SATELLITE \ n 4 4 4 I M 4 --qq) I P P 4 I I W B 4 4 4 4 4 4 !l MISSION SUPPORT MODULES MISSION SUPPORT MODULES EARLY WORKSHOP 3 M O IU PASSNATION a RCS STABILIZATION e SPACER IU (ATM) ' a 4 ' I 4 I 4 4 I 4 4 I I P qq-p+ 4 4 I 4 SYNC WORKSHOP 2 YR lU CMG STABILIZATION a N BROADCAST EXPERIMENT SPACER l U GROUND FITTED 4 4 4 n 4 II 4 8, B I a a - / I I STANDARD SUBSYSTEM SUPPORT MODULE a I 4 0 4 4 1975-80 4 4 I 4 2 YR LIFE MARS MISSION LORL GNC --- DATA PROCESSING ATTITUDE POINTING POWER - ENVIRONMENT �GUIDANCE NAVIGATION CONTROL SUBSYSTEM �GNC FUNCTIONAL REQUIREMENTS (UNMANNED MISSIONS) ORIENT THRUST. ROUND BASED STAR FIXES. DOPPLER RADAR. HORIZON SENSING. MIDC OURSE . �GNC FUNCTIONAL REQUIREMENTS (UNMANNED MISSIONS) MISSION PHASES NG ATTITUDE. ANDDOPPLER. SERTION INTO ARTH-PLANET TRAJ* PLANETARY-BOUND TRAJECTORY ORIENT THRUST, GROUND BASED. GROUND BASED. ORIENT (INCREASED MIDCOURSE, CELESTIAL FIXES* RANGE & RATE - EXPERIMENTS, ANTENNAS. 27 �INTERPLANETARY GNC REQUIREMENTS AND CAPABILITIES ? MARINER IV \ PRIOR TO C JUPITER FLYBY PRIOR 9 - 1 13 I ,1 I ONLY I I b I I I p REQUIRED/ ACTUAL ESTIMATED I I I CALENDAR YEARS I 1 DSN ONLY SELF-CONTAINED DSN + ONBOARD SENSOR @ 30M NM FROM JUPITER �SATURN GUIDANCE AND NAVIGATION P E R F O R M A N C E Vehicle Number Velocity Vector E r r o r n v (fti~) .,* rl, Required Performance Radius V e c t o r E r r o r A R (ft) Injection Angle E r r o r b ++(deg. ) �GNC TECHNOLOGY TRENDS BOOST PHASE MIDCOURSE CORRECTIONS PAYLOAD ATTITUDE CONTROL NAVIGATION STATE O F THE ART Command Gui, Limited (In B o o s t e r ) AV Temporary Excursions f o r A V Corrections MODIFICATION * L e s s Accurate Fixes at Periodic and C r i t i c a l 0 Aided by OnBoard Radar/ 0 Augmented by Multiple 4 V Corrections Measurements Command Gui. Improved Impact Parameter S t a t i s t i c a l Nav. A c c u r a t e OnBoard Nav. Multiple Optical Radar Verifi- f o r AV C o r r e c t i o n s A c c u r a t e Att. Cont. & Radar Sensors Cold Gas J e t s & CMGts Correction �TECHNOLOGY TRENDS - WEIGHT AND ACCURACY TRADES PROPELLANT WE REQUIREMENTS AV- FT/SEC STRAP-DOWN ACCURACY �INSTRUMENTATION COMMUNICATIONS SUBSYSTEM �MILESTONES TIME (W) MINIMUM PREDESIGN CONCEPTS PAPER MODEL & BREADBOARD (SELECT TECHNOLOGY) DEVELOPMENTAL MODEL (IN A USABLE CONFTGURATION) PROTOTYPE MODEL (LIKE PRODUCTION) PRODUCTION MODEL (QUALITY TEST & PRODUCTION UNITS) FLIGHT PASSENGER (FLIGHT QUALIFY) FLIGHT ACTIVE (ASSIGNED TO A MISSION) TOTAL TIME MAXIMUM �ICS CIRCUIT TECHNOLOGY ADVANCED ASTRIONICS SYSTEM BLOCK I1 IU (MODERATE 0 BI-POLAR TIEANSISTER INTEGRATED CIRCUITS (LSI) 50 + GATES/CHIP - TRANSISTER-TRANSISTER - BI -POLAR - DIODE - TRANSISTER LOGIC - CURRENT MODE LOGIC - INSULATED GATE FIELD • NEW TECHNOLOGIES - LOW TEMPERATURE EFFECT TMNSISTER (IGFET) SINGLE DIFFUSION (DC & AC) COMPLEMENTARY - HYBRID BI-POLAR/IGFET - COMPLEMENTARY - INTEGRATION - MOLECULAR CIRCUITS �INTEGRATED LOGIC CIRCUIT GATES P E R CHIP TRENDS 10K POWER GATES 1000 P4 H z U g 100 PI 8 E POSSIBLE BREAKTHROUGH COULD CAUSE SIGNIFICANT INCREASE IN NUMBER O F GATES P E R CHIP 4 a 10 LOWER POWER GATES TIME OF AVAILABILITY 35 �INTEGRATED CIRCUIT CHIP SIZE TRENDS '72 '7 4 TIME OF AVAILABILITY '7 6 �I INTEGRATED LOGIC CIRCUIT POWER-SPEED PRODUCT TRENDS TIME O F AVAILABILITY 37 �COMMUNICATION TECHNOLOGY - DATA RATE GROWTH J -10 - ----- 10 FRAMES/SEC 8 -l o - I - . - ---- - 6 - - - -10 4 - -- - - --- - 1 FRAME/SEC. 1 F R A M E / ~SEC. ~ YEARS �DATA ACQUISITION REQUIREMENTS �ELECTRICAL POWER SUBSYSTEM �UNMANNED SATELLITE ELECTRICAL BOWER REQUIREMENTS SATELLITE TYPES GE - GEOPHYSICAL EXPEFUMENT SE - SPACE EXPLORATION WS - WEATHER SATELLITE ND - NUCLEAR DETECTION MD - METEOROID BE - BIOLOGICAL EXPERIiVIENT CS - COMMUNICATIONS SATELLITE BT -BALLISTIC TEST CALENDARYEAR �lYIANNED SPACECRAFT POWER REQUIREMENTS CALENDAR YEAR �BATTERYANDFUELCELLTECHNOLOGY FLIGHT PR!MAR'( FUEL- CELLS U N I T POWER 1 5 KW 1 I ��NUCLEAR POWER TECHNOLOGY CALENDAR YEAR �ENVIRONMENTAL CONTROL SUBSYSTEM �ENVIRONMENTAL CONTROL REQUIREMENTS AND TECHNOLOGY Electronic Propelled Lunar Options MO L- RTGS ,-a Missions Louvers, Radiators, Active IU: Circ Fluid, Heaters, cold Plates, & Sublimator -prated Mariner 'Mars: Passive with Louvers & Heaters& Cold Plates s & Heaters & Cold Plates neer: passive / 1 57 - 6b 65 7b 75 CALENDARYEAR do 85 �LAB TESTS IU - S-IVB SEPARATION SYSTEM �PURPOSE AND DEFlbllTlOkl OF PAYLOADS A AND B a DETERMINE OPTIMUM SENSORS Q lN IT IATE SPACE MITEOROLOGY AND EARTH SURVEY 6 DETERMINE VALUE OF MAN'S PARTI C l PAT lON METEOROLOGY (A) NATURAL RESOURCE SURVEY (B) 6 MICROWAVE RADIOMETRY a MULTI SPECTRAL PHOTOGRAPHY a I R SPECTROSCOPY a INFRARED RADIOMETRY AND SPECTROSCOPY a POLAR IM n R Y a RADAR a UV PHOTO-S PECTROMETRY ��DOCKING RING PER l MENT RACK RACKllU INTERFACE CABLE 2 �CLUSTER MISSION! PROFILE S-IVB CLUSTER WORKSHOP --------- 5. 4. 9. IUlSLA DOCKED CSM DOCKED TO IUlSLA CSM SEPARATION b 14 DAYSl90DAYS 12. REENTRY �PROJECT THERMO PURPOSE : VERJFY LONG DURATION CRYOGENIC VEHICLE DESIGN TECHNIQUES - PROPULSION, I, E., MARS FLYBY - FUEL CELLS EXPERIMENTS (AT e lom2TO G'S) - CONDENSING HEAT TRANSFER - BOILING HEAT TRANSFER INTERFACE STABILITY - HIGH PERFORMANCE INSULATION - STRATIFICATION - MASS GAGING PROPELLANT TRANSFER - DESTRATIFICATION BOILOVER (ON PROPELLANT TRANSFER AM) BOILING H. T o TANKS) VENT SEPARATOR WEIGHT : 15K LBS S I B CAPABILITY : 22K LBS T O 260 NM �PROJECT THERMO IU/SLA SATELLITE (IBM-LOCKHEED-MSFC) IU - S-IVB SEPARATION �PROJECT THERMO IU/SLA EXPERIMENT MODULE (UNMANNED SATELLITE) LOWER SLA ACCELERATI THRUSTERS THRUSTER PROPELLANT TANKS �P R O J E C T THERMO IU/SLA EXPERIMENT MODULE I LOWER SLA* THRUSTERS *SLA - SPACECRAFT LM ADAPTER 1 / 6 0 ~SCALE ~ 1 JETS bHYDROGEN TANK DOME �PAYLOAD WEIGHT CONSTRAINTS (UPRATED SATURN-IB) EST. INJECTED WEIGHT (ABOVE S -1VB) : LESS NOSE CONE & SLA : INJECTED PAYLOAD WEIGHT : 22,400LBS. - 3,640LBS. 18,760 LBS. PAYLOAD MA RGIN (260NM) 3800 LBS. PAYLOAD (1000 LBS), �SATURN S-IVB AFT DMTERSTAGE SEPARATION SYSTEM UPRATED SATURN SATURN �RECOHHEMDEB IU/S-BVB SERARAT ION CONCEPT BEFORE SEPARATION AFTER SEPARATION �RECOMMENDED IU/S-IWW SEPARATION CONCEPT I U STRUCTURE TENS lON PLATE DEBRIS SHIELD SEPARATION PLANE ��IU/S-IVB SBPARATIOM SYSTEM QUALlFlCATlOM APPROACH o SMALL SEGMENT TESTS TO VER IFY PYROTECHNIC CHARGE AND STRUCTURE 0 LARGE SEGMENT TESTS TO VER IFY ENVIRONMENT 0 STATIC LOAD TESTS 0 SEPARATION SYSTEM QUALIFICATION TEST - COMPLETE I U STRUCTURE - S IVBISLA STRUCTURAL SEGMENTS �R I S K S DEPENDENCIES MARKETING �DEPENDENCIES AND RISKS DEPENDENCIES NASA PLANNING AND BUDGET - OSSA UNMANNED MISSION INCREASE ADVANCED SPACE STATION - WHEN? - MANNED PLANETARY FLIGHT - WHEN? NUCLEAR STAGE DEVELOPMENT ELECTRICAL POWER TECHNOLOGY VS COMMUNICATIONS TECHNIQUES, E. G. , LASERS TWO -YEARS MAN -IN -SPACE - - o (EARTH ORBIT) NASA/USAF MISSION INTEGRATION ASTRIONICS NASA BUDGET : $1.2B T O $0.4 8 SELECTED LAUNCH VEHICLE MIX - TITAN VERSUS S -1VB DERIVATIVES LSI CIRCUIT BREAKTHROUGH - WHEN? HOW? - PRE-EMPTION BY OTHER CONTRACTORS RISKS - Iu/s-IVB - MINIMAL CURRENT INVESTMENT, RISK REDUCED SEPARATION SYSTEM HARDWARE ($50K) VS APPROVED NASA PROJECTS �MARKETING 1 9 6 8 PLANS IN PREPARATION STRATEGY - COORDINATE STUDY, TESTS, DESIGNS WITH NASA/USAF PROPOSE FULL -SCALE IU -S IVB SEPARATION SYSTEM DEVELOPMENT SUBMIT UNSOLICITED PROPOSALS : EACH DESIGN DEVELOPED IN 1968 LEAD CUSTOMER NEW APPLICATIONS PROJECT IDENTIFICATION TECHNOLOGY HARDWARE DESIGN ACTIVITIES - IBM/LOCKHEED/MSFC PROPOSING IU/SLA FOR THERMO MEETINGS/VISITS NASA HEADQUARTERS AND MSFC WEEK AVERAGE) LOCKHEED, HUNTSVILLE (WEEKLY T O DAILY) NASA E R C PLANNED 3/68 BATELLE MEMORIAL INSTITUTE (NAsA/OSSA) MARTIN MARIETTA : IU/SLA, - - 11/20/67 11/1/67 ESTABLISH USAF CONTACTS THROUGH FSD-WEST AND WASHINGTON MARKETING � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000037 Title A name given to the resource Advanced Astrionics project review. Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. IBM No. 68-K05-0001 Description An account of the resource Given at the IRAD Technical Seminar, Gaithersburg, Maryland, January 30, 1968. F. L. Pugh, Principal investigator; E. C. Caldwell, Advanced IU Systems, IBM Huntsville. Creator An entity primarily responsible for making the resource Caldwell, E. C. Pugh, F. L. International Business Machines Corporation. Federal Systems Division. Space Systems Center Date A point or period of time associated with an event in the lifecycle of the resource 1968-01-30 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Launch vehicles (Astronautics)--Guidance systems Launch vehicles (Astronautics)--Control systems Spacecraft electronic equipment Spacecraft instruments Type The nature or genre of the resource Reports Text Source A related resource from which the described resource is derived Saturn V Collection Box 25, Folder 24 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050 https://digitalprojects.uah.edu/files/original/20/985/spc_stnv_000038.pdf 915f8c08118f287c21eafd53129da7c7 PDF Text Text AERO-ASTRODYNAMICS LABORATORY BIMONTHLY PROGRESS REPORT June-July 1968 INDEX 111 ........................... ADVANCED STUDIES OFFICE .................................. PROJECTS OFFICE .......................................... IV AEROSPACE ENVIRONMENT DIVISION TECHNICAL AND SCIENTIFIC STAFF . . . I1 v . . . .. . ......................... ASTRODYNAMICS AND GUIDANCE THEORY DIVISION A S c i e n t i f i c Advisory O f f i c e B Guidance Theory ranch C O p t i m i z a t i o n Theory Branch D Astrodynamics Branch . . . . V I I. VIII ..................................... ............................. ............................ ...................... ........................... AEROPHYSICS DIVISION A Mechanical Design O f f i c e B Aerodynamic Design Branch C Experimental Aerophysics Branch D Thermal Environment Branch E Unsteady Gas Dynamics Branch . VI ........................... ............... ........................... ............................... ........................... ................................. ................... DYNAMICS AND nIGHT MECHANICS DIVISION A Damping of Liquid O s c i l l a t i o n s by Wall Roughness B Saturn V ............................. C S a t u r n IB D S a t u r n Apollo A p p l i c a t i o n Program E G e n e r a t i o n of Real E a r t h Model C i r c u l a r and E l l i p t i c a l O r b i t V e l o c i t y Requirements S a t u r n V Launch Vehicle and S p a c e c r a f t Launch F Probability ..... ......... ....... ............................................ .................... ............... . .......................................... FLIGIFT TEST ANALYSIS DIVISION ............................ A . F l i g h t Mechanics Branch .............................. B. Tracking and O r b i t a l A n a l y s i s Branch ................. C . F l i g h t E v a l u a t i o n Branch ............................. . . . .. . �AERO-ASTRODYNAMICS LABORATORY BIMONTHLY PROGRESS REPORT I. TECHNICAL & SCIENTIFIC STAFF A TM X e n t i t l e d "Wind Vector C a l c u l a t i o n Using Crossed-Beam Data and D e t e c t o r Arrangement f o r H o r i z o n t a l Winds," was w r i t t e n and i s i n It s e t s f o r t h t h e c o n d i t i o n s i n which t h e process of being published. a continuous, though bounded, a r r a y of unknown winds w i t h i n a l i m i t e d space volume can be monitored w i t h s u f f i c i e n t accuracy and confidence. The g e n e r a l method has been a p p l i e d and f u r t h e r developed i n t h e p r a c t i c a l important c a s e of h o r i z o n t a l wind motion. As a n example, l o c a t i o n s and a t t i t u d e s of t h r e e ground-based d e t e c t o r s have been computed f o r measuring h o r i z o n t a l winds t h a t could be p r e s e n t a t t h e 100 m-level blowinr from two o p p o s i t e q u a r t e r s of t h e r o s e . (Heybey) 11. ADVANCED STUDIES OFFICE A. F l i g h t Mechanics and Performance Analysis Group 1. Launch Vehicles The RFQ on t h e "Launch Vehicle T r a j e c t o r y O p t i m i z a t i o n Comp u t e r Program (Phase IV)" was r e l e a s e d on June 13, 1968. The computer .program i s t o be developed f o r u s e on t h e 1108 system f u l l y u s i n g t h e remote s t a t i o n s f o r q u i c k response time. F i f t e e n p r o p o s a l s , which have been r e c e i v e d i n response t o t h e RFQ, a r e now being e v a l u a t e d . DAP i s a s s i s t i n g i n t h i s e v a l u a t i o n and s e l e c t i o n of t h e c o n t r a c t o r , and i t i s a n t i c i p a t e d t h a t they w i l l a s s i s t i n c o n t r a c t o r monitoring and o r i e n t a t i o n i n o r d e r t h a t t h e i r previous e f f o r t s may be e f f i c i e n t l y used and expanded. Requests f o r performance i n f o r m a t i o n have been r e c e i v e d from b o t h Col. Burke and M r . N o b l i t t of NASA Headquarters. These d a t a included performance c a p a b i l i t i e s of t h e I n t - 2 0 and I n t - 2 1 v e h i c l e s w i t h s t a n d a r d 5 - 2 engines and w i t h t h e J-2s e n g i n e s . This i n f o r m a t i o n i s t o be used f o r planning a c t i v i t i e s a t NASA Headquarters. �Performance d a t a on t h e S a t u r n and T i t a n v e h i c l e s a r e being run i n s u p p o r t of t h e u t i l i z a t i o n s t u d y . Data f o r t h e S a t u r n 660K v e h i c l e has been obtained and a r e p o r t published on June 20, 1968. The d a t a f o r t h e T i t a n IIIM have been completed, and a r e p o r t w i l l be published soon. Performance runs a r e a l s o being made on t h e SA-IB, SA-IB c o r e v e h i c l e , and SA-IB MLV 11.7B. 2. Nuclear S t u d i e s R-AS-VP'requested and was provided w i t h d a t a on t h e high energy mission performance c a p a b i l i t y of t h e t h r e e - s t a g e S a t u r n MLV-255 w i t h and w i t h o u t a Centaur f o u r t h s t a g e f o r a c o s t e f f e c t i v e n e s s comp a r i s o n s t u d y of t h e S a t u r n nuclear System w i t h a n a l l - c h e m i c a l system f o r h i g h energy missions i n t h e 1977-1980 time frame. Performance d a t a on a spectrum of v e h i c l e s have been g i v e n t o M r . Whit B r a n t l e y f o r OWS/NPS ( o r b i t a l workshop/nuclear e l e c t r i c power s y s tem) i n t e g r a t i o n s t u d y . 3. S a t u r n V Workshop On Monday, June 17, 1968, a p r e s e n t a t i o n was g i v e n t o D r . von Braun on t h e S a t u r n V Workshop a c t i v i t y . The d i s c u s s i o n was d i r e c t e d p r i m a r i l y a t answering a r e q u e s t from M r . Chuck Mathews' o f f i c e t o d e f i n e a n i n t e r m e d i a t e workshop t o be flown i n 1973-74. The c l a s s e s of s t a t i o n s developed were t h e f o l l o w i n g : I n t e g r a l : a l l systems, i . e . , crew q u a r t e r s , subsystems, experiments a r e a l l developed and launched i n t e g r a l l y . Hybrid: i n t e g r a l except t h a t t h e experimental module can b e interchanged a n d / o r flown s e p a r a t e l y . Modular: a l l major systems developed and flown s e p a r a t e l y and s m a l l s h o r t - d u r a t i o n s t a t i o n s , e . g . , MOLY SLA-lab type s t a t i o n s w i t h l i f e t i m e l i m i t e d t o 90 days. A s e r i e s of meetings was h e l d a t NASA Headquarters on t h e I n t e r m e d i a t e Space S t a t i o n (launched 1973-1974) l e a d i n g up t o a p r e s e n t a t i o n t o M r . Mathews on June 28, 1968, by MSC, Langley and MSFC. The MSFC p r e s e n t a t i o n was g e n e r a l l y considered t o be o u t s t a n d i n g i n terms of t h e amount of d a t a g e n e r a t e d i n t h e s h o r t p e r i o d of time allowed. The Langley group recommended a concept v e r y s i m i l a r t o t h e MORL launched on t h e I n t e r m e d i a t e 20 (S-IC/S-IVB) and r e s u p p l i e d by S a t u r n I B . MSC presented t h e i r MOM (Manned O r b i t i n g Module) concept using o n l y S a t u r n I B f o r launch of t h e s t a t i o n and n e c e s s a r y r e s u p p l y f l i g h t s . The Marshall s t u d y was much broader i n that f o u r concepts ( i n t e g r a l , �h y b r i d , modular, s m a l l / s h o r t d u r a t i o n ) were 'developed, w i t h primary emphasis being placed on t h e hybrid and modular o p t i o n s . The recomrnendat i o n s from Mathews and Mueller were t o s t r e s s , i n t h e f u t u r e , t h e modular approach and t o emphasize u s e of t h e I B . 4. P r e s s u r e Fed Launch Vehicle A p r e s e n t a t i o n was g i v e n t o M r . Frank Williams on J u l y 9, 1968, on t h e p r e s s u r e - f e d launch v e h i c l e performance t r a d e o f f s ( i . e . , r e l a t i v e p r o p e l l a n t l o a d i n g s ) on t h e two- and t h r e e - s t a g e v e h i c l e s . For t h e t h r e e - s t a g e v e h i c l e , b o t h two and f o u r engines were considered f o r t h e second s t a g e , and i t s performance a p p e a r s t o be 70 p e r c e n t t o 90 p e r c e n t h i g h e r t h a n a two-stage v e h i c l e of comparable l i f t o f f weight. B . As trodynamics and Miss i o n Analys i s Group 1. Optimum Mu1 t i - I m p u l s e Rendezvous Program An optimum multi-impulse rendezvous (OMIR) computer program has been o b t a i n e d from t h e Manned Space F l i g h t Center i n Houston. This program u s e s ~ a w d e n ' s primer v e c t o r concept t o determine t h e optimum number and t h e l o c a t i o n of t h e impulses. The OMIR program i s capable of determining optimal three-dimensional rendezvous t r a ject o r i e s r e q u i r i n g a s many a s s i x impulses, under t h e r e s t r i c t i o n of twobody motion. The OMIR program i s being made compatible w i t h t h e UNIVAC 1108 computer a t t h e MSFC Computation Laboratory. 2. unmanned P l a n e t a r y S t u d i e s Langley Research Center l e t f o u r c o n t r a c t s i n March and A p r i l of t h i s year t o s t u d y powered s p a c e c r a f t , d i r e c t v e r s u s i n d i r e c t m i s s i o n modes f o r t h e Mars l a n d e r c a p s u l e , and hard and s o f t l a n d e r s f o r t h e 1973 Mars mission. The c o n t r a c t s were (a) Mars S o f t Lander Capsule Study, McDonnell-Douglas C o r p o r a t i o n , $91K, 3 months, f i n a l p r e s e n t a t i o n June 25, 1968, COR, M r . Chuck I n g l e s , LRC. (b) Study of Powered S p a c e c r a f t f o r Mars Missions, The Boeing Company, $93K, 3 months, f i n a l p r e s e n t a t i o n June 26, 1968, COR M r . Canady, LRC. (c) Study of D i r e c t v e r s u s O r b i t a l E n t r y f o r Mars Miss i o n s , M a r t i n M a r i e t t a Corporation, $loOK, 3 months, f i n a l p r e s e n t a t i o n J u l y 1, 1968, COR, M r . Dan Snow, LRC. �(d) Mars Hard Lander Capsule Study, General E l e c t r i c Company, @4K, 3 months, f i n a l p r e s e n t a t i o n J u l y 30-31, COR, M r . Bob Smith, LRC. M r . Bobby E l l i s o n , from t h i s o f f i c e , a t t e n d e d t h e f i n a l p r e s e n t a t i o n on (a) and (d) above. These a r e r e p o r t e d i n t r i p r e p o r t s , R-AERO-X-28-68 and i n t h e P l a n e t a r y Working Group. 3. P l a n e t a r y Nuclear Mission Parameter Study TRW gave a p r e s e n t a t i o n J u l y 24 on t h e i r p l a n e t a r y n u c l e a r m i s s i o n parameter s t u d y , NAS8-5371. Mars o r b i t a l c a p t u r e - l a n d e r m i s s i o n s and a Venus o r b i t a l c a p t u r e m i s s i o n were s t u d i e d d u r i n g t h e 1980-93 time period. I n i t i a l v e h i c l e weight was optimized w i t h r e s p e c t t o v a r i o u s parameters. These included t r a j e c t o r y types and launch o p p o r t u n i t i e s , v e h i c l e con£ i g u r a t i o n s , p l a n e t a r y s t o p o v e r t i m e s , engine t h r u s t l e v e l s , n u c l e a r engine a f t e r c o o l i n g , e l l i p t i c a l parking o r b i t s a t t a r g e t p l a n e t , and e a r t h launch window d u r a t i o n . The use of e l l i p t i c a l parking o r b i t s a t t h e t a r g e t p l a n e t was found t o produce v e h i c l e weight s a v i n g of up t o 30 p e r c e n t over t h a t r e q u i r e d f o r c i r c u l a r parking o r b i t s . Also, by t h r u s t i n g d u r i n g a f t e r c o o l i n g , a 6 p e r c e n t weight s a v i n g was o b t a i n e d . Published r e s u l t s of t h i s s t u d y w i l l be a v a i l a b l e i n one month. F u r t h e r a n a l y s e s were recommended i n t h e a r e a s of e l l i p t i c a l parking o r b i t s a t e a r t h : t h e employment of m u l t i p l e burns f o r e j e c t i o n from parking o r b i t s and t h e a s s o c i a t e d r a d i a t i o n s h i e l d i n g p e n a l t i e s f o r r e p e t i t i v e passes through t h e Van A l l e n b e l t , launch window d u r a t i o n f o r d e p a r t u r e from t h e t a r g e t p l a n e t , and o p e r a t i o n a l d i f f i c u l t i e s involved i n t h e r e s t a r t and a f t e r c o o l ing of t h e n u c l e a r e n g i n e s . C. System Analysis Group The a n a l y s i s i s s t i l l i n p r o g r e s s t o determine t h e i m p l i c a t i o n s of c o n v e r t i n g t h e AS-210 S-IVB t o a S a t u r n V launched m i s s i o n w h i l e r e t a i n i n g i t s S a t u r n I Workshop backup s t a t u s . The p r e l i m i n a r y r e s u l t s of t h e MDC/MSFC s t u d y i n d i c a t e t h a t t h e conversion t o a S a t u r n V Workshop i s f e a s i b l e , r e l a t i v e l y s i m p l e , inexpensive, and a c h i e v a b l e s o a s t o c l o s e l y f o l l o w t h e S a t u r n I Workshop. Out of s e v e r a l approach o p t i o n s , t h e " s e l e c t e d " conversion p l a n (based on t h e r e l e a s e of AS-210 a t KSC) can be c a r r i e d o u t a t KSC i n 9 months from workshop r e l e a s e t o launch. �PROJECTS OFFICE 111, 1. AS-205 DCR Meeting On June 5 and 6, 1968, t h e AS-205 DCR Board met a t KSC. Launch Complex 34 and 39 were d i s c u s s e d d u r i n g t h e f i r s t day and h a l f . On t h e a f t e r n o o n of June 6, 1968, t h e AS-205 l a n d , l a n d i n g problem was d i s c u s s e d by MSFC. These items a r e b r i e f l y summarized below: M r . Huss, MSC, p r e s e n t e d t h e GO/NO-GO launch procedure t o avoid land l a n d i n g . There a r e t h r e e d e c i s i o n s involved, which a r e (1) pickup count, (2) crew i n g r e s s , and (3) launch. A l l t h r e e d e c i s i o n s w i l l be based on wind monitoring s i m u l a t i o n s a t MSC. The f i r s t two w i l l s i m u l a t e pad a b o r t which can w i t h s t a n d a wind from t h e e a s t 25 f t / s e c . The d e c i s i o n whether o r n o t t o launch w i l l be based of on s i m u l a t i o n covering t h e f i r s t 15 seconds of f l i g h t . As a r u l e of thumb, a n a v e r a g e wind component f o r a l t i t u d e s of 0 t o 7,000 f e e t of 1 f t / s e c o r g r e a t e r from 72" e a s t of n o r t h w i l l y i e l d p r e d i c t i o n of land impact. D e c i s i o n (1) w i l l be based on e s t i m a t e d winds 12-24 hours b e f o r e launch, whereas d e c i s i o n s (2) and (3) w i l l b e based on measured winds. For September, t h e r e i s x 90 p e r c e n t p r o b a b i l i t y o f crew i n g r e s s w i t h a launch p r o b a b i l i t y of 25 t o 35 p e r c e n t i f t h e winds a r e indeed r e s t r i c t e d t o avoid land landing. The MSFC and MSC p r o b a b i l i t y c a l c u l a t i o n s a r e i n agreement. - MSC a l s o p r e s e n t e d t h e AS-205 launch escape v e h i c l e , LEV a b o r t performance. P r e v i o u s l y t h e manual a b o r t l i m i t s of 3 d e g / s e c a t t i t u d e r a t e and 5 degrees a t t i t u d e e r r o r i n p i t c h and yaw have been employed due t o LEV c a p a b i l i t y . However, a s t r o n g push w i t h i n MSC has r e s u l t e d i n t h e e l i m i n a t i o n of t h e manual l i m i t s . The a u t o m a t i c a b o r t l i m i t of 5 d e g / s e c i s s t i l l v a l i d and w i l l c a t c h t h e i d e n t i f i e d f a i l u r e s r e q u i r i n g near-pad a b o r t . An e a r l y l o s s of p l a t f o r m w i l l r e s u l t i n t h v e h i c l e ' s f a i l i n g t o p i t c h , t h u s , f l y i n g v e r t i c a l l y . For t h i s f a i l u r e 5 and i f t h e range s a f e t y o f f i c e r w i l l a b o r t t h e f l i g h t a t ~ 5 seconds, t h e wind r e s t r i c t i o n s t o a v o i d land l a n d i n g d u r i n g t h e f i r s t 15 seconl i s a p p l i e d , t h e c a s e w i l l n o t r e s u l t i n l a n d i n g on l a n d . Of c o u r s e , tower c o l l i s i o n should occur and r e q u i r e a b o r t , l a n d impact i s q u e s t i a b l e . MSC summarized t h e land- and w a t e r - l a n d i n g c a p a b i l i t y , which . b e i n g updated f o r t h e h e a v i e r SIC. The land-landing t e s t s have show t h a t t h e AS-205 primary s t r u c t u r e w i l l s u r v i v e ; however, t h e i n t e r n a s p a c e c r a f t damage t o t h e RCS t a n k s , couch f o o t r e s t r a i n t , honeycomb s t r u t s , and secondary s t r u c t u r e i s unknown. M r . Hagood i n t r o d u c e d . AS-205 f l i g h t mechanics EDS summary, g i v i n g t h e purpose, t h e gound and c o n s t r a i n t s , and t h e method used i n determining t h e l i m i t s . M r . Swider, CCSD, p r e s e n t e d t h e r e s u l t s of t h e f a i l u r e mode simular and summarized t h e AS-205 a u t o m a t i c and manual l i m i t s . The r e q u i r f o r t h e Q-ball s e n s o r w a s questioned s i n c e t h e AS-205 a n a l y s i s sho �t h a t one a c t u a t o r hardover i s t h e o n l y f a i l u r e where t h e Q-ball (qa) i n d i c a t i o n i s a cue, and i t i s followed c l o s e l y by t h e o v e r r a t e s e n s o r . An a c t i o n item w a s a s s i g n e d t o determine t h e requirement f o r t h e Q-ball on S a t u r n I B . 2. Twelfth FLSP Meeting The 1 2 t h F l i g h t Limits Sub-panel Meeting was h e l d a t MSFC on June 5 , 1968. The AS-205 LEV l i m i t s and procedure f o r GO/NO-GO launch d e c i s i o n t o a v o i d land impact were d i s c u s s e d . Other items covered a r e a s f o l l o w s : - Analyses a r e i n p r o g r e s s t o d e t e r S a t u r n V LEV Limits mine i f manual a b o r t l i m i t s a r e a p p l i c a b l e f o r n e a r pad. MSC i s determining whether o r n o t the max a l i m i t f o r max q can be i n c r e a s e d . It a p p e a r s t h a t t h e b o l t s which a t t a c h t h e tower t o t h e CM w i l l be t h e r e s t r i c t i n g item. - The AS-503 launch v e h i c l e f l i g h t S a t u r n V, AS-503 mechanics EDS a n a l y s i s has been published. MSFC p o i n t e d o u t t h a t t h e S-IC outboard engines c a n t of = 2 degrees t o h e l p a l l e v i a t e t h e S / C l o a d s f o r one engine o u t w i l l be on AS-503. The backup t o t h e p l a t f o r m f a i l u r e w i l l n o t be implemented on S a t u r n I B o r V. On S a t u r n V, t h e d i s p l a y f o r p l a t f o r m f a i l u r e i s being modified such t h a t b o t h t h e guidance f a i l l i g h t ( p l a t f o r m f a i l u r e ) and t h e o v e r r a t e 1i g h t w i l l i n d i c a t e a p l a t f o r m f a i l u r e . This provides redundance and t h e two cues a r e a v a i l a b l e f o r crew t o abort: i f t h e f a i l u r e o c c u r s i n max q. review. - The FLSP EDS r e p o r t f o r AS-205 i n f i n a l Documentation Plans a r e t o b e g i n t h e AS-503 r e p o r t i n mid-August. - During t h e AS-205 Launch Vehicle DCR, APS F a i l u r e D r . Mueller asked i f t h e S-IVB could f l y w i t h one APS i n o p e r a t i v e . Analyses show t h a t , f o r t h e b o o s t phase, r o l l c o n t r o l i s maintained f o r one APS i n o p e r a t i v e . Analyses a l s o show t h a t , f o r t h e b o o s t phase, r o l l c o n t r o l i s maintained f o r one APS module f a i l u r e ; however, f o r t h e o r b i t a l phase,one module f a i l u r e r e s u l t s i n l o s s of c o n t r o l of t h e vehicle. - MSC i s proposing a m i s s i o n r u l e t o r e t a i n LET J e t t i s o n t h e launch escape tower (LET) p a s t nominal j e t t i s o n time i f Mode I1 a b o r t (SM a b o r t ) i s n o t achieved. This was d i s c u s s e d d u r i n g t h e meeti n g and R-AERO/R-ASTR a n a l y s e s show t h a t t h e v e h i c l e goes u n s t a b l e i f 22 seconds t h e LET is h e l d p a s t t h e S-IVB g a i n change, which o c c u r s a f t e r nominal j e t t i s o n . The m i s s i o n r u l e w i l l be modified t o r e f l e c t our r e s u l t s . The minutes of t h e meeting a r e being documented. - �3. J-2S Study Study p l a n s , ground r u l e s , and s e l e c t i o n of m i s s i o n prof i l e s have been accomplished. The s e l e c t e d s t u d y m i s s i o n p r o f i l e s i n c l u d e a b a s i c LOR miss i o n , synchronous, two-s t a g e low e a r t h o r b i t , and a 100 n.mi. p o l a r o r b i t . Nominal t r a j e c t o r i e s have been g e n e r a t e d f o r t h e s e s t u d y m i s s i o n p r o f i l e s . The f o l l o w i n g p r e l i m i n a r y d e s i g n c r i t e r i a have been t r a n s m i t t e d t o t h e s e v e r a l c o n t r a c t o r s : J-2s engine exhaust plume c h a r a c t e r i s t i c s , S - I 1 b a s e h e a t i n g environment, aerodynamic h e a t i n g environment, on-pad and i n - f l i g h t a c o u s t i c environment, and s t a t i c aerodynamic and l o a d d i s t r i b u t i o n c h a r a c t e r i s t i c s . 4. Plume Contamination T e s t i n g A plume contamination t e s t i n g program f o r t h e AAP C l u s t e r has been planned d u r i n g t h i s p e r i o d i n response t o a r e q u e s t from R-P&VE. R-AERO-AT c o n t a c t e d t h e A i r Force and MSC t o determine t h e e x t e n t of contamination t e s t i n g done i n t h e p a s t and planned f o r t h e f u t u r e . The A i r Force i s p r e s e n t l y t e s t i n g a t AEDC t o determine t h e contamination of t h e MDL by plume c o n s t i t u e n t s , and R-AERO-AT has cons i d e r e d t h i s t e s t i n g i n t h e t e s t p l a n . The p r e l i m i n a r y t e s t p l a n i s b e i n g e v a l u a t e d by R-P&VE and on August 2, 1968, a meeting has been scheduled t o determine t h e a v a i l a b i l i t y of funds. 5. AAP C l u s t e r Work continued d u r i n g June and July on t h e C l u s t e r Mission w i t h primary emphasis on t h e unmanned rendezvous a n a l y s e s f o r AAP-4, t h e e a r t h r e s o u r c e s experiments c o m p a t i b i l i t y f o r AAP-1/2, and performance improvement f o r AAP-2 t o overcome a growing payload weight/performance problem. E f f o r t t o d a t e i n d i c a t e s t h a t t h e h y b r i d s t a b l e o r b i t technique i s b e s t f o r t h e unmanned rendezvous of AAP-4. Studies indicate t h a t the use of a second burn i n t h e AAP-4 rendezvous scheme i s n o t a t t r a c t i v e . R e s u l t s of t h e e a r t h r e s o u r c e s experiments c o m p a t i b i l i t y a n a l y s e s t o d a t e i n d i c a t e t h a t t h e experiments can b e packaged and t i m e l i n e d on t h e AAP-1/2 m i s s i o n . However, t h e a d d i t i o n a l weight involved (about a 1,000 pounds) p l a c e s t h e AAP-2 i n a n e x c e s s i v e l y overweight c o n d i t i o n . Some of t h e performance impzovements b e i n g i n v e s t i g a t e d f o r AAP-2 i n c l u d e t h e u s e of t h e CSM RCS system t o b o o s t t h e AAP-2 t o h i g h e r a l t i t u d e , t h e r e b y reducing t h e r e q u i r e d i n s e r t i o n a l t i t u d e f o r AAP-2, use of a h i g h e r performance 3-2 e n g i n e i n t h e OWS S-IVB s t a g e and i n s e r t i o n of t h e AAP-2 a t p e r i g e e w i t h a c o a s t t o apogee f o r t h e p a s s i v a t i o n impulse t o c i r c u l a r i z e t h e o r b i t r a t h e r t h a n t h e p r e s e n t l y b a s e l i n e d apogee i n s e r t i o n w i t h immediate pass i v a t i o n . Another performance improvement that w i l l be i n v e s t i g a t e d , a s mentioned a t t h e B a s e l i n e Review Meeting a t MSFC on J u l y 23 and 24, 1968, i s t h e concept of p l a c i n g t h e AAP-2 i n t o a n e l l i p t i c a l o r b i t . R e s u l t s of t h i s i n v e s t i g a t i o n w i l l be r e p o r t e d a t a l a t e r date. �IV. AEROSPACE ENVIRONMENT DIVISION A. Environment Research Off i c e 1. During t h i s r e p o r t i n g p e r i o d , 45 rawin f l i g h t s were made by t h e MSFC Atmospheric Research F a c i l i t y i n s u p p o r t of s t a t i c t e s t s a t t h e T e s t Laboratory. S t a t i c t e s t s of t h e F-1 engine r e q u i r e d 34 f l i g h t s . Eleven f l i g h t s were r e q u i r e d f o r t h e two s t a t i c t e s t s of t h e S-IC b o o s t e r . 2. The CPS-9 weather r a d a r was placed back i n o p e r a t i o n , and d a t a f o r t h e R-AERO-YE thunders torm s t u d y a r e being a c q u i r e d . S e v e r a l of t h e Aerovane Anemometers have been s e r v i c e d i n s u p p o r t of t h i s s t u d y and d a t a have been recorded f o r t h e s t u d y . 3. A s e r i e s of t e s t s w i t h f o u r Climet cup-type anemometers was conducted i n t h e Dynamic Wind F a c i l i t y . Other t e s t s were conducted l s i n g t h e Reed-ball anemometer, b u t because of t h e h i g h t h r e s h o l d of t h e i n s t r u m e n t , no u s a b l e d a t a were o b t a i n e d . The Reed-ball anemometer i s a s t r a i n - g a g e type of i n s t r u m e n t , and t h e b r i d g e c i r c u i t i n t h e u n i t t e s t e d has a s t a r t i n g t h r e s h o l d of a b o u t 20 m i l e s p e r hour wind speed. This range of t h r e s h o l d makes t h i s instrument u n d e s i r a b l e f o r r e c o r d i n g s u r f a c e wind d a t a on a r o u t i n e b a s i s . 4. NASA's 150-meter M e t e o r o l o g i c a l Tower a . A l l r e c o r d i n g systems f u n c t i o n e d p r o p e r l y , p r o v i d i n g continuous wind, temperature, dew p o i n t , p r e s s u r e , and r e l a t i v e humidity data . b. being recorded. The s o l a r r a d i a t i o n gage was i n s t a l l e d and d a t a a r e now c . Two a u t o m a t i c r a i n gages which have been shipped t o t h e tower w i l l be i n s t a l l e d some time i n August. d. The wind d i r e c t i o n s e l e c t o r i s being r e d e s i g n e d . The d e s i g n has been completed and r e q u i r e d p a r t s f o r f a b r i c a t i o n ordered. The new s e l e c t o r should be ready by t h e f i r s t of November. e . A complete updated s e t of schematics f o r a l l systems on t h e tower was compiled and w i l l be added t o t h e Tower Operations Manua 1 . f . A 35 mm camera mounted a t t h e 30-meter l e v e l w i l l r e c o r d d a t a of thunderstorm a c t i v i t y i n t h e Cape a r e a . �B. Atmospheric Dynamics Branch 1. Jimsphere Temperature Sensor (NAS8-20588) The Jimsphere temperature s e n s o r peogram i s on schedule. P r e p a r a t i o n s a r e being made t o f i e l d t e s t the s e n s o r a t Wallops I s l a n d , V i r g i n i a , d u r i n g t h e f i r s t p a r t of September 1968. Some m o d i f i c a t i o n s have been made t o t h e e l e c t r o n i c package of t h e s e n s o r t o o b t a i n a more s t a b l e o u t p u t s i g n a l and t o reduce t h e weight of t h e balloon-borne s y s tem. An a r t i c l e on t h e temperature s e n s o r and t h e l a s t f i e l d t e s t s made a t Cape Kennedy has been a c c e p t e d by t h e J o u r n a l of Applied Meteorology, s u b j e c t t o some c o r r e c t i o n s being made i n t h e a r t i c l e . The a r t i c l e should be published i n t h e near f u t u r e . 2. Toxic Fuel D i f f u s i o n F o r e c a s t Handbook N e g o t i a t i o n s a r e i n p r o g r e s s on t h e proposed c o n t r a c t under DCN1-8-75-00103 e n t i t l e d , "Development of Toxic Fuel D i f f u s i o n F o r e c a s t Handbook." This s t u d y w i l l use s e v e r a l s o u r c e s of m e t e o r o l o g i c a l d a t a from t h e Cape Kennedy a r e a t o develop a n atmospheric d i f f u s i o n model which can e f f e c t i v e l y p r e d i c t down-wind c o n c e n t r a t i o n s of gaseous exhaust m a t e r i a l s r e l e a s e d d u r i n g a normal launch o r due t o a c o n f l a g r a tion. 3. Jimsphere Turbulence Program The Jimsphere program being performed a t Wallops I s l a n d , V i r g i n i a , is c o n t i n u i n g t o be used t o s u p p o r t t h e l a s e r r a d a r l a t m o s p h e r i c t u r b u l e n c e d e t e c t i o n program being conducted by D r . J . D. Lawrence, Jr., and M r . Steward O c h e l t r e e , of LRC. The LRC p e r s o n n e l have i n d i c a t e d t h a t t h e Jimsphere wind d a t a a r e of g r e a t v a l u e t o them i n t h e i r i n v e s t i g a t i o n of atmospheric t u r b u l e n c e . The Jimsphere d a t a w i l l be used t o provide a n i n d i c a t i o n of p o s s i b l e t u r b u l e n t r e g i o n s of t h e atmosphere. The d a t a from t h e s e r e g i o n s w i l l t h e n be c o r r e l a t e d w i t h survey a i r c r a f t response d a t a and l a s e r r a d a r r e t u r n s . D r . Lawrence and M r . O r c h e l t r e e p l a n t o v i s i t MSFC/R-AERO-Y p o s s i b l y i n August 1968 t o d i s c u s s t h e program. 4. Automatic Data Process f o r NASA's M e t e o r o l o g i c a l Tower Plans a r e being made t o a c q u i r e a n a u t o m a t i c d a t a p r o c e s s o r f o r NASA'S 150 meter m e t e o r o l o g i c a l tower. The p r o c e s s o r w i l l e l i m i n a t e t h e need t o reduce t h e m e t e o r o l o g i c a l d a t a by manual means. The manual r e d u c t i o n is now being done under a c r o s s s e r v i c e c o n t r a c t w i t h t h e N a t i o n a l Weather Records Center of A s h v i l l e , North C a r o l i n a . �C. T e r r e s t r i a l Environment Branch 1. A r e p o r t , "Frequency D i s t r i b u t i o n of S o l a r R a d i a t i o n a t A p a l a c h i c o l a , F l o r i d a , and Santa Maria, C a l i f o r n i a , " by Glenn E. Daniels has been prepared f o r p u b l i c a t i o n i n t h e n e x t Research Review. 2. A r e p o r t , " T e r r e s t r i a l Environment ( C l i m a t i c ) C r i t e r i a Guidelines f o r Use i n Space Vehicle Development, 1968 Revision," by Glenn E. D a n i e l s , e t a l . , i s being published. 3. Chrysler - Heating - In-House The problem of c o n s t r u c t i n g r e a l i s t i c thermodynamic atmosp h e r i c models s u i t a b l e f o r e s t a b l i s h i n g maximum and minimum d e s i g n and o p e r a t i o n a l c o n d i t i o n s f o r S a t u r n Launch Vehicles was d i s c u s s e d w i t h Chrysler C o r p o r a t i o n Space D i v i s i o n r e p r e s e n t a t i v e s d u r i n g a meeting a t MSFC on June 25, 1968. The p r e s e n t r e f e r e n c e atmospheres a r e s u i t a b l e f o r nominal c o n d i t i o n s , b u t t h e r e i s no "standard" atmosphere f o r maximum and minimum c o n d i t i o n s . For example, t h e r e i s no s t a n d a r d r e a l i s t i c atmosphere a v a i l a b l e f o r maximum aerodynamic h e a t i n g a n a l y s e s . A 1 though t h e C h r y s l e r r e p r e s e n t a t i v e s a t t h e meeting i n d i c a t e d t h a t t h i s work could be done w i t h i n t h e p r e s e n t c o n t r a c t , i t now a p p e a r s t h a t a s p e c i a l s t u d y may be r e q u i r e d . 4. World-Wide Cloud Cover (In-House) O r i g i n a l l y , p r o b a b i l i t y d i s t r i b u t i o n s of world-wide cloud cover were prepared f o r a r e a s approximately 60 NM i n diameter w i t h cond i t i o n a l d i s t r i b u t i o n s r e p r e s e n t i n g s p a t i a l and temporal cloud condit i o n a l i t y 200 NM away and 24 hours l a t e r . By means of computer programs completed d u r i n g June and J u l y , i t i s now p o s s i b l e t o (a) s c a l e t h e cloud c o n d i t i o n a l i t y f o r times and d i s t a n c e s o t h e r than 24 hours and 200 NM, (b) ad j us t t h e s t a t is t i c s f o r d i u r n a l changes, and (c) s c a l e t h e p r o b a b i l i t y and c o n d i t i o n a l p r o b a b i l i t y d i s t r i b u t i o n s f o r enlarged a r e a s i z e s . Memos R-AERO-YT-44-68 and R - A E R O - Y T - ~ ~ - concerned ~~, with earth-viewing a n a l y s i s over t h e U. S. f o r n a t u r a l r e s o u r c e s experiments, were d i s t r i b u t e d . �5. A c o u s t i c Wind P r o f i l e Mapping F a c i l i t y No d a t a were recorded t h i s p e r i o d by t h e A c o u s t i c a l Wind P r o f i l e Mapping F a c i l i t y a t Cape Kennedy because t h e f a c i l i t y ' s c a b l e system w a s b e i n g r e f u r b i s h e d . New c a b l e s , b o t h messenger and i n s t r u m e n t a t i o n , were shipped t o t h e Cape f o r i n s t a l l a t i o n by Pan American personnel. This r e f u r b i s h m e n t is scheduled t o be completed and operat i o n a l f o r t h e SA-205 launch. Wind s c r e e n s were purchased and w i l l be used f o r t h e SA-205 launch. These s c r e e n s a r e designed t o reduce wind n o i s e , and p e r m i t e a s i e r d e f i n i n g of r o c k e t exhaust n o i s e i n d a t a r e d u c t i o n . 6. NWRC An i n v e s t i g a t i o n of t h e azimuth v a r i a b i l i t y of t h e Cape Kennedy h o u r l y peak winds was begun. This s t u d y i s i n s u p p o r t of t h e r i s k l e v e l s a s s i g n e d t o t h e launch v e h i c l e c r i t i c a l wind l i m i t s . 7. U n i v e r s i t y of Georgia - C o n t r a c t NAS8-11175 The f o u r t e c h n i c a l r e p o r t s l i s t e d below were produced by t h e U n i v e r s i t y of Georgia d u r i n g June and July: a. b 8. . "Areas Under t h e Pearson Type I11 Curve." " P r o b a b i l i t i e s of Sequences of Favorable and Unfavora b l e Launching I n t e r v a l s a t Cape Kennedy." ." c. " C u r t a i l e d A t t r i b u t e Sampling d. "The Use of Second-Order Markov Chains i n E s t i m a t i n g P r o b a b i l i t i e s of Sequences of Favorable and Unfavora b l e Days f o r Launching Space Vehicles." Lockheed Support C o n t r a c t The launch p r o b a b i l i t y program which p r e v i o u s l y had cons i d e r e d ground winds, max q r e g i o n winds, and a d v e r s e w e a t h e r has been modified t o t a k e i n t o a c c o u n t t h e near-pad a b o r t c o n s t r a i n t f o r AS-205. A r e p o r t f o r AS-205 launch p r o b a b i l i t i e s should be ready f o r p u b l i c a t i o n i n August. Work i s c o n t i n u i n g on t h e a n a l y t i c a l s t u d y of t h e Cape Kennedy low l e v e l winds (0-2 km). The f i r s t s t e p w i l l be t o compare t h e l i n e a r two-dimensional t h e o r y w i t h r e c e n t s t a t i s t i c a l r e s u l t s . As work p r o g r e s s e s , i t i s a n t i c i p a t e d that more g e n e r a l a n a l y t i c a l models and a n o n l i n e a r numerical model w i l l be developed and t e s t e d . �A r e p o r t e n t i t l e d , "The Theory of Exceedances," was cornpleted during t h i s period. I n t h i s study, the p r o b a b i l i t y t h a t the mth l a r g e s t of t h e p a s t L o b s e r v a t i o n s w i l l be exceeded k times i n N f u t u r e t r i a l s i s d e r i v e d . The expected number of exceedances and t h e v a r i a n c e a r e a l s o found. An i n t e r p o l a t i v e scheme i s p r e s e n t e d f o r d e f i n i n g p r o b a b i l i t i e s a s s o c i a t e d w i t h v a l u e s n o t a c t u a l l y observed. This document w i l l be published a s a NASA c o n t r a c t o r r e p o r t . D. Space Environment Branch 1. A c o u s t i c G r a v i t y Wave Study The 1,000 hours, p l u s , of n i n e frequency d o p p l e r d a t a has been reduced and i s c u r r e n t l y undergoing p r e l i m i n a r y a n a l y s i s t o i d e n t i f y i o n o s p h e r i c d i s t u r b a n c e s caused by s t a t i c t e s t f i r i n g s of r o c k e t b o o s t e r s and thunderstorms. Thus f a r , t h e p i c t u r e remains u n c l e a r as t o t h e propag a t i o n of a c o u s t i c waves t o i o n o s p h e r i c h e i g h t s . There i s some i n d i c a t i o n that t h e a c o u s t i c waves may, on some days, be r e f l e c t e d by c r i t i c a l l a y e r b a r o c l i n i c i n s t a b i l i t y caused by mesospheric winds. It i s becoming a p p a r e n t t h a t f u r t h e r a n a l y s i s must i n c l u d e t h e e f f e c t s of i n t e r v e n i n g winds. 2. Thermal Conduction i n t h e Ionosphere A s e r i e s of e q u a t i o n s i s being programmed through which t h e thermal h e a t i n g of t h e upper atmosphere may b e d e r i v e d . The h e a t ing mechanisms b e i n g considered a r e thermal conduction by temperature g r a d i e n t s , e l a s t i c c o l l i s i o n s , r o t a t i o n a l and v i b r a t i o n a l h e a t i n g , and f i n e s t r u c t u r e e x c i t a t i o n through i n e l a s t i c c o l l i s i o n s . The d a t a o b t a i n e d from t h e r e c e n t thermospheric probe s h o t s w i l l be used t o c a l c u l a t e t h e a c t u a l h e a t i n g curve which i n t u r n w i l l b e compared w i t h t h e t h e o r e t i c a l models. 3. AFTAC/ITT Phase P a t h Sound Unit The AFTAC/ITT phase p a t h sounder u n i t w i l l be shipped t o Marshall Space F l i g h t Center on GBL. The instrument w i l l be l o c a t e d a t a s i t e c u r r e n t l y b e i n g used by t h e NASAIMSFC C-4 ionosonde. Arrangements w i l l then be made t o have two e n g i n e e r s from ITT come t o H u n t s v i l l e f o r two weeks t o b r i n g t h e i n s t r u m e n t t o o p e r a t i o n a l s t a t u s and t o t r a i n a l o c a l crew of e n g i n e e r s i n t h e o p e r a t i o n and maintenance of t h e s t e p p e d frequency phase p a t h sounder. This procedure should provide t h e maximum i n e f f e c t i v e o p e r a t i o n a t a minimum of c o s t . The l o c a l NASA e n g i n e e r t o have charge of t h e maintenance and o p e r a t i o n of t h e sounder u n i t is M r . Robert Turner, R-AERO-YT. �4. S t u d i e s Related t o t h e S t r u c t u r e and V a r i a b i l i t y of t h e Upper Atmosphere S t u d i e s r e l a t e d t o t h e s t r u c t u r e and v a r i a b i l i t y of t h e upper atmosphere have been d i r e c t e d t o (1) a d e t a i l e d comparison of atmospheric d e n s i t y that i s o b t a i n e d from s a t e l l i t e drag d a t a t o d e n s i t y of e x i s t i n g model atmospheres, (2) t h e c o n t i n u a t i o n of t h e a n a l y s i s of s i x MSFC thermosphere probe d a t a , and ( 3 ) t h e e s t a b l i s h m e n t of environment c r i t e r i a f o r s e v e r a l ATM e n g i n e e r i n g s t u d i e s . 5. S a t e l l i t e Drag Determined Density Study A d e t a i l e d a n a l y s i s of d e n s i t i e s o b t a i n e d from s a t e l l i t e drag d a t a has been i n i t i a t e d t o provide i n f o r m a t i o n needed f o r t h e r e f i n e m e n t of t h e MSFC Modified J a c c h i a Model Atmosphere (1967). Prel i m i n a r y r e s u l t s of t h i s a n a l y s i s have provided a technique f o r d i r e c t l y r e l a t i n g e x o s p h e r i c temperature t o atmospheric d e n s i t y . This t e c h n i q u e , which i s n o t l i m i t e d by t h e c o n s t a n t boundary c o n d i t i o n s i n h e r e n t i n t h e c u r r e n t MSFC model, w i l l be used i n developing a model atmosphere that i s i n agreement w i t h drag determined d e n s i t i e s a t a l l a l t i t u d e s . Low a l t i t u d e A i r Force s a t e l l i t e d a t a w i l l provide r e f i n e m e n t s t o t h e lower p o r t i o n of t h e MSFC model (150 t o 200 km) which w i l l p r o v i d e more a c c u r a t e i n p u t s t o MSFC s a t e l l i t e l i f e t i m e s t u d i e s . 6. Thermosphere Probe Study Diurnal v a r i a t i o n s of t h e thermosphere have been provided b y s t u d y of s i x MSFC thermosphere probe d a t a . Numerical techniques a p p l i e d t o t h e d a t a have r e f i n e d t h e d a t a and enabled a g r e a t e r amount t o be used. Numerical i n t e g r a t i o n of t h e s e d a t a , coupled w i t h known s a t e l l i t e d a t a , v i a a d i f f u s i o n technique has g i v e n i n s i g h t i n t o t h e lower thermosphere v a r i a b i l i t y . I n a d d i t i o n , a second i n t e g r a t i o n technique i n v o l v i n g a more complex d i f f u s i o n e q u a t i o n i s b e i n g t e s t e d . Comparison of t h e r e s u l t s of t h e two techniques should y i e l d f u r t h e r knowledge i n t h i s low thermospheric r e g i o n . A f i r s t r u n look a t t h e u t i l i z a t i o n of t h e h e a t e q u a t i o n ( a n o t h e r t h e o r e t i c a l approach) coupled w i t h t h e d a t a , has been made, and the groundwork has been f o r m u l a t e d f o r i t s a p p l i c a t i o n t o t h i s r e g i o n of t h e atmosphere. 7. ATM Environment C r i t e r i a S p e c i f i c environment c r i t e r i a i n p u t s f o r s e v e r a l ATM e n g i n e e r i n g s t u d i e s have been developed u s i n g t h e MSFC Modified Jacchia Model Atmosphere (1967). These i n p u t s c o n s i s t of (1) p r e d i c t i o n s of t h e time-dens i t y p r o f i l e s t o which t h e ATM w i l l be exposed, ( 2 ) l a t i tude v e r s u s l o n g i t u d e c r o s s s e c t i o n s of d e n s i t y f o r t h e approximate U P - 2 / U P - 1 launch d a t e , and (3) a n e s t i m a t e of t h e range of d e n s i t y t o which t h e A'IM w i l l be exposed. �I n e s t a b 1 i s h i n g ATM environment c r i t e r i a , p r e d i c t e d 81-day mean s o l a r f l u x v a l u e s a r e o b t a i n e d from t h e MSFC S o l a r Cycle P r e d i c t i o n Program. A s t a t i s t i c a l s t u d y has been i n i t i a t e d f o r t h e b e s t e s t i m a t e of t h e d a i l y s o l a r f l u x v a l u e t h a t should be a s s o c i a t e d w i t h t h e p r e d i c t e d 81-day mean v a l u e . A f i n a l d r a f t of t h e 1968 r e v i s i o n of NASA TM X-53521, "Space Environment C r i t e r i a G u i d e l i n e s f o r Use i n Space Vehicle Development 1967 Revision," has been completed and reviewed by t h e Space Sciences Laboratory. �V . AEROPHYS ICS DIVISION A. Mechanical Design Off i c e 1. Request has been made by -AE f o r t h e d e s i g n of models,probe s u p p o r t and t r a v e r s i n g equipment f o r j e t plume impingement t e s t s i n t h e IBFF. I n i t i a l t e s t s w i l l involve p r e s s u r e measurements. Following t e s t s w i l l i n c l u d e b o t h f o r c e and p r e s s u r e measurements. 2 . The following i s a p a r t i a l l i s t of a d d i t i o n a l p r o j e c t s and their current status. M o d i f i c a t i o n of Model 327, 14 WT (AU) Design P r e s s u r e Model, Water Tower Study , UAH (AU) Design M o d i f i c a t i o n of Pneumatic Work Bench (-A) Design X-Y-Z P o s i t i o n i n g Device, LDC (-LIE) Design Redesign of F l a t P l a t e Protuberance Design Heat T r a n s f e r Model L. R. C. 4' WT (AT) Design Heated Plenum Chamber LDWT (-AE) Design S a t u r n V Force Models, Bent C e n t e r i n g , 14" WT (-AD) Design C a l i b r a t i o n Equipment, H. R. E . Des ign/ Fabrication (-AE) 5 Component Micro Force Balance L. D . C. (-AE) Drafting 4" L. D. P r e s s u r e Model, L. T. V. WT (AD) Drafting Sapphire Windows, S. T. S . , 14" WT X-Beam (AE) Fabrication Nozzle and Plenum, Laser Beam (-A) Fabrication Redesign Survey Probe, 14" WT (AE) Fabrication Low Volume Diaphragm C u t t e r , IBFF (-AE) Fabrication V a r i a b l e P o r o s i t y Transonic T e s t S e c t i o n , 18.75% P i l o t Model, H. R. E. (-AE) Fabrication �V a r i a b l e P o r o s i t y Transonic T e s t S e c t i o n , H. R . E . (-AE) Fabrication Tracer M a t e r i a l I n j e c t o r , X-Beam, S. T. S. 14" WT (-A) Fabrication Strap-on Force Model, 14" WT (-AD) Delivered S a t u r n V P r e s s Model (No. 424), 14" WT (-AD) De 1i v e r ed B. Aerodynamic Des i g n Branch 1. Saturn I B a. AAP-I1 Aerodynamics S t a t i c aerodynamic c h a r a c t e r i s t i c s were d e f i n e d f o r t h e AAP-I1 v e h i c l e w i t h t h e proposed payload shroud, which has a 12'30' frustum r e p l a c i n g t h e 8O58' frustum. S t a t i c s t a b i l i t y and a x i a l f o r c e d a t a f o r c o n t r o l and t r a j e c t o r y s t u d i e s a r e d e f i n e d f o r a Mach number range from 0 t o 5 . 0 f o r a n g l e s of a t t a c k from 0' t o 10'. Distributed aerodynamic l o a d s , b o t h a x i a l and normal, were d e f i n e d f o r s t r u c t u r a l a n a l y s i s a t a n g l e s of a t t a c k of 0" t o 10' f o r t h e Mach number range from 0.8 t o 2.0. These d a t a were estimated and w i l l be updated when experimental d a t a become a v a i l a b l e . b. f o r the Saturn I B d u i t s ) . External tunnel t e s t d a t a , i n - f l i g h t venting pressures f o r the 68-42. c. S a t u r n IB/OWS S o l a r Panel Conduit P r e s s u r e s I n t e r n a l and e x t e r n a l p r e s s u r e bands have been d e f i n e d O r b i t a l Workshop v e h i c l e s o l a r panels f a i r i n g s (conp r e s s u r e bands, which were determined from MSFC 14-inch encompass a n a n g l e - o f - a t t a c k range up t o 8 d e g r e e s . An a n a l y s i s determined t h e maximum and mimimum i n t e r n a l f a i r i n g . These d a t a a r e being published i n R-AERO-AD- OWS A l t i t u d e Control System Aerodynamic loads on t h e workshop a l t i t u d e c o n t r o l system modules were determined f o r i n p u t i n t o t h e s t r u c t u r a l a n a l y s i s . The modules a r e mounted on t h e a f t s k i r t of t h e S-IVB s t a g e w i t h a 17'30' f a i r i n g extending forward on t h e tank s e c t i o n of t h e s t a g e . The e x t e r n a l p r e s s u r e s over t h e forward f a i r i n g and t h e main body of t h e module were d e f i n e d over t h e Mach range of 0.8 t o 1.95 f o r a n g l e s of a t t a c k of 0 t o 10". I n t e r n a l p r e s s u r e s f o r t h e nose f a i r i n g were a l s o d e f i n e d a s a f u n c t i o n of Mach number. Maximum s i d e load was p r e d i c t e d a s a d i s t r i b u t e d load over t h e module. These d a t a a r e being published i n a n o f f i c e memorandum, R-AERO-AD-68-42. �d. AAP-IT. S t a b i l i t y and Loads T e s t T e s t s have been scheduled i n t h e MSFC 14-inch TWT t o d e f i n e t h e s t a t i c s t a b i l i t y , a x i a l f o r c e c h a r a c t e r i s t i c s , and load d i s t r i b u t i o n s f o r t h e AAP-I1 launch v e h i c l e . The nose c o n f i g u r a t i o n of t h e v e h i c l e i s a m o d i f i c a t i o n of t h e g e n e r a l payload shape used on t h e AS-203. Two models, a .75 p e r c e n t s c a l e p r e s s u r e model of t h e upper s t a g e s e c t i o n of t h e v e h i c l e and a .55 p e r c e n t s c a l e f o r c e model of t h e t o t a l v e h i c l e c o n f i g u r a t i o n , a r e being f a b r i c a t e d f o r use i n t h e s e t e s t s . The p r e s s u r e model w i l l be t e s t e d f o r a Mach range of 0.80 t o 2.99 a t a n g l e s of a t t a c k of from -4" t o +12"; t h e f o r c e model i s t o b e i n v e s t i g a t e d a t Mach numbers ranging from 0.50 t o 4.96 i n a n a n g l e - o f - a t t a c k range of -4" t o +lo0. These t e s t s a r e t o be completed by mid-August. e. AAP D e f i n i t i o n of Plume Flow F i e l d f o r Nose Cone Ejection O f f i c e Memorandum R-AERO-AD-68-42 p r e s e n t s t h e r e s u l t s of a r e v i s e d a n a l y t i c a l a n a l y s i s d e f i n i n g t h e plume flow f i e l d e x p e r i enced by t h e payloads of t h e AAP-2 o r AAP-4 v e h i c l e s d u r i n g nose cone/ SLA e j e c t i o n . This updated a n a l y s i s , which s u p e r s e d e s R-AERO-AD-68-13, was p r e d i c a t e d by a p o s s i b l e c r i t i c a l aerodynamic load s i t u a t i o n imposed on t h e LEM of t h e AAP-4 v e h i c l e . The aerodynamic flow f i e l d i s t o be used i n con j u n c t i o n w i t h nose cone/ SLA e j e c t i o n t r a j e c t o r i e s (R-AERODCC-5-68) f o r d e f i n i t i o n of maximum aerodynamic l o a d s imposed on t h e exposed v e h i c l e payloads. 2. Saturn V a. A x i a l Force C h a r a c t e r i s t i c s The aerodynamic a x i a l f o r c e c h a r a c t e r i s t i c s have been determined f o r AS-503 and subs based on l a r g e model wind t u n n e l t e s t s and AS-502 f l i g h t b a s e p r e s s u r e measurements. These d a t a a r e p u b l i s h e d i n A comparison of t h e e f f e c t of scoop o f f i c e memorandum R-AERO-AD-68-37. removal on v e h i c l e s t a b i l i t y i s a l s o i n c l u d e d . The e f f e c t s shown a r e small. b. E f f e c t s of F71 Plume Induced Flow S e p a r a t i o n on Saturn V S t a t i c S t a b i l i t y The e f f e c t s of flow s e p a r a t i o n on t h e Apollo S a t u r n V analysis f i r s t s t a g e aerodynamics a r e p r e s e n t e d i n R - A E R O - A D - ~ ~ - ~ ~ The . r e v e a l e d a d e c r e a s e i n normal f o r c e and a forward s h i f t i n c e n t e r of These d a t a supersede t h o s e p r e s e n t e d i n NASA p r e s s u r e above Mach 3.0. TM X-53517 e n t i t l e d " S t a t i c Aerodynamics C h a r a c t e r i s t i c s of t h e ApolloS a t u r n V Vehicle" f o r power-on f l i g h t above Mach 3.0. �c. Aerodynamics of Saturn V + 5-25 Vehicle The s t a t i c aerodynamic c h a r a c t e r i s t i c s of t h e Saturn V J - 2 s v e h i c l e have been published i n o f f i c e memorandum R-Al3RO-A~-68-44. The l i n e a r aerodynamics, t o t a l and d i s t r i b u t e d , a r e presented f o r Mach The n o n l i n e a r aeronumbers of 0.9, 1.0, 1.1, 1.2, 1.46, 1.70 and 2.0. dynamics, t o t a l s and d i s t r i b u t i o n s , a r e presented f o r Mach numbers of 1.2, 1.46, 1.70 and 2.0 a t angles of a t t a c k t o 15". Axial f o r c e t o t a l s and d i s t r i b u t i o n s a r e a l s o presented. These d a t a a r e t o be used f o r preliminary s t u d i e s by t h e Boeing Company. d. - Hydrogen Venting Study Overboard venting of hydrogen i s being considered f o r t h e S-IVB s t a g e during f i r s t s t a g e f l i g h t f o r both Saturn IB and Saturn V launch v e h i c l e s . Because experimental d a t a on gas v e n t i n g i s 1imited , a n i n v e s t i g a t i o n i s being made t o a s s e s s t h e e f f e c t of v a r i o u s v e n t r a t e s Concentration l e v e l s w i l l be measured on downstream c o n c e n t r a t i o n of Hz. a t d i s t a n c e of 100 h (h = v e n t plume p e n e t r a t i o n h e i g h t ) downstream of a f l u s h c i r c u l a r v e n t p o r t a t s u p e r s o n i c Mach numbers and s c a l e d flow It is hoped t h a t t h i s i n v e s t i g a t i o n w i l l proratios (2 preset rate). v i d e a s e t of d a t a whose range i s broad enough t o cover f u t u r e H2 v e n t ing r a t e s . T e n t a t i v e plans c a l l f o r t e s t i n g i n MSFC f a c i l i t i e s during t h e next s i x months. e. Body of Revolution Viscous Cross-Flow I n v e s t i g a t i o n P r e s s u r e t e s t i n g i n t h e MSFC 14-inch TWT f a c i l i t y of t h e ogive-cylinder and o g i v e - c y l i n d e r - f r u s t u m - c y l i n d e r c o n f i g u r a t i o n has been completed. Time delays a s s o c i a t e d w i t h model i n s t a l l a t i o n and d a t a accuracy r e s u l t e d i n rescheduling t h e flow v i s u a l i z a t i o n p o r t i o n of t h i s t e s t u n t i l September. The flow v i s u a l i z a t i o n models have been flash-coated w i t h copper and then oxidized t o provide a b l a c k background f o r optimum c o n t r a s t i n r e l a t i o n t o t h e white china-clay t h a t i s used t o i d e n t i f y t h e l o c a l flow c o n d i t i o n . Longitudinal and r a d i a l l i n e s w i l l be s c r i b e d through t h i s coating i n t o t h e s t e e l model and then they w i l l be f i l l e d w i t h epoxy t o provide a white g r i d on a b l a c k background t o a s s i s t i n a c c u r a t e l y measuring changes i n s u r f a c e flow c h a r a c t e r i s t i c s . Design of t h e 4.0-inch diameter ogive-cylinder p r e s s u r e model t o be t e s t e d i n t h e LTV 4' HSWT has been completed. Delivery of t h e model plans t o f a b r i c a t i o n has been delayed, however, because of higher p r i o r i t y requirements of t h e d r a f t i n g s e c t i o n . September 1968. February 1969. A p r e - t e s t conference is scheduled w i t h LTV f o r The t e s t d a t e i s t e n t a t i v e l y scheduled f o r January- �3. General S i x t h I n t e r n a t i o n a l Symposium on R a r e f i e d Gas Dynamics M r . J o s h D. Johnson, R-AERO-ADE, a t t e n d e d t h e S i x t h I n t e r n a t i o n a l Symposium on R a r e f i e d Gas Dynamics which was h e l d a t Massachusetts I n s t i t u t e of Technology J u l y 22-26, 1968. A t t h i s symposium, approxim a t e l y 180 papers were p r e s e n t e d that d e s c r i b e d t h e o r e t i c a l and e x p e r i mental s t u d i e s t h a t have been performed r e c e n t l y i n r a r e f i e d gas dynamics A d e t a i l e d t r i p r e p o r t w i l l be d i s t r i b u t e d t o a p p r o p r i a t e people w i t h i n t h e Aero-Astrodynamics Laboratory. Experimental Aerophysics Branch C. 1. Low D e n s i t y Chamber The model n o z z l e has been f a b r i c a t e d and d e l i v e r e d f o r t h e experimental i n v e s t i g a t i o n of j e t plume impingement i n t h e Low D e n s i t y Chamber. I n i t i a l t e s t s i n measuring t h e impact p r e s s u r e of t h e C02 plume r e v e a l e d d i f f i c u l t i e s i n a l i g n i n g t h e probe and n o z z l e . Hardware r e f i n e m e n t s a r e now underway. 2. Impulse Base Flow F a c i l i t y Blockage t e s t s of t h e 18.75 p e r c e n t p i l o t High Reynolds Number equipment have been completed, and model s t a t i c p r e s s u r e measuring techniques a r e being s t u d i e d . The primary phases of t h e program ( s t a r t i n g l o a d s , blockage, and pressure-measuring t e c h n i q u e s ) have been e s s e n t i a l l y completed. Transonic t e s t i n g w i l l b e i n t e r r u p t e d f o r a n experimental program i n s u p p o r t of AAP/S-IVB Workshop plume impingement studies . The workshop plume impingement program, scheduled t o b e g i n August 12, 1968, w i l l b e d i v i d e d i n t o 6 p a r t s . 1. Plume s t u d y (Phase I). 2. Plume impingement p r e s s u r e on a f l a t p l a t e . 3. Plume impingement p r e s s u r e on a ' c y l i n d e r . 4. Plume impingement f o r c e s on a f l a t p l a t e . 5. Plume s t u d y (Phase 11). 6. AAPIWorkshop plume impingement f o r c e s . �(b) An i n v e s t i g a t i o n f o r R-AERO-AU t o determine flow s e p a r a t i o n c h a r a c t e r i s t i c s on s e v e r a l cone c y l i n d e r - f l a r e models. This t e s t i s t h e f i r s t phase of a shock-induced s e p a r a t i o n s t u d y t o be p e r formed i n t h e TWT on S a t u r n c o n f i g u r a t i o n s . Visual d a t a were recorded using o i l - f l o w , c h i n a - c l a y , and shadowgraph flow v i s u a l i z a t i o n t e c h n i q u e s . T o t a l runs: 64. ( c ) A p r e l i m i n a r y check was made on p o s s i b l e problems a s s o c i a t e d w i t h a n N2-cooled cone model. The model r e p r e s e n t s a p o r t i o n of t h e i n v e s t i g a t i o n t o be conducted by C h r y s l e r Space D i v i s i o n f o r R-AERO-AU, "The E v a l u a t i o n of t h e Acoustic Sources of Background Noise T o t a l runs: 9. i n Wind Tunnels ." (d) An i n v e s t i g a t i o n f o r R-AERO-AD of t h e e f f e c t of boundary l a y e r on f i n e f f i c i e n c y of a S a t u r n I B Fin. T o t a l r u n s : 41. The t u n n e l has experienced numerous d e l a y s i n r e c e i v i n g models f o r t e s t ing, r e s u l t i n g i n s h i f t e d schedules and t u n n e l down-time. The m u f f l e r has been i n s t a l l e d on t h e t u n n e l dump v a l v e a f t e r a n eight-month d e l a y . The n o i s e r e d u c t i o n has e l i m i n a t e d t h e previous h e a r i n g hazard. Tunnel-wall a d j u s t i n g jacks were i n s t a l l e d d u r i n g t h i s p e r i o d t o e n a b l e w a l l a n g l e s t o be s e t e x t e r n a l l y w i t h o u t opening t h e t u n n e l . This should r e s u l t i n a more e f f i c i e n t system and i n c r e a s e d run r a t e . 6. Instrumentation I n s t r u m e n t a t i o n was provided and o p e r a t e d f o r t h e R-AERO-AU protuberance t e s t conducted a t t h e AEDC 1 6 - ~ o o tTransonic P r o p u l s i o n Wind Tunnel. The 122-channel 20KHZ r e c o r d i n g system was used f o r t h e t e s t . It was a l s o provided, a l o n g w i t h a c o u s t i c t r a n s d u c e r s and o t h e r equipment, f o r a Lockheed-Sunnyvale a c o u s t i c t e s t i n v o l v i n g t h e upper s t a g e s of t h e T i t a n . Technical and o p e r a t i n g a s s i s t a n c e was a l s o provided f o r t h e Lockheed t e s t . Magnetic t a p e d u p l i c a t i n g o r "dubbing" has been completed f o r t h e above t e s t s , a s w e l l a s f o r a n e a r l i e r 4 p e r c e n t S a t u r n V s u p e r s o n i c t e s t conducted a t t h e same f a c i l i t y . The dubbed r e e l s of t a p e t o t a l e d 132, i n c l u d i n g copies made f o r Lockheed of t h e i r own t a p e s . 7. Data Reduction Besides t h e r o u t i n e f a c i l i t y t e s t d a t a , t h e f o r c e t e s t from t h e p i l o t HRE from t h e IBFF were reduced and p l o t t e d . A data s p e c i a l program was w r i t t e n f o r t h e s e d a t a , u s i n g t h e o n - l i n e p l o t t e r . This was our f i r s t p r o d u c t i o n a p p l i c a t i o n of t h e p l o t t e r , and i t was extremely u s e f u l . �D. Thermal Environment Branch 1. High Angle of Attack Heating T e s t The t e s t runs t o be made i n t h e U n i t a r y P l a n Tunnel have been completed and t h e model (75 p e r c e n t S a t u r n I B ) moved t o t h e Mach 6 tunnel f o r t h e f i n a l phase. The d a t a a r e now being reduced, and evaluat i o n w i l l begin s h o r t l y . Runs were completed f o r Mach numbers of 2.5 and 3.71 and Reynolds numbers of 1 . 5 x l o 6 and 3.5 x lo6. 2. R a d i a t i o n View F a c t o r Program Work was continued toward checking o u t t h e computer program. S e v e r a l coding changes were made, reducing t h e r u n time by approximately 20 p e r c e n t . Documentation of t h e theory and program was a l s o continued, and s e v e r a l s e c t i o n s of t h e r e p o r t were r e c e i v e d from t h e c o n t r a c t o r f o r review. E. Unsteady Gas Dynamics Branch 1. S a t u r n I B Ground Winds P r e l i m i n a r y s t u d i e s f o r modifying a p r e v i o u s l y c o n s t r u c t e d S a t u r n I B a e r o e l a s t i c wind t u n n e l model t o s i m u l a t e t h e AAP-2 and AAP-4 c o n f i g u r a t i o n s f o r ground wind s t u d i e s have been completed. S a t u r n I B wind t u n n e l t e s t d a t a w i l l b e f u r t h e r reduced t o b e t t e r p r e d i c t f u l l - s c a l e S a t u r n I B bending moments v e r s u s azimuth a n g l e . 2. S a t u r n V Ground Winds F a b r i c a t i o n of a n Uprated S a t u r n V ground winds a e r o e l a s t i c model has been completed by Atkins and M e r r i l l , I n c . Dynamic q u a l i f i c a t i o n t e s t s were r e c e n t l y conducted on t h e model a t t h e company s i t e . The model and i t s e l e c t r o n i c damper system should be shipped t o MSFC shortly. A s t u d y f o r determining t h e second mode e f f e c t s on ground wind loadings of t h e S a t u r n V f u e l e d weight c o n d i t i o n i s s t i l l i n progress. P r e l i m i n a r y p r e d i c t i o n s of s t a t i c and r e s u l t a n t bending moments v e r s u s azimuth a n g l e f o r t h e S a t u r n V v e h i c l e w i t h t h e LUT and MSS c o n f i g u r a t i o n f o r t h e c a s e where t h e damper i s a t t a c h e d were published on June 3 , 1968. �P r e d i c t i o n s of S a t u r n V, AS-503 bending moments f o r a l l azimuth a n g l e s u s i n g uprated dynamic c h a r a c t e r i s t i c s f o r t h e manned miss i o n a r e being made f o r a l l weight c o n f i g u r a t i o n s w i t h and w i t h o u t t h e MSS and a l s o w i t h and w i t h o u t t h e damper a t t a c h e d . These p r e d i c t i o n s , which w i l l s u p e r s e d e t h e p r e l i m i n a r y p r e d i c t i o n s mentioned above, should be published soon. Work has a l s o been i n i t i a t e d t o s t a t i s t i c a l l y a n a l y z e e x i s t ing S a t u r n V ground wind t e s t d a t a u s i n g t h e Lockheed-developed s t a t i s t i c a l a n a l y s e s program. 3. I n f 1i g h t Acoustics a . The ALOTS f i l m taken from AS-502 has been analyzed f o r i n v e s t i g a t i o n of t h e r e c i r c u l a t e d flow c o n d i t i o n s on t h e S-IC and S - I 1 s t a g e s . The amplitude and s p e c t r a l i n f o r m a t i o n d e r i v e d from l i m i t e d a p p l i c a b l e wind t u n n e l d a t a and from t h e f i l m enabled t h e e s t i m a t i o n of t h e f l u c t u a t i n g p r e s s u r e s on t h e v e h i c l e v e r s u s f l i g h t time. ~ e s u l t ing v e h i c l e l o a d s were d e r i v e d from a n a l y s i s of t h e s e p a r a t e d flow phenomenon observed d u r i n g f l i g h t and have been r e p o r t e d i n R-AERO-AU memorandum. Concern f o r t h e s e l o a d s prompted management t o o r d e r a n i n v e s t i g a t i o n of t h e p o s s i b i l i t y of implementing a measuring program on AS-503 o r subsequent f l i g h t t o e s t a b l i s h a n a d d u r a t e d e s c r i p t i o n of t h e phenomenon and t h e r e s u l t i n g l o a d s . The demands of such a program on AS-503 a r e b e i n g met i n r e g a r d t o t r a n s d u c e r a d a p t a t i o n f o r t h e temperat u r e and frequency o p e r a t i o n a l l i m i t s r e q u i r e d . R-ASTR i s a l s o s t u d y i n g t h e channel a v a i l a b i l i t i e s a n d / o r a1t e r n a t i v e s t o a c q u i r e d a t a f o r t h i s area. b. Comp. Lab. has r e c e n t l y r e p o r t e d that o v e r a l l time h i s t o r y i n £ o n n a t i o n i s now a v a i l a b l e ( f o r continuous s i g n a l a n a l y s i s ) from t h e a c o u s t i c a n a l y z e r . None of t h e OASPL time h i s t o r y d a t a has been provided f o r AS-501 o r 502. A s h o r t e r a v e r a g i n g time i s now b e i n g r e q u e s t e d f o r more a c c u r a t e p r e s e n t a t i o n of c e r t a i n d a t a t y p e s . Output from Comp. i s expected i n s e v e r a l weeks. c. A d d i t i o n a l f l u c t u a t i n g p r e s s u r e d a t a have been r e c e i v e d from Baganoff and A s s o c i a t e s . These d a t a a r e being prepared i n memorandum form and w i l l b e forwarded t o R-P&VE-S by t h e f i r s t week i n August. The v o l ume of c r o s s power s p e c t r a l d e n s i t y i n f o r m a t i o n t o be forwarded i s v e r y l a r g e . This r e p r e s e n t s f a i r l y comprehensive, p r e l i m i n a r y r e s u l t s f o r t h e z e r o a n g l e of a t t a c k c o n d i t i o n . d. A d d i t i o n a l c o n t r a c t work f o r t h e "Development of F u l l I n - F l i g h t A c o u s t i c Design C r i t e r i a S c a l i n g E f f e c t s " i s b e i n g i n i t i a t e d . Data from Ames f o u r p e r c e n t S a t u r n V, PSTL-1 and PSTL-2 wind t u n n e l c o n d i t i o n s , and f l i g h t w i l l be used. A l l o t h e r d a t a a v a i l a b l e i n t h e l i t e r a t u r e w i l l be included. �e . Requests f o r e s t i m a t e s of i n f l i g h t environments f o r f o u r s p e c i f i c , modified launch c o n f i g u r a t i o n s have been r e c e i v e d . These conf i g u r a t i o n s involve t h e use of t h e S a t u r n V (J-2s c o n f i g u r a t i o n ) v e h i c l e and t h e S a t u r n I B b o o s t e r w i t h a Centaur upper 9 t a g e . The environmental e s t i m a t e s f o r t h e s e c o n f i g u r a t i o n s have been made and forwarded t o t h e original requestors. f . A wind t u n n e l program has been conducted i n t h e AEDC 1 6 - f o o t t r a n s o n i c t u n n e l t o provide experimental i n f o r m a t i o n t o h e l p d e r i v e methods by which f l u c t u a t i n g a i r l o a d s can a c c u r a t e l y be p r e d i c t e d on launch v e h i c l e s . This wind tunnel t e s t program i s i n s u p p o r t of a c o n t r a c t w i t h Wyle L a b o r a t o r i e s , H u n t s v i l l e , e n t i t l e d "Environment Around Protuberances Submerged i n a Boundary Layer." The wind t u n n e l t e s t s s t a r t e d on May 23 and l a s t e d through June 4, 1968. S t a t i c and f l u c t u a t i n g p r e s s u r e s were measured i n t h e v i c i n i t y of g e n e r a l i z e d protuberance mounted on a s p l i t t e r p l a t e f o r a Mach number range of M = 0.6 t o M = 1.45. O i l flow s t u d i e s were conducted a l s o . A j o i n t MSFCIAir Force wind t u n n e l t e s t program was conducted from June 4 u n t i l t h e l a s t week i n June. This t e s t program cons i s ted of s e v e r a l b i c o n i c nose c o n f i g u r a t i o n s which w i l l provide a bas i s f o r a n a l y s e s of t h e c r o s s c o r r e l a t i o n c h a r a c t e r i s t i c s (necessary f o r d e s i g n c r i t e r i a ) of t h e i n f l i g h t f l u c t u a t i n g p r e s s u r e environment f o r v a r i o u s AAP m i s s i o n s . A v e r y s m a l l amount of d a t a from t h e s e t e s t s has been reduced i n t h e form of a few OASPL's ( o v e r a l l sound p r e s s u r e l e v e l s ) and a few 113-octave s p e c t r a p r i m a r i l y f o r d a t i n g and e d i t i n g , and f o r g u i d e l i n e s f o r planning t h e n e c e s s a r y c r o s s c o r r e l a t i o n d a t a r e d u c t i o n , which is a much more time-consuming p r o c e s s . C a r e f u l planning i s r e q u i r e d t o a c h i e v e t h e optimum amount of d e s i g n i n f o r m a t i o n from t h e tremendous amount of p o s s i b l e d a t a t o be reduced. The A i r Force, v i a Lockheed, paid f o r t h e i n i t i a l d a t a r e d u c t i o n . 4. Launch S i t e Acoustics a. The papers f o r t h e conference on n o i s e a l l e v i a t i o n f o r s u b s o n i c a i r c r a f t , t o be h e l d a t Langley Research Center i n October 1968, , a r e being prepared. The a b s t r a c t s f o r a l l t h e c e n t e r ' s p r e s e n t a t i o n s have been provided f o r t h e MSFC personnel who a r e involved and i n t e r e s t e d i n t h i s program. An a d d i t i o n a l paper i s being p r e s e n t e d on t h e "Typical Response of t h e Human Auditory System" by J . H. Jones. b. A program f o r t h e d e t e r m i n a t i o n of excess ground a t t e n u a t i o n i n t h e p r o p a g a t i o n of a c o u s t i c energy has been developed and i s working a t Lockheed f o r some 60 t e s t s (100,000 d a t a p o i n t s ) of l a r g e b o o s t e r s o r r o c k e t engines a t MSFC from 1965 t o 1967. The m e t e o r o l o g i c a l d a t a were t o be used i n t h i s program t o b e s t e v a l u a t e t h e d a t a a c q u i s i t i o n �c o n d i t i o n s and a l s o t o look f o r t h e p o s s i b l e i n f l u e n c e due t o s e v e r a l parameter v a r i a t i o n s of t h e ground impedance f o r t h i s s t u d y . However, t h e meteorologYca1 d a t a r e q u e s t e d from R-AERO-YT on May 28, 1968, a r e n o t y e t a v a i l a b l e f o r use because of Comp. Lab. problems. These problems may impact t h e t o t a l scope of t h e r e s u l t s f o r t h e p r e s e n t a t i o n t o t h e conference on Subsonic A i r c r a f t Noise A l l e v i a t i o n a t Langley i n October 1968. c . The A c o u s t i c Model T e s t F a c i l i t y (AMTF) a t T e s t Lab. has been e f f e c t i v e l y s h u t down because of t h e manpower s h o r t a g e f o r o p e r a t i o n a l use. The S a t u r n V model p r e s s u r e amplitude and phase i n f o r m a t i o n has thus been delayed and i s n o t of s u f f i c i e n t p r i o r i t y i n T e s t Lab. t o b r i n g a b o u t any t e s t i n g i n t h e immediate f u t u r e . Other s i m i l a r program have l i k e w i s e ceased. d. I n i t i a l p r e d i c t i o n of t h e A c o u s t i c Environment f o r t h e Nuclear Ground T e s t Module has been completed. These environmental e s t i m a t e s were r e l e a s e d i n memorandum form. A c o u s t i c environments f o r t h e J-2s n u c l e a r engine c o n f i g u r a t i o n s a l s o have been completed and have been s u p p l i e d i n a r e c e n t memorandum t o P&VE-SV and o t h e r s . 5. Panel F l u t t e r a. I n i t i a l computer runs of t h e low a s p e c t r a t i o panel f l u t t e r problem have been completed f o r s l e n d e r panels w i t h pinnededge c o n d i t i o n s . These v e r y s u c c e s s f u l runs showed t h a t t h e branch l i n e s i n t h e K-S p l a n e contained e i t h e r z e r o o r two f l u t t e r p o i n t s . The n e x t s t e p i s t o s e a r c h i n t h e thickness/dynamic-pressure p l a n e f o r t h e c r i t i c a l f l u t t e r boundaries. b. A n a l y s i s of t h e two-dimensional wavy-wall d a t a has resumed a f t e r some d e l a y due t o c o o r d i n a t i o n problems between MSFC, ARC and ARAP. Under t h e c u r r e n t agreement, MSFC w i l l provide p r e s s u r e d i s t r i b u t i o n s on t h e w a l l o b t a i n e d by using l i n e a r i z e d p o t e n t i a l t h e o r y a s w e l l a s shock wave p a t t e r n s and c o n s t a n t Mach l i n e p a t t e r n s o b t a i n e d by t h e n o n l i n e a r m e t h o d - o f - c h a r a c t e r i s t i c s s o l u t i o n . I n a d d i t i o n , a d d i t i o n a l boundary l a y e r i n f o r m a t i o n i s t o be o b t a i n e d over a f l a t w a l l i n t h e lower Mach number regime. c . NASA c o n t r a c t NAS8-21250 e n t i t l e d "High Amplitude S a t u r n S-IVB Panel F l u t t e r Tests" was i n i t i a t e d June 28, 1968, between NASA, MSFC and t h e McDonnel-Douglas C o r p o r a t i o n of S t . Louis, M i s s o u r i . This c o n t r a c t c a l l s f o r t h e McDonnell-Douglas C o r p o r a t i o n t o d e s i g n , conduct, and a n a l y z e t h e r e s u l t s of a panel f l u t t e r t e s t t o be conducted i n t h e Ames 2 x 2 f o o t t r a n s o n i c wind t u n n e l . The primary purpose of t h i s t e s t i s t o a s s e s s t h e magnitude of f l u t t e r , w i t h r e s p e c t t o dynamic p r e s s u r e d e f i c i e n c y , on panels s i m i l a r t o t h o s e found on t h e forward s k i r t of t h e S a t u r n S-IVB s t a g e . �A t t h e p r e s e n t time, a l l p r e p a r a t i o n s a r e proceeding on s c h e d u l e , l e a d i n g t o a t a r g e t d a t e of February 1, 1968, f o r t h e wind t u n n e l test. d. Boundary l a y e r and p r e s s u r e c o e f f i c i e n t d a t a from t h e two-dimensional wavy-wall t e s t s have been compiled and e d i t e d on t h e NASA 7094 computer, and have been forwarded t o ARAP, I n c . , t o be analyzed under NAS8-21294. e . S t u d i e s t o determine t h e l i m i t c y c l e behavior of f l u t t e r ing p a n e l s , t a k i n g i n t o account t h e e f f e c t s of i n - p l a n e compressive l o a d s and d i f f e r e n t i a l p r e s s u r e l o a d i n g s , a r e being continued. The computer program, developed by P r o f e s s o r E a r l H. Dowell a t P r i n c e t o n u n i v e r s i t y , * was modified t o c a l c u l a t e t h e r e q u i r e d Bessel f u n c t i o n t o handle a e r o dynamics more completely. The computer program a l s o was extended t o g e t c a l c u l a t i o n s of l a r g e r v a l u e s of i n p u t d a t a (mode number m = 6, a e r o dynamic d a t a number m = 90, e t c . ) by using t h e a c t u a l d a t a o b t a i n e d from AS-502. 6. S t a b i l i t y Derivatives Two r e p o r t s have been published by Danny D . Liu of Lockheed's H u n t s v i l l e Research and Engineering Center under NASA C o n t r a c t NAS8-20082: a . "Quas i - S l e n d e r Body Theory f o r Unsteady L i n e a r i z e d Transonic Flow P a s t Pointed Bodies of Revolution," (LMSC/HRECA791435) A p r i l 1968. I n t h i s r e p o r t , t h e l i n e a r i z e d t r a n s o n i c p o t e n t i a l e q u a t i o n i s solved f o r u s e i n c a l c u l a t i n g t h e unsteady aerodynamic p r e s s u r e s , f o r c e s , and moments f o r smooth, pointed r i g i d bodies of r e v o l u t i o n o s c i l l a t i n g w i t h a s u f f i c i e n t l y h i g h frequency a t a f r e e s t r e a m Mach number of one. This procedure y i e l d s s t a b i l i t y d e r i v a t i v e s expressed i n terms of body geometry, reduced frequency and body t h i c k n e s s r a t i o . S t a b i l i t y d e r i v a t i v e s were c a l c u l a t e d f o r a cone and a convex p a r a b o l i c ogive y i e l d i n g r e s u l t s t h a t a g r e e q u i t e w e l l w i t h a v a i l a b l e experimental s t a t i c s t a b i l i t y d a t a . b. "Some Approximate S o l u t i o n s f o r O s c i l l a t i n g Bodies of Revolution i n Nonlinear Transonic Flow," LMSC/HREC A791499, June 1968. This r e p o r t p r e s e n t s low frequency and h i g h frequency "asymptotic" d i p o l e s o l u t i o n s f o r bodies of r e v o l u t i o n o s c i l l a t i n g i n Mach 1 flow i n closed form. This i s a n e x t e n s i o n of Oswatitsch and ~ e u n e ' sp a r a b o l i c method f o r s t e a d y t r a n s o n i c flow. >c' Based on n o n l i n e a r p l a t e t h e o r y and f u l l l i n e a r i z e d ( i n v i s c i d , potent i a l ) aerodynamic theory. �These s o l u t i o n s a r e q u i t e g e n e r a l and a r e o b t a i n e d i n a form most convenient f o r performing s t a b i l i t y d e r i v a t i v e c a l c u l a t i o n s . 7. Numerical A n a l y s i s of Unsteady Flow Work under NASA c o n t r a c t NAS8-18034 w i t h Applied Theory, I n c . , has been completed and f i n a l r e p o r t s a r e being paepared. Under t h i s program, e x c e l l e n t r e s u l t s have been achieved u s i n g a f i n i t e d i f f e r e n c e numerical method t o s o l v e unsteady, compressible, v i s c o u s f l u i d flow problems f o r - b o t h s u b s o n i c and s u p e r s o n i c flow a t s e v e r a l Reynolds numbers. Of p a r t i c u l a r i n t e r e s t have been s t a t i o n a r y and o s c i l l a t i n g two-dimensional c y l i n d e r problems; two-dimensional f l a t p l a t e flow, b o t h w i t h and w i t h o u t boundary l a y e r t r i p s ; and axisymmetric flow over a forward-facing s t e p . 8. Quasi-Steady Analysis The flow v i s u a l i z a t i o n t e s t s i n t h e 14-inch t u n n e l have been completed, and t h e photographic coverage i s being processed. F a b r i c a t i o n of t h e shock-induced s e p a r a t i o n model has been completed, and t h e wind t u n n e l t e s t s w i l l b e g i n a b o u t t h e middle of September. A new b a l a n c e , designed f o r t h i s t e s t , i s being checked o u t and c a l i b r a t e d by Lockheed personnel. VI. ASTRODYNAMICS AND GUIDANCE THEORY DIVISION A. S c i e n t i f i c Advisory O f f i c e 1. U n i v e r s i t y of Texas ( C o n t r a c t NAS8-18120) Objective: Study of s t a b i l i t y and s e n s i t i v i t y of guidance systems. During t h e course of t h i s c o n t r a c t , P r o f . Lyle C l a r k , t h e p r i n c i p a l i n v e s t i g a t o r , and h i s c o l l e a g u e s and s t u d e n t s have s t u d i e d t h e problems a s s o c i a t e d w i t h s e n s i t i v i t y and s t a b i l i t y of guidance and c o n t r o l systems and have published many p a p e r s , i n c l u d i n g f i v e d o c t o r a l t h e s e s on v a r i o u s a s p e c t s of t h e s e problems. The r e p o r t s r e c e i v e d during t h i s reporting period include the following t i t l e s : (1) An approach t o suboptimal feedback c o n t r o l of nonl i n e a r systems ( t o be published i n t h e I n t e r n a t i o n a l J o u r n a l of C o n t r o l ) . (2) On l i n e a r systems w i t h a g e n e r a l i z e d performance criteria. �(3) On t h e s y n t h e s i s of suboptimal s p a c e c r a f t a t t i t u d e c o n t r o l s y s tems (Doctoral t h e s i s ) . (4) S e n s i t i v i t y of l i n e a r c o n t r o l systems t o l a r g e paramet e r variations. This l a s t paper gives. a d e f i n i t i o n of s e n s i t i v i t y which r e p r e s e n t s a n e v o l u t i o n of t h e o r i g i n a l concept a s t h e i n v e s t i g a t o r s s t r o v e t o f i n d a d e f i n i t i o n t h a t would be b o t h p r a c t i c a l and u s e f u l f o r .guidance and c o n t r o l s y s tems . 2. In-House E f f o r t s a r e c o n t i n u i n g i n t h e s t u d y of s t o c h a s t i c p r o c e s s e s . P a r t i c u l a r emphasis is being placed on t r y i n g t o determine t h e c a p a b i l i t y of t h e modern computer i n f i n d i n g a t l e a s t approximate s o l u t i o n s t o problems i n v o l v i n g t h e s e p r o c e s s e s . To t h i s end t h e van d e r Pol equat i o n ( a n o n l i n e a r second-order d i f f e r e n t i a l e q u a t i o n w i t h a s i n g l e parameter) was s e l e c t e d f o r s t u d y . Numerical and g r a p h i c a l s o l u t i o n s were o b t a i n e d f o r s e l e c t e d c o n s t a n t v a l u e s of t h e parameter. Then s o l u t i o n s of t h e same type were o b t a i n e d as each c o n s t a n t v a l u e of t h e parame t e r was p e r t u r b e d i n a random manner, and t h e s o l u t i o n s were then compared w i t h t h e unperturbed c a s e s . Work i s now i n p r o g r e s s t o perform t h e same s o r t of s t u d y f o r h i g h e r o r d e r systems and f o r systems w i t h more t h a n one parameter. The o b j e c t of t h e s e s t u d i e s i s t o determine t h e e f f e c t i v e n e s s of a g i v e n guidance o r c o n t r o l system t o do i t s job, s o t o speak, i n t h e presence of unknown and, indeed, unknowable random v a r i a t i o n s i n t h e miss i l e parameters. (Dearman) 3 . The w r i t i n g up of what could be c a l l e d by a working t i t l e , "A C r i t i c a l Survey of Methods and Formulae of C e l e s t i a l Mechanics," has been continued. R e c e n t l y included i n c o n s i d e r a t i o n has been t h e method proposed and p a r t l y e l a b o r a t e d by Groebner and Cap, using L i e s e r i e s . While t h i s method permits s l i g h t l y more i n s i g h t i n t o t h e b e h a v i o r of a p a r t from t h e n o n - a n a l y t i c s o l u t i o n s of t h e n-body problem, i t i s n o t y e t f i t f o r advantageous numerical a p p l i c a t h e two-body problem t i o n s . It could n e v e r t h e l e s s be hoped t h a t t h i s method could be adapt6 and augmented f o r a p p l i c a t i o n s t o some s p e c i f i c problems i n c e l e s t i a l mechanics. To avoid d u p l i c a t i o n of work, t h e a u t h o r s P r o f s . Groebner and Cap have been c o n t a c t e d i n w r i t i n g . (Festa) -- -- �B. Guidance Theory Branch 1. Support C o n t r a c t S t u d i e s a. General I n t e r p l a n e t a r y S t u d i e s The e r r o r s i n t h e computer program t o be used f o r t h e FPR s t u d y (using load r e l i e f c o n t r o l ) have been c o r r e c t e d . A d e t a i l e d checkout e f f o r t i s planned i n o r d e r t o p l a c e t h e program i n a product i o n s t a t u s i n t h e n e x t few weeks. This ef f o r t i s being c a r r i e d on a low p r i o r i t y b a s i s . The Guidance System E r r o r Study (GSES) computer program has been used t o e s t a b 1 i s h covariance m a t r i c e s a t v a r i o u s p o i n t s b e f o r e i n c l u d i n g t h e i n j e c t i o n p o i n t f o r a n E a r t h - to-Mars t r a j e c t o r y . The covariance m a t r i c e s w i l l be used i n mid-course guidance and o r b i t i n s e r t i o n guidance s tud i e s . b. Optimum O r b i t Trim Analyses This s t u d y was completed d u r i n g t h i s r e p o r t i n g p e r i o d and t h e r e s u l t s have been p u b l i s h e d . c. Optimal Guidance Study The a n a l y t i c a l and programming d i f f i c u l t i e g mentioned d u r i n g t h e l a s t r e p o r t i n g p e r i o d have been c o r r e c t e d . A forthcoming r e p o r t w i l l document t h e s e r e s u l t s , a l o n g w i t h some numerical examples of burn-coast-burn optimized t r a j e c t o r i e s which have been g e n e r a t e d w i t h t h e computer program. F u r t h e r e f f o r t s w i l l b e made t o improve and speed up t h i s computer program s o t h a t i t can be used f o r optimal guidance s imulation. d . Quas i-Opt i m a l Guidance Study Progress has been made r e g a r d i n g t h e i n c l u s i o n of t h e c o n s t r a i n t i n t o t h e QUOTA guidance scheme. The r e s u l t s of t h i s s t u d y w i l l be documented i n t h e near f u t u r e . k 2. Contracts a. Lockheed - Voyager Terminal Guidance Analysis A rough d r a f t of t h e f i n a l r e p o r t has been r e c e i v e d . The f i n a l r e p o r t should b e a v a i l a b l e soon. �b. - IBM A p p l i c a t i o n of Numerical Methods t o Extend C a p a b i l i t i e s f o r Optimal Rocket Guidance During t h i s r e p o r t i n g p e r i o d , i t was determined t h a t t h e computing a l g o r i t h m w i l l f i t on t h e LVDC and t h a t guidance c y c l e s of from 10 seconds a t t h e s t a r t t o 2 seconds near the end can be achieved. Future work w i l l be c o n c e n t r a t e d on c o n t i n u i n g t h e a d a p t a t i o n of OPGUIDE t o o t h e r types of m i s s i o n s such a s burn-coast-burn o r b i t a l t r a n s f e r and rendezvous. . Lockheed - Rendezvous Guidance I n t e r i m r e p o r t s summarizing t h e e f f o r t s on t h i s cont r a c t have been r e c e i v e d . An o r a l p r e s e n t a t i o n of t h e s e r e s u l t s was made r e c e n t l y . The f i r s t - b u r n guidance e q u a t i o n s a r e being r e f o r m u l a t e d u s i n g ~ e v i - ~ i v i t sa 'r e g u l a r i z i n g v a r i a b l e s Using t h e s e v a r i a b l e s a l l o w s t h e i n t r o d u c t i o n of n o n - c l a s s i c a l o r b i t a l elements t h a t a r e d e f i n e d even f o r c i r c u l a r o r b i t s and a r e slowly time-varying. The assumptions b a s i c t o t h e f i n a l - b u r n guidance concept a r e more n e a r l y f u l f i l l e d by i n t r o d u c i n g a n o t h e r burn phase n e a r t h e end of c o a s t . S i m u l a t i o n s t u d i e s a r e being performed u s i n g t h i s t h i r d burn. . 3. In-House S t u d i e s Some time was s p e n t d u r i n g t h i s r e p o r t i n g p e r i o d s t u d y i n g t h e LVDC s c a l i n g problem. It was decided t h a t a convenient way of s c a l i n g would be t o change t h e u n i t s of measurement. A new u n i t of l e n g t h , time and mass can be d e f i n e d such t h a t t h e n a v i g a t i o n and guidance e q u a t i o n s a r e s c a l e d (normalized) t o p r e v e n t overflow. The new u n i t s a r e o b t a i n e d by s e t t i n g t h e g r a v i t a t i o n a l c o n s t a n t equal t o 1, by s c a l i n g t h e l e n g t h by t h e r a d i u s of t h e e a r t h , and by s c a l i n g the mass by t h e i n i t i a l mass of t h e v e h i c l e . The QUOTA guidance scheme has been improved by updating With t h e updated t h e time d e r i v a t i v e s of t h e Lagrange m u l t i p l i e r s . X's QUOTA has s u c c e s s f u l l y flosm m i s s i o n s ( n u c l e a r s t a g e ) w i t h burn a r c s of 95 degrees w i t h a l o s s i n payload of l e s s than . O 1 p e r c e n t . A new approach t o t h e Apollo t a r g e t i n g problem i s b e i n g attempted. The problem i s being formulated s u c h that t h e guidance scheme (QUOTA) i s o l a t e s on c o n d i t i o n s near t h e moon1s s p h e r e of i n f l u ence. This i s accomplished by adding a closed form s o l u t i o n f o r t h e c o a s t phase t o t h e QUOTA guidance package. One advantage of t h i s approach, i n a d d i t i o n t o t h e f a c t t h a t t h e t a r g e t i n g and guidance problems have been combined, i s t h a t t h e s p e c i f i e d c o n d i t i o n s i n l u n a r space a r e not' l i m i t e d t o R and t a s i n Lambertls problem. �The two-impulse rendezvous problem has been formulated a s a n o p t i m i z a t i o n problem, and a computer program is being developed which minimizes t h e sum of t h e AV'S needed a t each end of t h e t r a j e c t o r y . This program w i l l provide t a r g e t i n g c o n d i t i o n s f o r rendezvous. C. O p t i m i z a t i o n Theory Branch 1. A p p l i c a t i o n of Optimal Control Theory t o CMG Momentum Dump ing Optimal c o n t r o l methods a r e being s t u d i e d a s a means of determining t h e b e s t momentum dumping c o n t r o l subsystem f o r t h e ATM v e h i c l e . The problem b e i n g i n v e s t i g a t e d i s t h e r e d u c t i o n of t h e accumul a t e d body-axis components of momentum s t o r e d i n t h e t h r e e control-moment gyros due t o n o n - c y c l i c d i s t u r b a n c e t o r q u e s encountered i n c o n t r o l l i n g t h e a t t i t u d e of t h e ATM c l u s t e r . The r e d u c t i o n must be accomplished d u r i n g t h e shadowed p o r t i o n of o r b i t , and i d e a l l y w i l l b e accomplished s t r i c t l y by maneuvers i n t h e g r a v i t y f i e l d which do n o t r e q u i r e use of a gas r e a c t i o n system. E f f o r t s have been d i r e c t e d toward f o r m u l a t i n g t h e problem i n a form which w i l l be amenable t o t h e a p p l i c a t i o n of optimal c o n t r o l t e c h n i q u e s , cons i s t e n t w i t h t h e p h y s i c a l c o n s t r a i n t s and n a t u r e of t h e C.M.G. c o n t r o l system. 2. S t a t i s t i c a l Wind Model - Hayes I n t e r n a t i o n a l (NAS8-21444) - Objective C o n s t r u c t i o n of a wind model f o r use i n s t a t i s t i c a l a n a l y s i s of launch v e h i c l e performance. The c e n t r a l i d e a of t h i s s t u d y i s t h e development of a f i l t e r t h a t shapes t h e s t a t i s t i c s of a w h i t e n o i s e i n p u t i n t o t h e b a s i c s t a t i s t i c s of measured wind and t u r b u l e n c e p r o f i l e s . The b a s i c t h e o r y and f e a s i b i l i t y of i t s a p p l i c a t i o n t o v e h i c l e d e s i g n and a n a l y s i s were demonstrated i n a previous s t u d y . The p r e s e n t work i s aimed toward using t h e f u l l body of a v a i l a b l e Jimsphere wind soundings t o develop a h i g h e r o r d e r f i l t e r whose o u t p u t w i l l i n c l u d e a l l important wind and t u r b u l e n c e f r e q u e n c i e s . Jimsphere sounding d a t a a r e now b e i n g reduced Concurrently, and covariances a r e b e i n g computed a t 50 meter i n t e r v a l s . needed t h e o r e t i c a l work i s being done f o r u t i l i z a t i o n of computed d a t a when they become a v a i l a b l e . 3. Minimax Control a. General Dynamics/ ~ o n v a i r(NAS8-21454) Objectives: (1) To extend t h e c-minimax (minimum peak v a l u e ) t h e o r y t o determine c-minimax performance i n t h e presence of �incomplete s p e c i f i e d d i s t u r b a n c e s ; (2) t o determine i f a g e n e r a l a n a l y t i c s o l u t i o n e x i s t s f o r c-minimax problems f o r l i n e a r dynamical s y s tems w i t h bounded i n p u t s ; and (3) t o i n v e s t i g a t e t h e computational problems a s s o c i a t e d w i t h t h e c u r r e n t f l o o d i n g technique used t o s o l v e minimax problems. The c o n t r a c t was signed d u r i n g t h i s r e p o r t i n g p e r i o d ; no progress r e p o r t s have y e t been r e c e i v e d . I n i t i a l emphasis w i l l be on o b j e c t i v e s (2) and (3) i n l i g h t of t h e computational d i f f i c u l t i e s experienced by s u p p o r t c o n t r a c t personnel using t h e c u r r e n t computational a l g o r i t h m and r e p o r t e d i n t h e April-May p r o g r e s s r e p o r t . b. Lockheed Support C o n t r a c t o r S t u d i e s B a s i c computational d i f f i c u l t i e s i n a p p l y i n g t h e c-minimax theory t o s p a c e c r a f t and launch v e h i c l e models which included a c t u a t o r dynamics were r e p o r t e d i n t h e April-May p r o g r e s s r e p o r t . The i n t r o d u c t i o n of s a t u r a t i o n c o n s t r a i n t s on t h e a c t u a t o r k e p t t h e response from going unbounded, b u t d i f f i c u l t y has been encountered i n f l o o d i n g t h e s t a t e s p a c e because of t h e tendency of t h e a l g o r i t h m t o keep t h e a c t u a t o r o p e r a t i n g on o r n e a r i t s s a t u r a t i o n bound. 4. S t a t i s t i c a l Optimal Control - Horieywell (NAS8-21063) O b j e c t i v e : To i n v e s t i g a t e f u r t h e r t h e a p p l i c a t i o n of t h e s t a t i s t i c a l o p t i m i z a t i o n technique developed under NAS8-11206. D r a f t copies of t h e f i n a l s t u d y r e p o r t and t h e computer program documentation r e p o r t have been r e c e i v e d and reviewed. The reviewers' comments have been r e t u r n e d on t h e f i n a l r e p o r t . The s t u d y r e s u l t s showed t h e optimum performance a v a i l a b l e and gave i n s i g h t i n t o t h e optimum behavior of t h e launch v e h i c l e model, which included bending and s l o s h i n g dynamics. Attempts t o develop a n a l y t i c means of s e l e c t i n g a s e n s o r complement and f i l t e r s which a r e b e s t i n t h e s e n s e of most c l o s e l y a c h i e v i n g t h e t h e o r e t i c a l optimum performance were d i s a p p o i n t i n g . A r e a l i z a b l e system was designed based on t h e optimum ( u n r e a l i z a b l e ) system, b u t t h i s d e s i g n was n o t s o s t r a i g h t f o r w a r d a s would be d e s i r a b l e . F u t u r e work i n t h i s a r e a would be u s e f u l , a l t h o u g h t h e b e s t approach i s not yet clear. The computer program documentation was r e q u e s t e d t o permit f u r t h e r in-house inves t i g a t i o n s of t h e technique. The program i s c u r r e n t l y r u n on CDC-6600 computer, which uses a b o u t one-half of t h e s t o r a g e a v a i l a b l e . One o p t i m i z a t i o n - e v a l u a t i o n r u n t a k e s a b o u t 20 minutes f o r It a p p e a r s t h e 25th o r d e r time-varying d e s c r i p t i o n of t h e v e h i c l e . t h a t , on our t h i r d - g e n e r a t i o n equipment, t h e program w i l l r e q u i r e o v e r l a y s f o r remote o p e r a t i o n and w i l l r e q u i r e 40 t o 100 minutes f o r one complete run. �5. S a t u r n V / ~ p o l l oLoad R e l i e f S t u d i e s - Northrop Rigid body a n a l y s e s a r e n e a r i n g completion. Two c a n d i d a t e systems n o t considered i n t h e o r ' i g i n a l Boeing s t u d y have shown a s i g n i f ic a n t r e d u c t i o n i n t h e v e h i c l e bending moment and w i l l be considered i n t h e more complete dynamic a n a l y s i s . An i n t e r i m r e p o r t w i l l be i s s u e d t o document t h e r e s u l t s of t h e r i g i d body a n a l y s i s . 6. Parameter Optimization Study f o r ATM - Lockheed A-hybrid s i m u l a t i o n of a s i m p l i f i e d ATM p o i n t i n g system and o p t i m i z e r c o n t i n u e s i n t h e check-out phase. The o p t i m i z a t i o n package has been programmed and checked o u t on t h e d i g i t a l p o r t i o n of t h e comp u t e r ; however, t h e v e h i c l e dynamic s i m u l a t i o n on t h e a n a l o g p o r t i o n has had d i f f i c u l t i e s w i t h s y s tem i n s t a b i l i t i e s C u r r e n t l y t h e a n a l o g s imulat i o n i s being modified t o match a program r u n s u c c e s s f u l l y by t h e Lockheed s u p p o r t group. . D. As trodynamics Branch 1. Broken Plane T r a j e c t o r i e s (Lockheed) Work was continued on s t u d y and documentation of t h e brokenplane computer program i n use by t h e c o n t r a c t o r . It was determined t h a t s e v e r a l s m a l l a n g l e approximations had been used i n t h e program which were n o t a p p l i c a b l e f o r a l l our needs and t h e s e approximations a r e b e i n g r e p l a c e d w i t h e x a c t f o r m u l a t i o n s . Also, t h e program was o r i g i n a l l y developed f o r t r a j e c t o r i e s between E a r t h , Venus, and Mars o n l y and i s being a l t e r e d t o accommodate f l i g h t s t o any of t h e p l a n e t s of t h e s o l a r s y s tem. I n a n e f f o r t t o a s c e r t a i n whether broken-plane t r a n s f e r s could be i n c o r p o r a t e d i n t o t h e c o n s t r u c t i o n of swingby t r a j e c t o r i e s w i t h any u s e f u l r e s u l t s , p r e l i m i n a r y t r a j e c t o r y c a l c u l a t i o n s were made w i t h t h e broken-plane program and t h e MAOT (Medium Accuracy O r b i t T r a n s f e r ) c o n i c program. These p r e l i m i n a r y c a l c u l a t i o n s i n d i c a t e t h a t t h e combinat i o n of broken plane and swingby w i l l o f f e r some d e f i n i t e advantage when one l e g of t h e s t a n d a r d swingby i s n e a r 180 d e g r e e s . These advantages w i l l be r e a l i z e d through, and w i l l e x t e n d , t h e o p p o r t u n i t i e s f o r lowenergy swingbys. 2. Miss i o n Des i g n C h a r t s (Lockheed) The problem of c o n s t r u c t i n g g e n e r a l i z e d m i s s i o n maps i s c e n t e r e d around t h e d e t e r m i n a t i o n of ways of p r e s e n t i n g a composite p l o t of many t r a j e c t o r y parameters a s f u n c t i o n s of launch d a t e and �a r r i v a l date. I n p r e s e n t i n g t h e s e parameters i n m i s s i o n map format, numerous i n t e r m e d i a t e c r o s s p l o t s of each t r a j e c t o r y parameter a r e r e q u i r e d . The Lockheed i n t e r p l a n e t a r y t r a j e c t o r y programs a r e b e i n g modified t o produce a u t o m a t i c p l o t s of t h e s e parameters a s f u n c t i o n s of launch and a r r i v a l d a t e s . 3. I n t e r p l a n e t a r y N-Body Programs a. Program Development Various f o r m u l a t i o n s of t h e e q u a t i o n s of motion and numerical i n t e g r a t i o n techniques considered b o t h a s s e p a r a t e u n i t s and a s combined packages a r e c o n t i n u i n g . b . T a r g e t i n g Research (Nor t h r o p ) An i n t e r n a l memo (68-15) has been published g i v i n g t h e r e s u l t s of t h e s t u d y of p e r t u r b e d c o n i c s o l u t i o n s t o i n t e r p l a n e t a r y t r a j e c t o r y problems. Work i s c o n t i n u i n g on t h e programming and checkout of t h e " a n a l y t i c conglomerate mass technique Investigation i s a l s o c o n t i n u i n g on t h e l a r g e time-step numerical i n t e g r a t i o n method. ." c. I s o l a t i o n Routine Research (Northrop) Recently programmed techniques a r e being checked o u t , and v a r i o u s r o u t i n e s a r e being compared. 4. Conic Programs f o r Small Computers Work i s c o n t i n u i n g on t h e program t o compute i n j e c t i o n p o s i t i o n and v e l o c i t y a s a f u n c t i o n of launch azimuth and i n j e c t i o n energy (C3). P r o g r e s s on t h i s work i s s e v e r e l y r e s t r i c t e d by t h e c u r r e n t l a c k of a c c e s s t o l o c a l computers. 5. O r b i t T r a n s f e r S t u d i e s (United A i r c r a f t NAS8-21091) The f i n a l r e p o r t on t h i s s t u d y has been r e c e i v e d , and a l l copies have been d i s t r i b u t e d . The r e p o r t c o n t a i n s a v e r y comprehensive assessment of t h e s t a t e of t h e a r t of impulsive s o l u t i o n s t o o r b i t t r a n s f e r and rendezvous problems and a b i b l i o g r a p h y of over 300 r e f e r e n c e papers which, i t i s thought, r e p r e s e n t a complete coverage of a v a i l a b l e knowledge i n t h e s e a r e a s . R e p r e s e n t a t i v e s of t h e AIAA J o u r n a l have cont a c t e d t h e a u t h o r s , and i t i s hoped t h a t t h e r e p o r t w i l l be p u b l i s h e d i n the Journal. �6. Odyssey (Lockheed) A r e p o r t presenting equations f o r the v a r i a t i o n i n perigee a l t i t u d e due t o s o l a r p e r t u r b a t i o n s has been paepared and i s being reviewed in-house. A low p r i o r i t y e f f o r t i s now under way t o d e f i n e launch o p p o r t u n i t i e s and d a i l y launch windows t o accommodate r e s t r i c t i o n s on t h e t r a j e c t o r y which would be n e c e s s a r y f o r a n Odyssey m i s s i o n . 7. Abort and A l t e r n a t e Mission S t u d i e s Documentation of t h e d e t a i l s of S a t u r n V v e h i c l e p e r f o r mance, guidance and c o n t r o l c h a r a c t e r i s t i c s , m i s s i o n s , and t r a j e c t o r y shaping i s being accumulated i n a p r o c e s s of f a m i l i a r i z a t i o n of branch personnel w i t h t h e problems of c o n t i n g e n c i e s and a b o r t s i t u a t i o n s . A r e q u e s t t o t h e Boeing Company f o r a s t u d y t o develop a comprehensive system-oriented d e s i g n f o r a f i r s t - s t a g e t i l t program t o accommodate a n S-IC engine f a i l u r e has been i n i t i a t e d . Work i s a l s o being' i n i t i a t e d in-house t o s t u d y t h e approach used t o provide f o r s u c c e s s f u l campletion of t h e m i s s i o n i n c a s e of l o s s of a n a c c e l e r o m e t e r o u t p u t . 8. O r b i t s i n Noncentral F i e l d s An e f f o r t i s b e i n g made t o assemble a l l u s e f u l closed-form s o l u t i o n s t o problems i n o r b i t a l mechanics, and t o i n d i c a t e t h e p h y s i c a l s i t u a t i o n s of which t h e s e a r e mathematical models. Problems a r e charact e r i z e d by a p o t e n t i a l f u n c t i o n i n t h e c o o r d i n a t e system used. Problems s t u d i e d t o d a t e i n c l u d e o r b i t s a b o u t o b l a t e , p r o l a t e , and pear-shaped objects. VII. DYNAMICS AND FLIGHT MECHANICS DIVISION A. Damping of Liquid O s c i l l a t i o n s by Wall Roughness (Ref. April-May 1968) T e s t s t o determine t h e e f f e c t s of w a l l roughness on t h e damping of l i q u i d o s c i l l a t i o n s have been extended t o cover t h e e f f e c t s of Reynolds number, a s w e l l a s roughness h e i g h t and l o c a t i o n . The Reynolds number was decreased by t e s t i n g i n a s m a l l e r t a n k and by u s i n g s u c r o s e w a t e r s o l u t i o n s w i t h v i s c o s i t i e s up t o 162 cp a s t e s t l i q u i d s . As expected, t h e damping was i n c r e a s e d by d e c r e a s i n g t h e Reynolds number. The d i f f e r e n c e between t h e smooth-wall damping and rough-wall damping was l e s s a t low Reynolds number t h a n a t h i g h Reynolds number. (DDS) �B. Saturn V 1. M i s s i o n P r o f i l e ( T r a j e c t o r y S h a p i n g , O p t i m i z a t i o n , TimeLining, e t c . ) a. S l i g h t s h o t D i s p o s a l Mode (Ref. Feb.-March 1968, p. 37) A p r e s e n t a t i o n was g i v e n summarizing t h e c u r r e n t r e s u l t s and c o n c l u s i o n s r e l a t i v e t o S-IVBIIU s p a c e c r a f t r e c o n t a c t and l u n a r debris. The s l i n g s h o t mode o f S-IVB d i s p o s a l p r e s e n t e d was b a s e d upon the following g u i d e l i n e s : ( 1 ) I n i t i a t e a n S-IVB p o s t i n j e c t i o n r e s i d u a l dump a t a n a t t i t u d e and t i m e s u c h t h a t (a) s p a c e c r a f t r e c o n t a c t is avoided, (b) e a r t h i m p a c t i s a v o i d e d , and (c) l u n a r impact i s minimized s u b j e c t t o ( a ) and (b) above. ( 2 ) The f o l l o w i n g recommendation was made. To a c c o u n t f o r t h e v a r i a b l e t i m e o f LM e x t r a c t i o n , t h e s l i n g s h o t a l t i t u d e r e q u i r e d t o a c c o m p l i s h S-IVB d i s p o s a l s h o u l d be: Time P a s t TL1 A t t i t u d e from Local H o r i z o n t a l 1 hr. 2 hr. 3-6 h r . An a c t i o n i t e m r e s u l t e d from t h e m e e t i n g t o d e t e r m i n e t h e t r a d e - o f f i n terms o f impact p r o b a b i l i t y of e a r t h impact v s l u n a r i m p a c t . I n s p e c t i o n i n d i c a t e d t h a t a d d i n g AV from t h e APS s y s tem - w i l l produce a s m a l l i n c r e a s e i n the earth-impact probability while reducing s i g n i f i c a n t l y the lunarimpact p r o b a b i l i t y . b. S - I 1 and S-IVB P r o p e l l a n t U t i l i z a t i o n System A n a l y s i s (NEW) ( 1 ) S - I 1 p r o p e l l a n t u t i l i z a t i o n f a i l u r e c a s e s were i n v e s t i g a t e d w i t h and w i t h o u t t h e time-guard a p p l i e d as a s a f e t y measure t o f o r c e a PU s h i f t i f a f a i l u r e had o c c u r r e d . Payload l o s s e s ranged from 40,000 l b s f o r a c l o s e d - l o o p PU f a i l u r e a t 2 . 5 s e c t o MR = 4 . 5 w i t h no time g u a r d t o 510 l b s w i t h a time-guard s e t a t t h e mincmum p e r f o r mance p e n a l t y t i m e f o r t h e same f a i l u r e . Data a r e f o r a n o m i n a l l y l o a d e d s t a g e w i t h 970K p r o p e l l a n t . �( 2 ) Various S - I 1 burn m i x t u r e o p t i o n s wel, -a c1gated w i t h open-loop PU o p e r a t i o n . Payload l o s s e s ranged from 518 l b s f o r t h e p r o f i l e of 5 . 0 / 5 . 5 / 4 . 7 t o 3600 l b s f o r 5 . 0 / 5 . 0 / 5 . 0 . (3) Closed-loop PU f a i l u r e c a s e s f o r o u t - o f - o r b i t burn w i t h o u t t h e time-guard were i n v e s t i g a t e d f o r t h e S-IVB s t a g e . Payload l o s s e s f o r a closed-loop PU a t f i r s t o p p o r t u n i t y v a r i e d from 9762 l b s (310 m/sec d e f i c i t ) f o r a f a i l a t 4.5 MR a t o r b e f o r e t h e nominal s h i f t time (back t o 5 . 0 MR) t o 2472 l b s (76 m/sec d e f i c i t ) f o r a f a i l u r e from 4.5 MR t o 5.5 MR a t t h e nominal s h i f t time back t o t h e 5.0 MR. Second o p p o r t u n i t y f a i l u r e s y i e l d e d 14497 l b s (474 m/sec v e l o c i t y d e f i c i t ) f o r a f a i l a t 4.5 MR a t i g n i t i o n t o 2391 l b s (73 m/sec v e l o c i t y d e f i c i t ) f o r a f a i l a t 5 . 5 MR. These a r e t h e extreme f a i l u r e c a s e s f o r t h e S-IVB closed-loop PU o p e r a t i o n . (4) Using a time s h i f t arrangement t o d u p l i c a t e closed-loop response y i e l d e d a payload l o s s of 500 l b s . (5) Open-loop cases w i t h c o n s t a n t burn mixture r a t i o s f o r t h e o u t - o f - o r b i t burn y i e l d e d payload l o s s e s of 481 l b s and 512 l b s f o r t h e f i r s t and second o p p o r t u n i t i e s , r e s p e c t i v e l y , w i t h a nominally loaded s t a g e . By adding 1800 l b s a d d i t i o n a l LH2 and changing t h e burn m i x t u r e r a t i o s , r e s p e c t i v e l y , t h e payload l o s s e s changed t o 127 l b s and 121 l b s f o r t h e f i r s t and second o p p o r t u n i t i e s , r e s p e c t i v e l y . This LH2 i n c r e a s e would a l s o be a p p l i c a b l e t o t h e closed- and open-loop schemes s t u d i e d and should provide approximately the' same performance e f f e c t . (6) The above d a t a were p r e s e n t e d a t t h e PU s t a t u s meeting t o D r . Rees, J u l y 16, 1968. (DAP) 2. Guidance a. S-I1 2 Engine Out (Ref. April-May 1968, p. 34) (1) O f f i c e Memo R-AERO-DGA-3-68 was a n a c t i o n item This l o g i c change from a j o i n t meeting i n A p r i l between ASTR and AERO. r e q u i r e d e n g i n e s - o u t d i s c r e t e s which r e q u i r e d hardware changes. S i n c e no a c t i o n was t a k e n t o implement t h e l o g i c changes, two-engines-out c a p a b i l i t y has n o t changed. (2) O f f i c e Memo R-AERO-DGA-5-68 r e d e f i n e s t h e S - I 1 s t a g e s o t h a t engine-out d i s c r e t e s a r e n o t r e q u i r e d . However, t h e guidance e q u a t i o n s a r e a d j u s t e d i f engines do go o u t . This approach i s more d e s i r a b l e than t h e one g i v e n i n R-AERO-DGA-3-68. It now appears t h a t t h e r e q u i r e d a c t i o n t o implement t h i s p r o p o s a l w i l l be slow, i f a t all. �( 3 ) The e f f e c t i v e d a t e was n o t s p e c i f i e d i n e i t h e r memorandum becaus'e t h e i r primary advantages a r e f o r f a i l u r e modes which have, i n t h e p a s t , been r u l e d o u t . These f a i l u r e modes a r e n o t a program requirement a t t h e p r e s e n t time. However, they could v e r y w e l l become a requirement a t a much more unfavorable time. For t h a t r e a s o n , DGA-7-68 was prepared. This memorandum recommends t h a t DM-5-68 be implemented f o r AS-503 and s u b s . (DM) b. E v a l u a t i o n of t h e AS-502 F l i g h t Anomaly (New) The 502 S - I 1 s t a g e l o s t two engines 104 seconds b e f o r e nominal S - I 1 c u t o f f . As a consequence, t h e S - I 1 s t a g e d burn-time was 59 seconds longer than expected. During t h i s time, t h e v e h i c l e f l e w a t a c o n s t a n t a t t i t u d e . Because of t h e extended burn-time and c o n s t a n t a t t i t u d e , t h e S-IVB s t a g e had t o make extreme maneuvers i n o r d e r t o meet t h e m i s s i o n c o n s t r a i n t s . As expected, t h e s m a l l a n g l e approximation t o t h e t r i g f u n c t i o n s of (K1 - K ~ impacted ~ ) t h e "switching function" during t h e S-IVB burn. The guidance e q u a t i o n can be c a l l e d h a r d l y more than a s w i t c h i n g f u n c t i o n s i n c e t h e v e h i c l e i s r e q u i r e d t o 'tilt a t a maximum r a t e +1 d e g / s e c b e t t e r than 90 p e r c e n t of t h e burn-time. A s i m u l a t i o n of t h e 502 S-IVB f l i g h t w i t h a b e t t e r t r i g f u n c t i o n a p p r o x i mation of (K1 - K ~ i n~ t h e) time-to-go e q u a t i o n showed a n i n j e c t i o n e r r o r of 700 meters i n a l t i t u d e w i t h no v e l o c i t y and f l i g h t p a t h a n g l e e r r o r s . This approach i s being f u r t h e r i n v e s t i g a t e d a s a p o s s i b i l i t y of implementation. (DGA) 3. Dynamics and Control a. S a t u r n V, S-IVB S l o s h Damping (New) A s t u d y of s l o s h damping i n t h e S-IVB, LH2 tank has r e c e n t l y been completed. As a r e s u l t a new s e t of LH2 damping v a l u e s i s being recommended. These new d a t a a r e based on t h e l a t e s t published i n f o r m a t i o n concerning w a l l damping i n c y l i n d r i c a l t a n k s . The r e v i s e d damping v a l u e s a r e somewhat s m a l l e r than previous d a t a , b u t should n o t c r e a t e any major problems. (DDS) b. S a t u r n V L a t e r a l - L o n g i t u d i n a l Coupling SA-502 (New) A two-degrees-of-freedom spring-mass model of t h e LTA-2 has been developed from t h e 43 x 43 dynamic m a t r i x developed by Boeing. The c o e f f i c i e n t s from t h i s model a r e being used i n analog s t u d i e s of t h e coupling between l a t e r a l and l o n g i t u d i n a l v i b r a t i o n modes which occurred d u r i n g AS-502. The analog s i m u l a t i o n s a r e of two types : �(1) One c o n s i d e r s t h e magnitude of t h e Pogo t h r u s t o s c i l l a t i o n a s a n 'open-loop f o r c i n g f u n c t i o n t o t h e l o n g i t u d i n a l mode, and has a s o u t p u t t h e l a t e r a l v e h i c l e and LEM motion. (2) The second has t h e Pogo closed-loop w i t h complete time-varying c o e f f i c i e n t s and t h e l a t e r a l - l o n g i t u d i n a l coupling. The r e s u l t s of t h e s t u d i e s show: (1) A good d u p l i c a t i o n of t h e i n s t a b i l i t y observed on AS-502. (2) A l o n g i t u d i n a l LEM a c c e l e r a t i o n of 0 . 6 5 g t s w i t h a l a t e r a l a c c e l e r a t i o n of 0.5g's f o r a peak t h r u s t o s c i l l a t i o n of 20,000 l b s . (3) No evidence of c o n t r o l system coupling w i t h Pogo. (4) Detuning Pogo (reducing s u c t i o n l i n e frequency) reduces l a t e r a l response by f a c t o r of 10 o r more. (5) Driving t h e l o n g i t u d i n a d mode w i t h 5,000 l b s peak amplitude w h i t e n o i s e produces v e r y l i t t l e l a t e r a l LEM response (> 0 . 2 g f s ) . ( 6 ) A h i g h s e n s i t i v i t y of t h e system t o s m a l l v a r i a t i o n s i n f r e q u e n c i e s , s t r u c t u r a l damping, and in£ luence c o e f f i c i e n t s e x i s t s (DD/DC) . c. Pogo S t a b i l i t y S t u d i e s (Ref. April-May 1968, p. 36) Equations d e s c r i b i n g t h e Pogo phenomenon have been d e r i v e d i n a form which permits t h e i r use i n a n e x i s t i n g d i g i t a l computer program f o r s t a b i l i t y a n a l y s i s . I n i t i a l computer runs have been made f o r t h e purpose of matching t h e AS-502 r e s u l t s and t h e r e b y v e r i f y i n g t h e model and t h e parameter v a l u e s used. These runs a l s o s e r v e a s a b a s e f o r parame t e r s e n s i t i v i t y s t u d i e s . The accumulator f i x i n t h e e q u a t i o n s w i l l be included a f t e r t h e s e p r e l i m i n a r y runs a r e completed. (DC) d. S a t u r n V Rigid Body Responses t o Plume Induced O s c i l l a t o r y Forces (New) A f i r s t - s t a g e f l i g h t s i m u l a t i o n was made which included a f u n c t i o n approximating t h e plume-induced o s c i l l a t o r y f o r c e s . The plume f o r c e was a 5 cps wave w i t h a peak-to-minimum v a l u e range of 11,500 pounds t o z e r o pounds, a c t i n g on t h e v e h i c l e a t 2 c a l i b e r s forward of t h e gimbal s t a t i o n . The f l i g h t time r e g i o n was 120 seconds t o 130 seconds. The �e f f e c t s of t h i s f o r c e on t h e r i g i d body responses were found t o have l i t t l e impact on t h e c o n t r o l system and r i g i d body bending moments. (DC) 5. P r o j e c t Information A p p l i c a b l e t o I n d i v i d u a l Vehicles a. AS-504 S t a t i s t i c a l Wind Response (New) C o n t r a c t NAS8-21314 i s i n i t s second month. The wind model t h e c o n t r a c t o r was d i r e c t e d t o use i s n o t s t a b l e i n t h e low a l t i t u d e ranges. A new wind model i s being r e f i n e d under a new c o n t r a c t u s i n g 1,000 Jimsphere p r o f i l e s . Now t h a t a d e c i s i o n has been made on t h e wind model, t h e e q u a t i o n s of motion f o r t h e system a r e being formulated. (DDD/GE) b. AS-503, S-LVB F l i g h t S t a g e Dynamic Data (Ref. April-May 1968, p. 38) An a n a l y s i s was made t o determine t h e p i t c h dynamic c h a r a c t e r i s t i c s f o r t h e unmanned AS-503 v e h i c l e d u r i n g t h e S-IVB p o r t i o n of f l i g h t . An a n a l y s i s was a l s o made of t h e manned v e r s i o n a f t e r S-IVB f i r s t burn. The r e s u l t s of t h e s e a n a l y s e s were published i n memorandum (D~s/~oeing) R-AERO-DD-117-68. c. AS-503 On-Pad Dynamic C h a r a c t e r i s t i c s (New) On-pad dynamic c h a r a c t e r i s t i c s were c a l c u l a t e d f o r s e v e r a l f u e l i n g c o n d i t i o n s on AS-503. These d a t a have been g i v e n t o R-AERO-AU f o r (DDS) p r e d i c t i o n of ground wind l o a d i n g s . C. Saturn I B 1. Dynamic Data f o r AS-205 S-IVB F l i g h t S t a g e (New) A bending and t o r s i o n a n a l y s i s was made of t h e S-IVB f l i g h t s t a g e u s i n g ~ o e i n g ' s s h e l l model. This type of a n a l y s i s i s n e c e s s a r y because of s h e l l - t y p e modes i n t h e range of 16-18 c y c l e s t h a t do n o t show up i n a beam model a n a l y s i s . Dynamic c h a r a c t e r i s t i c s o b t a i n e d from (~~S/~oeing) t h e a n a l y s i s were published i n memorandum R-AERO-DD-118-68. 2. Revised Bending A n a l y s i s of AS-205, F i r s t F l i g h t S t a g e (Ref. Feb.-March 1968, p. 38) An a n a l y s i s was made f o r AS-205 f i r s t - s t a g e f l i g h t and f o r on-pad c o n d i t i o n s t o i n c o r p o r a t e new mass d a t a i n c l u d i n g t h e r e v i s e d p r o p e l l a n t b u r n - r a t e w i t h t h e r e v i s e d inboard engine c u t o f f . Also updated s p a c e c r a f t s t i f f n e s s d a t a were i n c o r p o r a t e d , w i t h t h e primary change being i n t h e SLA a r e a . The r e s u l t s of t h e a n a l y s i s were publ(D~~/~hrysler) ished i n memorandum R-AERO-DD-116-68. �D. S a t u r n Apollo A p p l i c a t i o n Program 1. Cluster a. Mission P r o f i l e (1) Unmanned Rendezvous Using S-IVB S t a g e (Ref. April-May 1968, p. 40) Two b a s i c p r o f i l e s t o accomplish unmanned rendezvous have been s t u d i e d u s i n g t h e S-IVB workshop a t t i t u d e c o n t r o l system (WACS) modified f o r t r a n s l a t i o n a l t h r u s t . One method assumed i n s e r t i o n i n t o a n o r b i t 5 n a u t i c a l m i l e s above and downrange from t h e OWS using a r e s t a r t of t h e (P&VE Laboratory i n v e s t i g a t e d t h e m o d i f i c a t i o n s necesS-IVB J - 2 engine. s a r y f o r t h e r e s t a r t . ) T r a n s f e r was made w i t h a modified WACS p r o p u l s i o n system t o a w a i t i n g o r b i t 1 NM above t h e OWS. By v a r y i n g t h e time s p e n t i n t h e w a i t i n g o r b i t , t h e c o r r e c t l i g h t i n g c o n d i t i o n s could be c o n t r o l l e d f o r t h e t e r m i n a l phase. Rendezvous i s accomplished a s i n t h e Apollo S a t u r n I B d u a l rendezvous except i n t h i s c a s e t h e c h a s e r v e h i c l e (LM/ATM) w i l l be coming i n from above r a t h e r than below t h e t a r g e t . The o t h e r rendezvous technique assumes a d i r e c t i n s e r t i o n of t h e S-IVB/LM i n t o t h e OWS o r b i t 110 NM ahead of t h e OWS. (One hundred and t e n NM i s used t o a l l o w f o r 40 NM 30 i n s e r t i o n d i s p e r s i o n s and a lSIsecond launch window.) I n s e r t i o n i s then made w i t h t h e WACS i n t o a phasing o r b i t w i t h a p e r i o d longer than t h a t of t h e OWS. A f t e r two complete r e v o l u t i o n s i n t h i s o r b i t , t h e r e l a t i v e range has decreased t o 20 NM, and a second WACS burn i s made p l a c i n g i t on a n e l l i p s e which i n t e r c e p t s t h e OWS a f t e r a c e n t r a l a n g l e t r a v e l of 240". When s t a t i o n - k e e p i n g d i s t a n c e i s r e a c h e d , a t h i r d WACS burn is made which matches t h e S-IVB/L,M and OWS v e l o c i t i e s . An a n a l y s i s has a l s o been made f o r t h e s e two rendezvous methods of t h e a d d i t i o n a l WAC impulse n e c e s s a r y t o overcome i n s e r t i o n d i s p e r s i o n s (both performance and n a v i g a t i o n ) and t o account f o r LM rendezvous r a d a r e r r o r s . Both rendezvous p r o f i l e s r e q u i r e d l e s s p r o p e l l a n t than i s a v a i l a b l e i n t h e WACS. It was found t h a t t h e d e t r i m e n t a l consequences of t h e r a d a r e r r o r s could be reduced i f t h e l e s s a c c u r a t e a n g l e and a n g l e r a t e r a d a r d a t a were ignored. To make up f o r t h i s , more t h a n one measurement of range and range r a t e was taken t o determine t h e c o n i c parameters and p o s i t i o n on t h e c o n i c through c a l c u l a t i o n s i n t h e I U computer. The r e s u l t s of t h e s e s t u d i e s were p r e s e n t e d t o t h e AAP Basel i n e C o n f i g u r a t i o n Review on J u l y 23. (~A~/~orthrop) �(2) E a r t h Resources Experiment Impact on C l u s t e r I Mission (Ref. April-May 1968, p. 39) This s t u d y was extended t o i n c l u d e the conseqyences of t h e 34.26 i n c l i n a t i o n of AAP-2 on t h e UP-3A m i s s i o n . It was demons t r a t e d that s a t i s f a c t o r y launch o p p o r t u n i t i e s could be i n s u r e d a b o u t every t h i r d day n e a r t h e d e s i r e d launch d a t e of AAP-3A. (~AO/Northrop) (3) AAP-314 A l t e r n a t e Mission P r o f i l e and Launch Window Analys i s (New) During t h i s p e r i o d , a s t u d y was i n i t i a t e d t o d e t e r mine t h e m i s s i o n p r o f i l e and launch o p p o r t u n i t i e s assuming t h e AAP-314 i s flow s e p a r a t e from t h e OWS. The following a r e t h e ground r u l e s under which t h i s s t u d y i s being done: (a) A high i n c l i n a t i o n i s d e s i r a b l e t o increase the ATM sun o b s e r v a t i o n time. (b) The IU has a 7 112-hour l i f e t i m e f o r s t a b i l i z a t i o n of AAP-4 f o r docking maneuvers. (c) There is a minimum AAP-3 i n s e r t i o n of 81 x 120 NM. (d) Rendezvous between U P - 3 and 4 i s t o be accomp1i s hed by t h e s tandard c o - e l l i p t i c technique. It was found t h a t , i f a n i n c l i n a t i o n of 47" were used, two in-plane in-phase o p p o r t u n i t i e s could be provided on t h e same day. To s a t i s f y t h e second ground r u l e , t h e manned AAP-3 was launched f i r s t i n t o a n 81 x 120 NM o r b i t , c i r c u l a r i z i n g a t 120 NM w i t h t h e SPS. One day l a t e r AAP-4 i s i n s e r t e d d i r e c t l y i n t o a c i r c u l a r o r b i t . The a l t i t u d e s f o r t h e AAP-4 o r b i t being considered a r e 180, 170, and 200 NM. Various t r a d e - o f f s between launch window width, payload, m i s s i o n p r o f i l e , and rendezvous time have been made. Thus f a r , o n l y n o r t h e r l y launches i n t o t h e 47" i n c l i n a t i o n o r b i t have been considered. During t h e n e x t p e r i o d , a n a l y s i s f o r s o u t h e r l y launches should be completed and documentation should begin. (DAO/NO~ throp) (4) R o l l Required of UP-112 t o C a l i b r a t e S-049 (New) Experiment S-049 on t h e AAP-112 m i s s i o n has a n instrument t h a t must be c a l i b r a t e d sometime d u r i n g t h e m i s s i o n . The instrument i s c a l i b r a t e d by t a k i n g a photograph of t h e moon when t h e moon i s e q u a l t o o r g r e a t e r t h a n h a l f i l l u m i n a t e d . The o p t i c a l a x i s of t h e instrument l i e s i n t h e o r b i t plane of t h e AAP-112 o r b i t and p o i n t s i n t h e d i r e c t i o n of t h e m e r i d i a n which i s 180" away from t h e s u n ' s m e r i d i a n . The o n l y maneuvers p e r m i t t e d t h e AAP-112 a r e r o l l maneuvers �(no p i t c h o r yaw); thus t h e moon must l i e a t ( o r v e r y n e a r ) t h e i n t e r s e c t i o n of t h e moon's p l a n e and t h e AAP o r b i t p l a n e t o be v i s i b l e w i t h i n t h e f i e l d of view of t h e instrument. Then w i t h a r o l l maneuver of t h e AAP, t h e S-049 can view and photograph t h e moon. It i s immediately obvious t h a t , s i n c e t h e moon must b e e q u a l t o o r g r e a t e r t h a n h a l f i l l u m i n a t e d t o c a l i b r a t e t h e i n s t r u m e n t , t h e n o n l y h a l f of each l u n a r month, from f i r s t q u a r t e r t o l a s t q u a r t e r , w i l l b e a v a i l a b l e f o r c a l i b r a t i o n . Also, because of t h e p o i n t i n g d i r e c t i o n of t h e i n s t r u m e n t w i t h r e s p e c t t o t h e sun, t h e r e q u i r e d r o l l a n g l e of t h e AAP-112 w i l l always b e e q u a l t o o r l e s s t h a n 90 d e g r e e s . - A complete a n a l y s i s of t h e problem has been done u s i n g October 1, 1970, as a launch d a t e f o r UP-112. I f the mission lasts as long as 28 days, t h e n t h e r e w i l l always b e a time d u r i n g t h e m i s s i o n when t h e c a l i b r a t i o n can be done. During October of 1970, t h e c a l i b r a t i o n can b e done between October 8 and October 22. Given any launch time d u r i n g t h e day and any launch d a t e d u r i n g t h e f i r s t of October, i t is determined on what d a t e t h e c a l i b r a t i o n can be done and what r o l l a n g l e w i l l b e r e q u i r e d . Some launch times d u r i n g t h e day y i e l d s i n g l e s o l u t i o n s (one day on which t h e c a l i b r a t i o n i s p o s s i b l e ) , some launch times y i e l d double s o l u t i o n s , and some launch times y i e l d t r i p l e solutions. (DAO) (5) P r e l i m i n a r y F l i g h t P r o f i l e s f o r AAP-1 and 3A (New) An a n a l y s i s t o determine AAP-1 and AAP-3A launch v e h i c l e t a r g e t i n g parameters was made t o r e f l e c t v e h i c l e reassignments. The i n e r t i a l descending node and i n c l i n a t i o n were v a r i e d t o s a t i s f y t h r e e launch o p p o r t u n i t i e s f o r t h e AAP'1 and two launch o p p o r t u n i t i e s f o r t h e AAP-3A. The r e s u l t i n g optimum payloads f o r t h e f i r s t , second and w o r s t launch o p p o r t u n i t i e s of AAP-1 were 39228 l b s , 39230 l b s , and 39128 l b s , r e s p e c t i v e l y . For t h e f i r s t and second o p p o r t u n i t i e s f o r AAP-3A, t h e payload v a l u e s were 39865 l b s and 39897 l b s , r e s p e c t i v e l y . The purpose of t h e r e g e n e r a t i o n of t h e AAP-1 and AAP-3A launch window a n a l y s i s was t h e reassignment of SA-207 from AAP-1 t o AAP-3A and SA-206 from AAP-3A t o AAP-1. (DAP) (6) Design Reference Mission Document (DRMD) (New) AAP-314 . R e p r e s e n t a t i v e s of t h e Mar tin/Mar i e t t a Corp and members of R-AERO-DAM completed a comprehensive review of t h e DRMD f o r These s i x volumes p r o v i d e t h e Apollo A p p l i c a t i o n s miss i o n AAP-3/AAP-4. Program p l a n n e r s w i t h a c o n c i s e and dynamic d e f i n i t i o n of t h e b a s e l i n e m i s s i o n f o r u s e a s a g u i d e l i n e and planning document. The a n t i c i p a t e d r e l e a s e d a t e ( f o r review and comment) is t h e f i r s t of August. These volumes f o l l o w t h e same g e n e r a l o u t l i n e as t h e DRMD of U P - 1 1 2 published i n May 1968 (Ref. n o t e s of Dec.-Jan.). ( ~ ~ ~ I ~ a r t i n ) �(7) E a r t h Resources Experiments Impact on UP-l/AAP-2 AAP-3A (Ref. April-May 1968, p. 39) F u r t h e r s t u d i e s have been made i n t h e d e t e r m i n a t i o n of t h e c o m p a t i b i l i t y of performing e a r t h r e s o u r c e s experiments on t h e AAP-l/AAp-2 m i s s i o n . One a r e a under i n v e s t i g a t i o n i s t h e impact of t h e s e experiments on t h e AAP-3A m i s s i o n . It was found t h a t no r e a l i n c r e a s e i n s u n l i g h t time could be expected, a l t h o u g h t h e t o t a l time a v a i l a b l e was increased s i g n i f i c a n t l y . Another a r e a i n v e s t i g a t e d was t h e impact on t h e e a r t h r e s o u r c e s experiments of cloud cover. The r e s u l t s of t h i s s t u d y from R-AERO-YT show t h a t t h e t o t a l c l e a r (< 3 cloud cover) s u n l i g h t time (DAM) a v a i l a b l e f o r e a r t h r e s o u r c e s experiments i s s e v e r e l y reduced. b. Dynamics and C o n t r o l (1) CMG Maximum Volume C o n t r o l Law (Ref. April-May 1968, p. 44) A d i g i t a l s i m u l a t i o n of t h e c o n t r o l law i s i n progress. The r e s u l t s of t h e s i m u l a t i o n thus f a r look encouraging i n t h a t t h e law provides a n i s o g o n a l d i s t r i b u t i o n of t h e i n d i v i d u a l momentum v e c t o r s w h i l e f o l l o w i n g t h e commanded momentum v e c t o r . One limitation of t h e law t h a t has been observed i s a r a t e l i m i t a t i o n on how £as t t h e cont r o l may r e a c t . This l i m i t a t i o n i s being s t u d i e d t o s e e i f i t i s of p r a c t i c a l s i g n i f i c a n c e , and i f t h i s l i m i t a t i o n i s a problem, how i t may eliminated. (DDD) (2) Revised V i b r a t i o n Data f o r t h e AAP C l u s t e r (Ref. April-May 1968, p. 44) A new v i b r a t i o n a n a l y s i s was made f o r t h e AAP Cluster. The con£ i g u r a t i o n analyzed cons i s ts of t h e CSM docked a x i a l l y and t h e LM/ATM docked r a d i a l l y t o t h e MDA/AM/SLA/OWS. The ATM/OWS s o l a r panels a r e deployed w i t h consumables aboard and experiments deployed. The new a n a l y s i s was n e c e s s a r y because of a l a r g e i n c r e a s e i n f u r n i s h e d s t i f f n e s s v a l u e s of t h e OWS s o l a r panel s u p p o r t beams. The new d a t a (~~S/Martin) were published i n memorandum R-AERO-DD-119-68. (3) S-IVB P r o p e l l a n t S l o s h (New) A s i m u l a t i o n s t u d y of a c o a s t i n g S-IVB s t a g e i s underway t o determine t h e f e a s i b i l i t y of a n engine r e s t a r t a t low propell a n t l e v e l s . Various u l l a g i n g schemes w i l l a l s o be c o n s i d e r e d . Excess i v e p r o p e l l a n t s l o s h i n g could uncover t h e s u c t i o n l i n e i n l e t and cause a r e i g n i t i o n f a i l u r e . The purpose of t h i s s t u d y i s t o d e f i n e l i m i t s on u l l a g e t h r u s t i n g , p r o p e l l a n t l e v e l s , and maneuvers. (DDS) �(4) AAP-2 and AAP-4 Nose Cone J e t t i s o n w i t h Tower J e t t i s o n Motor (Ref. Feb. Mar. 1968, p. 42) S t u d i e s of nose cone j e t t i s o n w i t h t h e tower j e t t i son motor have continued a s v e h i c l e d e f i n i t i o n becomes more complete. I n c o r p o r a t e d i n t h e more r e c e n t s t u d i e s a r e the s w i t c h t o t h e AS-203 type nose cone w i t h a c y l i n d r i c a l e x t e n s i o n , t h e d e l e t i o n of s e v e r a l p o r t s on t h e MDA, and t h e a d d i t i o n of t h e probe cover and i t s m e t e o r i t e s h i e l d . Short-term c l e a r a n c e does n 6 t appear t o be a problem. Work has continued t o i d e n t i f y t h e plume impingement p r e s s u r e s on t h e AAP-4 LM where e x i s t ing s p e c i f i c a t i o n p r e s s u r e s a r e q u i t e low. Long-term c l e a r a n c e i n t h e absence of l a r g e guidance a c t i o n s i s a d e q u a t e , b u t t h e expected maximums of guidance a c t i o n s i n c o n j u n c t i o n w i t h t h e j e t t i s o n a r e s t i l l to b e (DC) investigated. (5) A c t i v e A t t i t u d e Control (New) S i m u l a t i o n w i t h t h e d i g i t a l computer r e a c t i o n cont r o l program has r e v e a l e d a need f o r improving t h e a c c u r a c y of t h e s o l u t i o n f o r t h e a t t i t u d e e r r o r s i n long r u n s . The problem g e n e r a l l y o c c u r s when t h e i n i t i a l a t t i t u d e e r r o r s a r e v e r y l a r g e . S i n c e t h i s l e n g t h y computation i s being performed i n d o u b l e - p r e c i s i o n w i t h a m a t r i x smoothing r o u t i n e , i t has been decided t q s w i t c h t h e e x a c t computation t o one based on s m a l l a n g l e approximations when t h e e r r o r s f a l l w i t h i n a cone where such approximation i s j u s t i f i e d . On t h e g r a v i t y g r a d i e n t momentum dumping s t u d y , a d a p t a t i o n of a d i g i t a l program t o t h i s s t u d y i s proceeding on s c h e d u l e . (DGA) The major t a s k remaining i s t o add t h e c o n t r o l l a w s . c. P r o j e c t Information A p p l i c a b l e t o Many Vehicles (1) Poss i b l e AAP Payload Improvements (New) A s a means of i n c r e a s i n g payload f o r AAP, v a r i o u s 5-2 engine swaps on t h e S-IVB s t a g e s were i n v e s t i g a t e d , a l o n g w i t h subo r b i t a l s t a r t s of t h e s e r v i c e module (2 112 s t a g e s ) , S-IVB s t a g e 208, and use of t h e p a s s i v a t i o n impulse f o r c i r c u l a r i z a t i o n . The engines analyzed were 5-2104 and 5-2111, e x t r a s from t h e S - I 1 s t a g e program, Payload g a i n s f o r t h e manned miss ions ranged from a minimum and J - 2 s . of 500 pounds f o r AAP-3 t o a maximum of 4600 pounds f o r AAP-1. For t h e unmanned m i s s i o n s , payload g a i n s ranged from a minimum of 360 pounds t o a maximum of 2270 pounds f o r AAP-2. (DAP) �(2) AAP-4 P r e l i m i n a r y Rigid Body Response A n a l y s i s (New) The s t u d y of t h e AAP-4 m i s s i o n , f i r s t f l i g h t s t a g e p r e l i m i n a r y r i g i d body responses has been completed and p u b l i s h e d . Vehicle responses and bending moments were determined f o r RSS bending moment c o n d i t i o n s i n t h e presence of 95 p e r c e n t i l e n o n - d i r e c t i o n a l wind p r o f i l e s . The f l i g h t c o n d i t i o n s i n v e s t i g a t e d were March 1, q a m a x , q max, and n e a r inboard engine c u t o f f . The maximum bending moment of t h e c a s e s was 66 m i l l i o n i n c h pounds n e a r t h e S-IBIS-IVB s e p a r a t i o n p l a n e i n t h e q max c a s e (T = 68 seconds). The maximum c o n t r o l a n g l e (DC) i n c u r r e d was 6.7 d e g r e e s f o r t h e wind p r o f i l e peaking a t q max. 2. OWS O r i e n t a t i o n S t u d i e s (Ref. April-May 1968, p. 45) The computer s i m u l a t i o n has been changed t o accommodate a d i f f e r e n t method of computing t h e atmospheric d e n s i t y . The method curve f i t s d e n s i t y d a t a s u p p l i e d by R-AERO-YS f o r d i f f e r e n t d a t e s , a l t i t u d e s , and solar-geomagnetic a c t i v i t i e s . The s i m u l a t i o n i s a l s o being changed t o make p o s s i b l e t h e e v a l u a t i o n of OWS maneuvers away from t h e X-POP o r i e n t a t i o n , and i n c l u d e s t h r u s t impingement on t h e OWS and t h e s o l a r arrays. Computer s i m u l a t i o n s of s o l a r p o i n t i n g experiments have been r u n f o r p a n g l e s o t h e r t h a n z e r o and i n d i c a t e a s e v e r e c o n t r o l impulse p e n a l t y . Also t h e c o n t r o l impulse budget f o r a 220-nauticalm i l e o r b i t i n November 1970 has been o b t a i n e d . S t u d i e s t h a t i n d i c a t e a n e g l i g i b l e e f f e c t on impulse requirements when t h e a r r a y s a r e r o t a t e d t o t h e s o l a r v e c t o r have a l s o been made. (DD) 3. ATM a. V i s i b i l i t y of t h e Earth-Moon L i b r a t i o n P o i n t s from ATM (Ref. April-May 1968, p. 38) The e q u a t i o n s f o r determining t h e a n g u l a r displacement of L4 and L5 from t h e l i n e of s i g h t between t h e ATM and t h e sun have been i n c o r p o r a t e d i n t o t h e N-body deck and checked o u t . Some runs have been made on t h e deck, and i t has been determined t h a t L5 would be v i s i b l e w i t h i n t h e f i e l d of view of t h e HA0 i n s t r u m e n t on J u l y 27, 1971, from approximately 1600 hours GMT t o approximately 2400 hours GMT. L4 would be v i s i b l e on August 1 5 , 1971, a g a i n approximately between t h e hours of 1600 GMT and 24 GMT. Then L5 would a g a i n be v i s i b l e on August 26, 1971, between t h e hours of 0600 GMT and 1300 GMT. This l a s t s i g h t i n g i s o u t n e a r t h e edge of t h e f i e l d of view of t h e HA0 instrument. No more viewing w i l l be p o s s i b l e u n t i l a b o u t s i x months l a t e r f o r r e a s o n s s t a t e d i n t h e April-May p r o g r e s s r e p o r t . Work i s c o n t i n u i n g t o determine t h e e x a c t viewing times f o r t h e time p e r i o d Jan.-Feb., 1972. (DAO) �b. AAP-4 LM/ATM Unmanned Rendezvous (Ref. Feb.-Mar. 1968, p. 45) D e t a i l e d guidance and n a v i g a t i o n a l a n a l y s e s have been g e n e r a t e d f o r one and two S-IVB i g n i t i o n p r o f i l e s . This w i l l a l l o w more r e a l i s t i c APS ( a u x i l i a r y p r o p u l s i o n systems) p r o p e l l a n t budgets t o be d e f i n e d . MSC was f u r n i s h e d w i t h a s e t of t h e s e d a t a t o use i n t h e i r a n a l y s i s of t h e LM/ATN p r o p e l l a n t budgets. Work c o n t i n u e s i n t h e a r e a of low AV rendezvous t r a n s f e r maneuvers and e s t a b 1 i s h i n g i g n i t i o n c r i t e r i a f o r t h e s e t h r u s t e v e n t s . The u s e of r a d a r d a t a i n c o n j u n c t i o n w i t h t h e ST-124M p l a t f o r m looks promising a s a s o u r c e of n a v i g a t i o n update. (DG/Nor t h r o p ) c. AAP Rendezvous S i m u l a t i o n Program (New) A rendezvous s i m u l a t i o n computer i s b e i n g developed that w i l l permit simultaneous s i m u l a t i o n of (1) a t a r g e t - s a t e l l i t e s t a t e , (2) p u r s u i t - e s t i m a t e d ( n a v i g a t i o n ) s t a t e , and (3) a c t u a l s t a t e , s o t h a t d e t a i l e d a n a l y s i s of rendezvous problems can be made i n a n o r d e r l y fashion. (DG) d. P a s s i v e A t t i t u d e C o n t r o l (New) (1) A l l p e r t i n e n t e q u a t i o n s f o r , a completely g e n e r a l s i m u l a t i o n of t h e aerodynamic damping concept have been completed. The system of e q u a t i o n s c o n t a i n s t h r e e r o t a t i o n a l degrees of freedom f o r t h e main body and a n independent s i n g l e degree of freedom f o r each p a n e l . The f o r m u l a t i o n a l s o a l l o w s t h e i n s e r t i o n of a n a r b i t r a r y d i h e d r a l a n g l e f o r each p a n e l . S i n c e t h e e q u a t i o n s have been c a s t completely i n m a t r i x form, they can be e a s i l y extended t o a d d i t i o n a l d e g r e e s of freedom. (2) E f f o r t i s being expended t o d e f i n e t h e aerodynamics f o r this particular application, since data a r e not available for the main body and each of t h e panels t a k e n s e p a r a t e l y . The procedure t h a t i s being followed i s t o use f o r t h e main body t h e aerodynamic d a t a a s r e p o r t e d i n document LMSC/HREC A791488 f o r t h e workshop w i t h t h e panels r e t r a c t e d and t o u s e a s e p a r a t e model f o r t h e p a n e l s . The shortcoming of t h i s procedure i s t h a t i t w i l l n o t i n c l u d e t h e e f f e c t of "shadowing" between t h e b o d i e s . A s b e t t e r d a t a become a v a i l a b l e , t h o s e new models can be added t o t h e program. ( 3 ) A c o n s i d e r a b l e number of d i g i t a l computer runs f o r t h e " s t o r e d c o n f i g u r a t i o n " w i t h t h e p a n e l s p a r a l l e l t o t h e OWS a x i s have been made. The s i m u l a t i o n s a r e g e n e r a l l y r u n up t o 360,000 seconds of r e a l time. Both t h e s t a b i l i t y f o r v a r i o u s i n i t i a l c o n d i t i o n s and t h e e f f e c t of t h e maximum i n t e g r a t i o n i n t e r v a l on t h e s o l u t i o n a c c u r a c y a r e being studied. �( 4 ) A r o u t i n e f o r f i t t i n g t h e OWS aerodynamic d a t a t o a double F o u r i e r s e r i e s has been programmed, and i s being checked o u t . The prog ram is s e t up f o r t h e 7 0 9 4 computer. (DCA) e. ATM S t a b i l i t y and Response (New) For new A'IM bending d a t a , f i l t e r s and g a i n s have been o b t a i n e d . Parameter s t u d i e s a r e being made t o i n v e s t i g a t e t h e s t a b i l i t y and time r e s p o n s e of t h e system a s t h e bending d a t a changes. (DDD) E. Generation of Real E a r t h Model C i r c u l a r and E l l i p t i c a l O r b i t V e l o c i t y Requirements (New) Data a r e b e i n g g e n e r a t e d t o determine i n s e r t i o n v e l o c i t i e s r e q u i r e d t o a t t a i n d e s i r e d o r b i t s ( r a d i u s of p e r i g e e and apogee a l t i tude) based on t h e F i s c h e r E l l i p s o i d r a t h e r than t h e s p h e r i c a l e a r t h g r a v i t y model. For a g i v e n o r b i t , i n s e r t i o n v e l o c i t y i s a f u n c t i o n of o r b i t a l i n c l i n a t i o n and i n s e r t i o n l a t i t u d e when t h e o b l a t e e a r t h g r a v i t y model i s employed. As a r e s u l t , i n s e r t i o n v e l o c i t y i s n o t cons t a n t over t h e e a r t h ' s s u r f a c e a s assumed when u s i n g t h e s p h e r i c a l e a r t h g r a v i t a t i o n a l c o n s t a n t . For example, t h e v e l o c i t y a t p e r i g e e of a n 81 x 120 NM o r b i t based on t h e s p h e r i c a l e a r t h model i s 7 8 3 5 . 4 6 mlsec. Assuming a n o r b i t a l i n c l i n a t i o n of 28.50 and a n i n s e r t i o n l a t i t u d e of 2 7 " , a p e r i g e e v e l o c i t y of 7 8 3 8 . 4 5 m/sec i s r e q u i r e d u s i n g t h e o b l a t e e a r t h g r a v i t y model. The d i f f e r e n c e between t h e two v e l o c i t i e s i s 2.98 m/sec. I f o r b i t a l i n s e r t i o n occurs a t t h e v e l o c i t y based on a s p h e r i c a l e a r t h model, t h e apogee a l t i t u d e w i l l b e l e s s t h a n t h a t d e s i r e d . The maximum d i s p e r s i o n s from t h e s p h e r i c a l e a r t h model v e l o c i t i e s occur f o r a n i n c l i n a t i o n of 9 0 d e g r e e s . (DAP) F. S a t u r n V Launch Vehicle and S p a c e c r a f t Launch P r o b a b i l i t y (New) A c o n t r a c t e d s t u d y has been undertaken by t h e Lockheed M i s s i l e s and Space Company under the d i r e c t i o n of -DAM f o r t h e purpose of c a l c u l a t i n g t h e p r o b a b i l i t y of a s u c c e s s f u l s p a c e m i s s i o n f o r a S a t u r n V launch v e h i c l e . It i s a n t i c i p a t e d t h a t t h i s s t u d y w i l l use t h e t h e o r y of Markov P r o c e s s e s f o r m i s s i o n s i m u l a t i o n , w i t h t h e end r e s u l t b e i n g a computer program g e n e r a l enough t o be used f o r a v a r i e t y of launch (~AM/Lockheed) v e h i c l e c o n f i g u r a t i o n s and v a r i o u s m i s s i o n t y p e s . �VIII. F'LIGHT TEST ANALYSIS DIVISION A. F l i g h t Mechanics Branch 1. S a t u r n IB a. A S - ~ O ~ / C S M - LRendezvous O~ ~ i si os n A b a s i c r e v i s i o n t o t h e launch v e h i c l e o p e r a t i o n a l mode was made w i t h t h e d e c i s i o n t o f l y w i t h open-loop o p e r a t i o n of t h e S-IVB p r o p e l l a n t u t i l i z a t i o n system. This d e c i s i o n r e q u i r e s t h e r e g e n e r a t i o n of t h e nominal o p e r a t i o n a l t r a j e c t o r y , d i s p e r s i o n a n a l y s i s (S-IVB phase o n l y ) , range s a f e t y , and a b o r t and a l t e r n a t e m i s s i o n s t u d i e s . Analysis of f a i l u r e modes of t h e p r o p e l l a n t u t i l i z a t i o n (PU) s y s tem r e v e a l e d t h a t t h e primary m i s s i o n could n o t be a t t a i n e d by t h e launch v e h i c l e f o r most of t h e f a i l u r e s considbred. It was t h u s determined by Program Management t h a t i t would be p r e f e r a b l e t o commit t h e m i s s i o n t o a l e s s t h a n 30 p e r f o m a n c e margin w i t h a n open-loop PU s y s tem r a t h e r t h a n r i s k completion of t h e m i s s i o n due t o a PU f a i l u r e . The a b o r t and a 1 t e r n a t e miss i o n document r e f l e c t i n g closed-loop o p e r a t i o n of t h e p r o p e l l a n t u t i l i z a t i o n system should be published i n e a r l y August. These d a t a should g i v e c h a r a c t e r i s t i c behavior similar t o t h a t of a n open-loop system. b. AS-206/AS-207 Dual Launch The S-IB s t a g e t i l t programs were r e g e n e r a t e d by CCSD t o e l i m i n a t e a d i s c r e p a n c y i n t h e time argument. These d a t a a r e a g a i n being reviewed f o r acceptance. The AS-207 I n t e r f a c e Control Document (ICD) was modified t o r e f l e c t P&VE o r b i t a l v e n t i n g d a t a which d i d n o t a g r e e t o t h e o r i g i n a l v e n t schedule. The o p e r a t i o n a l t r a j e c t o r i e s a r e expected from CCSD i n e a r l y Augus t . 2. Saturn V D i s t r i b u t i o n of t h e f i n a l o p e r a t i o n a l t r a j e c t o r y was delayed by a n e r r o r d i s c o v e r e d i n t h e S-IVB s t a g e s i m u l a t i o n The e r r o r has been c o r r e c t e d , and t h e document should be d i s t r i b u t e d soon. �The d i s p e r s i o n a n a l y s i s , which was r e turned t o Northrop t o c o r r e c t d e f i c i e n c i e s , i s expected t o be completed on,August 1. Range S a f e t y d a t a have been forwarded t o KSC r e f l e c t i n g launch from Complex 39B. The launch was s u b s e q u e n t l y rescheduled t o Complex 39A. No update i n t u r n i n g r a t e s w i l l be recorded; however, r e v i s e d envelope t r a j e c t o r i e s have been t r a n s m i t t e d v i a magnetic t a p e . No f u r t h e r requirements from KSC a r e a n t i c i p a t e d . b. A S - 5 0 3 / ~ - ~ i si os n The o p e r a t i o n a l t r a j e c t o r y was d i s t r i b u t e d on June 20, 1968. A l l MSC c o p i e s , however, were l o s t i n t h e m a i l . T r a j e c t o r y d a t a were a v a i l a b l e t o c r i t i c a l a r e a s by means of t h e magnetic t a p e normally t r a n s m i t t e d b e f o r e document r e l e a s e . The document d i d n o t r e f l e c t t h e f o l l o w i n g changes i n hardware, s o f t w a r e d a t a , and t r a c k i n g requirements: 2 deg c a n t i n S-IC outboard e n g i n e s , aerodynamic d a t a r e v i s i o n , and i n c r e a s e d e l e v a t i o n a n g l e requirement f o r Guaymas v i s i b i l i t y ( r e q u i r e d s h i f t i n 2nd burn i g n i t i o n ) . These changes w i l l b e i n c o r p o r a t e d i n a n update t o be published by August 3 , 1968. A f u r t h e r change due t o t h e s p a c e c r a f t 4g a c c e l e r a t i o n l i m i t a t i o n w i l l n o t be r e f l e c t e d f o r s e v e r a l weeks. The v e h i c l e maximum a c c e l e r a t i o n w i l l be' reduced by a l l o w i n g a 10-second e a r l i e r shutdown of t h e S-IC c e n t e r engine. The d i s p e r s i o n a n a l y s i s w i l l b e a v a i l a b l e i n e a r l y August. E f f e c t s of t h e above changes w i l l be a s s e s s e d b e f o r e planning a n update of t h e document. c. O r b i t a l Debris The S u r v i v a l and Risk Hazard r e p o r t s f o r AS-503 have been approved and forwarded t o t h e P r o j e c t s O f f i c e f o r d i s t r i b u t i o n . B. Tracking and O r b i t a l Analysis Branch 1. Saturn I B (1) The AS-205 S-IVB p r e d i c t e d l i f e t i m e and decay r a t e s were p r e s e n t e d a t t h e G&P Subpanel h e l d a t MSC on June 19, 1968. (2) Tracking and communications a n a l y s e s f o r t h e AS-205 Abort and A l t e r n a t e Missions have been completed and w i l l be included i n t h e Abort and A l t e r n a t e Mission document. �2. Saturn V (1) TBC has d e l i v e r e d p r e l i m i n a r y l i s t i n g of t r a c k i n g s t a t i o n a c q u i s i t i o n and l o s s times f o r t h e AS-503 I'D" Mission. The formal documentation w i l l n o t be a v a i l a b l e b e f o r e e a r l y September; however, t h e p r e l i m i n a r y d a t a (Memorandum R-AERO-FT-23-68) w i l l be s u f f i c i e n t l y a c c u r a t e t o a l l o w t h e u s e r s t o make p r e l i m i n a r y a n a l y s e s . (2) Because of t h e n e c e s s a r y r e p r e s s u r i z a t i o n of t h e LM, concern developed over t h e p o s s i b i l i t y of t h e CSM/LM n o t s e p a r a t i n g from t h e S-IVB i n time t o do t h e nominal two r e s t a r t s . Requests f o r d a t a of t r a c k i n g and communication coverage i f t h e two r e s t a r t s were delayed f o r a r e v o l u t i o n were honored by TBC. These d a t a v e r i f i e d t h a t t h e coverage was n o t a v a i l a b l e f o r t h e c r i t i c a l p e r i o d s of i n t e r e s t . Tracking a c q u i s i t i o n and l o s s d a t a updating t h e RT a n a l y s i s of t h e o r b i t a l and f i r s t o p p o r t u n i t y , a s w e l l a s t h e planned second o p p o r t u n i t y , were g e n e r a t e d a t t h e r e q u e s t of I-MO, and were d i s t r i b u t e d under Memorandum R-AERO-FT-24-68. c. General 1. I n response t o Action Item 21.2(R.T.), a p r e s e n t a t i o n on t h e key-hole e f f e c t v e r s u s v a r i a b l e launch azimuth was g i v e n a t t h e G&P Subpanel Metting a t MSC on June 19, 1968. The d a t a have a l s o been d i s t r i b u t e d under Memorandum R-AERO-FT-28-68. 3. AAP a. S a t u r n I B Workshop (1) The p r i n t o u t and a n e x p l a n a t o r y memorandum were s e n t t o t h e I&C Panel on t r a c k i n g - s t a t i o n look-angle i n f o r m a t i o n f o r t h e AAP-2/0WS. S i n c e t h e look a n g l e i n f o r m a t i o n i s dependent on t h e o r i e n t a t i o n of t h e OWS which is dependent upon s e v e r a l f a c t o r s , t h e look-angle a n a l y s i s could be used a s o n l y t y p i c a l information. (2) An approximate 20 p e r c e n t d e c r e a s e i n l i f e t i m e was noted i n our l a t e s t s t u d y on t h e c l u s t e r m i s s i o n . These l i f e t i m e s were based on a n e n l a r g e d s o l a r a r r a y (approximately 40% ) on t h e OWS. The s t u d y a l s o r e f l e c t s t h e l a t e s t s o l a r d a t a , aerodynamic d a t a , i n s e r t i o n v e c t o r (220 n.mi.), ML-14 s c h e d u l e , ecc. �( 3 ) Data a r e being g a t h e r e d on t h e workshop t o a n a l y z e p o s s i b l e s o l a r r a d i a t i o n e f f e c t s on t h e o r b i t a l decay and l i f e t i m e f o r t h e c l u s t e r m i s s i o n . P r e l i m i n a r y a p p r a i s a l s i n d i c a t e t h a t t h e r e should be no major p e r t u r b a t i o n s on our previous l i f e t i m e s t u d i e s . However, s i n c e t h e p a y l o a d / a l t i t u d e t r a d e o f f s a r e q u i t e c r i t i c a l , we p l a n t o check our e a r l i e r a p p r a i s a l . b. General (1) AAP L i f e t i m e A meeting was h e l d t o determine what atmospheres should be used by t h e C e n t e r s i n AAP s t u d i e s . It was decided t h a t t h e S p e c i a l 1962 U. S . Standard Atmosphere would be used f o r l i f e t i m e s t u d i e s , and t h e MSFC modified J a c c h i a 1967 model would be used f o r o t h e r AAP s t u d i e s where atmospheric v a r i a t i o n s need t o be accounted f o r . 4. General a . A meeting was h e l d June 3 w i t h D r . Leland Cunningham a t t h e U n i v e r s i t y of C a l i f o r n i a a t Berkeley t o i n i t i a t e t h e c o n t r a c t on p a s s i v e a t t i t u d e p r e d i c t i o n . Data on t h e OWS and Pegasus A v e h i c l e s were d e l i v e r e d t o f a c i l i t a t e h i s s t u d i e s , and t h e t a s k s and d i r e c t i o n of approach t o t h e problem were d i s c u s s e d . D r . Cunningham expressed h i s f e e l i n g t h a t t h e b e s t approach t o a n a l y z i n g t h e motion of t h e OWS i s a numerical i n t e g r a t i o n program (because of t h e s m a l l magnitudes of t h e i n i t i a l a n g u l a r r a t e s of t h e OWS). Under previous work done f o r MSFC, D r . Cunningham developed a numerical i n t e g r a t i o n program t o a n a l y z e t h e a t t i t u d e motion of Pegasus A; however, MSFC d i d n o t r e q u i r e documentation of t h i s program. T h e r e f o r e , i t was decided t h a t i n i t i a l e f f o r t on t h i s c o n t r a c t would b e d i r e c t e d toward documenting t h i s program and a d a p t i n g i t t o perform a n a l y s e s on t h e OWS. I f a v e r a g i n g techniques l a t e r appear t o be a usef u l approach t o t h e p a s s i v e OWS a n a l y s i s , then t h e numerical i n t e g r a t i o n program w i l l be used t o v e r i f y t h e average s o l u t i o n s . b. A program w r i t e u p has been r e c e i v e d from NSL on t h e Automatic Experiment Scheduling and O p t i m i z a t i o n Program (AESOP). Copies w i l l be d i s t r i b u t e d t o v a r i o u s Aero-Astrodynamic Laboratory personnel a f t e r t h e document has been reviewed. We s t i l l have some problems i n g e t t i n g t h e program t o r u n on t h e Univac 1108; however, we f e e l t h e s e a r e n o t unsolvable problems. �c. M r . H. Hufnagel, R-ASTR-BE, r e q u e s t e d i n f o r m a t i o n on ground-tracking i n s t r u m e n t a t i o n a c c u r a c i e s . M r . Hufnagel i s a member of t h e E l e c t r o n i c T r a j e c t o r y Measurements Working Group which is under t h e Inter-Range I n s t r u m e n t a t i o n Group Range Commanders Council. He was i n t e r e s t e d i n t h e a c c u r a c i e s of t h e v a r i o u s r a d a r measurements (range, aximuth, e l e v a t i o n , e t c . ) f o r USB and C-Band r a d a r s . We gave him t h e t a b l e s of a c c u r a c i e s from t h e Apollo Navigation Working Group Technical Report No. AN-1.3, dated December 1 5 , 1967, and informed him that t h e s e a c c u r a c i e s met t h e ,launch t r a j e c t o r y and o r b i t r e c o n s t r u c t i o n r e q u i r e ments f o r p o s t f l i g h t e v a l u a t i o n . He was a l s o informed t h a t contitluous coverage w i t h some redundancy was r e q u i r e d d u r i n g t h e launch phase. d . D r . H. 3 . Zimmennan, D i r e c t o r of t h e I n s t i t u t e f o r S c i e n t i f i c Research i n Aachen, Germany, has r e q u e s t e d a copy of t h e p a p e r , "A Mathematical Programming Approach t o t h e Scheduling of Experiments i n Space," co-authored by M r . Fleischman and p r e s e n t e d a t t h e TIMS Meeting i n San Francisco. - C. F l i g h t E v a l u a t i o n Branch 1. S a t u r n LB a. S-IVB Workshop R-ASTR-IE has developed a new measurement l i s t f o r d a t a t r a n s m i s s i o n a f t e r L+7 hours on t h e S-IVB Workshop. Except f o r l i n e a r a c c e l e r a t i o n d a t a , our i n s t r u m e n t a t i o n r e q u e s t i s s a t i s f i e d . Horizon s e n s o r d a t a f o r determining a t t i t u d e w i l l b e recorded on t a p e a t a sample r a t e of 1.25 samples/sec. A t t i t u d e c o n t r o l engine d a t a w i l l n o t be recorded on t a p e , b u t i t w i l l be t e l e m e t e r e d c o n t i n u o u s l y . R-P&VE i s a t t e m p t i n g t o have a t e l e m e t r y package added which w i l l i n c l u d e l i n e a r accelerometer data. A d i s c r e p a n c y was found between i n f o r m a t i o n concerning p a s s i v a t i o n i n t h e AS-204 FEWG Report and t h e AS-204 T r a j e c t o r y Report. The cause of t h e d i s c r e p a n c y was found t o be a gap i n t h e d a t a used t o determine t h e a c c e l e r a t i o n p r o f i l e p r e s e n t e d i n .the T r a j e c t o r y Report. A d d i t i o n a l d a t a were o b t a i n e d , and a n a l y s i s y i e l d e d r e s u l t s which agreed v e r y f a v o r a b l y w i t h t h e FEWG Report. Memorandum R - A E R O - F F - ~ ~ - ~ ~ p r e s e n t s t h e r e v i s e d d a t a . S t e p s have been t a k e n t o a s s u r e t h a t t h e r e w i l l be no d a t a gaps d u r i n g p e r i o d s of o r b i t p e r t u r b i n g a c t i v i t y (passivation, etc.) i n the future. �c. S a t u r n I B 6-D T r a j e c t o r y Simulator The o b j e c t i v e of t h i s program is t o develop a S a t u r n I B t r a j e c t o r y s i m u l a t o r i n s i x degrees of freedom that runs from guidance r e f e r e n c e r e l e a s e through a l l powered f l i g h t and o r b i t a l phases t o t h e p o i n t of s p a c e c r a f t s e p a r a t i o n . This program i s intended t o f u l f i l l our requirements f o r p r e f l i g h t and p o s t f l i g h t s t u d i e s on t h e I B v e h i c l e . The r e q u i r e d c a p a b i l i t y i s a complete six-degrees-of-freedom t r a j e c t o r y , a closed-loop guidance system, and closed-loop c o n t r o l f i l t e r s . The s t a t u s of t h e s e c a p a b i l i t i e s i n t h e program i s a s follows: (1) Complete six-degrees-of-freedom: A six-degrees-offreedom t r a j e c t o r y g e n e r a t e d from guidance r e f e r e n c e r e l e a s e through a l l powered f l i g h t phases i s implemented i n t h e S a t u r n I B deck. The c a p a b i l i t y t o s i m u l a t e t h e o r b i t a l f l i g h t of t h e S-IVB s t a g e a f t e r i n s e r t i o n u n t i l s p a c e c r a f t s e p a r a t i o n i s being developed. (2) Closed-loop c o n t r o l f i l t e r s : The complete c l o s e d loop c o n t r o l f i l t e r system of t h e S a t u r n I B v e h i c l e has been implemented i n t o t h e S a t u r n I B 6-D program. ( 3 ) Closed-loop guidance: The i t e r a t i v e guidance scheme a s implemented i n t h e onboard S a t u r n I B guidance computer has been i n c o r p o r a t e d i n t o t h e I B program i n closed-loop from guidance r e f e r e n c e r e l e a s e t o f i r s t S-IVB c u t o f f . The guidance e q u a t i o n s , which w i l l s i m u l a t e parking o r b i t u n t i l s p a c e c r a f t s e p a r a t i o n and w i l l a l s o have t h e c a p a b i l i t y f o r a c c e l e r o m e t e r f a i l u r e c a s e s and v e c t o r updates t o t h e o r b i t a l n a v i g a t i o n s y s tem, a r e being implemented i n t h e deck. 2. Saturn V b \ a. C l u s t e r e d Engine A n a l y s i s Computer Graphics A p p l i c a t i o n An SSR was submitted t o t h e Boeing ~ o m p a n y / ~ u n t s v i l l e t o i n v e s t i g a t e t h e advantages of u s i n g a g r a p h i c s d i s p l a y computer program on t h e c l u s t e r e d - e n g i n e s i m u l a t i o n method of a n a l y s i s . The g r a p h i c d i s p l a y c a p a b i l i t y could reduce t h e manpower requirements and s h o r t e n t h e turn-around time on s t a g e e v a l u a t i o n s . This method of e v a l u a t i o n computes p r o p u l s i o n and t r a j e c t o r y d a t a i n t h e u s u a l manner, b u t i t g r a p h i c a l l y d i s p l a y s prime parameters on a s c r e e n f o r o b s e r v a t i o n w h i l e r e t a i n i n g computer d a t a . The e n g i n e e r performing t h e a n a l y s i s can make adjustments t o p r o p u l s i o n parameters on the s p o t , and immediately s e e g r a p h i c a l l y t h e r e s u l t s of h i s a d j u s t m e n t s . I f t h e r e s u l t s a r e n o t a s he expected, he can add a d d i t i o n a l adjustments o r he can go back t o t h e o r i g i n a l d a t a and t r y completely new a d j u s t m e n t s , s i n c e b o t h t h e o r i g i n a l and a d j u s t e d d a t a a r e r e t a i n e d i n t h e computer. This procedure can be -epeated u n t i l h i s a n a l y s i s i s s a t i s f a c t o r y . Supposedly, t h e complete �a n a l y s i s can be performed w i t h o u t g e t t i n g o f f of t h e computer; a c t u a l l y , t h i s much s u c c e s s may n o t be a c h i e v e d . However, r e l a t i v e t o the time involved i n performing t h e a n a l y s i s a s it i s being done now, i t would appear t h a t a manpower s a v i n g s and a q u i c k e r turn-around time can be accomplished i f t h e g r a p h i c s d i s p l a y c a p a b i l i t y can be a p p l i e d t o t h e p r o p u l s i o n s i m u l a t i o n method. The c o s t of t h e SSR w i l l involve o n l y e x t r a computer h o u r s ; no a d d i t i o n a l manpower i s needed. b. SD-53 Guidance An e r r o r a n a l y s i s of t h e strapdown guidance i n e r t i a l measuring u n i t (IMU) has been done. The e r r o r model f o r t h e i n d i v i d u a l i n e r t i a l s e n s o r s i s e s s e n t i a l l y t h e same a s t h a t f o r i n s t r u m e n t s mounted on a gimbaled system. However, t h e e f f e c t s a r e n o t t h e same i n terms of a c c e l e r a t i o n e r r o r f e d i n t o t h e guidance computer. The strapdown a c c e l e r ometer measures a n g u l a r motion from t h e a c c e l e r o m e t e r o u t p u t s . Theref o r e , gyro e r r o r s , i n s t e a d of m i s a l i g n i n g t h e a c c e l e r o m e t e r measuring d i r e c t i o n a s f o r a gimbal system, r e s u l t i n erroneous a d j u s t m e n t s of t h e accelerometer outputs. c. AS-503 Abort and A l t e r n a t e Mission A n a l y s i s (1) Ground Rules - Complete. - (2) GFD Complete e x c e p t f o r v e r i f i c a t i o n of t h e S-11 s t a g e "Pu f a i l u r e t o t h e low s t o p f f p r o p u l s i o n p r e d i c t i o n c a s e . (3) Analysis S t a t u s (a) The document d e l i v e r y d a t e i s August 30, 1968. (b) The nominal t r a j e c t o r y has been g e n e r a t e d , and a few of t h e f a i l u r e c a s e s a r e b e i n g s t u d i e d . Two of t h e f a i l u r e c a s e s f o r which p r e l i m i n a r y t r a j e c t o r i e s have been g e n e r a t e d a r e : (1) "X" and "Z" a c c e l e r o m e t e r f a i l u r e s : Only s i n g l e a c c e l e r o m e t e r f a i l u r e s a r e being s t u d i e d . There appear t o b e problems i n r e a c h i n g t h e d e s i r e d e a r t h parking o r b i t should a n "X" a c c e l e r o m e t e r f a i l d u r i n g S-IC burn. The problems seem t o be r e l a t e d t o a n t n c o m p a t i b i l i t y between p r o p u l s i o n d a t a and t h e backup a c c e l e r o m e t e r presettings. F u r t h e r a n a l y s i s w i l l be made b e f o r e changes can be recommended. (2) S - I 1 p r o p e l l a n t u t i l i z a t i o n v a l v e f a i l u r e : The p r e l i m i n a r y c a s e s i n d i c a t e t h a t a f a i l u r e of t h e v a l v e a t 90 p e r c e n t t h r u s t t o t h e n u l l o r low "step" p o s i t i o n would r e q u i r e a n extended S-IVB burn t o r e a c h e a r t h parking o r b i t . The "range v e r s u s time" p l o t i n d i c a t e s that f o r a n e a r l y PU v a l v e f a i l u r e t h e v e h i c l e w i l l be r e q u i r e d t o "dive" t o g e t t o t h e d e s i r e d range a t i n s e r t i o n i n t o e a r t h parking o r b i t . These �p r e l i m i n a r y t r a j e c t o r i e s must be checked o u t b e f o r e a f i r m s t a t e m e n t can be made. (c) I-MO has r e q u e s t e d t h a t t h e following f a i l - u r e c a s e s be s t u d i e d : (1) S-IVB 2nd and 3rd burns w i t h t h e LEM a t t a c h e d and t h e p a n e l s detached. (2) S-IVB contingency burn w i t h t h e LEM a t t a c h e d and t h e panels detached. Data n e c e s s a r y t o compute t r a j e c t o r i e s corresponding t o Lllese f a i l u r e s have been o b t a i n e d and t h e c o n t r a c t o r (TBC) has agreed t o a "no c o s t I-MO would l i k e t o have t h e s e t r a j e c t o r i e s o r schedule impact extended t o 3 hours a f t e r S-IVB f i n a l c u t o f f (where t h e f i n a l c u t o f f r e f e r s a l s o t o e a r l y S-IVB c u t o f f s ) . A f t e r d i s c u s s i o n s were h e l d w i t h t h e c o n t r a c t o r (TBC) concerning t h e extended t r a j e c t o r i e s , i t was decided t h a t t h i s a d d i t i o n a l work would be done in-house. ." (d) I-MO a l s o r e q u e s t e d an S-111s-IVB d i r e c t s t a g i n g t r a j e c t o r y w i t h t h e LET remaining a t t a c h e d t o t h e S-IVB s t a g e . I-MO s t a t e d t h a t t h e r e was some disagreement between o r g a n i z a t i o n s w i t h i n MSC concerning t h e type of a b o r t r e q u i r e d should S - I 1 i g n i t i o n f a i l t o occur b e f o r e t h e "100 s e c - 300,000 f t a b o r t f r e e f a l l l i m i t l i n e " i s reached. The Abort and A l t e r n a t e Mission a n a l y s i s uses a "six-degrees-of-freedom r i g i d body" s e t of e q u a t i o n s of motion; t h e r e f o r e , t h e s t a b i l i t y a n a l y s i s must be made u s i n g o t h e r t o o l s . R-ASTR-I, c o n t a c t e d concerning t h e s t a b i l i t y a s p e c t , s t a t e d t h a t a n a n a l y s i s which i s a p p l i c a b l e t o t h i s problem was made u s i n g e a r l y AS-504 v e h i c l e mass The 504 a n a l y s i s r e v e a l e d t h a t t h e S-IVB w i t h tower and p r o p u l s i o n d a t a . on was only m a r g i n a l l y s t a b l e and t h e recommendation was t o j e t t i s o n t h e LET w i t h i n 1 0 seconds of S-IVB i g n i t i o n time. They p l a n t o do a n up-tod a t e a n a l y s i s of t h e AS-503 v e h i c l e w i t h i n t h e n e x t two weeks. d. AS-504 and 505 Abort and A 1 t e r n a t e Mission A n a l y s i s Ground r u l e s a r e being reviewed, and t h e GFD i s comp l e t e except f o r dual-engine-failure propulsion data. The d e l i v e r y d a t e f o r t h e a n a l y s i s document i s October 18, f o r 504, and December 9 f o r 505. �e . Navigation Update Analys i s An SSR was g i v e n t o TBC f o r t h i s s t u d y on June 28 and t h e a n a l y s i s r e s u l t s a r e scheduled f o r d e l i v e r y September 30. The AS-504 r e f e r e n c e t r a j e c t o r y w i l l be used f o r t h i s s t u d y . f. AS-501 P o s t f l i g h t T r a j e c t o r y NASA TM X-53746, e n t i t l e d "Saturn AS-501 P o s t f l i g h t Lrajeccory," has been p u b l i s h e d . The AS-502 t r a j e c t ~ r yr e p o r t , b e i n g done by The Boeing Company, w i l l be ready f o r d i s t r i b u t i o n i n August. g. ' S a t u r n V 6-D T r a j e c t o r y Simulator The o b j e c t i v e of t h i s program is t o develop a S a t u r n V t r a j e c t o r y s i m u l a t o r i n s i x degrees of freedom t h a t runs from guidance r e f e r e n c e r e l e a s e through a l l powered f l i g h t , t h e parking o r b i t , and w a i t i n g o r b i t phases of t h e l u n a r t r a j e c t o r y . This program i s intended t o f u l f i l l requirements f o r p r e f l i g h t and p o s t f l i g h t s t u d i e s on t h e Saturn V vehicle. The r e q u i r e d c a p a b i l i t y i s a complete s i x - d e g r e e s of-freedom t r a j e c t o r y , a closed-loop guidance system, a closed-loop p r o p e l l a n t u t i l i z a t i o n system, a closed-loop p r o p u l s i o n system, and closed-loop c o n t r o l f i l t e r s . The s t a t u s of t h e s e c a p a b i l i t i e s i n t h e program i s a s follows: (1) Complete s i x degrees of freedom: A complete s i x degrees-of-freedom t r a j e c t o r y has been g e n e r a t e d from guidance r e f e r e n c e r e l e a s e through a l l powered f l i g h t , t h e parking o r b i t , and t h e w a i t i n g o r b i t phases of t h e l u n a r t r a j e c t o r y . (2) Closed-loop c o n t r o l f i l t e r s : The complete c l o s e d loop c o n t r o l f i l t e r system of t h e S a t u r n V v e h i c l e i n each phase of powered f l i g h t has been implemented i n t o t h e S a t u r n V 6-D program. (3) Closed-loop guidance: The i t e r a t i v e guidance scheme implemented i n t h e onboard S a t u r n V guidance computer has been i n c o r p o r a t e d i n t o t h e S a t u r n V 6-D program i n closed-loop f r o m guidance r e f e r e n c e r e l e a s e t o f i r s t S-IVB c u t o f f . The guidance e q u a t i o n s which s i m u l a t e t h e parking o r b i t , r e s t a r t p r e p a r a t i o n , r e s t a r t , second powered f l i g h t , and w a i t i n g o r b i t have been p r e p a r e d , and a r e being implemented i n t h e deck. ( 4 ) Closed-loop p r o p u l s i o n s i m u l a t i o n s y s tern and closed-loop p r o p e l l a n t u t i l i z a t i o n system: The closed-loop PSM i s being developed i n a p a r a l l e l 6-D program. When d e c l a r e d o p e r a t i o n a l , i t w i l l b e t r a n s f e r r e d t o t h e 6-D program. C o n t r a c t NAS8-21160, which was completed on January 12, 1968 by O R I , provided t h e p o t e n t i a l a b i l i t y f o r closed-loop p r o p u l s i o n s i m u l a t i o n . The PSM provided by �O R 1 was n o t completely u s a b l e because s e v e r a l r e f i n e m e n t s were needed. S i n c e t h e above d a t e , in-house e f f o r t s t o make t h e PSM o p e r a t i o n a l have r e s u l t e d i n t h e following: - The complete c o n t r o l f i l t e r ( a ) Control F i l t e r s s i m u l a t i o n needed f o r a S a t u r n V v e h i c l e can now b e used w i t h t h e PSM. Machine core s t o r a g e problems i n t h i s a r e a have been s o l v e d . - (b) Mass D i s c o n t i n u i t i e s These a r e now handled a c c u r a t e l y . The PSM c o n s i d e r s t h e proper d i s c o n t i n u i t y i n t h e c e n t e r of g r a v i t y and moment of i n e r t i a computations. - For a more r e a l i s t i c (c) P r e s s u r i z a t i o n Tables s i m u l a t i o n of d i s p e r s i o n c a s e s (engine o u t , e t c . ) , p r e s s u r i z a t i o n t a b l e s a r e now i n p u t a s a f u n c t i o n of s t a g e mass l o s s i n s t e a d of s t a g e f l i g h t time . Before t h e PSM can be used i n s i m u l a t i o n s , t h e following o b j e c t i v e s must be completed: ( a ) The v a l i d i t y of t h e S-IVB p r o p e l l a n t u t i l i z a t i o n model must be v e r i f i e d . Some q u e s t i o n s a b o u t t h e completeness of t h e e q u a t i o n s have been r a i s e d . I (b) The PSM must b e demonstrated i n a continuous s i m u l a t e d f l i g h t from guidance r e f e r e n c e r e l e a s e through f i n a l S-IVB burn. This i n v o l v e s e s t a b l i s h i n g a nominal PSM g e n e r a t e d t r a j e c t o r y t h a t w i l l compare c l o s e l y w i t h a n o p e r a t i o n a l t r a j e c t o r y . C o n t r a c t NAS8-21467 w i t h O R 1 was l e t June 20, 1968, t o accomplish t h e two above o b j e c t i v e s . E f f o r t on t h e 7-month c o n t r a c t was i n i t i a t e d J u l y 1 7 , 1968 when OR1 met w i t h R-AERO-F, R-COMP, and CSC representatives. h. AS-503 Control The AS-503 wind launch c r i t e r i a document r e c e i v e d from TBC i s b e i n g reviewed b e f o r e p u b l i c a t i o n of t h e wind l i m i t s memorandum. The i n f l i g h t wind speed l i m i t s f o r t h e AS-503 "D" (wind b i a s e d t r a j e c t o r y ) a t t h e most c r i t i c a l a l t i t u d e (10 km) a r e 103 m/sec, 45 mlsec, and 29 m/sec f o r t a i l w i n d , crosswind, and headwind, r e s p e c t i v e l y , f o r a f a c t o r of s a f e t y of 1.4. Outboard engine c a n t was n o t c o n s i d e r e d ; however, i t i s n o t a n t i c i p a t e d that t h i s c a n t w i l l degrade t h e wind c a p a b i l i t y due t o reduced c o n t r o l a u t h o r i t y o r s t r u c t u r a l i n t e g r i t y . �3. General S t u d i e s The s t u d y c o n t r a c t NAS8-21289, e n t i t l e d " S t u d i e s i n t h e Theory and A p p l i c a t i o n of Kalman F i l t e r i n g , " was awarded to.UNIVAC. The p r i n c i p a l i n v e s t i g a t o r , M r . L. Teng, is l o c a t e d i n H u n t s v i l l e f o r t h e d u r a t i o n of t h e c o n t r a c t . The m a j o r e f f o r t t o d a t e h a s i n v o l v e d g a t h e r i n g i n £ o r m a t i o n and s t u d y i n g t h e d e v i a t i o n s of t h e Kalman f i l t e r and s i m i l a r methods. P a r t i c u l a r emphasis h a s b e e n p l a c e d on t h e assumpt i o n s r e q u i r e d by t h e v a r i o u s methods and d e r i v a t i o n s and how w e l l o u r p a r t i c u l a r problem c a n s a t i s f y t h e s e a s s u m p t i o n s . PUBLICATIONS 1. H a u s s l e r , J. and C . L. Varnado, " S a t u r n AS-501 P o s t light T r a j e c t o r y , " NASA TM X-53746, J u n e 1 8 , 1968, U n c l a s s i f i e d . 2. Lovingood, J . , 11Dynamical Polys ys tems as G e n e r a l i z a t i o n s o f C o n t r o l Systems," NASA TM X-53750, J u n e 26, 1968, U n c l a s s i f i e d . 3. Vaughan, W. W. and M. Susko, "Accuracy of Wind Data Obtained b y T r a c k i n g a J i m s p h e r e Wind S e n s o r S i m u l t a n e o u s l y by Two FPS-Radars," NASA TM X-53752, J u l y 5 , 1968, U n c l a s s i f i e d . 4. Heybey, W. H . , "Wind V e c t o r C a l c u l a t i o n s Using Crossed-Beam Data and D e t e c t o r Arrangement f o r Measuring H o r i z o n t a l Winds , I ' NASA TM X53754, J u l y 11, 1968, U n c l a s s i f i e d . 5. Buchannan, H. J . , "Drag on F l a t P l a t e s O s c i l l a t i n g i n I n c o m p r e s s i b l e F l u i d s a t Low Reynolds Numbers," NASA TM X-53759, J u l y 22, 1968, Unclass i f i e d . 6. - Gold, R i c h a r d , "Nonper i a p s i s t o - P e r i a p s i s T a n g e n t i a l T r a n s f e r s i n t o O r b i t s About Venus, Mars, and J u p i t e r , " Aero-Astrodynamics I n t e r n a l Note R-AERO-IN-68-3, J u l y 1 9 , 1968, U n c l a s s i f i e d . �APPROVAL ~ e t e~ i ue f , Aero-As trodynamics L a b o r a t o r y ero-As trodynamics L a b o r a t o r y DISTRIBUTION R-AERO-DIR Dr. Geisslei M r . Jean Mr. B u t l e r R-AERO-R M r . B e a n (4) Mrs. Hightower R- AERO- T Mr. Murphree Mr. Curnmings Dr. Heybey Mr. J a n d e b e u r Dr. Krause Mr. N a t h a n Mr. Few M r . von P u t t k a m e r R-AERO-P R-AERO-D R-AERO-G R-AERO-Y R-AERO-F R-AERO-X (8) (16) (6) (8) (8) (4) PAO, M r . K u r t z R-DIR, M r . W e i d n e r MS-H, I-V-P, M i s s J e r r e l l (3) Mr. Price � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000038 Title A name given to the resource "Aero-Astrodynamics Laboratory Bimonthly Progress Report: June - July 1968." Description An account of the resource Includes Technical and Scientific Staff; Advanced Studies Office; Projects Office; Aerospace Environment Division; Aerophysics Division; Astrodynamics and Guidance Theory Division; Dynamics and Flight Mechanics Division; Flight Test Analysis Division. Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center Date A point or period of time associated with an event in the lifecycle of the resource 1968-08-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) NASA space programs Project management Type The nature or genre of the resource Progress reports Text Source A related resource from which the described resource is derived Saturn V Collection Box 27, Folder 37 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050 https://digitalprojects.uah.edu/files/original/20/986/spc_stnv_000039.pdf 5e7da3535c0a89679f8e94a53f2cbe72 PDF Text Text AERO-ASTRODYNAMICS LABORATORY BIMONTHLY PROGRESS REPORT April-May 1968 INDEX Page ADVANCED STUDIES OFFICE . I1 ................................... ............................ ........................... .............................. ..................... ........................ AEROSPACE ENVIRONMENT DIVISION Environment Research O f f i c e A Space Environment Branch B C Environmental A p p l i c a t i o n s Branch D T e r r e s t r i a l Environment Branch . . . . AND GUIDANCE THEORY DIVISION ................ . ASTRODYNAMICS A . Astrodynamics Branch .................................. I11 ................................ ............................ PROJECTS OFFICE ........................................... V. AEROPHYSICS DIVISION ...................................... A . Mechanical Design O f f i c e .............................. B . Design Branch ......................................... C . Experimental Aerophysics Branch ....................... D . Thermal Environment Branch ............................ E . Unsteady Aerodynamics Branch .......................... V I. DYNAMICS AND FLIGHT MECHANICS DIVISION .................... A . M u l t i - P r o j e c t s ........................................ B . S a t u r n V .............................................. C . AAP ................................................... VII. FLIGHT TEST ANALYSIS DIVISION ............................. A . S p e c i a l P r o j e c t s O f f i c e ............................... B . F l i g h t Mechanics Branch ............................... C . Tracking and O r b i t a l A n a l y s i s Branch .................. D . F l i g h t E v a l u a t i o n Branch .............................. B C . . Guidance Theory Branch O p t i m i z a t i o n Theory Branch 1 �AERO-ASTRODYNAMICS LABORATORY BIMONTHLY PROGRESS REPORT April-May 1968 I. ADVANCED STUDIES OFFICE A. Miss i o n A n a l y s i s and A s trodynamics Group 1. Unmanned P l a n e t a r y Mission d e s i g n c h a r t s f o r t h e 1975 Mars o p p o r t u n i t y a r e being developed f o r type I and I1 h e l i o c e n t r i c p r o f i l e s . These d a t a w i l l be used t o determine s p a c e c r a f t s i z i n g and Mars' c a p t u r e o r b i t selection. The o v e r a l l unmanned p l a n e t a r y a c t i v i t y a t MSFC has been c u r t a i l e d f o r t h e l a s t month s i n c e M r . J i m Belew has been a s s i g n e d a s c h i e f o f t h e Lunar Group i n t h e ASO, and a replacement t o d i r e c t t h e unmanned p l a n e t a r y e f f o r t has n o t been d e s i g n a t e d . 2. S-IB, T i t a n Performance and Miss i o n C a p a b i l i t y Comparison This o f f i c e has g e n e r a t e d d a t a which w i l l d e p i c t t h e p e r formance and miss i o n payload c a p a b i l i t y comparison f o r the f o l l o w i n g launch v e h i c l e c o n f i g u r a t i o n s : + Centaur as upper s t a g e + SM a s upper s t a g e (1) S-IB (2) S-IB (3) T i t a n 111 D (4) T i t a n 111 C . + Centaur a s upper s t a g e These d a t a w i l l be included i n t h e m a t e r i a l f o r D r . von ~ r a u n ' sp r e s e n t a t i o n t o M r . Webb on t h e f u t u r e r o l e of t h e S-IB and T i t a n 111 launch vehicle. Documentation of t h e performance and m i s s i o n c a p a b i l i t y d a t a w i l l be a v a i l a b l e i n a memorandum. �3. JPL Double P r e c i s i o n T r a j e c t o r y Program (DPTRAJ) A meeting was h e l d a t JPL on A p r i l 16, 1968, (1) t o f a m i l i a r i z e f u t u r e u s e r s of t h e DPTRAJ w i t h t h e c a p a b i l i t y and development o u t l i n e , and (2) t o d i s c u s s t h e p o t e n t i a l problems of a d a p t i n g t h e program t o t h e UNIVAC 1108 computer system. Messrs. Bob E l l i s o n (R-AERO-X), Reynolds Duncan (R-AERO-G) and P e t e Boykin (CSC) a t t e n d e d from MSFC. The DPTRAJ w i l l be r e l e a s e d a t d i f f e r e n t phases of development. The phase I program, which has o r b i t - t r a c k i n g c a p a b i l i t y , i s b e i n g s e n t f a MSFC'S Computation Laboratory t h e week of June 3 , 1968. 4. S a t u r n V Workshop MSFC'S documentation of t h e three-month NASA Space S t a t i o n planning s t u d y , now i n f i n a l form, i s being reviewed by t h e Advance S t u d i e s Off i c e , Chief of R-AERO, R-ASTR and R-P&VE Continued e f f o r t w i l l i n v o l v e (1) f i n a l rendezvous and docking p r o f i l e a n a l y s i s , (2) space-s t a t i o n crew r e s c u e modes and t h e i r implementation, and ( 3 ) atmospheric e n t r y a n a l y s i s t o d e f i n e e n t r y c o r r i d o r s and s u r f a c e f o o t p r i n t a r e a s . B. F l i g h t Mechanics and Performance A n a l y s i s Group The problems and manpower requirements a s s o c i a t e d w i t h t h e i n t e g r a t i o n of t h e CSM o n t o t h e T i t a n 111 M a r e b e i n g a n a l y z e d . Before t h e T i t a n I11 could be used f o r manned f l i g h t by NASA, i t would be n e c e s s a r y t o r u n some q u a l i f i c a t i o n s s t u d i e s i n t h e f i e l d s of a e r o dynamics, thermodynamics, f 1i g h t mechanics, guidance, c o n t r o l and v e h i c l e dynamics. This o f f i c e i s s u p p o r t i n g t h e p r e s s u r e - f e d launch v e h i c l e study, d i r e c t e d by M r . Laue, and t h e S a t u r n u t i l i z a t i o n s t u d y . General f l i g h t mechanical s t u d i e s w i t h r e s p e c t t o s t a g e s i z i n g , module s i z e , and o v e r a l l performance e v a l u a t i o e a r e i n p r o g r e s s . C. Systems A n a l y s i s Group 1. The t e c h n i c a l i m p l i c a t i o n s of c o n v e r t i n g AS-210 t o a S a t u r n V launched m i s s i o n w h i l e r e t a i n i n g i t s S a t u r n I Workshop backup s t a t u s a r e b e i n g e v a l u a t e d . The i n i t i a l s t e p i s a n assessment of t h e impact of t h i s Light payload (= 63,500 l b s ) on t h e launch v e h i c l e , a s w e l l a s t h e impaet of t h e S a t u r n V launch environment on t h e workshop. P r e l i m i n a r y t r a j e c t o r y and aerodynamic d a t a f o r t h i s c o n f i g u r a t i o n have been g e n e r a t e d , . �A wind r e s p o n s e a n a l y s i s has been completed, and t h e r e s u l t i n g c o n t r o l data have been t r a n s m i t t e d t o R-P&VE-AV f o r load c a l c u l a t i o n s . The l o a d s d a t a on t h e workshop have been s e n t toMSC f o r t h e i r assessment of t h e impact on t h e workshop. The impact of t h e l i g h t payload on t h e launch v e h i c l e s t r u c t u r e w i l l be e v a l u a t e d a t M a r s h a l l . 2. The Boeing Company has begun f a b r i c a t i o n of a low c o s t p r e s s u r e - f e d "Ground Demonstration Stage" (GDS). The 8 112-foot diameter s t a g e i s t o be mated w i t h t h e TRW s c a l e d - u p LEMDE engine. T h r u s t of t h e TRW engine i s 250,000 pounds, f i r i n g d u r a t i o n is t o be 120 seconds, p r o p e l l a n t s a r e N204/U~MH, t a n k s t r u c t u r e i s HY 140 s t e e l , t a n k p r e s s u r e i s 390 p s i , and engine p r e s s u r e i s 300 p s i . The p r e s s u r i z a t i o n scheme f o r t h e GDS c o n s i s t s of p a s s i n g H202 over a c a t a l y s t f o r t h e N,94 tank p r e s s u r e and UDMH over a c a t a l y s t f o r the UDMH tank p r e s s u r e . T e s t t a r g e t d a t e i s November 1968. 11, AEROSPACE ENVIRONMENT DIVISION A. Environment Research O f f i c e 1. M r . 0. H. Vaughan reviewed Surveyor program r e p o r t s and o t h e r l i t e r a t u r e on t h e l u n a r s u r f a c e and environment. Also, d i s c u s s i o n s were h e l d w i t h D r . C. Wys, of JPL, a b o u t h i s M a r t i a n S u r f a c e Monograph. L i t e r a t u r e surveys of t h e thermal environment of Mercury and Mars c o n t i n u e d . 2. M r . Dalton has surveyed many books, r e p o r t s , and papers f o r p o s s i b l e r e l a t i o n t o h i s comparative a n a l y s i s of two sub-samples of 333 s p o r a d i c photographic meteors ( s e l e c t e d f o r minimum a b s o l u t e magnitude h y p o t h e t i c a l l y s c a l e d f o r escape v e l o c i t y by a l t e r n a t i v e f r o m u l a t i o n s of luminous e f f i c i e n c y ) The o u t 1 i n e f o r t h i s a n a l y s i s was p r e s e n t e d by M r . Dalton at: t h e Research Achievements Review h e r e on September 28 (NASA Technical Memorandum X-53706). About one hundred of t h o s e which were s t u d i e d were found t o be p e r t i n e n t r e f e r cnccs f o r t h i s purpose. This e f f o r t has been r e s t r i c t e d t o n o t more t h a n h a l f of M r . ~ a l t o n ' s r e g u l a r hours t o i n s u r e a more a c t i v e involvement i n b r o a d e r a r e a s of s p a c e p h y s i c s , mathematics and s t a t i s t i c s , and a e r o s p a c e environment r e s e a r c h . . 3. Atmospheric Research F a c i l i t y During t h i s p e r i o d , 100 rawinsonde f l i g h t s were made by t h e MSFC Atmospheric Research F a c i l i t y . A l l b u t f o u r of t h e s e f l i g h t s were made i n s u p p o r t of t h e s t a t i c f i r i n g s conducted by T e s t Laboratory. �The CPS-9 Weather Radar has been down a g r e a t d e a l of t h e time d u r i n g t h i s r e p o r t i n g p e r i o d . S e v e r a l u n i t s developed t r o u b l e s which seemed t o s p r e a d throughout t h e system. Major problems occurred w i t h t h e magnatron, p u l s e c a b l e and p u l s e c a p a c i t o r , and t h e p u l s e t r a n s f o r m e r and t h e d r i v e motor i n t h e modulator. These m a l f u n c t i o n s have beefi c o r r e c t e d and t h e system i s now o p e r a t i o n a l . A CPS-9 Radar/ thunders t o m s t u d y b e i n g p e r f brmed by R-AERO-YE was i n l t i a ted t h i s p e r i o d . This s t u d y w i l l use wind d a t a from 1 4 anemometer i n s t a l l a t i c l r t s w i t h i n a f i v e - m i l e r a d i u s of t h e r a d a r s i t e and t h e p i c t u r e s from t h e cPS-9 PPI: scope. These d a t a w i l l b e c o r r e l a t e d w i t h thunders tam a c t i v i t y as i t p a s s e s through<t h e a r e a . The ionosphere stari'on is o p e r a t i o n a l , and has been o p e r a t e d d u r i n g a l l s t a t i c t e s t s t h i s p e r i o d . Data were recorded by b o t h t h e scope-mounted p o l a r o i d and t h e 35-mm cameras. These d a t a were f ~ r w a r d e d t o R-AERO-YS f o r p r o c e s s i n g . The MSFC c l i m a t o l o g i c a l d a t a , cons i s t i n g of h o u r l y temperat u r e , humidity, p r e s s u r e , wind d i r e c t i o n , and wind speed d a t a d a t i n g from October 1961 t o t h e p r e s e n t has been reduced, t a b u l a t e d , and s e n t t o t h e Computation Laboratory t o be keypunched and s t o r e d on magnetic tape f o r f u t u r e reference. The Atmospheric Research F a c i l i t y has s u p p o r t e d s e v e r a l l a b o r a t o r i e s w i t h meteo'rological equipment and d a t a i n t h e f o l l o w i n g areas : (a) An instrument s h e l t e r , h y g r o t h e m g r a p h , and a comp l e t e aerovane system i n c l u d i n g a tower were i n s t a l l e d f o r Space Sciences L a b o r a t o r y a t t h e l r Radio As t r o n m y s i t e . (b) An i n s t r u m e n t s h e l t e r and hygrothesthograph were i n s t a l l e d f o r t h e Experimental Aerophys i c s Branch t o provide temperature measurements a t t h e High Reynolds Number F a c i l i t y . (c) Test U b o t a t 6 r y r e q u e s t e d , and was provided w i t h , r e l a t i v e humidity d a t a f o r a l l s t a t i c t e s t f i r i n g s dating back t o e a r l y 1964. (d) An Aerovane Sys tem was i n s tsllled a t t h e West F-1 T e s t Stand a t the r e q u e s t of R-P&VE. ( e ) The A m y ' s Range 1 was provided w i t h m a t e r i a l f o r c a l i b r a t i o n of t h e i f l a r g e r a d a r systems. (f) llg" e x p e r h e n t * Support wag provided Q u a l i t y Laboratory i n t h e i r z e r o �(g) T e s t Laboratory' s Hydrogen Hand1 ing F a c i l i t y was provided i n f o r m a t i o n concerning l i g h t n i n g a c t i v i t y i n t h e a r e a . (h) The dynamic wind s t a n d and d a t a a c q u i s i t i o n system were moved d u r i n g t h i s p e r i o d . The s t a n d was moved t o t h e open f i e l d s o u t h of Bldg. 4614, and t h e r e c o r d i n g equipment was moved t o a r a d a r van i n t h e same a r e a . S e v e r a l t e s t s have been conducted on f o u r Climets and t h e d a t a s e n t t o Computation Laboratory f o r r e d u c t i o n . More t e s t s a r e scheduled f o r t h e summer months. The Easterline-Angus S t r i p C h a r t Recorders a t t h e 150-meter m c t c o r o l o g i c a l tower a t KSC a r e beginning t o show t h e e f f e c t of c o n t i n u ous o p e r a t i o n s . The take-up r e e l s were r e p l a c e d d u r i n g t h i s p e r i o d , and arrangements a r e being made t o have a l l t h e s e r e c o r d e r s e i t h e r r e p l a c e d o r r e b u i l t . With t h e e x c e p t i o n of t h e r e c o r d e r s , a l l o t h e r equipment and s e n s o r s a r e f u n c t i o n i n g satis f a c t o r i l y , and continuous wind and temp e r a t u r e d a t a a r e b e i n g a c q u i r e d from t h e 150-meter tower. B . Space Environment Branch S t u d i e s r e l a t e d t o t h e s t r u c t u r e and v a r i a b i l i t y of t h e thermos p h e r e have been d i r e c t e d t o (1) t h e documentation of t h e "MSFC S t a t i c D i f f u s i o n Model (1967) ," (2) t h e d e t a i l e d a n a l y s i s of s i x MSFC thermosphere probes, ( 3 ) t h e development of t h e "MSFC Thermosphere Model (1968) P r e l i m i n a r y , " and ( 4 ) t h e e s t a b l i s h m e n t of t y p i c a l atmospheric d e n s i t y time p r o f i l e s f o r ATM environment c r i t e r i a . - The "MSFC S t a t i c D i f f u s i o n Model (1967)" i s b a s i c a l l y a comp u t e r i z e d v e r s i o n of J a c c h i a ' s S t a t i c D i f f u s i o n Model w i t h Walker's This d i f f u s i o n e q u a t i o n used i n p l a c e of ~ a c c h i as' t a b l e look-up. model i s documented i n d e t a i l i n memorandum R-AERO-YS-160-68. The documentation c o n t a i n s no new changes t o t h e model; i t i s provided mainly t o a s s i s t o t h e r ' d i v i s i o n s / l a b o r a t o r i e s i n t h e i n c o r p o r a t i o n of t h e model i n t h e i r e n g i n e e r i n g programs. A f t e r a d e t a i l e d comparative a n a l y s i s , we have found t h i s model t o b e s t d e f i n e t h e environment c r i t e r i a f o r a l l engineering studies However, t h i s model, l i k e ~ a c c h i as' , is s e r i o u s l y handicapped by t h e assumed c o n s t a n t boundary c o n d i t i o n s a t 120 h. . A d e t a i l e d a n a l y s i s of s i x MSFC thermosphere probes, launched January 24, 1967, has provided a d d i t i o n a l i n f o r m a t i o n concerning t h e d i u r n a l v a r i a t i o n s of t h e thermosphere. This i n f o r m a t i o n w i l l b e used t o e s t a b l i s h v a r i a b l e boundary c o n d i t i o n s a t 120 km a l t i t u d e and t h e r e b y r e f i n e our p r e s e n t atmospheric model. A p r e l i m i n a r y computer program 1~11ichhas been w r i t t e n f o r t h i s new atmospheric model w i l l be used as a f o c a l p o i n t f o r s u p p o r t c o n t r a c t o r and NASA s m e r employee s t u d i e s . This computer program is d e s c r i b e d i n memorandum R-AERO-YS-157-68. �Typical atmospheric d e n s i t y - t i m e p r o f i l e s which have been e s t a b l i s h e d f o r a 28-day ATM m i s s i o n a r e provided i n memorandum R-AERO-YS-153-68. A s i m i l a r p r o f i l e f o r a 56-day m i s s i o n w i l l be completed soon. P r e l i m i n a r y d i s c u s s ions have been completed w i t h t h e Space Sciences Laboratory r e l a t i v e t o t h e 1968 r e v i s i o n of NASA TM X-53521, "Space Environment C r i t e r i a G u i d e l i n e s f o r Use i n Space Vehicle Development 1967 Revision," which i s p r o g r e s s i n g on s c h e d u l e . The new r e v i s i o n w i l l c o n t a i n a more d e t a i l e d d i s c u s s i o n of t h e e a r t h ' s upper atmosphere, r e v i s e d atmospheric models f o r Mars and Venus, r e f i n e d and expanded d a t a concerning t h e s u r f a c e s of Mars and t h e Moon, and expanded r a d i a tion data. P a r t I of t h e atmospheric d e n s i t y d e t e r m i n a t i o n program i s almost completed. This program w i l l be used t o compute atmospheric d e n s i t i e s from s a t e l l i t e o r b i t d a t a which w i l l be used i n t h e development of t h e MSFC Thermosphere Model (1968). R-AERO-FT w i l l provide s u p p o r t i n t h e o r b i t d e t e r m i n a t i o n a r e a , and t h e e q u a t i o n s i n t h e i r program a r e being s t u d i e d . Upper Atmospheric Dynamics A newphase i n t h e s t u d y of T r a v e l i n g I o n o s p h e r i c Disturbances (TID'S) i s being unaertaken i n c o n j u n c t i o n w i t h t h e Aeronomy Laborat o r y a t ESSA. A new instrument c a l l e d a "kinesonde" has been developed by ESSA which provides d a t a on i o n o s p h e r i c motions u s i n g t h e s i g n a l f a d i n g p r i n c i p l e . M r . J. W. Wright of ESSA has o f f e r e d t o c o l l e c t d a t a a t MTF d u r i n g times of s t a t i c t e s t f i r i n g s of t h e SIC t o i n c o r p o r a t e i n t o our a c o u s t i c g r a v i t y wave s t u d y program. The d a t a would be of obvious i n t e r e s t t o our s t u d y and would a l s o p r o v i d e M r . Wright w i t h e x t e n s i v e d a t a and e x p e r i e n c e w i t h which t o f u r t h e r develop t h e techniques r e q u i r e d i n d a t a c o l l e c t i o n , a n a l y s i s , and i n t e r p r e t a t i o n . We a r e c u r r e n t l y a t t e m p t i n g t o provide M r . Wright w i t h a n antenna a r r a y and power s o u r c e a t MTF. Solar Activity Prediction A r e c e n t v i s i t t o t h e 4 t h Weather Wing i n Colorado S p r i n g s , t h e S o l a r F o r e c a s t F a c i l i t y a t NORAD, and t h e ESSA Boulder L a b o r a t o r i e s have served t o emphasize t h e d i f f i c u l t y of f o r e c a s t i n g s o l a r a c t i v i t y . Solar f l a r e s a r e r e l a t i v e l y e a s y t o p r e d i c t i n l o c a t i o n on t h e s o l a r d i s k ; howe v e r , i t i s v i r t u a l l y impossible t o p r e d i c t t h e s i z e , d u r a t i o n , and time of s o l a r a c t i v i t y of the f l a r e . Long range p r e d i c t i o n -- a y e a r o r more Even though t h e i s v i r t u a l l y impossible u n l e s s we can d e r i v e t h e c a u s e s . c e n t e r of mass t h e o r i e s l e a d t o long range p r e p l a n e t a r y p e r t u r b a t i o n and d i c t i o n s of s o l a r a c t i v i t y which a r e b o r d e r l i n e , t h e a c c e p t e d p r e d i c t i o n -- �of s o l a r a c t i v i t y t h r e e t o f o u r days i n advance i s n o t r e a l l y that much b c t t c r . Research needs t o be i n c r e a s e d i n view of t h e importance of t h c s c p r e d i c t i o n s t o o u r o r b i t a l l i f e t i m e and dynamic p r e d i c t i o n s . C. Environmental A p p l i c a t i o n s Branch 1. A n a l y s i s of Atmospheric Turbulence from FPS-16 Radar/ Jimsphere Data (NASA C o n t r a c t No. NAS8-21331 w i t h Meteorology Research, I n c . ) Work on t h i s c o n t r a c t is p r o g r e s s i n g smoothly. Approximately 95 p e r c e n t of t h e d a t a t o perform t h e c o n t r a c t has been r e c e i v e d by t h e c o n t r a c t o r . The d a t a that w i l l be analyzed by t h e c o n t r a c t o r i n c l u d e s (1) n i n e Jimsphere p r o f i l e s observed over Wallops I s l a n d w i t h a s s o c i a t e d p i l o t r e p o r t s f o r t h e month of December 1967, (2) two sequences of Jimsphere d a t a c o n t a i n i n g approximately 15 wind p r o f i l e s and each s e p a r a t e d i n time by one and one-half h o u r s , and (3) twelve c h a r t r o l l s which c o n t a i n t u r b u l e n c e d a t a o b t a i n e d by a n instrumented a i r c r a f t over Wallops I s l a n d d u r i n g February and March 1968. The a i r c r a f t d a t a mentioned i n item (3) i n c l u d e t r u e a i r speed, a l t i t u d e , a c c e l e r a t i o n of t h e c e n t e r of g r a v i t y of t h e a i r c r a f t , r o l l and p i t c h a n g l e s and a n g l e of a t t a c k . The c o n t r a c t o r i s now p r o c e s s i n g t h e Jimsphere d a t a t o determine t h e r e s o l v i n g power of t h e Jimsphere b a l l o o n f o r v e r t i c a l l e n g t h s c a l e s l e s s than 25 m. This i n f o r m a t i o n needs t o be e s t a b l i s h e d i n o r d e r t o determine i f t h e Jimsphere b a l l o o n i s capable of y i e l d i n g d a t a t h a t can be used t o determine t h e spectrum of t u r b u l e n c e i n t h e i n e r t i a l subrange s o t h a t v i s c o u s d i s s i p a t i o n r a t e s can b e determined. The v i s c o u s d i s s i p a t i d n r a t e is a key parameter i n a t m o s p h e r i c t u r b u l e n c e , and i t perhaps could be used a s a n i n d i c a t o r of t h e i n t e n s i t y of t u r b u l e n c e . 2. F i n a l Report on C o n t r a c t NAS8-21138 w i t h NAR The f i n a l r e p o r t , "Wind F i e l d A n a l y s i s f o r C a n t i l e v e r Loads," has been r e c e i v e d i n a c c e p t a b l e form. This work was completed by North American Rockwell C o r p o r a t i o n , Downey, C a l i f o r n i a , on which Ben U j i h a r a was t h e p r i n c i p a l i n v e s t i g a t o r . The r e p o r t , being p u b l i s h e d a s a NASA CR, w i l l be d i s t r i b u t e d by R-AERO-Y. Wind d a t a from t h e 500F t e s t s were used t o i l l u s t r a t e pad wind flow c o n d i t i o n s and flow a b o u t t h e ~ ~ ~ / ~ e h i c l e . �3. F a s t Response Anemometer Twenty-five p r o p o s a l s were r e c e i v e d i n r e p l y t o a n RFP f o r t l ~ cdevelopment of a £as t response anemometer. This anemometer w i l l be used t o o b t a i n d a t a f o r f r e q u e n c i e s > 1 cps t o be used i n s e l e c t e d s t r u c t u r a l r e s p o n s e s t u d i e s and aerodynamic s c a l i n g a n a l y s i s . The p r o p o s a l s have been e v a l u a t e d and a c o n t r a c t o r t e n t a t i v e l y s e l e c t e d . N e g o t i a t i o n w i t h t h e p r o s p e c t i v e c o n t r a c t o r should t a k e p l a c e soon, Tf t h e p r o s p e c t i v e c o n t r a c t o r a g r e e s t o meet c e r t a i n c o n d i t i o n s added t o t h e proposed development, work should begifi on t h e anemometer w i t h i n a few weeks. 4. Recent Reports on NASA1 s 150 m M e t e o r o l & i c a l Facility Tower Two r e p o r t s have r e c e n t l y been made a v a i l a b l e on NASA's 150 m M e t e o r o l o g i c a l Tower l o c a t e d a t KSC, F l o r i d a : (1) GP-465 e n t i t l e d , "Meteorological Measuring and Recording Equipment Descript i o n , C a l i b r a t i o n and Maintenance Procedures f o r NASA's 150 m Meteorol o g i c a l Tower F a c i l i t y , Kennedy Space C e n t e r , F l o r i d a , " d a t e d February 15, 1968; and (2) NASA X-53699 e n t i t l e d , "NASA's150 m M e t e o r o l o g i c a l Tower Located a t t h e Kennedy Space C e n t e r , F l o r i d a , " d a t e d January 1968 ( r e v i s e d ) . Copies of t h e s e r e p o r t s may be o b t a i n e d by c o n t a c t i n g R-AERO-YE, A t tn: John W. Kaufman (6-6392). 5. Winds Which Adversely A f f e c t Vehicle Operations ( C o n t r a c t NAS8-21292) M r . Joseph Goldman, p r i n c i p a l i n v e s t i g a t o r under c o n t r a c t NAS8-21292, of t h e U n i v e r s i t y 6f S a i n t Thomas (UST) v i s i t e d t h e Aeros p a c e Environment D i v i s i o n on A p r i l 1 2 t h t o c o o r d i n a t e and d i s c u s s work t o be done on t h e c o n t r a c t e n t i t l e d , "Analysis of Wind F i e l d Conditions which Adversely A f f e c t Vehicle Operations." It was agreed t h a t t h e ( I ) L i t e r a t u r e survey on t h e f o l l o w i n g work would b e completed by UST: s t a t e - o f - t h e - a r t of r e s e a r c h on winds a s s o c i a t e d t o thunderstorms ( l i g h t n i n g , h a i l , s t o r m d u r a t i o n , e t c . ) w i l l b e reviewed. (2) UST w i l l develop a t h e o r e t i c a l model and e m p i r i c a l model a s developed from a c t u a l atmospheric d a t a o b t a i n e d d u r i n g t h e occurrence of thunders torms (some of t h e s e d a t a w i l l be from NASA's 150 m ~ e t e o r ' o l o g i c a l Tower a t ICSC). (3) UST w i l l e v a l u a t e t h e s p e c t r a l a a a l y s i s of wind d a t a a c q u i r e d (Data a c q u i r e d a t NASA's 150 m M e t e o r o l o g i c a l d u r i n g thunders torms a t KSC. Tower w i l l be analyzed a t MSFC.) ( 4 ) F o r e c a s t techniques of wind a s s o c i a t e d t o thunderstorms, from t h e s y n o p t i c - t o m i c r o - s c a l e , w i l l be documented. (5) UST w i l l provide recommendations on f u t u r e d a t a r e q u i r e ments t o s t u d y thunders torms a t KSC. R e s u l t s of t h i s s t u d y a r e t d prov i d e a d d i t i o n a l environmental c r i t e r i a on s e v e r e s t o m s a s r e q u i r e d f o r d e s i g n and A p o l l o / S a t u r n v e h i c l e o p e r a t i o n s . M r . Goldmn v i s i t e d �KSC on May 21-22, 1968. The purpose of t h i s v i s i t was to-become f a m i l i a r w i t h KSC wind s e n s o r f a c i l i t i e s and l o c a l t e r r a i n e s p e c i a l l y i n t h e v i c i n i t y of Launch Complexes 37 and 39. 6. Revised MSFC Peak Wind Design Envelope A r e v i s e d MSFC peak ground wind speed envelope v a l i d f o r KSC has been developed by R-AERO-YE. This wind envelope w i l l s u p e r s e d e t h c envelope c o n s t r u c t i o n d a t a g i v e n f o r E a s t e r n T e s t Range a s shown i n t a b l e s 5.6A, 5.6B7 and 5.6C on pages 5.21 and 5.22 i n " ~ e r r e tsr i a l Environment ( C l i m a t i c ) C r i t e r i a G u i d e l i n e s f o r Use i n Space Vehicle ~ e v e l o p m e n t , 1966 Revision,'' NASA TM X-53328. The new d e s i g n wind envelope i s g i v e n by where u ( h ) i s t h e peak wind speed a t h e i g h t h ( i n m e t e r s ) above n a t u r a l g r a d e , and ulaa3 i s a known peak wind speed a t h = 18.3 m e t e r s . The parameter, k, i s g i v e n by Thus, upon s p e c i f y i n g t h e peak wind a t is i n m sec-l. where u18. 11 = 18.3 m sec'l, t h e peak wind p r o f i l e w i l l be completely s p e c i f i e d . However, i n o r d e r t o a c c o u n t f o r t h o s e c a s e s i n which peak wind d a t a a r e g i v e n a t h e i g h t s o t h e r 'than a t 18.3 m e t e r s , R-AERO-YE has developed a t a b l e of peak wind p r o f i l e s f o r a wide range of peak wind speed conditions. 7. I n v e s t i g a t i o n of t h e Turbulent Wind F i e l d Below 500 F e e t A l t i t u d e a t t h e E a s t e r n T e s t Range, F l o r i d a (NASA C o n t r a c t NAS8-21140) This c o n t r a c t , which i s being performed by t h e Pennsylvania S t a t e U n i v e r s i t y (PSU) i s p r o g r e s s i n g smoothly i n a l l a r e a s . The cont r a c t o r i s now a n a l y z i n g t h e coherence f u n c t i o n of t u r b u l e n c e and t h e s t a t i s t i c s of t h e l o n g i t u d i n a l and l a t e r a l wind f l u c t u a t i o n s of turbul e n c e i n t h e f i r s t 150 m of t h e atmosphere a t KSC. The c o n t r a c t o r found t h a t t h e coherence of t h e l o n g i t u d i n a l component of t u r b u l e n c e a t KSC i s v e r y s i m i l a r t o t h a t found a t Brookhaven, New York, w h i l e i t d i f f e r s somewhat from t h a t observed a t White Sands, New Mexico. The s t a t i s t i c a l s t u d i e s a r e aimed a t determining t h e d i s t r i b u t i o n f u n c t i o n of t h e wind J, �. I n a d d i t i o n , t h e s t a t i s t i c a l s t u d i e s w i l l determine the clcgrcc 01 d e p a r t u r e of t h e t u r b u l e n c e from a Gaussian p r o c e s s . A t the p r e s e n t time, i t a p p e a r s t h a t t h e l o n g i t u d i n a l component of t u r b u l e n c e i s almost a Gaussian p r o c e s s , w h i l e t h e l a t e r a l component t u r b u l e n c e has a bimodal d i s t r i b u t i o n f u n c t i o n . The bimodal c h a r a c t e r of t h e l a t e r a l d i s t r i b u t i o n i s due t o t h e t u r n i n g of t h e s t e a d y - s t a t e wind p r o f i l e w i t h h e i g h t (Ekman l a y e r ) i n t h e atmospheric boundary l a y e r . f 1 uctuations 8. A n a l y s i s of Ground Wind F i e l d A n a l y s i s f o r Design and Operation of Space Vehicles ( C o n t r a c t NAS8-21178) This c o n t r a c t i s being performed by C o r n e l l A e r o n a u t i c a l L a b o r a t o r i e s (CAL) of B u f f a l o , New York. During t h i s p e r i o d , CAL r e c e i v e d t h e l a s t shipment of d a t a t o complete t h e c o n t r a c t . The main emphasis d u r i n g t h i s p e r i o d was placed upon p r e s c r i b i n g l a t e r a l spectrum of t u r b u l e n c e f o r launch v e h i c l e response c a l c u l a t i o n s . F i n a l r e s u l t s a r c n o t y e t a v a i l a b l e , CAL has r e q u e s t e d a three-month no-cost extens i o n t o complete t h e c o n t r a c t , because of unavoidable d e l a y s i n programming and compute_ p r o c e s s i n g . This means t h a t t h e c o n t r a c t w i l l n o t be completed u n t i l September 30, 1968. 9. P r e l a u n c h Monitorship Program The M a r t i n - M a r i e t t a Corporation (Denver) i s developing a p r e l a u n c h m o n i t o r i n g program, which w i l l p r e d i c t t h e i n - f l i g h t l o a d s a t launch time based upon t h e wind p r o f i l e seven hours b e f o r e launch of a S a t u r n V launch v e h i c l e and c e r t a i n KSC i n - f l i g h t wind s t a t i s t i c s . I n o r d e r t o develop t h i s program t h e Martin-Marietta C o r p o r a t i o n r e q u i r e s wind s t a t i s t i c s f o r KSC t h a t d e s c r i b e (1) t h e wind d i r e c t i o n and speed v a r i a t i o n s i n t h e 10-15 krn a l t i t u d e r e g i o n , (2) t h e v a r i a t i o n s i n a l t i t u d e of t h e l e v e l of maximum wind i n t h e 10-15 km a l t i t u d e r e g i o n , and ( 3 ) t h e p e r s is t e n c e s t a t i s t i c s of in-£1 i g h t t u r b u l e n c e s p e c t r a . To determine t h e s p e c i f i c s t a t i s t i c s needed by t h e c o n t r a c t o r , a meeting was h e l d on May 29, 1968, a t MSFC w i t h M a r t i n - M a r i e t t a Corporation. The a t t e n d e e s were Messrs. Vaughan, K a u h a n , H i l l , and F i c h t l of R-AERO-Y and M r . Wilkining of t h e M a r t i n - M a r i e t t a C o r p o r a t i o n , and M r . R. Ryan and Mrs. A . King ( c o n t r a c t o r monitor) of R-AERO-DD. Wind speed p e r s i s t e n c e s t a t i s t i c s have been s u p p l i e d t o M a r t i n - M a r i e t t a Corporation f o r t h i s s t u d y . Computer programs t o c a l c u l a t e t h e o t h e r At s t a t i s t i c s mentioned above a r e now being w r i t t e n by.R-COMP-RRP. t h i s s t a g e , i t was decided t o c o n c e n t r a t e on s t a t i s t i c a l p r e d i c t i o n s of wind p r o f i l e c h a r a c t e r i s t i c s ( t u r b u l e n c e , s h e a r s , wind s p e e d s ) and v e h i c l e responses t h e r e t o . �10. Jimsphere Temperature Sensor (NASA C o n t r a c t NAS8-20588) Work on a temperature s e n s o r f o r t h e Jimsphere b a l l o o n has recommenced. The c o n t r a c t o r i s t h e GCA C o r p o r a t i o n of Bedford, Massachusetts. This c o n t r a c t w i l l be completed i n a b o u t s i x months. This f i n a l phase of t h e c o n t r a c t w i l l be concerned w i t h performing a d e t a i l e d e r r o r a n a l y s i s of t h e temperature s e n s o r system. 11. T r a i n i n g on M e t e o r o l o g i c a l Sensors M r . Wade P e r r y a t t e n d e d a t r a i n i n g s e n s o r s (wind s e n s o r s ) and a s s o c i a t e d equipment ments, I n c . f a c i l i t y a t Sunnyvale, C a l i f o r n i a . r e s p o n s i b l e f o r r e p a i r i n g wind s e n s o r s t h a t a r e 150 m M e t e o r o l o g i c a l Tower F a c i l i t y a t KSC. D. c o u r s e on m e t e o r o l o g i c a l a t t h e Climet I n s t r u M r . P e r r y w i l l soon be being used a t t h e NASA T e r r e s t r i a l Environment Branch 1. The major t a s k of f i t t i n g a n extreme v a l u e f u n c t i o n t o t h e Cape Kennedy peak wind speeds i s n e a r i n g completion. 2. M r . 0. E. Smith p r e s e n t e d a paper e n t i t l e d , "Atmospheric S t a t i s t i c s f o r Aerospace Vehicle Design, Mission Planning and Operat i o n s , " a t t h e Third N a t i o n a l Conference on Aerospace Meteorology, May 6-7, 1968, a t New Orleans. The meeting was sponsored by t h e American M e t e o r o l o g i c a l S o c i e t y , t h e American I n s t i t u t e of Aeronautics and A s t r o n a u t i c s Committee on Atmospheric Environment, and t h e I n s t i t u t e of Environmental S c i e n c e s . 3 . Standard ' d e v i a t i o n s of p r e s s u r e , t e m p e r a t u r e , and d e n s i t y t o 120 km w i t h r e s p e c t t o t h e 1963 P a t r i c k Reference Atmosphere were published i n memorandum R-AERO-YT-27-68, d a t e d A p r i l 4 , 1968, t o provide atmospheric d a t a f o r u s e i n t r a j e c t o r y h e a t i n g s t u d i e s . 4. Considerable work on background m a t e r i a l f o r LOX and f u e l temperature p r e d i c t i o n s was done. Although no s a t i s f a c t o r y s o l u t i o n t o t h e p r e d i c t i o n problem was developed, e r r o r s i n t h e proposed C h r y s l e r method were d i s c o v e r e d i n time t o p r e v e n t e x t e n s i v e work a l o n g unprod u c t i v e l i n e s . To e n i b l e a l l concerned t o b e t t e r understand t h e problem, a c o o r d i n a t i o n meeting was h e l d i n New Orleans w i t h C h r y s l e r Corporation Space D i v i s i o n and P&VE personnel on May 6 . �The f i r s t of s e v e r a l computer programs being developed f o r 5. use w i t h t h e World-Wide Cloud Cover S t a t i s t i c s was completed a t t h e end of May. S e v e r a l a d d i t i o n a l computer programs w i l l be r e q u i r e d t o make f u l l use of t h e cloud s t a t i s t i c s i n miss i o n s i m u l a t i o n e x e r c i s e s ; howe v e r , some b a s i c m a t e r i a l u s e f u l i n m i s s i o n a n a l y s i s s t u d i e s can be f u r n i s h e d now. A memorandum c o n t a i n i n g cloud s t a t i s t i c s f o r t h e E a r t h Resources Experiment was i s s u e d on May 24, 1968, R-AERO-YT-32-68. 6. Lockheed Support C o n t r a c t An a n a l y t i c a l s t u d y of t h e Cape Kennedy low l e v e l winds (0-2 km) has begun. The s u r f a c e f r i c t i o n l a y e r and t h e Ekman s p i r a l t h e o r y a r e now being i n v e s t i g a t e d . The h o u r l y peak wind speeds and two a d d i t i o n a l y e a r s of winds a l o f t d a t a a r e being added t o t h e program from which "launch p r o b a b i l i t i e s ' ' a r e computed. 7. NWRC C o n t r a c t -- Government Order 76789 An i n v e s t i g a t i o n o f t h e s e a b r e e z e a t Cape Kennedy is being conducted f o r u s e i n t h e near-pad a b o r t problem. 111, ASTRODYNAMICS AND GUIDANCE THEORY DIVISION A. As trodynamics Branch 1. Miss i o n A n a l y s i s Programs (Lockheed) A u s e r ' s manual f o r s e v e r a l small m i s s i o n a n a l y s i s programs e n t i t l e d "Quick-Look Miss i o n Analys i s Programs ," has been camp l e t e d and d e l i v e r e d t o R-AERO-GA f o r review. This document d i s c u s s e s t h e t e c h ~ i q u e sused t o c a l c u l a t e some of t h e more important t r a j e c t o r y d e s i g n parameters f o r the d e s i g n of a n o r b i t a b o u t a t a r g e t p l a n e t . It a l s o i n c l u d e s a u s e r ' s manual f o r t h e P l a n e t a r y O r b i t Design and O c c u l t a t i o n Computer Program. 2. Broken Plane T r a j e c t o r i e s (Lockheed) Work w a s continued on t h e a n a l y s i s of b r ~ k e n - p l a n e i n t e r p l a n e t a r y t r a n s f e r s . Broken-plane t r a j e c t o r y d a t a f o r t h e 1973, 1975, 1977 and 1979 Mars m i s s i o n o p p o r t u n i t i e s have been g e n e r a t e d and a Lockheed t e c h n i c a l n o t e p r e s e n t t n g t h e s e d a t a has been w r i t t e n . The TN has been reviewed and i s being prepared f o r p u b l i c a t i o n . The o p t i m i z a t i o n scheme used i n t h e broken-plane computer program is being i n v e s t i g a t e d i n a n e f f o r t t o complete a thorough documentation of t h e mathematical approach used as w e l l a s a u s e r ' s manual f o r t h e program. �3. Miss ion Design Charts (Lockheed) I n i t i a l work was begun on a n a n a l y s i s t o determine t h e t r a j e c t o r y design parameters t h a t a r e t h e most meaningful i n d e s c r i b i n g p l a n e t a r y and i n t e r p l a n e t a r y miss i o n requirements. This analys i s i s d i r e c t e d toward t h e des ign and c o n s t r u c t i o n of g e n e r a l m i s s i o n des ign c h a r t s p o r t r a y i n g t h e s e parameters a s f u n c t i o n s of launch and t a r g e t p l a n e t encounter d a t e s f o r a l l types of i n t e r p l a n e t a r y t r a n s i t s ( i . e . , s i n g l e plane Type I and Type 11, broken-plane, and p l a n e t a r y swinbys). These mission design c h a r t s w i l l be designed t o show t h e mission requirements f o r a l l types of t r a n s i t s during a given mission opport u n i t y , t o enable t h e t r a j e c t o r y a n a l y s t t o r a p i d l y a s s e s s t h e type of t r a n s i t t h a t y i e l d s t h e most d e s i r a b l e t r a n s f e r c h a r a c t e r i s t i c s . An e x i s t i n g i n t e r p l a n e t a r y t r a j e c t o r y computer program i s being modified t o extend i t s c a p a b i l i t y , f o r use i n t h i s a n a l y s i s , through the addit i o n of automatic p l o t r o u t i n e s and a s u b r o u t i n e f o r computing t o t a l miss i o n A,. 4. O r b i t s i n Non-Central F i e l d s There is a l a r g e number of f a i r l y g e n e r a l non-central p o t e n t i a l f u n c t i o n s which g i v e r i s e t o a s e p a r a b l e Hamil ton-Jacobi equation, and hence a closed-form s o l u t i o n f o r the corresponding o r b i t . I n p o l a r c o o r d i n a t e s , f o r example, any p o t e n t i a l of t h e form V(r,O) = Vl(r) v 2 ( 8 ) / r 2 l e a d s t o a closed-form s o l u t i o n . A program has been w r i t t e n t o compute and p l o t t h e r e s u l t i n g o r b i t s . + Coordinate systems beyond t h e conventional ones can be developed by noting t h a t con jugate harmonic f u n c t i o n s w i l l y i e l d a Hamiltonian w i t h no cross-products of momenta, i . e . , one t h a t may be a ttaclced convenient2y. Any closed-form s o l u t i o n w i l l be examined f o r a p p l i c a b i l i t y t o some a c t u a l physical s i t u a t i o n , f o r example, o r b i t s about non-spherical b o d i e s , o r o r b i t s of s p a c e c r a f t s u b j e c t t o s e v e r a l a t t r a c t i o n s . Applicat i o n s w i l l most l i k e l y c o n s i s t of t h e development of o s c u l a t i n g o r b i t s , o r of patching techniques. 5. I n t e r p l a n e t a r y N-Body Programs a. Program Development A r e p o r t on t h e i n i t i a l phases of a s t u d y of e f f i c i e n t i n t e r p l a n e t a r y i n t e g r a t i n g computer programs was given a t t h e r e c e n t Research Achievements Review. An o u t l i n e of t h e s t r u c t u r e of t h e s t u d y was given, a s w e l l a s a few examples of how t h e p r o j e c t e d s t u d y r e s u l t s might be used i n t h e c o n s t r u c t i o n of e f f i c i e n t i n t e r p l a n e t a r y programs. The paper w i l l be published i n t h e MSFC Research Achievements Review a2 (Third S e r i e s ) . �b. T a r g e t i n g Research Work i n t h i s a r e a has proceeded w e l l . S e v e r a l of t h e o r i g i n a l approaches have been e l i m i n a t e d a s good c a n d i d a t e s f o r use i n advanced programs. I n p a r t i c u l a r , t h e two-body approximations i n g e n e r a l have been found l a c k i n g and w i l l no l o n g e r b e considered. A r e p o r t on t h e s t u d i e s of two-body approaches s u p p o r t i n g t h i s conclusion w i l l be prepared. A method c a l l e d t h e " A n a l y t i c Conglomerate Mass ~ e c h n i q u e "which i s based on a paper by W. Bollennan of t h e German Aeronautics and Space Experimental S t a t i o n , e n t i t l e d , " R e p r e s e n t a t i o n of T r a j e c t o r y and V e l o c i t y Coordinates f o r Space F l i g h t by a Generalized Icepler Approximation and C o r r e c t i o n s i n t h e I t e r a t i o n Procedure , I ' March 1966, a v a i l a b l e a s NASA TT F-11, 387, i s being g i v e n f u r t h e r cons i d e r a t i o n . Also a n approach u s i n g l a r g e time s t e p i n t e g r a t i o n ( c o n s t a n t o r v a r i a b l e s t e p s i z e ) and a s i m p l i f i e d s o l a r system model i s s t i l l being i n v e s t i g a t e d . c . I s o l a t i o n Routine Research Some c a n d i d a t e r o u t i n e s a r e now being programmed f o r comparison on t h e computer t o a s s i s t i n t h e s e l e c t o r y r o u t i n e s f o r use i n d i f f e r e n t a p p l i c a t i o n s . 6. Conic Program f o r Small Computers The programs b e i n g combined t o form t h i s c o n i c program have a l l been transformed i n t o s u b r o u t i n e form. The remaining work w i l l be c o n c e n t r a t e d on t h e d r i v e r program and a few s m a l l a d d i t i o n s which a r e n e c e s s a r y f o r t h e needed accuracy. One of t h e s e a d d i t i o n s i s t h e computation of t h e n e c e s s a r y burn a r c s a s a f u n c t i o n of launch The computation of t h e i n j e c t i o n azimuth and i n j e c t i o n energy (C3). p o s i t i o n and v e l o c i t y w i l l b e checked a g a i n s t i n t e g r a t e d b o o s t t r a j e c t o r i e s f o r a c c u r a c y , and a comparison w i l l be made of t h e e f f i c i e n c y and a c c u r a c y of t h i s method a s opposed t o i n t e r p o l a t i o n f o r t h e i n j e c t i o n s t a t e v e c t o r from a precomputed volume of i n t e g r a t e d b o o s t trajectories. 7. O r b i t T r a n s f e r S t u d i e s (United A i r c r a f t NAS8-21091) The rough d r a f t of t h e f i n a l r e p o r t has been reviewed, and r e s u l t s of our review have been d i s c u s s e d w i t h t h e c o n t r a c t o r . A l l c o r r e c t i o n s and r e v i s i o n s have been agreed upon, and t h e f i n a l copies w i l l be a v a i l a b l e f o r d i s t r i b u t i o n soon. �8. Odyssey (Lockheed) Worlc was continued on t h e i n v e s t i g a t i o n of t h e v a r i a t i o n i n pclrigcc a l t i t u d e of h i g h l y e c c e n t r i c e a r t h o r b i t s a s a r e s u l t of l u n a r and s o l a r p e r t u r b a t i o n s . A closed-form a n a l y t i c a l e q u a t i o n , g i v i n g t h e v a r i a t i o n i n p e r i g e e a l t i t u d e p e r r e v o l u t i o n , due t o s o l a r p e r t u r b a t i o n s , i s being used i n a n e f f o r t t o choose t h e i n i t i a l launch c o n d i t i o n s t h a t r e s u l t i n t h e d e s i r e d o r b i t l i f e t i m e and p e r i g e e a l t i tude v a r i a t i o n . A r e p o r t on t h e s e e q u a t i o n s and t h e i r a p p l i c a t i o n t o t h i s problem i s being prepared and should be a v a i l a b l e by t h e time of t h e next progress r e p o r t . B. Guidance Theory Branch 1. Support C o n t r a c t S t u d i e s a. General I n t e r p l a n e t a r y S t u d i e s The FPR s t u d y u s i n g load r e l i e f c o n t r o l has been delayed due t o slow turn-around on t h e 1108 computer. Also, e r r o r s i n t o r q u e computations have been found i n t h e computer program. Correct i o n s a r e b e i n g made. b. Quas i-Optimal Guidance Study The AS-502 m i s s i o n (S-IVB s t a g e o n l y ) has been s u c c e s s f u l l y s i m u l a t e d u s i n g QUOTA as t h e guidance scheme. Nominal S-IVB performance and i d e a l n a v i g a t i o n v a l u e s f o r t h e s t a t e v a r i a b l e s were assumed. An a t t e m p t i s being made t o i n c o r p o r a t e t h e c o n s t r a i n t on t h e c o n t r o l v a r i a b l e (2 r a t e l i m i t ) i n t o t h e QUOTA l o g i c . I f s u c c e s s f u l , t h i s w i l l a l l o w QUOTA t o o p t i m a l l y f l y m i s s i o n s where c o n s t r a i n t s on the control variable a r e c r i t i c a l . c. Optimum O r b i t Trim Analyses The r e s u l t s of t h e s t u d y u s i n g QUOTA f o r a n o r b i t t r i m a n a l y s i s a r e b e i n g documented. d. Optimal Guidance Study Because of a n a l y t i c a l and programming d i f f i c u l t i e s encountered d u r i n g t h i s r e p o r t i n g p e r i o d , much e f f o r t was expended on c o r r e c t i n g e r r o r s and o r g a n i z i n g r e s u l t s . Some a d d i t i o n a l p r o g r e s s was made i n f o r m u l a t i n g and programming t h e e q u a t i o n s f o r t h e d e t e r m i n a t i o n of t h e m a t r i x of p a r t i a l s of t h e i n i t i a l unknowns w i t h r e s p e c t t o t h e initial state. �2. Contracts a. Lockheed - Voyager Terminal Guidance A n a l y s i s A closed-loop guidance model f o r t e r m i n a l guidance has been i n v e s t i g a t e d . The closed-loop s y s tem shows a s i g n i f i c a n t improvement over t h e p r e v i o u s l y p o s t u l a t e d open-loop model. With a closed-loop s y s tem, t h e d i s p e r s i o n of t h e o r b i t a l elements a b o u t t h e i r nominals , i s almost e n t i r e l y a f u n c t i o n of t h e n a v i g a t i o n accuracy assumed. Highly a c c u r a t e i n s e r t i o n s can be accomplished, i f t r a c k i n g d a t a can b e taken and processed v e r y c l o s e (4 t o 6 h o u r s ) t o t h e i g n i t i o n p o i n t . b. - IBM A p p l i c a t i o n o f Numerical Methods t o Extend C a p a b i l i t i e s f o r Optimal ~ o c k e tGuidance The o b j e c t i v e of t h i s new c o n t r a c t i s t o provide a r e l i a b l e , f l e x i b l e , and e f f i c i e n t method f o r computing f u e l - o p t i m a l r o c k e t t r a j e c t o r i e s ( w i t h b o t h burn and c o a s t a r c s ) . A t a meeting h e l d w i t h t h e c o n t r a c t o r t o d i s c u s s t h e d e t a i l s of t h e t e c h n i c a l approach t o t h e problem, i t was decided t h a t c a n d i d a t e s f o r t h e main a l g o r i t h m which computes optimal f i n i t e - t h r u s t o r b i t t r a n s f e r s w i l l i n c l u d e a mu1 ti-dimens i o n a l s e c a n t method, quas i - l i n e a r i z a t i o n , and a modified ~ e w t o n ' smethod. c. Lockheed - Rendezvous Guidance The IBM 7094 computer programs developed under t h i s c o n t r a c t have been converted t o r u n on t h e CDC-3200 and t h e SDS-930. The r e s u l t i n g i n c r e a s e i n computer a c c e s s i b i l i t y i s a l l o w i n g a l a r g e r amount of s i m u l a t i o n t o be done u s i n g t y p i c a l AAP g u i d e l i n e s . These r e s u l t s w i l l be p r e s e n t e d soon. 3. In-House S t u d i e s a . Work i s c o n t i n u i n g on t h e computer program based on the techniques developed i n t h e f i n a l r e p o r t f o r c o n t r a c t NAS8-20269 (Optimal C o n t r o l Theory w i t h A p p l i c a t i o n s t o Optimal T r a j e c t o r y and Guidance Problems by Charles M. Chambers). Another method, ~ e w t o n ' smethod f o r t h e s o l u t i o n of boundary v a l u e problems by u s e of p a r t i a l d e r i v a t i v e s , i s b e i n g developed a s a computer program which i s t o be compared t o chambers' method , �b. A guidance s i m u l a t i o n deck i s being developed by mott i f y ing a n c x i s t ing computer program. Various guidance schemes w i l l hc progri~mccl a s s u b r o u t i n e s . Guidance schemes can be compared by s i~nula t i n g a miss i o n using t h e v a r i o u s guidance s u b r o u t i n e s . c . Closed-form s o l u t i o n s f o r powered f l i g h t i n a c o n s t a n t g r a v i t y f i e l d have been developed w i t h mass a s t h e independent v a r i a b l e . This a l l o w s a l l of t h e p a r t i a l d e r i v a t i v e t r a n s i t i o n m a t r i c e s t o be o b t a i n e d i n c l o s e d form. These r e s u l t s have been used t o c o n s t r u c t a computer program t o s o l v e t h e COV boundary v a l u e problem. d. The three-dimensional COV deck f o r t h e CDC-3200 comp u t e r i s now capable of f l y i n g t o s i x d i f f e r e n t c u t - o f f s u r f a c e s . A t r a j e c t o r y w i t h a n optimal c o a s t p e r i o d was r e c e n t l y obtained using a v e h i c l e and geometry a p p r o p r i a t e t o a n U P m i s s i o n . A c a p a b i l i t y t o handle i n e q u a l i t y c o n s t r a i n t s and a rendezvous c a p a b i l i t y i s planned f o r the future. e . A computer program which w i l l perform a p r e f l i g h t e r r o r a n a l y s i s on i n t e r p l a n e t a r y t r a j e c t o r i e s i s b e i n g developed. This program a s s e s s e s t h e probable midcourse AV requirements and p r o v i d e s , a f t e r each midcourse c o r r e c t i o n , t h e c o v a r i a n c e m a t r i x of t h e e r r o r s i n time of f l i g h t , and i n t h e miss parameters a t t h e t a r g e t p l a n e t . C. O p t i m i z a t i o n Theory Branch 1. Review of S t a b i l i t y Requirements Some r e c e n t d i s c u s s i o n s have been h e l d concerning t h e necess i t y of imposing s t a b i l i t y margin requirements on a launch v e h i c l e f l i g h t c o n t r o l system. No c o n c l u s i o n s have y e t been reached. NASA TM X-53735, "A D i s c u s s i o n of t h e S t a b i l i t y Requirements f o r a Launch Vehicle F l i g h t Control Sys tern," has been published t o document t h e d i s c u s s i o n t o d a t e and t o s o l i c i t p a r t i c i p a t i o n i n t h e d i s c u s s i o n by o t h e r s . Some responses t o t h e r e p o r t have a l r e a d y been r e c e i v e d . 2. S t a t i s t i c a l Wind Model A c o n t r a c t i s being n e g o t i a t e d w i t h Hayes I n t e r n a t i o n a l t o use t h e c u r r e n t l y a v a i l a b l e Jimsphere d a t a t o c o n s t r u c t a new wind model f o r use i n s t a t i s t i c a l a n a l y s e s of launch v e h i c l e performance. The model w i l l assume t h e wind ( n o n - s t a t i o n a r y ) t o be Gaussian t o p e r m i t l i n e a r a n a l y s i s of t h e v e h i c l e ' s performance, b u t i t w i l l be of h i g h e r o r d e r and more a c c u r a t e t h a n c u r r e n t l y a v a i l a b l e models of t h i s t y p e . M r . George F i c h t l of R-AERO-Y i s p a r t i c i p a t i n g i n t h e s t u d y . �3. A n a l y t i c a l Study of S p a c e c r a f t P o i n t i n g E r r o r Research i s being done on a n a n a l y t i c approach t o t h e problem of minimizing s p a c e c r a f t p o i n t i n g e r r o r d u r i n g midcourse, o r b i t i n s e r t i o n , and o r b i t t r i m maneuvers d u r i n g i n t e r p l a n e t a r y f l i g h t . Various c o n t r o l laws a r e being used and s e n s i t i v i t y f u n c t i o n s a r e employed t o determine s u i t a b l e g a i n s f o r minimizing t h e t e r m i n a l p o i n t ing e r r o r . A Voyager c l a s s s p a c e c r a f t is being used i n t h e s t u d y ; howe v e r , t h e r e s u l t s may b e extended t o t h e g e n e r a l c l a s s of i n t e r p l a n e t a r y vehicles. 4. Minimax Control A s t u d y of a minimax c o n t r o l computational a l g o r i t h i s being performed by Lockheed s u p p o r t c o n t r a c t o r s i n c o n j u n c t i o n w i t h D r . C. D. Johnson of t h e U n i v e r s i t y of Alabama and in-house personnel. The s t u d y has been p r o d u c t i v e from a p r a c t i c a l v i e w p a i n t i n b r i n g i n g t o l i g h t some problems i n t h e s y n t h e s i s of minimax c o n t r o l l e r s . F i r s t , s i n c e t h e a l g o r i t h m u s e s backward-time i n t e g r a t i o n , f a s t time-constant elements s u c h a s a c t u a t o r s can g i v e problems u n l e s s t h e i r n o n l i n e a r c h a r a c t e r i s t i c s a r e modeled i n s u c h a way a s t o p r e v e n t divergence. Second, t h e d i m e n s i o n a l i t y of high-order systems can q u i c k l y l e a d t o unwieldy v i s u a l i z a t i o n and long computer times. The r e s u l t s of t h e s t u d y a r e expected t o be p r e s e n t e d a t t h e A N Guidance, C o n t r o l , and F l i g h t Dynamics Conference i n August . 5. Parameter Optimization Study f o r ATM Support C o n t r a c t o r - Lockheed The a n a l o g phase of t h e hybrid s i m u l a t i o n i s undergoing check-out, and t h e o p t i m i z a t i o n package i s b e i n g p r o g r a m e d on t h e d i g i t a l computer as t h e n e x t p o r t i o n of t h e program sequence. The t o t a l program should be i n t h e check-out phase by mid-July. It is hoped t h e a n a l y s i s w i l l e s t a b l i s h t h e u s e f u l n e s s of t h e c o n j u g a t e g r a d i e n t technique f o r parameter o p t i m i z a t i o n problems by developing c o n t r o l l e r f o r a complex s y s tern such a s t h e ATM. an "~ptimum'~ 6. Nor t h r o p Support C o n t r a c t o r a. S a t u r n po pol lo Load R e l i e f S t u d i e s I n i t i a l r i g i d body s t u d i e s (time v a r y i n g c o e f f i c i e n t s ) d r e under way f o r a t y p i c a l S a t u r n VIApollo c o n f i g u r a t i o n (SA-504)Candidate c o n t r o l l e r s must provide a s i g n i f i c a n t r e d u c t i o n i n t h e v e h i c l e bending moment t o be considered f o r t h e more complete a n a l y s i s which w i l l i n c l u d e t h e v e h i c l e bending dynamics. These s t u d i e s , which a r e supplemental t o e a r l i e r ones made by Boeing, s e e k t o answer ques t i o n s r a i s e d by t h e e a r l i e r work. �b. Numerical Methods i n T r a j e c t o r y Optimization A new r e p o r t being prepared on t h e e q u a t i o n s of v a r i a t i o n w i l l examine t h e e f f e c t of d i s c o n t i n u i t i e s on t h e e q u a t i o n s of v a r i a t i o n i n more d e t a i l than has been done p r e v i o u s l y . c. Analytical F i l t e r Synthesis A r e p o r t on a n a p p l i c a b i l i t y s t u d y of a r e c e n t (1967) f i l t e r s y n t h e s i s technique proposed by R. W. Bass has been d r a f t e d . In g e n e r a l , t h e c o n c l u s i o n s were n e g a t i v e . I n i t s p r e s e n t s t a t e , t h e technique does n o t appear t o be a s u s e f u l a s was o r i g i n a l l y expected. 7. North American (NAS8-21077) O b j e c t i v e : Development of means of computing optimal orbital transf ers for f i n i t e thrust. The c o n t r a c t was completed d u r i n g t h i s r e p o r t i n g p e r i o d . Because t h e r e s u l t s were incomplete, a g e n e r a l d i s t r i b u t i o n of t h e r e p o r t s was n o t made. An e x t e n s i o n of t h i s c o n t r a c t t o complete t h e d e t a i l s of t h e three-dimensional, s i n g l e - c e n t e r case and t o extend t h e e x i s t i n g work t o t h e r e s t r i c t e d three-body problem, i s expected. 8. Honeywell (NAS8-21063) O b j e c t i v e : To i n v e s t i g a t e f u r t h e r t h e a p p l i c a t i o n of t h e s t a t i s t i c a l o p t i m i z a t i o n technique developed under NAS8-11206. The o p t i m i z a t i o n program has been s u c c e s s f u l l y extended t o use a h i g h - o r d e r model of t h e launch v e h i c l e , and t h e optimum g a i n s have been c a l c u l a t e d assuming t h a t a l l s t a t e s a r e measurable. A d i s c r e p a n c y i n t h e q u a l i t a t i v e r e s u l t s o b t a i n e d under t h i s c o n t r a c t and t h e p r o j e c t - o r i e n t e d r e s u l t s o b t a i n e d on t h e same v e h i c l e under c o n t r a c t NAS8-21171 l e d t o t h e d i s c o v e r y of a d a t a e r r o r i n t h e i n p u t d a t a f o r t h e o p t i m i z a t i o n program. This e r r o r has been c o r r e c t e d i n s o f a r a s p o s s i b l e w i t h i n t h e a v a i l a b l e funds. However, some of t h e q u a l i t a t i v e r e s u l t s on t h e s e n s o r c h o i c e problem appearing i n t h e f i n a l r e p o r t w i l l have t o be based on t h e i n c o r r e c t d a t a . �There s t i l l e x i s t some convergence problems i n t h e i t e r a schcmc used t o o b t a i n t h e q u a d r a t i c o p t i m i z a t i o n problem equival c n t t o t h c o r i g i n a l o p t i m i z a t i o n problem, which i s minimizing t h e 1 i k c L illood of f a i l u r e . However, a g r a d u a t e s t u d e n t a t Purdue, motiv a t c d by t h e g e n e r a l a p p l i c a b i l i t y of t h e o p t i m i z a t i o n technique used i n t h e s t u d y , has provided a n improved convergence technique. I f t h i s technique checks o u t , i t w i l l be documented i n t h e f i n a l r e p o r t . lr i v c A s m a l l c o n t r a c t e x t e n s i o n has been l e t t o permit t h e documentation o f t h e o p t i m i z a t i o n program used i n t h i s s t u d y , s o t h a t the program can b e used i n f u t u r e in-house r e s e a r c h w i t h o u t d u p l i c a t i n g t h e expense involved i n developing t h e program. It i s planned t h a t MSFC personnel w i l l go t o ~ o n e y w e l l ' s f a c i l i t y t o become f a m i l i a r w i t h the o p e r a t i o n of t h e program b e f o r e i t s t r a n s f e r r a l t o MSFC. F i n a l w r i t t e n and o r a l r e p o r t s on t h e r e s u l t s of t h i s s t u d y a r e expected w i t h i n the next reporting period. �IV. PROJECTS OFFICE 1. AAP Experiments C a p a b i l i t y This Laboratory has been p a r t i c i p a t i n g i n AAP Experiments Comp a t i b i l i t y s t u d i e s d u r i n g A p r i l and May t o determine t h e f e a s i b i l i t y of i n c l u d i n g experiments which w i l l r e t u r n d a t a p e r t a i n i n g t o the n a t u r a l r e s o u r c e s on e a r t h . These e a r t h r e s o u r c e s experiments a r e p r i m a r i l y photographic experiments i n b o t h t h e v i s u a l and i n f r a - r e d spectrum. A r e p o r t was made t o M r . Luskin on May 15 on t h e e a r t h r e s o u r c e s e x p e r i ments i n which t h i s Laboratory p r e s e n t e d t h e o r b i t a l a l t i t u d e l i n c l i n a t i o n c o n s i d e r a t i o n s , t h e miss i o n sequence, and some of t h e p o i n t i n g and c o n t r o l problems. This s t a t u s r e p o r t showed t h a t t h e r e has been major i n c o m p a t i b i l i t y recognized which would n o t a l l o w any proposed e a r t h r e s o u r c e s t o f l y ; however, f u r t h e r s t u d i e s were r e q u i r e d . F u r t h e r e f f o r t i s proceeding under a group formed by t h e Mission Requirements A r e p o r t w i t h recommendations Panel and headed by M r . Sims (R-AERO-P). concerning t h e f e a s i b i l i t y of f l y i n g e a r t h r e s o u r c e s experiments i s t o be made t o D r . Mueller i n t h e l a t t e r p a r t of June. 2. S a t u r n V SE&IS C o n t r a c t The Boeing Company submitted a proposal on MSFC Supplemental Agreement 262, implementation of launch schedule APD-4H. This proposal i s being reviewed w i t h i n t h e l a b o r a t o r y t o i n s u r e t h a t t h e S a t u r n V program o b j e c t i v e s w i l l be accomplished. N e g o t i a t i o n s on t h i s c o n t r a c t change a r e expected t o b e g i n i n mid-June. V. AEROPHYSICS DIVISION A. Mechanical Design O f f i c e 1. A new d e s i g n of a f u l l s c a l e High Reynolds Number Equipment Diaphragm C u t t e r using a four-arm g r i d s u p p o r t has been completed. T e s t s i n d i c a t e d t h a t a four-arm g r i d g i v e s b e t t e r diaphragm p e t a l ing than t h e 8-arm g r i d p r e v i o u s l y used. 2. A r e q u e s t has been made by R-AERO-AD f o r s i x S a t u r n V f o r c e models f o r t e s t i n g i n MSFC 14" wind t u n n e l . Four of t h e models w i l l have "bent" c e n t e r l i n e s i n o r d e r t o determine t h e e f f e c t of v e h i c l e bending on s t a t i c aerodynamics of t h e S a t u r n V. ME Laboratory has been r e q u e s t e d t o make s t u d i e s t o determine t h e most economical method of f a b r i c a t i n g t h e "bent" models. Design w i l l begin when t h e s e s t u d i e s a r e completed. �3 . The following i s a p a r t i a l l i s t of a d d i t i o n a l p r o j e c t s and t l ~ c i rc u r r e n t s t a t u s . Redesign of F l a t P l a t e Protuberance Heat T r a n s f e r Model, L. R . C . , 4' WT (AT) Design Heated Plenum Chamber, L. D. WT (AE) Design C a l i b r a t i o n Equipment f o r High Reynolds Number T e s t Equipment (AE) Design Sapphire Windows, S. T. S . , 14" WT, X-Beam (AE) Design 5 Component Micro Force Balance, L. D. C. Drafting 4" O.D. P r e s s u r e Model, L. T. V . , (AE) WT (AD) Drafting Pneumatic Work Bench (NSC) (A) Drafting Nozzle and Plenum, Laser Beam (A) Drafting Redesigned Survey Probe, 14" WT (AE) Fabrication Low Volume Diaphragm C u t t e r , IBFF (AE) Fabrication V a r i a b l e P o r o s i t y Transonic T e s t S e c t i o n Fabrication 18.75% P i l o t Model, High Reynolds T e s t Equipment (AE) V a r i a b l e P o r o s i t y Transonic T e s t S e c t i o n High Reynolds T e s t Equipment (AE) Fabrication Strap-On Force Model, 14" WT (AD) Fabrication T r a c e r M a t e r i a l I n j e c t o r , X-Beam, S.T.S., 14" WT (A) Fabrication Major Components, High Reynolds Number T e s t Equipment Fabrication ( P a r t i a l Delivery) P r e s s u r e Models, X-Beam, SST, 14" WT (AF) Delivered S l o s h Force Measuring System (DD) n e l ivered 5" O . D . , S a t . V. Base Flow Model, X-Beam 14" WT (A) Force Models, Experimental, L. D. C . (AE) Delivered Delivered �B. Design Branch 1. O r b i t a l Workshop Aerodynamics The S a t u r n I B o r b i t a l workshop v e h i c l e e x t e r n a l c o n f i g u r a t i o n has been changed s e v e r a l times a n d , a t p r e s e n t , a frustum a n g l e i n c r e a s e from B058' i s being c o n s i d e r e d . S i n c e aerodynamic d a t a a r e r e q u i r e d f o r s t r u c t u r a l t r a j e c t o r y and c o n t r o l a n a l y s i s , t h e aerodynamic c h a r a c t e r i s t i c s were d e f i n e d f o r the c u r r e n t c o n f i g u r a t i o n . S t a b i l i t y d a t a were based on small model wind t u n n e l t e s t conducted i n t h e MSFC 14" t r i s o n i c wind t u n n e l . Local normal f o r c e c o e f f i c i e n t d i s t r i b u t i o n s were defined based on e x p e r i m e n t a 1 , a n a l y t i c a l and e m p i r i c a l d a t a . Data a r e p r e s e n t e d f o r a n g l e s of a t t a c k of 0 t o 10 degrees f o r Mach numbers 01 0.8 t o 2.0. These d a t a a r e published i n o f f i c e memorandum R-AEROAD-68-24. 2. S o l a r Panel Shroud and APS F a i r i n g s f o r S-IB/AAP-11 By t h e end of February 1968, i t became e v i d e n t t h a t R-P&VE was n e a r i n g completion of t h e s t r u c t u r a l d e s i g n of t h e s o l a r panel U n t i l t h i s time, no shroud and APS f a i r i n g s f o r t h e S a t u r n IB/AAP-11. experimental d a t a had been obtained t o v e r i f y e s t i m a t e d load d i s t r i b u t i o n s . To i n c o r p o r a t e a p o s s i b l e weight s a v i n g s i n t h e d e s i g n of t h e s e u n i t s , R-P&VE needed t h e s e d a t a by a b o u t t h e second week of A p r i l 1968. T e s t s were conducted i n t h e MSFC t r i s o n i c wind t u n n e l d u r ing t h e second week of A p r i l 1968. P r e s s u r e d i s t r i b u t i o n s were obtained a t Mach numbers from 0.8 t o 1.96 f o r a n g l e s of a t t a c k up t o 8 d e g r e e s . These d a t a were f u r n i s h e d t o R-P&VE approximately one week l a t e r than promised because of l a c k of t i m e l y s u p p o r t i n model d e s i g n and f a b r i c a t i o n . 3 S a t u r n S-IVB APS R1E Engine Plume D e f i n i t i o n f o r Plume Impingement Analyses Plume c h a r a c t e r i s t i c s (Mach number, p r e s s u r e , t e m p e r a t u r e , d e n s i t y , and chemistry p r o f i l e s ) f o r t h e R1E engine of t h e S-IVB APS u n i t s have been developed. These d a t a , which a r e a p p l i c a b l e f o r p e r f orrning plume impingement and contamination a n a l y s e s over a f f e c t e d a r e a s of t h e S-IVB workshop v e h i c l e , a r e p r e s e n t e d i n o f f i c e memorandum R-AERO-AD-68-34, May 1 7 , 1968. 4. S a t u r n V High A l t i t u d e Flow S e p a r a t i o n E f f e c t s on Vehicle Stability An a n a l y s i s i s being made t o determine t h e e f f e c t s of flow The flow s e p a r a s e p a r a t i o n on S a t u r n V s t a t i c s t a b i l i t y aerodynamics. t i o n , caused by t h e expanding exhaust plume, has been observed b o t h on t h e ground and from a i r c r a f t . From t h e s e o b s e r v a t i o n s , t h e p o i n t of flow s e p a r a t i o n has been d e f i n e d a s a f u n c t i o n of a l t i t u d e . �A l l changes i n t h e aerodynamics due t o flow s e p a r a t i o n w i l l occur a f t e r Mach 3.0. Vellicle c o n t r o l w i l l n o t be g r e a t l y a f f e c t e d hccilr~sc of the low dynamic p r e s s u r e . R e s u l t s of t h i s a n a l y s i s w i l l be pub1 ished i n t h e near f u t u r e . 5. AS-205/CSM Axial Force C h a r a c t e r i s t i c s Power-on a x i a l f o r c e c o e f f i c i e n t s were r e v i s e d f o r the AS-ZO~/CSMv e h i c l e based on t h e AS-203 and AS-204 f l i g h t d a t a . These v e h i c l e s had t h e c o r r e c t base c o n f i g u r a t i o n w i t h t h e engine shrouds removed and t u r b i n e exhaust d u c t s r e r o u t e d . F l i g h t d a t a r e f l e c t a d e c r e a s e i n t o t a l a x i a l f o r c e c o e f f i c i e n t . The l i f t - o f f term which has been included i n t h e a x i a l f o r c e c o e f f i c i e n t i s now d e l e t e d based on f l i g h t r e s u l t s . These d a t a a r e published i n o f f i c e memorandum K-AERO-AD-68-25. 6. S a t u r n V Power-On Aerodynamic Drag An improved method of p r e s e n t i n g v e h i c l e a x i a l f o r c e has been developed t o more a c c u r a t e l y d e f i n e b a s e d r a g e f f e c t s d u r i n g f i r s t stage flight. The new approach d e f i n e s a forebody a x i a l f o r c e coeff i c i e n t a s a f u n c t i o n of Mach number and a curve o f ' a v e r a g e b a s e p r e s s u r e (Pb - P,) v e r s u s a l t i t u d e . T o t a l v e h i c l e d r a g i s computed by summing t h e above curves f o r a g i v e n Mach number, a l t i t u d e , and dynamic p r e s s u r e . P r e l i m i n a r y a n a l y s i s of AS-502 f l i g h t d a t a i n d i c a t e s a 25 p e r c e n t d e c r e a s e i n a x i a l f o r c e from t h e d e s i g n d a t a i n NASA TM X-53517. About 15 p e r c e n t of t h i s d e c r e a s e i s due t o scoop removal. The remainder of t h e d i f f e r e n c e i s caused by t h e d i f f e r e n c e between f l i g h t d a t a and wind t u n n e l t e s t s . F i n a l d a t a w i l l be published t o update d e s i g n a x i a l force . 7. Q-Ball Angle of A t t a c k Sensor S i n c e MSC i s c o n s i d e r i n g removing t h e q - b a l l cover p o s s i b l y t h i r t y minutes b e f o r e v e h i c l e launch, A s t r i o n i c s Laboratory i s concerned a b o u t t h e e f f e c t s of r a i n on t h e q - b a l l d u r i n g t h i s time p e r i o d . A s t r i o n i c s has a l s o reopened t h e q u e s t i o n of f l y i n g through r a i n and c l o u d s . No complete environmental t e s t i n g has e v e r been accomplished on t h e q - b a l l because, i n t h e p a s t , R&D v e h i c l e s were n o t flown i n r a i n . But, w i t h t h e moon s h o t launch windows being l i m i t e d , S a t u r n V v e h i c l e s may b e f i r e d r e g a r d l e s s of t h e weather. A s t r i o n i c s has asked R-AERO-AD t o h e l p i n planning and running n e c e s s a r y t e s t s t o determine t h e e f f e c t s of r a i n on t h e q - b a l l . �8. Orif i c e Flow C o e f f i c i e n t I n v e s t i g a t i o n The t e s t d a t a from Ames, which i s being p l o t t e d on t h e 7090 Computer a t t h e Computation Laboratory, a r e almost complete; NSL w i l l publish a f i s a l data report. Because of t h e unavoidable d e l a y s encountered d u r i n g t h i s program which d e p l e t e d t h e c o n t r a c t f u n d s , t h e a d d i t i o n a l t e s t s scheduled f o r t h e MSFC 14-inch TWT and t h e IBFF have been postponed i n d e f i n i t e l y . NSL has r e c e i v e d a four-month no-cost c o n t r a c t e x t e n s i o n t o a l l o w them t o f i n i s h t h e r e p o r t work. The major d e l a y s which occurred a t Ames were due t o (1) l a s t-minute s c h e d u l e changes and instrument m a l f u n c t i o n s , (2) t h e i r d e l a y i n sending MSFC f i n a l d a t a , and ( 3 ) Computation L a b o r a t o r y ' s d e l a y i n m a n i p u l a t i n g and p l o t t i n g t h e d a t a . 9. Body of Revolution Viscous Cross-Flow I n v e s t i g a t i o n P r e s s u r e t e s t s of t h e v i s c o u s c r o s s - f l o w models a r e underway i n t h e MSFC 14-inch TWT. The f o u r models c o n s i s t of two c o n f i g u r a Each t i o n s : a n o g i v e - c y l i n d e r and a n o g i v e - c y l i n d e r - f r u s t u m - c y l i n d e r . c o n f i g u r a t i o n has two model s i z e s : a 1 . 0 - i n c h diameter and a n 0.5-inch d i a m e t e r . The Mach number range i s 0.40 through 1.96, and t h e a n g l e of a t t a c k range i s 0, 5 , 10, 15, 20 and 25 d e g r e e s . Model i n s t a l l a t i o n and d a t a a c c u r a c y problems may cause a two- t o three-week d e l a y i n comp l e t i n g t h e program. C. Experimental Aerophysics Branch 1. Low ens i t y Chamber The i n v e s t i g a t i o n of t h e use of t h e Low Density Chamber a s t h e a l t i t u d e s i m u l a t o r f o r performing t h e j e t plume impingement t e s t a n d l o r determining t h e a p p r o p r i a t e n e s s of C02 gas a s t h e t e s t medium h a s continued. To determine i f C02 i s s a t i s f a c t o r y a s a t e s t medium, t h e following experiments were designed and a r e being prepared: (a) Determination of t h e o n s e t a n d / o r presence of condens a t i o n i n t h e C02 plume by impact p r e s s u r e measurement techniques and l i g h t s c a t t e r i n g t e c h n i q u e s . (b) Impact p r e s s u r e survey of C02 plume'for comparison t o a t h e o r e t i c a l plume. (c) Measurement of f o r c e s and moments produced by a C02 j e t exhausting p a r a l l e l t o a f l a t p l a t e i n a vacuum ( f o r comparison t o pub1 ished d a t a ) . �A l l ol: tllc. cxpcrimcntal hardware has been ordered and i s on hand ( i n c l u d ing a 2-component b a l a n c e f o r experiment c ) w i t h t h e e x c e p t i o n of model n o z z l c s . Altllough t h e c l o s e t o l e r a n c e s on t h e s e n o z z l e s p r e s e n t a problem i n manufacturing, a t t e m p t s a r e s t i l l being made t o f a b r i c a t e them. Some t e s t s have a l r e a d y been r u n t o observe t h e presence of C 0 2 condensation i n t h e plume, u s i n g t h e l i g h t - s c a t t e r i n g technique. A 1 though no q u a n t i t a t i v e r e s u l t s were o b t a i n e d , flow v i s u a l i z a t i o n of t h e condensation i n t h e plume was f u r n i s h e d . F u r t h e r t r i a l s a r e being made t o r e f i n e t h e photographs f o r documentation. 2. IBFF The Impulse Base Flow F a c i l i t y has completed t h e Mach 2 s t a r t i n g load phase of the p i l o t model High Reynolds Number program. The d a t a , which i n c l u d e a n a n g l e of a t t a c k range from 0 t o 18 degrees w i t h charge p r e s s u r e s from 65 t o 715 p s i a , a r e being a n a l y z e d . Subs o n i c and t r a n s o n i c f o r c e d a t a phases a r e scheduled t o b e g i n t h e week 01 May 27. Following t h e f o r c e t e s t s , blockage t e s t s a r e scheduled. Some problems have been encountered w i t h t h e s t r a i n gauge b a l a n c e system used t o measure model s t a r t i n g load. High p r e s s u r e (715 p s i a ) environments w i t h a r a p i d decompression seem t o a f f e c t t h e s t r a i n gauge bond. A f t e r s e v e r a l load a p p l i c a t i o n s , l a r g e z e r o s h i f t s o c c u r r e d . I n s p e c t i o n r e v e a l e d numerous bubbles under t h e gauges, n e c e s s i t a t i n g regaging . Plans a r e being made f o r the f l a t - p l z t e s i n g l e - n o z z l e phase of t h e p a r a m e t r i c program t o f o l l o w t h e p i l o t model HRE program. Run sclledules have been r e c e i v e d , and d e s i g n i s under way f o r p l a t e mounting. A c o n i c a l n o z z l e and a contoured n o z z l e (5-2), which have been r e c e i v e d , a r e ready f o r i n s t a l l a t i o n . This i n v e s t i g a t i o n must be scheduled i n l i g h t of o t h e r p r o j e c t s and a v a i l a b i l i t y of manpower. The High Reynolds Number T e s t Equipment program has made c o n s i d e r a b l e p r o g r e s s d u r i n g t h e p a s t two months. Concrete work f o r t h e s u p p l y tube s u p p o r t s and 1,000,000 l b s t h r u s t anchor has been completed. Welding of t h e s u p p l y tube and a i r reducing s t a t i o n i s scheduled t o b e g i n i n e a r l y June. The f o l l o w i n g i s a l i s t of hardware items and t h e i r confirmed d e l i v e r y d a t e s : (a) (b) D i f f u s e r and s p o o l s Tension rods June 3 J u l y 18 �(c) (d) (e) Bridge f o r crane Model s u p p o r t Supersonic t e s t s e c t i o n June 15 July 8 J u l y 22. C a l i b r a t i o n model requirements have been forwarded t o t h e Mechanical Design O f f i c e . Model p r e s s u r e s w i l l be measured w i t h t h e trapped volume technique. I n s t r u m e n t a t i o n r e q u i r e d f o r t h i s technique has been o r d e r e d . A group from AEDC s p e n t a day a t t h e Wind Tunnel looking a t t e s t d a t a and q u e s t i o n i n g personnel a b o u t our High Reynolds T e s t Equipment. AEDC t e n t a t i v e l y plans t o b u i l d a tube wind t u n n e l w i t h a 1 2 - f o o t diameter t e s t s e c t i o n , a 1000 long supply t u b e , 500 p s i a s t a g n a t i o n p r e s s u r e , configured much l i k e t h e MSFC equipment. Two groups from Boeing have a l s o v i s i t e d r e c e n t l y f o r d i s c u s s ions concerning t h e i r pos s i b l e development of a tube wind t u n n e l . - 4. Thermal-Acous t i c J e t F a c i l i t y (TAJF) Tes t s a r e c o n t i n u i n g by R-AERO-AF personne 1 us ing t h e c r o s s beam system. T o t a l runs t o d a t e : 269. Power and h i g h p r e s s u r e gas connections t o t h e helium h e a t e r have s t i l l n o t been made. The c o n t r a c t l ~ a sn o t y e t been awarded, b u t i s expected any day, Since t h e c o n t r a c t c a l l s f o r completion w i t h i n 60 d a y s , hookup might be made b e f o r e t h e end of J u l y . 5. 1.4 x 14-Inch T r i s o n i c Wind Tunnel The f o l l o w i n g t e s t s were r u n d u r i n g A p r i l and May 1968: ( a ) An i n v e s t i g a t i o n f o r R-AERO-AF i n t o t h e flow and a c o u s t i c c h a r a c t e r i s t i c s of t h e 14" T r i s o n i c wind t u n n e l s p e c i a l t e s t s e c t i o n . The work was i n p r e p a r a t i o n f o r f u t u r e t e s t s using t h e c r o s s beam c o r r e l a t i o n equipment. P r e s s u r e and a c o u s t i c surveys were made a l o n g the high speed S c h l i e r e n movies f o r shock f l u c t u a t i o n . T o t a l runs: 64. (b) An i n v e s t i g a t i o n f o r R-AERO-AD t o o b t a i n p r e s s u r e d a t a t o v e r i f y e s t i m a t e d load d i s t r i b u t i o n s on t h e s o l a r panel shrouds and APS u n i t s of t h e S a t u r n 113/AAP-I1 v e h i c l e . T o t a l r u n s : 38. ( c ) An i n v e s t i g a t i o n t o determine t h e reduced a x i a l f o r c e due t o removing t h e base flow d e f l e c t o r s from t h e Apollo-Saturn V launch v e h i c l e . The i n v e s t i g a t i o n compared d a t a t o t h a t o b t a i n e d from c o r n e l l ' s 8 - f o o t Transonic Tunnel. T o t a l r u n s : 4 4 . �( d ) A p r e l i m i n a r y e n t r y f o r R-AERO-AD on t h e v i s c o u s c r o s s - 1 l ow inves t i g a t i o n . P r e s s u r e and f o r c e d a t a were obtained on [our models. These d a t a w i l l b e compared w i t h f u t u r e t e s t s . T o t a l r u n s : 55. ( e ) A c o n t i n u a t i o n of t h e i n v e s t i g a t i o n of v i s c o u s c r o s s flow. This p r e s s u r e phase, being conducted by ~ h r y s l e rs' Space D i v i s i o n f o r R-AERO-AD, i s c u r r e n t l y i n p r o g r e s s . To i n c r e a s e t h e t u n n e l r u n r a t e , R-TEST aFr and compressed a i r from t h e t u n n e l compressors a r e being used s imul taneous l y . 6. 7 x 7-Inch B i s o n i c Tunnel The BWT was r e c a l i b r a t e d d u r i n g t h e r e p o r t i n g period t o cover c e n t e r l i n e a s w e l l a s o f f - c e n t e r 1 i n e Mach number d i s t r i b u t i o n s . The complete s u b s o n i c and s u p e r s o n i c range was covered. T o t a l r u n s : 110. 7. I n s trumenta t i o n The protuberance model was r e c e i v e d May 3 --form --. t h e AEDC shops f o r t h e i n s t r u m e n t a t i o n of t h e 122 a c o u s t i c channels and 400 s t a t i c p r e s s u r e s . Assembly time f o r t h e i n s t r u m e n t a t i o n was reduced by t h r e e man months of e f f o r t s i n c e i t was p o s s i b l e t o use t h e w i r i n g a s s e m b l i e s removed from t h e 4 p e r c e n t S a t u r n V a c o u s t i c s model which was t e s t e d a t AEDC a b o u t one y e a r ago. A - The model was shipped t o AEDC May 14, and t e s t i n g began May 20. The f i r s t n i g h t of t e s t i n g was i n v a l i d a t e d because of a t u n n e l water l e a k . Water c o n c e n t r a t i o n s were s o heavy t h a t t h e model had t o be t a k e n a p a r t t h e n e x t day, each s t a t i c p r e s s u r e l i n e blown d r y , and t h e S c a n i v a l v e s disassembled, c l e a n e d , and d r i e d . P a r t s of t h e model r e q u i r e d b a i l i n g o u t of t h e w a t e r . T e s t i n g i s expected t o c o n t i n u e through June 5 . 8. Data Reduction Besides t h e normal t e s t d a t a , approximately 800 d a t a c a s e s were processed f o r t h e shadow s c a n n e r . Most of t h i s work is done on t h e CDC 3200 l o c a t e d i n B u i l d i n g 4200. D. Thermal Environment Branch 1. The s p e c t r o r a d i o m e t e r i n s t r u m e n t a t i o n system developed by Rocketdyne under C o n t r a c t NAS8-21144 has been i n s t a l l e d and checked o u t i n t h e B-3 t e s t c e l l a t t h e Rocketdyne Nevada F i e l d Laboratory (NFL). T e s t s on FLOX/CH4 p r o p e l l a n t combination, c u r r e n t l y underway, a r e being �monitored. I n a d d i t i o n t o our use of t h e d a t a from t h e s e t e s t s , t h e r e s u l t s w i l l b e used by Langley Research Center and Rocketdyne a s a d e s i g n a i d i n t h e development of a h i g h performance i n j e c t o r . 2. The hardware and t e s t s e t - u p f o r t h e experimental composite engine s t u d y (NAS7-521) being done by Rocketdyne has been completed. Because of a n e x p l o s i o n i n t h e a d j a c e n t t e s t c e l l , t h e i n s t r u m e n t a t i o n system was damaged, b u t t h i s has been r e p a i r e d and f u l l s c a l e t e s t i n g i s t o begin i n J u l y . 3 . Two c o n t r a c t s w i t h t h e General Applied Science L a b o r a t o r i e s , Both of I n c . have r e c e n t l y been i n i t i a t e d : NAS8-21264 and NAS8-21387. t h e s e c o n t r a c t s a r e f o r a n a l y t i c a l s t u d i e s of r e a c t i n g gas flows and t h e i r e f f e c t on p r o p u l s i o n systems. Progress on t h e s e e f f o r t s w i l l be r e p o r t e d i n more d e t a i l l a t e r . 4 . High a n g l e of a t t a c k h e a t i n g t e s t s : A t r i p was made t o Langley Research Center d u r i n g t h e week of May 12 t o d i s c u s s h i g h a n g l e o f - a t t a c k h e a t i n g t e s t s t o b e r u n a t LRC. It was l e a r n e d t h a t t h e U n i t a r y P l a n Tunnel w i l l be down on t h e o r i g i n a l l y planned d a t e t o e n t e r t h e t u n n e l (mid-July). Consequently, t h e t e s t d a t e has been changed t o t h e f i r s t of J u l y . The p r e s e n t model s t i n g e r , intended f o r AEDC, i s n o t a d a p t a b l e f o r e i t h e r U n i t y P l a n o r 20-inch t u n n e l s of LRC. Drawings llave been made f o r new s t i n g e r s , and t h e machining should commence d u r i n g t h e l a s t week of May. 5. R a d i a t i o n and low d e n s i t y drag c o e f f i c i e n t view f a c t o r program: Checking o u t t h e r a d i a t i o n view f a c t o r computer program and documentation of t h e Modified F r e e Molecular Drag Program continued. Documentation of t h e R a d i a t i o n View F a c t o r Program was s t a r t e d d u r i n g t h i s p e r i o d . A d d i t i o n a l funds t o c o n t i n u e work on t h i s s t u d y i n t h e a r e a s of s p e c t r a l r a d i a t i o n , r e f l e c t e d r a d i a t i o n , and t h e use of t h e contour i n t e g r a l method have been r e q u e s t e d . 6. O r b i t a l Workshop S o l a r Array: A thermal a n a l y s i s of t h e S-IVB O r b i t a l Workshop s o l a r a r r a y has been i n i t i a t e d . This s t u d y should be completed by t h e week of May 26. E. Unsteady Aerodynamics Branch 1. S a t u r n I B Ground Winds S t u d i e s f o r modifying a p r e v i o u s l y c o n s t r u c t e d S a t u r n I B a e r o e l a s t i c wind t u n n e l model t o s i m u l a t e t h e AAP-2 and AAP-4 c o n f i g u r a t i o n s a r e b e i n g continued. �P r e d i c t i o n s of ground-wind-induced l o a d s f o r S a t u r n I B , AS-205 v e h i c l e s i n t h e completely f u e l e d and empty weight c o n d i t i o n s have been completed. These d a t a were published A p r i l 24, 1968. A l l a v a i l a b l e S a t u r n I B wind t u n n e l t e s t d a t a were examined I o r e s t a b l i s h i n g c r i t i c a l wind v e l o c i t i e s f o r t h e S a t u r n I B AS-205 i n t h e i n t e r m e d i a t e weight c o n d i t i o n s . Recommendations f o r e s t a b 1 i s h i n g t h e s e c r i t i c a l wind v e l o c i t i e s were published May 23, 1968. 2. S a t u r n V Ground Winds An o n - s i t e i n s p e c t i o n was made of t h e p r o g r e s s i n f a b r i c a t i o n of a n Uprated S a t u r n V ground winds model by Atkins and M e r r i l l , I n c . An e x t e n s i o n has been i n i t i a t e d t o t h e c o n t r a c t f o r t h e model completion. The c o n t r a c t should be completed by mid-July. A s t u d y f o r determining t h e second mode e f f e c t s on ground wind l o a d i n g s of the S a t u r n V f u e l e d weight c o n d i t i o n i s i n p r o g r e s s . P r e d i c t i o n of s t a t i c wind loads f o r t h e S a t u r n V v e h i c l e w i t h t h e LUT and MSS c o n f i g u r a t i o n i s completed. These r e s u l t s should be published s h o r t l y . 3. I n f 1i g h t Acoustics a . Systematic phase and amplitude d i s t o r t i o n s t h a t occurred i n d a t a a c q u i s i t i o n and r e d u c t i o n systems used i n t h e f o u r - p e r c e n t AEDC experiment have been determined e x p e r i m e n t a l l y by Baganoff and A s s o c i a t e s . The r e s u l t s show t h a t we may c r o s s - c o r r e l a t e any two d a t a channels w i t h i n a t a p e r e c o r d e r head and produce o n l y 0.2 db amplitude and 2.0 degree phase d i s t o r t i o n s , and a c r o s s r e c o r d e r heads i t i s p o s s i b l e t o produce f i n a l r e s u l t s w i t h a s c a t t e r band of 0.5 db amplitude and 5.0-degree phase. These d a t a were p r e s e n t e d f o r t h e f u l l frequency r a n g e of 10 t o 20 k i l o h e r t z . b . A d d i t i o n a l f l u c t u a t i n g p r e s s u r e d a t a r e c e i v e d from Baganoff and A s s o c i a t e s w i l l be forwarded t o R-P&VE-S. The v e r y l a r g e volume of cross-power s p e c t r a l d e n s i t y i n f o r m a t i o n t o b e forwarded r e p r e s e n t s f a i r l y comprehensive p r e l i m i n a r y r e s u l t s f o r t h e z e r o a n g l e of a t t a c k c o n d i t i o n . c . A d d i t i o n a l c o n t r a c t work f o r t h e "Development of F u l l I n - f l i g h t A c o u s t i c Design C r i t e r i a S c a l i n g E f f e c t s " i s being i n i t i a t e d . Data from Ames f o u r p e r c e n t S a t u r n V , PSTL-1 and PSTL-2 wind t u n n e l c o n d i t i o n s , and f l i g h t w i l l be used a s w e l l a s o t h e r d a t a a v a i l a b l e i n t h e 1i t e r a t u r e . �(1. Kequcs ts f o r e s t i m a t e s of i n f l i g h t environments f o r Lot~rspc.c i f i c , mod i f ied l a u n c l ~c o n f i g u r a t i o n s have been r e c e i v e d . These conLi.gtlrations involve the use of t h e S a t u r n V b o o s t e r (a I B b o o s t e r w i t h a C c ~ ~ t i l uupper r s t a g e ) . The environmental e s t i m a t e s f o r t h e s e conf i g u r a t i o n s w i l l be published a s soon a s p o s s i b l e . e . The FEWG i n p u t f o r unsteady aerodynamic ( a c o u s t i c , f l u t t e r , e t c . ) i s i n t r a n s i t i o n and w i l l be t h e f u l l r e s p o n s i b i l i t y of R-AERO-AU. There a r e c o n s t r a i n t s f o r providing FEWG i n p u t d a t a which w i l l c r e a t e i n c r e a s e d manpower e f f o r t f o r a p e r i o d of time b e f o r e and a f t c r a f l i g h t . The a c o u s t i c problems i n meeting t h e AS-502 r e q u i r e ments of t h e FEWG a r e due mainly t o computer problems a t Comp. Lab. Thcsc problems should be solved b e f o r e t h e n e x t f l i g h t ; o t h e r w i s e , t h e n e x t FEWG r e p o r t may be delayed. The a d d i t i o n a l i n c r e a s e i n manpower c f l o r t n e c e s s a r y f o r providing d a t a and a t t e n d i n g meetings f o r FEWG i n p u t w i l l d e l a y t h e d e t a i l e d a n a l y s e s of t h e inhouse t e c h n i c a l evaluat i o n and a p p l i c a t i o n s of p a s t , c u r r e n t , and f u t u r e f l i g h t d a t a . Howe v e r , because of t h e AS-502 problems, t h e s e d a t a a r e b e i n g analyzed inhouse a s f a s t a s they become a v a i l a b l e . Also f i l m s have been r e q u e s t e d f o r a n a n a l y s i s of t h e flame f r o n t s t a b i l i t y o r plume motion i n t h e f i v e h e r t z o s c i l l a t i o n s observed on AS-502. Houston has s e v e r a l of t h e f i l m s and a p p a r e n t l y a r e r e l u c t a n t t o r e t u r n them. A n a l y s i s w i l l proceed when f i l m s become available. 4. Launch S i t e Acoustics a . The conference on n o i s e a l l e v i a t i o n f o r s u b s o n i c a i r c r a f t , t o be h e l d a t Langley Research Center i n October 1968, w i l l be t h e s u b j e c t of a planning meeting a t Headquarters on June 11. The a b s t r a c t s f o r a l l t h e c e n t e r s ' p r e s e n t a t i o n s have been provided f o r t h e MSFC p e r s o n n e l involved i n t h i s program. Three t e n t a t i v e papers a r e planned from MSFC: (1) a paper on t h e crossed-beam system of D r . Krause, a paper on a c o u s t i c f o c u s i n g by 0 . E. Smith, and a t o p i c on p r o p a g a t i o n ane excess ground a t t e n u a t i o n e f f e c t s by S. Guest. b. The v e h i c l e a c o u s t i c f l i g h t d a t a r e p o r t s f o r AS-501 and 502 a r e being prepared. Because of some d a t a s h o r t a g e s caused by computer problems a t t h e Comp. Lab., d a t a s u b s t i t u t i o n s have been made which a r e The a c o u s t i c a n a l y z e r n o t meeting t h e o r i g i n a l requirements of R-AERO-AU. system has been r e t u r n e d t o t h e manufacturer f o r r e p a i r s . c . A program f o r t h e d e t e r m i n a t i o n of excess ground a t t e n u a t i o n i n t h e p r o p a g a t i o n of a c o u s t i c energy has been developed and i s working a t Lockheed f o r some 60 t e s t s of l a r g e b o o s t e r s o r r o c k e t engines a t MSFC from 1965 t o 1967. The m e t e o r o l o g i c a l d a t a a r e t o be used i n t h i s �program t o bcs t e v a l u a t e the d a t a a c q u i s i t i o n c o n d i t i o n s and t o look f o r the POSS i b l e i n £ luence of s e a s o n a l v a r i a t i o n s on t h e ground impedance f o r t l i i s s t u d y . Some 100,000 d a t a p o i n t s w i l l p e r m i t some s t a t i s t i c a l e v a l u a t i o n of t h e r e s u l t s f o r f i e l d use under g i v e n c o n d i t i o n s . d . The A c o u s t i c Model T e s t F a c i l i t y (AMTF) a t T e s t Lab, has been e f f e c t i v e l y s h u t down because of a n a p p a r e n t s h o r t a g e of manpower f o r o p e r a t i o n a l use. The S a t u r n V model p r e s s u r e amplitude and phase i n f o r m a t i o n has thus been delayed and i s n o t of s u f f i c i e n t p r i o r i t y i n T e s t Lab. t o a l l o w t e s t i n g i n t h e immediate f u t u r e . Other s i m i l a r programs have l i k e w i s e ceased. e . The R-AERO-AU i n p u t t o " P r e d i c t i o n s of B l a s t and Acoustic Environments of Large Space Boosters," a j o i n t NASA/AF hazards manual, has been completed. P r e l i m i n a r y d r a f t s of t h e hazards manual a r e a n t i c i p a t e d t h i s summer. f . P r e d i c t i o n of t h e A c o u s t i c Environment f o r t h e Nuclear Ground T e s t Module i s approximately 80 p e r c e n t complete. These environmental e s t i m a t e s w i l l be r e l e a s e d i n a memorandum when completed. 5. Panel F l u t t e r Dynamic s t r a i n d a t a from t h e AS-~O~/S-IVBforward s k i r t show evidence of panel f l u t t e r e x i s t i n g d u r i n g t h e s u p e r s o n i c f 1i ~ " ' regime. A f u l l r e p o r t i s being prepared. 6. Quasi-Steady A n a l y s i s T e s t d a t a from r e c e n t t e s t s on c o n v e c t i v e wake and f r e e o s c i l l a t i o n models a r e p r e s e n t l y being reduced and a n a l y z e d . Flow v i s u a l i z a t i o n t e s t s a r e planned i n June 1968, on a cone-cylinder-£ l a r e body. Also, b a l l i s t i c range t e s t s a t BRL on Apollo forebody c o n f i g u r a t i o n s a r e now scheduled i n June 1968. F a b r i c a t i o n of t h e shock-induced s e p a r a t i o n model (planned f o r f u t u r e t e s t i n g ) has been i n i t i a t e d . VI. DYNAMICS AND FLIGHT MECHANICS DIVISION A. Multi-Projects 1. Mission P r o j e c t s R e s t r i c t e d 3-Body Problems (New): I n order t o l a y a base f o r i n v e s t i g a t i o n i n t o f u t u r e m i s s i o n s t o t h e earth-moon 1i b r a t i o n p o i n t , t h e following s t u d y i s b e i n g performed. P e r i o d i c a s y m p t o t i c o r b i t s have been t r a c e d s u c c e s s f u l l y from e q u a l mass r a t i o s , y = 0 , t o a mass r a t i o , y = 0.9. The mass r a t i o y i s d e f i n e d : �where M1 and M2 a r e t h e masses of t h e p r i m a r i e s . It i s hoped t h a t t h e t r a c e can be s u c c e s s f u l l y c a r r i e d p a s t t h e c r i t i c a l mass r a t i o , y = 0.9229 ..., t o t h e mass r a t i o of t h e earth-moon system, y = 0.9757 The c r i t i c a l mass r a t i o is t h e mass r a t i o where t h e c h a r a c t e r i s t i c exponents of t h e s o l u t i o n s t o t h e l i n e a r i z e d e q u a t i o n s i n t h e neighborhood of t h e t r i a n g u l a r l i b r a t i o n p o i n t s change from complex t o pure imaginary. The complex c h a r a c t e r i s t i c exponents g i v e r i s e t o s p i r a l i n g motion i n t o o r o u t from t h e l i b r a t i o n p o i n t s , depending on whether t h e r e a l p a r t of t h e complex number i s n e g a t i v e o r p o s i t i v e . The pure imaginary exponent g i v e s r i s e t o p u r e l y p e r i o d i c motion s o t h a t when t h e c r i t i c a l mass r a t i o i s passed the o r b i t s change t h e i r b a s i c n a t u r e from s p i r a l i n g o r b i t s ( c a l l e d p e r i o d i c - a s y m p t o t i c ) t o p e r i o d i c o r b i t s i n t h e neighborhood of t h e t r i a h g u l a r l i b r a t i o n . (DAO) ... . 2. Guidance a. S-IVB S o f t Lunar Landing Study (Ref: 1968, p. 36) February-March A p r e s e n t a t i o n on t h e S-IVB s o f t l u n a r l a n d i n g s t u d y s t a t u s was g i v e n t o t h e R-AERO-D s t a f f d u r i n g A p r i l . The s t a t u s review covered t h e f o l l o w i n g t o p i c s : (1) (2) Basic mission p r o f i l e . An a n a l y t i c a l i n v e s t i g a t i o n of t h e changes i n t h e i t e r a t i v e guidance e q u a t i o n s t o perform 3-dimens i o n a l r e t r o - b u r n s . (3) Implementations and v e r i f i c a t i o n of t h e s e changes. (4) A n a l y t i c development of a n i g n i t i o n c r i t e r i o n f o r t h e l u n a r deboost and l u n a r l a n d i n g burns. (5) A p r e l i m i n a r y performance a n a l y s i s t o check t h e o p t i m a l i t y and a c c u r a c y of t h e guidance scheme. It was recommended t h a t performance improvement s t u d i e s b e i n i t i a t e d by R-AERO-DA. A t t h e p r e s e n t l e v e l of e f f o r t (112 man), t h e n e x t major s t a t u s review w i l l be i n approximately one y e a r . The f o l l o w i n g items w i l l be analyzed and r e p o r t e d on a t t h a t time: �(I) I n v e s t i g a t i o n of s i m p l i f i e d n a v i g a t i o n a l a i d s (beacon, e t c . ) t o provide information f o r i n p u t i n t o guidance scheme . b. (2) How t h i s i n f o r m a t i o n could be o b t a i n e d using curr e n t l y a v a i l a b l e hardware. (3) A d d i t i o n a l hardware, i f r e q u i r e d . (4) Boil-of f i n f o r m a t i o n from s t a g e c o n t r a c t o r s . (5) Optimum m i s s i o n p r o f i l e w i t h and w i t h o u t a b o i l off constraint. (6) Landing a t t i t u d e recommendations (DGINorthrop) mode. - u s i n g a hover S-11, 2 Engines Out (New) S - I 1 2-engines-out l o g i c was published i n a memorandum a s a n a c t i o n item from a meeting between ASTR and AERO l a b s . This l o g i c r e q u i r e s engine-out d i s c r e t e s i g n a l s . As f a r a s known, t h e d e c i s i o n t o implement f o r two engines has n o t been made. Even w i t h t h i s l o g i c , t h e S - I 1 s t a g e i s s t i l l n o t a d e q u a t e l y d e f i n e d a s f a r a s guidance i s concerned, A memorandum d e f i n i n g t h e S - I 1 s t a g e by o t h e r than p r e - s e t burn times i s b e i n g prepared. This d e f i n i t i o n w i l l remove t h e requirement f o r engineso u t d i s c r e t e s i g n a l s . (DGA) c. LLM Midcourse C o r r e c t i o n (New) A q u i c k a n a l y s i s of a n LLM midcourse c o r r e c t i o n , AV budget has i n d i c a t e d t h a t t h e AV r e q u i r e d w i l l i n c r e a s e by a b o u t 20 p e r (DGA) c e n t when t h e MCC i s delayed from 4 hours t o 10 hours a f t e r TLI. 3. Dynamics and Control a. S t a g e S e p a r a t i o n Computer Program (New) A two-part computer program t o s i m u l a t e s t a g e s e p a r a t i o n has been w r i t t e n and checked o u t i n F o r t r a n I1 f o r t h e SDS 930 comp u t e r . The f i r s t p a r t of t h e program s i m u l a t e s t h e r o t a t i o n a l motion of a s i n g l e body i n a n i n e r t i a l c o o r d i n a t e system u n t i l changing f o r c e s ( i . e . , t h r u s t t a i l - o f f f o r c e s and r e t r o - f o r c e s ) s e p a r a t e t h e two b o d i e s . Thcn t h e second p a r t of t h e program s i m u l a t e s t h e motion of t h e two bodies i n s i x degrees of freedom and c a l c u l a t e s t h e r e l a t i v e p o s i t i o n v c c t o r between a r b i t r a r y p o i n t s ( s p e c i f i e d i n t h e program i n p u f ) expressed i n a c o o r d i n a t e system f i x e d i n one of t h e b o d i e s . The program i s g e n e r a l i n t h e s e n s e t h a t i t can be used w i t h v a r i o u s c o n f i g u r a t i o n s . Use of t h e 930 computer e l i m i n a t e s much turn-around time. (DC) �b. Local Angle-of-Attack Response (New) E f f e c t s on Vehicle Dynamic The downwash normal f o r c e d i s t r i b u t i o n of a d e f l e c t e d v e h i c l e i s being computed. An aerodynamic t r a n s f o r m a t i o n was d e r i v e d t h a t c a r r i e s t h e p a r t i a l d i f f e r e n t i a l e q u a t i o n from C a r t e s i a n c o o r d i n a t e s i n t o t h e c o o r d i n a t e s of a d e f l e c t e d body. A method of e v a l u a t i n g g e n e r a l ized bending f o r c e s , a s w e l l a s a e r o e l a s t i c e f f e c t s , is being developed. (DD/~hrysler) c. S t r u c t u r a l Damping Research (New) Two c o n t r a c t s a r e being awarded t o Lockheed f o r s t u d i e s of s t r u c t u r a l damping. The f i r s t w i l l a t t e m p t t o c o r r e l a t e t h e damping of t h e 115 s c a l e model of t h e S a t u r n I v e h i c l e w i t h t h e damping of i t s components and t h e a n a l y t i c a l energy d i s t r i b u t i o n . Work under t h e second c o n t r a c t w i l l a t t e m p t t o s i m i l a r l y p r e d i c t t h e s t r u c t u r a l damping of t h e AAP C l u s t e r . Some t e s t i n g w i l l b e done t o provide b a s e l i n e and v e r i f i c a (D~SI~ockheed) tion data. d. Damping of Liquid O s c i l l a t i o n s by Wall Roughness (New) The e f f e c t s of w a l l roughness on t h e damping of l i q u i d o s c i l l a t i o n s i n a r e c t a n g u l a r b a s i n a r e being i n v e s t i g a t e d . The b a s i n i s made of g l a s s (20" x 10" x 10") and t h e t e s t l i q u i d i s w a t e r p l u s two p a r t s p e r thousand Aerosol MA. The f i r s t s l o s h made i s e x c i t e d by a p p l y ing a p e r i o d i c f o r c e t o t h e b a s i c p a r a l l e l t o t h e 20-inch dimension. Some of t h e r e s u l t s a r e a s f o l l o w s : (1) With a 9-inch d e p t h , t h e presence of 3-inch by 10-inch s t r i p s of !/lo g r i t (approximately 1110-inch diameter p a r t i c l e s ) on t h e 10-inch wide tank ends w i t h t h e lower edge of t h e s t r i p s 7 inches from t h e tank bottom caused a 65 p e r c e n t i n c r e a s e i n t h e l o g decrement of t h e f r e e decay compared t o t h e smooth w a l l v a l v e . 2) The presence of i/30 g r i t (approximately 03-inch d i a m e t e r ) i n s t r i p s \ caused a 23 p e r c e n t i n c r e a s e i n damping over t h e smooth-wall v a l v e . ( 3 ) A s expected from r i n g b a f f l e s t u d i e s , roughness near t h e tank bottom i s much l e s s e f f e c t i v e i n i n c r e a s i n g t h e damping than roughness i n c o n t a c t w i t h t h e l i q u i d s u r f a c e . (One-inch roughness s t r i p s a t t h e s u r f a c e were o n l y s l i g h t l y l e s s e f f e c t i v e t h a n t e n - i n c h s t r i p s covering t h e e n t i r e end w a l l s .) (DDS) �1. Dynamics and Control a. S a t u r n V Launcher Ana 1y s i s (New) - Umbilical Tower V i b r a t i o n Methods a r e being developed f o r e v a l u a t i n g t h e v i b r a t i o n a l c h a r a c t e r i s t i c s of t h e S a t u r n V l a u n c h e r - u m b i l i c a l tower combina- t i o n . A method of a n a l y s i s and d i g i t a l computer programs a r e a l s o being developed f o r determining t h e modes and f r e q u e n c i e s of l a r g e s p a c e frames. The program f o r a n a l y z i n g s p a c e frames, which uses a r e p e t i t i v e s o l u t i o n technique, has been checked o u t w i t h a r e l a t i v e l y (DDS/Lockheed) s m a l l plane frame problem. b. S a t u r n V, S-IVB Coast S t a b i l i t y (New) A s e r i e s of s i m u l a t i o n runs has been made t o s t u d y t h e dynamics of t h e S-IVB s t a g e a f t e r second burn. The mass of propell a n t l e f t on board was v a r i e d , and t h e v e h i c l e s continuous v e n t system was turned o f f , This would permit t h e p r o p e l l a n t t o s e a t i n t h e upper domes of b o t h t a n k s under t h e i n f l u e n c e of aerodynamic d r a g . R e s u l t s of t h e s e runs show t h a t t h e v e h i c l e can be c o n t r o l l e d by t h e APS system. A d d i t i o n a l r u n s w i l l b e made t o confirm t h i s f o r v e r y low f l u i d l e v e l s . Tllc o b j e c t i v e of t h e s t u d y w i l l be t o d e f i n e t h e l i m i t s on t h e amount of t h e p r o p e l l a n t l e f t on board f o r which t h e v e h i c l e i s s t a b l e , w i t h o u t t h e continuous v e n t system. (DDS) c. S a t u r n V T h e o r e t i c a l T r a n s f e r Function Study (New) The f l i g h t mechanic yaw e q u a t i o n s of motion and cont r o l have been formulated f o r S a t u r n V. These e q u a t i o n s i n c l u d e f o u r bending modes and t h e f i r s t s l o s h mode f o r each p r o p e l l a n t tank. S l o s h n o n l i n e a r i t i e s i n damping c o e f f i c i e n t s a r e b e i n g i n c l u d e d . The e f f e c t of wind p e n e t r a t i o n i s a l s o b e i n g e v a l u a t e d . T h e o r e t i c a l t r a n s f e r funct i o n f o r t h e S a t u r n V v e h i c l e w i l l be determined f o r t h e b o o s t phase. Comparisons w i t h f l i g h t d a t a w i l l be made f o r model v e r i f i c a t i o n . dynamic S c i e n c e ) d. L o n g i t u d i n a l I n s t a b i l i t y of t h e S a t u r n V Vehicle (Pogo) (New) A r e p r e s e n t a t i v e mathematical model of t h e v e h i c l e l o n g i t u d i n a l s t r u c t u r a l modes, p r o p e l l a n t t a n k s , p r o p e l l a n t s u c t i o n l i n e s , pumps, and engine t h r u s t c h a r a c t e r i s t i c s a r e being formulated Tor t h e S a t u r n V t o s t u d y t h e i r coupled i n t e r a c t i o n (Pogo) e f f e c t a s w i t n e s s e d from t h e f l i g h t t e s t r e s u l t s of S a t u r n 502. This system �w i l l kc analyzed i n the l o n g i t u d i n a l mode by determining Nyquist s t a b i l i t y p l oLs ([sing a d i g i t a l s o l u t i o n . Concurrently, t h i s l o n g i t u d i n a l ins ~ ; t ib1 i t y w i l l a l s o be simulated on t h e hybrid 650 analog computer. ' r l ~ c , ~ ~ n a l oco~nputcr g o f f e r s wide range i n n o t o n l y s i m u l a t i n g t h e l o n g i t u d i n a l i n s t a b i l i t y b u t i n r a p i d l y e v a l u a t i n g p o t e n t i a l " f i x e s " by means oP parameter v a r i a t i o n s . A coupled l o n g i t u d i n a l - l a t e r a l a n a l y s i s w i l l a l s o be s t u d i e d on analog equipment. (Dc/DD/~orthrop) e. Second F l i g h t S t a g e , Dual Engine Out Control Anal ys i s (New) The a n a l y s i s of d u a l engine f a i l u r e i n t h e second f l i g h t s t a g e of t h e S a t u r n V has been i n i t i a t e d . A s t a b i l i t y a n a l y s i s has been performed on a system model which included p i t c h - r o l l coupling. Prel i m i n a r y r e s u l t s i n d i c a t e a low c o n t r o l system frequency and a damping r a t i o l e s s than 20 p e r c e n t d u r i n g second s t a g e f l i g h t f o r c o n d i t i o n s of two c o n t r o l engines o u t . The response a n a l y s i s of t h i s system has been i n i t i a t e d . The model i n c l u d e s t h e a p p r o p r i a t e guidance maneuver r e s u l t ing from two engines o u t , a l t h o u g h t h e guidance and c o n t r o l a r e uncoupled (DC) i n the present simulation. f. S-111s-IVB S e p a r a t i o n w i t h No T i l t A r r e s t (New) The e f f e c t of c o n t i n u i n g t h e guidance cormnands u n t i l engine c u t o f f on t h e S-111s-IVB s e p a r a t i o n of t h e AS-503 " B o i l e r p l a t e " conf i g u r a t i o n i s being s t u d i e d . According t o p r e l i m i n a r y r e s u l t s , t h e separation clearance i s r e l a t i v e l y i n s e n s i t i v e t o the turning r a t e a t the beginning of s e p a r a t i o n , and i f a l l retro-motors o p e r a t e , c o n t i n u a t i o n of t h e guidance commands w i l l n o t j e o p a r d i z e s e p a r a t i o n c l e a r a n c e , I f one r e t r o - m o t o r f a i l s , t h e r e s u l t i n g plume impingement f o r c e on t h e i n t e r s t a g e a d a p t e r reduces t h e c l e a r a n c e between t h e S-IVB s t a g e engine b e l l and t h e top of t h e i n t e r s t a g e a d a p t e r by 85 p e r c e n t of t h e a v a i l a b l e c l e a r a n c e . I f r e t r o - m o t o r misalignment t o l e r a n c e s ( l o ) -- e . g . , o f f s e t t o l e r a n c e (6" l o n g i t u d i n a l and 2" l a t e r a l ) and r o t a t i o n r a t e v a r i a t i o n ( . 5 " / s e c ) a r e imposed on t h e r e t r o - o u t c o n d i t i o n , t h e r e s u l t i n g 3 0 v a r i a t i o n t a k e s a n o t h e r 1 4 t o 15 p e r c e n t of t h e a v a i l a b l e c l e a r a n c e , depending on t h e t u r n i n g r a t e a t t h e beginning of s e p a r a t i o n (guidancecommand i n f l u e n c e d ) and which r e t r o - m o t o r f a i l s . I f t h e i n i t i a l t u r n i n g r a t e i s one d e g / s e c nose-down, t h e 3 0 envelope c l e a r s f o r any retro-motoi o u t . I f i t i s one d e g l s e c nose-up, t h e 30 envelope c l e a r s f o r a lower r c t r o - m o t o r o u t ( f i n p o s i t i o n A o r D), and t h e p r o b a b i l i t y of c l e a r i n g i s b e t t e r than 99 p e r c e n t f o r a n upper retro-motor o u t . (DC) -- �3. I'rojcct a. Information A p p l i c a b l e t o I n d i v i d u a l Vchicles AS-503 Dynamic Data f o r A l t e r n a t e Miss i o n A f t e r Payload S e p a r a t i o n (New) A document c o n t a i n i n g t h e c u r r e n t bending and t o r s i o n d a t a f o r t h e AS-503 a l t e r n a t e m i s s i o n a f t e r payload s e p a r a t i o n has been completed. The a n a l y s i s was made using t h e assumption t h a t t h e SLA panels a r e j e t t i s o n e d f o r t h e m i s s i o n . This document i s t o be d i s t r i buted under cover memorandum R-AERO-DD-107-68. An e a r l i e r a n a l y s i s was conducted w i t h t h e SLA panels i n t a c t and deployed 45"; t h e r e s u l t s of tlla t a n a l y s i s were published under memorandum R-AERO-DD-102-68. It i s c u r r e n t l y planned t h a t t h e SLA panels w i l l be j e t t i s o n e d . (~~S/~oeing) b. AS-503 Dynamics Data (Ref: Dec. 1967-Jan. 1968) A complete r e v i s i o n of dynamic d a t a f o r AS-503 was made t o update t h e t h i r d f l i g h t c o n f i g u r a t i o n l a t e r a l dynamic charact e r i s t i c s t o i n c l u d e t h e e f f e c t s of c u r r e n t mass d a t a and a more d e t a i l e d mathematical model and t o i n c l u d e yaw modes. There a r e a l s o c o r r e c t e d t o r s i o n a l dynamic c h a r a c t e r i s t i c s f o r t h e S-IVB b o o s t p o r t i o n of t h e f l i g h t . A f t e r review, t h i s document w i l l be d i s t r i b u t e d under cover memorandum R-AERO-DD-108-68. (~~Sf~oeing) c. AAP 1. Cluster a. Miss i o n P r o f i l e (1) Vis i b i l i t y of t h e Ear th-Moon L i b r a t i o n P o i n t s from ATM (New) A new a c t i o n has been i n i t i a t e d t o s u p p o r t t h e ATM m i s s i o n a t t h e r e q u e s t of Space Sciences Laboratory. One of t h e e x p e r i ments on board (HAO) i s a s o l a r coronagraph w i t h a 3" f i e l d of view. During experiment o p e r a t i o n , i t i s always c e n t e r e d on t h e sun. It has been proposed t o use t h i s i n s t r u m e n t t o view t h e t r i a n g u l a r l i b r a t i o n p o i n t s L4 and L5 of t h e earth-moon system whenever t h e s e p o i n t s pass w i t h i n t h e 3O f i e l d of view of t h i s i n s t r u m e n t . The a c t i o n taken h e r e has been t o determine when t h e s e l i b r a t i o n p o i n t s w i l l pass w i t h i n the 3 " f i e l d o i view of t h i s instrument. A s e t of e q u a t i o n s t o determine t h e a n g u l a r displacement of L4 and 25 from t h e l i n e of s i g h t between t h e ATM and t h e sun have been d e r i v e d and s e n t t o t h e Computation L a b o r a t o r y t o b e included i n t h e N-body deck. Checkout of t h e s e e q u a t i o n s i s expected t o b c g i n w i t h i n a b o u t two weeks. Some p r e l i m i n a r y c a l c u l a t i o n s have i n d i c a t e d t h a t t h e r e a r e two 35-day p e r i o d s d u r i n g each y e a r , each period �s e p a r a t e d by s i x months, d u r i n g which t h i s experiment i s p o s s i b l e ( t h i s i s clue t o t h e s m a l l f i e l d of view of t h e instrument and t h e f a c t t h a t i t i s always c e n t e r e d on t h e s u n ) . These two times of y e a r correspond t o t h e two i n t e r s e c t i o n s of t h e moon's o r b i t plane w i t h t h e e c l i p t i c plane. The times of t h e s e two i n t e r s e c t i o n s change g r a d u a l l y from y e a r t o y e a r and thus have t o be determined f o r any s p e c i f i e d y e a r . For t h e y e a r s 1970-71 t h e i n t e r s e c t i o n s occur on October 25, 1970 and A p r i l 25, 1971. T h i r t y - f i v e - d a y p e r i o d s c e n t e r e d on t h e s e two d a t e s g i v e t h e times during which t h i s experiment i s p o s s i b l e . (DAO) (2) E a r t h Resources Experiment Impact on C l u s t e r I Miss i o n (New) A q u i c k r e s p o n s e s t u d y was i n i t i a t e d t o provide t h e m i s s i o n impact of adding e a r t h r e s o u r c e s experiments t o t h e p r e s e n t c l u s t e r . This s t u d y was undertaken i n s u p p o r t of t h e Luskin Committee r e p o r t on May 15. Because of t h e e a r t h r e s o u r c e s experiment r e q u i r e ments f o r d a t a a t l a t i t u d e s h i g h e r t h a n 29", a t r a d e o f f of m i s s i o n l e n g t h , payload, and a l t i t u d e was made. By lowering d e s i r e d l i f e t i m e t o 270 d a y s , t h e workshop a l t i t u d e could be lowered t o 200 NM. Keeping t h e same workshop i n j e c t i o n weight a s p r e s e n t l y planned allowed t h e i n c l i n a t i o n t o be i n c r e a s e d t o approximately 35 d e g r e e s . A t t h i s a l t i t u d e and i n c l i n a t i o n , a s i n g l e U P - 1 launch o p p o r t u n i t y can b e provided every 4 days. By " f i n e tuning" t h e i n c l i n a t i o n t o 34.26 degrees two launch o p p o r t u n i t i e s p e r day can be provided every f o u r days. The time between t h e two AAP- 1 launch o p p o r t u n i t i e s i s approximately f i v e h o u r s . Targeting f o r t h e AAP-2 workshop o r b i t and U P - 1 launch o p p o r t u n i t i e s was proThe d e s i r a b i l i t y of v i d e d t o g e n e r a t e launch v e h i c l e t r a j e c t o r i e s p r o v i d i n g two launch o p p o r t u n i t i e s per day i s b e i n g d i s c u s s e d w i t h i n NASA. Items t o be considered i n c l u d e launch a b o r t r e c o v e r y l i g h t i n g , rendezvous l i g h t i n g , e a r t h r e s o u r c e s experiment 1i g h t i n g , and e a r l i e s t r e c o v e r y l i g h t i n g . Also t o be considered a r e range s a f e t y c o r r i d o r s and placement of r e c o v e r y f o r c e s . Work c o n t i n u e s t o s u p p o r t more d e t a i l e d p r e s e n t a t i o n s t o NASA h e a d q u a r t e r s i n June 1968. (DAO) . (3) E a r t h Resources Experiment Impact on MP-112 (New) A s t u d y has been undertaken t o determine t h e comp a t i b i l i t y of seven e a r t h r e s o u r c e s experiments w i t h t h e AAP-L/Z m i s s i o n . The a r e a of prime i n t e r e s t of t h e s e experiments is t h e USA w i t h some experiments cons t r a i n e d t o d a y l i g h t viewing. The t o t a l time over t h e USA d u r i n g s i o n was determined f o r b o t h 29" and 35" i n c l i n e d o r b i t s a l t i t u d e . Four o r f i v e o p p o r t u n i t i e s p e r day occur w i t h t h e USA b e i n g a n average of 10 minutes i n l e n g h t . These were t h e n i n t e g r a t e d w i t h t h e b a s i c crew c y c l e and t h e A t h e 28-day misa t a 220 n.mi. t h e passes over opportunities A P - ~ biomedical /~ �experiments, r e s u l t i n g i n 48 USA passes o r approximately 9 hours of over-USA time a v a i l a b l e f o r a s t r o n a u t monitoring of t h e e a r t h r e s o u r c e s expcr iments . L i g h t i n g over t h e USA i s a f u n c t i o n of launch time. A l a t e morning launch a f f o r d s f a v o r a b l e USA l i g h t i n g e a r l y i n t h e 28-day m i s s i o n , a n evening launch t h e mid-mission days, and a n i g h t launch t h e l a t t e r miss i o n days. (DAM) (4) J - 2 s D i r e c t Rendezvous (New) An i n v e s t i g a t i o n of t h e use of t h e J - 2 s engine t o provide f o r d i r e c t rendezvous c a p a b i l i t y has begun. The p r o f i l e cons i s t s of S-IB and S-IVB h i g h t h r u s t phases w i t h u s e of t h e J-2s engine i d l e mode (5000 l b . t h r u s t ) f o r t h e t e r m i n a l rendezvous p o s i t i o n and v e l o c i t y c o n t r o l . By v a r y i n g t h e l e n g t h of i d l e mode burn, a launch window can be provided. When a p p l i e d t o t h e AAP-4 unmanned rendezvous problem, a 30-second launch window can be provided by v a r y i n g t h e l e n g t h of t h e i d l e mode from approximately 900 t o 600 seconds. The payload t r a d e o f f f o r t h i s window i s approximately 1000 l b s . ; however, t h e payload i n c r e a s e due t o J-2S engine t h r u s t and s p e c i f i c impulse improvement i s a b o u t 2500 pounds. The n e t i n c r e a s e over t h e p r e s e n t AAP-4 v e h i c l e c a p a b i l i t y i n t o a 220 NM o r b i t would be i n t h e o r d e r of 1500 pounds. The S-IVB t h r u s t s t r u c t u r e would n o t r e q u i r e beef-up because t h e J-2s t h r u s t was h e l d t o t h e p r e s e n t t h r u s t s t r u c t u r e c a p a b i l i t y (240,000 I b thrust). Cost and s c h e d u l e c o n s i d e r a t i o n s would probably r u l e o u t t h e a p p l i c a t i o n of t h e J-2S engine f o r t h e AAP-4 unmanned rendezvous v e h i c l e ; however, i t s f u t u r e use f o r a n unmanned l o g i s t i c s c a r r i e r and a s a r e s c u e v e h i c l e s h o u l d b e noted. ( ~ ~ 0 1 ~ p p lA i enda l y s i s ) (5) - Unmanned Rendezvous Using S-IVB Stage (Ref: February-March 1968, p. 4 4 ) . The S-IVB unmanned rendezvous s t u d y i s c o n t i n u i n g i n o r d e r t o r e f i n e m i s s i o n p r o f i l e s e l e c t i o n and t o provide a b a s i s upon which t h e p r o f i l e can be implemented. P r e s e n t a t i o n s on t h e s t u d y were n u d e t o t h e MSC AAP program o f f i c e on A p r i l 4 , 1968 and t o D r . von Braun on May 1, 1968. A review of t h e s t u d y was a l s o made t o t h e Miss i o n Rcquiremcnts Panel on May 22, 1968. An a n a l y s i s of t h e guidance and n a v i g a t i o n a c c u r a c i e s a t t h e second S-IVB c u t o f f r e s u l t e d i n t h e n e c e s s i t y of p r o v i d i n g a c o n s t a n t d e l t a h e i g h t burn a s soon a s p o s s i b l e a f t e r t h e S-IVB second burn. The maximum s i z e of t h i s burn i s 10.8 m e t e r s p e r second. An a l t e r n a t e mode would b e t o burn i n t o a n e l l i p t i c a l o r b i t w i t h t h e proper energy d i f f e r e n t i a l . �The plane change burn r e q u i r e s yawing t o a n a l t i tr~tlc apl'roximna t e l y pcrpcnd i c u l a r t o t h e o r b i t a l plane. Because of t h e ST- 1 24 M p l a t f o r m i n n c r gimbal (yaw) 1i m i t of 45 d e g r e e s , p r e l i m i n a r y d i s cuss ions w i t h As t r i o n i c s people have been h e l d . These d i s c u s s ions have pointed o u t t h a t k i t s t o modify t h e ST-124 M p l a t f o r m t o a 4-gimbal c o n f i g u r a t i o n have been purchased f o r t h e S a t u r n program. The impact of t h i s m o d i f i c a t i o n i s being considered a t A s t r i o n i c s . I n designing the t r a j e c t o r i e s f o r the terminal rendezvous phase of a m i s s i o n , t h e r e a r i s e s a need f o r a r a p i d method of i n v e s t i g a t i n g t h e c h a r a c t e r i s t i c s of a g r e a t number of p r o f i l e s . These c h a r a c t e r i s t i c s i n c l u d e p r o p e l l a n t r e q u i r e m e n t s , t i m i n g , l i g h t i n g , t e r m i n a l approach a n g l e s , sens i t i v i t y t o e r r o r s i n measuring t h e r e l a t i v e p o s i t i o n s and v e l o c i t i e s , and e r r o r s i n making t h e p r o p u l s i v e maneuvers. During t h i s p e r i o d , s e v e r a l monograms were developed which a i d i n t h e i n v e s t i g a t i o n of t h e s e p r o f i l e s These monograms g i v e t h e r e l a t i v e v e l o c i t y v e c t o r s a t t h e i n i t i a t i o n and f i n a l i z a t i o n of t h e t e r m i n a l phase a s a f u n c t i o n of t h e r e l a t i v e p o s i t i o n v e c t o r and t h e time t o be s p e n t i n performing the t e r m i n a l phase. . The use of t h e LM rendezvous r a d a r f o r t h e v e r n i e r burns has been s t u d i e d i n terms of range, range r a t e , and antenna e l e v a t i o n a n g l e e r r o r s . Based upon t h e 3 0 random and b i a s e r r o r s provided by MSC, t h e e r r o r i n TPF p o s i t i o n was found t o be approximately 5 k i l o m e t e r s i f t h e r a d a r ' d a t a were used t o compute t h e TPI burn. T h e r e f o r e , a midcourse c o r r e c t i o n w a s added t o t h e t e r m i n a l phase p r o f i l e . Weight and performance c o n s i d e r a t i o n s due t o adding r e s t a r t c a p a b i l i t y t o t h e p r e s e n t S-IVB s t a g e a r e b e i n g s t u d i e d by P&VE L a b o r a t o r y and Douglas. The I U system problems involved i n i n t e r f a c i n g w i t h t h e LM rendezvous r a d a r a r e b e i n g pursued by ( D A O / N tOh~r o p ) As tr i o n i c s Lab. (6) AAP-4 LM/ATM Unmanned Rendezvous (Ref: February-March 1968, p. 45) - F u r t h e r a n a l y s i s of t h e S-IVB LM/ATM unmanned rendezvous w i l l c o n t i n u e . A d e t a i l e d performance d i s p e r s i o n a n a l y s i s and n a v i g a t i o n a l a n a l y s i s w i l l be performed s o that a more e x a c t APS p r o p e l l a n t budget can be d e t i n e d . The guidance requirements f o r t h e low /\V t r a n s f e r maneuvers a r e a l s o b e i n g a n a l y z e d , a s w e l l as navigat i o n u p d a t e s , u s i n g r a d a r i n f o r m a t i o n s o t h a t launch v e h i c l e d i g i t a l computer s t o r a g e requirements can b e determined. A q u i c k look a t t h e u s e of IGM t r a j e c t o r y shaping i n S - I B s t a g e a f t e r max q i n d i c a t e s t h a t approximately 900 l b s of payload a t o r b i t a l i n s e r t i o n can b e achieved w i t h a 1 0 p e r c e n t i n c r e a s e i n s t r u c t u r a l l o a d s . This may be needed a t a l a t e r d a t e i f payload problems occur w i t h t h e 2nd S-IVB s t a g e i g n i t i o n made i n a c h i e v i n g rendezvous. (DG) �(7) AAP-3A Launch Opportunity and Rendezvous A n a l y s i s (Ref: February-March 1968, p. 40) AAP-3A l i f t - o f f i s scheduled (ML-13) t o occur a f t e r day 119 ( r e f e r e n c e d t o AAP-2 l a u n c h ) . This a l l o w s 28 days f o r t h e AAP-1 m i s s i o n and 90 days f o r s t o r a g e b e f o r e AAP-3A miss i o n i s s t a r t e d . Two n e a r i n - p l a n e inphase launch o p p o r t u n i t i e s occur on day 129 a f t e r AAP-2 launch. The p r e v i o u s l y c a l c u l a t e d AAP-1 and a n g l e d i d n o t s a t i s f y t h e l i g h t i n g c o n s t r a i n t s . That i s , nominal t e r m i n a l phase i n i t i a t i o n (TPI) occurs i n darkness s o t h a t t h e t a r g e t can be o p t i c a l l y t r a c k e d a g a i n s t a s t e l l a r background. A l s o , t h e t e r m i n a l phase f i n a l i z a t i o n (TPF) maneuver occurs a t a t i m e e q u i v a l e n t t o 140° of t a r g e t t r a v e l l a t e r and i s planned t o occur a t s u n r i s e t o o b t a i n t h e d e s i r e d , v i s i b i l i t y d u r i n g t h e docking maneuvers. The time from p u r s u i t launch t o rendezvous was optimized t o s a t i s f y t h e AAP-3A rendezvous l i g h t i n g c o n s t r a i n t s . The r e s u l t i n g t a r g e t l e a d a n g l e a t AAP-3A launch was found t o be 4.704 d e g r e e s . The time from UP-3A launch t o rendezvous i s 5 hours 21 minutes 52.7 seconds, and t h e t o t a l AV r e q u i r e d i s 136 m/s. This s t u d y i s now being documented. (DAO) (8) Data Bank (New) The f i r s t monthly s t a t u s r e p o r t of t h e M a r t i n ~ a r i e ~ ts a Data ' Bank (R-AERO-DAM-27-68) i s being d i s t r i b u t e d . The d a t a bank i s a computerized d a t a s t o r a g e and r e t r i e v a l system f o r c o l l e c t i n g , m a i n t a i n i n g , r e t r i e v i n g and r e p o r t i n g d a t a concerning d e s c r i p t i o n s of The s t a t u s r e p o r t provides a c u r r e n t and conplanned AAP experiments, s o l i d a t e d r e f e r e n c e t o t h e AAP experiment i n f o r m a t i o n c o n t a i n e d i n t h e d a t a bank. Capsule i n f o r m a t i o n such a s experiment number, t i t l e , ob ject i v e , crew time, experiment time r e q u i r e m e n t s , w e i g h t , volume, peak power, e t c . , a r e g i v e n f o r each experiment. Most of t h e c a n d i d a t e AAP-112 experiments a r e contained i n t h e d a t a bank. However, t h e bank i s c o n t i n u o u s l y being updated and does n o t y e t c o n t a i n G A A P c a n d i d a t e experiments. A s t a t u s r e p o r t of t h e d a t a bank w i l l be published monthly. This f i r s t r e p o r t had a l i m i t e d d i s t r i b u t i o n . D i s t r i b u t i o n of (DAMIMartin) Later r e p o r t s w i l l be i n c r e a s e d i f necessary. (9) * Des i g n Reference Miss i o n Document (DRMD) (Ref: February-March 1968, p. 39) The AAP-112 Design Reference Mission Document has been r e c e i v e d from M a r t i n M a r i e t t a and d i s t r i b u t i o n f o r comments has been made under cover memorandum R-AERO-DAM-28-68. The DRMD i s a comprehensive survey of t h e AAP-1/2 m i s s i o n from launch of AAP-2 t o t h e r e c o v e r y of CM-1 and c o n s i s t s of s i x volumes a s follows: �Volume I Volume I1 Volume I11 VolumeIV Volume V Volume V I b. - Miss i o n Des c r i p t i o n - Detailed Orbit Trajectory - Design Engineering I n t e g r a t e d Miss i o n Time1 i n e -AttitudeMissionTimeline I n t e g r a t e d Miss i o n Sys tems D e s c r i p t i o n s and Requirements A l t e r n a t e Mission and Contingency Plans. - - Guidance (1) AAP-3 Guidance C o m p a t i b i l i t y A n a l y s i s (New) A meeting was h e l d on A p r i l 14, 1968, between t h e guidance people of MSFC and MSC t o d i s c u s s t h e p o s s i b l e causes of a c t i o n t o be taken concerning t h e AAP-3 launch v e h i c l e guidance c o m p a t i b i l i t y f o r a n a s c e n t t o a n 81 x 120 n.mi. e l l i p s e u s i n g t h e S-IB, S-IVB, and CSM s t a g e s t o a c h i e v e a p e r i g e e i n s e r t i o n , There a r e s e v e r a l p o s s i b i l i t i e s a v a i l a b l e f o r t h e AAP-3 m i s s i o n . The t r u e s t a g e IGM e q u a t i o n s could be used t o s t e e r t h e S-IVB s t a g e s t o a n a i r p o i n t , s l i g h t l y beyond S-Ill3 f u e l d e p l e t i o n , t h a t has been s e l e c t e d from a n optimized t r a j e c t o r y t o o r b i t a l i n s e r t i o n . Our a n a l y s i s showed t h a t compatible take-over c o n d i t i o n s r e s u l t e d f o r e i t h e r t h e CSM u s i n g c r o s s -product s t e e r i n g o r one-stage IGM e q u a t i o n s . The CSM n a v i g a t i o n system, because of t h e gyro compassing t e c h n i q u e of l a y i n g t h e launch azimuth, makes i t d e s i r a b l e t o e n f o r c e t h e d e s i r e d o r b i t a l p l a n e a t S-IVB f u e l d e p l e t i o n s o t h a t o n l y p i t c h s t e e r i n g w i l l be r e q u i r e d of t h e CSM t o a c h i e v e o r b i t a l i n s e r t i o n . The guidance people of MSC i n d i c a t e d t h a t t h e most d e s i r a b l e system from a complete c o m p a t i b i l i t y s t a n d p o i n t would be f o r t h e S-IVB s t a g e t o use two-stage yaw s t e e r i n g and t h r e e - s t a g e p i t c h s t e e r i n g and use t h e one-stage IGM e q u a t i o n s i n t h e CSM. They a l s o i n d i c a t e d t h a t i t would be d i f f i c u l t t o s e l l t h e change i n guidance e q u a t i o n s t o t h e i r management s i n c e t h e c r o s s - p r o d u c t s t e e r i n g would do t h e t a s k f o r t h e AAP-3 m i s s i o n . The b a s i c rendezvous phasing c a p a b i l i t y of t h e G IM system LN/ATM was p o i n t e d o u t , and some bakcground m a t e r i a l from t h e S-IVB unmanned rendezvous s t u d y w a s p r e s e n t e d i n t h e hope t h a t i t would s t r e n g t h e n t h e i r argument f o r a more compatible system w i t h MSC management. The f i n a l d e c i s i o n was delayed u n t i l a l a t e r d a t e s o t h a t MSC could be s u r e t h a t any d e c i s i o n made would n o t j e o p a r d i z e f l e x i b i l i t y f o r l a t e r missions. (DG) - �c. Dynamics and Control (1) CMG Maximum Volume C o n t r o l Law (New) For t h e CMG c o n t r o l l a w c u r r e n t l y proposed, t h e momentum v e c t o r s of t h e i n d i v i d u a l CMG' s a r e o r i e n t e d i n a n i s o g o n a l d i s t r i b u t ion t o eliminate the " a n t i - p a r a l l e l " condition. The i s o g o n a l d i s t r i b u t i o n has been i n v e s t i g a t e d and found t o p o s s e s s a n extreme p r o p e r t y ; t h a t i s , t h e volume formed by t h e t h r e e gyromomentum v e c t o r s i s a maximum. This i n v e s t i g a t i o n was c a r r i e d o u t i n o r d e r t o p u t t h e d i s t r i b u t i o n on a f i n n mathematical b a s i s , and w i t h t h e hope that t h e i n v e s t i g a t i o n would y i e l d a more s u i t a b l e c o n t r o l l a w . A new c o n t r o l l a w has been f o m u l a t e d i n which one law r e p l a c e s t h e two laws t h a t were r e q u i r e d p r e v i o u s l y . The new c o n t r o l law i s s t i l l i n a p r e l i m i n a r y s t a g e . Because of t h e complexity of t h e mathematics, most of t h e a n a l y s i s and t e s t i n g i s being done on t h e d i g i t a l computer. Once t h e programs a r e running, a more a c c u r a t e (DDD) s t a t e m e n t may be made on t h e u s e f u l n e s s of t h e l a w . (2) AAP C l u s t e r S t r u c t u r a l Dynamics (New) P r e l i m i n a r y bending v i b r a t i o n c h a r a c t e r i s t i c s f o r s e v e r a l c o n f i g u r a t i o n s of t h e AAP C l u s t e r have been computed, and t h e r e s u l t s f o r t h e complete c l u s t e r documented i n memorandum R-AERO-DD-9968. The dynamic d a t a f o r t h e CSM docked t o t h e LM/ATM were g i v e n i n ~ . r e s u l t s of a n a l y s e s of s e v e r a l o t h e r memorandum R - A E R O - D D - ~ ~ - ~ The c o n f i g u r a t i o n s a r e being reviewed. (DDS) d. P r o j e c t Information Applicable t o Individual Vehicles (1) Response A n a l y s i s of AAP-2 F i r s t F l i g h t Stage (New) The response a n a l y s i s of t h e AAP-2 m i s s i o n i s being documented. The v e h i c l e c o n f i g u r a t i o n included exterior-mounted s o l a r p a n e l s , AAP b a s e l i n e APS u n i t s , and SLA/NC j e t t i s o n r o c k e t . Aerodynamic moment c h a r a c t e r i s t i c s f o r t h i s con£ i g u r a t i o n were s u f f i c i e n t l y high s o t h a t t h e c o n t r o l a n g l e r e q u i r e d i n t h e presence of t h e 95 p e r c e n t winds was 8.0 degrees a t max q f o r t h e RSS bending moment c o n d i t i o n s . Tlle c o n t r o l l a b i l i t y margin i s s a t i s f a c t o r y f o r a non-malfunction £1 i g h t ; llowever, h i g h bending moments a r e i n c u r r e d . A t 1 0 km, 68 s e c from 1 i f t o f f , t h e bending moment ( i n c l u d i n g margin f o r f l e x i b l e body dynamics) i s 62.5 m i l l i o n i n l b s ; a t max q , 7 3 s e c , t h e bending moment i s 61.3 m i l l i o n i n l b s . (DC) �ATM S o l a r Panel F l e x i b i l i t y (New) a. A d e t a i l e d a n a l y s i s has been made of t h e f l e x i b i l i t y of t h e ATM s o l a r p a n e l s . The e f f e c t s of frame bending, panel s h e a r , p i n deformation and s o l i d l u b r i c a n t deformation have been included i n t h e a n a l y s i s . These d a t a w i l l b e i n c o r p o r a t e d i n t o t h e AAP C l u s t e r dynamic a n a l y s i s and should be u s e f u l i n f u t u r e damping p r e d i c t i o n s . (~D~l~ockheed) b. A'IM P o i n t i n g (New) Response s t u d i e s a r e determining t h e e r r o r o b t a i n e d f o r t h e ATM f o r v a r i o u s d i s t u r b a n c e s . A t o t a l s i m u l a t i o n of t h e CMG e l a s t i c body c l u s t e r i s b e i n g used f o r t h e s t u d y . Two bending modes a r e included. S i n c e r e s u l t s a r e j u s t beginning t o come i n from Computation L a b o r a t o r y , we cannot y e t draw any c o n c l u s i o n s as t o e r r o r expected. (DD/NO t h~r o p ) 3. OWS a. P a s s i v e A t t i t u d e Control (Ref: P- 43) February - March 1968, A memo has been w r i t t e n summarizing t h e r e s u l t s of a s o l a r panel misalignment s t u d y of t h e OWS i n t h e s t o r a g e mode. The s t u d y i n d i c a t e s t h a t a n i n c r e a s e of t h e aerodynamic c o e f f i c i e n t s by 30 p e r c e n t can cause a maximum a n g u l a r d e v i a t i o n of a b o u t 20" from t h e nominal p i t c h and yaw a t t i t u d e a f t e r t e n o r b i t s ; t h i s a t t i t u d e behavior might r e q u i r e a corresponding a t t i t u d e c o r r e c t i o n by r e a c t i o n j e t s . A t t h a t time, t h e v e h i c l e begins t o s p i n up a l o n g i t s l o n g i t u d i n a l a x i s t o a f i n a l r a t e of approximately 0.5 d e g l s e c o r more. The r e p o r t on t h e comparison of t h r e e s t e e r i n g laws f o r t h e ATM SIXPAC CMG c o n t r o l system has been p u b l i s h e d . The r e p o r t is t i t l e d " E v a l u a t i o n of S t a b i l i t y f o r Three C o n t r o l C o n f i g u r a t i o n s of t h e ATM SIXPAC Control System," Report 'I'M-54130-185, LMSCIHREC A781369, d a t e d A p r i l 1968. The r e s u l t s i n d i c a t e i n s t a b i l i t y of t h e Langley cont r o l law f o r some gimbal p o s i t i o n s , b u t s t a b i l i t y i s i n d i c a t e d f o r a l l (DCAILockheed) c a s e s f o r t h e cross-product and H-vector c o n t r o l law. b . OWS O r i e n t a t i o n S t u d i e s (Ref: February-March 1968) Aerodynamic t o r q u e s f o r t h e X-POP o r i e n t a t i o n of t h e OWS have been added t o t h e computer s i m u l a t i o n of t h e r o t a t i o n a l dynamics and c o n t r o l system of t h e workshop. This was done by expanding t h e a e r o dynamic c o e f f i c i e n t s a s a t r u n c a t e d F o u r i e r s e r i e s . The s i m u l a t i o n has a l s o been modified t o i n c l u d e t h e e f f e c t s of v e n t i n g t o r q u e s . �S t u d i e s have been completed on deadbands, e . g . , s h i f t , e r r a t i c engine t h r u s t , a e r o and v e n t i n g t o r q u e s . S t u d i e s t o determine t h e e I f e c t of launch d a t e , s u n s p o t number, and a l t i t u d e s on impulse regiments a r e now b e i n g run. (DD) VII. FLIGHT TEST ANALYSIS DIVISION A. Special Projects Office 1. Saturn V a. F l i g h t E v a l u a t i o n Working Group (FEWG) The launch v e h i c l e f l i g h t e v a l u a t i o n of AS-502 i s n e a r ing completion. Work on t h e 60-day e v a l u a t i o n r e p o r t has been rescheduled t o provide f o r completion i n 74 t o 78 days. This r e v i s e d s c h e d u l e i s a r e s u l t of t h e unusual m a l f u n c t i o n s experienced and a n e x p e d i t e d i n i t i a l e v a l u a t i o n o r i e n t e d toward r a p i d i d e n t i f i c a t i o n of anomalies r a t h e r than f i n a l reporting. To d a t e , t h e F l i g h t E v a l u a t i o n Working Group has comp l e t e d t h e f o l l o w i n g AS-502 f l i g h t r e s u l t s documentation: 3-day TWX Report t o NASA Headquarters 10-day TWX Report t o NASA Headquarters F l i g h t E v a l u a t i o n B u l l e t i n s No. 1, 2 and 3 Completed minutes of two FEWG E v a l u a t i o n meetings. D i r e c t s u p p o r t has been provided f o r a p r e s e n t a t i o n of AS-502 r e s u l t s t o General P h i l l i p s , t h e AS-503 Design C e r t i f i c a t i o n Review, and on a continuous b a s i s t o t h e S a t u r n F l i g h t E v a l u a t i o n Panel i n t h e j o i n t MSC~MSFC i n v e s t i g a t i o n of t h e AS-502 133-Second T r a n s i e n t . b. F l i g h t E v a l u a t i o n Panel (FEP) O n - s i t e s u p p o r t and c o o r d i n a t i o n w a s provided under t h e a u s p i c e s of t h e F l i g h t E v a l u a t i o n Panel (FEP) f o r t h e i n v e s t i g a t i o n of May 26, 1968. t h e AS-502 f l i g h t anaomaly a t 133 seconds from A p r i l 20 S t r u c t u r a l and i n s t r u m e n t a t i o n d e s i g n e n g i n e e r s from b o t h IBM ( f o r t h e IU) and McDonnell-Douglas ( f o r t h e S-IVB) were working a t E l l i n g t o n AFB, Texas, t h e s i t e of t h e anomaly t a s k team, d u r i n g t h a t p e r i o d . P&VE gave i n t e r m i t t e n t o n - s i t e s u p p o r t t o t h e a n a l y s i s e f f o r t through M r . E. E. Beam of i t s Dynamics and Loads ranch. The MSFC o n - s i t e e f f o r t was managed - �a n d coordinated by t h e FEP (Messrs. Graham, Lindberg and Nathan). The MSFC t a s k was supported a t H u n t s v i l l e by v a r i o u s R-AERO, R-ASTR, R-COMP, It-l'&VIC, I<-QUAT, and prime c o n t r a c t o r elements. A r e p o r t summarizing t h e i-nvtst i g a t i o n w i l l be d i s t r i b u t e d i n e a r l y June 1968. c. Current P r o p u l s i o n Simulation Module S t a t u s The S a t u r n Performance E v a l u a t i o n Deck w i t h the Propuls i o n S i m u l a t i o n Module (SPED-PSM) i s o p e r a t i o n a l through f i r s t S-IVB burn o n l y . The module has been i n s t a l l e d i n the second S-IVB burn port i o n of t h e program, b u t i s n o t y e t o p e r a t i o n a l . The SPED-PSM program has t h e following closed-loop p r o p u l s i o n performance g e n e r a t i n g c a p a b i l i t y . (1) D i s p e r s i o n s i n t h r u s t and f l o w r a t e r e s u l t i n g from d i s p e r s ions i n t h e independent p r o p u l s i o n s y s tem parameter can be simulated . (2) Engine-out and o t h e r p r o p u l s i o n system m a l f u n c t i o n s a n d / o r f a i l u r e s can be c o n s i d e r e d . (3) S - I 1 and S-IVB PU system o p e r a t i o n a n d / o r malfunct i o n a r e simulated. ( 4 ) Center of g r a v i t y and moment of i n e r t i a a r e computed f o r any of t h e d i s p e r s i o n o r m a l f u n c t i o n cases . S e v e r a l r e f i n e m e n t s t o SPED-PSM which i n c r e a s e t h e a c c u r a c y of t h e s i m u l a t i o n have been made s i n c e January of t h i s y e a r . (5) A complete c o n t r o l f i l t e r s i m u l a t i o n has been i n s t a l l e d i n t h e program, b u t v i r t u a l l y no machine c o r e s t o r a g e space remains. (6) The c a p a b i l i t y t o c o r r e c t l y c o n s i d e r d i s c r e t e mass l o s s e s i n t h e mass c e n t e r of g r a v i t y and moment of i n e r t i a r o u t i n e s has been added. (7) I n p u t t a b l e s can be p u t i n a s a f u n c t i o n of e i t h e r f l i g h t time o r mass l o s s , thus p r o v i d i n g a b e t t e r s i m u l a t i o n f o r d i s p e r s i o n a n a l y s e s and m a l f u n c t i o n s . S e v e r a l o t h e r r e f i n e m e n t s t o t h e SPED-PSM program a r e c u r r e n t l y underway which w i l l f u r t h e r i n c r e a s e t h e accuracy of t h e simul a t i o n i n some a r e a s and w i l l a l s o d e c r e a s e t h e turn-around time f o r both a complete p o w e r f l i g h t s i m u l a t i o n and d i s p e r s i o n a n a l y s i s . �(8) An improved S-IVB PU model has become a v a i l a b l e , This improved model w i l l be programmed and checked o u t w i t h i n t h e n e x t few weeks. (9) I n i t i a l i z a t i o n l o g i c f o r performing p e r t u r b a t i o n s i n one s t a g e w i t h o u t r e r u n n i n g t h e nominal c a s e s f o r a l l previous s t a g e s has been developed f o r t h e S a t u r n V t r a j e c t o r y g e n e r a t o r . This same scheme w i l l be adapted t o t h e SPED-PSM program. (10) Logic f o r running t h e i n t o - o r b i t , c o a s t , and o u t o f - o r b i t v e r s i o n s of SPED-PSM back-to-back w i t h o u t having t o come o f f t h e computer w i l l be i n s t a l l e d . The SPED-PSM v e r s i o n completed i n January used SA-501 v e h i c l e i n f o r m a t i o n a s i n p u t d a t a . The o u t p u t from t h i s was compared w i t h t h a t g i v e n i n t h e p r e f l i g h t p r o p u l s i o n performance p r e d i c t i o n tapes and t h e o p e r a t i o n a l t r a j e c t o r y . The average d e v i a t i o n i n t h r u s t and f l o w r a t e f o r each s t a g e and t h e d e v i a t i o n i n v e l o c i t y a t t h e c u t o f f of each s t a g e were: s - IC"' S-I1 S-IVB Thrus t , % -0.76 +O. 62 -0.57 Flowrate, % +O. 29 -0.11 +4.6 parame t e r / ~ t a g e Velocity M / S ~ C -15.9 -131.3 +9.6 The propuls i o n parameter comparisons a r e q u i t e good f o r the S-IC and S - I 1 s t a g e s , b u t e n t i r e l y unacceptable f o r t h e S-IVB s t a g e . Although t h i s problem i s n o t y e t r e s o l v e d , t h e i n s t a l l a t i o n of the improved S-IVB PU model i s expected t o make a s i g n i f i c a n t improvement i n t h i s comparison. The v e l o c i t y d e v i a t i o n s n o t o n l y r e f l e c t t h e d e v i a t i o n s i n t h e p r o p u l s i o n parameters b u t a l s o o t h e r inadequacies of t h e s i m u l a t i o n scheme, e . g . , t h e S-IC v e l o c i t y d e v i a t i o n s (about -12.8 m/sec), inadequate r e p r e s e n t a t i o n of c e n t e r engine decay (about -3.0 m/sec) and t h e l a c k of c o n t r o l f i l t e r s i m u l a t i o n . The S - I 1 v e l o c i t y d e v i a t i o n s a r e c o n s i d e r a b l y more complex b u t a r e a t t r i b u t e d t o p r o p u l s i o n parameter d e v i a t i o n s (about +21.0 m / s e c ) , l a c k of c o n s i d e r a t i o n of t h e S-IC/S-I1 i n t e r s t a g e and launch escape tower j e t t i s o n i n g i n t h e mass l o s s r o u t i n e (about -131.3 m/sec) and ;7' S-IC Outboard engine c u t o f f . 48 �l s o i n t l ~ c . c c n t t r of g r a v i t y and moment of i n e r t i a r o u t i n e s (no d a t a v a i l a b l v Tor t h e s e c f f c c t s ) and t h e l a c k of c o n t r o l f i l t e r s i m u l a t i o n . h e S-IVB s t a g e should c u t o f f when a p r e s e t v e l o c i t y i s reached. An cror which allowed two d i f f e r e n t v e l o c i t y p r e s e t t i n g s t o be used f o r le two s i m u l a t i o n s i s r e s p o n s i b l e f o r t h e e n t i r e S-IVB c u t o f f v e l o c i t y r v i a t i o n . Another comparison w i l l be made a s soon a s t h e r e f i n e m e n t s j r e s e n t l y underway a r e completed. I An RFQ has been i s s u e d . t o perform a s t u d y t o determine t h e a c c u r a c y and adequacy of t h e SPED-PSM. Three items a r e t o be accomplished under t h i s t a s k . (1) E x e r c i s e t h e v a r i o u s o p t i o n s t o determine i f they a r e working p r o p e r l y under a v a r i e t y of c o n d i t i o n s . (2) Compare t h e e q u a t i o n s f o r t h e v a r i o u s p r o p u l s i o n parameters w i t h t h o s e from t h e MARK s e r i e s of programs ( i f documentation is a v a i l a b l e ) . This w i l l g i v e a n i n d i c a t i o n of t h e adequacy of t h e s imula t i o n . ( 3 ) Compare t h e SPED-PSM o u t p u t w i t h t h e corresponding o u t p u t from t h e p r e f l i g h t p r o p u l s i o n p r e d i c t i o n t a p e s and t h e o p e r a t i o n a l t r a j e c t o r y from t h e s e t a p e s . This w i l l be used t o d e t e r mine t h e a c c u r a c y of t h e s i m u l a t i o n . This s t u d y w i l l l a s t a b o u t s i x months and r e q u i r e a b o u t 1,000 manhours of c o n t r a c t s u p p o r t . B. F l i g h t Mechanics Branch 1. Saturn I B a. AS-2051 CSM-101 Rendezvous Miss i o n The A S - ~ O ~ I C S M -Launch ~ O ~ Vehicle D i s p e r s i o n Analysis Data Report has been completed. This a n a l y s i s shows the 30 F l i g h t Performance Reserve t o be 1249 pounds. Fixed-time p a r t i a l s ( a t 7000 seconds) now being g e n e r a t e d a r e t o be completed t h e e a r l y p a r t of June. The Launch Vehicle O p e r a t i o n a l T r a j e c t o r y Data Report i s a l s o complete. This document i n c l u d e s d e t a i l e d t r a j e c t o r y d a t a from guidance r e f e r e n c e r e l e a s e t o t h e l o s s of S-IVB/IU l i f e t i m e . Under nominal c o n d i t i o n s , t h e S-IVBIIUISC w i l l a t t a i n t h e d e s i r e d o r b i t w i t h 1874 pounds of u s a b l e p r o p e l l a n t . This i s approximately 600 pounds i n excess of t h e FPR r e q u i r e m e n t s . These d a t a were g e n e r a t e d using a spacec r a f t weight of 36,300 pounds. �The o r b i t a l t r a j e c t o r i e s using t h e nominal and +3a impulses from t h e o r b i t a l s a f i n g e x e r c i s e have been generated and s u p p l i e d t o MSC. The Launch Vehicle Abort and A l t e r n a t e Mission document i s s t i l l i n p r o g r e s s . A d d i t i o n a l PU f a i l u r e c a s e s , e t c . , have been generated a s p a r t of t h i s a n a l y s i s . The Launch Vehicle Range S a f e t y A n a l y s i s i s approximately 7 5 p e r c e n t complete. This document w i l l b e p u b l i s h e d , a l o n g w i t h t h e a s s o c i a t e d "Cape Tape , I 1 t h e f i r s t h a l f of June. MSFC i n p u t s i n t o t h e J o i n t O p e r a t i o n a l T r a j e c t o r y Document and a J o i n t O p e r a t i o n a l T r a j e c t o r y T a r g e t i n g Document have been generated. These documents w i l l be published a s soon a s MSC completes t h e i r input. A memorandum concerning the f eas i b i l i t y of c o n t r o l 1 ing r e - e n t r y of t h e S-IVB s t a g e was prepared i n response t o a n a c t i o n item a s s i g n e d a t t h e Apollo Design C e r t i f i c a t i o n Review Board Meeting. b. 2061207 Dual Launch The S-IB s t a g e t i l t polynomials and S-IVB s t a g e guidance p r e s e t t i n g s have been g e n e r a t e d f o r t h i s m i s s i o n . These d a t a , documented i n CCSD r e p o r t numbers TN-AP-68-322 and TN-AP-68-324, a r e being reviewed and should be d i s t r i b u t e d by mid-June. initiated. 2. The d i s p e r s i o n a n a l y s e s f o r t h e s e v e h i c l e s have been They a r e t o be d e l i v e r e d t o MSFC around August 1. Saturn V S e v e r a l computer r u n s s i m u l a t i n g two engines o u t i n t h e S - I 1 s t a g e were made i n s u p p o r t of t h e AS-502 f l i g h t e v a l u a t i o n and s p e c i a l i n v e s t i g a t i o n of t h e 502 anomalies. which v e r i f i e d £1 i g h t d a t a . These r e s u l t e d i n overspeeds The " f i n a l " o p e r a t i o n a l t r a j e c t o r y f o r t h e BP-30 miss i o n i s being g e n e r a t e d by in-house personnel r a t h e r than the Boeing Company. The primary r e a s o n f o r t h i s i s t h e extremely high c o s t e s t i m a t e s s u p p l i e d by TBC f o r t h i s e f f o r t . This approach i s a l s o being used i n t h e f i n a l d i s p e r s i o n a n a l y s i s . The r e l e a s e of t h e t r a j e c t o r y a n a l y s i s and t h e d i s p e r s i o n a n a l y s i s i s scheduled f o r June 15 and J u l y 15, r e s p e c t i v e l y . �c. AS-503-D Mission Boeing t r a n s m i t t e d a p r e l i m i n a r y o p e r a t i o n a l t r a j e c t o r y on May 2 7 , 1968. This c o o r d i n a t i o n s h e e t w i l l be r e l e a s e d on o r about Junc 10. The p r e l i m i n a r y document c o n t a i n s m i s s i o n o b j e c t i v e s , cons t r a i n t s , shaping g u i d e l i n e s , guidance p r e s e t t i n g s ( i n c l u d e s a "no wind" b i a s t i l t program), t r a j e c t o r y d e s c r i p t i o n s , t r a j e c t o r y and o r b i t summary, c r i t i c a l e v e n t sequence, a mass c h a r a c t e r i s t i c s summary, a v e h i c l e p r o p u l s i o n c h a r a c t e r i s t i c s summary, and a t r a j e c t o r y l i s t i n g . d. AS-504-E Mission P r e s e n t planning c a l l s f o r a r e l e a s e of t h e i n i t i a l o p e r a t i o n a l t r a j e c t o r y around t h e f i r s t week i n September, w i t h t h e f i n a l o p e r a t i o n a l t r a j e c t o r y around December 1. The d i s p e r s i o n a n a l y s i s should be a v a i l a b l e i n e a r l y October, and t h e range s a f e t y d a t a s e n t t o KSC around t h e end of October o r e a r l y November. e. O r b i t a l Debris The S u r v i v a l and Risk Hazard Reports f o r t h e AS-503 v e h i c l e a r e b e i n g documented and w i l l be d e l i v e r e d t o R-AERO-FM t h e f i r s t week i n June. These r e p o r t s w i l l be reviewed b e f o r e t h e y a r e d i s t r i b u t e d t o t h e necessary centers. f . Lunar Landing Miss i o n (LLM) A l a r g e summer e x e r c i s e of t h e q u i c k r e t a r g e t i n g mode of o p e r a t i o n i s t e n t a t i v e l y scheduled t o b e g i n J u l y 15. A l l i n t r a c e n t e r l i n k s between AERO, ASTR, P&VE, COMP, and I 0 ( i n c l u d i n g I-MO) a r e hoped t o be c l o s e d . Also a d d i t i o n a l i n t e r c e n t e r l i n k s on communication v e r i f i c a t i o n wind cause check, e t c . , w i l l be e x e r c i s e d a s much a s p o s s i b l e . Some o t h e r primary o b j e c t i v e s a r e t o i n c l u d e t h r e e launch months (probably ~ u l y ,August, and September 1969) a t l e a s t one four-day launch month, and a look a t A t l a n t i c i n j e c t i o n s . A v e r y thorough s c a n of p o s s i b l e launch d a t e i s planned, t h e primary i n t e n t being t o add t o our l u n a r m i s s i o n knowledge. g. Current S t a t u s of S t a t i s t i c a l Analysis f o r T r a j e c t o r y S i m u l a t i o n of S a t u r n V Vehicles P r o g r e s s by Lockheed M i s s i l e and Space Company has been g e n e r a l l y good on t h i s c o n t r a c t , which cons i s t s b a s i c a l l y of two modificat i o n s of t h e "SPED" deck: (1) a s t a t i s t i c a l sampling program which i s being d e s i g n e d , coded, and i n s t a l l e d i n t h e "SPED" deck; and (2) a s t a t i s t i c a l computations program which i s being d e s i g n e d , coded, and i n s t a l l e d i n t h e "SPED~!deck. The s t a t i s t i c a l sampling program i s being �dcsigncd t o provide a random s e l e c t i o n of i n p u t parameters and t h e s t a t i s t i c a l computations program w i l l compute mean v a l u e s , covariance ma t r i c c s , s tandard d e v i a t i o n s , c o r r e l a t i o n c o e f f i c i e n t s , cumulative d is t r i b u t i o n f u n c t i o n s ( p l o t s ) , median v a l u e s , and a type of con£ idence i n ~ c r v a lf o r a l a r g e number of o u t p u t parameters. Sample runs by Loclclieed w i t h r e s p e c t t o t h e above m o d i f i c a t i o n s a r e now being made. C. Tracking and O r b i t a l Analysis Branch 1. Saturn I B (1) P r e l i m i n a r y a c q u i s i t i o n and l o s s times were t r a n s m i t t e d t o M r . T. E . Buckley a t GSFC. M r . Buckley i s a Bendix F i e l d Engineer s u p p o r t i n g GSFC i n Network Operations ( L e t t e r May 2, 1968). ( 2 ) Analysis has been performed and documented by memorandum R-AERO-FT-18-68 on t h e p r e d i c t e d AS-205 S-IVB o r b i t a l decay and 1i f e t i m e . This a n a l y s i s i n c l u d e s d i s p e r s i o n due t o k3a off-nominal s t a g e p a s s i v a t i o n s a s w e l l a s t h e d i s p e r s i o n s due t o atmospheric uncertainties. (3) The t r a c k i n g and communications a n a l y s i s on t h e A S - ~ O ~ / C S M 101 O p e r a t i o n a l T r a j e c t o r y has been completed and i s docuThis a n a l y s i s was performed mented i n memorandum R-AERO-FT-20-68. in-house and a l o n g w i t h t h e look a n g l e i n f o r m a t i o n g e n e r a t e d , s i g n i f i e s an updating of p r e s e n t c a p a b i l i t i e s . (4) A p r e l i m i n a r y copy of t h e AS-205 look a n g l e d a t a was s e n t t o M r . John Gurley, MSC, on a magnetic t a p e . A t t h e time t h e s e d a t a were completed, t h e p o l a r i z a t i o n a n g l e d a t a were i n c o r r e c t . The f i n a l look a n g l e i n f o r m a t i o n c o n t a i n s t h e c o r r e c t e d p o l a r i z a t i o n a n g l e data. The t r a c k i n g and communications network t o be used on the AS-207/206 Rendezvous Mission has been s e n t t o CCSD ( L e t t e r A p r i l 5 ) . 2. Saturn V (1) A c q u i s i t i o n and l o s s times f o r Corona, C a l i f o r n i a , were t r a n s m i t t e d by TWX t o M r . Kimball of t h e Naval Weapons C e n t e r . These d a t a were r e q u e s t e d by t h e Weapons Center t o a i d i n t e s t s of new r a d a r equipment. �(2) Look a n g l e time h i s t o r i e s f o r the launch phase of AS-501 and AS-502 were r e q u e s t e d by M r . Frank S h e l t o n , GSFC. The information was t r a n s m i t t e d by l e t t e r dated A p r i l 22, 1968. ( 3 ) Information r e g a r d i n g t h e AS-502 S-IVB s p e n t s t a g e l u n a r - s o l a r e f f e c t s and p e r t u r b a t i o n s , a l o n g w i t h r e l a t e d r e f e r e n c e s , was . s e n t t o D r . Knothe, KSC, by l e t t e r dated A p r i l 19, 1968. D r . Knothe has expressed a s t r o n g i n t e r e s t i n t h e s e 502 a n a l y s e s . The l a t e s t TBC v e r s i o n of t h e AS-503 "D" miss i o n t r a j e c t o r y has seemingly s a t i s f i e d t h e v a r i o u s people who r e c e i v e VHF t e l e m e t r y d a t a . I n a d d i t i o n t o having coverage f o r t h e b u r n s , t h e f u e l dump i s now o b s e r v a b l e b e f o r e t h e s l a n t range exceeds 4500 km. This range has been e s t a b l i s h e d a s t h e maximum range f o r which VHF t e l e m e t r y d a t a can be r e c e i v e d and s t i l l be of good q u a l i t y . 3. Apollo A p p l i c a t i o n s a. S a t u r n IB Workshop (1) Decay and l i f e t i m e i n f o r m a t i o n on t h e c l u s t e r m i s s i o n was prepared f o r p r e s e n t a t i o n t o D r . von Braun on May 3rd and t o M r . Luskin on May 1 5 t h . These d a t a were included i n M r . Deaton's p r e s e n t a t ion. (2) Decay and l i f e t i m e i n f o r m a t i o n on t h e c l u s t e r m i s s i o n was p r e s e n t e d a t t h e Miss i o n Requirements Panel meeting h e l d a t MSPC on May 22nd. We a r e now documenting t h i s l a t e s t i n f o r m a t i o n i n a memor and um . (3) The use of t h e c o n s t r a i n t Generator Program was s u p p l ied t o R-AERO-DA f o r t h e i r t imel i n e a n a l y s i s on t h e AAP-1/ 2 miss ion. This program has demonstrated i t s v a l u e by p r o v i d i n g a n e x c e l l e n t b a s e t o s t a r t experiment s c h e d u l i n g . The program, however, r e q u i r e s e x c e s s i v e IBM 7094 computer time f o r long d u r a t i o n m i s s i o n s . We a r e reviewing t h e program, and w i l l a t t e m p t t o g e t i t running on t h e 1108 system. This should r e l i e v e some of t h e computer time problem. (4) We a r e a t t e m p t i n g t o g e n e r a t e r e p r e s e n t a t i v e look a n g l e s f o r As t r i o n i c s Lab f o r t h e antenna p a t t e r n s t u d i e s . We have r e c e i v e d a p o s t - p a s s i v a t i o n v e c t o r f o r a 230 n.m. c i r c u l a r , 28.9 degree i n c l i n a t t o n o r b i t . The f i r s t s t e p was t o determine t h e yaw and r o l l maneuvers n e c e s s a r y f o r t h e s o l a r a r r a y s t o a c q u i r e t h e sun. This has been done f o r t h i s p a r t i c u l a r v e c t o r . This i n f o r m a t i o n w i l l then be i n p u t t o ~ o c k h e e d ' s look a n g l e deck. �Wc b e l i e v e t h a t a s t u d y t o a s c e r t a i n g e n e r a l yaw ai~tlrot l mancttvrrs a s a f u n c t i o n of time and i n c l i n a t i o n would be of intc>rc1st. T l l i s i s now being done in-house. b. S a t u r n V Workshop S u r v e i l l a n c e coverage on t h e S a t u r n V Workshop from launch t o i n s e r t i o n (270 n.m. o r b i t ) and a 24-hour o r b i t a l p e r i o d has been completed and i s documented i n memorandum R-AERO-FT-14-68. These a n a l y s e s w i l l be included i n t h e phase A documentation. 4. General a. Lifetime (1) M r . A 1 Baker of Bellcomm met w i t h M r . Paul Revels its and M r . Russ Pimm (LMSC) t o d i s c u s s t h e o r b i t a l l i f e t i m e program o p t ions and capab il i t i e s He s p e n t approximately s i x hours d i s c u s s i n g t h e program and seemed t o be q u i t e pleased w i t h i t s o v e r a l l f e a t u r e s . It a p p e a r s t h a t Bellcomm i s planning t o use i t much more e x t e n s i v e l y i n miss i o n planning. - . (2) I n c o n n e c t i o n w i t h our l i f e t i m e s t u d i e s , LMSC m i s s i o n s u p p o r t has analyzed t h e decay of Echo I. Because of t h e l a c k t h e b a l l o o n supposedly has of knowledge of p o s s i b l e changing of C+/M been punctured by meteors and p o s s i b l y d e f l a t e s a t lower a l t i t u d e s and expands a t t h e h i g h e r a l t i t u d e s , a f f e c t i n g b o t h t h e drag p e r t u r b a t i o n s , t h e e x a c t p o s i t i o n s and v e l o c i t i e s a s well a s the s o l a r pressure f o r c e a r e very d i f f i c u l t t o predict. -- -- 11 I n o r d e r t o e s t i m a t e t h e l i f e t i m e of Echo I ( h e r e e s t i m a t e " must be emphasized due t o t h e inadequate knowledge of AIM), t h r e e runs were made. The f i r s t r u n used t r a c k i n g d a t a from SAO on November 8 , 1967, w i t h CDA/M = 16.643 m2/kg and A/M times s o l a r p r e s s u r e ( P r ) = 0.000045 kg a s i n i t i a l c o n d i t i o n s , and i n t e g r a t e d w i t h H. W. Small d e n s i t y model. The r e s u l t i n g impact d a t e was May 8 , 1968. The second r u n began w i t h t r a c k i n g d a t a on May 1 0 , 1967, b u t w i t h a change i n t h c a r e a p r e s e n t e d t o t h e s o l a r p r e s s u r e (AIM = Pr = 0.000040 ~ ~ l k g ) The . r e s u l t i n g impact d a t e was June 5 , 1968. The t h i r d r u n used t h e same t r a c k ~ used a ing d a t a a s t h e second, b u t changed Pr AIM t o 0.000045 N T / ~and c ~ A / M= 12.482 m2/kg. The r e s u l t i n g impact d a t e was June 9 , 1968. It should be emphasized t h a t t h e s e d a t a a r e very u n c e r t a i n because of t h e nebulous c h a r a c t e r of t h e p h y s i c a l parameters of t h e b a l l o o n . However, based on t h e November 8 , 1967 elements, t h e e r r o r i n our two p r e d i c t i o n s was 3 p e r c e n t and 4 p e r c e n t f o r t h e June 5 t h and June 9 t h p r e d i c t e d decay d a t e s , r e s p e c t i v e l y . These r e s u l t s a r e v e r y encouraging. �(3) NORAD P r e s e n t a t i o n on T I P The NORAD p r e s e n t a t i o n on t h e i r Tracking and Impact P r c d i c t i o n Program g i v e n i n Washington on May 2 1 s t was q u i t e i n t e r e s t i n g . NOKAD i s p r e s e n t l y keeping up w i t h over 1 , 3 0 0 s a t e l l i t e s i n o r b i t . Their m i s s i o n i s t e r m i n a l decay p r e d i c t i o n , weapons s u p p o r t , s e n s o r c a l i b r a t i o n , and e a r t h model d e t e r m i n a t i o n . The p r e s e n t a t i o n c o n s i s t e d of t h e t e r m i n a l decay p r e d i c t i o n s and how t h e y a r e performed. Two programs a r e p r i m a r i l y involved; one i s King-Hele Decay Program which g i v e s them e s t i m a t e d decay p r e d i c t i o n s f o r 1,300 s a t e l l i t e s i n a b o u t one minute of computer time. This program, a n a l y t i c i n n a t u r e , uses mean o r b i t a l elements and t h e r a t e of change of p e r i o d t o p r e d i c t decay. The program i s e s t i m a t e d t o have an accuracy of from 10-25 p e r c e n t (one sigma). The second program, which c o n s i s t s of a s p i r a l decay technique used over s h o r t time p e r i o d s (from 7-10 days b e f o r e i m p a c t ) , i s a v a r i a t i o n or-parameters technique and i s used up t o approximately 20 minutes b e f o r e impact, then a Cowell i n t e g r a t i o n p r e d i c t i o n i s made t o impact. The second program r e q u i r e s t r a c k i n g i n f o r m a t i o n t o update t h e s a t e l l i t e ' s o r b i t a l elements; i t was s t a t e d t h a t a c c u r a t e p r e d i c t i o n s (5-10 p e r c e n t / one sigma) could be made over a c e r t a i n time p e r i o d i f t r a c k i n g i n f o r m a t i o n of approximately the same p r e d i c t i o n p e r i o d l e n g t h were a v a i l a b l e b e f o r e the prediction. I n o t h e r words, i f they had 12 hours of d a t a a r c , they could a c c u r a t e l y p r e d i c t 12 hours ahead. I f they had 10 days of t r a c k i n g d a t a , they could a c c u r a t e l y p r e d i c t approximately 10 days ahead. This does n o t seem t o be a major accomplishment i n comparing t h i s t o our pres e n t c a p a b i l i t i e s . The second program uses t h e SPADATS 1966 e a r t h model w i t h 9 zonal and 6 t h o r d e r t e s s e r a l harmonics, t h e 1966 ~ a c c h i adynamic atmosphere mode above 120 km, and t h e 1962 U. S. Standard model below 120 km. Other atmospheric models, which i n c l u d e e f f e c t s due t o s o l a r a c t i v i t y and geomagnetics, have n o t been e v a l u a t e d . One of NORAD's prime s o u r c e s of t r a c k i n g informat i o n i s t h e B a l l i s t i c M i s s i l e E a r l y Warning System (BMEWS) . They have v i r t u a l l y no t r a c k i n g i n f o r m a t i o n from t h e Southern Bemisphere and v e r y l i t t l e below 35" l a t i t u d e . One of t h e i r prime reasons f o r t h e p r e s e n t a t i o n was t o a t t e m p t t o s o l i c i t e NASA t r a c k i n g s u p p o r t . Their "boxscore" s i n c e June 1965, o u t of 314 TIP decays, i s a s f o l l o w s : 109 impact p r e d i c t i o n s w i t h i n +5 minutes accuracy 81 impact p r e d i c t i o n s w i t h i n k10 minutes a c c u r a c y 68 impact p r e d i c t i o n s w i t h i n +20 minutes a c c u r a c y 75 impact had v i s u a l c o n f i r m a t i o n 8 impacts have had p i e c e s r e c o v e r e d . �These a c c u r a c i e s sound v e r y good, b u t i t must be r cmemb e r e d t h a t they need c o n t i n u i n g t r a c k i n g i n f o r m a t i o n over the l a s t 10 days and w i t h t h i s i n f o r m a t i o n , t h e accuracy i s 5-10 p e r c e n t (one s igma) . P r e s e n t l y , NORAD uses s e v e r a l a g e n c i e s t o confirm decay: SAO 12 Baker-Nunn Cameras 122 moonwatch 1127th F i e l d A c t i v i t y Group 67 a i r a t t a c h e s a t embassies NORAD Reg ions 205 i n d i v i d u a l i n s t a l l a t i o n s A i r Weather S e r v i c e 300 a i r weather s t a t i o n s Civilian Airlines P i l o t s from 65 world a i r l i n e s i n 36 c o u n t r i e s Ships a t Sea A l l major f l e e t s and r o u t e s Other M i l i t a r y and C i v i l i a n Sources. A 1 though t h e p r e s e n t a t i o n was i n t e r e s t i n g from an i n f o r m a t i o n v i e w p o i n t , t h e r e seemed t o be l i t t l e which would be of any g r e a t h e l p t o us. S o l a r a c t i v i t y p r e d i c t i o n s a r e made o n l y 90 days i n advance; t h u s , no h e l p t h e r e . They d i d make a p o i n t t h a t i f NASA r e q u i r e s any s u p p o r t on monitoring any s a t e l l i t e , f o r decay purposes o r o t h e r w i s e , they were w i l l i n g t o cooperate and, p r e s e n t l y a t l e a s t , w i t h no c o s t t o NASA. . This p r e s e n t a t i o n was coordinated by Col S c h u l h e r r from NASA Headquarters. Approximately 20 people a t t e n d e d t h e p r e s e n t a t i o n . Col. Baird and Col. White were t h e A i r Force o f f i c e r s i n charge of t h i s a s p e c t of NORAD'S work. (4) We have r e c e n t l y r e c e i v e d from D. G. King-Hele h i s l a t e s t works i n s a t e l l i t e l i f e t i m e and atmospheric d e n s i t y . To r e c i p r o c a t e t h i s g e s t u r e , we p l a n t o send him M r . ~ l e i s c h m a n ' s and M r . ~ e v e l s ' paper which was p r e s e n t e d a t t h e 3rd N a t i o n a l Conference on Aerospace Meteorology i n New Orleans on May 7 t h . The paper, e n t i t l e d "The I n f l u e n c ing F a c t o r s i n S a t e l l i t e O r b i t a l Decay and L i f e t i m e A n a l y s i s , " i s publi s h e d i n t h e proceedings of t h e meeting. �D. F l i g h t E v a l u a t i o n Branch 1. Saturn I B a. AS-205 (1) h o - ~ n ~ i n e s - o uControl t A s p e c i a l s t u d y of t h e c o n t r o l and m i s s i o n performance c a p a b i l i t i e s of t h e S a t u r n I B v e h i c l e w i t h l o s s of t h r u s t on two H-1 engines i s underway by CCSD, SSR #114. This w i l l provide i n l o r m a t i o n r e q u i r e d t o formulate a b o r t c r i t e r i a p e r t i n e n t t o crew s a f e t y and d e a c t i v a t i o n time f o r two-engine-out a u t o m a t i c a b o r t . Report r e s u l t s a r e expected on June 28, 1968. (2) I n f l i g h t Wind C a p a b i l i t y The i n f l i g h t wind c a p a b i l i t y of t h e AS-205 v e h i c l e f o r a non-wind b i a s e d f l i g h t program has been determined. For a s a f e t y f a c t o r of 1 . 4 and using a root-sum s q u a r e technique of combining t h e e f f e c t s of v e h i c l e t o l e r a n c e s , environmental t o l e r a n c e s , wind s h e a r s , and g u s t s , t h e v e h i c l e i s wind l i m i t e d t o 7 2 , 95 and 7 3 m/sec f o r head, t a i l , and c r o s s winds, r e s p e c t i v e l y . (3) Emergency D e t e c t i o n System (EDS) A j o i n t MSC/MSFC document of t h e AS-205 f l i g h t l i m i t s and a b o r t c r i t e r i a f o r a l l i d e n t i f i a b l e f a i l u r e modes has been h e l d up pending r e s o l u t i o n by MSC of t h e launch escape v e h i c l e l i m i t s 50 s e c o n d s ) . It now a p p e a r s t h a t MSC i n t h e e a r l y f l i g h t phase (0 w i l l r e a l i g n t h e launch escape motors t o handle s a t u r a t e d c o n t r o l s i g n a l f a i l u r e s and withdraw launch escape v e h i c l e l i m i t s t h a t were p r e v i o u s l y proposed of 3 d e g l s e c r a t e and 5 deg a t t i t u d e e r r o r i n p i t c h o r yaw and 15 deg r o l l a t t i t u d e e r r o r l i m i t . These c o n s t r a i n t s were r e s u l t i n g i n some unnecessary a b o r t s . - 2. Saturn V (1) Post F l i g h t Trajectory The p o s t - f l i g h t t r a j e c t o r i e s on t h e AS-502 launch v e h i c l e have been e s t a b 1 i s h e d and d i s t r i b u t e d t o t h e v a r i o u s t r a j e c t o r y u s e r s . The AS-502 t r a j e c t o r y was c l o s e t o nominal u n t i l t h e premature c u t o f f of t h e two S - I 1 e n g i n e s . A f t e r t h i s anomaly o c c u r r e d , t h e t r a j e c t o r y d e v i a t e d s i g n i f i c a n t l y from nominal. A t S-IVB c u t o f f , t h e spacef i x e d v e l o c i t y was 48.94 m/s g r e a t e r t h a n nominal. T h i s , a l o n g w i t h a �f l i g h t p a t h a n g l e of 0.378 deg l e s s than nominal, produced a n e l l i p t i c a l o r b i t w i t h a n e c c e n t r i c i t y 0.0138 g r e a t e r t h a n nominal. The r e s u l t i n g apogee of the o r b i t was 171.5 km h i g h e r than nominal, and t h e p e r i g e e was 1 2 . 2 km l e s s than nominal. A ground command t o t h e s p a c e c r a f t t o s e p a r a t e t h e LV/SC was g i v e n when i t was a s c e r t a i n e d t h a t t h e S-IVB s tage f a i l e d t o r e i g n i t e . Considerable time and e f f o r t w e r e s p e n t working w i t h TBC t o a s s u r e t h a t the p o s t - f l i g h t t r a j e c t o r y d e l i v e r i e s t h e y made were t e c h n i c a l l y a d e q u a t e f o r d i s t r i b u t i o n t o t h e t r a j e c t o r y u s e r s . AS-502 I t was f e l t t h a t d u p l i c a was t o be a p a r a l l e l t r a i n i n g e x e r c i s e by TBC. t i o n of e f f o r t would be e l i m i n a t e d i f TBC d e l i v e r i e s were used a s t h e o f f i c i a l t r a j e c t o r i e s . TBC did a n e x c e l l e n t job and f u r n i s h e d h i g h quality trajectories. Tracking d a t a a v a i l a b l e on AS-502 were of good q u a l i t y . GLOTRAC S t a t i o n I d a t a and C-band r a d a r d a t a from f i v e d i f f e r e n t s i t e s were t h e primary d a t a used i n t h e p o s t - f l i g h t powered f l i g h t t r a j e c t o r y . ODOP, Camera, and U n i f i e d S-band d a t a were a l s o used t o judge t h e q u a l i t y of t r a j e c t o r y . Free f l i g h t t r a j e c t o r i e s of t h e s p e n t s t a g e s were g e n e r a t e d u s i n g t h e a c t u a l s e p a r a t i o n c o n d i t i o n s and assuming t h e o r e t i c a l drag c h a r a c t e r i s t i c s . The S-IC s t a g e was observed breaking up a b o u t 397 seconds range time by photographic coverage from a n a i r c r a f t . The S-IVB s t a g e remained i n o r b i t and r e - e n t e r e d on A p r i l 26th. The AS-502 o r b i t a l i n s e r t i o n c o n d i t i o n s and r e s u l t i n g ephemeris up t o S-IVBISC s e p a r a t i o n were determined. Good agreement w i t h t h e MSC-determined ephemeris and s e p a r a t i o n c o n d i t i o n s was o b t a i n e d . The MSFC ephemeris was determined by n u m e r i c a l l y i n t e g r a t i n g t h e " b e s t e s t i mate" i n s e r t i o n c o n d i t i o n s forward t o s e p a r a t i o n (11667.8 s e c R.T.). These i n s e r t i o n c o n d i t i o n s were based on a l e a s t s q u a r e s f i t of t r a c k i n g d a t a (C-band) s p r e a d over t h e e n t i r e time of f l i g h t from i n s e r t i o n t o s e p a r a t i o n . The t e l e m e t e r e d guidance v e l o c i t y d a t a were used t o develop polynomial curve f i t s t o provide a v e n t i n g model. This model was s a t i s f a c t o r y and the b i a s e s solved f o r were i n r e a s o n a b l e agreement w i t h l a b o r a t o r y measurements. One i n t e r e s t i n g f a c t of t h e o r b i t a l determinat i o n was t h e u s e , f o r t h e f i r s t time, of C-band t r a c k i n g from a s h i p (REDSTONE). The d a t a were s u r p r i s i n g l y good and provided a more r e l i a b l e e s t i m a t e of t h e i n s e r t i o n parameters t h a n would have been p o s s i b l e o t h e r w i s e . Data d e l i v e r y was good w i t h a l l C-band t r a c k i n g r e c e i v e d by MSFC 30 hours. Low speed u n i f i e d S-band d a t a were r e c e i v e d over within L 15 days. Analysis of t h e s e d a t a i s c o n t i n u i n g . t e l e t y p e by L + + �(2) Pos t - F l i g h t P r o p u l s i o n Simulation I n p r e p a r a t i o n f o r the AS-502 f l i g h t , t h e s t a g e cont r a c t o r s matched t h e p r e d i c t e d o p e r a t i o n a l t r a j e c t o r y (O.T.) on t h e i r r e s p e c t i v e s t a g e s w i t h t h e i r p r o p u l s i o n s i m u l a t i o n programs. A f t e r AS-502 f l i g h t , t h e urgency of s p e c i a l s t u d i e s being performed t o v e r i f y t h e unusual performance of t h e f l i g h t delayed t h e d e l i v e r y of p r o p u l s i o n r e c o n s t r u c t i o n t a p e s and a s s o c i a t e d w e i g h t s . However, t h e s e a r e now i n hand. P r e l i m i n a r y a n a l y s e s on a l l s t a g e s have been performed. The r e s u l t s of t h e s e a n a l y s e s were p r e s e n t e d t o t h e F l i g h t E v a l u a t i o n Working Group meeting and have been submitted f o r t h e FEWG r e p o r t . S-IC s t a g e a n a l y s i s from t h e s i m u l a t i o n procedure i n d i c a t e s t h a t t h e average s e a l e v e l t h r u s t was v e r y c l o s e t o p r e d i c t e d . The a v e r a g e p r o p e l l a n t flow r a t e was almost 0.7 p e r c e n t l e s s than p r e d i c t e d and t h e s p e c i f i c impulse was almost 0.7 p e r c e n t h i g h e r t h a n p r e d i c t e d . Because of t h e a i r scoops having been removed from AS-502, a d i f f e r e n t drag c o e f f i c i e n t was expected. A lower t o t a l drag c o e f f i c i e n t w a s observed on AS-502. S e v e r a l f l i g h t s w i t h t h i s same c o n f i g u r a t i o n w i l l be r e q u i r e d t o a c c u r a t e l y determine t h e new drag c o e f f i c i e n t . The S - I 1 s t a g e a n a l y s i s was complicated by t h e twoengine shutdown. As a r e s u l t , t h e t o t a l f l i g h t a v e r a g e s f o r l o n g i t u d i n a l t h r u s t , v e h i c l e mass l o s s r a t e , and s p e c i f i c impulse was q u i t e d i f f e r e n t from p r e d i c t e d . Stage performance b e f o r e t h e m a l f u n c t i o n (170 s e c ) was v e r y c l o s e t o p r e d i c t e d . T h r u s t , p r o p e l l a n t flow r a t e and m i x t u r e r a t i o were .43 p e r c e n t , .52 p e r c e n t and .73 p e r c e n t , r e s p e c t i v e l y , below p r e d i c t e d v a l u e s w h i l e s p e c i f i c impulse exceeded p r e d i c t i o n by 0.09 p e r c e n t . The S-IVB s t a g e a n a l y s i s showed a n i n c r e a s e of 0.58 perc e n t and 0.34 p e r c e n t compared t o p r e d i c t e d i n t h e t o t a l a v e r a g e t h r u s t and flow r a t e , r e s p e c t i v e l y . S p e c i f i c impulse decreased by 0.2 p e r c e n t . The S-IVB burn time was 29.2 seconds l o n g e r t h a n p r e d i c t e d . This deviat i o n was e x p l a i n e d by d e v i a t i o n i n i n i t i a l mass, flow r a t e , t h r u s t and p r e c o n d i t i o n s of f l i g h t ( v e l o c i t y magnitude, e l e v a t i o n of f l i g h t , p a t h a n g l e , and a l t i t u d e ) . (3) AS-502 Guidance The major loop guidance (LVDC) t e l e m e t r y was reduced and e d i t e d w i t h o n l y minor problems. The e d i t procedure a d e q u a t e l y handled t h e few d a t a dropouts t h a t occurred. Hornever, time and d a t a a t a few p o i n t s were n o t compatible. These occurred near s t a g i n g where t h e e d i t c o n s t r a i n t s a r e r e l a x e d . Data p l o t s v e r s u s time i n d i c a t e d erroneous t i m e s , and the processed d a t a were ad jus t e d a c c o r d i n g l y . Such e r r o r s a r e t o be expected. �The minor loop t e l e m e t r y (LVDA) was more d i f f i c u l t e d i t t h a n expected. There were more than u s u a l time e r r o r s because o: overflow of word b i t s and major loop t e l e m e t r y o v e r r i d i n g t h e LVDA out p u t s . This i s u s u a l l y handled by e l i m i n a t i n g time p o i n t s o u t of seque when e d i t i n g t h e d a t a . S i n c e t h e LVDA d a t a a r e sampled approximately 25 times p e r second, t h e r e i s a redundancy of d a t a . However, t h e time e r r o r s noted on AS-502 caused t h e e l i m i n a t i o n of d a t a where r e c y c l i n g of t h e accumulators o r c u r r e d . These problems a r e d i f f i c u l t t o a u t o m a t i c a l l y c o r r e c t . C o r r e c t i o n s were made by hand and i n p u t by c a r d s f o r corrections t o the tape outputs. A f t e r t h e guidance t e l e m e t r y were reduced, e d i t e d , and d a t a d i s t r i b u t e d t o v a r i o u s c o n t r a c t o r s and MSC, a timing e r r o r was d i s covered i n t h e LVDA d a t a by comparing similar measurements w i t h t h e d i g i t a l guidance o u t p u t s . IBM people were r e q u e s t e d t o check t h e d a t a r e d u c t i o n procedures; t h e y were found t o b e c o r r e c t . However, a f t e r checking t h e d a t a r e d u c t i o n program, i t was found t h a t t h e updating of time r e f e r e n c e f o r LVDA d a t a w i t h i n a major computer c y c l e was done at: t h e end of t h e c y c l e i n s t e a d of t h e beginning. This r e s u l t e d i n a time b i a s approximately e q u a l t o a major computer c y c l e and v a r y i n g d u r i n g powered f l i g h t a c c o r d i n g t o t h e n e c e s s a r y computations t o b e made. This has been c o r r e c t e d and a n a d j u s t e d d a t a t a p e s e n t t o MSC. Some roughness i n v e l o c i t i e s caused by i n t e r p o l a t i o n d u r i n g s t a g i n g i s b e i n g smoothed. This c o r r e c t i o n w i l l be made i n a d d i t i o n t o t h e LVDA c o r r e c t i o n s , and d i s t r i b u t i o n of c o r r e c t e d d a t a w i l l b e made a c c o r d i n g t o t h e PDRD r e q u e s t s f o r t h e f i n a l s e l e c t e d guidance d a t a . (4) AS-502 Control APS engine chamber p r e s s u r e d a t a i n d i c a t e s t h a t f u e l d e p l e t e d i n module I a.t: 21,953 s e c R.T. A t 22,030 seconds, t h e yaw a t t i t u d e e r r o r d a t a show t h a t t h e nominal +1 deg APS deadband has been exceeded and t h a t yaw a t t i t u d e r a t e s were i n c r e a s i n g due t o l o s s of t h r u s t i n t h i s module and LOX v e n t i n g . Fuel d e p l e t i o n occurred i n module I11 a t 22,602 seconds. Angular r a t e s continued t o i n c r e a s e and were approximately 7 d e g / s e c and 2.5 d e g / s e c i n yaw and p i t c h r e s p e c t i v e l y , by 22,800 seconds. A f t e r t h i s time, tumble r a t e s were reduced from r a d a r and o p t i c a l t r a c k i n g d a t a which a r e a v a i l a b l e u n t i l launch +10 days. Tumble r a t e s continued t o i n c r e a s e due t o LOX v e n t i n g u n t i l a r a t e of 180 d e g / s e c was recorded on t h e 9 t h day f o l l o w i n g launch. b. AS-503 (Mission D) Abort and A l t e r n a t e Mission A n a l y s i s The AS-503 A&AM document d e l i v e r y d a t e has been changed from June 15 t o August 1 f o r t h e . 'following r e a s o n s : �(1) The f i r s t s e t of p r o p u l s i o n s y s t e m m a l f u n c t i o n d a t a f u r n i s h e d by R-P&VE c o n s i s t e d of ( a ) s i n g l e S-IC and S - I 1 s t a g e engine f a i l u r e s , and (b) S-IVB extended burns. These c a s e s were generated from a p r e d i c t e d nominal which has s i n c e been updated. (2) The f i r s t s e t of d a t a d i d n o t c o n t a i n dual-enginef a i l u r e c a s e s f o r S-IC and S-11 s t a g e s , S - I 1 and S-IVB PU v a l v e f a i l u r e , o r f a i l u r e t o LET and i n t e r s t a g e t o j e t t i s o n . A complete s e t of new AS-503 p r o p u l s i o n system m a l f u n c t i o n c a s e s were r e q u e s t e d from R-P&VE-P. The new d a t a , which w i l l c o n t a i n c a s e s mentioned i n (1) and ( 2 ) , w i l l b e compatible w i t h t h e p r o p u l s i o n system performance p r e d i c t i o n s being used i n t h e c u r r e n t AS-503 operat i o n a l t r a j e c t o r y . I n t h e i r r e p l y t o t h e r e q u e s t , R-P&VE-P s t a t e d t h a t t h e d a t a would be a v a i l a b l e a b o u t June 1, 1968. 3. General a. AZUS~/GLOTRAC Tracking Requirements Because of budgetary c o n s i d e r a t i o n s , t h e q u e s t i o n a r o s e whether Azusa/GLOTRAC s u p p o r t was r e q u i r e d on f u t u r e S a t u r n v e h i c l e s . O r i g i n a l l y i t was agreed t h a t t h i s s u p p o r t was r e q u i r e d f o r a l l R&D S a t u r n v e h i c l e s . The R&D phase of t h e S a t u r n IB program has been comp l e t e d . Although t h e S a t u r n V E D program is n o t completed, i t is f e l t t h a t a l l of t h e R&D o b j e c t i v e s t h a t r e q u i r e Azus~/GLoTRAc s u p p o r t on t h e S a t u r n V have been achieved. T h e r e f o r e , a p p r o p r i a t e a c t i o n has been i n i t i a t e d t o d e l e t e any f u t u r e MSFC requirements f o r AZUS~/GLOTRAC support. b. S t a t e Vector "Update" Analysis An agreement was made a t t h e l a s t G&P meeting t h a t t h e f o l l o w i n g would b e done. (1) An o u t l i n e of t h e 'Is t a t e v e c t o r " update a n a l y s i s proposed would be s e n t through t h e Co-Chairman of t h e G&P Subpanel t o a p p r o p r i a t e o r g a n i z a t i o n s of MSC. (2) A r e q u e s t would b e made t o MSC f o r t h e (1) a c c u r a c i e s a s s o c i a t e d w i t h t h e r e a l - t i m e determined s t a t e v e c t o r , and (2) t h e a c c u r a c i e s a s s o c i a t e d w i t h t h e e x t r a p o l a t i o n of t h e r e a l - t i m e determined s t a t e v e c t o r t o t h e p o i n t of implementation. This procedure w i l l a i d i n making s u r e t h a t a n a l y s i s w i l l b e made u s i n g r e a l i s t i c assumptions and o u t p u t t h e i n f o r m a t i o n r e q u i r e d by b o t h MSFC and MSC. �The a n a l y s i s proposal has been w r i t t e n and copies l a v e been d i s t r i b u t e d t o v a r i o u s MSFC o r g a n i z a t i o n s f o r concurrence b e f o r e sending i t t o MSC. MSC w i l l probably d e s i r e s e v e r a l of t h e magnetic t a p e s coming from t h e planned s i m u l a t i o n s t o a i d them i n t h e i r s t u d i e s . c. S a t u r n V 6-D T r a j e c t o r y Simulator The e s t a b l i s h e d o b j e c t i v e of t h i s program is t o develop a S a t u r n V t r a j e c t o r y s i m u l a t o r i n s i x degrees of freedom that r u n s from guidance r e f e r e n c e r e l e a s e through a l l powered f l i g h t phases and t h e parking o r b i t phase t o t h e p o i n t of i n j e c t i o n i n t o a l u n a r t r a j e c t o r y . This program i s intended t o f u l f i l l t h e R-AERO-FF 6-D requirements f o r p r e f l i g h t and p o s t - f l i g h t s t u d i e s . The r e q u i r e d c a p a b i l i t y i s a complete six-degrees-of-freedom t r a j e c t o r y , a closedloop guidance system, a closed-loop p r o p e l l a n t u t i l i z a t i o n system, a closed-loop p r o p u l s i o n system, and closed-loop c o n t r o l f i l t e r s . The s t a t u s of t h e s e c a p a b i l i t i e s i n t h e program i s as follows: A complete (1) Complete 6-degrees-of-freedom: 6-degrees-of-freedom t r a j e c t o r y g e n e r a t e d from guidance r e f e r e n c e r e l e a s e through a l l powered f l i g h t and o r b i t a l f l i g h t has been s u c c e s s f u l l y implemented i n t h e SAAM-V deck. The second burn of t h e S-IVB s t a g e and o r b i t a l f l i g h t were r u n i n t h e open-loop guidance mode w i t h a t t i t u d e commands i n p u t . (2) Closed-loop c o n t r o l f i l t e r s : The complete closedloop c o n t r o l f i l t e r system of t h e S a t u r n V v e h i c l e has been i n c o r p o r a t e d i n t o t h e S a t u r n V 6-D program. ( 3 ) Closed-loop guidance: The i t e r a t i v e guidance scheme a s implemented i n t h e onboard S a t u r n V guidance computer has been i n c o r p o r a t e d i n t o t h e SAAM-V program i n closed loop from guidance r e f e r e n c e r e l e a s e t o f i r s t S-IVB c u t o f f . The guidance e q u a t i o n s which s i m u l a t e t h e parking o r b i t , r e s t a r t p r e p a r a t i o n , r e s t a r t , second powered f l i g h t , and w a i t i n g o r b i t have been prepared. The c a p a b i l i t y t o s i m u l a t e a c c e l e r o m e t e r f a i l u r e c a s e s and t o perform v e c t o r updates t o t h e o r b i t a l n a v i g a t i o n system has been i n c l u d e d . The programming and implementation of t h e s e e q u a t i o n s i n t h e deck a r e i n p r o g r e s s . ( 4 ) Closed-loop p r o p u l s i o n s i m u l a t i o n system and closed-loop p r o p e l l a n t u t i l i z a t i o n system: The closed-loop p r o p u l s i o n s i m u l a t i o n module (PSM) i s being developed i n a p a r a l l e l 6-D program. When d e c l a r e d o p e r a t i o n a l , t h e PSM w i l l be t r a n s f e r r e d t o t h e R-AERO-PF �6-D program. C o n t r a c t NAS8-21160 completed on January 12, 1968 by Operations Research, Inc. provided R-AERO-F w i t h t h e p o t e n t i a l a b i l i t y f o r closed-loop p r o p u l s i o n s i m u l a t i o n . The PSM provided by O R 1 was n o t considered completely u s a b l e s i n c e s e v e r a l r e f i n e m e n t s were needed. Since t h e time t h e above d a t a were o b t a i n e d , in-house e f f o r t s t o make t h e PSM o p e r a t i o n a l have r e s u l t e d i n t h e following: - (a) Control F i l t e r s The completed c o n t r o l f i l t e r s i m u l a t i o n needed f o r a S a t u r n V v e h i c l e can now be used i n c o n j u n c t i o n w i t h t h e PSM. Machine core s t o r a g e problems i n t h i s a r e a have been overcome. (b) Mass D i s c o n t i n u i t i e s These a r e now handled by t h e PSM a c c u r a t e l y . The PSM c o n s i d e r s t h e proper d i s c o n t i n u i t y i n t h e c e n t e r of g r a v i t y and moment of i n e r t i a computations. (c) For a more r e a l i s t i c simulaP r e s s u r i z a t i o n Tables t i o n of d i s p e r s i o n c a s e s (engine o u t , e t c . ) , p r e s s u r i z a t i o n t a b l e s a r e now i n p u t a s a f u n c t i o n of mass l o s s i n s t e a d of s t a g e f l i g h t time. - - Before t h e PSM can be used i n s i m u l a t i o n s , t h e following must be completed: (a) The v a l i d i t y of t h e S-IVB p r o p e l l a n t u t i l i z a t i o n model must b e v e r i f i e d . Some q u e s t i o n s a b o u t t h e completeness of t h e e q u a t i o n s a r e p r e s e n t l y b e i n g investigated. (b) Demonstrate t h e PSM i n a continuous s i m u l a t e d f l i g h t from guidance r e f e r e n c e r e l e a s e through f i n a l S-IVB burn. This i n v o l v e s e s t a b l i s h i n g a nominal PSM g e n e r a t e d t r a j e c t o r y that w i l l corn pare very c l o s e l y w i t h a n operational t r a j e c t o r y (c) Demonstrate t h e p e r t u r b a t i v e c a p a b i l i t y of t h e PS These t h r e e items a r e i n p r o g r e s s . It a p p e a r s t h a t O R 1 may be awarded a n a d d i t i o n a l c o n t r a c t t o a s s i s t i n e l e v a t i n g t h e PSM t o an operational status. �BIBLIOGRAPHY 1. G a l l i , D. H., "The Use of S t a t i s t i c s i n Guidance A n a l y s i s ," IN-AERO-68-2, U n c l a s s i f i e d , A p r i l 17, 1968. 2. G i l l i s , W. T. , "Damping of Thermoelas t i c S t r u c t u r e s , I 1 U n c l a s s i f i e d , NASA TM X-53722, A p r i l 1 0 , 1968. 3. E u l e r , H. C., "Solar A c t i v i t y ~ n d i c e ," s NASA TM X-53727, May 15, 1968. 4. Pack, Homer, "A Method of Bending V i b r a t i o n Analysis f o r a Vehicle w i t h F l e x i b l y Suspended Components," NASA 'IM X-53733, A p r i l 30, 1968. 5. Harkins, S . , "Compartment Venting and Pipe Flow w i t h Beat Addition," NASA TM X-53734, A p r i l 23, 1968. 6. Redus, J . R., "A D i s c u s s i o n of t h e S t a b i l i t y Requirements f o r a Launch Vehicle F l i g h t Control System," NASA TM X-53735, May 3 , 1968. 7. G r e g o r i a , D. G . , "A Generalized S t a t e V a r i a b l e Approach t o t h e Problem of Absolute S t a b i l i t y , " NASA 'IM X-53736, May 6, 1968. 8. Smith, R. E . , D. K. Weidner and C. L. H a s s e l t i n e , " O r b i t a l Environment C r i t e r i a and A p p l i c a t i o n s , " NASA TM X-53741, May 29, 1968. �APPROVAL ctor , Aero-As t r o d y n a m i c s L a b o r a t o r y E . D. G e i s s l e r D i r e c t o r , Aero-As t r o d y n a m i c s L a b o r a t o r y DISTRIBUTION R-AERO-DIR Dr. G e i s s l e r M r . Jean Mr. B u t l e r R-AERO-R M r . B e a n (4) Mrs. Hightower R-AERO-T Mr. M u r p h r e e Mr. C u m i n g s Dr. Heybey Mr. J a n d e b e u r Dr. K r a u s e Mr. N a t h a n M r . Few M r . von P u t t k a m e r PAO, M r . K u r t z R-DIR, M r . W e i d n e r MS-H, Miss J e r r e l l (3) I-V-P, Mr. Price R-AERO-P R-AERO-D R-AERO-A R-AERO-G R-AERO-Y R-AERO-F R-AERO-X (8) (16) (16) (6) (8) (8) (4) � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000039 Title A name given to the resource "Aero-Astrodynamics Laboratory Bimonthly Progress Report: April - May 1968." Description An account of the resource Includes Advanced Studies Office, Aerospace Environment Division, Astrodynamics and Guidance Theory Division, Projects Office, Aerophysics Division, Dynamics and Flight Mechanics Division, Flight Test Analysis Division. Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center Date A point or period of time associated with an event in the lifecycle of the resource 1968-06-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) NASA space programs Project management Type The nature or genre of the resource Progress reports Text Source A related resource from which the described resource is derived Saturn V Collection Box 27, Folder 1 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050 https://digitalprojects.uah.edu/files/original/20/987/spc_stnv_000040.pdf 03a53e602bbb20f751d1fa9250de24bb PDF Text Text AERO-ASTRODYNAMICS LABORATORY BIMONTHLY PROGRESS REPORT February .March 1968 INDEX Page TECHNICAL AND SCIENTIFIC STAFF ........................... . .................................. ............................... ............. ...... AEROSPACE ENVIRONMENT DIVISION ........................... A . Atmospheric Dynamics Branch .......................... B . Space Environment Branch ............................. C . T e r r e s t r i a l Environment Branch ........................ PROJECTS OFFICE .......................................... ADVANCED STUDIES OFFICE A Systems A n a l y s i s Group B . Mission A n a l y s i s and Astrodynamics Group C F l i g h t Mechanics and Performance A n a l y s i s Group I1 . . . 111 .' v. ASTRODYNAMICS AND GUIDANCE THEORY DIVISION ............... A . Guidance Theory Branch ............................... IV . B C. VI . ........................... ................................. O p t i m i z a t i o n Theory Branch Astrodynamics Branch ..................................... ...................... ............................. AEROPHYSICS DIVISION A F l u i d Mechanics Research O f f i c e B Mechanical Design O f f i c e C Aerodynamic Design Branch D Experimental Aerophysics Branch E Thermal Environment Branch F . Unsteady Aerodynamics Branch . . . ............................ ...................... ........................... ......................... . . . ................... ............................................. . ............................................ ................... .............................................. V I I I . FLIGHT TEST ANALYSIS DIVISION ............................ A . S p e c i a l P r o j e c t s O f f i c e .............................. B . F l i g h t Mechanics Branch .............................. C . Tracking and O r b i t a l A n a l y s i s Branch ................. VII DYNAMICS AND FLIGHT MECHANICS DIVISION A . Multi-Projects B . Saturn V C Saturn I B D . S a t u r n Apollo A p p l i c a t i o n s Program E . General ....................................... D . F l i g h t E v a l u a t i o n Branch ............................. �AERO-ASTRODYNAMICS LABORATORY BIMONTHLY PROGRESS REPORT February I. - March 1968 TECHNICAL AND SCIENTIFIC STAFF 1. ODYSSEY Some s u g g e s t i o n s f o r optimizing t h e package of e a r t h o r b i t a l aeronomy experiments ( p a s s i v e s p h e r e ensemble, paddlewheel s a t e l l i t e , d e n s i t o m e t e r , and mass s p e c t r o m e t e r ) t o i n c l u d e i n j e c t i n g i n t o a n o r b i t of high e c c e n t r i c i t y have been made. Among t h e many advantages of t h e s e s u g g e s t i o n s would be a b e t t e r d e f i n i t i o n of t h e f r e e molecular and nearf r e e - m o l e c u l a r flow drag c o e f f i c i e n t s . However, some problems a s s o c i a t e d w i t h implementing t h e experiment package i n t o such a h i g h e c c e n t r i c i t y o r b i t ( E = . 8 5 , i n i t i a l p e r i g e e 170 km) a r e being c a r e f u l l y s c r u t i n i z e d . Included i n t h e s e problems a r e t h e paddlewheel and p a s s i v e s p h e r e s a t e l l i t e aerodynamic h e a t i n g environment which c o n t i n u e s t o be d e f i n e d f o r t h e lower p e r i g e e a l t i t u d e s . For example, a t a g i v e n s e t of i n i t i a l c o n d i t i o n s , i n c l u d i n g i n i t i a l p o s i t i o n of p e r i g e e a t 170 km, t h e h e i g h t of p e r i g e e has been c a l c u l a t e d t o d e c r e a s e t o a s low a s 120 km i n s e v e r a l days by t h e l u n a r and s o l a r p e r t u r b a t i o n s . Some p r e l i m i n a r y s u r f a c e temperatures r e l a t e d t o the p a s s i v e s p h e r e a r e b e i n g g e n e r a t e d corresponding t o t h e s e e s t i m a t e d p e r i g e e a l t i t u d e s around 120 km. (Few) 2 . E x t e n s i v e i n v e s t i g a t i o n s were c a r r i e d o u t on t h e proper a r r a n g e ment of ground-fixed d e t e c t o r s and beams t o measure wind v e l o c i t y a t a predetermined h e i g h t . S p e c i a l c a r e was g i v e n t o t h e e f f e c t of observat i o n a l e r r o r on t h e outcome. The work i s i n t h e f i n a l s t a g e s now; t e n e t s and r e s u l t s w i l l be r e p o r t e d on i n a TM-X t o be w r i t t e n and published i n t h e weeks t o come. A n o t e i s being prepared on two-spot i s o t r o p y and t h e r e l a t i o n s h i p of two-point and two-beam covariances a s developed w i t h t h e a i d of (Heybey) F o u r i e r t r a n s forms. 11. A. ADVANCED STUDIES OFFICE Sys terns Analysis Group J a y H. Laue of R-P&VE-AP made a p r e s e n t a t i o n t o M r . Frank Williams, R-AS-DIR on t h e p r e s s u r e - f e d launch v e h i c l e (PFLV) in-house s t u d y on March 2 7 , 1968. A t t h e l a s t AS0 management b r i e f i n g on t h e PFLV (November 1 9 6 7 ) , a b a s e l i n e c o n f i g u r a t i o n was s e l e c t e d f o r in-depth a n a l y s i s d u r i n g �Phase I of the s t u d y . The r e s u l t s of t h e Phase I s t u d y were t h e s u b s t a n c e of t h e March 27 p r e s e n t a t i o n . Phase I r e s u l t s showed t h e b a s e l i n e conf i g u r a t i o n p r o p e l l a n t tanks t o be e x c e s s i v e l y t h i c k , t h a t geometric s c a l i n g of s t a g e s i s n o t d e s i r a b l e , and t h e v e h i c l e was expensive. M r . Laue then p r e s e n t e d a c a n d i d a t e f o r t h e Phase I1 c o n f i g u r a t i o n , t h e main f e a t u r e s of which a r e c l u s t e r e d p r o p e l l a n t tanks w i t h s m a l l e r w a l l t h i c k n e s s and commonality of hardware between s t a g e s r a t h e r than emphasis on s c a l i n g . The proposed c o n f i g u r a t i o n has more hardware i n common between s t a g e s than do t h e p r e s e n t T i t a n c o n f i g u r a t i o n s . The C h r y s l e r Corporation Space D i v i s i o n (CCSD) "National Space Booster Studytt w i l l be funded and work i s expected t o be under c o n t r a c t w i t h i n a few days. The s t u d y i s expected t o c o n s i s t of t h e f o l l o w i n g g e n e r a t i o n of a launch v e h i c l e spectrum t o g i v e a n i n t e g r a t e d i n c r e mental c a p a b i l i t y t o match t h e missions provided by MSFC; i n v e s t i g a t i o n of s p e c i f i c a t i o n s f o r launch v e h i c l e d e s i g n , development and o p e r a t i o n s t o determine what s p e c i f i c a t i o n s r a i s e c o s t s ; recommendation of s p e c i f i c a t i o n changes on p r e s e n t launch v e h i c l e s t o reduce c o s t s of p r e s e n t systems; and a p r e s s u r e - f e d launch v e h i c l e s t u d y ( i n c l u d i n g e n g i n e s ) . B. Miss i o n Analys i s and As trodynamics Group 1. S a t u r n V Workshop A s e c t i o n e n t i t l e d " O r b i t a l Analysis" has been completed f o r i n c o r p o r a t i o n i n t o t h e MSFC's S a t u r n V Workshop r e p o r t . The c o n t e n t of t h i s s e c t i o n i n c l u d e s i n f o r m a t i o n p e r t i n e n t t o o r b i t a l l i f e t i m e , rendezvous -compatible o r b i t s , ground launch window, t h e sun' s i l l u m i n a t i o n a n g l e r e l a t i v e t o t h e workshop o r b i t p l a n e , sun-synchronous o r b i t s , v e h i c l e a t t i t u d e , and gimbal a n g l e h i s t o r i e s . 2. Synchronous O r b i t S t u d i e s I n s u p p o r t of t h e AS0 "Synchronous O r b i t Study ," p r e l i m i n a r y S a t u r n V payload c a p a b i l i t i e s t o 80, 90, 100, 110, and 120 degrees west l o n g i t u d e hover p o i n t s and zero-degree synchronous o r b i t i n c l i n a t i o n s have been c a l c u l a t e d and t r a n s m i t t e d t o M r . Paul Thomas, R-AS. I n r e s p o n s e t o a r e q u e s t by M r . Tidd, R-AS-OM, a spectrum of launch v e h i c l e payloads t o a 90° West hover p o i n t f o r z e r o and 28.5" i n c l i n a t i o n synchronous o r b i t s has been o b t a i n e d . The v e h i c l e s conT i t a n I I I C , T i t a n 1 1 I ~ / ~ g e n aA , t l a s SLA-3A/ s i d e r e d were S a t u r n IB/SM, Agena, A t l a s sLV- 3C/ Centaur, and TAT/DELTA/FW~. �3. AIAA Technology f o r Manned P l a n e t a r y Mission Meeting M r . Bobby E l l i s o n from t h i s o f f i c e a t t e n d e d t h i s meeting on March 4-6, 1968, i n New Orleans. A copy of t h e papers presented a r e a v a i l a b l e i n t h i s o f f i c e f o r information and review. 4. Unmanned P l a n e t a r y Study A s t u d y i s underway by R-AERO-XF on t h e performance of t h e T i t a n family of launch v e h i c l e s . The c o n f i g u r a t i o n and weight summaries have been received from R-P&VE-A on the T i t a n 111~/Centaur, T i t a n I I ~ F I T r a n s t a g e , T i t a n I I I F / S t r e t c h e d Transtage, T i t a n IIIF/ Centaur, T i t a n IIIM, and T i t a n I I I C . These T i t a n c o n f i g u r a t i o n s and aur t h e spectrum t h e Saturn V, Saturn IB/SM, and Saturn ~ ~ / ~ e n t comprise of launch v e h i c l e s t o be used i n Unmanned P l a n e t a r y Study. A d a t a package was prepared f o r M r . Frank Williams, R-AS-DIR, f o r use a t t h e OSSA "Planetary Working Group" on A p r i l 3 , 1968. The P l a n e t a r y Working Group i s headed by M r . Don Hearth of OSSA. This package c o n s i s t e d of background and c u r r e n t m a t e r i a l being generated i n t h e AS0 Unmanned P l a n e t a r y Study. 5. In-House Study "Application of Voyager S p a c e c r a f t t o Venus and J u p i t e r M i s s ions" Although the e s s e n t i a l s p a c e c r a f t and a s t r i o n i c s d a t a have n o t y e t been received from R-P&VE-A and R-ASTR-A, documentation of t h e s tudy has begun. C. F l i g h t Mechanics and Performance Analys is Group The major a c t i v i t y of t h i s group has been t o support t h e f i n a l a n a l y s i s of t h e Phase A s t u d y of t h e Saturn V Workshop. Documentatic of t h i s work should soon be completed. Data have been generated f o r t h e two-s tage S a t u r n V, including performance, instantaneous impact p o i n t s , impact zones, and t r a j e c t o r y shaping t o modify t h e S-IC impa zone. Data of t h i s same type have a l s o been generated f o r t h e l o g i s v e h i c l e s including both t h e T i t a n 111 and t h e S-IB. A program i s being modified f o r t h e CDC 3200 computer t o enabl t h i s group t o respond more q u i c k l y t o r e q u e s t s f o r raw f l i g h t mecha data. On February 1, t h e Mission Analysis Task Group met a t NASA He; q u a r t e r s . M r . Goldsby from t h i s o f f i c e provided information on pe formance, range s a f e t y and a b o r t problems of t h e Saturn V Workshop �On February 15, M r . Goldsby presented t h e continued work of t h i s o f f i c e on t h e range s a f e t y and a b o r t problem a t a meeting of t h e OWS Task Group a t MSC. M r . Madewell and M r . Becker of R-AS0 made a p r e s e n t a t i o n t o M r . Matthews, NASA Headquarters, on March 7 and 8, and t o t h e Thompson Committee on March 12 on t h e S a t u r n V Workshop. On March 1 3 , M r . Becker and M r . Madewel 1 reviewed t h e r e s u l t s of t h e i r p r e s e n t a t i o n s f o r members of t h e MSFC t a s k group. They r e p o r t e d that t h e i r p r e s e n t a t i o n s t o M r . Matthews and t o t h e Thompson Committee r e s u l t e d i n no major d e c i s i o n s and t h a t p o s i t i v e d i r e c t i o n s f o r c o n t i n u i n g t h e e f f o r t were n o t provided. They a l s o s t a t e d t h a t M r . Matthews d i d n o t f e e l t h a t a l l p o s s i b l e a l t e r n a t i v e s l e a d i n g t o a "C" type of c o n f i g u r a t i o n have been d e r i v e d and t h a t he does n o t want t o c o n s t r a i n any o p t i o n s a t t h i s time. M r . Becker and M r . Madewell r e p o r t e d t h a t M r . Matthews d i s c u s s e d a s p e c i f i c concept t h a t tends t o be more advanced t h a n "B", b u t l e s s The comments a t t h e MSFC meeting on t h e 1 3 t h advanced than "C". 'revealed t h a t no major d e c i s i o n s can be expected on t h e S a t u r n V Workshop (1) u n t i l t h e Thompson Committee has f i n a l i z e d t h e i r r e p o r t , (2) u n t i l t h e consequences of t h e p r e s e n t budgetary e x e r c i s e s a r e r e a l i z e d , and ( 3 ) u n t i l t h e Hideaway meeting i s h e l d . A subsequent meeting on March 29 w i t h R-ASA personnel r e s u l t e d i n n o t h i n g of consequence. 111, AEROSPACE ENVIRONMENT DIVISION A. Atmospheric Dynamics Branch 1. CPS-9 Radar/Thunderstorm Study a t MSFC During 1968 The CPS-9 weather r a d a r l o c a t e d a t t h e Atmospheric Research F a c i l i t y (Bldg. 4614) w i l l b e used by R-AERO-Y t o s t u d y l o c a l thunderstorm development, motion, and a s s o c i a t e d s u r f a c e wind c o n d i t i o n s i n t h e s p r i n g and summer of 1968. Data and i n s t r u m e n t a t i o n requirements f o r t h i s s t u d y have been s p e c i f i e d i n memorandum R-AERO-YE-129-68, "CPS-9 ~ a d a r / T h u n d e r s t o r m Study a t MSFC During 1968." The p r e p a r a t o r y work n e c e s s a r y f o r i n i t i a l d a t a a c q u i s i t i o n f o r S a t u r n V ground wind problems has begun, and t h e p r o j e c t is expected t o be i n o p e r a t i o n as planned. 2. Environmental T e s t s of Jimsphere and Rose Type Balloons M r . John W. Kaufman and M r . Dennis W. Camp v i s i t e d t h e D-4 s i t e of E g l i n A i r Force Base, F l o r i d a , t o p a r t i c i p a t e i n f i e l d t e s t s of t h e Jimsphere and v a r i o u s Rose-type b a l l o o n s used t o a c q u i r e upper atmosp h e r i c wind p r o f i l e d a t a . These t e s t s were performed d u r i n g March 1968. M r . John Wright of AFCRL, t h e t e s t d i r e c t o r , i s r e s p o n s i b l e f o r e v a l u a t i n g t h e r e s u l t s of t h e s e f i e l d t e s t s . The f o l l o w i n g types of b a l l o o n s were used: �- AFCRL'S s t a n d a r d 40-inch d i a m e t e r , 8-gore B - a 40-inch d i a m e t e r , 4-gore (shaped), Rose Type A Type Rose. without the b u i l t - i n corner r e f l e c t o r . Type C -a Type D - MSFC'S 40-inch d i a m e t e r , 4-gore (shaped), Rose cont a i n i n g a corner r e f l e c t o r . 2-meter ~ i m s p h e r e . These t e s t s were conducted f o r t h e f o l l o w i n g r e a s o n s : a. To determine f u r t h e r t h e e r r o r s i n f i n e - s c a l e winds by o b t a i n i n g more d u a l - t r a c k d a t a i n h i g h wind f i e l d s . b. To determine if advance Rose d e s i g n s can be t r a c k e d t o g r e a t e r d i s t a n c e s and lower a n g l e s t h a n t h e s t a n d a r d Rose. c. To check t h e newer r a p i d - i n f l a t i o n v a l v e and i t s e f f e c t on Rose performance . d. To compare some Jimspheres w i t h t h e Rose. M r . Moses Sharenow of t h e F o r t Monmouth S i g n a l Corp L a b o r a t o r i e s (Code: AM SEL-BL-TE) w a s a t t h e D-4 s i t e d u r i n g t h e week of March 1 0 t h t o w i t n e s s t h e f i e l d t e s t s . M r . Sharenow, who is r e s p o n s i b l e f o r s t a n d a r d i z i n g t h e Jimsphere as r e q u e s t e d by R-AERO-Y, p l a n s t o review t h e r e s u l t s of t h e s e t e s t s . The s t a n d a r d i z i n g of t h e Jimsphere w i l l depend l a r g e l y on M r . sharenow's o p i n i o n of t h e s e t e s t s and t h e t e s t r e s u l t s . M r . Sharenow expressed d i s p l e a s u r e i n t h e way t h e t e s t s were b e i n g conducted. The primary r e a s o n f o r t h i s d i s p l e a s u r e was t h a t M r . Sharenow d i d n o t b e l i e v e t h e AFCRL people were i n t e r e s t e d i n p r o v i d i n g him w i t h i n f o r m a t i o n he needed t o perform h i s r e s p o n s i b i l i t y of s t a n d a r d i z i n g t h e Jimsphere. For t h e same r e a s o n , M r . Kaufman and M r . Camp were n o t comp l e t e l y pleased w i t h the t e s t s . M r . Kaufman and M r . Camp a l s o v i s i t e d KSC t o d i s c u s s v a r i o u s problems r e l a t e d t o t h e a c q u i s i t i o n of lower and upper atmospheric d a t a i n regard t o r o u t i n e d a t a a c q u i s i t i o n , s p e c i a l research t a s k s , the launch of S a t u r n v e h i c l e s , e t c . 3. F a s t Response Anemometer Twenty-five p r o p o s a l s were r e c e i v e d i n r e p l y t o a n RFP f o r t h e development of a f a s t response anemometer. This anemometer w i l l be used t o o b t a i n d a t a f o r f r e q u e n c i e s > 1 cps t o be used i n s e l e c t e d s t r u c t u r a l r e s p o n s e s t u d i e s and aerodynamic s c a l i n g a n a l y s i s . The proposals have been e v a l u a t e d and a c o n t r a c t o r t e n t a t i v e l y s e l e c t e d . �N e g o t i a t i o n w i t h t h e p r o s p e c t i v e c o n t r a c t o r should t a k e p l a c e soon. I f t h e p r o s p e c t i v e c o n t r a c t o r a g r e e s t o meet c e r t a i n c o n d i t i o n s added t o t h e proposed development, work should begin on t h e anemometer w i t h i n a few weeks . 4. A n a l y s i s of Atmospheric Turbulence from FPS-16 ~ a d a r l ~ i m s p h e r e Data (NASA C o n t r a c t NAS8-21331) The purpose of t h i s c o n t r a c t w i t h Meteorology Research, I n c . , i n i t i a t e d i n February 1968, i s t o determine t h e c a p a b i l i t y of t h e FPS-16 r a d a r l ~ i m s p h e r esystem t o d e t e c t c l e a r a i r t u r b u l e n c e (CAT). The cont r a c t o r has r e c e i v e d a i r c r a f t and Jimsphere d a t a f o r e l e v e n c a s e s of CAT observed over Wallops I s l a n d d u r i n g December 1967. I n a d d i t i o n , we w i l l r e c e i v e seven c a s e s of t u r b u l e n c e f o r t h e month of February 1968 when t h e d a t a become a v a i l a b l e . I f i t is demonstrated t h a t t h e FPS-16 r a d a r l ~ i m s p h e r ewind s e n s i n g system i s capable of d e t e c t i n g CAT, t h e n i t w i l l b e p o s s i b l e t o develop a g l o b a l CAT climatology. This informat i o n i s u r g e n t l y needed by v a r i o u s government a g e n c i e s , t h e armed f o r c e s , and commercial a i r l i n e s . A t t h e p r e s e n t time, CAT d a t a a r e o b t a i n e d by instrumented a i r c r a f t , which a r e expensive t o o p e r a t e and m a i n t a i n and a r e s u b j e c t t o o p e r a t i o n a l c o n s t r a i n t s . These f a c t o r s a c c o r d i n g l y l i m i t t h e q u a n t i t y of d a t a a v a i l a b l e t o perform s t a t i s t i c a l a n a l y s e s . On t h e o t h e r hand, t h e Jimsphere wind d e t e c t o r is r e l a t i v e l y cheap, and t h e r e a r e v i r t u a l l y no o p e r a t i o n a l c o n s t r a i n t s . This means t h a t a l a r g e q u a n t i t y of d a t a can be o b t a i n e d i n a s h o r t p e r i o d of time and t h a t a CAT c l i m a t o l o g y could be developed w i t h i n t h e n e x t f i v e y e a r s i f t h e c u r r e n t s t u d i e s show t h a t adequate e n g i n e e r i n g d a t a may be d e r i v e d from t h e system. 5. Real Time Anemometer Data t o HOSC Real-time wind v e l o c i t y p r o f i l e d a t a w i l l be t r a n s m i t t e d t o HOSC f o r a l l f u t u r e S a t u r n launches. This i n c l u d e s d a t a from t h e two r e f e r e n c e h e i g h t anemometers a t t h e 60-foot (18.3m) l e v e l and winds from a t o p t h e LUTS o r s e r v i c e s t r u c t u r e , depending on t h e launch pad b e i n g used. Such d a t a w i l l b e r e c e i v e d from LC37B, 39A, and 39B, b u t n o t from LC34 u n l e s s i t i s decided t h a t LC34 w i l l be used t o launch f u t u r e Saturn vehicles. 6. F i n a l Report on C o n t r a c t NAS8-21138 w i t h NAR The f i n a l r e p o r t , "Wind F i e l d A n a l y s i s f o r C a n t i l e v e r Loads," has been r e c e i v e d from North American Rockwell C o r p o r a t i o n , Downey, C a l i f o r n i a ; Ben U j i h a r a was t h e p r i n c i p a l i n v e s t i g a t o r . The r e p o r t Wind d a t a w i l l be published a s a NASA CR and d i s t r i b u t e d by R-AERO-Y. from t h e 500F t e s t s were used t o i l l u s t r a t e pad wind-flow c o n d i t i o n s and flow a b o u t t h e ~ ~ T I V e h i c l e . �7. Reduction of Meteorological Tower Data by NWRC M r . John Kaufman (R-AERO-YE/MSFC/NASA), M r . Paul Harness (R-COMP-RRP/MSFc/NASA), and M r . L e s t e r Keene (IN-DAT-P/KSC/NASA) v i s i t e d t h e N a t i o n a l Weather Records Center (NWRC) of ESSA a t A s h e v i l l e , North C a r o l i n a , on February 8 , 1968, t o d i s c u s s d a t a r e d u c t i o n techniques and problems r e l a t e d t o reducing NASA's 150-meter m e t e o r o l o g i c a l tower d a t a . NWRC is r e s p o n s i b l e f o r reducing t h e d a t a t h a t are recorded on paper s t r i p c h a r t s , a c c o r d i n g t o t h e scope of work under Government Order No. H-13207A. S i x t e e n months (December 1965 through March 1967) of t h e s e m e t e o r o l o g i c a l tower d a t a have been reduced and made a v a i l a b l e t o R-AERO-Y f o r formal a n a l y s e s . Although t h e d a t a - r e c o r d i n g t e c h n i q u e s a t t h e tower f a c i l i t y have g r e a t l y improved s i n c e t h e f i r s t few weeks of i t s o p e r a t i o n , v a r i o u s d a t a - r e c o r d i n g problems s t i l l e x i s t . With t h e c o o p e r a t i o n of KSC (Mr. Keene), R-AERO-Y/MSFC,and NWRC p e r s o n n e l , t h e s e problems should be e l i m i n a t e d . 8. Recent Reports on NASA's 150 m M e t e o r o l o g i c a l Tower F a c i l i t y Two r e p o r t s have r e c e n t l y been made a v a i l a b l e on NASA'S 150 m M e t e o r o l o g i c a l Tower l o c a t e d a t KSC, F l o r i d a : (1) GP-465 e n t i t l e d , "Meteorological Measuring and Recording Equipment D e s c r i p t i o n , C a l i b r a t i o n and Maintenance Procedures f o r NASA's 150 m M e t e o r o l o g i c a l Tower F a c i l i t y , Kennedy Space C e n t e r , F l o r i d a , " dated February 1 5 , 1968; and ( 2 ) NASA TM X-53699 e n t i t l e d , "NASA's 150-Meter M e t e o r o l o g i c a l Tower Located a t t h e Kennedy Space Center, F l o r i d a , " d a t e d J a n u a r y 1958 (Revised) . I 1 Copies of t h e s e r e p o r t s may b e o b t a i n e d by c o n t a c t i n g R-AERO-YE, Attn: John W. Kaufman (876-6392). B. Space Environment Branch 1. The continued in-depth a n a l y s e s of t h e e i g h t thermosphere probes launched d u r i n g t h e f i r s t q u a r t e r of 1967 has g e n e r a t e d a d d i t i o n a l i n f o r m a t i o n a b o u t t h e d i u r n a l v a r i a t i o n of b o t h t h e n e u t r a l and charged p o r t i o n s of t h e e a r t h ' s upper atmosphere i n t h e "ignorosphere" (90-140 km) r e g i o n . This i n f o r m a t i o n i s being combined w i t h t h e r e s u l t s of c u r r e n t s t u d i e s t o deve op improved 10.7 cm s o l a r f l u x and geomagnetic index (Kp) p r e d i c t i o n s i n t h e development of a r e f i n e d model of t h e upper atmosphere. 2. I n e s t a b 1 i s h i n g t h e o r b i t a l n a t u r a l environment c r i t e r i a f o r t h e AAP-1 and -2 m i s s i o n s , i t became e v i d e n t t h a t a d e t a i l e d time prof i l e o f t h e d e n s i t y that could be expected would be of v a l u e i n c u r r e n t v e h i c l e motion and torque accumulation a n a l y s e s . A time p r o f i l e i s being developed using ~ a c c h i a ' s " S t a t i c D i f f u s i o n Model" w i t h 10.7 cm s o l a r f l u x and Kp i n d i c e s that e x i s t e d i n October 1960, a time p e r i o d �d u r i n g which t h e s o l a r a c t i v i t y was a t t h e same l e v e l as t h a t p r e d i c t e d f o r t h e AAP-1 and - 2 m i s s i o n s using c u r r e n t p r e d i c t i o n techniques and C u r r e n t p r e d i c t i o n techniques cannot provide t h e miss i o n guide1 i n e s amount of d e t a i l r e q u i r e d t o c o n s t r u c t t h i s p r o f i l e . Work has begun on a s i m i l a r p r o f i l e f o r t h e 56-day m i s s i o n of AAP-3 and -4. . 3. A p r e l i m i n a r y d r a f t of t h e " O r b i t a l Environment C r i t e r i a monograph b e i n g produced f o r OART has been completed. The document c o n t a i n s a b r i e f review of d a t a a c q u i s i t i o n and modeling t e c h n i q u e s , a s w e l l as a d e t a i l e d d i s c u s s i o n of ~ a c c h i a ' s" S t a t i c D i f f u s i o n Model" and how i t should be a p p l i e d i n v e h i c l e development programs and a s s o c i a t e d ana 1ys e s . 4. P r e d i c t e d v a l u e s of n a t u r a l environmental parameters a t o r b i t a l a l t i t u d e s f o r t h e 1972-1975 time frame were provided t o t h e Advanced Systems O f f i c e f o r use i n t h e i r S a t u r n IB and S a t u r n V launched workshop analyses. 5 . Work was begun on e s t a b l i s h i n g a n o r b i t a l d e t e r m i n a t i o n program t o b e used i n f u t u r e a n a l y s e s f o r d e r i v i n g atmospheric d e n s i t y v a l u e s from t h e o r b i t a l decay of s a t e l l i t e s . These v a l u e s w i l l t h e n be used i n c o n j u n c t i o n w i t h t h e r e s u l t s of our rocket-launched probe measurements i n c o n s t r u c t i n g a r e f i n e d model of t h e upper atmosphere. 6. A major r e v i s i o n t o TM X-53521, "Space Environment C r i t e r i a G u i d e l i n e s f o r Use i n Space Vehicle Development, 1967 Revision," i s This r e v i s i o n w i l l be a j o i n t AERO-SSL e f f o r t w i t h t e c h n i c a l underway. i n f o r m a t i o n on e l e c t r o m a g n e t i c r a d i a t i o n , r a d i a t i o n , and meteoroids being provided by SSL. The r e v i s i o n should be published t h i s summer. 7. The h i s t o r i c a l Geophysical Data Tape has been updated. Master f i l e No. 2 now c o n t a i n s d a i l y , 27-, 54-, and 81-day running mean, monthly mean, and 12-monthly mean v a l u e s of b o t h t h e 10.7 cm s o l a r f l u x and t h e Zurich s u n s p o t numbers, a s w e l l a s t h r e e h o u r l y e q u i v a l e n t p l a n e t a r y amplitude, a p , v a l u e s converted from published geomagnetic a c t i v i t y , Kp, v a l u e s . Data on t h i s t a p e a r e l i s t e d by modified J u l i a n days, day of y e a r , and d a t e . 8. Work i s c o n t i n u i n g on d e f i n i n g a compatible complement of experiments f o r t h e Odyssey p r o j e c t . S e v e r a l i t e r a t i o n s have developed a s e t of i n s t r u m e n t a t i o n t h a t w i l l provide measurements of t h e composit i o n and d e n s i t y of t h e n e u t r a l atmosphere, t h e thermal and momentum accommodation c o e f f i c i e n t s , t h e f r e e - and n e a r - f r e e d r a g c o e f f i c i e n t s , and i n f o r m a t i o n concerning t h e shape of t h e e a r t h . �9. Work i s c o n t i n u i n g on r e f i n i n g models of t h e atmospheres of Venus, Mars, and Mercury f o r i n c l u s i o n i n t h e f o u r t h coming r e v i s i o n t o TM X-53521. A m a j o r i t y of t h e e f f o r t i s on Venus u s i n g t h e new Mariner and Venera d a t a o b t a i n e d from the open l i t e r a t u r e . 10. S e v e r a l s t a t i c t e s t f i r i n g s have been monitored by t h e ionos p h e r i c phase p a t h sounding network. One problem now r a p i d l y becoming c r i t i c a l is t h e backlog of unreduced d a t a which a r e accumulating. Although t h e A i r Force i n Rome, New York, i s reducing t h e d a t a t a p e s a t no c o s t t o NASA, t h e p r i o r i t y g i v e n t o t h i s d a t a r e d u c t i o n i s s o low, t h e r e i s seldom s u f f i c i e n t computer time t o reduce t h e d a t a . A t r i p i s planned t o Rome, New York, and t h e Avco-Boston p l a n t i n t h e n e a r f u t u r e t o t r y t o d e a l w i t h t h e problem. The MSFC swept frequency ionos onde i s now o p e r a t i o n a l and is providing ionograms b e f o r e , d u r i n g , and a f t e r s t a t i c t e s t f i r i n g s . 11. An u n s o l i c i t e d p r o p o s a l has been r e c e i v e d from D r . J . B. B l i z a r d of t h e Denver Research I n s t i t u t e t o update and extend h e r 120day s o l a r f l a r e p r e d i c t i o n technique. Funding i s being sought f o r t h i s work. C. ~ e r r e tsr i a l Environment Branch 1. The f o l l o w i n g o f f i c e memos have been i s s u e d : a . R-AERO-YT-11-68, "A S t a t i s t i c a l Anal ys i s of t h e 'Earth' s Atmosphere f o r a S e l e c t e d Geographic Area," d a t e d February 9 , 1968. b . R-AERO-YT-17-68, "Ground Wind Risk Levels f o r Apollo 6 (AS-502) f o r One-Hour Exposure f o r Each Hour During March and A p r i l , " d a t e d March 6 , 1968. c . R-AERO-YT-18-68, d a t e d March 6, 1968. "Additional Atmospheric Moisture Values , I 1 d . R-AERO-YT-25,68, "Some Peak Ground Wind R i s k Levels f o r Apollo 6 (AS-502) f o r One-Hour Exposure d u r i n g MSS Removal," dated March 25, 1968. e . R-AERO-YT-27-68, "Standard D e v i a t i o n s of P r e s s u r e , Temperat u r e , and Density w i t h Respect t o t h e P a t r i c k Reference Atmosphere 1963, t o 120 Krn A l t i t u d e , " dated A p r i l 4, 1968. A c o n t r i b u t i o n t o t h e Research Achievements Review, Volume 11, Report No. 10, "A S t a t i s t i c a l A n a l y s i s of Winds f o r Aerospace Vehicle Design, Mission Planning, and Operations , I 1 p r e s e n t s s e v e r a l s t a t i s t i c a l concepts w i t h examples. �2. Contracts a. A l l i e d Research A s s o c i a t e s , I n c . , Concord, Mass. ( C o n t r a c t NAS8-21040) The f i n a l r e p o r t and t h e b a s i c s t a t i s t i c s f o r t h e World-Wide Cloud Cover Study f o r AAP m i s s i o n a n a l y s i s have been d e l i v e r e d . Computer programs t o e n a b l e u s t o u s e t h e cloud s t a t i s t i c s i n m i s s i o n s i m u l a t i o n s t u d i e s a r e b e i n g developed in-house. b. U n i v e r s i t y of Georgia, Department of S t a t i s t i c s ( C o n t r a c t NAS8-11175) We have r e c e i v e d a n i n t e r i m t e c h n i c a l r e p o r t e n t i t l e d "The Use of P r i o r I n f o r m a t i o n i n Determining Confidence I n t e r v a l s on Success P r o b a b i l i t i e s , " by F. R u s s e l l Helm. c. Lockheed-Huntsville The c o n t r a c t o r compared t h e f o l l o w i n g t h r e e methods t o determine t h e parameters of F i s h e r - T i p p e t t Type I d i s t r i b u t i o n from a s t a t i s t i c a l sample of extremes: (1) Gumbells method of moments, ( 2 ) ~ i e b l e i n ' smethod, and (3) method of maximum l i k e l i h o o d . The a c c u r a c y and e f f i c i e n c y of t h e s e methods i n e s t i m a t i n g t h e parameters depend on sample s i z e and t h e parameter. A computer program was devised which w i l l be a u s e f u l t o o l i n t h e a n a l y s i s of extreme v a l u e s t a t i s t i c s . This o f f i c e has a requirement f o r f i t t i n g t h i s d i s t r i b u t i o n f u n c t i o n t o many samples. 3. In-House Tasks a . Data a r e being produced t o b e t t e r d e f i n e t h e p r o b a b i l i t y of e a s t e r l y winds f o r t h e AS-205 and AS-503 e a r l y a b o r t problems. b . Ground Wind I n v e s t i g a t i o n s Considerable e f f o r t has been devoted t o e s t a b 1 i s h i n g u n i f i e d exposure p e r i o d p r o b a b i l i t i e s f o r ground winds. An e x t e n s i o n of extreme v a l u e s t a t i s t i c a l techniques proves t o produce cons i s t e n t r e s u l t s f o r t h e r i s k of exceeding wind peak speed v a l u e s . The r e s u l t s of t h i s i n v e s t i g a t i o n a r e u r g e n t l y needed by KSC f o r r e d e s i g n of LUT p l a t f o r m s , and by MSFC f o r o p e r a t i o n s and m i s s i o n planning. �c . S e v e r a l i n v e s t i g a t i o n s have been completed and the following r e p o r t s a r e being prepared: (1) Thunderstorm P e r s i s t e n c e f o r Cape Kennedy. (2) A u t o c o r r e l a t i o n s f o r Winds A l o f t over Cape Kennedy. (3) Winds A l o f t Exceedance P r o b a b i l i t i e s f o r Mission Planning. ( 4 ) Winds A l o f t C o n d i t i o n a l P r o b a b i l i t i e s f o r Mission Planning. IV. (5) Exceedance P r o b a b i l i t i e s f o r Peak Ground Winds. (6) E s t i m a t i o n s i n Extreme Values. PROJECTS OFFICE 1. S a t u r n I B and V EDS a. High Q Abort Problem For s e v e r a l months MSFC has been a n a l y z i n g t h e problem of i n a b i l i t y t o w i t h s t a n d t h e l o a d s d u r i n g a l l engine shutdown f o r a b o r t d u r i n g t h e max q r e g i o n (60 t o 110 seconds) f o r S a t u r n I B and V. During a b o r t , t h e compression l o a d s being a p p l i e d by t h e engine t h r u s t a r e suddenly l o s t , r e s u l t i n g i n i n c r e a s i n g c r i t i c a l t e n s i o n l o a d s . Under c e r t a i n m a l f u n c t i o n s t h e L / V exceeds t h e s t r u c t u r a l c a p a b i l i t y i n l e s s than - 5 seconds a f t e r a b o r t i n i t i a t i o n . I t is p o i n t e d o u t t h a t t h e CM/SM p h y s i c a l s e p a r a t i o n occurs a b o u t . 2 seconds a f t e r a b o r t i n i t i a t i o n . MSFC has been a t t e m p t i n g t o meet a n MSC s p e c i f i e d c r i t e r i a of a b o u t a 300-foot s e p a r a t i o n d i s t a n c e between t h e a b o r t CM and L / V b e f o r e breakup. This r e q u i r e d a t l e a s t 2 t o 3 seconds s e p a r a t i o n time and was t o a s s u r e < 6 . 1 p s i o v e r p r e s s u r e on t h e CM a f t e r a n e x p l o s i o n , which was assumed t o occur a t L/V breakup. During t h e l a s t Crew S a f e t y Panel Meeting, MSC pres e n t e d some p r e l i m i n a r y r e s u l t s of t h e l a t e s t e x p l o s i o n s t u d i e s which i n d i c a t e d t h a t t h e r e q u i r e d s e p a r a t i o n d i s t a n c e f o r S a t u r n I B was n o t s o g r e a t a s e a r l i e r s p e c i f i e d . The most i n t e r e s t i n g and important a s p e c t of t h e r e v i s e d d a t a is t h a t , f o r a l t i t u d e s corresponding t o and above t h e max q r e g i o n where t h e problem e x i s t s , t h e o v e r p r e s s u r e c r i t e r i a < 6 . 1 p s i can b e met w i t h v i r t u a l l y z e r o s e p a r a t i o n d i s t a n c e r e q u i r e d between t h e a b o r t e d CM and L / V b e f o r e L / V breakup. This means t h a t t h e S a t u r n I B problem has disappeared based on t h e r e v i s e d e x p l o s i o n c r i t e r i a d a t a . I n d i s c u s s i o n s w i t h MSC, they s t a t e d t h a t t h e S a t u r n V e x p l o s i o n s t u d i e s a r e n o t complete. However, they f e e l t h a t t h e S a t u r n V r e s u l t s w i l l be s i m i l a r t o S a t u r n IB r e s u l t s . The r e c e n t r e s u l t s have been p r e s e n t e d t o b o t h S a t u r n I B and V Program Managers, and t h e small r i s k involved w i t h max q a b o r t s has been a c c e p t e d . �b. S-IC Control Engine Out S / C Breakup Problem Analysis conducted on AS-504 v e h i c l e i n d i c a t e s t h a t l o a d s a t t h e CM/SM j o i n t w i l l exceed t h e c a p a b i l i t y a s t h e r e s u l t of a s i n g l e S-IC e n g i n e - o u t . The bending moment a t t h i s j o i n t i s approximately 30 p e r c e n t h i g h e r than t h e maximum l o a d s p r e d i c t e d f o r AS-503 ( 5 . 3 x 10" i n - l b s f o r AS-503 compared t o 6 . 9 x l o 6 i n - l b s f o r AS-504 a t SIC s t a t i o n 1010). This bending moment i n c r e a s e i s due t o t h e f o l l o w i n g d i f f e r e n c e s between t h e AS-503 and AS-504: (1) i n c r e a s e d payload weight (95 K f o r AS-503; 100 K f o r AS-504); (2) i n c r e a s e d p r o p e l l a n t l o a d i n g (255,000 pounds i n S-IC and 40,000 pounds i n S - I 1 s t a g e ) ; and approximately 14 p e r c e n t . This (3) decreased S - I 1 s t a g e s t i f f n e s s c o n d i t i o n i s n o t s i g n i f i c a n t l y a f f e c t e d by winds. Data f o r t h e s e a n a l y s e s have been s e n t t o MSC f o r more d e t a i l e d s t r u c t u r a l load s t u d i e s . This problem i s s e v e r e i n s o f a r a s i t w i l l n o t a l l o w warning time f o r EDS t o a l l o w s a f e a b o r t . These d a t a have been p r e s e n t e d t o D r . Rudolph, S a t u r n V Program Manager, and t o D r . Rees a t Downey, C a l i f o r n i a . A t t h e meeting w i t h D r . Rees, i t was concluded t h a t a S I C beef-up t o w i t h s t a n d l o a d s of 6.9 x l o 6 i n - l b s (maximum p r e d i c t e d l o a d s f o r 504 a t S/C s t a t i o n 1010) was n o t f e a s i b l e . I n a d d i t i o n , i t was f e l t t h a t l o a d s of t h i s magnitude would probably cause problems i n o t h e r p o r t i o n s of t h e S / C such a s SM o r LM, a s w e l l a s CM/SM j o i n t . The problem w i l l be s t u d i e d by MSFC i n v e s t i g a t i n g methods of reducing l o a d s , and MSC i n v e s t i g a t i n g methods of i n c r e a s i n g S / C load c a p a b i l i t y . The f o l l o w i n g a c t i o n items a r e i n p r o g r e s s : (1) MSFC w i l l r e - a n a l y z e F-1 engine-out malfunct i o n , from t h e s t a n d p o i n t s of component r e l i a b i l i t y and engine t h r u s t decay c h a r a c t e r i s t i c s following m a l f u n c t i o n s (SIC l o a d s a r e v e r y s e n s i t i v e t o t h r u s t decay r a t e ) ; (2) MSFC w i l l i n v e s t i g a t e a l l a s p e c t s of c a n t i n g t h e F-1 outboard c o n t r o l e n g i n e s , w i t h e i t h e r a n e l e c t r i c a l b i a s o r mechanical f i x , t o h e l p a l l e v i a t e t h e l o a d s f o r S-IC c o n t r o l engine o u t . (A 2 1 / 2 degree c a n t w i l l be a n a l y z e d , s i n c e t h i s i s approximately t h e l i m i t f o r e l e c t r i c a l b i a s , and being a b l e t o m a i n t a i n c o n t r o l f o r nominal f l i g h t ; t h i s w i l l reduce t h e S / C l o a d i n g t o 5 . 8 x 10" i n - l b s f o r one S-IC engine o u t . ) ( 3 ) Msc/NAR w i l l determine p r e s e n t S / C c a p a b i l i t y f o r s i n g l e F-1 c o n t r o l engine o u t , and beef-up n e c e s s a r y t o w i t h s t a n d l o a d s of 6 . 0 x 10" i n - l b s bending moment; and (4) MSC/NARw i l l t e s t S / C i n August 1968. - The S a t u r n I B AS-206/LM-2 m i s s i o n which was planned a s backup t o AS-204/L,M-I has been c a n c e l l e d . The AS-206 v e h i c l e w i l l now be used, i f r e q u i r e d f o r t h e Apollo Program, w i t h AS-207 f o r t h e S a t u r n I B d u a l miss i o n . A l l AS-206/CM-2 s t u d i e s have been c a n c e l l e d e x c e p t f o r t h o s e v e r y n e a r completion. These s t u d i e s a r e b e i n g documented f o r f u t u r e reference. �3. S - I 1 Spray Foam I n s u l a t i o n F u r t h e r t e s t s of t h e S - I 1 S t a g e Spray Foam I n s u l a t i o n were conducted on t h e X-15 d u r i n g March. The i n s u l a t i o n samples were mounted on t h e upper speed b r a k e , i n s t r u m e n t e d , and flown over t h e AS-504 max h e a t i n g t r a j e c t o r y . The temperatures t o b e a t t a i n e d on t h e i n s u l a t i o n was t h e p r e d i c t e d smooth w a l l temperature of 530" F. The sample on t h e s t a r b o a r d speed brake was t o be photographed w i t h a camera mounted i n t h e s t a r b o a r d wing t i p ; however, t h e camera f a i l e d a f t e r exposing 2 f e e t of f i l m . The d a t a a r e being analyzed t o determine t h e temperatures a t t a i n e d and t h e e f f e c t i v e n e s s of t h e i n s u l a t i o n . The r e s u l t s of t h i s a n a l y s i s a r e expected i n e a r l y A p r i l . 4. AAP C l u s t e r The a n a l y s i s of t h e f i r s t c l u s t e r m i s s i o n has continued, and s p e c i f i c a l l y , t h e impact of t h e ML-13A schedule on t h e c l u s t e r r e q u i r e ments was p r e s e n t e d t o D r . Mueller a t t h e LM/ATMTask Team Review i n Washington, D. C . on March 15 and 16, 1968. R e s u l t s of t h i s meeting i n d i c a t e d t h e d e s i r a b i l i t y , s u b s e q u e n t l y approved, f o r t h e LM/ATM unmanned rendezvous and remote manual docking. I n t e r c e n t e r a c t i v i t i e s on m i s s i o n r e q u i r e m e n t s , guidance, performance, dynamics, and o t h e r a r e a s have been coordinated by Mission Requirements Panel Meetings on February 20 and 21, 1968, and March 28 and 29, 1968. �V. ASTRODYNAMICS AND GUIDANCE THEORY DIVISION A. Guidance Theory Branch 1. Support C o n t r a c t S t u d i e s a. General I n t e r p l a n e t a r y S t u d i e s Work i s c o n t i n u i n g on program development f o r t h e FPR s t u d y u s i n g load r e l i e f c o n t r o l . Modules f o r computing quaternion'' r a t e s from i n p u t gimbal a n g l e r a t e s and f o r computing gimbal a n g l e r a t e s from i n p u t q u a t e r n i o n r a t e s have been f o r m a l i z e d , programmed and checked o u t f o r F o r t r a n e r r o r s on t h e Univac 1107 computer. A t e c h n i c a l n o t e e n t i t l e d , "Comparison of S e v e r a l Midcourse Guidance Schemes" has been completed. b. Optimal Guidance Study The problem of o b t a i n i n g good i n i t i a l approximations f o r t h e Lagrange m u l t i p l i e r s has e s s e n t i a l l y been s o l v e d . The u s e of t h e impulsive approximations a s s t a r t i n g v a l u e s i n t h e Newton-Raphson i t e r a t i o n has l e d t o convergence i n every case a t t e m p t e d . The p a r t i c u l a r problems examined were two-dimensional a s c e n t - t o - c i r c u l a r - o r b i t s w i t h r a d i i ranging from 200 t o 1100 n a u t i c a l m i l e s . Bang-bang c o n t r o l was implemented and t h e t r a n s f e r t r a j e c t o r i e s were t y p i c a l l y s h o r t t h r u s t / long coas t / s hor t t h r u s t . It i s i n t e r e s t i n g t o n o t e t h e l i n e a r r a t e of convergence of t h e Newton-Raphson i t e r a t i o n . Empirical checks by computational means i n d i c a t e t h a t t h e m a t r i x of p a r t i a l d e r i v a t i v e s of t h e t e r m i n a l f u n c t i o n s w i t h r e s p e c t t o the unknown m u l t i p l i e r s and f i n a l time becomes s i n g u l a r a t t h e c o r r e c t v a l u e s of t h e m u l t i p l i e r s and f i n a l time. This i d e a i s being i n v e s t i g a t e d a n a l y t i c a l l y . Because of t h e slow l i n e a r convergence of t h e Newton-Raphson i t e r a t i o n on t h e s e p a r t i c u l a r problems, v a r i o u s e x t r a p o l a t i o n a l g o r i t h m s a r e b e i n g implemented. - >'c The t r a n s f o r m a t i o n of c o o r d i n a t e s through t h e commonly used E u l e r a n g l e s can be r e p l a c e d by a t r a n s f o r m a t i o n i n v o l v i n g f o u r E u l e r parameters i n which t r i g o n o m e t r i c f u n c t i o n s do n o t e x p l i c i t l y a p p e a r . These E u l e r parameters may be regarded a s the components of a q u a t e r n i o n . The q u a t e r n i o n f o r m u l a t i o n i s h i g h l y e f f i c i e n t f o r computing purposes. �I n v e s t i g a t i o n of i n t e g r a t i o n techniques has continued. l i m i n a r y i n v e s t i g a t i o n of t h e Romberg i n t e g r a t i o n method has r e v e a l e d t h a t Romberg i s n o t s o s a t i s f a c t o r y a s e q u i v a l e n t Runge-Kutta formula, The flaw i n Romberg methods i s due t o t h e p r o h i b i t i v e number of d e r i v ~ t i v e e v a l u a t i o n s r e q u i r e d . For example, a t h i r d o r d e r Romberg (using ~ y s t r o m ' s second o r d e r method) r e q u i r e s t h r e e e v a l u a t i o n s of t h e d e r i v a t i v e p e r i n t e g r a t i o n s t e p , w h i l e t y p i c a l Runge-Kutta methods r e q u i r e d two e v a l u a t i o n s . For h i g h e r o r d e r methods, Romberg i s even more punishing: a n i n t h - o r d e r Romberg r e q u i r e s 31 e v a l u a t i o n s , RungeK u t t a t e n t h - o r d e r , o n l y 12. However, t h e s t e p - s i z e c o n t r o l f e a t u r e of Romberg may be u s e f u l f o r low o r d e r formulas. c. Quas i-Optimal Guidance Study T r a j e c t o r i e s t e r m i n a t i n g i n v a r i o u s e l l i p t i c a l o r b i t s were g e n e r a t e d u s i n g QUOTA a s a guidance technique. The r e s u l t s a r e now b e i l compared w i t h COV and IGM r e s u l t s . A survey of t r a j e c t o r i e s w a s general v a r y i n g t h e frequency of update time f o r t h e guidance scheme (QUOTA). Also, a s t u d y of a l t e r n a t e m i s s i o n p o s s i b i l i t i e s f o r t h e (100 n.mi. x Sync) a l t i t u d e e l l i p t i c a l o r b i t has been i n i t i a t e d . A s t u d y of QUOTA a p p l i e d t o h y p e r b o l i c - t o - e l l i p t i c deboos t p o i n t e d o u t t h e need f o r a n a l y t i c c o n t i n u a t i o n i n e v a l u a t i n g t h e s t a t e v a r i a b l e i n t e g r a l s f o r QUOTA. A f t e r t h i s m o d i f i c a t i o n , t h e r e s u l t s have been v e r y s a t i s f a c t o r y . 2. Contracts a. Lockheed - Voyager Terminal Guidance A n a l y s i s The examination of e r r o r s e n s i t i v i t y a s a f u n c t i o n of t e r m i n a l geometry i s p r o g r e s s i n g . During t h e l a s t r e p o r t i n g p e r i o d , t h e c a p a b i l i t y t o a c c o u n t f o r c o r r e l a t e d n a v i g a t i o n a l e r r o r s was included i n t h e program. A s ix-dimens i o n a l c o v a r i a n c e m a t r i x , which i s a f u n c t i o n of t h e n a v i g a t i o n a c c u r a c y p o s t u l a t e d , is i n p u t i n o r d e r t o c o r r e l a t e t h e p o s i t i o n and v e l o c i t y e r r o r a t i g n i t i o n . It was found t h a t the parameter a ( t h e a n g l e between t h e t h r u s t v e c t o r and t h e v e l o c i t y v e c t o r a t i g n i t i o n ) has a major e f f e c t on t h e magnitude of many of the o r b i t a l e r r o r p a r t i a l d e r i v a t i v e s . b. Lockheed - Rendezvous Guidance Two r e p o r t s have been submitted t h i s period: "The Minimizat i o n of t h e Fuel Consumption i n t h e F i r s t Burn of a P l a n a r Two-Burn Rendezvous" and "Extens i o n of t h e Dual-Phase Plane Terminal Guidance The f i r s t r e p o r t shows t h a t t h e Method t o Long Terminal Burn Times." f i r s t burn i t e r a t i o n scheme is s u p e r l i n e a r , and t h e second extends t h e dual-phase plane a n a l y s i s of t h e second burn t o i n c l u d e f i r s t o r d e r gravitational effects. �3. In-House S t u d i e s a , A paper e n t i t l e d "A Method of T r a j e c t o r y A n a l y s i s w i t h Multimission C a p a b i l i t y and Guidance Application" has been accepted f o r p r e s e n t a t i o n a t t h e 1968 AIAA Guidance, C o n t r o l and F l i g h t Dynamics Conference. The three-dimensional o p t i m i z a t i o n deck programmed f o r t h e CDC-3200 performs q u i t e w e l l , and has a u t o m a t i c a l l y found t h e optimal time f o r a s i m u l a t e d m i x t u r e r a t i o s h i f t of a two s t a g e v e h i c l e , t h e optimal launch azimuth of a s i m i l a r v e h i c l e s , and t h e optimal c o a s t time f o r a v e h i c l e t r a n s f e r r i n g between 100 n.m. c i r c u l a r o r b i t and a coplanar 200 n.m. c i r c u l a r o r b i t . b. The C a r t e s i a n c o o r d i n a t e , completely g e n e r a l , closed-form s o l u t i o n of t h e two-body s t a t e and s t a t e t r a n s i t i o n m a t r i c e s have been used t o connect two p o s i t i o n v e c t o r s w i t h a c o n i c i n a f i x e d i n t e r v a l of time. Then a 3 x 3 m a t r i x i s developed which m u l t i p l i e s e r r o r s i n t h e p o s i t i o n v e c t o r t o y i e l d t h e c o r r e c t i o n i n t h e v e l o c i t y v e c t o r f o r midc o u r s e guidance. This m a t r i x can be computed i n c l o s e d form a t any time i n t h e i n t e r v a l of i n i t i a l time t o f i n a l time. F u r t h e r e f f o r t s a r e needed t o p a t c h c o n i c s a t b o t h ends o r t o n u m e r i c a l l y i n t e g r a t e a t t h e two ends s o t h a t t h e e f f e c t s of t h e launch p l a n e t and t h e t a r g e t p l a n e t can b e included i n t h e computations. An e x t e n s i o n of t h i s work l e a d s t o c l o s e d form s o l u t i o n s f o r t h e primer v e c t o r ( o r t h e Lagrangian m u l t i p l i e r s ) which can be used t o minimize t h e V, o r t h e AV needed t o accomp l i s h rendezvous ( i n s t e a d of j u s t matching t h e p o s i t i o n v e c t o r s ) . A s was mentioned i n t h e previous p r o g r e s s r e p o r t , t h e closed-form s o l u t i o n s f o r t h e m u l t i p l i e r s and a s s o c i a t e d t r a n s i t i o n m a t r i c e s a r e a v a i l a b l e and d u r i n g t h i s r e p o r t i n g p e r i o d t h e f o r m u l a t i o n of t h e optimal two-impulse rendezvous u s i n g t h e closed-form s o l u t i o n s has been completed. A computer program u s i n g t h i s f o r m u l a t i o n i s y e t t o be developed. c . An a p p l i c a t i o n of t h e techniques developed i n t h e f i n a l r e p o r t f o r c o n t r a c t NAS8-20269 (Optimal Control Theory w i t h A p p l i c a t i o n s t o Optimal T r a j e c t o r y and Guidance Problems by Charles M. Chambers) has been formulated f o r u s e as a computer program. When t h e computer programming is completed , t h i s method can be compared w i t h o t h e r methods f o r s o l v i n g boundary v a l u e problems a s s o c i a t e d w i t h optimal guidance. B. O p t i m i z a t i o n Theory Branch 1. A p p l i c a t i o n of F u n c t i o n a l A n a l y s i s t o O p t i m i z a t i o n Theory Research i s now underway i n t h e a r e a of f u n c t i o n a l a n a l y s i s . The o b j e c t is t o survey some of t h e e x i s t i n g l i t e r a t u r e t o determine whether advances i n t h e f i e l d have u s e f u l a p p l i c a t i o n t o problems i n optimization theory. �2. Research i n Control Moment Gyros Momentum Management Work was i n i t i a t e d on a problem i n h e r e n t i n t h e use of c o n t r o ~ moment gyros f o r a t t i t u d e c o n t r o l of a s p a c e v e h i c l e , i . e . , l o s s of t h e a b i l i t y t o provide a needed c o n t r o l torque because of t h e o r i e n t a t i o n of t h e a n g u l a r momentum v e c t o r s of t h e g y r o s . The s t u d y w i l l u s e optimal c o n t r o l t h e o r y t o f i n d a n optimal s o l u t i o n t o t h e problem e i t h e r through m o d i f i c a t i o n of t h e e x i s t i n g scheme o r development of a new concept. 3. A n a l y t i c S o l u t i o n of T r a j e c t o r i e s P e r t u r b e d by P l a n a r Force The NASA Technical Note d e a l i n g w i t h t h e motion of a s a t e l l i t e under t h e combined i n f l u e n c e of K e p l e r i a n and p l a n a r f o r c e f i e l d s has been prepared. P r e l i m i n a r y d r a f t p u b l i c a t i o n s a r e expected soon. 4 . I n i t i a l work has been undertaken on a problem which c o n s i d e r s l a r g e s c a l e d e f l e c t i o n s of ropes and c a b l e s . This s t u d y should have important a p p l i c a t i o n s t o t e t h e r s between s a t e l l i t e s , t e t h e r s f o r a s t r o n a u t s t o a s a t e l l i t e , and p o s s i b l y even t o t h e problem of a s t a t i o n a r y s a t e l l i t e a t t a c h e d t o t h e s u r f a c e of t h e e a r t h . 5. A paper "Load-Reducing F l i g h t Control Systems f o r t h e S a t u r n V w i t h Various Payloads," submitted t o t h e A I M Guidance, Control and F l i g h t Dynamics Conference, was a c c e p t e d f o r p r e s e n t a t i o n . 6. Northrop Schedule Order No. 5 2 a. A n a l y t i c a l F i l t e r Design Study The f i n a l r e p o r t on t h e i n v e s t i g a t i o n of t h e a n a l y t i c a l f i l t e r d e s i g n technique proposed by R. W. Bass i n 1965 has been r e c e i v e d and d i s t r i b u t e d . Because of d i f f i c u l t i e s encountered i n a c h i e v i n g good overa l l performance w i t h t h e f i l t e r s designed by t h i s t e c h n i q u e , no f u r t h e r i n v e s t i g a t i o n i s planned. I A p r e s e n t a t i o n was made on t h e r e s u l t s of i n i t i a l i n v e s t i g a t i o n of a modified a n a l y t i c a l d e s i g n technique proposed by Bass i n 1967 t o overcome some of t h e problems of h i s e a r l i e r technique. It was demons t r a t e d a n a l y t i c a l l y that t h i s modified technique has a g r e a t d e a l of d i f f i c u l t y i n a c h i e v i n g s u c c e s s f u l o p e r a t i o n w i t h low o r d e r f i l t e r s . I f h i g h o r d e r f i l t e r s a r e t o be used, one might as w e l l t r y t o approximate Kalman-type f i l t e r s . S i n c e previous e f f o r t s u s i n g known a n a l y t i c a l d e s i g n techniques have been u n s u c c e s s f u l f o r space v e h i c l e a p p l i c a t i o n s , some thought i s now b e i n g g i v e n t o t r y i n g t o e s t a b l i s h what requirements on t h e f i l t e r we have i n p r a c t i c e , i n t h e hope t h a t a n a n a l y t i c o r computero r i e n t e d i t e r a t i v e technique can be devised t o meet our s p e c i f i c requirements. �b. Sampled-Data Root Locus Program The o r i g i n a l program assumed t h a t continuous f i l t e r s and sampling occurred o n l y on t h e t o t a l compensated e r r o r s i g n a l . Capabili t y t o employ d i g i t a l compensation on t h e loop s i g n a l has been added. However, t h i s a d d i t i o n has d e t e c t e d what a r e a p p a r e n t l y some l o g i c e r r o r s i n t h e o r i g i n a l program n o t p r e v i o u s l y found. Logic changes have a l s o been i n c o r p o r a t e d t o permit more a c c u r a t e d e t e r m i n a t i o n of low frequency r o o t s and t o permit more r a p i d d e t e r m i n a t i o n of t h e s t a b i l i t y of t h e closed-loop system. It i s hoped that t h i s e f f o r t w i l l be concluded i n t h e near f u t u r e . c. S p a c e c r a f t A t t i t u d e Control Study A previous s t u d y of a t t i t u d e c o n t r o l of a l a r g e s p a c e c r a f t d u r i n g i n s e r t i o n i n t o o r b i t a b o u t a n o t h e r p l a n e t showed undue s e n s i t i v i t y of performance t o CG o f f s e t s . Before t h e s t u d y was t e r m i n a t e d , a b r i e f e f f o r t was conducted t o s e e i f t h e a d d i t i o n of some e a s i l y o b t a i n e d a c c e l e r a t i o n o r i n t e g r a l a t t i t u d e e r r o r s i g n a l s would reduce t h e s e n s i t i v i t y . Only l i m i t e d s u c c e s s w a s achieved w i t h o u t s o p h i s t i c a t e d s i g n a l p r o c e s s i n g . The f i n a l r e p o r t on t h i s s t u d y has been published and d i s t r i b u t e d t o i n t e r e s t e d persons. d. Load R e l i e f of t h e S a t u r n v / ~ p o l l o An i n v e s t i g a t i o n has been i n i t i a t e d t o determine i f s i g n i f i c a n t load r e l i e f of t h e S a t u r n v I ~ p 0 1 1 0is p o s s i b l e u s i n g some simple techniques n o t considered by Boeing i n t h e i r r e c e n t s t u d y . This i n v e s t i g a t i o n i s a l s o being used as a n o p p o r t u n i t y t o e v a l u a t e t h e u t i l i t y of a d e s i g n technique proposed by Tomovic and b r i e f l y i n v e s t i g a t e d by D r . F r e d e r i c k a s a Summer F a c u l t y Fellow l a s t summer. The f i n a l r e p o r t by Boeing under c o n t r a c t NAS8-21070 and t h e d a b used by Boeing i n t h e i r s t u d y have been r e c e i v e d and e v a l u a t e d , and a computer program t o employ Tomovic's method has been w r i t t e n . 7. Lockheed Schedule Order 57 a. Parameter Optimization Study f o r ATM System Work continued on t h e h y b r i d s i m u l a t i o n of t h e ATM a t t i t u d e c o n t r o l s y s tern f o r t h e c o n j u g a t e g r a d i e n t method of parameter optimizat i o n . A l i n e a r i z e d dynamic model of t h e system has been developed. Two performance i n d i c e s a r e now under cons i d e r a t i o n . One minimizes t h e mean-square e r r o r of t h e p o i n t i n g system, and t h e o t h e r minimizes t h e mean-square command e r r o r t o t h e cMG's. �b. t r o l f o r any checked o u t . Alabama, t h e algorithm t o ncorporated 8. A p p l i c a t i o n of C-Minimax Control Theory The a l g o r i t h m f o r computation of t h e C-minimax optimal cons p e c i f i e d p l a n t has been s e t up on t h e hybrid computer and Suggestions by D r . C. D. Johnson of t h e U n i v e r s i t y of o r i g i n a t o r of t h e a l g o r i t h m , on m o d i f i c a t i o n s t o t h e b a s i c improve a c c u r a c y and v i s i b i l i t y of t h e r e s u l t s have been and checked o u t . Honeywell (NAS8-21171) O b j e c t i v e : To improve t h e performance of t h e load r e l i e f cont r o l system f o r t h e S a t u r n V l ~ o y a g e rdesigned by Honeywell under NAS8-11206. The c o n t r a c t p e r i o d c l o s e d on March 26, 1968. P r e l i m i n a r y c o p i e s of t h e f i n a l r e p o r t have been r e c e i v e d and reviewed. The o f f i c i a l f i n a l r e p o r t s w i l l be d i s t r i b u t e d w i t h a summarizing cover memo t o complete t h e study. C. As trodynamics Branch 1. Mission A n a l y s i s Programs A number of programs n e c e s s a r y f o r n e a r - p l a n e t a r y and i n t e r p l a n e t a r y m i s s i o n a n a l y s i s a r e b e i n g assembled and developed by Lockheed under t h e m i s s i o n s u p p o r t c o n t r a c t . These programs, i n c l u d i n g t h e f o l l o w i n g , a r e being documented and t r a n s f e r r e d t o inhouse c a p a b i l i t y . a. Planetary Orbiter Occultation This program computes o c c u l t a t i o n of v a r i o u s b o d i e s (e .g. , s u n , e a r t h , Canopus) a s viewed from a probe i n o r b i t a b o u t a g i v e n p l a n e t . The program i s now o p e r a t i o n a l . b. Swingby A program t o compute t r a j e c t o r i e s which make use of c l o s e swingbys of p l a n e t s a s a means of t r i p time o r energy m o d i f i c a t i o n has a l s o been checked-out and t r a n s f e r r e d . Some q u e s t i o n s concerning t h e o p t i m i z a t i o n o p t i o n s f o r t h e t o t a l t r a j e c t o r y a r e s t i l l being s t u d i e d . c. Ground Track and I l l u m i n a t i o n This Lockheed/Sunnyvale program has n o t y e t been made operational locally. �d. Broken-Plane T r a j e c t o r i e s Work i s c o n t i n u i n g on checkout of a program t o compute broken-plane ( t h r e e - i m p u l s e ) t r a j e c t o r i e s . Some a p p a r e n t d i s c r e p a n c i e s i n t h e d a t a have l e d t o a n i n v e s t i g a t i o n by Lockheed of t h e o p t i m i z a t i o n scheme which determines t h e p o i n t f o r a p p l y i n g t h e midcourse plane-change impulse. 2. Mission Design C h a r t s a. Improved V a r i a b l e s A means of g e n e r a t i n g miss i o n maps i n terms of payload i n t a r g e t - p l a n e t o r b i t has been developed. C e r t a i n assumptions concerning t h e v e h i c l e and miss i o n must be i n c o r p o r a t e d t o a c h i e v e t h i s t r a n s f ormat i o n . Other s i g n i f i c a n t v a r i a b l e s a r e being i n v e s t i g a t e d f o r p o s s i b l e r e p r e s e n t a t i o n on miss i o n c h a r t s . b. Expansion t o I n c l u d e Other T r a j e c t o r y Types (Lockheed) C u r r e n t l y a v a i l a b l e m i s s i o n maps c o n s i d e r d i r e c t t r a j e c t o r i e s o n l y . A r e c e n t l y i n i t i a t e d e f f o r t w i l l expand t h e n o n - d e t a i l e d v e r s i o n s of t h e maps t o i n c l u d e o t h e r forms of t r a j e c t o r i e s , i n c l u d i n g b o t h Type I and Type I1 d i r e c t , broken p l a n e , and swingby. 3. A p p l i c a t i o n s of Non-Central Force Problems t o C e l e s t i a l Mechanics Closed-form s o l u t i o n s f o r t r a j e c t o r y problems which approximate r e a l i s t i c s i t u a t i o n s a r e being studied f o r possible a p p l i c a t i o n t o i n t e r p l a n e t a r y t r a j e c t o r y c a l c u l a t i o n . The work i n t h i s a r e a is based on t h e f a c t t h a t two-body motion i n a n o n - c e n t r a l f i e l d d e r i v e d from a p o t e n t i a l of t h e form V(r, 8) = Vl(r v 2 ( e ) / r 2 (where r and 9 a r e p o l a r c o o r d i n a t e s of t h e body i n motion) l e a d s t o a s e p a r a b l e Hamilton-Jacobi e q u a t i o n . The f o r c e on a s p a c e v e h i c l e a t t r a c t e d by s e v e r a l b o d i e s can be reasona b l y w e l l approximated, l o c a l l y a t l e a s t , by such n o n - c e n t r a l f i e l d s . A program t o p l o t t h e a s s o c i a t e d t r a j e c t o r i e s i s b e i n g developed. It is expected t h a t we w i l l e v e n t u a l l y use t h e s e t r a j e c t o r i e s , t o g e t h e r w i t h a p a t c h i n g program t o compute i n t e r p l a n e t a r y t r a j e c t o r i e s . + 4. I n t e r p l a n e t a r y n-Body Programs a. Program Development Work on t h e i n t e r p l a n e t a r y n-body program i s c o n t i n u i n g i n d e p e n d a b i l i t y of i s o l a t i o n r o u t i n e s and program s e l f two main a r e a s : s u f f i c i e n c y . I s o l a t i o n r o u t i n e s a r e being studied i n a n e f f o r t t o i d e n t i f y one r o u t i n e which w i l l provide a l a r g e r e g i o n of convergence �w i t h f a s t convergent p r o p e r t i e s . To a t t a i n a s e l f - s u f f i c i e n t program two a r e a s a r e being i n v e s t i g a t e d . F i r s t , a method is needed f o r t h e program t o o b t a i n double p r e c i s i o n s t a t e v e c t o r s of t h e p l a n e t s a s a f u n c t i o n of time w i t h o u t u s i n g e x t e r n a l t a p e s o u r c e s . Secondly, a method f o r g e n e r a t ing i n i t i a l g u e s s e s i s needed. P r e s e n t l y , a s e p a r a t e program has t o be r u n t o g e n e r a t e t h e s e g u e s s e s , b u t such a r o u t i n e could be i n c o r p o r a t e d i n t o t h e n-body program. Then, t r a j e c t o r i e s could be g e n e r a t e d w i t h o u t g e t t i n g o f f t h e computer. (See paragraphs f o r p r o g r e s s r e p o r t on t h i s i n i t i a l guess g e n e r a t o r program.) b. T a r g e t i n g Research (Northrop) S e v e r a l approaches t o the i n t e r p l a n e t a r y t a r g e t i n g problem a r e being pursued. The a r t i f i c i a l focus method would determine a c o n i c connecting t h e launch and a r r i v a l p l a n e t s u s i n g a n a r t i f i c i a l f o c u s . A second method would r e q u i r e f i t t i n g a two-body c o n i c through t h e d e s i r e d d e p a r t u r e and a r r i v a l p o i n t s and then computing t h e n e t a c c e l e r a t i o n f o r s e v e r a l s e l e c t e d p o i n t s a l o n g t h e t r a j e c t o r y i n hopes of more n e a r l y r e p r e s e n t i n g a n i n t e g r a t e d n-body s o l u t i o n . Another approach is t h e p o s s i b i l i t y of u s i n g a c o n s t a n t s t e p i n t e g r a t i o n scheme w i t h a s implifiied model of t h e s o l a r system. c. I s o l a t i o n Routine Research (Northrop) I n the s t u d y of i s o l a t i o n r o u t i n e s , s e v e r a l promising methods have been i d e n t i f i e d , and more d e t a i l e d s t u d i e s a r e b e i n g conducted i n a n e f f o r t t o s e l e c t a "best" r o u t i n e o r combination of r o u t i n e s which can be included i n a n i n t e r p l a n e t a r y program f o r c r i t i c a l e v a l u a t i o n . 5. Conic Program f o r Small Computers Work is w e l l underway i n t h e g e n e r a t i o n of a scaled-down c o n i c program f o r u s e on s m a l l computers (IBM 1130, CDC 930). This program has a two-fold purpose. F i r s t , i t would provide most of t h e i n f o r m a t i o n t h a t l a r g e r c o n i c programs p r o v i d e , b u t would be more e a s i l y a v a i l a b l e and would have cons i d e r a b l y f a s t e r turn-around time Secondly, i n s u b r o u t i n e form, i t would provide i n i t i a l guesses f o r t h e i n t e r p l a n e t a r y programs. The program i s being assembled by combining s e v e r a l s m a l l inhouse programs w i t h a few programs o b t a i n e d from o t h e r groups, s u c h as t h e S u r f a c e Launch Window program provided by R-AERO-X. . 6. Optimum Orb i t T r a n s f e r a. Energy Requirements Study The i n v e s t i g a t i o n of t h e g e n e r a l energy requirements f o r o r b i t a l t r a n s f e r i s c o n t i n u i n g . Programming of t h e c o p l a n a r - c i r c u l a r , c o p l a n a r - e l l i p t i c a l , and i n c l i n e d - c i r c u l a r c a s e s should s t a r t soon. �b. Impulsive T r a j e c t o r y Survey (United A i r c r a f t MS8-21091) A rough d r a f t of t h e f i n a l r e p o r t is being reviewed. The b i b l i o g r a p h y of t h e survey l i s t s 310 s i g n i f i c a n t papers i n t h e f i e l d of impulsive t r a j e c t o r i e s . The r e p o r t should s e r v e t o summarize t h e s u b j e c t a r e a t o d a t e , a s w e l l a s i n d i c a t i n g r e g i o n s where f u r t h e r r e s e a r c h i s required. 7. Odyssey (Lockheed) P r e l i m i n a r y t r a j e c t o r i e s have been r u n f o r t h e e l l i p t i c o r b i t Odyssey experiment. This o r b i t experiment makes use of the s o l a r and l u n a r p e r t u r b a t i o n e f f e c t s t o a c h i e v e a f a i r l y wide range of p e r i g e e a l t i t u d e s over t h e experiment l i f e t i m e . Q u a l i t a t i v e e f f e c t s of l u n a r and s o l a r p e r t u r b a t i o n s a r e being determined i n o r d e r t o s p e c i f y i n i t i a l c o n d i t i o n s t o y i e l d t h e d e s i r e d range of p e r i g e e a l t i t u d e . QI. AEROPHYSICS D I V I S I O N A. F l u i d Mechanics Research O f f i c e 1. Aerodynamic Crossed-Beam Programs The redesigned s p e c i a l t e s t s e c t i o n of t h e 14-inch wind t u n n e l was r e t u r n e d t o the ME Laboratory f o r rework. D i f f i c u l t y was encountered i n t h e assembly d u r i n g p r e p a r a t i o n f o r checkout and c a l i b r a t i o n . The t e s t s e c t i o n has been r e t u r n e d and assembled, and t e s t i n g i s now underway. 2. Atmospheric Crossed-Beam Program From January 15 t o A p r i l 3 , 1968, 24 complete t e s t runs cons i s t i n g of crossed-beam and anemometer r e c o r d s have been r e p o r t e d by Colorado S t a t e U n i v e r s i t y . The r e c o r d s c o n s i s t e d of t h e following: a. z e r o beam s e p a r a t i o n s , b. l a r g e beam s e p a r a t i o n s ( g r e a t e r t h a n 60 m), and c. experiments w i t h beams p a r a l l e l t o t h e ground t o d e t e r mine i f measurements can be made under cloudy c o n d i t i o n s . A simple o n - l i n e phase c a l i b r a t i o n method has been designed and t e s t e d by CSU. These t e s t s r e v e a l e d a phase mismatch i n t h e photod e t e c t o r e l e c t r o n i c s . Steps a r e being taken t o c o r r e c t t h i s mismatch. The c o n t r a c t f o r t h e new computer code i s being n e g o t i a t e d w i t h IITRI. The CSU c o n t r a c t amendment was signed on March 25. CSU's r e p l y on the RFQ has been r e c e i v e d and i s being e v a l u a t e d . �3. Base Flow and S e p a r a t i o n Study The second t e s t phase of t h e base flow and s e p a r a t i o n s t u d y was completed on February 29, 1968, a t t h e Rosemount Aero-Hypersonic Laborat o r y ' s 6 x 9-inch blowdown t u n n e l . F i f t y - f i v e runs were made d u r i n g a s i x - d a y period i n v o l v i n g base f l u c t u a t i n g p r e s s u r e and h o t w i r e c o r r e l a t i o n measurements. The d a t a a r e being e v a l u a t e d . B. Mechanical Des ign O f f i c e 1. The Transonic T e s t S e c t i o n f o r t h e High Reynolds Number T e s t Equipment i s being redesigned t o i n c l u d e v a r i a b l e - p o r o s i t y w a l l s . The o r i g i n a l d e s i g n by Fluidyne Corporation d i d n o t have t h i s f e a t u r e . 2. A p r o t o t y p e micro-force balance system f o r use i n measuring r o c k e t c o n t r o l impingement f o r c e s on s p a c e c r a f t components i s being designed. The b a l a n c e system w i l l use semi-conductor s t r a i n gages t o measure up t o 5 components of f o r c e . T e s t w i l l be conducted i n t h e Low Density Chamber. 3 . A v a r i a b l e p o r o s i t y t r a n s o n i c t e s t s e c t i o n f o r t h e 18.75 p e r c e n t High Reynolds Number Equipment P i l o t Model has been designed and r e l e a s e d for fabrication. 4. The following i s a p a r t i a l l i s t of a d d i t i o n a l p r o j e c t s and t h e i r current s t a t u s . Redesign of F l a t P l a t e Protuberance Heat T r a n s f e r Model, L.R. C . , 4' WT (AT) Design Heated Plenum Chamber, L.D. WT (AE) Design Redesign of Survey Probe, 14" WT (AE) Drafting 4" O.D. P r e s s u r e Model, L.T.V. WT (AD) Drafting Low Volume Diaphragm C u t t e r , IBFF (AE) Drafting P r e s s u r e Models, X-Beam, STS, 14" WT (AF) Des i g n S l o s h Force Measuring System (DD) Fabrication Strap-on Force Models, 14" WT (AD) Fabrication Tracer M a t e r i a l I n j e c t o r , X-Beam, STS, 14" WT (AF) Fabrication �C. 5" O . D . , S a t . V, o a s e Flow Model, X-Beam 14" WT (AF) Fabrication Force Models, Experimental, L.D.C. Fabrication (AE) Major Components f o r High Reynolds Number T e s t Equipment (AE) Fabrication Heat S h i e l d , Model and D i f f u s e r Assembly (AT) De 1i v e r e d 18.75% Model of High Reynolds No. T e s t Equipment (AE) Delivered Remote F l o o r and C e i l i n g Adjustment Hardware, 14" WT (AE) Delivered P r e s s u r e Model (5' Cone), 14" WT (AU) Delivered Temperature Model (5' Cone), 14'' WT (AU) Delivered Diaphragm C u t t e r f o r High Reynolds Number T e s t Equipment (AU) Delivered P r e s s u r e Model, New S o l a r Panel Shroud, AAP, 14" WT (AD) Delivered Aerodynamic Design Branch 1. E x t e r n a l L o n g i t u d i n a l P r e s s u r e D i s t r i b u t i o n s over t h e Apollo-Saturn V S p a c e c r a f t Compartment The e x t e r n a l p r e s s u r e d i s t r i b u t i o n s over t h e Apollo-Saturn V s p a c e c r a f t compartment have been extended and s l i g h t l y r e v i s e d . The d a t a , f o r a n g l e s of a t t a c k of 4, 8 and 12 degrees and f o r Mach numbers between 0.80 and 1 . 4 0 , a r e p r e s e n t e d i n o f f i c e memorandum R-AERO-AD-68-12. 2. S a t u r n V S t a t i c Aerodynamic T e s t s a t CAL Some e s t i m a t e s have i n d i c a t e d t h a t a r e d u c t i o n of t e n p e r c e n t i n forebody a x i a l f o r c e f o r t h e Apollo-Saturn V would be r e a l i z e d w i t h t h e r e c e n t removal of b a s e scoops from t h e S-IC s t a g e . Consequently, a t e s t was conducted i n t h e CAL 8 - f o o t t r a n s o n i c wind t u n n e l t o o b t a i n s t a t i c aerodynamic c h a r a c t e r i s t i c s f o r t h e v e h i c l e w i t h scoops removed. T e s t s were conducted March 25, 1968 a t Mach numbers between 0.5 and 1 . 3 u s i n g a 0.9 p e r c e n t s c a l e d model. P r e l i m i n a r y r e s u l t s i n d i c a t e a reduct i o n i n forebody a x i a l f o r c e v a r y i n g from 15 p e r c e n t a t Moo = 1.1 t o 5 0 p e r c e n t a t M o o D 0.5, w h i l e low a n g l e - o f - a t t a c k c e n t e r of p r e s s u r e and normal f o r c e g r a d i e n t s remain unchanged. �3. S a t u r n V/S-11-8 Spray Foam I n s u l a t i o n The second phase of aerodynamic t e s t s on 10 x 10-inch samples of S-11-8 s p r a y foam i n s u l a t i o n were completed i n t h e MSFC 14-inch t r i s o n i c wind t u n n e l d u r i n g t h e l a t t e r p a r t of March. T e s t panels coated w i t h a "chemical dynatherm" and uncoated panels were f l u s h mounted i n t h e t u n n e l s i d e w a l l and s u b j e c t e d t o aerodynamic l o a d s which simulated t h o s e of t h e maximum dynamic p r e s s u r e c o n d i t i o n s of t h e 501 f l i g h t t r a j e c t o r y . These t e s t s , a s i n t h e f i r s t phase, d i d not simulate the S-I1 s k i n f l i g h t temperatures. These t e s t s included t h e i n v e s t i g a t i o n of t h e e f f e c t s due t o debonded a r e a s under t h e foam f o r b o t h coated and uncoated p a n e l s . F a i l u r e s of t h e f i r s t phase t e s t s were due t o d i f f e r e n t i a l p r e s s u r e s a c r o s s t h e closed c e l l s c r e a t e d by a i r trapped under t h e foam. This was avoided i n t h e s e t e s t s by a p p l y i n g a vacuum t o t h e a r e a under t h e foam. This procedure was considered t o be a r e a s o n a b l e s i m u l a t i o n of t h e p r e s s u r e s under cryogenic temperatures encountered on t h e a c t u a l S - I 1 s t a g e . Under t h e s e c o n d i t i o n s , t h e r e were no f a i l u r e s of debonded panels even f o r dynamic p r e s s u r e s of a b o u t 180 p e r c e n t g r e a t e r than t h a t of f l i g h t . Other d e f e c t s s t u d i e d c o n s i s t e d of s k i n cracks and debonds of coated p a n e l s , and coated panels w i t h seams i n t h e foam. The l a t t e r occur on t h e v e h i c l e where s e c t i o n s of i n s u l a t i o n meet i n a r e a s where i t i s n o t f e a s i b l e t o s p r a y t h e tank s k i n i n one continuous s h e e t , There were no s k i n f a i l u r e s e x c e p t those which occurred f o r 4-inch o r l a r g e r t r a n s v e r s e cracks i n c o n j u n c t i o n w i t h l a r g e s e m i - c i r c u l a r s k i n debonds 4-inches wide and 3-inches deep. The s k i n t o r e a t t h e ends of t h e c r a c k and propagated outward. Based on t h e s e o b s e r v a t i o n s , t h e p r e d i c t i o n of s k i n l o s s on t h e S - I 1 s t a g e i s n o t p o s s i b l e s i n c e t h e f a i l u r e propagated t o t h e s i d e edges of t h e s m a l l t e s t p a n e l s . A r e p o r t p r e s e n t i n g t h e t e s t r e s u l t s is being p r e p a r e d . 4. Nonlinear L i f t of Bodies of Revolution The Phase I s t u d y , which i n c l u d e s t h e d e t e r m i n a t i o n of t h e d e t a i l e d p r e s s u r e d i s t r i b u t i o n on o g i v e - c y l i n d e r and o g i v e - c y l i n d e r / f r u s t u m - c y l i n d e r models i n t h e MSFC 14-inch t r i s o n i c wind t u n n e l i s scheduled f o r A p r i l 15, 1968. An a t t e m p t t o r u n t h e Phase I d a t a r e d u c t i o n program on t h e R-COMP 7094 f a i l e d because of t h e u n a v a i l a b i l i t y of a s u b r o u t i n e which CCSD has r e c e i v e d permission t o r u n t h e had been included by C h r y s l e r . program a t S l i d e l l , thus e l i m i n a t i n g t h e need f o r modifying and checking o u t t h e program a t R-COMP. �C h r y s l e r has completed t h e f a b r i c a t i o n and d e l i v e r y of the Phasc I p r e s s u r e models. The d e s i g n of t h e Phase I1 v o r t e x survey equipment i s underway. 5. Aerodynamic Loads on t h e Proposed SLA F a i r i n g f o r AAP-I1 Vehicles The l o c a l aerodynamic loads on a proposed f a i r i n g f o r t h e MDA probe have been determined. The e f f e c t s on t o t a l v e h i c l e s t a b i l i t y , drag and l o a d s were a l s o determined. These d a t a have been published i n O f f i c e Memorandum R-AERO-AD-68-8, "Aerodynamic Loads on t h e SLA F a i r ing f o r AAP-I1 Mission," dated February 23, 1968. 6. Plume Impingement E f f e c t s t o t h e MDA o r ATM due t o E j e c t i o n of t h e Nose Cone/SLA from t h e AAP-I1 and AAP-IV Vehicle P r e l i m i n a r y p r e s s u r e , h e a t t r a n s f e r , and plume c o n s t i t u e n t e f f e c t s experienced by t h e payloads of t h e AAP-I1 o r AAP-IV v e h i c l e s d u r i n g nose cone/SL,A e j e c t i o n have been developed. The d a t a a r e a p p l i c a b l e f o r d e f i n i n g a d v e r s e e f f e c t s of p a r t i c l e contamination o r aerodynamic thermal loads o r p r e s s u r e loads on ATM experiment packages o r MDA f u n c t i o n a l s u r f a c e s . These r e s u l t s a r e p r e s e n t e d i n O f f i c e Memorandum R-AERO-AD-68-13, d a t e d March 13, 1968. 7. S a t u r n I B A x i a l Force C h a r a c t e r i s t i c s The aerodynamic a x i a l f o r c e c h a r a c t e r i s t i c s of t h e S a t u r n I B v e h i c l e s have been r e v i s e d based on a n a n a l y s i s of f l i g h t b a s e p r e s s u r e measurements. These d a t a have been published i n R-AERO-AD-68-19 f o r t h e AS-206 and AS-207 v e h i c l e s . 8. Apollo-Saturn I Vehicle Aerodynamics S t a t i c s t a b i l i t y and normal f o r c e c o e f f i c i e n t d i s t r i b u t i o n s f o r t h e Apollo-Saturn I v e h i c l e were d e f i n e d a t a n g l e s of a t t a c k of 1 4 and 16 degrees over t h e Mach number range. These d a t a were d e f i n e d based on experimental t r e n d s and lower a n g l e of a t t a c k d a t a . These r e s u l t s , published i n O f f i c e Memorandum R-AERO-AD-68-9, supplement t h e d e s i g n c r i t e r i a published i n NASA TM X-53657. These d a t a a r e f o r i n p u t i n t o c o n t r o l and s t r u c t u r a l a n a l y s i s of t h e v e h i c l e f o r off-nominal t r a jectories studies . 9. O r b i t a l Aerodynamics During t h i s r e p o r t i n g p e r i o d , aerodynamic d a t a f o r AAP m i s s i o n "A" have been updated t o i n c l u d e a n g l e s of a t t a c k from 250 t o 290 d e g r e e s . P r e v i o u s l y , d a t a ( p r e s e n t e d i n O f f i c e Memorandum R-AERO-AD-67-90) had been c a l c u l a t e d o n l y f o r a n a n g l e of a t t a c k of 270 d e g r e e s . The updated �d a t a a r e contained i n Off i c e Memorandum R-AERO-AD-68-10, " O r b i t a l d a t e d February 28, 1968. Aerodynamic Data f o r AAP Mission "A"," 10. Body of Revolution Viscous Cross flow I n v e s t i g a t i o n A method has been found by which t h e s t a i n l e s s s t e e l flowv i s u a l i z a t i o n models can be darkened (chemically t r e a t e d ) . A g r i d of l o n g i t u d i n a l and r a d i a l l i n e s w i l l t h e n b e a p p l i e d t o t h e model by u s i n g a s m a l l t h i n b u r n i s h i n g t o o l . The c o n t r a s t between t h e d a r k models and t h e w h i t e c h i n a c l a y should provide e x c e l l e n t f l o w - v i s u a l i z a t i o n p i c t u r e s . The g r i d system on t h e model w i l l a l l o w changes i n flow c h a r a c t e r is t i c s due t o Reynolds number t o be r e l a t e d t o l o n g i t u d i n a l and r a d i a l d imens i o n s . Some a d d i t i o n a l f o r c e d a t a a r e r e q u i r e d f o r comparison w i t h follow-on p r e s s u r e t e s t s of v i s c o u s c r o s s flow models. The f o r c e t e s t s a r e scheduled t o b e g i n on A p r i l 9 , 1968 and t h e p r e s s u r e t e s t s a r e scheduled t o b e g i n on A p r i l 15, 1968. D. Experimental Aerophysics Branch 1. Low Density Chamber The problems of j e t plume behavior i n vacuum and j e t plume impingement f o r c e s from c o n t r o l j e t s s t r i k i n g s p a c e c r a f t components have c r e a t e d a need f o r experimental d a t a . To e s t a b l i s h a c a p a b i l i t y i n t h e a v a i l a b l e f a c i l i t i e s t o measure flow and thermodynamic p r o p e r t i e s i n cool and h o t j e t s , a program has been s t a r t e d t o determine t h e f e a s i b i l i t y of (1) u s i n g t h e low-density chamber a s t h e a l t i t u d e s i m u l a t o r and (2) e x h a u s t i n g s c a l e model n o z z l e s i n t o t h e chamber w i t h C 0 2 a s t h e flow medium. Various experiments have been r u n t o determine t h e o p e r a t ing l i m i t s and t o d e v i s e t e s t i n g approaches. The f o l l o w i n g parameters have been e s t a b 1 ished: ( a ) Mass flow r a t e s of 10 grams/second of C02 can be maintained a t a l t i t u d e s of approximately 75 km. Of c o u r s e , l e s s e r flow r a t e s ( 0 . 1 gram p e r second) can be maintained a t h i g h e r a l t i t u d e s (150-200 km). (b) Model s i z e s have been e s t a b l i s h e d t o r a n g e from 1 0 : l s c a l e t o 4 0 : l s c a l e . The 1 0 : l s c a l e model would be a segment of t h e O r b i t a l Workshop, and t h e 40:l s c a l e would be a complete OWS model w i t h a body diameter of approximately 6 i n c h e s . One problem now being i n v e s t i g a t e d is t h e a l l o w a b l e t o l e r a n c e s when b u i l d i n g such s m a l l model n o z z l e s . For i n s t a n c e , t h e 4 0 : l s c a l e of t h e APS t h r u s t e r would have a t h r o a t diameter of 0.011 i n c h ; t o g e t a t h r u s t ' e r r o r of l e s s t h a n 2 p e r c e n t , t h e t o l e r a n c e on t h e t h r o a t diameter would have t o be +0.0001 i n c h . �(c) Experiments have been r u n which i n d i c a t e t h a t t h e p r e s s u r c s t o be measured a r e i n t h e range of t h e thermocouple gauge type p r e s s u r e s e n s o r . Some of t h e s e s e n s o r s a r e on hand and o t h e r s have been o r d e r e d . A l l should be a v a i l a b l e when f a b r i c a t i o n of t h e f i r s t p r e s s u r e model i s completed. R-AERO-AD has f u r n i s h e d t h e c o n f i g u r a t i o n of the p r e s s u r e model. A s i n g l e component b a l a n c e i s on hand f o r measuring a x i a l loads and a multi-component b a l a n c e i s being designed by R-AERO-AM. (d) A problem has come t o l i g h t d u r i n g t h e s e i n i t i a l s t u d i e s t h a t r e q u i r e s f u r t h e r i n v e s t i g a t i o n . The temperature and p r e s s u r e t o which t h e C02 is expanded i n t h e t h r u s t e r nozzle t h e o r e t i c a l l y p l a c e t h e C02 i n a two-phase ( g a s - s o l i d ) r e g i o n . I n i t i a l experimental r e s u l t s However, more d e t a i l e d i n d i c a t e t h a t supersaturation i s occurring experiments w i l l be conducted t o determine c o n c l u s i v e l y whether t h e r e is condensation. . 2. Impulse Base Flow F a c i l i t y (IBFF) The t h r e e - e n g i n e phase of t h e p a r a m e t r i c b a s e h e a t i n g s t u d y was completed d u r i n g February. Remaining i n t h i s program a r e s i n g l e engine w i t h c o n i c a l and contoured nozzles and a four-engine c o n f i g u r a t i o n . This program, however, has been i n t e r r u p t e d f o r high p r i o r i t y Reynolds Number P i l o t Model t e s t i n g . The 18.75 p e r c e n t High Reynolds Number P i l o t Model equipment has been i n s t a l l e d and h y d r o s t a t i c a l l y p r o o f - t e s t e d . Work is being done t o p e r f e c t t h e new diaphragm c u t t e r mechanism. T e s t i n g scheduled t o b e g i n w i t h i n t h e month i s expected t o provide experimental d a t a on t h e unsteady s t a r t i n g process a s s o c i a t e d w i t h t h i s type of f a c i l i t y . Of primary i n t e r e s t i n t h e t e s t s a r e parameters such a s model and s t i n g s t a r t i n g l o a d s , t u n n e l blockage from model and s t i n g s i z i n g , tunnel s t a r t time, etc. 3. High Reynolds Number T e s t Equipment The 50-foot s p h e r e and 45-degree i n l e t elbow a r e complete and a r e being p a i n t e d . S i n c e b i d s r e c e i v e d on a l l remaining hardware a r e below our o r i g i n a l e s t i m a t e s , s u f f i c i e n t money remains t o purchase a t r a n s o n i c t e s t s e c t i o n . The Fluid-Dyne drawings a r e b e i n g modified s o t h a t t h e t r a n s o n i c t e s t s e c t i o n may go o u t f o r b i d s . The 48" diaphragm t e s t was begun, and should be completed w i t h i n t h e n e x t s i x o r e i g h t weeks. �4. Thermal-Acous t i c J e t F a c i l i t y (TAJF) The c o l d flow d u c t of t h e TAJF i s being used t o phase NASA personnel i n t o t h e o p e r a t i o n of t h e c r o s s beam. This work was formerly done by IITRI a s p a r t of t h e i r c o n t r a c t . Power and h i g h p r e s s u r e gas connections t o t h e Helium Heater have s t i l l n o t been made. S i n c e t h e l a s t r e p o r t , R-OM managed t o have t h e work removed from t h e o v e r a l l center-wide c o n s o l i d a t e d b i d package and handled a s a s e p a r a t e item. The b e n e f i t s a r e d o u b t f u l , however, because t h e b i d package of which i t was o r i g i n a l l y a p a r t has a l r e a d y been awarded, and t h e s e p a r a t e job is j u s t now a t Purchasing Off i c e t o go o u t f o r b i d s . The Laboratory had t o f u r n i s h $5,000, and i n t h e p r o c e s s , t h e e n t i r e job went t o Washington f o r review. With l u c k , we may be hooked up by mid-May. 5. 1 4 x 14-Inch T r i s o n i c Wind Tunnel The following t e s t s were r u n d u r i n g February and March 1968: (1) A p r e l i m i n a r y i n v e s t i g a t i o n t o d e f i n e t h e mean flow around v a r i o u s protuberances and t o a c q u i r e i n i t i a l d a t a on t h e magnitude of t h e f l u c t u a t i n g loads a t b o t h t r a n s o n i c and s u p e r s o n i c Mach numbers. T o t a l runs: 191. (2) A c o n t i n u a t i o n of t h e i n v e s t i g a t i o n f o r R-AERO-AU of t h e quas i - s t e a d y o s c i l l a t i o n wake s t u d y . This s t u d y cons i s ts of determining t h e dynamic damping c h a r a c t e r i s t i c s of a 30-degree cone model submerged i n t h e wake of v a r i o u s wake-source c o n f i g u r a t i o n s a s t h e r e l a t i v e o r i e n t a t i o n between t h e wake s o u r c e and t h e submerged models is v a r i e d . This t e s t e n t r y was t h e f i f t h phase of t h e s t u d y . T o t a l r u n s : 80. ( 3 ) An i n v e s t i g a t i o n f o r R-AERO-AU t o determine t h e e f f e c t of changes i n Mach number, o s c i l l a t i o n a m p l i t u d e , and a f t e r - b o d y geometry on t h e p i t c h damping d e r i v a t i v e s of a r i g i d S a t u r n / A p o l l o forebody con£ i g u r a t i o n . The t e s t w a s terminated prematurely because of a model f a i l u r e . T o t a l runs: 45. A n o t i c e a b l e improvement i n compressor maintenance has r e s u l t e d from t h e r e c e n t change-over from o r g a n i c o i l t o s y n t h e t i c o i l l u b r i c a t i o ] This s u b s t i t u t i o n w i l l v i r t u a l l y e l i m i n a t e dangers from b u r n i n g o i l vapol and reduce carbon d e p o s i t s on compressor v a l v e s . �6. Instrumentation The d i g i t a l magnetic t a p e u n i t has been completely checked o u t w i t h the former shock t u n n e l a n a l o g - t o - d i g i t a l c o n v e r t e r . This system i s t o be used i n t h e f u t u r e f o r p i l o t s t u d i e s of o n - l i n e r e a l - t i m e d i g i t i z i n g of atmospheric cross-beam d a t a . I n t h e meantime, i t has been used i n a d a t a decimation s t u d y f o r R-AERO-AU. The u n i t worked q u i t e s u c c e s s f u l l y and i s a v a i l a b l e f o r any o t h e r work. The l a s e r crossed-beam system formerly was engineered and o p e r a t e d by IITRI. MSFC has now assumed t h i s r e s p o n s i b i l i t y and the system has been i n s t a l l e d a t t h e f a c i l i t y , checked o u t and i s i n use on a t e s t . As "simple" a s t h e s y s tem was, i t r e q u i r e d a b o u t t h r e e weeks t o g e t i t operating properly. For a c o u s t i c t e s t i n g i n t h e 14" t u n n e l and t h e TAJF, a 34-channel m u l t i p l e x system has been b u i l t o u t of t h e 122-channel system purchased f o r t h e S a t u r n 45 p e r c e n t t e s t a t AEDC. It has been i n s t a l l e d i n a s m a l l p o r t a b l e r a c k which can be placed a t t h e t e s t f a c i l i t i e s and cabled t o a c e n t r a l wide-band r e c o r d e r l o c a t e d i n t h e l a b s p a c e . This w i l l save moving t h e e n t i r e system f o r s m a l l t e s t s and t h e a t t e n d a n t wear and t e a r . R-AERO-AU i s c o n s i d e r i n g a t e s t t o measure t h e unsteady f o r c e s on a span-wise c y l i n d e r . This poses some i n t e r e s t i n g and d i f f i c u l t problems of measurement, and a crude a n a l y s i s has been made i n a memo d a t e d March 2 7 , 1968, e n t i t l e d "Balances t o Measure Unsteady Loads on C y l i n d e r s . I' The plume impingement problems mentioned e a r l i e r have opened t h e a r e a of low-range f o r c e measurements, ranging from one o r two pounds downward t o a few thousandths of a pound. A s t a t u s r e p o r t is g i v e n i n a memo d a t e d March 26, 1968, "Low-Range Force Balances f o r Plume Impingement work." 7. O r b i t a l Aerodynamics The p h o t o - c e l l s c a n n e r system i s complete i n a l l r e s p e c t s . The program t o provide moment d a t a a b o u t b o t h t h e X and Y axes has been comp l e t e d and checked o u t . The program has a l s o been r u n on t h e CDC 3200 computer i n B u i l d i n g 4200, and runs w i t h o u t change. Thus, backup comput a t i o n i s a v a i l a b l e . The o u t p u t d a t a and o u t p u t format have been agreed upon by a l l concerned. No f u r t h e r r e p o r t i n g w i l l be made on t h i s item. The d i g i t a l TV s c a n n e r is s t i l l i n computer checkout. �8. Data Reduction Aside from t h e normal f a c i l i t y d a t a r e d u c t i o n , s e v e r a l a d d i t i o n a l programs have been w r i t t e n . One program t o l e a s t - s q u a r e s - c u r v e f i t wind t u n n e l c o e f f i c i e n t d a t a and remove t h e t a r e v a l u e s of t h e c o e f f i c i e n t has been w r i t t e n and checked o u t f o r a p a r t i c u l a r t e s t . The new n o z z l e f o r t h e s p e c i a l t e s t s e c t i o n f o r crossed-beam work i s t o be c a l i b r a t e d . A s p e c i a l program was w r i t t e n f o r t h i s work . As p a r t of t h e n o n l i n e a r l i f t (viscous c r o s s flow) s t u d i e s , a t e s t i s t o be r u n i n t h e 14-inch t u n n e l u s i n g a model w i t h about 300 p r e s s u r e o r i f i c e s . A program was w r i t t e n t o reduce t h e s e d a t a t o p r e s s u r e c o e f f i c i e n t s , s o r t i t i n t o s e q u e n t i a l form, p r i n t , and punch t h e r e s u l t s f o r f u r t h e r a n a l y s i s by C h r y s l e r . E . Thermal Environment Branch 1. The s p e c t r o r a d i o m e t e r developed by Rocketdyne under C o n t r a c t NAS8-21144 i s being i n s t a l l e d i n t h e B-3 t e s t c e l l a t t h e Rocketdyne Nevada F i e l d Laboratory (NFL). The a b s o r p t i o n - s o u r c e housings and s p a t i a l s c a n mechanism have been assembled, a l i g n e d , and checked o u t , and a r e being i n s t a l l e d i n t h e t e s t c e l l a t NFL. I t is hoped t h a t t h e f i r s t t e s t s i n t h e t e s t c e l l , beginning t h e l a s t of March, can be monitored. The measurement of HF a b s o r p t i o n c o e f f i c i e n t s was delayed because of t h e r e l o c a t i o n of equipment. This problem has been r e s o l v e d , and measurements of HF a b s o r p t i o n c o e f f i c i e n t s w i l l b e g i n immediately. 2. The i n v i s c i d a n a l y s i s of a s i n g l e F-1 exhaust plume a t v a r i o u s a l t i t u d e s f o r t h e S-IC s t a g e r a d i a t i o n s t u d y h a s been completed. These plumes have been s t o r e d on t a p e and w i l l b e used by t h e Boeing Company i n t h e i r r a d i a t i o n a n a l y s i s . The v i s c o u s a n a l y s i s of t h e s e plumes is c o n t i n u i n g . The r e s u l t s of t h e s e f l o w - f i e l d c a l c u l a t i o n s w i l l b e used i n t h e gaseous r a d i a t i o n program t o t r y t o e x p l a i n t h e r a d i a t i o n "hump" i n t h e AS-501 d a t a . 3 . A f t e r a n unexpected d e l a y i n o b t a i n i n g t h e c o n t i n u a t i o n t o C o n t r a c t NAS7-521, work has s t a r t e d on t h e experimental composite engine s t u d y being conducted by Rocketdyne. Engine f a b r i c a t i o n and i n s t a l l a t i o n have been completed, and t h e t e s t s t a n d is b e i n g r e a c t i v a t e d . Hot f i r i n g s a r e scheduled f o r May 1968 r a t h e r than February as p r e v i o u s l y reported. �4. R a d i a t i o n and Low Density Drag C o e f f i c i e n t View F a c t o r Program During t h i s p e r i o d t h e checking o u t of t h e v i e w - f a c t o r computer code was continued. An a l t e r n a t i v e pre-shade s u b r o u t i n e was developed and coded i n which t h e elements of a s u r f a c e w i l l b e checked f o r shading a s opposed t o checking t h e nodes of t h e p r e s e n t s u b r o u t i n e . F i n a l checko u t of t h e contour i n t e g r a l method was a l s o continued; r e s u l t s o b t a i n e d were i n agreement w i t h a n e x i s t i n g v i e w - f a c t o r program, a s w e l l as some e x a c t a n a l y t i c a l s o l u t i o n s . The program checkout has been delayed because of r e c e n t long turn-around times a t t h e Computation Laboratory. This s i t u a t i o n i s expected t o improve.. 5. High a n g l e - o f - a t t a c k h e a t i n g t e s t s w i l l be r u n a t Langley Research Center beginning i n June o r J u l y . The t e s t s w i l l be monitored and t h e r e s u l t s analyzed by C C S D / N ~Orleans. W The t e s t parameters w i l l i n c l u d e a Mach number range of 3 t o 6, Reynolds numberlft of .44 x 10" t o 9 . 3 x lo6, and a n a n g l e - o f - a t t a c k range of 0 t o 35 d e g r e e s . 6. Protuberance T e s t Work has been i n i t i a t e d t o b u i l d a new t e s t p l a t e . U n f o r t u n a t e l y , having been weakened by s e v e r a l previous m o d i f i c a t i o n s , t h e p l a t e became s l i g h t l y warped a l o n g t h e c e n t e r l i n e when t h e m o d i f i c a t i o n s f o r t h i s t e s t were made. This was s u b s e q u e n t l y v e r i f i e d i n t e s t r u n s a t Langley Research Center. Drawings of t h e p l a t e have been s e n t t o R-AERO-AM f o r s t u d y . F. Uns teady Aerodynamics Branch 1. S a t u r n IB Ground Winds S t u d i e s a r e b e i n g conducted t o determine t h e r e q u i r e d m o d i f i c a t i o n s f o r s i m u l a t i n g t h e AAP-2 and AAP-4 c o n f i g u r a t i o n s w i t h a S a t u r n I B a e r o e l a s t i c wind t u n n e l model c o n s t r u c t e d f o r d i f f e r e n t s t r u c t u r a l charact e r i s t i c s . Wind-induced l o a d s f o r S a t u r n I B , AS-205, a r e b e i n g p r e d i c t e d . These p r e d i c t i o n s w i l l be published as soon a s completed. 2. S a t u r n V Ground Winds The f a b r i c a t i o n of t h e Uprated S a t u r n V ground winds model by A t k i n s and M e r r i l l has been delayed because of a n overrun i n funds. No d a t e f o r model checkout t e s t s and d e l i v e r y has y e t been s e t . A s t u d y f o r determining t h e second mode bending moment c o n t r i b u t i o n t o t h e ground wind l o a d s imposed on t h e S a t u r n V v e h i c l e empty-onpad c o n f i g u r a t i o n has been completed; t h e r e s u l t s were published Feb, 14, 1968. A s i m i l a r s t u d y i s being made f o r t h e S a t u r n V f u e l e d weight cond i t i o n . �P r e d i c t i o n s of ground wind loads and r e s u l t i n g d e f l e c t i o n s f o r t h e S a t u r n V empty-on-pad and i n t e r m e d i a t e weight c o n d i t i o n s w i t h t h e LUT and MSS c o n f i g u r a t i o n s have been completed. This i n f o r m a t i o n was published March 22, 1968. Also, ground wind l o a d s f o r t h e S a t u r n V, i n t e r m e d i a t e weight c o n d i t i o n w i t h t h e LUT and MSS c o n f i g u r a t i o n w i t h dampers detached have been completed and t h e r e s u l t s were published March 26, 1968. 3. I n f 1i g h t Acous t i c s a . Systematic phase and amplitude d i s t o r t i o n s t h a t occurred i n t h e d a t a a c q u i s i t i o n and r e d u c t i o n systems used i n t h e f o u r - p e r c e n t AEDC experiment a r e being determined e x p e r i m e n t a l l y by Baganoff and A s s o c i a t e s . This i s a long and l a b o r i o u s e f f o r t . Experimental r e s u l t s o b t a i n e d u s i n g t h e w h i t e n o i s e c a l i b r a t i o n d a t a recorded a t t h e time t h e f o u r - p e r c e n t S a t u r n V model experiment was being conducted i n d i c a t e t h a t v a r i a n c e s i n phase a n g l e due t o system d i s t o r t i o n s w i l l be of t h e o r d e r of 1 . 5 d e g r e e s . This r e s u l t i s v e r y f a v o r a b l e and demonstrates t h a t a l a r g e m a j o r i t y of t h e AEDC f l u c t u a t i n g p r e s s u r e d a t a w i l l be phase-correctable. b . F l u c t u a t i n g p r e s s u r e s have been e s t i m a t e d f o r t h e s o l a r panel pods mounted on t h e S-IVB s t a g e of t h e S a t u r n IVB and S a t u r n V, a s r e q u e s t e d by R-AERO-XS. c. Supplemental cross-power s p e c t r a l d e n s i t i e s from t h e f o u r p e r c e n t S a t u r n V experiment a r e being prepared f o r R-P&VE-S t o use i n s t r u c t u r a l response c a l c u l a t i o n s . d . F l u c t u a t i n g p r e s s u r e d a t a o b t a i n e d from t h e f o u r - p e r c e n t model t e s t a r e f i n a l i z e d and w i l l be published soon. e . A wind t u n n e l program has been scheduled i n t h e AEDC 16f o o t t r a n s o n i c t u n n e l t o provide experimental i n f o r m a t i o n t o h e l p d e r i v e methods by which f l u c t u a t i n g a i r l o a d s can be a c c u r a t e l y p r e d i c t e d on and around e x t e r n a l protuberances on launch v e h i c l e s . The program, t o b e g i n on May 20, 1968, w i l l l a s t f o r a b o u t two weeks. The s t a t i c and dynamic p r e s s u r e s environment f o r a group of g e n e r a l i z e d p r o t u b e r a n c e s and some s p e c i f i c geometry protuberance w i l l be measured f o r a Mach number range of 0.6 t o 1 . 6 . 4. Launch S i t e A c o u s t i c s a . An R-AERO-AU member a t t e n d e d a planning meeting a t Headq u a r t e r s , a s t h e MSFC r e p r e s e n t a t i v e , f o r a conference on NASA'S prog r e s s i n t h e a p p l i c a t i o n of r e s e a r c h on n o i s e a l l e v i a t i o n t o s u b s o n i c a i r c r a f t . Two papers on a c o u s t i c s have M r . Weidner's a p p r o v a l t o be g i v e n from MSFC1s Aero Lab i n October. The conference i s t o be h e l d a t Langley Research Center w i t h approximately 300 a t t e n d e e s from a l l a r e a s of a i r c r a f t d e s i g n and o p e r a t i o n a l concerns. 33 �. b Acoustic d a t a a c q u i s i t i o n f o r f a r - f i e l d locations f o r AS-204, AS-205 and subsequent f l i g h t s i s being i n v e s t i g a t e d i n conjunct i o n w i t h KSC. c . Attenuation-of-sound e s t i m a t e s a r e being s t u d i e d from a c o u s t i c d a t a from 66 s t a t i c t e s t s of the F-1 engine, t h e S - I and I B , and t h e S-IC s t a g e s a t MSFC from 1965 t o December 1967. Data a r e being s e l e c t e d w i t h a minimum of r e f r a c t i o n i n f l u e n c e s t o more a c c u r a t e l y d e f i n e a c o u s t i c environments f o r r o c k e t o r j e t engine o p e r a t i o n i n populated o r u n c o n t r o l l e d a r e a s . These r e s u l t s a r e a p p l i c a b l e t o i n d u s t r i a l use f o r any n o i s e s o u r c e , and may a l s o be used f o r t r a n s portation applications, etc. d . The p r e l i m i n a r y i n p u t " P r e d i c t i o n of B l a s t and A c o u s t i c Environment of Large Space Boosters" f o r t h e j o i n t NASA/AF hazards manual has been p r e s e n t e d f o r i n c l u s i o n by t h e Committee on Environmental Health and Toxicology of t h e I n t e r a g e n c y Chemical Rocket Propuls i o n Group. Minor r e v i s i o n s o r a d d i t i o n s may be made f o r r e a s o n s of compatibility. e . The concern f o r t h e a c o u s t i c environment of t h e Nuclear Rocket s t a t i o n i s being i n v e s t i g a t e d . A copy of R-P&VE's r e p o r t on t h e a c o u s t i c environments. w i l l be obtained and compared w i t h t h e pred i c t i o n s now being prepared by R-AERO-AU, f o r n u c l e a r engine o p e r a t i o n s . f . A c o u s t i c d a t a from c l u s t e r t e s t s of model r o c k e t engines a t AMTF a r e p a r t i a l l y complete. Manpower t e s t s u p p o r t is a s e r i o u s problem w i t h programs i n t h i s a r e a . g . T e s t s of t h e S a t u r n V s c a l e model f o r on-pad and s i m u l a t e d l i f t - o f f c o n d i t i o n t e s t s a t AMTF has n o t begun because of manpower l i m i t a t i o n s a t T e s t Laboratory. 5. Panel F l u t t e r a . E v a l u a t i o n of t h e AS-204 f l i g h t panel f l u t t e r d a t a showed t h a t t h e most of t h e panel l o a d i n g was due t o random e x c i t a t i o n . Howe v e r , evidence of l i m i t e d amplitude panel f l u t t e r was p r e s e n t a s expected. Both types of l o a d i n g s were i n s i g n i f i c a n t f o r t h e AS-204 panels because t h e a c t u a l parameters a f f e c t i n g t h e s e l o a d i n g s were n o t conducive t o f l u t t e r on t h i s f l i g h t . A d d i t i o n a l i n f l i g h t f l u t t e r measurements w i l l be made on t h e S-IVB s t a g e of t h e AS-502 f l i g h t . �b. A p r o j e c t meeting was h e l d a t ARC w i t h r e p r e s e n t a t i v e s from ARC, MSFC and ARAP t o d i s c u s s f u r t h e r d a t a a n a l y s i s and d a t a r e p o r t i n g of t h e two-d h e n s i o n a l wavy-wall d a t a o b t a i n e d i n t h e Ames % 2 - f o o t t r a n s o n i c wind t u n n e l . A d d i t i o n a l t e s t s t o o b t a i n boundary l a y e r i n f o r m a t i o n i n t h e h i g h s u b s o n i c and t r a n s o n i c Mach number r e g i o n s were a l s o o u t l i n e d . These t e s t s w i l l a l s o be performed i n t h e Ames 2-foot t u n n e l . 6. Quas i-Steady O s c i l l a t i n g Wake and F r e e 0s c i l l a t i n g o Configuration Dynamic T e s t s on ~ a t u r n / ~ p o l lForebody T e s t s on t h i s phase of t h e program were conducted from February 14 t o March 1, 1968, and a g a i n from March 6 t o 13. This phase of t h e t e s t was t o determine upstream communication e f f e c t s of 30-degree cone on v a r i o u s wake s o u r c e s . A f r e e - o s c i l l a t i o n b a l a n c e was i n s t a l l e d i n a 30-degree cone, which could be moved t o v a r i o u s l o c a t i o n s behind t h e wake s o u r c e s . The v a r i o u s wake s o u r c e s were equipped w i t h e i t h e r Bytrex o r K i s t l e r X-ducers , depending on what wake s o u r c e was being employed. T e s t s were s a t i s f a c t o r y w i t h o n l y minor problems. From March 1 t o March 6 (between t h e above two p e r i o d s ) , a f r e e o s c i l l a t i o n dynamic t e s t was conducted on a S a t u r n / A p o l l o forebody c o n f i g u r a t i o n . This program, removed from t h e s c h e d u l e because t h e tower came l o o s e on t h e model, w i l l be rescheduled a t a l a t e r d a t e . �VII. A. DYNAMICS AND FLIGHT MECHANICS DIVISION Multi-Projects 1. Guidance a. Synchronous O r b i t Study (New) This s t u d y , s t a r t e d a b o u t one year ago on a low p r i o r i t y b a s i s , i s n e a r l y complete, and should be documented by l a t e May 1968. The a n a l y s i s was d i r e c t e d toward determining t h e c o m p a t i b i l i t y of t h e IGM guidance system and t h e n e c e s s a r y t a r g e t i n g s u r f a c e f o r a c h i e v i n g a n e a r t h synchronous o r b i t using t h e S a t u r n V launch v e h i c l e . P a r t I of t h e s t u d y e s t a b l i s h e d t h e guided t r a j e c t o r y i n t o e a r t h synchronous a l t i t u d e a t a n o r b i t a l i n c l i n a t i o n e q u a l t o t h e l a t i t u d e of t h e launch s i t e , and P a r t 11 e s t a b l i s h e d a guided t r a j e c t o r y i n t o a t r u e e a r t h synchronous o r b i t . ( ~ G I N o r t h r o p ) b. S-IVB S o f t Lunar Landing Study (Ref: May 1966, p. 33) This s t u d y was i n i t i a t e d a b o u t 1 1 / 2 y e a r s ago on a low p r i o r i t y b a s i s t o e s t a b l i s h t h e f e a s i b i l i t y of using t h e b a s i c S a t u r n V Launch Vehicle and determine t h e r e q u i r e d changes t o t h e t a r g e t i n g philosophy f o r IGM t o g u i d e each phase of t h e m i s s i o n . The payload above t h e d r y S-IVB s t a g e on t h e l u n a r s u r f a c e i s approximately 35,000 pounds when t h e S-IVB s t a g e a c h i e v e s s o f t l a n d i n g v i a a l u n a r parking o r b i t . (~GINorthrop) An i n t e r i m review i s planned f o r e a r l y A p r i l . 2. Dynamics and Control a. GPS High Speed Analog (Ref: J a n . 1968, p. 41) A l l t h e t a p e s f o r t h e 1120 winds have been r e c e i v e d and checked o u t . Three t a p e s a r e a v a i l a b l e : (1) t o t a l wind p r o f i l e , ( 2 ) f i l t e r e d wind p r o f i l e , and ( 3 ) t u r b u l e n c e f i l t e r e d o u t of t h e t o t a l wind p r o f i l e . These t a p e s e x i s t f o r b o t h t h e s c a l a r and d i r e c t i o n a l winds. Using the o r i g i n a l 400 s c a l a r wind sample has e s s e n t i a l l y v e r i f i e d t h e 1120 s c a l a r wind p r o f i l e s . It i s planned t o s t u d y t h e v e h i c l e r e s p o n s e u s i n g t h e d i r e c t i o n a l winds t o v e r i f y conclusions of the s c a l a r wind s t u d y . A l l s t u d i e s t o d a t e s t i l l show t h a t t h e s y n t h e t i c p r o f i l e i s s l i g h t l y c o n s e r v a t i v e f o r t h e S a t u r n V. (DDD) �b. Pre-Launch Wind Monitoring (New) A c o n t r a c t was awarded i n March t o Martin-Denver t o e s tabl i s l l a b e t t e r technique f o r pre-launch wind monitoring. The wind is t o be s e p a r a t e d i n t o quas i - s teady and t u r b u l e n c e p r o f i l e s w i t h perk i s t e n c e c h a r a c t e r i s t i c s a t t a c h e d t o each. The p r e d i c t e d launch v e h i c l e is t h e n based on t h e s e winds s e v e r a l hours b e f o r e launch. chara art in) B. Saturn V 1. Mission P r o f i l e S-IVB Disposal Analysis (Ref: 0ct.-Nov. 1967, p. 45): The l u n a r i m p a c t l s l i n g s h o t mode of S-IVB d i s p o s a l i m p l i e s adding a n e g a t i v e impulse t o t h e s p e n t s t a g e soon a f t e r s p a c e c r a f t s e p a r a t i o n , a l t e r i n g t h e t r a j e c t o r y s o t h a t i t e i t h e r impacts t h e moon, passes i n t o a " s l i n g shot" c o r r i d o r where escape v e l o c i t y i s a t t a i n e d , o r a c h i e v e s a v e r y long l i f e t i m e e l l i p t i c a l o r b i t . The a t t i t u d e of t h e s p e n t S-IVB s t a g e a t t h e commencement of r e s i d u a l p r o p e l l a n t dumping was v a r i e d i n a s e a r c h f o r a l u n a r i m p a c t l n o n e a r t h r e t u r n c o r r i d o r wide enough t o cover a l l propellant residual uncertainties. Such a c o r r i d o r was found a t an a t t i t u d e a n g l e of 180" w i t h r e s p e c t t o t h e l o c a l h o r i z o n t a l ( p e r p e n d i c u l a r t o t h e l o c a l r a d i u s v e c t o r and p o i n t i n g away from t h e moon), which a s s u r e s no e a r t h r e t u r n c o n s i d e r i n g a l l earth-moon g e o m e t r i e s , a l l p r a c t i c a b l e times of AV a p p l i c a t i o n , and +3 sigma i n j e c t i o n a c c u r a c i e s . The r e s u l t s of t h i s Boeing s t u d y have been p r e s e n t e d t o t h e F l i g h t Mechanics Panel (~AMI~oeing) and t h e Guidance, Performance, and Dynamics Subpanel. 2. Dynamics and C o n t r o l a. S a t u r n V T h e o r e t i c a l T r a n s f e r Functions (New) A c o n t r a c t has been awarded t o Dynamic S c i e n c e s t o develop a t h e o r e t i c a l t r a n s f e r f u n c t i o n f o r t h e S a t u r n V s p a c e v e h i c l e . The approach t o be developed can be used f o r wind t u r b u l e n c e r e s p o n s e s t u d i e s and f l i g h t e v a l u a t i o n procedures. (DD) b. Local Angle-of-Attack (New) A t h e e f f e c t s of To be included t i o n , and l i f t E f f e c t s on Vehicle Dynamic Response c o n t r a c t has been awarded C h r y s l e r - H u n t s v i l l e t o determine l o c a l a n g l e of a t t a c k on v e h i c l e r e s p o n s e f o r t h e S a t u r n V. i n t h e s t u d y a r e t h e v e h i c l e e l a s t i c modes, g u s t p e n e t r a growth e f f e c t s . (DD) �c. LM E x t r a c t i o n from S-IVB ( ~ e w ) A meeting was a t t e n d e d a t M S C ' S r e q u e s t t o d i s c u s s LM e x t r a c t i o n from t h e S-IVB s t a g e . Data which i n d i c a t e d inadequate s e p a r a t i o n c l e a r a n c e s u s i n g t h e S e r v i c e Module RCS t o e x t r a c t t h e LM i n t h e presence of c e r t a i n malfunctions were p r e s e n t e d . A s p r i n g powered method of LM e x t r a c t i o n was then introduced a s t h e mode of LM e x t r a c t i o n from t h e S-IVB s t a g e . The assumptions, t h e i n p u t d a t a , and t h e d i g i t a l program used f o r t h e dynamics s t u d i e s were r e v i s e d . (DC) 3. P r o j e c t Information A p p l i c a b l e t o I n d i v i d u a l Vehicles a. AS-504 Dynamics Data (New) A document c o n t a i n i n g updated SA-504 s t r u c t u r a l dynamic c h a r a c t e r i s t i c s f o r use i n f l i g h t c o n t r o l system d e s i g n and v e r i f i c a t i o n has been prepared. R e f l e c t e d i n t h e a n a l y s i s a r e r e c e n t payload and S - I 1 LH2 t a n k s t i f f n e s s changes, a s w e l l a s t h e dynamic e f f e c t s of r e l o c a t i n g t h e C o n t r o l / E ~ Sr a t e gyro t o t h e bottom of i t s I U mounting p l a t e . This document i s being d i s t r i b u t e d a s f i n a l d a t a f o r c o n t r o l (~~S/~oeing) system v e r i f i c a t i o n . C. Saturn I B P r o j e c t I n f o r m a t i o n A p p l i c a b l e t o I n d i v i d u a l Vehicles a. AS-205 C a n t i l e v e r Modes (New) A c a n t i l e v e r e d bending v i b r a t i o n a n a l y s i s f o r AS-205 was comp l e t e d . P e r t i n e n t d a t a o b t a i n e d from t h e a n a l y s i s were published i n R-AERO-DD-~~-~~ (DDS) . b. AS-205 Bending A n a l y s i s (New) A bending v i b r a t i o n a n a l y s i s has been performed f o r t h e AS-205 v e h i c l e t o provide d a t a f o r a f i n a l c o n t r o l system v e r i f i c a t i o n . F e a t u r e s i n c l u d e a n improved r e p r e s e n t a t i o n of t h e i n t e r s t a g e s t r u c t u r e developed by Lockheed and use of s t a t i c t e s t s t i f f n e s s v a l u e s f o r t h e spacecraft structures. (DDS) �D. S a t u r n Apollo A p p l i c a t i o n s rrogram 1. Cluster a. Mission P r o f i l e (1) AAP-~/UP-~ Experiment Timeline (Ref: P. 48) March 1967, "AAP-~/AAP-~Experiment Timeline A n a l y s i s , I f dated January 15, 1968 has been published. This document, which updates a s i m i l a r one dated January 9 , 1968, r e f l e c t s changes i n t h e experiment l i s t , performance requirements, m i s s i o n p l a n , and crew c y c l e . The r e p o r t i n c l u d e s a b a s i c m i s s i o n p l a n , experiment complement and time r e q u i r e m e n t s , d a i l y experiment crew time a l l o c a t i o n s , and a d e t a i l e d t i m e l i n e of a c t i v i t i e s . Updates of t h e experiment t i m e l i n e s f o r t h i s m i s s i o n a r e continuous, a s c u r r e n t changes r e q u i r e d through use of t h e F l i g h t D i r e c t i v e 3C and new b a s e l i n e s c o n f i g u r a t i o n d e f i n i t i o n s a r e i n c o r p o r a t e d . The n e x t update i s expected t o be documented by A p r i l 1. ( ~ ~ M / ~ a r t i n ) (2) C o m p a t i b i l i t y Analysis f o r 1968, p. 44) Am (Ref: Dec. -Jan. 1967- ATM o p e r a t i o n a l time requirements f o r t h e 56-day AAP-314 miss ion have been subs t a n t i a l l y reduced through simultaneous s c h e d u l i n g of compatible experiments. Requirements of each experiment w i t h r e s p e c t t o p o i n t i n g and c o n t r o l were d i v i d e d i n t o f i v e modes of o p e r a t i o n . Experiments w i t h modes of t h e same o r l e s s s t r i n g e n t p o i n t i n g and cont r o l requirements a r e scheduled t o r u n s i m u l t a n e o u s l y w i t h t h e e x p e r i ment c o n t r o l l i n g t h e c l u s t e r a t t i t u d e . It was found t h a t i f compatible experiments a r e o p e r a t e d s i m u l t a n e o u s l y , i t i s p o s s i b l e t o almost double t h e amount of d a t a - t a k i n g time f o r t h e t o t a l ATM package of experiments. It a p p e a r s t h a t we w i l l be a b l e t o meet t h e d a t a - t a k i n g requirements of ATM by using t h i s approach. This philosophy was p r e s e n t e d t o D r . M u e l l e r , March 1 5 , 1968. Timelines a r e being g e n e r a t e d f o r b o t h a one-man and two-man requirement f o r simultaneous Am experiment o p e r a t i o n . Also, t h e human f a c t o r element of one-versus-two-man o p e r a t i o n i s being e v a l u a t e d , a l o n g w i t h t h e impact of simultaneous o p e r a t i o n s of s e v e r a l experiments on s y s tem and sub-sys tems r e q u i r e m e n t s . �AAP C o m p a t i b i l i t y Analysis i s a t a s k covered under t h e M a r t i n AAP I n t e g r a t i o n C o n t r a c t . As a r e s u l t of a v i s i t t o Denver, M a r t i n was r e c e n t l y d i r e c t e d t o b e g i n t h i s t a s k . The c o m p a t i b i l i t y a n a l y s i s was envisioned a s a f u n c t i o n t o be performed a f t e r r e l e a s e of t h e Design Reference Mission Document ( s e e p a r a . D.L.a.(5), AAP Base1i n e M i s s i o n D e s c r i p t i o n Document). I n the c o m p a t i b i l i t y a n a l y s i s , the miss i o n , e x p e r i ments, and s y s tems con£ l i c t s and i n c o m p a t i b i l i t i e s evidenced i n t h e f i r s t v e r s i o n of t h e DRMD w i l l be i d e n t i f i e d and documented. From t h a t p o i n t on, t h e c o m p a t i b i l i t y a n a l y s i s w i l l be c o n t i n u o u s l y updated a s old i n c o m p a t a b i l i t i e s a r e r e s o l v e d and new ones a p p e a r . A t t h e meeting i n Denver, M a r t i n was d i r e c t e d t o (a) produce a f u n c t i o n a l flow diagram of t h e t a s k , (b) make a d e t a i l e d o u t l i n e of t h e documentation, (c) produce a l i s t of purposes and o b j e c t i v e s of the task, (d) make a l i s t of i n p u t s and o u t p u t s f o r t h e t a s k . A d d i t i o n a l d e t a i l s a r e contained i n a t r i p r e p o r t d a t e d March 1 8 . Mart i n ) (3) (DAM/ AAP-3A Launch Opportunity and Rendezvous (New) A launch o p p o r t u n i t y and rendezvous a n a l y s i s f o r AAP-3A m i s s i o n i s being made. AAP-3A l i f t - o f f i s scheduled (ML-13) t o occur a f t e r day 119 ( r e f e r e n c e d t o U P - 2 l a u n c h ) . The AAP-2 workshop o r b i t The mishas decayed t o a 219 n.mi. c i r c u l a r o r b i t a t AAP-3A l i f t - o f f . s i o n p r o f i l e f o r AAP-3A r e q u i r e s a n i n j e c t i o n a t p e r i g e e of a n 81/120 n.mi. o r b i t . A f t e r a c o a s t of one r e v o l u t i o n , r a i s e apogee t o 209 n.mi. A t apogee make a phase maneuver t o a 209/199 o r b i t . A f t e r c o a s t i n g one r e v o l u t i o n , c i r c u l a r i z e i n t o a 209 n.mi. o r b i t ( c o - e l l i p t i c ) , c o a s t a minimum of 30 minutes and perform TPI and TPF. The nominal phasing r e q u i r e s t h a t AAP-3A l e a d AAP-2 by 6.438 degrees a t AAP-3A launch. The b e s t p a i r of in-phase, i n - p l a n e launch o p p o r t u n i t i e s f o r AAP-3A o c c u r s on day 129. For in-phase launches on t h i s day, t h e plane changes r e q u i r e d cause a payload d e g r a d a t i o n of l e s s t h a n 10 pounds. The launch parameters f o r t h e two launch o p p o r t u n i t i e s a r e a s f o l l o w s : �Timc - F i r s t Opportunity Day: 1Ir:Min: Sec Second Opportunity 129: 2:43:45.8 129:4:31:51.9 Node (deg) I n c l . (deg) Plane Change A s i m i l a r a n a l y s i s was made f o r AAP-112 documented i n R-AERO-DAO-4-68, March 2 1 , 1968. (DAO) (4) - CSM/LM A l t e r n a t e Mission Sun Observation Time Aug.-Sept. 1967, p. 46) (Ref: One of t h e f a c t o r s determining t h e d e s i r a b i l i t y of t h e LM/ATM f l y i n g decoupled from the OWS i n a h i g h i n c l i n a t i o n o r b i t i s t h e t o t a l amount of sun o b s e r v a t i o n time a v a i l a b l e d u r i n g t h e e n t i r e miss i o n . A s t u d y made d u r i n g t h i s r e p o r t i n g period g i v e s t h e maximum and minimum t o t a l times f o r t h e m i s s i o n d u r i n g which t h e s p a c e c r a f t i s o u t s i d e t h e e a r t h ' s umbra ( t h e e x a c t t o t a l time depending on t h e launch time of d a y ) . These maximum and minimum times a r e p l o t t e d v s i n c l i n a t i o n f o r a l t i t u d e s of 150 NM, and 200 NM. It was assumed t h a t t h e launch d a t e was i n January 1971 and t h e l e n g t h of t h e m i s s i o n was 28 days. I n a d d i t i o n t o t h i s , a n e s t i m a t e was made of t h e percentage of t h e o r b i t s t h a t t h e sun and the two t r a c k i n g s t a r s , Canopus and Achernar, a r e a l l t h r e e simult a n e o u s l y o c c u l t e d by t h e e a r t h . Two c a s e s were considered: (5) (a) Launch January 1, 1971, a t 3 p.m. EST i n t o a 50 p e r c e n t i n c l i n a t i o n , 200 NM o r b i t . For a 28-day m i s s i o n , a l l t h r e e w i l l be s i m u l t a n e o u s l y o c c u l t e d a t some time f o r 25 p e r c e n t of t h e orbits. (b) Launch March 1, 1970, a t 3 p.m. EST i n t o a 28.95O i n c l i n a t i o n , 230-NM o r b i t . For a 56-day m i s s i o n , a l l t h r e e w i l l be s i m u l t a n e o u s l y o c c u l t e d a t some time f o r 40 p e r c e n t of t h e o r b i t s . (DAO) Mission P r o f i l e f o r C l u s t e r Miss i o n (Ref: 1967-68, p. 43) Dec. -Jan. A p r e l i m i n a r y m i s s i o n p r o f i l e has been completed f o r the AAP-2 m i s s i o n . The launch v e h i c l e c o n s i s t s of t h e 208 S-IB s t a g e and the 2 1 2 S-IVB s t a g e which i n s e r t s i t s e l f and payload c l o s e t o apogee i n t o a 230 x 215 NM o r b i t . Oxidizer and f u e l dump sequences a r e �immediately i n i t i a t e d t o c i r c u l a r i z e i n a 230-mile o r b i t . SLA/Nose cone j e t t i s o n d u r i n g S-IVB powered f l i g h t was used f o r t h i s p r o f i l e . P a r a m e t r i c performance d a t a f o r t h e AAP-1 miss i o n using v e h i c l e 207 have been g e n e r a t e d . S p e c i f i c c a s e s f o r e a r l y , l a t e , and t h e w o r s t launch window cases a r e being s t u d i e d . (DAP) b. Dynamics and Control (1) OWS o r i e n t a t i o n S t u d i e s (Ref: P . 46) Dec. -Jan. 1967-68, The c o n t r o l system impulse requirements f o r t h e C l u s t e r I M - 1 3 m i s s i o n schedule a r e being determined. The s t u d y is concerned w i t h t h e e f f e c t s of man motion, aerodynamic g r a v i t y g r a d i e n t , v e h i c l e v e n t s , s e n s o r e r r o r s , o r b i t decay, docking d i s t u r b a n c e s , and g r a v i t y g r a d i e n t s t o r a g e . The p r e s e n t b a s e l i n e has a r e a c t i o n j e t w i t h pseudo-rate c o n t r o l d u r i n g Mission 1, 2, and 3A and has CMG f o r t h e o t h e r m i s s i o n s . The p r o p u l s i o n system i s s i z e d f o r 220,000 l b - s e c of impulse using 25 l b engines w i t h a minimum impulse of 1.25. P r e s e n t s t u d i e s i n d i c a t e a impulse requirement of 130 l b s - s e c . per o r b i t t o keep t h e workshop i n t h e X-POP o r i e n t a t i o n mode and t o t a l impulse requirement s l i g h t l y above 200,000 l b s - s e c . (DD) c. P r o j e c t Information A p p l i c a b l e t o I n d i v i d u a l Vehicles (1) AAP-2 Mission Rigid Body Response Study (New) A r i g i d body response a n a l y s i s of t h e f i r s t s t a g e f l i g h t of t h e AAP-2 m i s s i o n is being performed. F l i g h t c o n d i t i o n s of Mach 1, qa max, q max and n e a r IECO a r e being i n v e s t i g a t e d . Rigid body responses a r e being obtained f o r t h e RSS bending moments f o r t h e s e c a s e s . Aerodynamic d a t a r e c e i v e d f o r t h e workshop have n o t included any d a t a concerning coupling between planes due t o t h e s o l a r p a n e l s b e i n g o u t of p l a n e ; t h e r e f o r e , t h i s e f f e c t has n o t been included i n t h e p r e s e n t a n a l y s i s . The 95 p e r c e n t i l e winds a r e b e i n g used, and i t i s expected t h a t , i n t h e q max c a s e , ' t h e 8' gimbal l i m i t w i l l be reached f o r t h e RSS bending moment c o n d i t i o n s , b u t l o s s of c o n t r o l i s n o t expected. (DC) (2) S L , / N O SCone ~ J e t t i s o n a s a n I n t e g r a l P i e c e (Ref: Jan.-Feb. 1968, p. 46) Development of a scheme t o j e t t i s o n t h e SLA and nose cone as a n i n t e g r a l p i e c e i n t h e AAP-2 and AAP-4 m i s s i o n s c o n t i n u e s . A d d i t i o n a l t r a j e c t o r i e s of t h e s I , ~ / n o s e cone r e l a t i v e t o t h e S-IVB s t a g e and payload have been g e n e r a t e d a s d a t a and assumptions have been r e f i n e d . �P r e l i m i n a r y c l e a r a n c e d a t a were f u r n i s h e d t o R-AERO-P f o r p r e s e n t a t i o n a t an AAP Systems Review f o r D r . von Braun on January 24, 1968. These d a t a were documented i n R-AERO-DCC-1-68. A more r e c e n t s t u d y has been made i n which two base t h r u s t v e c t o r c a n t a n g l e s f o r t h e LES tower j e t t i s o n motor were compared. Both base c a n t a n g l e s , 3.8 degrees and 2.5 d e g r e e s , provide c l e a r a n c e s , though t h e s m a l l e r (2.5") b a s e c a n t i s p r e f e r a b l e because t h e margin of c l e a r a n c e f o r t h e 3.8 degrees base c a n t a n g l e i s s m a l l . (DC) 2. OWS P a s s i v e A t t i t u d e Control (Ref: Dec.-Jan. 1967-68, p. 46) The p a s s i v e s t a b i l i t y s t u d y of approximate models of space v e h i c l e c l u s t e r s was completed. R e s u l t s of t h e "angular momentum" approach a r e summarized i n LMSC TM 54130-171 e n t i t l e d " R o t a t i o n a l Motion of a S a t e l l i t e a b o u t I t s Center of Mass Under G r a v i t a t i o n a l and AeroThe approach uses t h e Bogolyubov method of a v e r a g i n g dynamic Torques . ' I on t h e aerodynamic and g r a v i t y g r a d i e n t t o r q u e s . The r e s u l t s a g r e e w i t h complete dynamic computer r u n s . A study t o define the i n i t i a l conditions f o r g r a v i t y gradient c a p t u r e of t h e s t o r e d c o n f i g u r a t i o n has been i n i t i a t e d . S t a b i l i t y over t h e f i r s t N-orbits w i l l be considered. (~CAILockheed) 3. ATM AAP Launch Vehicles C a n t i l e v e r Modes (New) C a n t i l e v e r e d bending v i b r a t i o n a n a l y s e s f o r t h e AAP launch v e h i c l e s were made. Each v e h i c l e was analyzed i n t h e l i f t - o f f f u e l condit i o n and w i t h a l l p r o p e l l a n t removed from t h e S-IVB and S-IB s t a g e s . Data (DDS) . o b t a i n e d from t h i s s t u d y a r e g i v e n i n R - A E R O - D D - ~ ~ - ~ ~ 4. Unmanned Rendezvous a. Mission P r o f i l e (1) Unmanned Rendezvous - Tether (New) A b r i e f s t u d y was made d u r i n g t h i s p e r i o d t o determine t h e f e a s i b i l i t y of docking a n unmanned LM/ATM t o t h e OWS by u s i n g a t e t h e r . The s t u d y was e s s e n t i a l l y i n two p a r t s : �(a) Tether deployment between t h e OWS and t h e LM/ATM which w a s i n v e s t i g a t e d by t h e M a r t i n Company, Denver, Colorado. (b) R e t r i e v a l techniques whereby t h e LM/ATM could b e brought w i t h i n c l o s e proximity of t h e OWS by making d i s c r e t e p u l l s on t h e t e t h e r a f t e r attachment. Two d i f f e r e n t r e t r i e v a l techniques were i n v e s t i g a t e d . The f i r s t r e q u i r e s t h a t t h e LM/ATM be i n s e r t e d i n t o a n e a r c i r c u l a r o r b i t c o n c e n t r i c w i t h the OWS o r b i t e i t h e r above and c o n s i d e r a b l y ahead of t h e OWS o r below and c o n s i d e r a b l y behind t h e OWS. The LM/ATM i s t h e n caused t o go through a s e r i e s ( 3 o r 4) of n e a r Hohmann t r a n s f e r s by p u l l i n g on t h e t e t h e r . The f i n a l c i r c u l a r a t t i t u d e of each t r a n s f e r i s made t o l i e n e a r e r and n e a r e r t o t h a t of t h e OWS u n t i l t h e LMIATM i s i n t h e same o r b i t and q u i t e n e a r t h e OWS. I n t h e o t h e r r e t r i e v a l method, t h e LN/ATM i s i n s e r t e d i n t o a n o r b i t of e q u a l period w i t h t h e OWS, b u t w i t h a d i f ferent eccentricity. (The LM/ATM remains i n a n e a r l y c o n s t a n t i n e r t i a l d i r e c t i o n from t h e OWS i n t h i s o r b i t . ) By p u l l i n g on t h e t e t h e r a t s p e c i f i c times, t h e LM/ATMo r b i t a l e c c e n t r i c i t y can be brought n e a r e r and n e a r e r t o t h a t of t h e OWS u n t i l a g a i n t h e two a r e brought i n t o c l o s e proximity. (DAO) (2) Unmanned Rendezvous - Using S-IVB S t a g e (New) To determine t h e f e a s i b i l i t y of u s i n g t h e S-IVB and I U s t a g e t o p l a c e t h e LMIATM w i t h i n 500 f e e t of t h e OWS, a s t u d y w a s made us ing t h e f o l l o w i n g ground r u l e s : (a) The S-IVB w i l l have r e s t a r t c a p a b i l i t y . (b) Two R-IE l o n g i t u d i n a l t h r u s t e r s w i l l be provided. (c) LM r a d a r w i l l be used f o r v e r n i e r maneuvers. (d) The I U l i f e t i m e w i l l be extended t o 1 0 112 h o u r s . (e) Guidance and Navigation w i l l be improved by 213. (f) The launch window requirement i s 30 seconds. (g) The S-IVB i s i n s e r t e d a t a p e r i g e e a l t i t u d e of 80 NM. A nominal t i m e l i n e and m i s s i o n p r o f i l e was developed which s a t i s f i e d t h e s e ground r u l e s and a p r o p e l l a n t budget f o r t h e nominal p r o f i l e was prepared. The most promising f l i g h t p r o f i l e �c o n s i s t s of d i r e c t i n j e c t i o n i n t o a n e l l i p t i c a l phasing o r b i t , a minor c o r r e c t i o n a f t e r 112 o r b i t using t h e S-IVB a u x i l i a r y p r o p u l s i o n system o r workshop a u x i l i a r y c o n t r o l (WAC) system, a f t e r 1 114 t o 1 314 o r b i t c i r c u l a r i z a t i o n w i t h a second S-IVB burn, a l l c o n t r o l l e d by t h e I U . These maneuvers a r e followed t y p i c a l l y by 4 v e r n i e r b u r n s , l e s s t h a n 4 m/s each, u s i n g t h e a u x i l i a r y p r o p u l s i o n system. The s t u d y i s proceeding w i t h an a n a l y s i s of t h e consequences of i n s e r t i o n e r r o r s a t c i r c u l a r i z a t i o n due t o S-IVB p r o p u l s i o n , n a v i g a t i o n , and guidance. (~~O/~orthrop) b. Guidance AAP-4 LM/ATM Unmanned Rendezvous (New) The f e a s i b i l i t y of a c h i e v i n g unmanned rendezvous of t h e uu ATM w i t h t h e o r b i t a l workshop has been s t u d i e d . The b a s i c K e p l e r i a n a n a l y s i s and IGM t a r g e t i n g , a l o n g w i t h d e t a i l e d guidance and n a v i g a t i o n a n a l y s i s of t h e d i f f e r e n t approaches t o rendezvous, were achieved through The a n a l y s i s included u s i n g t h e LM/ATM prot h e e f f o r t s of R-AERO-DG. p u l s i o n system t o a c h i e v e rendezvous and u s i n g t h e S-IVB s t a g e w i t h a proposed second i g n i t i o n of t h e S-IVB s t a g e . A f t e r t h e second S-IVB i g n i t i o n , t h e f i n a l rendezvous maneuvers were achieved u s i n g t h e APS (DG) p r o p u l s i o n s y s tern. E. General Dynamic Response of a Launch Vehicle Model (New) A s e r i e s of damping and response t e s t s on t h e 115 s c a l e model S a t u r n I w a s r u n . T h e o r e t i c a l p r e d i c t i o n s based on r e s o n a n t response d a t a a r e shown t o be a c c u r a t e f o r e i t h e r s i n u s o i d a l o r random e x c i t a t i o n . However, experimental r e s u l t s on response peaks due t o combined and s i n e random e x c i t a t i o n s did n o t a g r e e w i t h a n a l y t i c a l p r e d i c t i o n s . I n another t e s t , t h e s t r u c t u r a l damping i n one mode was found t o be independent of (DD~/~ockheed). r e s p o n s e amplitude i n a n o t h e r mode. �VIII. A. FLIGHT TEST ANALYSIS DIVISION Special Projects Office 1. AS-204 F l i g h t E v a l u a t i o n The AS-204 F l i g h t E v a l u a t i o n has r e v e a l e d t h a t a l l major systems performed w i t h i n d e s i g n l i m i t s and c l o s e t o p r e d i c t e d v a l u e s throughout f l i g h t . Although no malfunctions o r d e v i a t i o n s t h a t a d v e r s e l y a f f e c t e d f l i g h t o r m i s s i o n accomplishment o c c u r r e d , a few r e f i n e m e n t s based on f l i g h t t e s t r e s u l t s a r e being i n c o r p o r a t e d f o r f u t u r e f l i g h t s . These a r e d i s c u s s e d i n d e t a i l i n t h e r e p o r t , " R e s u l t s of t h e Fourth S a t u r n I B Launch Vehicle T e s t F l i g h t AS-204,'' by t h e S a t u r n F l i g h t E v a l u a t i o n Working Group. This r e p o r t w i l l be d i s t r i b u t e d by A p r i l 1 2 , 1968. The AS-204 t e s t f l i g h t demonstrated t h e s u c c e s s f u l performance of t h e o r b i t a l s a f i n g experiment i n c l u d i n g p r o p e l l a n t v e n t i n g , p r o p e l l a n t dump, cold helium dump, and s t a g e / e n g i n e pneumatic s u p p l y dump. This f l i g h t a l s o demonstrated t h e adequacy of t h e a t t i t u d e c o n t r o l and v e h i c l e e l e c t r i c a l systems t o perform f o r extended d u r a t i o n i n o r b i t . 2. F l i g h t E v a l u a t i o n Panel The f i f t e e n t h meeting of t h e Apollo F l i g h t E v a l u a t i o n Panel took p l a c e a t MSC on March 5 , 1968. Main d i s c u s s i o n items were launch and f l i g h t anomalies d e f i n i t i o n s , e v a l u a t i o n r e p o r t s e c u r i t y c l a s s i f i c a t i o n , range z e r o and l i f t - o f f times d e f i n i t i o n s , and e v a l u a t i o n p l a n s f o r Apollo 6 (AS-502). An e v a l u a t i o n summary of t h e Apollo 5 (AS-204) f l i g h t was p r e s e n t e d by MSC and MSFC. 3. Apollo A p p l i c a t i o n s - FEWG-Payload E x t e n s i v e e f f o r t s have been made d u r i n g t h i s p e r i o d t o a r r i v e a t t a s k d e f i n i t i o n and d e s c r i p t i o n s of work d e s i r e d from t h e Payload I n t e g r a t i o n C o n t r a c t o r s r e l a t e d t o planning f o r and r e p o r t i n g t h e r e s u l t s of t h e p o s t f l i g h t e v a l u a t i o n . These e f f o r t s were n o t involved i n t h e phase C work, and many a s p e c t s have n o t r e a d i l y been made c l e a r , p a r t i c u l a r l y a s t o t h e c a r r i e r systems. This a r e a i s s t i l l being pursued and w i l l b e r e s o l v e d soon. E f f o r t s have been made t o g e t t h e proper i d e n t i f i c a t i o n of p o s t £1 i g h t d a t a hand1 ing and e v a l u a t i o n f u n c t i o n s i n t o t h e Experiment I n t e g r a t i o n Requirement Documents (EIRD). This s e c t i o n , which should l o g i c a l l y be a t t h e end of t h e document f o l l o w i n g t h e Mission Operations S e c t i o n , has n o t been a p p e a r i n g . A l l d e t a i l s a r e n o t y e t a v a i l a b l e , b u t t h e AAP Program O f f i c e has agreed t o t h i s item and w i l l b e g i n implementation. The d e t a i l s of t h e s a t i s f a c t i o n of t h e s e requirements w i l l be p r e s e n t e d Payload (FEWG-P) documents. i n t h e v a r i o u s F l i g h t E v a l u a t i o n Working Group - �B. F l i g h t Mechanics Branch 1. Saturn I B a. 205/CS~-101 Rendezvous Mission Work was i n i t i a t e d February 1, 1968, t o g e n e r a t e a wind b i a s e d and a n unbiased t r a j e c t o r y p r o f i l e f o r t h e 205 m i s s i o n . The S-IB t i l t programs, S-IVB p r e s e t t i n g s , and a s s o c i a t e d t r a j e c t o r i e s were comp l e t e d on February 13. These t r a j e c t o r i e s were g e n e r a t e d u s i n g a 0.7% t h r u s t b i a s . On March 1 3 , i t was agreed by R-AERO and R-P&VE t h a t t h e t h r u s t b i a s should be reduced t o 0.4% and t h a t t h e S-IB s t a g e drag coeff i c i e n t should be r e v i s e d . These changes were i n c o r p o r a t e d i n t h e unbiased t r a j e c t o r y p r o f i l e . A t p r e s e n t , it a p p e a r s t h a t t h e S-IVB u s a b l e p r o p e l l a n t s a r e a b o u t 300 pounds g r e a t e r than t h e r e q u i r e d FPR. The o r b i t a l t r a j e c t o r y is s t i l l n o t complete because of i n s u f f i c i e n t d a t a and o r b i t a l sequence changes. The d i s p e r s i o n a n a l y s i s i s a b o u t 90 p e r c e n t complete. This e f f o r t was delayed because t h e S-IVB propuls i o n d i s p e r s ions were n o t available. About 5 p e r c e n t of t h e a b o r t and a l t e r n a t e m i s s i o n t r a j e c t o r i e s have been g e n e r a t e d . Before t h i s m i s s i o n was o f f i c i a l l y c a n c e l e d , t h e f o l l o w i n g documents had been completed: (1) "AS-206lLM-2 Launch Vehicle Operat i o n a l F l i g h t T r a j e c t o r y D i s p e r s i o n A n a l y s i s , " d a t e d March 1 5 , 1968; and (2) "AS-206lLM-2 Launch Vehicle O p e r a t i o n a l F l i g h t T r a j e c t o r y , " d a t e d March 1 8 , 1968. c. 2061 207 Rendezvous The 206 v e h i c l e has been r e a s s i g n e d t o t h e d u a l 2061207 m i s s i o n . Government Furnished Documentation i s being prepared t o be forwarded t o CCSD t o g e n e r a t e t h e o p e r a t i o n a l t r a j e c t o r i e s and d i s p e r s ion analyses f o r t h i s mission. d. S a t u r n I B Q u a r t e r l y Performance Sununary The performance summary f o r t h e mainstream Apollo miss ions was d i s t r i b u t e d i n memorandum R-AERO-FMR-64-68, March 13, 1968. �2. Saturn V The "revised" f i n a l t r a j e c t o r y f o r AS-502 i s b e i n g d i s t r i b u t e a . A d i s t u r b i n g f a c t o r has been i n t h e S-IC s t a g e p r o p u l s i o n . It appears t h a t t h e "tag" v a l u e s had been updated a l o n g w i t h t h e r e v i s i o n s which allowed a f u e l s e n s o r c u t o f f , a b o u t 1 . 5 p e r c e n t i n c r e a s e i n t h r u s t . This r e s u l t e d i n a n e f f e c t i v e i n c r e a s e i n s p e c i f i c impulse s i n c e t h e flow r a t e remained r e l a t i v e l y unchanged. The r e v i s e d ECF (End Conditions of F l i g h t ) and PCF (Pred i c t e d c o n d i t i o n s of F l i g h t ) memos have been p u b l i s h e d . An update t o t h e D i s p e r s i o n A n a l y s i s is being v e r i f i e d and should be r e l e a s e d b e f o r e aunch. The P r o j e c t s O f f i c e has informed R-AERO-FMT t h a t t h e ~ P / 3 0 w i l l be o f f - l o a d e d 11,000 l b s i n s t e a d of t h e 6,000 l b s o r i g i n a l l y planned. As f a r a s EMT knows now, t h e r e a r e no r e q u i r e d p r e s e t t i n g changes. In-house range s a f e t y a n a l y s i s on t h i s m i s s i o n is c o n t i n u i n g . c. AS-503 D Mission TBC i s scheduled t o d e l i v e r t h e S-IC t i l t programs t o MSFC by A p r i l 3, 1968. TBC i s a l s o examining t h e f o l l o w i n g 8 c a s e s i n o r d e r t o s e l e c t t h e c a s e t h a t s a t i s f i e s t h e most c o n s t r a i n t s f o r t h e D mission: 70 2nd S-IVB burn 70 I' 11 11 0" - 10 p i t c h 45" It 11 yaw t o t h e l e f t 11 11 11 I1 The r e s u l t s of t h e s e c a s e s w i l l be a v a i l a b l e by A p r i l 3, 1968. It i s s l i g h t l y d i s t u r b i n g t h a t TBC has been engaged i n t h i s e f f o r t s i n c e February 2 1 , 1968, and s t i l l R-AERO-FM had t o s e l e c t which r u n s were t o be made f o r a p a r a m e t r i c s t u d y i n t h e shaping and t a r g e t i n g of t h e 503-D mission. �A demonstration of t h e Quick Response T a r g e t i n g Program (QRTP) was given t o MSFC p r i m a r i l y t o e v a l u a t e t h e c o n t r a c t u a l l i n e items 105 and 106. This program was designed and planned f o r r a p i d l u n a r t a r g e t i n g and o p e r a t i o n a l t r a j e c t o r y a n a l y s i s . The following i s a summary of t h i s demonstration: It was found t h a t t h e program was n o t r e a l l y o p e r a t i o n a l ; t h a t t h e p l o t s of t h e i n t e r c e n t e r t a r g e t o b j e c t i v e s were incomplete; t h a t t h e AV'S r e s u l t i n g from midcourse c o r r e c t i o n s r a n h i g h e r than expected ( j u s t w i t h i n t o l e r a n c e ) ; t h a t t h e s p l i t t i n g of t h e d u a l o p p o r t u n i t y time of launch d i d n o t o p e r a t e w i t h i n s p e c i f i c a t i o n s ; t h a t i n t h e e v e n t a time of launch was s e l e c t e d which caused something o t h e r than a n e x a c t azimuth which was on one of t h e i n p u t t a p e s , t h e deck (a) would n o t r u n , and (b) t h e f i x was t o r e c y c l e back t o GRR (which is u n d e s i r a b l e ) ; t h a t p o r t i o n s of t h e e a r t h parking o r b i t were being i n t e g r a t e d twice; t h a t a much l o n g e r p o r t i o n of t h e t r a n s l u n a r i n j e c t i o n was being i n t e g r a t e d by t h e on-board n a v i g a t o r t h a n was n e c e s s a r y ; t h a t t h e i n t e g r a t i o n s t e p s used i n b o t h c o a s t and powered f l i g h t were n o t optimum, b u t could be s i g n i f i c a n t l y i n c r e a s e d ; t h a t t h e documentation would n o t a l l o w experienced e n g i n e e r s t o work, decode, and r u n t h e program. On t h e p l u s s i d e , t h e program d i d accomplish t h e o v e r a l l job i n t h e s p e c i f i e d time l i n e ; t h e program was shown t o be s a t i s f a c t o r i l y continuous and a u t o m a t i c , and t h e program a l l o w s MSFC t o s a t i s f y i t s i n t e r c e n t e r commitments i n a s a t i s f a c t o r y manner. Also t h e program cont r i b u t e d t o t h e MSFC s t a t e of t h e a r t i n ( a ) use of burn polynomials f o r i s o l a t i o n and c a l i b r a t i n g w i t h two cOV' s ; (b) i n c r e a s i n g i s o l a t i o n r e 1 i a b i l i t y by i n t r o d u c t i o n of a d i s c o n t i n u i t y method which a l l o w s convergence of a l m o s t a l l l u n a r c a s e s ; ( c ) providing a n automated s p l i t launch time model; (d) providing m u l t i - c a s e s t a c k i n g c a p a b i l i t y ; and ( e ) p r o v i d i n g a continuous t a r g e t t o v e r i f i c a t i o n t o midcourse c a p a b i l i t y . e. O r b i t a l Debris Documents LMsc/HREc A 791053 and LMSC/HRECA 791097, "AS-502 S u r v i v a l and Risk Hazard Analyses," were reviewed and d i s t r i b u t e d . The 503 b o i l e r p l a t e o r b i t a l d e b r i s a n a l y s i s i s a b o u t 50 perc e n t complete. �C. Tracking and O r b i t a l Analysis Branch 1. Saturn I B Tracking and communications a n a l y s i s on t h e o p e r a t i o n a l t r a j e c t o r y launch phase has been completed. Documentation w i l l be delayed u n t i l t h e o r b i t a l t r a j e c t o r y i s a v a i l a b l e t o complete o r b i t a l coverage a n a l y s i s . The AS-206/LN-2 L / V o p e r a t i o n a l t r a j e c t o r y t r a c k i n g and communications a c q u i s i t i o n and l o s s times were r e c e i v e d from CCSD. S i n c e t h e m i s s i o n has been c a n c e l l e d , t h e d a t a w i l l n o t be d i s t r i b u t e d . 2. Saturn V (1) A considerable amount of in-house e f f o r t has been s p e n t i n a n a l y z i n g e a r t h and moon impacts of t h e AS-502 S-IVB s t a g e . The s t a g e i s i n j e c t e d i n t o a h i g h l y e l l i p t i c a l o r b i t (period of a b o u t 16 d a y s ) , and depending on time and d a t e of launch, t h e s t a g e could impact e i t h e r t h e moon o r t h e e a r t h on i t s f i r s t o r b i t . Some of t h e r e s u l t s have been docuand R-AERO-FT-6-68. These memoranda mented i n memoranda R-AERO-FT-~.-~~ p r e s e n t impact d a t a f o r t h e weeks of March 25 and A p r i l 1, r e s p e c t i v e l y . Data f o r t h e week of A p r i l 8 have a l s o been g e n e r a t e d . (2) M r . Tom Buckley, Bendix F i e l d Engineering Corporation, 16 days) i n s u p p o r t of GSFC, r e q u e s t e d g e o d e t i c d a t a (one f u l l o r b i t on t h e nominal AS-502 o r b i t a l t r a j e c t o r y . S i n c e t h e s e d a t a were n o t a v a i l a b l e i n t h e AS-502 o p e r a t i o n a l t r a j e c t o r y , t h e y were g e n e r a t e d in-house by t h i s o f f i c e . The i n f o r m a t i o n was assembled and s e n t t o M r . Buckley by l e t t e r d a t e d February 9, 1968. - ( 3 ) Transformations of t h r e e s t a t e v e c t o r s from MCCH s i m u l a t i o n s were provided t o M r . Cremin. These t r a n s f o r m a t i o n s were i n response t o MSC r e q u e s t f o r v e r i f i c a t i o n of n a v i g a t i o n v e c t o r u p d a t e s . M r . Cremin used t h e d a t a i n a memorandum t o t h e MSC Co-Chairman of t h e G&P Subpanel. ( 4 ) Because of a delayed i n i t i a t i o n of t h e i n e r t i a l hold b e f o r e t h e r e s t a r t of t h e S-IVB, t h e look-angle d a t a provided t o R-ASTR and s e v e r a l c o n t r a c t o r s w i l l be s l i g h t l y i n e r r o r . We have c o n t a c t e d M r . Ely, R-ASTR-I, who i n d i c a t e t h a t t h e o r i g i n a l in£ ormation would be a c c e p t a b l e . The v a r i o u s c o n t r a c t o r s were n o t i f i e d of t h i s s l i g h t change. �(1) S t u d i e s s i m i l a r t o t h e AS-502 S-IVB impact a n a l y s e s were performed on t h e AS-503 (UM) S-IVB s t a g e i n s u p p o r t of R-AERO-FM. It appears t h a t t h i s type of a n a l y s e s w i l l be r e q u i r e d on a l l t r a j e c t o r i e s which a r e h i g h l y e l l i p t i c a l and undergo b o t h s o l a r and l u n a r perturbations. (2) Tracking and communications coverage on t h e AS-503 b o i l e r p l a t e c o n f i g u r a t i o n was d i s t r i b u t e d under Memorandum R-AERO-FT1-68. (3) A memorandum, R-AERO-FT-7-68, showing t h e command coverage f o r t h e nominal and c o n t i n g e n c i e s c a s e s of t h e S-IVB r e s t a r t s has been d i s t r i b u t e d . This memorandum i n a d d i t i o n t o R-AERO-FT- 2-68, which p r e s e n t s t r a c k i n g and communications coverage on t h e p r e l i m i n a r y AS-503 a l t e r n a t e m i s s i o n p r o f i l e u t i l i z i n g t h r e e S-IVB b u r n s , r e p r e s e n t s a c o n s i d e r a b l e e f f o r t on our p a r t . These s t u d i e s were done i n conjunct i o n w i t h R-AERO-DA i n s u p p o r t of t h e G&P Subpanel and t h e FMP on t h e AS-503 manned miss i o n . (4) Meetings have been h e l d w i t h R-AERO-FM and TBC t o d i s c u s s c r i t e r i a used t o o b t a i n t e l e m e t r y coverage f o r t h e second r e s t a r t of t h e S-IVB on t h e manned m i s s i o n . These meetings should a i d TBC t o c l a r i f y c e r t a i n ground r u l e s t o shape t h e S-IVB b u r n s . c. General (1) TBC has completed SSR-167, "The E f f e c t of Launch AziThis e f f o r t was d e s i g n a t e d t o i n d i c a t e muth on Antenna Look Angles .I1 t h e v a r i a t i o n i n look a n g l e s d u r i n g launch, parking o r b i t , and t r a n s l u n a r i n j e c t i o n p e r i o d s , and was based on t h e AS-504 Reference T r a j e c t o r y and t h e l a t e s t a t t i t u d e t i m e l i n e s . The i n f o r m a t i o n was p r e s e n t e d t o R-ASTR and I-MO and was a l s o p r e s e n t e d a t t h e Reference T r a j e c t o r y Subpanel h e l d a t MSC on March 22, 1968. ( 2 ) NSL m i s s i o n s u p p o r t i s c u r r e n t l y i n v e s t i g a t i n g t h e S-Band ground s t a t i o n key-hole v a r i a t i o n s due t o t h e v a r i a b l e launch azimuth requirements of t h e LLM. 3. Apollo A p p l i c a t i o n s a. C l u s t e r Mission (1) Lifetime Analysis ( a ) The l a t e s t l i f e t i m e i n f o r m a t i o n on t h e ML-13 c l u s t e r m i s s i o n was p r e s e n t e d a t t h e Mission Requirements Panel on February 2 1 , 1968, and has been documented i n Memorandum R-AERO-FT-3-68. M r . Lavender p r e s e n t e d t h i s same i n f o r m a t i o n i n Washington on February 27. �(b) P r e s e n t planning on t h e c l u s t e r m i s s i o n is t o f l y t h e OWS t o a 230 n.m. a l t i t u d e . This a l t i t u d e w i l l g u a r a n t e e (-20) a n o r b i t a l l i f e t i m e t o complete f l i g h t s 1, 2 , 3A, 3 , and 4. The nominal decay w i l l provide enough l i f e t i m e t o complete t h e e n t i r e ML-13 s c h e d u l e of r e v i s i t s w i t h f l i g h t s 5 , 6, and 7 . I t may be p o s s i b l e t o b o o s t t h e OWS w i t h SIC RCS burns w i t h t h e CSM'S on f l i g h t s 1, 3A, o r 3 by approximately 5 o r 1 0 n.m., and t h i s would i n c r e a s e t h e l i f e t i m e of t h e OWS. These b o o s t s would be n e c e s s a r y only i f t h e OWS decayed a l o n g t h e -20 decay curve. We have i n v e s t i g a t e d b o o s t i n g t h e OWS a t t h e beginning of each CSM rendezvous o r j u s t b e f o r e d e o r b i t of t h e CM. This means t h a t b o o s t s a r e p o s s i b l e a t 1, 29, 119, 175, 270, and 326 days i n t o t h e m i s s i o n . Only one b o o s t i s p o s s i b l e f o r each CSM, hence, b o o s t a t e i t h e r 1 o r 29 d a y s , a t e i t h e r 119 o r 175 days, and a t e i t h e r 270 o r 326 days. It i s a l s o p o s s i b l e t o b o o s t w i t h each CSM v i s i t o r w i t h two of t h e v i s i t s . Again, t h i s would depend on t h e decay. I n any e v e n t , t h e b o o s t must n o t p l a c e t h e OWS i n t o a h i g h e r o r b i t t h a n 230 n.m. f o r t h e n e x t CSM rendezvous. A l l combinations of CSM b o o s t s have been i n v e s t i g a t e d . These s t u d i e s a r e documented i n memorandum R-AERO-FT-8-68. ( c ) A p r e s e n t a t i o n on t h e CSM b o o s t e f f e c t s on t h e c l u s t e r l i f e t i m e were p r e s e n t e d t o D r . Mueller on March 1 5 , 1968. A t t h i s time, MSC i n d i c a t e d i t was p o s s i b l e f o r t h e CSM t o b o o s t t h e OWS. (2) Tracking and Communications A n a l y s i s A p r e s e n t a t i o n on communications coverage on t h e c l u s t e r m i s s i o n was g i v e n a t t h e Mission Requirements Panel on February 21, 1968. The d a t a p r e s e n t e d a r e o n l y a small p a r t of t r a c k i n g and communications a n a l y s i s on t h e c l u s t e r m i s s i o n p r e s e n t l y underway. We hope t o have t h e s t u d y documented by May 1st. (3) Martin I n t e g r a t i o n Contract S e v e r a l meetings have been held w i t h t h e MMC personnel concerning branch t a s k s . A t t h i s time, i t a p p e a r s t h a t a l l our t a s k s which we r e q u e s t e d w i l l be included i n t h e c o n t r a c t . From t a s k d e s c r i p t i o n s and c o n v e r s a t i o n s w i t h Martin and Bendix p e r s o n n e l , they seem t o understand and seem t o be capable of responding t o a l l phases. b. A 1 t e r n a t e Uncoupled Mission L i f e t i m e Analysis: S t u d i e s have been made on b o t h t h e OWS m i s s i o n (AAP-1, 2, and 3A f l i g h t s ) and on ATM Mission (AAP-3, 4 f l i g h t s ) . R e s u l t s w i l l be published soon. �c. S a t u r n V Workshop (1) L i f e t i m e Analyses L i f e t i m e a n a l y s e s on t h e S a t u r n V workshop have been completed and a r e documented i n Memorandum R-AERO-FT-9-68. These s t u d i e s included l i f e t i m e s on t h e workshop f o r v a r i o u s c i r c u l a r o r b i t s i n c l i n e d a t 50 d e g r e e s , on a n S - I 1 s t a g e i n b o t h a 270 n.m. c i r c u l a r o r b i t and a 100 by 270 n.m. e l l i p t i c o r b i t , and on a n S-IVB s t a g e of a l o g i s t i c s f l i g h t i n a n 87 x 120 n.m. e l l i p t i c o r b i t . O r b i t a l i n c l i n a t i o n e f f e c t s on l i f e t i m e a r e a l s o included. These d a t a were s u p p l i e d t o M r . Goldsby f o r i n c l u s i o n i n t h e Phase A r e p o r t t o be published by Bellcomm. (2) Tracking and Communications Analyses Data a r e being prepared on t h e a s c e n t and o r b i t a l coverage of t h e S a t u r n V Workshop. These d a t a w i l l be included i n t h e MSFC documentation on t h e S a t u r n V Workshop which w i l l be more d e t a i l e d than t h e Bellcomm r e p o r t . 4. General a . M r . Fleischman a t t e n d e d a symposium i n Washington, D. C . , a t NASA Headquarters on January 29-30, 1968. The symposium was e n t i t l e d 11 Recent Advances i n Numerical Analysis" and was sponsored by D r . Raymond Wilson of OART. M r . Fleischman made a p r e s e n t a t i o n on "The A p p l i c a t i o n of Numerical Techniques i n O r b i t a l L i f e t i m e and S a t e l l i t e Decay Analysis." b. D r . Wilson (OART) c a l l e d M r . Fleischman and r e q u e s t e d cop of the a r t i c l e i n t h e January " A s t r o n a u t i c s and Aeronautics ." This ha, bcen done. He a l s o r e q u e s t e d t h a t he be s e n t any c o p i e s of o t h e r pub1 ished m a t e r i a l which we may have. I n response t o t h i s , we have s e n t him p r e l i m i n a r y c o p i e s of t h e paper which M r . Fleischman w i l l p r e s e n t a t New Orleans i n May. Copies of t h e l i f e t i m e a r t i c l e i n January A s t r o n a u t i c s and Aeronautics have a l s o been s e n t t o D r . Mueller. c. A paper e n t i t l e d "A Mathematical Programming Approach t o t h e Scheduling of Experiments i n Space," by E . F. Fleischman, AeroAstrodynamics Laboratory,and P. M. T r e u e n f e l s and P. R. R e b e l e i n of Honeywell, I n c o r p o r a t e d , has been submitted t o PA0 f o r a p p r o v a l . This paper i s t o be g i v e n a t t h e 33rd N a t i o n a l Meeting of t h e Operations Research S o c i e t y of America t o be h e l d i n San F r a n c i s c o on May 1-3, 1968. �D. F l i g h t E v a l u a t i o n Branch 1. Saturn I B (1) Post-Flight Trajectory The i n t e r m e d i a t e (7-day) and f i n a l (14-day) pos t - f 1i g h t l e s t a b l i s h e d by CCSD. This i s t h e f i r s t t r a j e c t o r i e s on ~ ~ - 2 0 4 / L M -were v e h i c l e f o r which CCSD c o n t r a c t u a l l y had t h e r e s p o n s i b i l i t y f o r t h e t o t a l p o s t - f l i g h t t r a j e c t o r y e f f o r t w i t h t h e e x c e p t i o n of t h e p r e l i m i n a r y (2-day) t r a j e c t o r y . They performed v e r y w e l l , d e l i v e r i n g t r a j e c t o r i e s of e x c e l l e n t q u a l i t y i n a t i m e l y manner. The AS-204 o r b i t a l f l i g h t was e v a l u a t e d , and a s a t i s f a c t o r y agreement w i t h the MSC-determined ephemeris from i n s e r t i o n t o S-IVB/LM-1 s e p a r a t i o n was o b t a i n e d . Tracking d a t a d e l i v e r y was somewhat improved over t h e AS-501 f l i g h t , b u t s t i l l l e f t much t o be d e s i r e d . The b i g g e s t problem i n the o r b i t e v a l u a t i o n was a c c u r a t e l y modeling t h e v e n t ing p r o f i l e . The v e n t i n g was n o t continuous, a s i t was on AS-501, b u t was confined t o the p a s s i v a t i o n experiment and subsequent time. F u r t h e r comp l i c a t i n g t h e s i t u a t i o n were occurrences such a s a d a p t e r panel deployment and S-IVB/LM-1 s e p a r a t i o n which imparted impulsive p e r t u r b a t i o n s t o t h e o r b i t a l t r a j e c t o r y . The a c c u r a t e d e t e r m i n a t i o n and modeling of a l l t h e s e e f f e c t s was, of course, of primary importance i n determining t h e o r b i t a l ephemeris. (2) P o s t - F l i g h t Control E v a l u a t i o n The AS-204lLM-1 I U t e l e m e t r y i n d i c a t e d a l o s s of a l t i , tude c o n t r o l on the s p e n t s t a g e between 37,208 and 37,308 seconds range time. Analyses t o p i n p o i n t t h e e x a c t cause have been somewhat hampere by l a c k of good t r a j e c t o r y d a t a t o p i n p o i n t t h e a l t i t u d e and a t t i t u d e time h i s t o r i e s d u r i n g t h i s period of f l i g h t . Since t h e S-IVB t e l e m e t r y was n o t o p e r a t i n g a t t h i s time, i t was not p o s s i b l e t o determine whether t h e a u x i l i a r y p r o p u l s i o n system (APS) had r u n o u t of p r o p e l l a n t o r had ceased o p e r a t i n g due t o o t h e r c a u s e s . A t t h e time t h e l o s s of c o n t r o l o c c u r r e d , t h e v e h i c l e was f l y i n g a t a c o n s t a n t s p a c e - f i x e d a t t i t u d e , and t h e l o c a l a n g l e of a t t a c k was approximately 80 degrees (nose up). Since t h e o r b i t would have had t o decay t o a b o u t 105 km a l t i t u d e f o r aerodynamic f o r c e s t o overcome t h e APS, t h e most probable cause was APS p r o p e l l a n t d e p l e t i o n coupled w i t h aerodynamic f o r c e s . The most r e c e n t t r a j e c t o r y a v a i l a b l e based on a s t a t e v e c t o r e s t a b l i s h e d a t 9117 seconds range time (immediately a f t e r p a s s i v a t i o n ) shows t h a t p e r i g e e s h i f t e d and occurred between Tananarive and Hawaii a t approximately 141 km a l t i t u d e . A p r e l i m i n a r y i n v e s t i g a t i o n of t h e �aerodynamics involved i n d i c a t e s t h a t even a t 140 km t h e r e i s enough moment t o cause t h e observed motion and t h a t between 120 and 130 krn t h e aerodynamic f o r c e s would have been more than s u f f i c i e n t t o cause t h e observed d i s t u r b a n c e . Both IBM and MDAC have agreed t h a t l o s s of APS p r o p e l l a n t coupled w i t h aerodynamics i s the most f e a s i b l e e x p l a n a t i o n . Data from Hawaii showed t h e v e h i c l e t o be coning w i t h t h e base of t h e S-IVB p o i n t i n g g e n e r a l l y a l o n g t h e v e l o c i t y v e c t o r ( i . e . , f l y i n g t a i l f i r s t ) . It i s n o t expected t h a t any more d e t a i l e d a n a l y s e s can be made u n l e s s a b e t t e r t r a j e c t o r y can be obtained from t h e l i m i t e d t r a c k i n g d a t a a v a i l a b l e from the 6 t h and 7 t h passes over Tananarive and Hawaii. Pos t - F l i g h t P r o p u l s i o n Simulation (3) The p r o p u l s i o n systems of t h e S-IB and S-IVB s t a g e s were e v a l u a t e d u s i n g t h e r e c o n s t r u c t e d p r o p u l s i o n s y s tem performance a n a l y s i s c o n t r i b u t e d by t h e s t a g e c o n t r a c t o r s . The e v a l u a t i o n s d e r i v e d by t h e s t a g e c o n t r a c t o r s were included i n t h e FEWG r e p o r t . The S-IB and S-IVB s t a g e a n a l y s i s r e s u l t s a r e summarized i n t h e t a b l e below. (These r e s u l t s a r e from a f l i g h t s i m u l a t i o n a n a l y s i s . ) The averages a r e computed over t h e t o t a l s t a g e burn times, Av . T h r u s t (N) Nom. Act. - Stape S-IB S-IVB % Deviation A C- ~ N O ~ / N O ~ A'v. ISP NO^ ~ c t . . % Deviation ~ct-NO~/NO~. 7265223 7355609 1.24 260.62 263.48 1.10 950549 962492 1 26 426 07 425 1 - .23 The p r o p u l s i o n e v a l u a t i o n techniques a r e b e i n g s t u d i e d f u r t h e r i n preparation for future flights. 2. Saturn V a. General (1) LVDC Navigation Update There r e c e n t l y has been much i n t e r e s t i n t h e updating of t h e launch v e h i c l e guidance computer b e f o r e second burn on t h e S a t u r n V v e h i c l e s . The a c c u r a c y w i t h which t h i s can be performed i s g r e a t l y i n f l u e n c e d by t h e accuracy of t h e n e a r - r e a l - t i m e i n s e r t i o n v e c t o r . To o b t a i n a n e s t i m a t e of t h e a c c u r a c y of t h e n e a r - r e a l - t i m e v e c t o r , a comparison was made between i t and t h e corresponding time p o i n t on t h e f i n a l p o s t These v e c t o r s were o b t a i n e d f l i g h t trajectory for three recent vehicles. r e c e n t l y from MSC f o r t h r e e v e h i c l e s and a r e what t h e y considered t h e realtime v e c t o r s . �SA-203 Space-Fixed V e l o c i t y (m/s) F l i g h t Path Angle (deg) Near-RealTime 7788.7 -0.044 Final PostFlight 7793.6 -0.002 Final-RealTime 4.9 -0.042 A l t i t u d e (m) 190926 191039 Cross Range (m) 45139 44927 -212 Cross Range V e l o c i t y (m/s) 358.2 362.2 4.0 113 This comparison i s made a t 442.9 seconds range time. The n e a r - r e a l - t i m e v e c t o r on AS-203 was determined w i t h d a t a from t h e impact p r e d i c t o r . Near-RealTime Space-Fixed V e l o c i t y (m/s) F l i g h t P a t h Angle (deg) 7798.3 -0.014 F i n a l PostFlight Final-RealTime 7792.3 -6.0 0.010 -0.024 A l t i t u d e (m) 192011 192097 Cross Range (m) 56293 55677 Cross Range V e l o c i t y (m/s) 252.6 266.2 86 -616 13.6 This comparison is made a t 681.25 seconds range time. On AS-501 t h e nearr e a l - t i m e v e c t o r was determined from U n i f i e d S-Band t r a c k i n g d a t a . AS-2041~-1 Near-RealTime Final PostFlight Final-Real. Time Space-Fixed V e l o c i t y (m/s) 7829.2 7828.5 -0.7 F l i g h t P a t h Angle (deg) 0.013 0.005 -0.008 A l t i t u d e (m) 169253 163443 -5810 Cross Range (m) 93217 92688 -529 Cross Range V e l o c i t y (m/s) 533.7 532.6 -1.1 This comparison i s made a t 602.99 seconds range time. The AS-204 nearr e a l - t i m e v e c t o r was determined from Bermuda C-Band r a d a r t r a c k i n g d a t a . �According t o MSC the n e a r - r e a l - t i m e i n s e r t i o n v e c t o r can p r e s e n t l y be determined from f i v e d i f f e r e n t s o u r c e s : (1) t e l e m e t e r e d launch v e h i c l e guidance d a t a , (2) telemetered s p a c e c r a f t guidance d a t a , (3) u n i f i e d S-Band t r a c k i n g d a t a , (4) impact p r e d i c t o r d a t a , (5) s h i p C-Band r a d a r d a t a . Which v e c t o r t o use i s a human d e c i s i o n t o be made on t h e b a s i s of which v e c t o r "looks" t h e b e s t . The accuracy w i t h which t h e v e c t o r can be updated depends on how w e l l t h e i n s e r t i o n v e c t o r can be i n t e g r a t e d forward, i n a d d i t i o n . t o t h e a c c u r a c y of t h e i n s e r t i o n v e c t o r . The v e l o c i t y e r r o r s shown i n t h e above comparisons i f i n t e g r a t e d over much time would r e s u l t i n s i z a b l e p o s i t i o n e r r o r s . Also, t h e accuracy of t h e v e n t i n g and a e r o dynamic f o r c e s w i l l a f f e c t t h e updated v e c t o r s i n c e t h e s e must be cons i d e r e d i n any i n t e g r a t i o n . T h e r e f o r e , c o n s i d e r a b l e work is y e t t o b e done t o f u l l y understand t h e a c c u r a c y a t t a i n a b l e w i t h a v e c t o r update. (2) LVDC Navigation Update C a p a b i l i t y Checkout Accelerometer measurement e r r o r s and f a i l u r e s d u r i n g t h e b o o s t phase of t h e l u n a r m i s s i o n may c r e a t e a need f o r n a v i g a t i o n update. This update may become n e c e s s a r y t o minimize t h e midcourse c o r r e c t i o n o r t o b e a b l e t o perform t r a n s l u n a r i n j e c t i o n (TLI). To determine t h e need and a b i l i t y t o perform a n u p d a t e , t h e f o l l o w i n g a n a l y s e s must be performed t o answer t h e following q u e s t i o n s : (a) What is t h e philosophy of performing TLI burn w i t h o r w i t h o u t a n update? (b) Can midcourse c o r r e c t i o n s be made such t h a t t h e m i s s i o n can be achieved f o r a n a c c e l e r o m e t e r f a i l u r e assuming t h a t a s t a t e v e c t o r update i s made b e f o r e second burn ( s t i l l a p e r t u r b a t i o n i n second burn plus l o s s of performance)? The t r a j e c t o r y d i s p e r s i o n s propagated through i n s e r t i o ~ must be determined f o r t h e v a r i o u s a c c e l e r o m e t e r f a i l u r e s and f a i l u r e t i m e s . This w i l l b e done c o n s i d e r i n g t h e p o s s i b l e p r o p u l s i o n system performance d i s p e r s i o n s which could e x i s t w i t h t h e backup f/m s e l e c t i o n s a v a i l a b l e . The above t r a j e c t o r i e s w i l l r e q u i r e e v a l u a t i o n by MSC t o determine i f midcourse c o r r e c t i o n s can be made f o r e i t h e r t h e "no update'' o r "update" c a s e s . The p o s s i b l e d i s p e r s i o n s which e x i s t f o r s t a t e v e c t o r update w i l l be analyzed through t r a j e c t o r y s i m u l a t i o n programs. The s t a t e v e c t o r update w i l l b e a f u n c t i o n of t h e a c c u r a c y of t h e r e a l - t i m e o r b i t d e t e r m i n a t i o n and how a c c u r a t e a n e x t r a p o l a t i o n t o t h e implementat i o n p o i n t can b e made. These a c c u r a c i e s a r e dependent on t h e f l i g h t azimuth, v e n t i n g , aerodynamics, e t c . �The r e s u l t s of t h e s e a n a l y s e s w i l l h e l p t o determine the philosophy f o r s e l e c t i n g t h e backup f/m t o be used f o l l o w i n g a n accelerometer f a i l u r e . (Bias f o r h i g h , nominal, o r low performance case?) MSC should provide t h e AS-502 real-time-determined v e c t o r and a v e c t o r e x t r a p o l a t e d t o t h e p o i n t a t which a n update might be performed (a p o i n t b e f o r e second S-IB burn) f o r comparison w i t h t h e pos t - f l i g h t o r b i t d e t e r m i n a t i o n . (3) Abort and A l t e r n a t e Mission T r a j e c t o r y Simulator The e s t a b l i s h e d o b j e c t i v e of t h i s program i s t o develop a S a t u r n V t r a j e c t o r y s i m u l a t o r i n six-degrees-of-freedom t h a t c a l c u l a t e s a t r a j e c t o r y from guidance r e f e r e n c e r e l e a s e through a l l powered f l i g h t phases and t h e parking o r b i t phase t o t h e p o i n t of i n j e c t i o n i n t o a l u n a r t r a j e c t o r y . This program i s intended t o s i m u l a t e t r a j e c t o r y c a s e s f o r a b o r t and a l t e r n a t e miss i o n s t u d i e s The r e q u i r e d c a p a b i l i t y i s a complete six-degrees-of-freedom t r a j e c t o r y w i t h closed-loop guidance, closed-loop p r o p e l l a n t u t i l i z a t i o n and p r o p u l s i o n system, and c l o s e d loop c o n t r o l f i l t e r s ; each c a p a b i l i t y must handle a b o r t and a l t e r n a t e m i s s i o n f a i l u r e s . The s t a t u s of t h e v a r i o u s c a p a b i l i t i e s of t h e d e s i r e d program is a s f o l l o w s : . A complete s i x ( a ) Complete Six-Degrees-of-Freedom: degrees-of-freedom t r a j e c t o r y generated from guidance r e f e r e n c e r e l e a s e through a l l powered f l i g h t and o r b i t a l f l i g h t has been s u c c e s s f u l l y implemented i n t h e SAM-V deck. The p r e s e n t method of c o n t r o l l i n g t h e S a t u r n v e h i c l e by g e n e r a t i n g a t t i t u d e e r r o r s i g n a l s permits a p o i n t of d i s c o n t i n u i t y d u r i n g a complete 360" o r b i t a l r e v o l u t i o n of t h e v e h i c l e when t h e s i g n a l s may be e r r o n e o u s l y l a r g e . A new method which s u p p r e s s e s t h i s e r r o r has been devised and checked o u t i n a l l o r b i t a l phases of flight. (b) Closed-Loop Guidance: The I t e r a t i v e Guidance Scheme a s implemented i n t h e onboard S a t u r n V guidance computer has been i n c o r p o r a t e d i n t o t h e SAAM-V program i n closed loop from guidance r e f e r e n c e r e l e a s e t o f i r s t S-IVB c u t o f f . The guidance e q u a t i o n s which s i m u l a t e t h e parking o r b i t , r e s t a r t p r e p a r a t i o n , r e s t a r t , a c c e l e r o m e t e r p r o c e s s i n g , minor loop s u p p o r t , and which c a l c u l a t e t h e o u t - o f - o r b i t t e r m i n a l c o n d i t i o n s have been prepared f o r programming and l i n k i n g i n t o t h e deck. ( c ) Closed-Loop Control F i l t e r : The complete closedloop c o n t r o l f i l t e r system of t h e S a t u r n V has been s u c c e s s f u l l y i n c o r porated i n t o t h e SAAM-V program and has been checked o u t . �(d) Closed-Loop P r o p e l l a n t U t i l i z a t i o n P r o p u l s i o n Sys tem: C o n t r a c t NAS8-21160 was l e t t o Operations Research I n c o r p o r a t e d (ORI) on June 30, 1967 t o provide R-AERO-F w i t h c a p a b i l i t y t o g e n e r a t e closed-loop p r o p u l s i o n performance. This c a p a b i l i t y was provided, b u t new in-house r e f i n e m e n t s a r e underway t o enhance t h e c a p a b i l i t y of t h e P r o p u l s i o n S i m u l a t i o n Module (PSM). Three of t h e s e r e f i n e m e n t s a r e : - (1) Control F i l t e r s The c o n t r o l f i l t e r s can now be used i n c o n j u n c t i o n w i t h t h e PSM. C e r t a i n o t h e r modules were s t r e a m l i n e d i n o r d e r t o provide t h e machine c o r e s t o r a g e r e q u i r e d by t h e c o n t r o l f i l t e r s . (2) Mass D i s c o n t i n u i t i e s The c e n t e r of g r a v i t y , moment of i n e r t i a and mass r o u t i n e s have been modified t o account f o r d i s c r e t e n a s s l o s s e s (such a s tower j e t t i s o n , e t c . ) . These mass d i s c o n t i n u i t i e s caused d i s c o n t i n u i t i e s i n t h e c e n t e r of g r a v i t y and moments of i n e r t i a which a r e now being handled p r o p e r l y . (3) P r e s s u r i z a t i o n Tables The i n p u t t a b l e s f o r u l l a g e p r e s s u r i z a t i o n , e t c . , which were i n p u t a s a f u n c t i o n of s t a g e time a r e now being i n p u t a s a f u n c t i o n of mass dumped overboard, This i s more r e a l i s t i c f o r d i s p e r s i o n c a s e s and should s u f f i c e i n handling p r e s s u r i z a t i o n i n p u t s f o r off-nominal c a s e s . - - There i s one remaining major r e f i n e m e n t f o r u s e of t h e PSM: t h e S-IVB p r o p e l l a n t u n t i l i z a t i o n s i m u l a t i o n r o u t i n e . P&VE t e l l s us t h a t t h e s i m u l a t i o n we a r e now u s i n g i s n o t t h e most c u r r e n t s i m u l a t i o n . Means of o b t a i n i n g t h e l a t e s t PU model used by P&VE a r e b e i n g i n v e s t i g a t e d . I n a d d i t i o n , t h e r e i s t h e t a s k of t r a n s f e r r i n g t h e PSM from t h e o r i g i n a l 6-D program i n which i t was implemented i n t o t h e c u r r e n t SAAM-V 6-D program. Lif t o f f Analysis MSC has informed us t h a t t h e launch r e l e a s e s u r f a c e wind l i m i t f o r t h e AS-502 launch w i l l be 27 knots (peak) f o r winds from 150 t o 210 degrees azimuth and 31 k n o t s (peak) from a l l o t h e r azimuths. This i s due t o s p a c e c r a f t s t r u c t u r a l c o n s i d e r a t i o n s . This launch r e l e a s e wind l i m i t i s more r e s t r i c t i v e than t h e l i m i t s imposed on t h e b o o s t v e h i c l e duc t o t h e maintenance of adequate l i f t o f f c l e a r a n c e s . �The p r e d i c t e d AS-502 s o f t r e l e a s e rod c h a r a c t e r i s t i c s w i l l be t h e same a s t h o s e used f o r AS-501 p r e d i c t e d l i f t o f f motion s t u d i e s . F l i g h t evaluation r e s u l t s indicated higher-than-predicted r e l e a s e forces e x i s t e d on t h e AS-501 f l i g h t . This r e s u l t was a t t r i b u t e d t o t h e rods being improperly l u b r i c a t e d . P&VE s t a t e s t h a t t h e AS-502 s o f t - r e l e a s e mechanisms w i l l be more e f f e c t i v e l y greased t h a n t h e ones on AS-501. The s o f t - r e l e a s e mechanisms on AS-502 a r e t o be s u f f i c i e n t l y instrumented t o more a c c u r a t e l y d e f i n e t h e rod f o r c e s because t h e i n s t r u m e n t a t i o n on t h e AS-501 launch was inadequate. AS-502 r e s t r a i n i n g f o r c e s w i l l be t h r e e f o u r t h s of t h e p r e d i c t e d AS-501 r e s t r a i n i n g f o r c e because 12 s o f t - r e l e a s e rods were used i n s t e a d of 16. The e f f e c t of t h i s change i s a n i n c r e a s e d l i f t o f f a c c e l e r a t i o n and t h e r e f o r e g r e a t e r v e h i c l e / l a u n c h s u p p o r t equipment c l e a r a n c e s . Camera coverage f o r AS-502 l i f t o f f motion w i l l be essent i a l l y t h e same a s AS-501. Because of t h e removal of t h e a i r scoops, t h e camera o r i g i n a l l y s e t up t o view them has been r o t a t e d t o view t h e shroud of engine #1. The a d d i t i o n a l l i f t o f f t a r g e t camera r e q u e s t e d f o r AS-502 was n o t approved by t h e KSC c o n t r o l board. A r e q u e s t was a l s o made f o r r e l o c a t i n g t h e holddown arm cameras f o r AS-502, because t h e i r view d u r i n g AS-501 launch was p a r t i a l l y obscured by t h e r e t r a c t a b l e cover on t h e holddown arms. This r e q u e s t was a l s o r e j e c t e d by KSC. (1) BP-30 Wind L i m i t s The i n f l i g h t wind speed l i m i t s f o r t h e AS-503 BP a t t h e most c r i t i c a l a l t i t u d e (10 km) a r e 7 9 m/sec, 56 m/sec, and 62 m/sec f o r t a i l - w i n d , cross-wind and head-wind, r e s p e c t i v e l y . Wind r e s t r i c t i o n s of t h i s magnitude r e s u l t i n a v e r y low p r o b a b i l i t y of launch d e l a y due t o in£ 1i g h t winds. (2) BP-30 Abort and A l t e r n a t e Mission A n a l y s i s The AS-503 (BP-30) a n a l y s i s was completed by TBC and d e l i v e r e d on t h e r e q u i r e d d a t e . The document i s r e a d y f o r d i s t r i b u t i o n and a cover memo i s being prepared. The a n a l y s i s p o i n t e d o u t t h a t t h e f r e e f a l l l i m i t l i n e , contained i n t h e AS-501 s p a c e c r a f t a b o r t and a l t e r n a t e m i s s i o n r e p o r t , would be v i o l a t e d i f t h e S-IC had a s i n g l e engine t o f a i l a t c e r t a i n times. The following i s a summary of t h e m i s s i o n completion c a p a b i l i t y which e x i s t s f o l l o w i n g e i t h e r a n S-IC s i n g l e engine shutdown, a n S - I 1 s i n g l e engine shutdown, o r e a r l y S-111s-IVB staging (direct). �(a) S-IC Single-Engine Shutdown Performance c a p a b i l i t y t o a c h i e v e ' p a r k i n g o r b i t i n s e r t i o n f o r a n S-IC s i n g l e - e n g i n e shutdown e x i s t s f o r a l l times. L i f t o f f i n t e r f e r e n c e i s encountered f o r S-IC s i n g l e - e n g i n e shutdowns b e f o r e 5 seconds. For a p e r i o d of a b o u t 10 seconds i n t h e maximum dynamic p r e s s u r e r e g i o n , l o s s of c o n t r o l is p o s s i b l e f o r c e r t a i n wind/ engine shutdown combinations. Loss of c o n t r o l i s more l i k e l y f o r a n upper-engine shutdown. The primary m i s s i o n , t r a n s l u n a r - o r b i t i n j e c t i o n , can be achieved f o r a l l S-IC s i n g l e - e n g i n e shutdown times a f t e r 125 seconds f o r a lower-engine shutdown, and a f t e r 105 seconds f o r a n upperengine shutdown. The r e q u i r e d p r o p e l l a n t r e s e r v e a t i n j e c t i o n i s maint a i n e d f o r t h i s s t a t e d c a p a b i l i t y . The S-IVB r e s t a r t l i m i t is s a t i s f i e d f o r S-IC lower-engine shutdowns a f t e r 95 seconds and f o r upper-engine shutdowns a f t e r 65 seconds. (b) S - I 1 Single-Engine Shutdown Parking o r b i t i n s e r t i o n and S-IVB r e s t a r t c a p a b i l i t y e x i s t f o r a l l S - I 1 s i n g l e - e n g i n e shutdowns. Lower o r upper S - I 1 s i n g l e - e n g i n e shutdowns a f t e r 85 seconds a c h i e v e t r a n s l u n a r o r b i t injection. (c) S-111s-IVB Direct Staging A l l S - I 1 p r o p u l s i o n m a l f u n c t i o n shutdowns, followed by a n S-111s-IVB d i r e c t s t a g i n g b e f o r e 190 seconds from S - I 1 i g n i t i o n , f a i l t o a c h i e v e i n s e r t i o n and r e s u l t i n s u b o r b i t a l l o b s o r e c c e n t r i c o r b i t s , or f a i l t o achieve i n s e r t i o n with required propellant reserves. A l l l a t e r d i r e c t s t a g i n g s a c h i e v e parking o r b i t . S-IVB r e s t a r t c a p a b i l i t y e x i s t s f o r d i r e c t i n g s t a g i n g s a f t e r 350 seconds. Primary m i s s i o n c a p a b i l i t y e x i s t s f o r d i r e c t s t a g i n g a f t e r 360 seconds. A d i r e c t s t a g ing o c c u r r i n g b e f o r e S - I 1 i g n i t i o n plus 120 seconds r e s u l t s i n a n A t l a n t i c Ocean impact of t h e S-IVB. Land impacts i n t h e Canary I s l a n d s o r on t h e A f r i c a n Continent occur f o r d i r e c t s t a g i n g s from 120 t o 190 scconds. Malfunction time, g e o c e n t r i c r a d i u s , i n e r t i a l v e l o c i t y , and i n c r t i a l p a t h a n g l e a t t h e time of ground-command i n t e r r u p t were d e t e r mined f o r maximum, minimum, and r e f e r e n c e performance. (3) Mission D Abort and A l t e r n a t e Mission A n a l y s i s Most of t h e d a t a r e q u i r e d by TBC t o make t h e a n a l y s i s has been s u p p l i e d . Four items t o be f u r n i s h e d a r e : (a) Mission d e s c r i p t i o n documentation. (b) S p a c e c r a f t v e l o c i t y and p a t h a n g l e l i m i t s v e r s u s time r e q u i r e d t o determine v i o l a t i o n of f r e e f a l l 1i m i t s . �(c) Mass c h a r a c t e r i s t i c s f o r t h e m a l f u n c t i o n case where t h e launch escape tower f a i l s t o j e t t i s o n . (d) Mass c h a r a c t e r i s t i c s f o r the m a l f u n c t i o n case where 2nd plane s e p a r a t i o n f a i l s t o occur. Meetings have been h e l d w i t h M r . F. McDonald and B. Hughes, TBC, concerning t h e ground r u l e s f o r t h e a n a l y s i s . Two problem a r e a s a r e p r e s e n t l y d e l a y i n g t h e ground r u l e s . One a r e a i s t h e s i m u l a t i o n of dual engine f a i l u r e s f o r S-IC and S - I 1 s t a g e s , and t h e o t h e r i s t h e d e t e r m i n a t i o n of e f f e c t s of t h e a c c e l e r o m e t e r f a i l u r e s , overs peed and underspeed i n t o t h e v a r i o u s o r b i t s £011 n ~ i n n parking o r b i t . BIBLIOGRAPHY 1. Purdy, K. W . , "An A c o u s t i c J e t f o r E v a l u a t i o n of Laser Doppler V e l o c i t y I n s t r u m e n t , " IN-AERO-68-1, March 19, 1968, U n c l a s s i f i e d . 2. Astrodynamics and Guidance Theory D i v i s i o n , "Astrodynamics, Guidance, and Control Review $/1," TM X-53709, Feb. 21, 1968. 3. Aerophys i c s D i v i s i o n , "Special i s t Conference on Molecular R a d i a t i o n TM X-53711, and I t s A p p l i c a t i o n t o D i a g n o s t i c Techniques," Feb. 23, 1968. 4. Funk, B. H . , "A Simple Explanation of the Fundamental P r i n c i p l e of Cross Beam Remote Sensing," TM X-53712, Feb. 28, 1968. 5. Tomlin, D . , J r . , " O n e - ~ i m e n s i o n a l Wave Motion i n P r i s m a t i c Bars due t o Impulse Loads w i t h and Without Coulomb Damping," TM X-53714, March 1, 1968. 6. Gwin, Hal S . , "Impulse Base Flow F a c i l i t y Technical Handbook," TM X-53716, March 1 3 , 1968. �APPROVAL /zg.r , Aero-As t r o d y n a m i c s L a b o r a t o r y E . D. G e i s s l e r D i r e c t o r , Aero-As t r o d y n a m i c s L a b o r a t o r y DISTRIBUTION R-AERO-DIR Dr. G e i s s l e r M r . Jean Mr. B u t l e r PAO, Mr. K u r t z R-DIR, M r . W e i d n e r MS-H, M i s s J e r r e l l (3) R-AERO-R M r . B e a n (4) Mrs. Hightower R-AERO- T Mr. M u r p h r e e Mr. Cummings Dr. Heybey Mr. Jandebeur Dr. K r a u s e Mr. N a t h a n M r . Few M r . von P u t t k a m e r R-AERO-P R-AERO-D R-AERO-A R-AERO-G R-AERO-Y R-AERO-F R-AERO-X (8) (16) (16) (6) (8) (8) (4) I-V-P, Mr. P r i c e � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000040 Title A name given to the resource "Aero-Astrodynamics Laboratory Bimonthly Progress Report: February - March 1968." Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center Date A point or period of time associated with an event in the lifecycle of the resource 1968-04-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) NASA space programs Project management Type The nature or genre of the resource Progress reports Text Source A related resource from which the described resource is derived Saturn V Collection Box 26, Folder 12 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050 https://digitalprojects.uah.edu/files/original/20/988/spc_stnv_000041.pdf 52912fb9a6b9dd29290837a8aa90c7a1 PDF Text Text AERO-ASTRODYNAMICS W O R A T O R Y BTMONTRLY PROGRESS REPORT t. r\ February and March 1 9 6 7 : INDEX 3 I . TECHNICAL AND SCIENTIFIC STAFF . III . TI IV . V, VI. . ADVANCED STUDIES OFFICE ......................... ................................ ........................................ AEROSPACE ENVLRO'NMENT DIVISION ......................... AEROPHYSICS D I V I S I O N ...... ............................. A . F l u i d Mechanics Research Office .................... B . Mechanical Design O f f i c e ................a.m......... C . Aerodynamic Design Branch .............. . . . ........ D . Experimental Aerophysics Branch .................... E . Thermal Environment Branch ......................... F . Unsteady Aerodynamics Branch ....................... ASTRODYMHICSANDGULDANCE ~ O R Y D I V I S Z O ............. N A . S c i e n t i f i c A d v i s o r y O f f i c e ..................*...... B . O p t i m i z a t i o n Theory Branch ......................... C . Astrodynamics Branch. .............................. D . Guidance Theory Branch.. ........................... PROJECTS OFFICE ................. ...................................... ..... .......................................... ............. . ................................................ VIII. PLIGHT TEST AWLYSIS DIVISION .......................... A . S p e c i a l P r o j e c t s Office ............................ 3 . Tracking and O r b i t a l A n a l y s i s Branch. .............. C . F l i g h t Evaluarion Branch ............. .............. l3 . F l i g h t Mechanics Branch ............................. BIBLIOGRAPHY .................................................. VII D~ICSANDFLIGHTMECHANLCSDIVISION A Multi-Projects B Saturn V C Saturn I B D AAP E General Methods Dynamics and Control . .. . ................................. 1 2 5 7 12 12 13 14 20 26 30 34 34 36 39 41 44 44 4L 47 47 51 52 52 53 56 60 63 �AERO-ASTRODYWYTCS LABORATORY BIMONTHLY PROGRESS REPORT I, TECmICAEAND 1. S C I E N T I F I C STAFF Dynamics of Cable-Connected S p a c e S t a t i o n s An analytical method has b e e n developed f o r the dynamic problems of t w o i d e n t i c a l cable-connected space s t a t i o n s which are r o t a t i n g about a n a x i s p e r p e n d i c u l a r L O t h e i r orbital p l a n e in f r e e flight. 'Fne connec Ling cable i s t r e a t e d as an elas t i c beam w i t h t r a n s verse v i b r a t o r y m o t i o n s b o t h in and out of t h e p l a n e of r o t a t i o n . Thf nonhomogeneous boundary conditions d u e ta t h e roll, pitch, and yaw motions of the space s t a t i o n s a r e r c s o l v e d by ustng fictitious concentrated-masses concept. This a p p r o a c h o f f e r s a more accurate r e p r c s e n t a tion of the s y s tern than that g i v e n by the lumped-masses t r a n s £ex matrix method. T h i s a n a l y s i s can be e x t e n d e d e a s i l y f o r a nonsyrrtmetric s y s t e m . (Liu) 2. ODYSSEY Experiment concepts and p r e l irninary s t u d y r e s u l ts p e r t a i n i n g to the Odyssey configuration, m i s s i o n p l a n s , and s u b s y s t e m requirements a r e b e i n g i n v e s t i g a t e d a s part of Ehe p r o j e c t d e f i n i t i o n s t u d y . Specifically, c u r r e n t s t u d i e s a r e i n v e s t i g a t i n g t h e passive s p h e r e s , r e q u i r e d o r b i t a l a l t i t u d e s , and r e s u l t i n g s p h e r e s e p a r a t i o n d i s t a n c e s f o r varying o r b i t a l lifetimes. A reference m i s s i o n p l a n ( n o t to b e confused with t h e a c t u a l mission p l a n which requires a l a u n c h d a t e ) has been o u t l i n e d which serves as a tool f o r data a c q u i s i t i o n times, command sequences, a n d b u s subs ys t e m requircrnenEs s u c h as g u i d a n c c a n d c o n t r o l a c c u r a c i e s , t r a n s m i t t e r and r e c e i v e r p o w e r , and r e c o r d e r capacities. A preliminary perturbation a n a l y s i s of the g u i d a n c e e r r o r s h a s been completed. The r e s u l t s i n d i c a t e t h a t e x t r e m e a c c u r a c i e s a r e not required, a n d e r r o r s of two d e g r e e s in a t t i t u d e d u r i n g t h r u s t i n g p e r i o d s will be a l l o w a b l e to m e e t orbit change accuracy requirements. P r e l i m i n a r y s t u d i c s t h u s f a r i n d i c a t e a preference f o r the C - l e n g i n e over the TRW a n d R - 4 ~ e n g i n e s as p r o p u l s i o n r c q u i r e m c n t s f o r t h e b u s . Tankage of t h e Saturn V/ S-IVB APS p r o v i d e s capacities r e q u i r e d for f u e l a n d o x i d i z e r . P r o p e l l a n t c a p a c i t y , i n c l u d i n g b a t h t a n k s , i s a b o u t 660 pounds which i s a d e q u a t e f o r Odyssey f i r s t - c u t r e q u i r e m e n t s o f about 5 6 0 pounds. C o n t i n u e d i n v e s t i g a t i o n into the pos s ibSe l o c a r ion aboard a l a u n c h vehicle has confirmed t h e i n a d e q u a c y of i n t e r n a l s p a c e . Fur themore, t h e uprared S a t u r n IB v e h i c l e s considered as p o s s i b l e c a n d i d a t e s a r e m a r g i n a l in r e g a r d to p a y l o a d capacity. F u r t h e r a n a l y s i s of the externaLly m a u n t c d pod approach appears as the most p r o m i s i n g c o n f i g u r a t i o n . Mass a n d moment of i n e r t i a da L a for t h e bus c o n f i g u r a t i o n have been g e n e r a t e d anc: �u s e d i n prelimfnary a t t i t g d e c o n t r o l system s t u d i e s . Seme l a y o u t s of the S - I V E a f t skirt s u p p o r t i n g s t r u c t u r e w e r e made to aid in determining pod s u p p o r t r e q u i r e m e n t s . Aerodynamic e f f e c r s r e l a t e d LO this c o n f i g u r a tian a r e a l s o under study by R-AERO-A. Both steady a n d unsteady pod l o a d s a r e S e i n g i n v e s t i g a t e d as well as t h e overall e f f e c t s on v e h i c l e aerodynamic c h a r a c t e r is tics due to the e x t e r n e l l y mounted pod s t r u c t u r e . IFevr] TI. ADVAXCED STUDIES OFFICE A. F l i g h t Flechanics and Performance An i n v e s t i g a t i o n of the T i t a n 111-C performance capability has been p u b l i s h e d in m e m o r a n d m R-AERO-X-67-45. Much e f f o r t has been d e v o t e d te g e n e r a t i n g performance d a t a of the S a t u r n V (516) launch v e h i c l e ( u s L ~ g3-2 and J-2s p r o p u l s i o n ) . The a n a l y s i s a l s o compares the P r o d u c t Improved S a t u r n V. The study considers three different m i s s i o n p r o f i l e s : 100 N. mi. c i r c u l a r , 100 x 263.5 e l l i p s e , and a 72-hour lunar transfer. The exercise lus been in s u p p o r t of che Planetary JAG, When u p r a t e d F-L analysis with ?"nsust t a i l o r i n g has been completed, the r e s u l t s w i l l be documented. An investigation of the performance c a p a b i l i t y of the S a t u r n vehicle (516) to high energy (C3 km2/sec2) type m i s s ions has been i n i t i a t e d . The f l i g h t geometry reserves have been r e c a l c u l a t e d far these p r o f i l e s and r e s u l t s are expected in about t w o weeks. T h e f i n a l phase of t h e 3-burn S-IVB s t u d y (S-ZVB in lunar o r b i t ) has been c o m p l e t e d , i n d i c a t i n g the capability of p u r t i n g approximately 103,000 I b s ( i n c l u d i n g the S-IVB s t a g e ) in a 100 N. mi. circular Puner o r b i t u s i n g 5-25 propulsion. The f i n a l report i s b e i n g documented. A performance analysis of (two-burn) S - I n i n s e r t i o n i n t o a 6,000 N. mi. e q u a t o r i a l o r b i t has been published in memorandum R-AERO-X47 -37. A memorandum e n t i t l e d ' ' P e r f o ~ n c eand T r a j e c t o r y Daca f o r t h e S a t u r n 5P.- 217 Vehicle" has been d i s t r i b u t e d . This memorandum, R-AEROX-67-14, which is in response to R-P&m-AV-66-246, shows a comparison of :he 5-25 and s t a n d a r d 5-2. A s requested by DMSF, the performance c h a r a c t e r i s t i c s of t h e u p r a t e d Saturn v e h i c l e s have been u p d a t e d f o r t h e H z a d q u a r t e r s Prospectus. �B. Syscems Analysis Group l. Spent Stage U t i l i z a t i o n An orientation m e e t i n g w i t h DAC on t h e spent S - I n u t i l i z a t i o n study was h e l d a t MSFC onMarch 8 - 9 . The majority of t h c f i r s t d a y was ~ a k e nup w i t h presentations by MSFC personnel on t h e status of Workshop #1, o b j e c t i v e s and s c h e d u l e s of the p r e s e n t study e f f o r t , and a transmf t t a l of technical data to DAC. Mr. Wood of t h i s off i c e p r e s e n t e d the f Light performance d a t a to be used d u r i n g the study. The remainder of the time was used by DAC to present their s t u d y organization, clarify questions r a i s e d previously a b o u t certain k e y p c o p l c a s s i g n e d to the s t u d y , and the t e c h n i c a l approach to be used. M r . Verderaime of R-MRO-D and M r . Josh Johnson of R-AERO-A were invited t o attend the orientation. DAC personnel expressed a great i n t e r e s t Pn the orbital aerodynamic work b e i n g done by AERO and i n d i c a t e d khey w o u l d c o n t a c t M r . Johnson on t h i s matter in t h c near f u t u r e . 2. IU Xodif i c a t i e n A p r o p o s a l from IBM in response to a s o l e source RFQ from AS0 for s t u d y i n g requtred modifications to the As tr ionics sys terns t o be u s e d w i t h the u p r a t e d S a t u r n launch vehicles has bccn evaluated. The s c o p e of the proposal was w i t h i n the available resources of $225,000 for the s t u d y . A technical pre-negotiation s e s s i o n was h e l d on February 10, 1967, attended by the c o n t r a c t i n g o f f i c e r , representatives of A S 0 and the coLlocated off ices, and representatives of IBM to i n s u r e u n d e r s t a n d ing of the level of t e c h n i c a l d e p t h expected and the approach to be Laken. Tile l u n d s available f o r the s t u d y must be c o n t r a c t u a l l y committed by A p r i l 15, 1967. 3. S a t u r n I 3 Improvement The proposal f r o m CCSD f o r a Phase 111 s t u d y of fur thes u p r a t i n g the S a t u r n I l a u n c h vehicle wa6 of 9 scope more t h a n twice the a v a i l a b l e r e s o u r c e s of $125,000. An i n f o r m a l pre-negotiation session was held a t MSFC on March 2 , 1 9 6 7 , at which CCSD p r e s e n s e d a d e t a i l e d b r e a k - o u t of the man-hours involved on a task- to-task bas is and t h e i r recommendations on ways i n which the scope of work c o u l d be r e d u c e d w i t h o u t compromising rhe d e s i r e d r e s u l t s . The scope of work still was somewhat t o o l a r g e , and CCSD was instructed to come back w i t h a r e d u c e d proposal b y the following week, s i n c e this money nus t a l s o b e c o m i t t c d by A p r i l 15, 1967. �4. S a t u r n V Improvement S t u d i e s a. Launch F a c i l i r y Test T h e Tes t L a b o r a t o r y is checking o u t t h e i r f a c k l i t f e s modc-1, u s i n g n Saturn V model, The s o l i d propellant f o s t h e u p r a t e d cnnf t g u r a r Ton is on o r d e r from UTC. b. Base Beating Tes t The base he&ting t e s t s nr Cornel I A e r o n a u t i c a l Laborat n r s l u v e r u n i n t o d i f f i c u l t y in model f a b r i c a t i o n . This w i l l delay the t e s t s t a r t i n g d a t e u n t i l September. The solid p r o p e l l a n t for rhe GAL t e s t s is b e i n g o r d e r e d with t h e group for R-TEST from UTC. C, As trodyaamics & Miss i n n Analysis Group I. Manned Planetary Flyby Missions B a s e d on ~ a r u r n / ~ ~ c l l l o Sys tern T h i s twelve-month s t u d y c o n t r a c t w i t h North American Aviat i o n is c u r r e n t 1 y approaching the three-quarter comp Le t i o n mark. The t h i r d - q u a r t e y - r e v i e w of t h i s s t u d y c o n t r a c t w i l l be h e l d at MSFC approximately May 1, 1967. The particulars of rhe meeting will be announced as they become f i r i a 1 i z t . d . 2. NASA In-House P l a n e t a r y J o i n t A c t i o n Group (JAG) The r e s u l t s of t h i s s t u d y a r e being documented. The i n p u t s of R-AERO-X are t a be submitted to R-AS0 on A p r i l 1 4 , 1967. AS0 has t17t respoils i b i 1i ~ Lor y coord i n a ting the MSFC e f f o r t s . R-AERO-X w a s res pous ibl e f o r launch sequence and timelines, as c e n t p r o f i l e s and e a r t h 1 nunch vehicle p e r f e m a c e , i n t e r p l a n e t a r y i n j e c t i o n r e q u i r e m e n t s , and bascline m i s s i o n definition. It is expected t h a t the planatary JAG will cantinup for s e v e r a l months y e t , bur. at t h i s t i m e it is not clear what goals w i l l b e p u r s u e d or a t w h a t p a c e . 3, Con t r a c t o r s O p t i m u m r e e n t r y a n a l y s i s u s i n g the s t e e p e s t a s c e n t o p t i m i z r i t i u n teclin i q u e has b e e n c ~ l p l ted r and d o c u m e n t e d in Xor ~ h r o p r e p o r t TM-792-7-143 March 1 9 6 7 . The report p r e s e n t s t h e s t e e p e s t a s c e n t m e t h o d d e v ~ l c p e dby B r y s o n and Denham for s o l v i n g o p t i m a l p r o g r a m i n g problems v i t h s t a t e v a r i a b l e i n e q u a l i t y c o n s t r a i n t s . �A s t u d y 05 impulsive v e l o c i t y requirement: far a b o r t i n g a planned Mars stopover mission i n t o a powered Mars f l y b y m i s s i o n has been completed, The a n a l y s i s considered direct f l i g h t p r o f i l e s to Mars and return, a n d p r o f ilcs which i n c l u d c d t h c Vcnus s w i n g b y mode. This s t u d y has been documented in Lockheed R e p o r t TM 54130-130 LMSC/HREC, F e b r u a r y 1967. 4. Analytical Launch Window Program An analytical digital computer program model d e s i g n e d to c a l c u l a t e o r b i t a l launch window requirements for interplanetary m i s s i o n has been d e v e l o p e d , programmed and checked o u t . E x c e l l e n t a g r e e m e n t of r e s u l t s has been demonstrated between a calculus of v a r i a t i a n trajectory program and the analytical program. Parametric a n a l y s i s f o r selected Venus and Mars m i s s ion is underway. 111. PROJECTS OFFICE 1. F l i g h t Limits Sub-panel T h e seventh F l i g h t Limits Sub-panel meeting was held a t MSFC on F e b r u a r y 14, 1 9 6 7 . During the meeting MSFC p r e s e n t e d the Saturn V EDS status and the planned a c t i v i t i e s toward d e f i n i n g r e q u i r e m e n t for the launch vehicle a n d spacecraft to a t t a i n an a c c e p t a b l e emergency d e t e c t i o n s y s t e m . The r e s u l t s of the meeting a r e documented in memorandum R-AERO-P-82-67, d a t e d F e b r u a r y 23, 1967. 2. Range S a f e t y Sui-Panel The seventh Range S a f e t y Sub-Panel meeting w a s h e l d a t KSC on Elarch 15, 1967. The Eastern Test: Range (ETR) was b r i e f e d on the S a t u r n I B rendezvous m i s s i o n and the S a t u r n V lunax l a n d i n g m i s s ion, ETR p r e s c n t c d t h c i r u s e o f the NASA Range S a f e t y data. This r e s u l t s in a b e t t e r u n d e r s t a n d i n g of the use/requirernent f o r data. The minutes of the meeting are b e i n g documented. 3. G u i d a n c e and Performance Sub-panel Meeting The Twenty-Fif th Guidance and Performance Sub-Pane 1 mee r i n g was h e l d a t MSC on March 2 2 , 1 9 6 7 . The e m p h a s i s was on adjusting the m i s s i o n p l a n n i n g and o r b i t a l a t t i t u d e maneuver and v e n t i n g timelines to the S a t u r n I3 mission changes. Other t o p i c s included the c o o r d i n a t e reference systems f o r gimbal a n g l e data t r a n s f e r s , a s t a t u s r e p o r t on the AS-503 ?ropellant r e s i d u a l s problem, and some r e s u l t s of AS-503 two i n j e c t i o n simulations. The r e s u l t s o f the meeting are b e i n g d o c r ~ m ~ n t e d . �4. S a t u r n IB Piissiwn Change Direction has been received t o implement the AS-204/LY-1m i s q i o n f r m l a u n c h complex 37B. AS-205, though n o t f i n n e d up on a11 d r t a i l s , w i l l c a r r y a CSM p a y l o a d . AS-206 w i l l c a r r y a LM payload and AS-207 a CSY; this w i l l be a d u a l m i s s i o n . P r i m a r y crnphasis is being p l a c e d on accomplishment of the work f o r A S - 2 0 4 . The CCSD systems s u p p o r t e f f o r t s a r e be ing realigned f o r t h e above m i s s i o n c h a n g e s . 5. S a t u r n IB Program Review An Aero-Astrodynamics Laboratory S a t u r n IB Program RevLew was h e l d on February 2 0 , 1967. The follo17ing t o p i c s w e r e covered: (1) m i s s i o n description, ( 2 ) s t a t u s of mission planning for Apol.10 and M P , and ( 3 ) s p e c i a l problems, E f f o r t s have been e x p e n d e d on the e f f e c t of various Locat i o n s of t h e o r b i t a l Workshop (OWS) solar a r r a y on the S-IVB. Tile p r e s e n t baseline conf i g u r a r i o n for the OWS has a solar array arrangement extended from the a l r l o c k module (AM). This con£ i g u r a t i o n is e x p e c t e d to change in the near future to a c o n d u i t arrangement along rhe S-IVB. A c t i v i t y has a l s o involved c o n s i d e r a t i o n of an a c t i v e cont r o l s y s t e m f o r the OWS to extend the s t a b i l i z a t i o n beyond the i n i t i a l 7 I/2 h o u r s a n d f o r reuse. E f f o r t s have been expended on the o p t i m i z a t i o n of payload for the AAP-3/4 f l i g h t s . However, f i n a l i n s e r t i o n a l t i t u d e for the U P - 4 EL i g h t cannot b e determined u n t i l a f t e r the MSC-MSFC M i s s i o n Requirements Panel has worked the task j o i n t l y . C o n s i d e r a t i o n has been g i v e n to t"n empact: o f a 3 - f o o t s l i c e between the IU a n d SLR to allow more room f o r rhe ATM telescape-hydrogen tank clearance and r o allow lowering t h e A m package r e l a t i v e to the ATM rack for b e t t e r as r r o n a u t a c c e s s a n d f i l m recovery. 7. 1967. S a t u r n V Speech M r . Ttnius s p o k e to the Tuscaloosa Kiwanis C l u b on February 53, The speech was e n t i t l e d , " S a t u r n V Program and ALabam." �8. AERO S/ C na ta Book D i s t r i b u t i o n has been c o m p l e t e d on Revision 5 to the Internal Aero-Astrodynanics Laboratory S / C Data Book ( W B ) . This reviscon c o n s i s t e d principally of an u p d a t e d G&C section, many S / C system and s u b s y s t e m illustrations and d e s c r i p t i o n s ( i n c l u d i n g recerll d e t a i l s on t h e o p e r a t i o n a l systems of t h e crew such as p e r s o n a l e q u i p m e n t , couches, waste management, survtval equipment, etc.) and d e t a i l s on the S / C s y s tems t h a t a r e t o b e o p e r a t e d by t h e crew (such as docking and e a r t h Pandi n g s y s terns). A t t e m p t s are a l s o being m a d e t o d e c l a s s i f y the data book s o t h a t it w i l l be more a c c e s s i b l e to R-AERO p e r s o n n e l . IV. AEROSPACE ENVIRONMENT D I V I S I O N 1. The FPS- 16 radar/Jimsphere temperature sensor was f 1ight t e s t e d a t Cape Kennedy, F l o r i d a , d u r i n g the week of February 27 t h r o u g h March 3, 1967. These tests were conducted by Ms. D e n n i s Canp ol: R-AERO-YE, c o n t r a c t o r personnel from the GCA C o r p o r a t i o n of B e d f o r d , Mass., a n d KSC personnel. The f l i g h t tests were partial-lly successful. The major problems experienced d u r i n g these t e s t s were w i t h the balloon-borne a n t e n n a a n d with the o u t p u t of power from the balloon-born transmitter. Work is underway by GCA to correct: these problems. Subsequently, mock-up f l i g h t r e s t s w i l l be m a d e at the contractor's p l a n L L o a s c e r t a i n t h a t these problems have been corrected before returning to KSC to c o n d u c t additional i d e a l i z e d f l i g h t tes ts 'This Jitnsphere temperature task is b e i n g c o n d u c t e d under the M S F C / ~ S Ac o n t r a c t NAS8-20588. . 2 . Wind profile d a t a f o r MSFC' s meteorological t o w e r i n t e r £esence on w i n d s p r o g r a m b e i n g c o l l e c t e d at NP.SAt s 2 5 0 - m meteorological tower facility a t KSC, F l o r i d a , a r e b e i n g r e c o r d e d on magnetic tape in analog form and p u t i n t o d i g i t a l f o r m by personnel of MSFC1s Computation Labora- Lory. The inhouse Baeing contractors a r e to perform the a n a l y s i s and prepare a f i n a l r e p a r t o n t h i s t o p i c . The final r e s u l t s will i n c l u d e wind velocity c o r r e c t i o n factors w i t h r e s p e c t to height and wind disection, s p e c t r d l analyses w h l d l w i l l relaLe Llle severiLy of the tower's i n t e r f e r e n c e , s u g g e s t i o n s on how to r e d u c e t h e t o w e r i n t e r f e r e n c e on w i n d s , i f a p p r e c i a b l e , etc. 3 . Average and peak hourly wind profile data have been r e c e i v e d f o r a one-week p e r i o d a s measured in May 1966 an t h e 1600-foot meteorological tower f a c i l i t y (WKY-TV Tower, Oklahoma C i t y ) o p e r a t e d by the National Severe Storms Laboratory (NSSL) at Norman, Oklahoma (NASA contract government order No. H-92101). Mr. Charles K. H i l l (R-AERO-YE) has recently been named technical representative on t h i s program w i t h Mr. John Kaufman (R-AERO-YE) as a s s i s t a n t . The format of the punched c a r d sample o f data has been checked out by p e r s o n n e l of - �MSFC/R-COMP and d c t e r m i n c d t o be a c c e p t a b l e . Recent t e l e p h o n e c m u n i c a t i o n w i t h M r . Leslie D. S a n d e r s , NSSL Project S c i e n t i s t on t h i s c o n t r a c t , I n d i c a t e d t h a t additional d a t a of t h i s t y p e w i l l be made available to R-AERO-YE i n the near f u t u r e b e g i n n i n g w i t h the sample of data f r o m Play 1966. This is a u n i q u e source 0 5 data which will p r o v i d e d e t a i l e d rcind prof i l e clmrac t e s i s tics u s i n g f i x e d anemometers above 500 ft (150 m) w h i c h i s t h e maximum h e i g h t of NASA'S meteorolcrg-ical tower at: KSC. 4 . An investigation is b e i n g conducred by R-AERO-YE i n t o the p e s s i h i l i t i e s f o r o b t a i n i n g d a t a on thunderstorms at Cape Kennedy and 7 i ~ a r r i t . t : I s l a n d i n 1967 by means of radar t r a c k s . A memorandum, p r e p a r e d by Mr. John N. Kaufman, C n i e f , R-AERO-YE, has been d i r e c t e d to M r . G a m i n Emanuel, I-NO-R at: KSC, r e q u e s t i n g t h i s infarmation for the thunderstorm season, Flay ~ h r o u g hSeptember. These thunderstorm radar tracks are to b e u s e d in an e x i s t i n g i n v e s t i g a t i o n of the s t u d y of extreme w i n d s a s s o c i a t e d w i t h such storms, e s p e c i a l l y to study the w i n d p r o f i l e data r e c o r d e d at NASA's 150-rn meteoraLagical rower f a c i l iry and ar- the various Saturn Launch p a d s (LC 34, 3 7 , and 39). One p o s s i b l e source of the data is from the A i r F o r c e , who o p e r a t e a weather d e t e c t i o n radar at PAF'B. Various personnel a t KSC have been contacted on t h i s matter, and it i s f e l t t h a t t h e s e t h u n d e r s torm/radar tracks can be made available. 5. The s t a t u s of data acquired from NASA's 150-m meteorological tower located at Cape Kennedy, F l o r i d a , is by m o n t h l y periods as fo2lows: a. Data R e d u c t i o n - (1) December 1965 through August: 1966 Data r e d u c t i o n by National Weather Records Center in Asheville, N , C., is complece and a l l m a g n e t i c t a p e s , p r i n t o u t s , and chart records have been r e t u r n e d to R-AEKO-YIMSFC. - (2) September 1966 through November 1966 Data r e d u c t i o n by NWRC is near completion and will be s e n t to MSFC s o o n . 13) December 1966 through February 1 9 6 7 - Data r e d u c t i o n by hWRC is in process. The National Weather Records C e n t e r in Asheville, W. C., is r e d u c i n g these data for R-AERO-Y u n d e r government o r d e r can t r a c t No. H-13207A. b. Data Analyses - P r i n r o u t s for fre( I ) December 1965 through my 1966 quency d i s t r i b u t i o n s of mean w i n d s p e e d s and temperatures were examined and bad data p o i n t s s p e c i f i e d by Environmental A p p l i c a t i o n s Branch personnel. L i s t i n g s of these bad d a t a were sent to NWRC and the �Computation Laboratory for correction and/or elimination. good data f o r t h i s p e r i o d are in p r o c e s s by R-AERO-YE. Analyses of - (2) June 1966 ~hroughAugust 1966 "'Debugging" f o r t h i s data p e r i o d is in process. L i s t i n g s of bad data points w i l l b e s e n t t o NWRC and Compu La Lion Labura Lory for correct i o n a n d / o r e l intimation. - (3) December 1965 through November 1966 Numerous analyses by R-AERO-YE f o r one year of meteoroEogica1 tower data are i n p r o c e s s as v a l i d d a t a a r e c e r t i f i e d . R-AERO-YE e f f o r t s to analyze magnetic- tape-recorded w i n d p r o f i l e data axe progressing s a t i s f a c t o r i l y . This i n c l u d e s the s tat i s t i c a l p r o p e r t i e s of t u r b u l e n c e , auto- and cross-correlations, the spectrum a £ turbulence, gust c h a r a c t e r i s t i c s , etc. Also, the analyses of wind profile data in s u p p o r t to t h e SA-5OOF Ground Wind Loads T e s t conducted in 1966 are c o n t i n u i n g . 6. During t h i s p e r i o d , 123 rawinsonde f l i g h t s were made at the Atmospheric Research F a c i l i t y . There were 35 f l i g h t s in support of Test Laboratoryts Acoustic S t u d i e s . A t o t a l of 44 flights w e r e made i n s u p p o r t of static tests: 1 5 flights f o r t h e F-1 engine and 29 for the S-IB t e s t s . There were 4 f l i g h t s conducted f o r a s p e c i a l f r o n m l s t u d y , and 2 flights w i t h dual-tracking data for a s y s t e m s comparison s t u d y of the GKD equipment. 7. The 150-m mefeorological tower at: Kennedy Space Center was i n s t r u m e n t e d for the tower i n t e r f e r e n c e s t u d y . This program c a l l e d f o r the ins t a l l a t i o n o f another 18-meter tower near the base of the 150-meter tower and add f t f onal wind sens a r v on the tower. 8. The A tmos pher ic Research Facility c o n t i n u e d s u p p o r t i n g Tes r L a b o r a t o r y by p r o v i d i n g m e t e o r o l o g i c a l data and s e r v i c e to atmospherical m e a s u r i n g and r e c o r d i n g equipment. These data and s e r v i c e s are u s e d by Test L a b o r a t o r y f a r acaus tic s t u d i e s and static tests. 9. Renovation of the A c o u s t i c Wind Measuring F a c i l i t y was completed. The microphone cable had b e e n damaged by personnel working in rhe a r e a , or by environmental c a u s e s . The r e c o r d i n g equipment, r e l o c a t e d in b l o c k house No. 21, will be operational f a r the next S a t u r n launch. Design of a modification kit to modify M-88 Nike rocker motors This modification makes the M-88 c m p a t i b l e w i t h launch f a c i l i t i e s a t Kennedy Space Center. These m o t o r s a r e used f o r the NikeTomahawk-Thermos phere Program. 10. was comple t e d . �I I. T h e d e s i g n f o r anemometer mounts and s i g n a l c o n d i t i a n l n g units was f i n i s h e d ; t h c y will be f a b r i c a t e d and i n s t a l l e d on t h e 400-f o o t tower a t Range 1. 12. New c a b l e was installed and is b e i n g checked o u t f o r the Dynamic h i n d s Facil i t y , which s h o u l d be operational by May 1, 1 9 6 7 . 1 3 , All equipment L t e m s , e x c e p t for the contrnl cryntaT nscillatorn, o r d e r e d f o r t h c i o n o s p h e r i c gravity wave s t u d y have been received. The W D C s i t e l o c a t e d near Valhermosa S p r i n g s , Alabama, has been i n s t a l l e d except: f ~ - rt h e t I ~ r e etowers for t h e d i p o l e antennas. N e g o t i a t i o n s on tljc AVCO proposal a r e b e i n g f i n a l i z e d . 14. S t a t i s t i c a l environmental m o d e l s of s o l a r flare proton events a r e b e i n g d e r i v e d . Frobabillty values for v a r i o u s mission l e n g t h s are b e i n g c a l c u l a ~ e dby rwo methods. The f i r s t m e t h o d assumes random d i s t r i b u t i o n of the s o l a r flares throughout the s i x y e a r s of h i g h e s t solar a c t i v i t y and u s e s a binomial expansion t o d e t e r m i n e associated p r o b a b i l i t y f o r various mFssion lengths. The second method assumes the d i s t r i b u t i o n f o u n d in solar cycle 19 f o r various misston lengths, The f i r s t method p r o v i d e d p r o b a b i l i t y values which c o u l d n o t e a s i l y be fit to a p r o b a b i l - i t y versus f l u x curve s o t h a t large errors were i n c u r r e d In the s t a t i s t i c a l models. The second method is now being examined to s e e f f more r e a l i s t i c p r o b a b i l i t y values can be obtained. 15. The ionosonde located at Cape Kennedy has now been transferred to t h e I n s t i t u t e for Telecammunications Sciences and Aeronomy (ITSA), vrlzo has i n f o m l l y agreed t h a t MSFC w i l l get: che Ionosorrde Lor use i11 o u r i o n o s p h e r i c and S a t u r n launch programs. Following our A p r i l 25 scheduLed Nike/Tomahawk thermosphere probe f i r i n g s at Cape Kennedy, the ionosonde e q u i p m e n t w i l l be packed and s h i p p e d to MSFG, Here, we p l a n to van-mount the sounder equipment for use on a c t i v e programs at MSFC a n d at Cape Kennedy. An e q u i p m e n t retrofit to t h i s sounder which will i n c r e a s e the aquipment range a n d s e n s i t f v i t y has been proposed by ITSA. ?t appears nm t h a t t h i s r e t r o f i t will have to w a i t u n t i l i m e d i a t e program demands have been met. 1 6 . A p r o p o s a l to m a p t h e S c u r r e n t systems i n t h e ionosphere from 9 a low o r b i t s u b s a t e l l i t e package has been p r o p o s e d by ITSA. A purrhasLng request has been i n i t i a t e d on a Phase A feasibility s t u d y of t h i s proposal. The basic c o n c e p t is f o r a s m a l l package to b e r c t r o - f i r e d from a l a r g e r laboratory t y p e vehicle. The package would c o n t a i n a s m a l l propulsion system capable 05 augmenting its L i f e t i m e in, say, a 120 km c i r c u l a r o r b i t f a r s e v e r a l o r b i t s . The package would then measure t h e g l o b a l S, c u r r e n t system and would provide data f o r areas p r e v i o u s l y inaccessible: �1 7 . A program is being s t a r t e d to determine a more realistic ( f o r d e s i g n c r i t e r i a a n d mission s t u d i e s ) model for o u t e r zone Van Allen p a r t i c l e s . The d a t a now being used are time-averaged data and do n o t i n c l u d e the extreme flux-energy s p e c t r a to be encountered. I n this program we hope to develop extreme model trapped-particle enviranrnents and t h e i r a s s o c i a t e d p r o b a b i l i t y of encounter, 18. D a t a a r e b e i n g c o m p i l e d f o r use as natural environmental parame t e r d e s i g n s p e c i f i c a t i o n s f o r the Voyager Spacecraft Phase C contract. It appears that the May 1, 1967 deadline will be met. 19. A revised v e r s i o n of the Lincoln-McNish solar c y c l e prediction technique has been p~ogrammed and is now available in the P r o d u c t i o n Group of the Computation Laboratory u n d e r the title "Solar Predictions." This program should b e used by all personnel r e q u i r i n g p r e d i c t e d values of the f u t u r e level of solar a c t i v i t y . 20. Two I n d e p e n d e n t programs, DENSTY SMALL and DENSTY JACCHIA 1964, a r e also available in t h e Production Group. The DENSTY SMALL routine should be u s e d f o r a l l o r b i t a l lifetime predict-ion s t u d i e s ; all other o r b i t a l dynamics analyses should use the DENSTY JACCHIA 1964 r o u t i n e . 21. Prel h i n a r y r e s u l t s aE the six Nike-Tomahawk probes launched i n d i c a t e tlia L the m e a s ured d iurrxal varia Lion i r z Lernpera Lure is smewlw t l a r g e r than that predicted theoretically by the JACCWU L964 model amas phere . 22. The paper ent i r l e d "Atmospheric Models Relative to Orbital L i f e t i m e Investigationst' presented a t the American Meteorological Society National Cowerence on High A l t i t u d e Meteorology and S p a c e Weather i n Houston, Texas, 29-31 March 1967 was very f a v o r a b l y received. Our p h i l o s o p h y of using d i f f e r e n t model atmospheres f o r d i f f e r e n t a p p l i c a t i o n s i s i d e n t i c a l to the concept used by the U. S. A f r Force. 23. Work d u r i n g t h i s r e p o r t i n g period has been d e v o t e d ta (1) the e s ~ a b l f s l u i t e n t01 M a r L i a r r atmospheric information essential. to the environmental d e s i g n c r i t e r i a far the Voyager Phase C RFP, (2) the pub1 ication of TM X-53521, "Space Environment Criteria GuFdelines for Use in Space Vehicle Development (1967 Revision) ," (33 the completion of TR-793-7-142, "Analytical Model of t h e Martian Surface," by Korthrop s u p p o r t c o n t r a c t o r u n d e r contract NAS8-20082, ( 4 ) the completion of a p a p e r e n k i t l e d "The Marbian A t m o s p l ~ e r e , " wlxich is to be g i v e n at the A p r i l 1 0 I E S Conference in Washington, D C., and (5) the continua t t o n of a very de ta-iled s t u d y concerning t h e theare t i c a l aspects of o b t a i n i n g Mar tiafi amos pheric in£orma t i o n through the vacuum c h b e r s i m u l a t i o n of t h e Nar t i a n atmosphere . . �A. F l u i d Mechanics Research O f f i c e I. S t a t u s of X-Beam Development During the week of March 20, an exploratory test was pewformed on a i i v e - e n g i n e c l u s t e r i n s t a l l e d in the W F . The crossbeam was u s e d in making s p a c e - t i m e correlations withLn the shear layer r e g i o n s of t h e i n r e r a c t i n g plumes. A similar t e s t was also conducted ~ ! r i r i n gt h i s p e r i o d on a s i n g l e engine with shocks in the flow. A p r e s e n t a t i o n on t h e current position a n d f u t u r e plans for the cross-beam program was given to Dr. Johnson (R-EO-DIR) on March 1 4 , 1 9 6 7 . A c o n r r a c r w i t h the IIT Research Insritute has been s i g n e d f o r the continuation of the aerodynamic cross-beam t e s t programs. A l s o a contract has been s i g n e d w i t h Colorado S t a t e U n i v e r s i t y for a CrossedBeam Weather Watch Study. Work is progressing on s c h e d u l e f o r the assenbling of t e s t e q u i p m e n t and a s s o c i a t e d hardware f o r t h e atmospheric f i e l d t e s t a: the Army rnereorological tower at Redatone Arsenal. 2. O r b i t a l Aerodynamic Calculation Research The Monte Carlo approach to the s t u d y of the shadow and wake effects in f r e e molecular flow has yielded very interes Ling r e s u l t s which can be incorporated into the present orbital aerodynamic c a l c u l a tion programs, From the s t u d y of W o d i s c s at various separation d i s t a n c e s , a s i m p l e expression f o r the divergence of t h e flow from the hyperthermal l i m i t can be determined as a f u n c t i o n of the s p e e d r a t i o . Quantitatively, the a n a l y s i s shows that t h e f l o w diverges from t r u e bgperthermal f l o w by approximately 2.5 degrees at a s p e e d r a t i o of 5 a n d about 1 d e g r e e at a s p e e d r a t i o 0 5 10. For some o r b i t a l c o n f i g u r a t i o n s , neglecting this small divergence in tF.e flow could r e s u l t in a f a c t o r of 2 e r r o r in the a e r o d y n a m i c c a l c u l a t i o n . In t h e s t u d y of concave b o d i e s , i n c l u d i n g wedges, semic y l i n d e r s (of g e n e r a l cross-sectional shape) and concave hemispheres, t h e most s i g i l i f icant f e a t u r e i s the deviation from the hyperthermal s o l u t i o n s g i v e n by Schamberg, In h i s a n a l y s i s , the e f f e c t of the conc a v i t y was t o decrease t h e d r a g c o e f f i c i e n t , while t h i s s t u d y (alang w i t h a few o t h e r s ) now i n d i c a t e s an increase in the drag c o e f f i c i e n t . Specifi c a l l y , w h i l e ScIlamberg% a n a l y s i s anc the Monte Carlo a p p r o a c h borh y i e l d a d r a g coefficient value of 2.63 f o r a sphere ( w i t h an accommodation c o e f f i c i e n t of 0.51, Schamberg's value for a concave hemisphere is Less t h a n 2.63,1~7hilet h e Monte C a r l o y i e l d s 2.90. Other parameters which c a n b e compared, such as the number of molecules e x i s t i n g at each c o l l i s i o n and t h e f l u x along the surface, are i n agreement. �B. Mechanical Design Office 1. The single-component m i c r o f o r c e balance (No. 220) has been c a l i b r a t e d and i n s t a l l e d i n the Low D e n s i t y Chamber for t e s t i n g . The b a l a n c e is capable of measuring 112 to 8 gm d r a g f o r c e s with an a c c u r a c y of 2 1 1 2 p e r c e n t , A backup balance i d e n t i c a l Co number 226 has been ordered. 2. Two m o d e l s o f p r o p o s e d S-IVB O r b i t a l Workshop c a n f i g u r a - t ions have been designed and f a b r t c a t e d on a rush b a s i s f o r use in determintng p r o j e c t e d areas and area moments of inertia of the models at various a n g l e s of a r t a c k . A modellmirror s u p p a r t f i x t u r e f o r use in a c q u i s i t f o n of these data is b e i n g b u i l t . 3 . The following i s a partial l i s t o f additional p r o j e c t s and t h e i r currer-t status: 4 P e r c e n t Saturn V force model and balances - Design AEDC Modification of f i v e - e n g i n e model - CFD - - P r e s s u r e probes and s u p p o r t system Design Des i g n 14" wind runnel Balance, drive systemand r e l a t e d e q u i p m e n t f o r s l o s h farce measurements Design Remote c o n t r o l hardware f o r f l o o r a n d ceiling adjusment TTS, 14" WT Des i g n - - Temperature - Mismatch T e s t Section - Five-component balance, 112-inch 0 . D . 8-foot O . D . vacuum exhausr plenum D r a f t ix?g - Drafting - Variable p o r o s i t y walls for TTS, 14" WT Draf r i n g - Fabrication Boom and clamps f o r meteorological t e s t i n g on 400-foot RSA tower Fabrication Fins and axisymrnetric body and balance, Fabrication - 14" WT - S a t u r n V, thin s k i n heat t r a n s f e r model, JPL - Fabrication �S a t u r n IB forced oscillation model and balance, 14'' WT Fabrication - Modification of S - I B force model, 14" WT - Fabrication - Jigs for modification 05 Nike motors, KSC Fabrication S t r a p - o n boosters f o r S-TC model (CAL d e s i g n ) , Fabrication CAL F l a t p l a t e model (NSL d e s i g n ) , Ames - Fabrication Laser Doppler Turbulence Hardware, Raytheon d e s i g n Fabrication - 0 s c i l l a t ing wake model (Lockheed d e s i g n ) - Cold flow stilling chamber and nozzle for laser work Del ivered - Pressure models f o r X-beam SPLTS, 14T1WT - Sidewall-mounted i n t e r s t a g e h i n g e model and balance 14" WT - C. Fabrication - Del ivered Delivered Aerodynamic Design Branch 1. U p r a t e d S a t u r n TIAS-206 Aerodynamic Inves t i g a t ion Tests have been completed to determine the s t a t i c l o n g i t u d i n a l s t a b i l i t y a n d a x i a l force characteristics for the u p r a t e d S a t u r n I/AS-206 v e h i c l e configuration. The t e s t s were conducted at AEDC' s s u p e r s o n i c a n d hypersonic tunnels, CAL' s t r a n s o n i c tunnel, a n d MSFC'S 14-inch r r i s o n i c ~ u n n e lduring t h e fall of 1966. The data obtained were analyzed and have been documented a s R-AERO-AD- 6 6 - 6 3 . 2. Saturn IB w i t h External Mounted Solar Panels The mounting of e x t e r n a l s o l a r arrays has been s t u d i e d The area of the s o l a r arrays c o n s i d e r e d is 800 square feet. The three external l o c a t i o n s being c o n s i d e r e d are (1) the forward s k i r t : o f the S-IVB s t a g e , (2) the a f t skirt of t h e S-IVfi s t a g e , a n d (3) t h e c o n d u i t that extends f r o m s t a t i o n 1188 forward approximately 400 i n c h e s . The c o n d u i t mount is t h e most d e s i r a b l e from the aerodynamic c o n s i d e r a t i o n s because the maximum height is 1 2 inches as compared t o 42 i n c h e s f o r the other external configurations. f o r rhe Saturn XI3 v e h i c l e . �P r e l i m i n a r y aerodynamic l o a d s on t h e s o l a r p a n e l s mounted on the forward and a f t s k i r t s of the S-IVB s t a g e are d e f i n e d fn O f f i c e Memo R - A E R O - A D - ~ ~ -a~n~d ,aerodynamic Loads an the conduits are p r e s e n t e d in O f f ice Memo R-AERO-AD-67-27. 3, S a t u r n IB Vehicle - S t r u c t u r a l Modification The a d d i t i o n of external s t r i n g e r s to s t i f f e n the S a t u r n LB instrument unit has been p r o p o s e d . T h i s w o u l d h e l p el i m F n a t e v i b r a t ianal problems w i t h the ST-124 g u i d a n c e plarforrn e n c o u n t e r e d on past Sarurn LB f l i g h t s . This p r o p o s a l was reviewed and found a c c e p t a b l e from a s t a t i c aerodynamic s t a n d p o i n t ( r e f e r e n c e R-AERO-AD-67-19). 4, S a t u r n IIB/Z;M Vehicle a. Local Flow F i e l d P r o p e r t i e s Local Mach numbers, p r e s s u r e s , temperatures, densities , and v e l o c i t i e s have b e e n computed f o r the u p p e r half of the S a t u r n I B / W vehicle f o r f r e e stream Mach numbers ranging from 3 . 7 to 12.0. These data determined for both a = 0" and = 8" Iuve been documented i n CCSD TB-AP-46-74 a n d a r e enclosed i n R-AERO-AD-67-14. b. Compartment Venting I n - f l i g h t v e n t i n g analyses of t h e S-IBIS-IVBi n t e r s rage a n d t h e S - I B t a i l b a r r e l compartments have b e e n completed and documented in CCSD TB-AP-66-75 (R-AERO-AD-57-12) , and CCSD TB-AP-66-76 (R-AERO-AD- 6 7 - 1 3 ) , respectively. T h e s e d o c u m e n t s presenE maximum and minimum bands of internal p r e s s u r e f o r each compartaenr. 5. S a t u r n LR/LM w i t h Three- a n d Six-Foot: Length E x t e t s i o n s The aerodyn~mic s t a t i c s e a b i l i t y a n d l o c a l normal f o r c e c o e f f i c i e n t s f o r the d e s i g n Mach number and angle ot at tack r a n g e have b e e n derermined. The configurations s t u d i e d c o n s i s t e d of (1) a 3 - f o o t c y l i n d r i c a l e x t e n s i o n 260 inches in diameter and (2) a 6 - f o o t c y l i n d r i c a l e x t e n s i o n 260 inches in diameter a d d e d between t h e Saturn IB v e h i c l e IU a n d the SLA. The abme d e s i g n d a t a a r e b e i n g pl.rhlfshed in an o f f i c e memorandum. The perturbetion en compartment v e n t i n g d u e t o t h e i n c r e a s e i n volume i s b e i n g d e t e r m i n e d and w i l l be p u b l i s h e d in the future. 6. S a t u r n I E Improvement Studies - MSFC Wind Tunnel Tests Data from w i n d tunnel t e s t s of several proposed S a t u r n I E con£ i g u r a t i o n s which a r e u p r a t e d w i t h 120-inch d i a m e t e r s o l i d r o c k e t motor s t r a p - o n u n i t s have been i n c l u d e d i n bwo r e p o r t s which are b e i n g reviewed. �S t a t i c s t a b i l i t y , axial f o r c e a n d loads o n the 70-incli diameter S - D s t a g e tanks a r e i n c l u d e d in these r e p o r t s . CCSD has been f u r n i s h e d w i t h data from these t e s t s in b o ~ ht a b u l a t e d a n d magnetic tape Eorm. 7. ~ p o l l o / ~ a c u sVn Aerodynamic Characteristics f o r L i f t o f f Analysis Aerodynamic c h a r a c t e r i s t L c s f o r S a t u r n V lif to£f a n a l y s e s were e s t a h l i s h e d September 1966 in NASA X-53517, The data established were for t h e c a s e o f ground wind d i r e c t e d into the l a u n c h umbilical tower t h e r e b y s u p p o r t i n g t h e c r i t i c a l vehicle/ launch tower clearance analysis. To further support the vehicle close-support clearance analyses resulting from g r o u n d w i n d from various directions, aerodynamic data h a v e been p u b l i s h e d t o supplement the data of TM X-53517. These data are presented in Office Memo R - A E R O - A D - ~ ~ - ~The ~ . data are based on the l a t e s t available ground w i n d s experimental data. 8. Apallo/Saturn V S t a t i c F o r c e and Pressure T e s t s at AEDC A conference was h e l d at AEDC to d i s c u s s r e s t i n g a 4 p e r model of t h e ApollolSaturn V i n t h e AEDC 16-foot t r a n s o n i c wind t u n n e l in September 1967. The scope of the t e s t program has been changed to include pressure d i s t r i b u t i o n s on the a £t cyl i n d e r , shrouds, and fins, as well as the o r i g i n a l total f o r c e measurements. Data w i l l b e o b t a i n e d f o r angles of a t t a c k up to 14 degrees f o r Mach numbers from 0.6 to 1.4 w i t h Reynolds number variations. cent scaled 9. Apollol~at u r n V S - I C I S-11 I n t e r s tage Aerodynamics The subsonic-transonic portion of t h e investigation was c o n d u c t e d in the MSFC 14-inch TGirT from March 6 to March 2 0 , 1967. The t e s t s were conducted over a Mach number range of 0.50 through 1.96 a n d a n a l p h a r a n g e of 0 through 180 degrees. Data for a few angles of a t t a c k were obtained f o r Mach 2.74 and 2 . 9 9 f o r c o r r e l a t i o n of the p r e s e n t t e s t method with t h a t of the previous supersonic t e s t s . Model hardware cons is t e d of a half -model splitter-plate sys tern mounted on the tunnel sidewall as o p p o s e d to t h e s ting-mounted model used d u r i n g the supersonic i n v e s t i g a t i o n . Data agreement between rhe f x o s y s t m s TlraS good for low angles of a t t a c k . For alphas near 45 and 135 degrees, the s p l i t r e r - p l a t e d a t a appear t o be low. The d a t a are b e i n g analyzed and e f f o r t s are b e i n g d i r e c t e d toward dctcrmining the causcs and magnitudes of the data discrepancies so t h a t proper c o r r e c t i o n s can be made. �10. ApoPlolSaturn V Aerodynamic Force T e s t s The a n a l y s i s report o f the m o s t recent Apollo/Saturn V aerod y n a m i c f o r c e tests has not been completed because p r e s s i n g t i m e schedules in ather areas have allowed only minimal effort on t h i s task. this r e p o r t s h o u l d b e r e a d y for publication In May 1967. PI. S a t u r n V However, L i f t o f f Aerodynamics The current A p o l l o / ~ a turn V 1iftoff maneuver has c r e a t e d a need for more d e t a i l e d informatton concerning on-pad loads caused by ground w i n d s . Available d a t a d o n o t provide total s t a L i c loads nor is the engine-on s i t u a t i o n considered; t h e r e f o r e , a test will he conducted in the LTV low s p e e d w i n d tunnel to determine loads on the ApolIalSaturn V while in t h e lau~lchp o s i t i o n for both engine-on and e n g i n e - o f f s i t u a t i o n s . Alsa, loads w i l l be determined as a function of altitude as the vehicle r i s e s o f f t h e pad. Models and associated t e s t h a r d w a r e w i l l . b e d e s i g n e d a n d f a b r i c a t e d by LTV. It is estimated t h a t the r e s u l t s of t h e program w i l l be a v a i l a b l e by August 1967. 12. Saturn V I a t e r f ereace Free Fin-Shroud Inves t i g a tions The data from wind tunnel tests r a n d u c t e d to p r o v i d e i n t e r f e r e n c e f r e e lvads VII ~ l i rSaturli V r i l l s a n d s h r o u d s have b e e n r e d u c e d an? checked. These data a r e b e i n g analyzed a n d a r e p o r t s h o u l d be r e a d y by June 1967. 13. S a t u r n V Roll I n v e s t i g a 5 i o n The e f f e c t s o f roll angle on the s t a t i c longitudinal s t a b i l i t y and axial f o r c e characteristics for the Apolle/Saturn V v e h i c l e were s t u d i e d in the MSFC 14-inch TWT. A 0.3366 percent scale model with all proruberances was used in t h i s t e s t . The d a t a were reduced and a n a l y z e d and are available in Office Xemo R-AERO-AD-67-11. 14. S a t u r n V Voyager Ground Wind S t a t i c Aerodynamic Loads A n aerodynamic f oad d i s t r i b u t i o n far d e t e r m i n i n g l o a d s d u e to ground w i n d s an the S a t u r n V Voyager has been p u b l i s h e d i n O f f i c e Memo R-AERO-AD-67-20, d a t e d March 9 , 1 9 6 7 . The l o a d d i s t r i b u t i o n m u s t b e used in conjunction w i t h t h e a p p r o p r i a t e horizontal ground w i n d s profile t a o b t a i n v a l i d l o a d i n g s . 15. S a t u r n Y Improvement S t u d y An aerodynamic analysis w i l l soon be p u b l i s h e d for an u p r a t e d S a t u r n V v e h t c l e ~ 5 t hf o u r 120- inch seven-s egment , sol id motors attached t o the S-IC boos tcr. TIIC a n a l y s i s is b a s e d on experimental w i n d tunnel data o b t a i n e d f r o m the HSFC 14-inch uind tunnel. �16. S a t u r n V E l a s t i c Body Aerodynamics The a e r o d y n a m i c s f o r a deflected vehicle have been d e t e r m i n e d front linearized theory coupled w i t h s t a n d a r d Apollo/Saturn V load d i s t r i b u t i o n s . The incremental load d i s t r i b u t i o n s d u e t o bending m=re determined for Mach number 1.2 and a rigid body angle of a t t a c k of 8 d e g r e e s . A bent v e h i c l e s h a p e was o b t a i n e d from R-AERO-D. T h e s e aerodynamic d a t a will b e used by R-MRO-D t o determine t h e m a x i m u m b e n d i n g moments f o r an e l a s t i c body. 17. O r i f i c e Flow C o e f f i c i e n t S t u d y The o r i f i c e flow i n v e s t i g a t i o n which s u p p o r t s t h e S a t u r n V v e n t i n g program was i n i t i a l l y conducted in the Ames 6-foot s u p e r s o n i c wind tunnel in November 1966. The f inaL d a t a were recetved h y Nor throp Space Labs f r o m ARO of Ames Research C e n t e r . These data were analyzed a n d found to c o n t a i n many errors, most of which c o u l d be a t t r i b u t e d to e r r o r s in the ARO data reduction program. ARO acknowledged the probLerns by r e c h e c k i n g t h e data and making necessary changes. Thc c o r r e c t e d data have been received and a r e b e i n g analyzed by NSL. S i n c e f u r ~ h e rt e s t i n g is r e q u i r e d because of the m o d e l and ins trum~nrationproblems e n c o u n t e r e d during the f i r s t zest, a model r e d e s i g n was i n i t i a t e d and was r e c e n t l y f i n i s h e d by NSL. Fabrication 1lril.1 begin s h o r t l y a n d is scheduled to b e completed by about June 15, 1967. The contractor's proposal in response to the RFQ f o r e x t e n s i o n of the p r e s e n t c o n t r a c t to cover the additional t e s t i n g at Ames a n d a l i m i t e d program at MSFC was r e c e i v e d and approved. The new contract e x t e n s i o n s h o u l d soon be f i n a l . 18. Body of R e v o l u t i o n V i s c o u s Crossflow Investigation High Reynolds number data o b t a i n e d a t LTV a r e b e i n g evaluated. Additional h i g h angle of a t t a c k t e s t i n g began Harch 23 in the MSFC 14-inch f a c i l i t y a n d will c o n t i n u e t h r o u g h A p r i l 17. The vapor s c r e e n technique of o b t a i n i n g photographs of t h e Lrail i n g v o r t e x s y s tern w i l l b e checked a g a i n d u r i n g t h i s t e s t . The two major problems in t h i s area a r e controlling t h e p r o p e r amount of mois Lure in t h e test s e c t i o n , and pos i t i o n i n g t h e camera downstream such that t h e 1i g h t i n g is a d e q u a t e a n d the viewing angle is r e a l i s r i c . 19. Low D e n s i t y Wind Tunnel T e s t s The E n g i n e e r i n g Phys i c s Sect i o n (R-AERO-AEP) has had a d r a g balance f a b r i c a r e d f o r use in the MSFC Low D e n s i t y (Mach 4 ) Wind Tunnel. This balance is capable of measuring drag loads on b o d i e s in �t h e load range f r m one to t e n grams. This b a l a n c e will be u s e d to measure drag loads on spheres, cylinders, d i s c s , and p o i n t e d cones t h a t have a n i n e d e g r e e half-angle. The Knudsen number will be varied over a w i d e range s o that data can be obtained in the continuum s L i p , trans it i o n a l , and f r e e molecule flow regimes. The Knudsen number will be varied b y changing the w i n d t u n n e l s t a g n a t i o n pressure and by u s i n g s e v e r a l d i f f e r e n t s i z e m o d e l s . The drag data from these tests will be compared rrrrth similar drag measurements t h a t have been made in s i m i l a r low d e n s i t y w i n d tunnels e x i s t i n g in the United S t a t e s . 20. Reaction Control System (RCS) Impingement E f f e c t s on the Lunar Module (LM)J ~ p olo l Telescope Mount {ATM) In a memorandum to t h e P r o j e c t s O f f i c e (R-P&VE-PT-67-M-62-D, d a t e d F e b r u a r y 1 4 , 19671, Mr. H. G. P a u l requested t h a t LM RCS impingement e f f e c t s on the m / ~ m be investigated. The Lockheed Missiles and S p a c e CompanylHuntsvil l e was a l s o a s k e d to i n v e s t i g a t e t h i s problem. E f f o r t s in the Aero-Astrodynamfcs L a b o r a t o r y have been confined to monitoring t h e Lockheed e f f o r t . Lockheed has inves tigated t h r u s t l o s s and h e a t i n g r a t e s d u e to RCS impingement. M r . J. D. Johnson, R-AERO-ADE, h a s monitored the thrust loss calculations and Mr. Rochelle, R-AERO-ATB, has monitored t h e b e a t i n g r a t e c a l c u l a t i o n s . Lockheed is p r e p a r i n g r e p o r t s for Mr. George Hopson, R-P&E-PTD, t h a t p r e s e n t RCS plume shapes, h e a t i n g r a t e s , and t h r u s t - l a s s e s . These reports will be completed d u r i n g the f i r s t h a l f of A p r i l . Meetings f o r MSFC and MSC personnel were h e l d by R - E V E on %rch 9 and 30 to d i s c u s s t h e LM/ATM RCS impingement problem. At these mee Lings it was decided t h a t MSFC (R-ASTR and R-?&m) s h o u l d investigate t h e u s e of d e f l e c t o r s in conjunction w i t h retractable s o l a r p a n e l s . 21. Orbital Aerodynamics A s c h e d u l e has been established f a r rhe calculation of o r b i ~ a laerodynamics f o r t h e o r b i t a l workshop and L'MIATM cluster eonfiguration. This schedule is presented in memorandum R-AERO-AD-67-18, d a r e d March 7 , 1 9 6 1 . These c a l c u l a t i o n s are b e i n g made by the Lockheed Missiles and S p a c e Company u n d e r NASA S u p p o r t Contract NAS8-20082 a s d i r e c t e d in Schedule Order No. 65. To meet the s c h e d u l e , the number of Lockhecd personnel working oc Schedule O r d e r Ha. 65 was increased to s i x . Lockheed i s p r e s e n t l y 3 days behind s c h e d u l e . This i s p a r t l y because of a d e l a y in c o n f i g u r a t i o n d e f i n i t i o n . During t h i s r e p o r t i n g p e r i o d , Lockheed p e r s o n n e l have c a l c u l a t e d o r b i t a l aerodynamics f o r several orbital workshop and LM/ATM c l u s t e r configurations . These d a t a a r e p r e s e n t e d in the following memorandums: �(I) O r b i t a l a e r o d ynarnic character i s t i c s f o r t h e orb i t a P workshop w i t h the docked mapping and survey s y s t e m WSS) w i t h and w i t h o u t the docked c m n d and service module (CSM), R-AERO-AD-67-24, March 15, 1 9 6 7 . (2) O r b i t a l aerodynamic character is t i c s f o r the c l u s t e r arrangement of the o r b i t a l workshop, R-AERO-AD-67-25, March 15, 1967. (3) Orbrtal aerodynamic character is tics f o r t h e cormnand a n d service module, R-AERO-0-67-26, March 15, 1967. (4) O r b i t a l aerodynamic characterts tics of the c l u s t e r arrangement of the orbital workshop with and without the docked cormand and s e r v i c e module, R-AERO-AD-67-29, Karch 28, 1 9 6 7 . A "shadow method" of p r e d i c t i n g aerodynamic c o e f f i c i e n t s on an a r b i t r a r y body in the free molecular, high speed r a t i o flow regime was fnves t i g a t e d (in-house) d u r i n g F e b r u a r y and Harch. The "shadow m e t l ~ o d " involves measuring frontal areas from m o d e l shadows p r o j e c t e d b y a parallel lighr beam, u s i n g t h e f r o n t a l area in c o n j u n c r i o n w i t h empirical data to determine the drag coefficient of the body, and resolving the drag coefficient into force and moment c o e f f i c i e n t s r e l a t i v e to a body-axis system. The i n v e s t i g a t i o n proved the method to be satisfactory. E f f o r t s a r e now underway to eliminate some problem areas and to etreaml i n e t h e p r o c e d u r e as much as p o s s i b l e . Although a computer program was compiled t o c a l c u l a t e coefficients once areas are o b t a i n e d , mechani c a l integration of areas causes the p r e s e n t p r o c e d u r e to be t i m e consuming. Two automated systems c u r r e n t l y being developed by R-AERD-RB a n d R-AERO-AEI w i l l hope f u l l y reduce the t i m e r e q u i r e d to g e n e r a t e data. D. E x p e r i m e n t a l Aerophys i c s Branch 1. 14 x 14-Lnch T r i s o n i c Wind Tunnel The following t e s t s were conducted d u r i n g the r e p o r t p e r i a d of F e b r u a r y and March: (a) The i n v e s t i g a t i o n by Lockheed f o r R-AERO-AL te determine the e f f e c t of an oscillating wake s o u r c e on t h e aerodynamic c h a r a c t e r i s t i c s of t h e S a t a r n ZB a n d V A p o l l o c m a n d modules submerged in t h e wake was can t i n u e d . �(b) An i n v e s t i g a t i o n for AMICOM te determine the f e a s i b i l i t y of the use of f l u i d amplifiers f o r a l t i t u d e control devices. The t e s t was d i s c o n t i n u e d because of model malfunctions b u t i s expected to be resumed l a t e r . (c) A n inves Ligation into c e r t a i n flow phenomena associ a t e d w i t h the testing of winged configurations at different wall porosities in the h i g h s u b s o n i c s p e e d range. This was done in cooperation w i t h McDonnell A i r c r a f t who f u r n i s h e d t h e model. Total r u n s : 6. (d) A preliminary investigation by I I T X T f o r R-AERO-AM to determine t h e s t a t i c and a c o u s t i c pressures on c y l i n d r i c a l and s t e p models p r i o r to o p t i c a l crassbeam measurements i n t h e special test s e c t ion. Total suns: 52. (c) An i n v e s t i g a t i o n for R-AERO-AD to d e t e r n i n e the s t a t i c s t a b i l i t y a n d a x i a l farce characteris tics of thc S a t u r n V S - I C / S - I 1 i n t e r s t a g e ring. T o t a l runs: 139. updated. permit. (£1 An investigation f a r R-AERO-AD to d e t e r m i n e t h e s t a t i c s t a b i l i t y and axial force characteris t i c s of proposed Saturn IB (AS-206) configurations w i t h a n d w i t h o u t solar panel shrouds. Total runs: 37. (g) An investigation f o r R-AERO-AD to s t u d y the v i s c o u s cross-flow e f f e c t s on b o d i e s of r e v o l u t i o n a c h i g h angles of a t t a c k . T e s t is c u r r e n t l y i n progress. The tunnel control and instrumcntacion p a n e l s a r e b e i n g The new c a b i n e t s and panels will be i n s t a l l e d as s c h e d u l e s Work is underway to develop a s u i t a b l e vzpor s c r e e n t e c h nique i n the tunnel. T h e technique is unique in s u p c r s o n i c blotqdot.m wind tunnels because of d i f f i c u l t y in o b t a i n i n g t h e proper c o n d i t i o n s in the relatively s h o r t blow time. The t u n n e l is heavily scheduled through June 1.967. �2. 7 x 7-Inch B i s o n i c Wind Tunnel The BWT has been reassembled a f t e r an e x t e n s i v e cleaning and should be o p e r a t i o n a l by May 1, 1967. The e l e c t r i c a l sysrem has b e e n reworked a n d u p d a t e d . 3. Thermal A c o u s t i c J e t Facility Tests on the cold flow duct have been continuing f o r R-AERO-AY on n o z z l e flow a n a l ys is u s i n g t h e cross -beam correlation Lechnique. T e s t s have been c o n d u c t e d on b o t h srngle and c l u s t e r e d nozzle configurations. E x ~ e n s i v eshadowgraphic photography coverage has a l s o been made. T o t a l runs: 7 4 1 . C o n t i n u e d t e s t i n g has been s c h e d u l e d for May 1 9 6 7 . The he 1ium heater has undergone a major d es i g n change. This was the d i r e c t r e s u l t of NASA i n s p e c t i o n of the u n i t . The cont r a c t d e l i v e r y d a t e is now s e t at early summer. 4. Hot and C o l d Flow T e s t F a c i l i t i e s Both t h e HFTF a n d the CFTF have been i n a c r i v e d u r i n g t h i s r e p o r Ling p e r i o d In ger.era1, the c o l d f l o w duct of the TAJF will run t e s t s p r e v i o u s l y associated w i t h the CFTF. The CFTF i s held in a r e a d y status. . 5. IBFF The I m p u l s e Base Flow F a c i l i t y was s c h e d u l e d t h i s e n t i r e p e r i o d La determine the sound i n t e n s i t y l e v e l s of t h e f u t u r e high Reynolds number equipment d u r i n g flaw initiation time and d u r i n g normal run t i m e . It is d e s i r e d to keep the i n t e n s i t y b e P m 1 2 0 db SPL. I n t e n s i t y levels observed w i t h a 1 / 2 5 s c a l e model of the f u t u r e equipment were approximately 1 9 0 db when the m o d e l charge pressure w a s 650 p s ig ( t h e estimated charge pressure of the f u t u r e equipment). A1 h measurements were obtained with the model exhaus Ling to t h e amosphere. Dbviausly, some r e d u c t i o n in i n t e n s i t y was r e q u i r e d . A f t e r s e v e r a l c o n s i d e r a t i o n s , discharging the model i n t o a s p h e r e and then slowly v e n t i n g t h e s p h e r e to atmosphere was chosen a s one solution. T n t e n s i t y l e v e l s of 1 3 5 d b w e r e recorded (peak levels for 2 miZliseconds d u r a t i o n ) when the m o d e l exhausted i n t o the sphere. T e s t s were n u d e to determine if a r a d i a l e n t r y or a tangantial e n t r y i n t o the s p h e r e h a d any effect on the i n t e n s i t y levels. Differences in i n t e n s i r y levels based on sphere e n t r y were small; howzver, s t r u c t u r a l loads on the sphere �resulting from t h e i n i t i a l M a s t of a i r c r i t i c a l . The r a d i a l e n t r y b l a s t e d the whereas t h e t a n g e n t i a l e n t r y l o a d e d t h e p r c s e n t e d s t r u c t u r a l d e s i g n problems on diameter) . (opening of the diaphragm) were o p p o s i t e s L d e of the sphere sphere unequally. Both c a s e s t h e full s c a l e sphere ( 5 0 f o o t A s a r e s u l t of the above t e s t s , a m o d i f i e d r a d i a l e n t r y inLo t h e s p h e r e was s e l e c t e d . The m o d i f i c a t i o n allows the sphere to be l o a d e d e q u a l l y , t h u s e l i m i n a t i n g t5e structural p r o b l e m s . The op tirnum flow geometry of the p r e v i o u s l y mentioned modification i s p r e s e n t l y b e i n g s t u d i e d . The i n t e n s i t y l e v e l a f the f l o w with t h e modification i s expected to be less t h a n the 135 d b o b s e r v e d earlier. 6. Nigh Reynolds Number T e s t Equipment Design of the h a r d w a r e is p r o g r e s s i n g s a t i s f a c t o r i l y . PLuiDyne e s t i m a t e s t h a t d e s i g n work w i l l be completed in l a t e Kay. P r o c u r e m e n r a c t t o n s have been i n i t i a t e d f o r the sphere and the s u p p l y t u b e . The s e t t l i n g chamjer and a few other miscellaneous items will be o r d e r e d s h o r t l y . A l l procurement a c t i o n s are being h e l d in R&DO until f u n d i n g can be arranged. D i s c u s s i o n s are underway w i t h F&DO to determine working arrangements, l i n e s of c o m u n i c a t i s n s , a n d i r t c r f a c e requirements necessary to f a b r i c a t e a n d e r e c t the t e s t equipment. 7. Low D e n s i t y Calibration suns on t h e Mach 4 low Runs b o t h u p s t r e a m and dormstream of the n o z z l e e x i t i n c h e s . Resul t s from t h i s t e s t will d e f i n e the f 1 OW and tlbz Mach number g r a d i c n .~ c o n t i n u e d w i t h the i m p a c t p r e s s u r e p r o b e . dens l t y nozz Le have have been complctcd to a d i s t a n c e of 1 2 i s e n t r o p i c c o r e o f the A p e n d u l u m - ~ y p e m i c r o f o r c e b a l a n c e (KO. 220) h a s b e e n c a l i b r a t e d and installed in thc low dens ity w i n d t u n n e l . R e s u l t s thus f a r look v e r y p r o m i s i n g as d r a g forces have been r e a s u r e d on a h a l f c y l i n d e r a n d hemisphere m o d e l . P r e s e n t l y , t h e s e d a t a arc b e i n g u s e d t o c a l c u l a t e d r a g c o e f f i c i e n t s , a n d t h e r e s u l t s a r e b e i n g compared with theory and other published experimental r e s u l t s . Due to the size of t h e m o d e l s (3-inch d i a m e t e r sphere, 3- inch diameter by 6 - i n c h half-cyl i n G e r ) , the r c s u l t s will b c takcn f r o m the t r a n s i t i o n flo~t1r e g i m e . T h t s was; Other m o d e l s arc b e i n g v e r i f i e d by t h e measured experimental r e s u l t s . f a b r i c a t e d which w i l l e x t e n d r a n g e of drag forces to b e mcasured and will a l s o a1Lor.1 measurements t o b e m a d e ir, t h e f r e e molecular f l o w regime. (I$e w i l l . have Knudscn numbers of 1 < Kn < 3 d u r f n g our f i r s t e x p e r h e a t s .) �8. Heat Transfer Fnstrumentation The s t a t is t i c a l a n a l y s Fs c o n d u c t e d on the h e a t transfer gages has been continued. Thus f a r , no d i s t r i b u t i o n has been found whtch d e f i n e s t h e c h a r a c ~ e r itics s of the heat gages. Ames Research C e n t e r has b e e n very i n t e r e s t e d in our experiences and techniques concerning t h i n f i l m heat t r a n s f e r gages. They are devziaping a shock tunnel similar to ours. We have l o a n e d s m c i n s trumcntation items and samples of o u r h e a t transfer g a g e s . 9, Data Reduction Reduction 05 114 r u n s by R-AERO-AE of the S a t u r n V a c o u s t i c t e s t s was made by automated data handling a n d p r o c e s s i n g e q u i p m e n t . T h i s represents 40 percent of t h e d a t a t h a t are to b e r e d u c e d to sound p r e s s u r e levels. The r e d u c t i o n of t h e s e 12,000 a c o u s t i c measurements was t r a n s m i t t e d to R-AERO-AU March 29. The r e d u c t i o n program was i n t e r r u p t e d when the equipment w a s re-shipped to AEDC March 6 f o r t h e second p h s 2 test in the s u p e r s o n i c s e c t i o n of t h e PWT. The equipment was r e t u r n e d March 17 and is b e i n g reassembled to provide R-AERO-AU w i t h the remainder of the test data. It: appears t h a t R-AEBO-AE will reduce all d a t a to overall s o u n d p r e s s u r e l e v e l s , and R-COKE' will d o t h e s p e c t r a l a n d temporal r e d u c t i o n . Data w a s r e d u c e d d i g i t a l l y f a r t e s t s r u n in the TASF, 14inch w i n d t u n n e l , a n d the Pow d e n s i t y chamber. The program to r e d u c e t h e above m e n r i o n e d a c o u s t i c data was made f u l l y o p e r a t i o n a l . Most of these t e s t s r e q u i r e d a u t o m a t i c p l o t t t n g . It: is i n t e r e s t i n g to n o t e t h a t , f o r t h e p a s t few rnonchs, over one-half of our d i g i t a l data r e d u c t i o n e f f o r t is f o r t e s t s c o n d u c t e d at s i t e s other than MSFC. a. General The multiplex wide-band tape system purchased for use w i t h t h e Saturn V 4 p e r c e n t m o d e l was used to record d a t a f r m the 14-inch tunnel. The t e s t r e q u i r i n g the s y s t e m was a study of the press u r e f l u c t u a t i o n s in the s p e c i a l t e s t sectLon f o r the crossed-beam aerodynamic program. The above t e s t and t h e 4 p e r c e n t a c o u s t i c d a t a r e d u c tion and t e s tFng at AEDC I-lave u s e d a b o u t all available instrumentation manpower d u r i n g t h i s p e r i o d . �b. O r b i t a l Aerodynamics Scanner System A high s p e e d d i g i t a l s y s t m has been assembled by R-AERO-AEL for the a c q u i s i t i o n a n d determination of a vehicle's area and area mmtents. The sys tern is based upon converting the t e l e v i s e d image from a closed c F r c u i t t e l e v i s i o n camera i n t o a d i g i t a l measurement representation of t h e vehicle's area and area l o c a t i o n . An image m e a s u r e m e n t is r e c o r d e d in 1 / 6 0 of a second, b u t the t r a n s f e r of the d a t a to an IBM card for data reduction by R-AERO-AE computer complex r e d u c e s the s p e e d to 2 m i n u t e s f o r each image r e c o r d e d , i.e., each a t t i t u d e of t h e vehicle. (1) A computer program to s c a l e t h e data into area and area moments is b e i n g debugged. The system can b e f u l l y operational d u s ing the n e x t r e p o r t i n g period. (2) Purchased parts for another type of scanner s y s t e m based upon a bar of phatacells are a r r i v i n g . Manufactured p a r t s are expected f r o m R-ME in the next f e w d a y s . Control c i r c u i t s and w i r i n g d r a w i n g s are a l m o s t completed. Tt is e s t i m a t e d t h a t w i r i n g and checkout w i l l b e completed d u r i n g t h e next t w o months. c. High Reynolds Number Equipment P r e s s u r e T e s t i n g The high Reynolds number equipment is expected to r e q u i r e a large number (50-200) of chanfiels of pressure measurements for t y p i c a l models. E f f o r t s in d e v e l o p i n g the hardware and techniques are l i m i t e d . Two major problems e x i s t : Firsr, the downstream d i a p h r a g m subjects the model and i n s trurnentatTon to the high charge p r e s s u r e , t h e n d r o p s to a much lower running p r e s s u r e which is t h e d e s i r e d valve t o b e r e c o r d e d . This k m p l i e s t h a t high pressure gages and equipment must be u s e d with the problem o f r e s a l u t P o n at the low e n d , or the transducers m u s t b e valved o f f from the high pressure. Second, the large number of channels d i c t a t e a scanning type of measurement f o r economic p u r p o s e s , i f none other. Our p r e s e n t t h i n k i n g i s t o p u t all i n s t r u m e n t a t i o n inside the m o d e l , us ing s p e c i s l mu1 ti-channel i s o l a t i o n valves and s p e c i a l 'nigh s p e e d s c a n n i n g valves. These items will b e m o d i f i c a t i o n s of c u r r e n t l y available hardware. One scanner s h o u l d be a b l e t o measure p r e s s u r e every 5 or s o milliseconds; 10 ganged scanners w o u l d a c c m o d a t e 100 c h a n n e l s i n the 5 0 - m i l l i s e c o n d f l o w time. These figures a r e v e r y reasonable f o r the f a c i l i t y and m o d e l s i z e s i n v o l v e d . �E. Thermal Environment Branch 1. Saturn V - S-11 Stage The B o e i n g Company has taken over the d i r e c t i o n of t h e multi-protuberance h e a t i n g test. A r u n s c h e d u l e has been d r a m - u p a n d the p r o t u b e r a n c e models are b e i n g reinstrumented by the F a c i l i t i e s Branch u n d e r the d i r e c t i o n of Herb B u s h . A d d i t i o n a l ~hermocouples a r e to be installed on f o u r of the models, T h e t e s t p l a c e w i l l a l s o have to be mod if i e d and the e x t e n t of m o d i f i c a t i o n is b e i n g determined. T"?e test will b e conducted at the Langley Research Center in the f a l l . 2. S a t u r n IB a. Fl i g h t E v a l u a t i o n Because of an expansion i n scope for the f i n a l r e p a s t of the SA-203 infrared spectrometer f l i g h t data evaluation, rhe report has been delayed; however, F t has been approved for publication a n d s h o u l d be d i s t r i b u t e d soon. A few m i n o r tasks remain to be completed in preparation for the next thermal data evaluation, Needless to say, these t a s k s are n o t u r g e n t s i n c e the SA-204 l a u n c h has been delayed. b. Base and Aerodynamf c Heating The SA- 206 maximum aerorherrnad ynamic environment was p u b 1 ished i n r e p o r t TN-AP-67-174. An addendum to the S A - 2 0 4 launch environment r e p o r t (TK-AP-66-79) has b e e n pub1 i s h e d This addendum c o n t a i n s t w o figures . t h a t were rnis labeled and i n c o r r e c t 1 y p l o t t e d in t h e o r i g i n a l document. These i n a c c u r a c i e s , however, d o n o t affect the o r i g i n a l conclusions a n d in no way j e o p a r d i z e the SA-204 launch vehicle. The o r i g i n a l c o n c l u s i o n s were made on the b a s i s of rough p l o t s t h a t were c o r r e c t . The SA-205 launch vehicle t h e m 1 envfronments have been p r e d i c t e d and a r e scheduled to be reviewed. The e n v i r o m e n t s are to b e used for p o s t - f l i g h t data comparisons and r e q u i r e d s t r u c t u r a l temperature a n a l y s e s , and s h o u l d b e released on s c h e d u l e . c. 5 - I B High Angle of Artack Aerodynamic H e a t i n g The manufacturing of o u r m o d e l began in early March a n d is progressing smoothly. Since spot welding the thermocouples to t h e i n s i d e o f the c y l i n d r i c a l shell i s n o t the p r o b l e m i t was expected The use to b e , t-hat portion of the manufacturing will b e done inchouse. of an a n a l o g computer TO r e d u c e the t z s t data is b e i n g s t u d i e d . �' h e S a t u r n V!Voyager thermal a n a l y s i s for t h e maximum h e a t i n g t r a j e c t o r y has been completed for the continuum flow regime a n d the r e s u l t s will b e p u b l i s h e d soon. l i e a t r a t e s f o r the s l i p a n d f r e e molecular flow regime h a v e b e e n calculated up to o r b i t a l ;ltituc?e. Knudsen numbers were c a l c u l a t e d f o r variotzs vehicle l o c a t i o a s . TIc nose s e c t i o n was f o u n d to er?ter t h e sl i~ flaw r e g h e at an a l t i t u d e of approximately 81,000 feet and t h e e n t i r e vehicle was in t h e s l i p flow r e g i m e at a n a l t i t u d e of 235,000 f e e t . The vehicle entered the free m o l e c u l a r flow regime a t an a l t i t u d e range of 3 6 2 , 0 3 0 to 603,000 f e e t (depending on the p o r t i o n of t h e v e h i c l e being cons i d e r e d ) . The h e a t r a t e s in r h e trznsition regime, between s l i p and free molecular f l o w , arc being c a l c u l a t e d as a l i n e a r v a r i a t i o n of the Knudsen number between t h e i r values a t the e x t r e m e s of the t r a n s i t i o n r e g i o n . Completion of t h t s l a s t calculation w l l l complete the h e a t r a t e h i s t o r y f o r the a s c e n t phase a£ f l i g h t . The cal c u l a t i a n s of orbital h e e t i n g d u e to radiation a r e in progress. A d e s c r i p t i o n of the Voyager vehicle and i t s o r b i t is b e i n g " i n p u t " t o a Hear Flux computer program. 4. M T s cel laneous a. - eonductton Ablation A n a l y s i s U s i n g a Lax-Wcndroff T y p e D i f fercnce Scheme Equa Lions have been d e r i v e d for che one-d h e n s i o n a l heat conduction problem u s i n g a Lax-Wendreff t y p e difference scheme. The e q u a t i o n s vill b e p r o g r a m e d to check the s t a b i l i t y a t the s u r f a c e where scme d i f f i c u l t y was encouctered in es tab1 i s h i n g a genes21 express i o n f o r t h e s t a b i l j t y c r i t e r i a b e c a u s e o f the i n t r o d u c r i a n of c e n v t c t i v e heat t r a n s f e r . A n a l y t i c r e s u l t s i-ndicate an i n c r e a s e in r k e F o u r i e r m o d u l u s of at 1 e a s t two to four times t h a t of t h e c n n v e n r i o n a l "forward d i f f e r e n c e " scheme. T h i s p r o c e d u r e w i l l e v e n t u a l l y b e ex t e n d e d to i n c l u d e an ablating m a t e r i a l i n an e f f o r t to iessen rhe s ~ r i n g e n t s t a b i l i t y c r i t e r i a of the " forwzrd d i f f e r e n c e scheme , I 1 b. Development of a n Orbital H e a t i n g Computer Progran The e x i s t i n g HTL o r b i t a l heating c o m p u E e r progrzm is b e i n g m o d i f i e d t o t n c r e a s c irs usefulness a n d v e r s a t i l i t y . These m o d i f i c a r i o n s c o n s i s t of f i v e additional s u b r o u t i n e s and m y be l i s t e d a5 f o l lmrrs: (i) A n o p t i o n that w i l l allow che u s e r to d i v i d ~a s u r f a c e of r e v o l u t i o n i n t o a n a r b i t r a r y r , s n h e r of d i s ~ s . Each d i s c i s t h e n equally s u b d i v i d e d i n t o a n arbitrary number of s u r f a c e c l e m e n t s a n d t h e L r c e n t r o i d s caLcu!ated. This i n E o r m a t i o n is T e d i n t o the b a s i c program which t h e n caI cula t e s the c o r r e s p o n d ing u n i t n u m l s a n d inci.d e n t heat flux. �(2) An option f o r u s i n g o r b i t a l mzchanics f o r a n (3) Tables for controlling the s u r f a c e a b s o r p t i v i t y as of incidence. e l l i p t i c orbit. a f u n c t i o n of t h e angle (4) An o p t i o n for "selec~ive" plotting of heat f l u x v e r s u s rime. (5) An o p t i o n f a r i n t e g r a t i n g incident heat flux over the en t i r e v e h i c l e . Mathematical formulation of these sodificatFons was completed d u r i n g the p a s t two months. Computer p r o g r a m i n g of these modif i c a t i a n s s h o u l d be c m p l e t e d soon, c. A n a l y t i c a l S o l u t i o n of Three-Stream Mixing R a d i a l t e m p e r a t u r e p r o f i l e s f o r rhe three- s tream m i x i n g were c o l s truc t c d at several axial l o c a t i o n s . A 1 t h o u g h the p r e d i c t i o n of o n s e t of a f t e r b u r n i n g appears r e a s o n a b l e , a q u e s t i o n e x i s t s as to the v a l i d i t y of t h e i n p u t f o r the t e m p e r a t u r e and c o m p o s i t i o n . These input v a l u e s are being checked. outs to determine the e f f e c t on the p r e d i c t e d s t a r t of a f terburning. case d. A n a l y s i s of Flow F i e l d Solutions Involving Reacting Fluids A h e u r i s t i c approach is being followed to u n i f y the rechniques of t r e a t m e n t of non-equilibrium fluid flows. Included will b e a linearization technique as a p p l i e d to t h e equations of chemical r e a c t i o n , a a e t h o d of s o l u ~ i o nf o r the l i n e a r s e t which evolves, an e x t e n s i o n of the procedures to two-dimensional problems, and r h ~a p p l ic a t i o n t o a f l u i d problem o f a moving s t r e a m w i t h r e a c t i o n s . e. Nozzle and J e t Wake Study The u n s t e a d y equations of motfon used in the t r a n s o n i c f l o w s o l u t i o n have been c a s t in a d i f f e r e n t form a n d reporgrammed to h a n d l e f l o w s w i t h f u e l s t r i a t i o n s . A s u c c e s s f u l c a l c u l a t i o n of a t r a n s o n i c f l o w f i e l d w i t h Q / F g r a d i e n t s has been m a d e . This c a l c u l a t i o n , which d i f f e r s from the supersonic a p p r o a c h previous ly r e p o r t e d , i n d i c a t e s t h e same t r e n d , t h e r e b y s u b s t a n r i a r i n g r h i s m e t h o d af a n a l y s i s . Good c o r r e l a t i o n of the Rocketdyne v e r n i e r e n g i n e measured data w i t h t h e method of characteristics has been o b t a i n e d f o r These d a t a , which c o n t a i n d e f i n F t e O/F g r a d i e n t e f f e c t s , the e x i t p l a n e . have been successfully c o r r e l a t e d . �f. Equilibrium Real Gas/~ormal Shock Program f o r S t a g n a t i o n P o i n t Heating Two s t u d i e s a r e b e i n g conducted. The f f r s t is to d e v e l o p c o r r e l a t i o n formulae f o r convective heating as a p p l i e d to e n t r y into a p o s t u l a t e d Martian amosphere. Essential1 y, t h i s s t u d y involves performing normal shock c a l c u l a t i o n s and boundary layer solutions for t h e gas m i x t u r e u n d e r consideration. The h e a t i n g rates w i l l then be c o r r e l a t e d on t h e b a s i s of f r e e s t r e m entry conditions. A problem w i t h a modified v e r s i o n of t h e nonnal shock code w a s discovered when attempting calculations w i t h the Martian atmosphere. This d i f f i c u l t y has been resolved and work on t h e normal shock c a l c u l a t i o n s is progress i n g . The second s t u d y involves a review of t h e y l ~ y s i c sand f l u i d mechanics of r a d i a tion-coupled blunt body flow f i e l d s A solution, d e v e l o p e d b y Lockheed' s P a l o A t t o Res e a r r h Laboratories , to t h e v i s c o u s hypersonic shock layer with r a d i a E i o n coup1 ing has h e e n reviewed. . g. Theoretical and Experfmental Investigation of T e k t i t e Ablation The g o a l of t h i s s t u d y is to evaluate s u r f a c e effects d u r i n g ablation of t e k t i t e materials. Three experimental t e s t s u s i n g a small L O X / I - I ~ engine for s y s tern checkout and La determine p h o t o g r a p h i c plume geometry h a v e been complefed a: the MSFC T e s t L a b o r a t o r y . Because oE t h e o p t i c a l p r o p e r t i e s of a LOX/H, plume, some d i f f i c u l t y was expected with t h e p h o t o g r a p h i c measurements; however, s a t i s f a c t o r y r e s u l t s were o b t a i n e d by u s i n g i n f r a r e d film t o photograph t h e plumes. h. Base P r e s s u r e and Environment The p e r t i o n s of t h i s task now b e i n g i n v e s t i g a t e d involve :he t u r b u l e n t boundary lager growth on nozzle walls with mass injection rnd the r e a c t i n g shear l a y e r at the plume boundary. The Technical Data Release g i v i r - g the r e s u l t s of t h e v i s c o u s m i x i n g analysis of a sea-level F-1 plume is complete. Five a d d i t i o n a l analyses of sea-level v i s c o u s plumes a r e in progress. These i n c l u d e t h e H-l e n g i n e , the S-IC r e r r o mator, the S - I 1 r e t r o and u l l a g e motors, and the S-IV13 ullage motor. The investigation of t h e s e s o l i d r n o t ~ r sat s e a level was prompted by t h e t h r e a t of z c c F d e n t a 1 iglition of anf of these motors while t h e S a t u r n V is on the pad o r in t h e V e r t i c a l Assembly B u i l d i n g . �i. S t a g e Separation Thermodynamics The t u r b u l e n t flow s e c t i o n of the LMSC/WC Real Gas Boundary Layer Program i s b e i n g s t u d i e d e x t e n s i v e l y to ensure accuracy of t h e method of calculation of all p r o p e r t i e s i n the boundary layer. Two approximate relations for the s k i n f r i c t i o n c o e f f i c i e n t , based on the Reynolds number evaluated at: reference conditions, have been i n c l u d e d i n t h e program for c m p a r i s o n w t t h the r e s u l t s of the iteration scheme. Results of the technique t o f i n d corrections to an axisymnetric method-of-characteristics solution of t h e impingement f l o w f i e l d to approximate the three-dimens i o n a l "spreading" effects of r o c k e t exhaust plume i m p i n g i n g on a solid boundary are being c o r r e l a t e d and studied . g. A b l a t i v e Environment Analysis This t a s k involves t h e development of a method of anal ys is a n d r e l a t e d d i g i t a l computer program to a n a l y z e the thermal d ecompos ition- in-depth of c k a r r i n g - t y p e ablative materials. Also, v a r i o u s " h o t - j o b s ' h c o n c e r n i n g a b l a t o r a p p l i c a t i o n s a r e performed. D u r i n g t h i s month wark continued on the decomposition-in-depth program. A technical review was held w i t h R-AERO-AT to d i s c u s s d e t a i l s of the work to d a t e and plans f o r future areas to be i n v e s t i g a t e d . F . Unsteady A e s odynarnics Branch 1. I n f l i g h t Fluctuating Pressure and A c o u s t i c Environments a. The s u p e r s o n i c phase (M = 1 . 6 to 3 . 0 ) of the 4 p e r c e n t S a t u r n V f l u c t u a t i n g p r e s s u r e test conducted in t h e AEDC 1 6 - f o o t wind tunnel was ctsmpleted on I%rch 2 1 , 1967. The s t a t i c pressure c o e f f i c t e n t s and velocity r a t i o s f o r this test were computed on l i n e and r e c o r d e d on magnetic t a p e . This informa tion will be available a s soon as it can be p l o t t e d on t h e a u t o m a t f c data p l o t t e r a t the MSFC 1 4 - i n c h wind t u n n e l . The f l u c t u a t i n g pressure data were a l s o recorded on magnetic tape. Data r e d u c t i o n and a n a l y s i s w i l l b e g i n on the f l u c t u a t i n g pressure d a t a as soon as computler time and manpower are available. b. Pre1imir.ary r e v i s e d fluctuating pressure environments d e r i v e d from the AEDC m o d e l experiment have been g i v e n to R-P&VE-S f o r s t r u c t u r a l response calculations. The fluceuaring pressure d a t a r e d u c t i o n from t h e c. AEDC experiment is at the following s t a g e : �Transonic: (1) A l l root mean s q u a r e v a l u e s have been c o m p l e t e d . (2) S p e c t r u m a n a l y s i s o f seven p e r c e n t of available data i s b e i n g c o n d u c t e d (3) N o c o r r e l a t l o n analyses have h e ~ n . however, it is p l a n n e d to Let a c o n t r a c t o r do r h e s e a n a l y s e s . attempted; Supersonic: KO data analyses have b e e n i n i t i a t e d . d. Task O r d e r No. 9 for Baganoff A s s o c i a t e s was written f o r r e d u c t i o n of t h e fluctuating p r e s s u r e data on the MSFC/AYES s e p a r a t e d flow e x p e r i m e n t . Mach numbers from 2.5 to 3.5 were of concern in t h i s r e q u e s t for cross-psd' s a n d narrow-band t i m e c o r r e l a t i o n s . Data from t h c las t task o r d e r were r e c e i v e d chis week and w F l l b e combined with t h e o t h e r s t e p - h e i g h t and shoulder-angle con£ i g u r a t i o n s i n a n attempt t o d e f i n e t h e e n v i r o n m e n t a l characteris tics a£ t h e phenomena i n d u c i n g t h e fluctuzting pressure environments in the various d i s t i n c t p o r t i o n s of t h e flow in terms oE t h e flow parameters and the geometry. 2. Launch S i t e A c o u s t i c E n v i r o n m e n t s a . The AS-202 i n f l i g h t a c o u s t i c datz evaluation r e p o r t has been completed and will b e d i s t r i b u t e d soon. b . Wyie C o n t r a c t EAS8-2iO60 e n t i t l e d "Investigation of t h e Noise G e n e r a t i o n Mechanisms of D e f l e c t e d and U n d e f l e c t e d S u p e r s o n i c Rocket Exhaust" has been extended for a n o t h e r y e a r . An experiment a s s o c i a t e d w i t h one o f the tasks of t h i s year's e f E o r t i s in progress. T h i s experiment w a s d e s i g n e d to measure the n o i s e generated by various r e g i o n s of a s u p e r s o n i c j e t . c. The j e t i.mpingement program f o r a c q u i s i t i o n of a c o u s t i c d a t a i s nearing complerion. Three more t e s t s are to be perEormed whes, t h e p r o b l E m s c o n c e r n i n g adequate e n g i n e o p e r a t i o n a l parzrnc t e r s a r e c o r rected. Overall sound pressure level t i m e histories have b ~ e nr u n on t h e c u r r e n t l y available t e s t data. Spectral analyscs a r e t o bc s e l c c t e d for c o n d u c t a n c e by R-TJXST-ICA. T e s t s s h o u l d be c o m p l e t e d w i t h i c one month. d. F u l l - s c a l e 5-2 (LOXILH:) horizontal undeflec?ed f l o w e n g i n e t e s t s a r e to b e conducted at s t a n d number 500 CTL T e s t Laboratory. The e n g i n e is to b e o p e r a t e d f o r 30 seconds p e r t e s t from 200,000 p o u n d s t h r u s t dotm to 20,000 pounds t h r u s t i n s t e p s and t h e n i n a t h r o t f l a b l e m o d e if no problems a r i s e . Nozzle expans ion r a t i o s of 2 7 . 5 : 1, 14: i , a n d 4 0 : T are te b e used in the program. C o o r d i n a t i o n w i t h T e s t L a b o r a t o r y �is underway to a c q u i r e a c o u s t i c d a t a f r o m the engine area and from the farfield g r o u n d plane area. These data w i l l be used to obtain the a c o u s t i c sound source characteristics f o r t h i s undeflected engine in the chosen aperational modes . e. Acoustic d a t a from AMTF on the Bell-Cone engine n o z z l e t e s t s a r e k i n g analyzed. Anomalies in several t e s t s have made necessary two additional t e s t s . From pxeliminary view, the cone nozzles pro- d u c e d m o r e Energy i n t h e higher f r e q u e n c y bands t h a n d i d the b e l l n o z z l e ; however, more lm.7 Srequeccy e n e r g y i s observed from the b e l l t e s t s . The OA SPL v a l u e s show less v a r i a t i o n than the s p e c t r a , s i n c e the energy e f f e c t i v e l y s h F E t e d to a lower frequency peak value, More d e t a i l e d analyses are being conducted. A c o u s t i c data concerning engine clustering e f f e c t s E i g h t c l u s t e r s with various crus ter diameters and e n g i n e separations a r e b e i n g c o n s i d e r e d i n s u p p l e m e n t i n g similar d a t a a c q u i r e d last: year under c o n t r a c t w i t h Martin Company. have been reques t e d . S i n c e m o d e l fabrication is about one m o n t h about one month away, a c o u s t i c tests f o r the 1120-scale S a t u r n V launch v e h i c l e will b e g i n soon. Problems w i t h the phase accuracy have arisen because of a n o i s y t u b e in the cathode follower, P o t t i n g of t h e tube has n o t solved t h i s problem. Tube inadequacies are blamed for the d a t a s y s t e m delay. The MLV s t u d y with the four s o l i d p r o p e l l a n t s t r a p - o n uoFts will l i k e w i s e be d e l a y e d since t h e y a r e scheduled to follow t h e a c o u s t i c t e s t s f. High Reynolds Number Equipment (J3RNE): Tests have been c o n d u c t e d t o determine zhe f e a s i b i l i r y of exhausting into a c l o s e d sphere. V a r i o u s techniques of reducing t h e pressure and g l o a d i n g have been t e a t e d in relation to exhausting rhrough a p e r f o r a t e d p i p e a r r a n g r r n ~ n t i n t o t h e sphere. An o p t i m u m p e r f o r a t e d pipe based on t h e resulting d i m i n i s h e d ~ c o u tsi c environments and g loading on the model s p h e r e were s e l e c t e d . Because a£ the marginal environments w i t h r e s p e c t t o personnel exposure criteria that are p o t e n t i a l l y r e l a t e d to o p e r a t i o n of the f u l l s c a l e f a c i l i t y , a d d i t i o n a l t e s t s a r e t o be performed on a m o d e l sphere of a more realistic s c a l e ; the latter madel was much more massive a t i d s i g i d because of the unscaled , thickness. A1 t e r n a t e methods of e n v i r o n mental r e d u c t i o n are to be surveyed and experimentally inves t i g a t e d if no severe problems i n t e r f e r e ; the o t h e r methods i n c l u d e p a r t i a l a n d / o r complete s u b m e r s i o n o f t h e sphere in an earth-like m e d i u m , a d u c t e d p i p e arrangement in ehe form of a c o n v e n t i o n a l muffler d e s i g n , and other f e a s ible approaches if t i m e and manpower permit. �3. Aeraelas t i c C h a r a c t e r f s t i c s a. P i t c h Damping The new dynamic b a l a n c e system, d e s i g n e d for u s e in TWT, has been completed a n d w i l l b e t e s r e d soon. Arrangements a r e b e i n g m a d e t o have the data from the p i t c h damping tests a n a l y z e d by M C u n d e r an e x i s t i n g support contract. The t e s t is scheduled to r u n the f i r s t t w o weeks in June. the MSFC 14-inch b. S t a b i l i t g Derivatives The a n a l y s i s of a b ~ d yoE revolution in u n s t e a d y f l o w is complete a n d a r r p o r l r entitled "A L i n e a r i z e d C h a r a c t e r i s t i c s Method for S u p e r s o n i c FLOW Pas t Bodies Q£ Revolution Performing Bending Oscill a t i o n s " w i l l b e p u b l i s h e d soon. The i n v e s t i g a t o r s i n this s c u d y were D. L i u , b o t h of Lockheed. A linearized c h a r a c t e r is L ics: inti Lliod Ilas been ou L l i n e d for supersonic ilow p a s L £ l e x i b l e b o d i e s of revolution which p e r f o r m l ~ wfrequency b e n d i n g o s c i l l a t i o n s This approach i s an e x t e n s i o n of previous work by Oswatitsch and Erdmann (1954) and P l a t t e r a n d Sherer ( 1 9 6 7 ) f o r r i g i d b o d i e s t o t h e c a s e of e l a s t i c b o d i e s . This extension r e q u i r e s a reformulation of t h e vhole problem in a w i n d - f i x e d c o o r d i n a t e system,whereas t h e previous approaches p e l r m i t t e l l t h e use of body-fixed c o o r d i n a t e s , A s s h o w n b y Hoffman and P l a t z e r (1966) a T a y l o r - s e r i e s e x p a n s i o n has to b e p e r formed i n w i n d - f i x e d c o o r d i n a t e s to o b t a i n a c o r r e c t formulation of t h e boundary conditions at: t h e o s c i l l a t i n g b o d y , t h u s g r e a t l y complicating t h e r z s u l t i n g e x p r e s s i o n s . Furthermore, i n t h e w i n d - f i x ~ dformular i o n t h e e q u a t i o n f o r the o s c i l l a t i n g body s u r f a c e c e a s e s to a p p l y in t h e n e i g h b z r h o o d o f rhe apex caus i n g compl i c a t i o n s in formulating g e n e r a l l y val i d s t a r t i n p c o n d i t i a n s M. F. P l a t z e r a n d . . 4. Panel F l u t t e r a. An investigation of n o n l i n e a r oscillations of a t h r e ~ dimensional. F l u t t e r i n g platc i n underway u s i n g thc E. H. Dowel1 analytical method for S a t u r n IB vehicles 204 to 2 0 7 . The p r o b l e m of two- a n d three-dimensional p l a t e s i n a h i g h s u p e r s o n i c f 1ow ilndergoing l i m i t e d oscillations has b e e n s t u d i e d by Dowell up t o t h e p l a t e l e n g t h a n d w i d t h r a t i o of two. The present: s t u d y involves t h e a p p l i c a t i o n of ow ell's method to l a r g e r characteristfc v a l u e s which e x i s t for t h ~ S a t u r n IB v e h i c l e , b . A l l of the d a t a frcm t h e wavy-wall p a n e l i l u t t e r t e s c s c o n d u c t e d in t h e dmes Research c e n t e r ' s 2 by 2- Eoor t m n s o n Fc w i n d tunnel bavc been r e c e i v e d by NSFC, and f u r t h e r d a t a r e d u c t i o n w i l l b e c a r r i e d o u t in the near f u t u r e . �5. S a t u r n V Grou rid W-ind s Data r e d u c t i o n for the f u e l e d w e i g h t condition i s c o n t i n u i n g to p r e d i c t full-scale b e n d i n g moments for t h r e e vehicle s t a t i o n s and d e f l e c t i o n s at t h e damper c o n n e c t s t a t i o n versus w i n d velocity. E I r . Moore of PGtW r e q u e s t e d t h i s i n f o r m a t i o n to q u a l i f y t h e damper reconnect c a p a b i l i t y . D u r i n g the i n i t i a l phase of these data analyses, it was observed t h a t t l ~ tr e s t d a t a from the u p p e r model measurement s t a t i o n c o n t a i n s poss i b l y two higher f r e q u e n c i e s superimposed on the f i r s t cantilevered frequency. It is surmtsed t h a t t h e s e h i g h e r f r e q u e n c i e s a r e s e c o n d and t h i r d cantilevered f r e q u e n c i e s ; however, because of d a t a r e d u c t i o n and Computation L a b o r a t o r y scheduling problems, t h e s e d a t a have n o t bcen cornplerely analyzed. 4 q u i c k look, however, i n d i c a t e s t h a t t h e deflections at t h e damper s t a t i o n d u e to rhesc h i g h e r f r e q u e n c i e s will b e small compared t a the d e f l e c t i o n s p r o d u c e d by t h e f i r s t mode f r e q u e n c y , A t p r e s e n t a p r e l i m i n a r y report c o n t a i n i c g p r e d i c t e d b e n d i n g moments a ~ deflcctians d based upon t h e f i r s r mode o n l y is being m i t t e n and will b e fallowed by a f i n a l r e p o r t c o n t a i n i n g rhe h i g h e r f r e q u e n c y data when a v a i l a b l e . VI. A S T R O D Y N M C S AND GUIDANCE THEORY DIVISION A. S c i e n t i f i c Advisory Office 1. In-House (a) A discuss i o n of a papcr by Chen and Yates w i l l appear in the ASPE Basic E n g i n e e r i n g along w i t h t h e p a p e r . ( b ) A p a p e r e n ~ i t l e d "on ~kamura's Uniqueness Theoremti has been accepted for p u b l i c a t i o n by the Proceedings of the American Math S o c i e tly. (c) The p a p e r , "Eps i l o n - F i x e d S t a b i l i t y and Vector Liapunov Functions, " has been subrnFtted to the Proceedings of the .4merican M a t h S o c i e t y . In the p a p e r necessary and s u f f i c i e n t c o n d i t i o n s are obtained f o r an i n i t i a l c o n d i t i n n set to correspond to s o l u t i o n s bounded b y a f i x e d bound. The concept is extended to v e c t o r Eiapunov f u n c t i o n s where suf fLc i e n t c o n d i t i o n s a r e o t tained . ( d ) The p a p e r , '%n t h e Equivalence of C e r t a i n S t a b i l i t y P r o p e r t i e s , " c l a r i f i e s some of the known stability d e f i n i t i o n s and shotcs t h e r e l a t i o n w i t h the right-hand s i d e s . �(el Concepts in f i n i t e s t a b i l i t y are under c o n s i d e r a t i o n , and a comprehensive unified summary of the r e s u l t s is b e i n g completed. Necessary and s u f f i c i e n t c o n d i t i o n s a r e o b t a i n e d f o r finite s t a b i l i t y , and v e c t o r Liapunov f u n c t i o n s are shown to b e extremely us e f u 1. (George a n d Gund ers on) 2. Contracts a. Brown U n i v e r s i t y ( C o n t r a c t MS8-11264) I n f a n t e is c o n t i n u i n g h i s work on the s t a b i l i t y of t i m e varying systems. He is now c o n s i d e r i n g equations b y averaging t h e m through a Liapunov f u n c t i o n and exploFting the Wazewski i n e q u a l i t y . h few p r o m i s i n g results have been o b t a i n e d . Meyer is c o n t i n u i n g l z i s research on he e x i s t e n c e of global L i a p u n o v f u n c t i o n s . At present it seems 1:kely t h a t some of t h e r e s u l t s obtained f o r two-dimensional sys terns can be c a r r i e d over to the n-dimens i o n a l Mors e-Smale s y s terns. Weiss is working on a cmprehens i v e t h e o r y of c o n t r o l l a b i l i t y f o r nonlinear ttme-varying d i f f e r e n t i a l s y s t e m s which c o n t a i n delays. One of the main r e s u l t s w i l l be of the following form: R non1inear delay-differential s ys tern is controllable w i t h r e s p e c t to all i n i r i a l f u n c t i o n s in a neighborhood of t h e origin of a given f u n c t i o n space B if its " f i r s t variation" is completely controllable with r e s p e c t to B. Combining t h i s r e s u l t w i t h a n a p p r o p r i a t e theorem on s L a b i l i t y u n d e r perturbing forces will p r o d u c e a global controllab i L i t y c r i t e r i o n for a large class of delay-differential systems, These r e s u l t s are expected to s t i m u l a t e research on o p t h a 1 c o n t r o l f o r s u c h s y s t e m s f n i ~ h i c hthe t a r g e t set is in a Banach space rather than in Euclidean s p a c e . Miller i s c o n r i n u i n g h i s work on weak solutions of n o n l i n e a r h y p e r b o l i c p a r t i a l d i f f e r e n t i a l e q u a t i o n s . This inwes t i g a r i o n is directed toward f i n d i n g c x i s t e n c e and uniqueness theorems in e q u a t i o n s w i t h more than two i n d e p e n d e n t variables. b. Drexel I n s t i t u t e ( C o n t r a c t M S 8 - 2 0 3 4 7 ) Most of our e f f o r t s d u r i n g F e b r u a r y a n d & r c h were devoted to attempts t o prove a theorem conjectured in t h e m o n t h l y r e p o r t f o r J a n u a r y . Only limited p a r t i a l r e s u l t s have been o b t a i n e d . These v i l l b e announced l a t e r . �c. G e n e r a l P r e c i s i o n Aerospace ( C o n t r a c t NAS8-20026) Work has been c o n t t n u i n g in the develaprnentz of the d i g i t a l programs t h a t w i l l normalize a time-dependent H a r n i l t o n i a n to second order. The p r e s e n t s t a g e of t h e development is in the area of us ing t h ~ characteris t i c matrix of the related l ir.ear d i f r ' e r e n t i a l equat i o n to o b t a i n the r e q u i r e d p e r i o d i c transformation matrix g i v e n b y F l o q u e t Theory. 3 (Dearman) Optimization Theory Branch 1. Sacurn V / ~ o ~ a g eShroud r Study A m ~ m o r a n d u mdocumenting preliminary r i g i d body c o n t r o l responses a n d a s s o c i a t e d b e n d i n g moments f o r t h e S a r u r n VlVoyager ( 4 5 foot c y i i n d r i c a l payload) w i t h a t t i t u d e control sys tern w i l l soon b e p u b l i s h e d . The memorandum p r e s e n t s d a t a f o r u s e in shroud d e s i g n , e x t e n d i n g e a r l i e r s t u d i e s and i n c l u d i n g seven t i m e p o i n t s a l o n g t h e f i r s t s t a g e t r a j e c t o r y f ~ the r d e s i g n w i n d c o n d i t i o n s , 95 p e r c e n t a r c h w i n d p r o f fie, and maxfmum wFnds f o r currently p l a n n e d miss i o n s , December 95 percent wind p r o f i l e . Future e f f o r t s will be d i r e c t e d toward establishing c a p a j i l i t y of various s h r o u d l e n g t h c o n f i g u r a t i o n s to tiriths tand g i v e n w i n d c o n d i t i o n s . This information w i l l b e u s e d i n launch p r o b a b i l i t y s r u d i e s . 2. Analytic R e d u c t i o n of Optimal Trajectory Problem A computer program u s i n g a newly discovered transformation which r e d u c e s the determination of an o p t i m a l vacuum f l i g h t t r a j e c t o r y t o the s o l u t i o n of n i n e f i r s t o r d e r d i f f e r e n t i a l e q u a t i o n s i n s ~ e a dof twelve and the i s o l a t i o n of two unknowns i n s t e a d of f i v e w i l l be comp L e t e d soon. This program s h o u l d c o n s i d e r a b l y reduce rhe t i m e r e q u i r e d to compute an optimal trajectory. At: present an e f f a r ~to check the new program a g a i n s t an e x i s t i n g program is underway. An i n s t a b i l i t y in t h e i s o l a t i o n p r o c e d u r e which is used to s a l v e the two-point boundary value p r o b l e m has been e n c o u n t e r e d . The i s o l a t i o n scheme works corr e c t l y for c e r t a i n problems b u r founders on others. Improvements on he i s o l a t i o n scheme a n d other component parts ~f the over-all program are under study. An attempt t o m o d i f y the analytical equations used in this program to a more convenient form is b e i n g m a d e . No new integrals of the s y s t e m have been found and p r e s e n t work is d i r e c t e d toward t h e d i s c o v e r y of a c a n o n i c a l transformation which i n c o r p o r a t e s t h e k n o m t h r e e integrals i n t o Lhe Harniltonian by direct e l i m i n a t i o n of variables c o n j u g a t e t3 the momenta represented by these i n t e g r a l s . �3. Voyager S p a c e c r a f t A t t i t u d e C o n t r o l S t u d i e s are p r e s e n t l y i n progress on functional d e s i g n of t h e a t t i t u d e c o n t r o l s y s t e m for t h e Voyager spacecraft. Modes of c o n t r o l b e i n g investtgated i n c l u d e a c q u i s i t i o n of c e l e s t i a l r e f e r e n c e s , maneuvers p r e p a r a t o r y t o m o t o r l i r i ~ ~ g sand , c r u i s e u r l i m i t cycle operation. Disturbance t o r q u e s to b e con; i d e r e d i n i n t e r p l a n e t a r y fl i g h r a n d Mars o r b i t have been computed and g a i n s , t h r u s t e r size, e t c . , are b e i n g parameterized t o minimize f u e l consumption and d e m o n s t r a t e a d e q u a t e performance u n d e r time and a c c u r a c y requirements a £ the m i s s i o n . T h e r e s u l t s of t h i s p r e l F m i n a z - y p h a s e of the s t u d y w i l l be p u b l i s h e d a t t h e end af A p r i l . 4, Reusable L a u n c h V e h i c l e Control A paper e n r i t l e d " C o n t r o l S y s t e m s f o r R e u s a b l e Launch Vehicles" has b e e n p r e p a r e d for p r e s e n t a t i o n at tlre SAE Space Technology Conference to be h e l d on May 9-12 at Palo Alto, C a l i f o r n i a . The paper c a n c l u d e s t h a t t h e r e a r e apparently no c o n t r o l requirements f o r t h i s class of v e h i c l e w h i c h demand development of new rechnology a r e a s ; howe v e r , s e v e r a l a r e a s of r e u s a b l e v e h i c l e d e s i g n can d i r e c t l y b e n e f i t h y early integration of c o n t r o l capabilities. a. S a t u r n VlVoyager Load R e l i e f Objective: To d e v e l o p an e f f e c t i v e load r e l i e f c o n t r o l system f o r S a t u r n V/Voyager. T h e c o n t r a c t o r made an oral p r e s e n s a t i o n of the r e s u l t s o f t h e c u r r e n t s t u d y on F e b r u a r y 14. The f i n a l r e p o r t has bcen a p p r o v e d a n d copies w i l l soon b e d i s t r i b u t e d . Work on t h e s t u d y e x t d n s ion, w h i c h \#:ill apply t h e control t e c h n i q u e to t h e current 4 5 - f o o ~paylozd conf i g u r a t i o n a n d c o r r e c t t w o d e f i c i e n c i e s o f the o r i g i n a l c o n t r o l s y s t e m , has been delayed p e n d i n g the r e l e a s e o f funds. b. Development of T o l e r a n t C o n t r o l System Objective: To develop centroll~rswhich max~rnizc thc t o l e r a n c e to veh iclc and environmental parameter v a r i a t i o n s . The technical s t u d y is complete and t h e F i n a l r e p o r t d r a f t has b e e n r e v i s e d . R e s u l t s of the s t u d y i n c l u d c t h e development o f a b a s i c s y n t h e s i s t e c h n i q u e u s i n g a h y b r i d computer s i m u l a t i o n nncj the a p p l i c a t i a n of t h i s s y n t h e s i s t e c h n t q u e in s e l e c t i o n o f a controller to meet s p e c i f i e d c o n d i t i o n s . The controller was r e l a t i v e l y s i m p l e i n concept, m e t the general requirements, a n d a p p e a r e d to b e relarively tolerant to paramctcr variations. �Thc synthesis rechnique needs f u r t h e r development in b r o a d e n i n g the class of c a n d i d a t e c o n t r o l s y s tems u n d e r c o n s i d e r a tion, and in inregraring f l e x i b l e vehicle requirements into the program. Yo funds a r e available to e x t e n d the c o n t r a c t . 6. mortlr American A v i a t i o n ( l A S 8 - 2 1 0 7 7 ) Objective: To e x t e n d t h e c a p a b i l i t y of a quas i-1 i n e a r i z a t i n n t e c h n i q U P f o r computing f i n i t e - t h r u s t: optimal trans f e r s . T h i s is a new contract exrending the work o f c o n t r a c t SAS8-20238. D u r i n g t h e first r e p o r t i n g p e r i o d of c o n t r a c t 1JAS8-21077, m o d i f i c a t i o r l s were i n i t i a t e d to rewrlte t h e existing quasl-llnear orbit transfer program in F o r t r a n R f o r u s e on the IBM 360 s y s tern. The program for s inglr center, t h r e e - d i m e n s i o n a l transfers is a n t i c i p a t e d ta advance t o c h c c k o u t s t a t u s w i t h i n three months. 7, Corncll Aeronautical Laboratory (NAS8-18054) Oh j u c t ive: To d e t e r m i n e the Eras i b i l i t y of applying a p timl c o n t r n l theory to tile s ynthcs i s of lau5ch vehf che c o n t r o l sys tems . Because of some p r o m i s ing new developments which have arisen in the c o u r s e o f thc investigation ( e . g m r a m o r e d i r e c t formulation of t h e s t o c h a s t i c o p t i m a l c o n t r o l p r o b l e m ) , it has been necessary to proceed a t a slower r a t e than was o r i g i n a l l y e n v i s i o n e d to achieve good u t i l i z a tion of t h e new r e s u l t s . To complete the work originally i n t e n d e d t o b e accompPished under khis c o n t r a c t , the contractor has requested a na-cos t e x t e n s i o n of three months ( t o J u n e 30, 1967). 8, Sys rems 'I'echnology, Lnc. (XAS8-11419) Objective: To d e t e r m i n e the L i m i t a t i o n s of conventional c o n t r o l s y s t e m s f o r v e h i c l e s e x h i b i t i n g a l a r g e amount of F n t e m o d a l coup l ing . The d r a f t of the final r e p o r t on t h i s c o n t r a c t , which was due l a s t December, was r e c e i v e d on March 30 a n d i s b e i n g r e v i e w e d . Objective: Te s t u d y the a p p l i c a t i o n of the S a t u r n V j V o y a g e r l o a d r e l i e f s y s t e m a n d other l o a d r e l i e f s y s t e m s t o the S a t u r n V/Apollo. Work on t h i s c o n t r a c t was i n i t i a t e d or March 2. E f f o r t s f a r have b e e n d i r e c t e d toward collection and preparation of thc i n p u t d a t a ( t h e v e h i c l e u s e d in t h e s t u d y will be chc SA-505), preparation of a s t u d y p l a n a n d schedule, and definition of c o n v e n t i o n a l c o n t r o l l e r s to be u s e d in t h e s t u d y , b o t h as c a n d i d a t e s and =or comparslson of performanct. w i t h a d v a n ~ e d cuntroll e r s . so �10, N o r t h r o p S c h e d u l e O r d e r No. 26 a. A n a l y t i c Design of Vehicle Control Systems Objective: To i n v e s t i g a t e a n a l y t i c a l d e s i g n techniques for l i n e a r systems. A s w a s p r e v i o u s l y r e p o r t e d , t h i s work i s being t e r m i n a t e d b e f o r e completion of a l l a s s i g n e d tasks because of the w o r k load r e q u i r e d on Voyager. A t e r m i t a l r e p a r t a n the r e s u l t s of L11e s t u d y t o d a t e has been t r r i t t e n and is b e i n g reviewed. b. C o n t r o l and Separation S t u d i e s of t h e Saturn V/Voyager O b j e c t i ~ e : To i n v e s t i g a t e load r e l i e f systems f o r t h e S a t u r n v l ~ o y a g e ra n d t o provide separation dynamic s t u d i e s f o r the Voyager s h r o u d d e s i g n s t u d y . Checkout of the program developec f o r s i m u l a t i o n of "over-the-nose" s h r o u d separation has been c m p l e t e d and s e l e c t e d c a s e s have been run w t t h t y p i c e l values of various parameters o f m o t i o n . 11. Narthrep Schedule O r d e r S o . 35 To d e s i g n and assess the p e r f o m a n c e o f a t t i tude control s y s t e m s f o r t h e Voyager xhich o p e r a t e d u r i n g p r o p u l s i v e Objective: maneuvers. This s c h e d u l e o r d e r was i n i t i a t e d d u r i n g this r e p o r t i n g C o n t r o l systems are to b e d e s i g n e d functionally for b o t h t h e period. l i q u i d a n d sol i d s p a c e c r a f t configurations. S t u d y of the pertinent phase B documentation, formulation of the s t u d y approach, and p r e p a r a t i o n of the necessary computer programs has been comple red. Performance of attitude/attitude-rate s y s t e m s d u r i n g t h e arrival d a t e separarion maneuver is b e i n g analyzed. C. A s trodynarnics Branch 1. I n t e r p l a n e t a r y T r a n s i t Studies (In-Rouse) a. Work has been completed on the extraction a£ a sing1.e p r e c i s i o n , power series integration, n-body deck from t h e d o u h l e p r c c i s i ~ n versior.. Work is contFnuing on the s t u d y of a " b e s t " i s o l a t i o n r o u t i n e f o r u s e in both o f t h e s e d e c k s . In c o n j u l c tion w i c h t h i s , a program f o r t h e IBM 1130 has been written, coded, and checked o u t which �c r ~ r n i j l l t c . , o r b i t ~ lp a r m e t e r s a r , d t h e a s s o c L a t e d v z i u e s of B a T a n d E.R at : I ; ~ r ias functions o l t h e injection c o n d i t i o n s at: e a r t h . A KASA technical memorandum rghicli p r o v i d e s a sampl c. V0q'agc.r trajecrory f o r u s e in p r e l i m i n a r y d e s i g n work is in r e p r o s c l c t i o n The r e p o r t c o n t a i n s an cxplana t i o n of t h e process tlut w a s u s e d in the s i . l c . c ~ i o nof he tra j i s c t o r y , problems i n v o i v e d w i t h i t s ger,ern t i o r , , and zr22s of f u t u r e s t u d y which n e e d co b e explascd in o r d e r to provide b c t t c r sarnpte trajectories. I n the meantime, work has been i n i r i a t e d to p r o v i d e t h r e e trajectories f o r each of the four Launch o p p o r t u n i t i e s : 1973, 1 9 7 5 , 1 9 7 7 , a n d 1979. The t r a j e c t o r i e s will, i n general, be t a k e n one from t h e b e g i n n i n g , one near the middle, a n d one from t h e end o f a l a u n c h p e r i o d w i t h i n each o p p o r t u n i t y . I t is p l a n n e d to p u b t i s h t h e s e t r a j e c t o r i e s in four reports c o r r e s p o n d i n g to the f o u r l a u n c h opportunities ( 3 t r a j e c t o r i e s in each r e p o r t ) . b. E x t e n s i v e checks a r e b e i n g m a d e of "he AV requirements for separatian of a r r i v a l d a t e s and for b r a k i n g into o r b i t and o r b i t t r i m maneuvers. The effects of Mars o b l a t e n e s s on Voyager t y p e o r b i t s a r c a l s o be'lng s t u d i e d . c. C e r t a i n m i n o r modifications have b e e n incorporated into the Marshall Interplanetary C o n i c Trajectory Program. These m o d i f i c a t i o n s , which a r e concerned p r i m a r i l y w i t h the o u t p u t capab i l i t i e s o f t h e program, w i l l p r o v i d e t h e u s e r a more complete d e s c r i p t i o n of the generated trajectory. Work continues on the incorporation of an autonm t i c p l o t t i n g routine i n t o t h e Marshall Interplanetary Conic Trajectory Program w h i c h will e n a b l e mechanical plotting of graphs resulting from t h e g e n e r a r i a n of s e l e c t e d trajectory parameters. d. Energy requirements for trans-Mass inject ion and arrival as functions of l a u n c h d a t e arc b e i n g p r e p a r e d for graphical p r e s e n t a t i o r 2 S u p p o r t Contract a. Cislunar Orbit Studies A l 1 c i s l u n a r p e r i g e e s t a b i l iza t i o n s t u d i c s havi. hc t.r: c o m p l c r e d a n d t h e r e s u l ~ sa r e p r e s e n t l y being corr,piled into a c m n r c hensive, three-part report which w i l l i n c l u d e : s t a b i l i z a t i o n Sy o~tini i n g the l a u n c h time, t h e p e r i o d , a n d the i n i t i a l e a r t h - m o o n p r o b e n n g l r s t a b i l i z a t i o n b y u s i n g a t r a n s v e r s e velocity i n c r e m e n t at a p o z e e ; a n d s t a b i l i z a t i o n by u s i n g b o t h transverse and r a d i a l velocity incremeazs at a p o q e e . �b. Interplanetary Transit Studies The m o d i f i e d v e r s i o n of the Harshall Interplanetary Conic Trajectory Program for b o t h powered and unpowered f l i g h t s has been complete1 y checked o u t a n d is operational for direct Ear th-Mars-Ear th miss i n n s a n d for e i t h e r Venus-Mars-Earth or Earth-Mars-Venus t r a j e c t a r i e s f o r t r a n s f e r s u s i n g e i t h e r option 1, 2 , o r 3 ( c o n s t a n t C3, s t r a i g h t run or minimum C3) for the f i r s t l e g of t h e trajectory and o p t i o n 1 or 3 f o r t h e s e c o n d leg. F u r t h e r additions te the deck are b e i n g made so t h a t t h e final v e r s i o n will allow t h e u s e of any combination of o p t i o n s 1, 2 , and 3 for c a l c u l a t i n g the i n d i v i d u a l s i n g l e leg t r a j e c t o r i e s t h a t a r e used in d , e t e r m i n i n g the trajectory requirements for s o u n d - t r i p f l y b y or swingby m i ss ions . The study o f the in-flight velocity impulse r e q u i r e d t o a c h i e v e an eight-day separation of a r r i v a l times f o r t w o Saturn V vehicles d e p a r t i n g e a r t h an a trajectory LO Mars has been comple r e d . Work is nearing completion on the generation of l a u n c h o p p o r t u n i t y graphs f o r t h e years 1 9 7 3 , 1975, 1977, a n d 1979. By p l o t t i n g and cross-plotting data generated by the JPL conic program, t h e completed g r a p h s w i l l show all p o s s i b l e launch p e r i o d s available d u r i n g each opportunity each opportunity b e i n g d e f i n e d by r ~ s t r i c t i o n sof the declination n f t h e outgoing asymptote, the. l a u n c h energy (C,), a n d the a r r i v a l hyperboltc excess velocity at Mars. - A study of various f l i g h t parameters f o r the type I1 Earth-Mars t r a j e c t o r i e s in the 1973-1979 time p e r i o d has b e e n i n i t i a t e d . The r e s u l t s of t h i s s t u d y w i l l be t h e p r e s e n t a t i o n of these parameters as functions c ~ f t h e l a u n c h d a t e s d i s t r l ' h r i t e d 1 5 d a y s to ~ a c hs i r i ~n f t h p departure d a t e s that allow minimum energy t r a n s f e r . Parameters t o b e c o n s i d e r e d i n c l u d e : arrival date, flight time, declination, righr ascens ion o r the d e p a r t u r e and arrival asymptotes relative to the central p l a n e t ' s equator and equinox, c~mmunication d i s t a n c e at a r r i v a l , d e p a r t u r e e n e r g y , h y p e r b o l i c excess s p e e d at a r r i v a l , i n c l i n a t i o n of the flight plane t o t h ~e r l i p t i c , t.he angl P between She depart- us^ asympt-ote a n d rhe s u n ~ e a r ~vhe c t o r , and the angle between the a r r i v a l a s y m p t o t e and t h e Mars-sun v e c t o r , D. G u i d a n c e Theory Branch 1. S u p p o r t C o n t r a c r S t u d i e s a. Power S e r i e s S o l u t i o n for I n i t i a l Lagrange Multipliers The energy, momentum, and transversal i t y cond iti o n s , expanded in t h i r d - o r d e r T a y l o r s e r i e s , have been expressed e x p l i c i t l y i n terns oi the Lagrange multipliers. Computer programs have been coded �f o r evaluating the c o e f f i c i e n t s of the mu1 t i p l i e r s in these s e r i e s , and t h e y a r e p r e s e n t 1 y o p e r a t i o n a l f o r the energy a n d two transversal ity c o n d i t i o n s . Work continues on the coding and "debugging" of programs f o r the o t h e r s e r i e s c o e f f i c i e n t s . b. Quasi-Optimal Guidance S t u d y Various cut-of f surfaces are b e i n g inves t i g a ~ e d i n c o n j u n c t i o n with the quasi-optimal guidance scheme. The ( r , v , 0) cut-a£ f s u r f a c e has been checked out; the (r ,v, 2 , i) and (r ,v,3, i, n> s u r f a c e s a r e be in^ checked o u t . Energy-angular momentum ( C s , C1) and energy-angular m o m e n t u m inclination (C3, Cl, i) surfaces are b e i n g formulated, c. Voyager Project S u p p o r t S t u d i e s Work has been inf t i a t e d to c a l c u l a t e S a t u r n V/ Voyager a s c e n t t r a j e c t o r i e s w i t h an escape energy of 32.5 km'/sec2 at l a u n c h a z i m u t h from 45 to 115 degrees (in 5-degree increments) e a s t of n o r t h . These trajectories w i l l then b e run (by in-house personnel) from e a r t h p a r k i n g o r b i t to Mars to simulate Voyager trajectories. A m o d i f i e d form of the lunar hypersurface has been u s e d for t a r g e t i n g of Mars t r a j e c t o r i e s . A 100 km out-of-plane p e r t u r b a t i o n of the injection point in parking o r b i t r e s u l t e d in only a 3000 km error in the m i s s d is tance at Mars. 2. Contracts a. Boeing - Rendezvous Guidance The f i n a l r e p o r t ? m s been received. b. Lockheed - Rendezvous Guidance The contract is being renewed and there was no work done d u r i n g t h i s p e r i o d . c. Uand e r b i l t U n i v e r s i t y Work is c o n t i n u i n g on o b t a i n i n g s u f f i c i e n t c o n d i t i o n s f o r the Mayer form of the extended Balza problem. The work of B l i s s and Hes t e n e s on the s i n g l e s t a g e Mayer problem has been s t u d i e d . It i s h o p e d that the Mayer form of the extended Bolza problem can be t r a n s formed such t h a t it becomes a s i n g l e stage Maycr problem. �d. General P r e c i s ion For the low-thrus t g u i d a n c e problem, the f e e d b a c k g a i n s d o not produce a s i g n i f i c a n t increase in a c c u r a c y over the open-Loop approach when o n l y t h e energy at c u t o f f i s s p e c i f i e d . The reason for this is t h a t t h e open-loop g u i d a n c e gives fairly good r e s u l t s when only the t e r m i n a l e n e r g y fs s p e c i f i e d ; thus to f u r t h e r test the approach, an a d d i t i o n a l c o n s t r a i n t such a s the r a n g e angle is b e i n g added to the guidance s i m u l a t i o n . 3. In-House Studies a. Voyager S t u d i e s A terminal g u i d a n c e s e n s i t i v i t y s tud y for t h e Voyager mission has been completed and the results a r e being p u b l i s h e d . A s t u d y was performed to determine the AV needed to accomplish the separation of arrival t i m e of the two s p a c e c r a f t a t firs f o r a l l t h e launch o p p o r t u n i t i e s . In t h i s s t u d y , c o n i c approximations were used; however, a check c a s e was computed on the JPL space d e c k t o v e r i f y that c o n i c approximations were s u f f i c t e n t f a r the s t u d y . A computer program h a s been developed which c a l c u l a t e s the m i n i m u m change in v e l o c i t y (AV) needed to t r a n s f e r from a s p e c i f i e d approach hyperbola to a s p e c i f i e d o r b i t about Yars. R o t a t i o n of p e r i aps is of tb.e p a r k i n g o r b i t away from t h e p e r i a p s i s a £ the approach hyperbola is c o n s i d e r e d in o r d e r to determine the AV p e n a l t y incurred by placing the p e r i a p s i s of t h e parking o r b i t near one of the terminators b. Various forrnulations of the bas ic Fletcher-PoweP I m i n i m i z a t i o n technique have been t r i e d on a set of t e s t f u n c t i o n s t o f i n d one y i e l d i n g t h e h i g h e s t rate of convergence. Good convergence rates have been achieved b u t the ultimate s p e e d i s n o t b e l i e v e d to have been reached. The generalized secant m i n i m i z a t i o n t e c h n i q u e has b e e n shown to be 2 to 4 times f a s t e r than Newton-Raphson when c m p a r c d on the b a s i s of function evaluations. A mod if i e d s e c a n t t e c h n i q u e is now b e i n g ~ p p l i e dto the two-point boundary value p r o b l e m a r i s i n g in t h e calculztion of op titnal t r a j e c t o r i e s . c. To fur=l-ler i n c r e a s e the s p e e d of the o p r i m a l t h s u s t coast-thrust program t h e completely g e n e r a l closed-form s o l u t i o n f o r t h e s t a t e vzriables and t h e Lagrange multipliers across a c o a s t arc have been a d d e d . �d. E f f o r t has been e x p e n d e d i n s t u d y i n g t h e approaches to rhe s o l u t i o n of the boundary val.ue problem which involves c o n v e r t i n g the boundary value p r o b l e m to a d i f f e r e n t l a 1 e q u a t i o n and i n t e g r a t i n g the d i f f e r e n t i a l e q u a t i o n to o b t a i n a solution. This approach s h o u l d a d d more speed and e f f i c i e n c y when more difficult problems with switching f u n c t i o n s are attempted. VIL. DYNAMICS AND ETIGHT M E C W T I C S DIVISION A. Multi-Projects - Dynamics and Control A e r o e l a s t i c Load Growth: This s t u d y i s b e i n g made to determine t h e o r i g i n of rhe unexplained external body moments observed during the Saturn 1 Elock 11 f l i g h t s . These e x t e r n a l moments which arc necessary to mainrain the r e c o r d e d f 1 i g h t c o n d i t i o n s are s ignif i c a n t l y Large ( 1 0 0 , 0 0 0 to 700,000 N-MI and have provoked much speculation as to t h e i r cause. A s t a t i c a e r o e l a s t i c load growrh a n a l y s i s o f rhe S a t u r n I Block II vehicles has tentatively shown tmnat t h e aeroelasric e q u i l i b r i u m l o a d i n g induces a n aerodynamic moment which has not p r e v i o u s l y been i n c l u d e d in f l i g h t mechanics. Comparisons between t h e observed £1i g h t test unexplained moment and t h i s a e r o e l a s t i c moment i n d i c a t e good agreem e n t in magnitude a n d d i r e c t i o n for a l l f l i g h r s in both p i t c h a n d yaw. These f i n d t n g s , a l o n g w i t h a method for i n c l u d i n g aeroelastic l a a d growth in the p r e s e n t six-degrees -of -freedom trajectory simulation programs ( w i t h minor r e v i s i o n s ,are b e i n g documented in a technical r e p o r r to be completed soon. (DD) > B. Saturn V I. M i s s ion P r o f i l e S-IVB L u n a r Impact S t u d y : At the reqaest of NASA H e a d q u a r t e r s , a s t u d y is in p r o g r e s s to evaluate t h e probability of S-ITJB 1u n a r impact for t h e l u n a r m i s s ion. The two primary ob sect ives of the s t u d y a r e to determine rhe maneuvers r e q u i r e d t o assure no l u n a r i m p a c t a n d t o determine t h e f e a s i b i l i t y of performing a maneuver to cause l u n a r i m p a c t w i t h i n a c e r t a i n area on the moon. This s t u d y s h o u l d be complete by A p r i l 15. ( ~ ~ . 1 / 3 o e i n g ) - a. Guidance Backup for T r a n s l u n a r I n j e c t i o n Several documents have been r e c e i v e d from Bellcomm a n d MSC which d e s c r i b e the NIT c r a s s - p r o d ~ c t s t e e r i n g e q u a r i o n and the Lambert solution to the conic time c o n s t r a i n t problem. The separate �p o r t i o n s have b e e n v e r i f i e d , b u t an o v e r a l l c l o s e d l o o p evaluation of the guidancz backup system has n o t y e t been made. A performance and a c c u r a c y s t u d y of the backup g u i d a n c e system will b e made i n the f u t u r e from the s t a n d p o i n t t h a t t h i s is a backup system t o be u s e d in an emergency only. (DG) b. Launch Vehicle Lunar Targeting Using a p a t c h conic program developed f o r MSC by TRW, a year's l u n a r t a r g e t i n g is being s t u d i e d . The s t u d y is b e i n g made t o d e t e r m i n e the e f f e c t on the hypersurface across a year's launch opportunities. (DAM/Boeing) 3. Dynamics arid C o n t r o l a. Dynamic T e s t R e s u l t s The c o r r e l a t i o n of dynamic t e s t r e s u l t s with theor e t i c a l p r e d i c t i o n s showed a large l o c a l effect on the r a t e gyro package which was mounted on the cold p l a t e . The evaluation of these data has l e d to an u p d a t i n g of the d e s i g n data f o r f u t u r e S a t u r n V vehicles A m o r e d e f i n i t i v e s t r u c t u r a l damping v a l u e can be p r e d i c t e d , as well as the l o c a l influences on the r a t e g y r o package. The r e s u l t s a £ t h e data evaluation of Ll~edyrxamlc t e s t t l l ~ d L t s impact: on d e s i g n data are b e i n g p u b l i s h e d in R-AERO-DD-21-67. @DS) b. 503 Res i d u a l P r o p e l l a n t s S e v e r a l s t u d i e s have been made for the translunar E l i g h r S-IVB p o r t i o n . The f a c t that L O X v e n k a n d n o t a l i g n e d through the v e h i c l e center of g r a v i t y r e s u l t s in Large slosh waves t l m t r e q u i r e e x c e s s i v e t i m e f o r damping. The solution to t h i s problem is a nonp r o p u l s i v e LOX vent and a p r o p u l s ive LH, vent. The propulsive LHvent is required to k e e p the l i q u i d s e t t l e d a n d ta maintain c o n t r o l . (DDD) c. S a t u r n V L i f t - O f f ?lotion A d d i t i o n a l l i f t - o f f motion d a t a have been generated f o r 5 n c l u s i o n w i t h t h a t previously documented i n s u p p o r t of t h e swing These data are published in Memo R-AERO-DCC- 1 67, arm redes ign F e b r u a r y 8 , 1967 and Fn Memo R-AERO-DCC-~-L~. (DC) . - �4. P r o j e c t I n f o r m a t i o n Applicable to Many Vehicles a. S a t u r n V Current Performance V e h i c l e c u r r e n t performance, which was updated ir F e b r u a r y and March, was r e l e a s e d in confidential memorandum R-AERODAP-15-67 d a t e d March 1 6 , 1967. During February, t h e AS-501 and 502 v e h i c l e s were r e i n s t a t e d into the c u r r e n t performance. Payload f o r AS-503 i n c r e a s e d over January by 613 pounds. Vehicles AS-504, 505, and 5 0 6 e s t i m a t e d payload c a p a b i l i t y was 518, 5 4 9 , a n d 1308 pounds, r e s p e c t i v e l y , above the p r o j e c t e d payload. This was due p r i m a r i l y to new d r a g data f o r AS-503 and s u b s e q u e n t v e h i c l e s . For vehicles AS-501 and 5 0 2 , there was no change from February to March. Payload increased f o r A S - 5 0 3 over February by 24 pounds. Payload decreased from February to March f o r v e h i c l e s AS-504, 505, and 5 0 6 and were 135, 143, and 1 2 3 6 pounds, r e s p e c t i v e l y , above the p r o j e c t e d payload. The payload change was d u e to weight changes. The performance was based on 1 9 6 7 February and Narch c u r r e n t w e i g h t s and was transmitted to I n d u s t r i a l Operations. (~~PIBoeing) b. A t t i t u d e Timelines for Vehicles 5 0 1 through 504 SSR-108, " S a t u r n V Parking O r b i t and P o s t I n j e c t i o n A t t i t u d e Time L i n e s , " was released 2-9-67. The report p r o v i d e s a summary of c o a s t flight v e h i c l e a t t i t u d e requirements and a t t i t u d e angles which s a t i s f y t h e r e q u i r m e n t s . The report covers Sat-urn V vehicles SA-501 t h r o u g h SA-504 b u t is n o t up to date. ( ~ A P / ~ o e i n g ) 5. Project I n f o r m a t i o n Applicable to I n d i v i d u a l Vehicles a. SSR-126 AS-503 Excess Propellant Elimination Methods Evaluation The amount of excess propellant left in the S-IVB at This amount of propellant c o n s t i t u t e s a c o n t r o l problem if it cannot: be s e a t e d d u r i n g docking. Twelve methods injection i s 7 8 , 6 0 0 pounds. oF reducing the excess S-IVB p r o p e l l a n t to t h e i n v e s t i g a t e d , two of which are considered more others: ( I ) early S-I1 engine: cutoff and (2) propellant through the 5-2 engine during c o a s t b. d e s i r e d amount were feasible than the e x p u l s i o n of excess flight. (DAP/Boeing) AS-504 Reference Trajectory Documentation Development of the SA-504 reference trajectory is cont i n u i n g on s c h e d u l e . A 1 1 out-of - o r b i t targeting i s o l a t i o n s and t r a j e c t o r i e s t h r o u g h o r b i t a r e complete; f i f t y percent of the o u t - o f - o r b i t t r a j e c t o r i e s a n d twenry-five percent: of t h e space t r a j e c t o r i e s have been v e r i f i e d . One book of the f i v e under development has been prepared. (DAPI ~ o i neg ) �I. P r o j e c t I n f o r m a t i o n Applicable t o Many Vehicles a. AAP C u r r e n t Performance Current performance d u r i n g February a n d March for U P - I , 2 , 3 , a n d 4 l a u n s l ~v e h i c l e s was d i s t r i b u t e d in memorandums R-AERO-DAP-9- 67 (February 1 6 , 1967) and R-AERO-DAP-14-67 @arch 1 4 , 1 9 6 7 ) . During F e b r u a r y , U P - I , 2 , 3 , and 4 p a y l o a d s increased 1987, 2 4 2 , 1981, a n d 9540 pounds, r e s p e c t i v e l y , over January. This was d u e ro w e i g h t , p r o p u l s i o n , e n g i n e m i x t u r e ratio s h i f t t i r r ~ e arid m i s s i o n altitude change. For >larch, t h e p a y l o a d s for U P - 1 , 2, and 4 decreased from February by 3 4 6 , 4 7 , and 9361 pounds, respectively. This was due to weight: a n d S-IVB mains t a g e o x i d i z e r change p l u s m i s s i o n a l t i t u d e change fuw AAP-4. U P - 3 showed an i n c r e a s e in payioad from February of 45 pounds d u e primarily to weight d e c r e a s e . The c u r r e n t performance w a s transmitted t o I n d u s t r i a l Opera t i o n s . (DAP/Chrys Per) 2, Project I n f o m tion A p p l icab Le to Znd i v i d u a l Vehicles AS-2071 208 Preliminary A b o r t and Alternate Miss ion SLudies AS-207 / 208 p r e l i m i n a r y a b o r t and alternate m i s s i o n s t u d i e s (TN-AP-66-132, and TN-AP-66-133) have been r e c e i v e d E r m C h r y s l e r . (DAPJ C h r y s l e r ) 1. Project A b l e This s t l ~ d yhas been t e r m i n a t e d . A f i r a l r e p o r t on the conclus i o n s and r e c m e n d a t i o n s d e a l ing w i t h f 1 i g h t mechanics has been d i s t r i b u t e d as memorandum R-AERO-DM-5-67. (DAO) a. M P - 1 and SAAP-2 P r e l i m i n a r y Reference T r a j e c t o r y A l l analyses have bccn c o m p l e t e d f o r t h e U P - 1 l a u n c h v e l i i c l e p r e L i m i n a r y r e f e r e n c e t r a j e c t o r y (TN-AP-67-18A) and was submitred to MSFC on March 24, 1967. A r e p o r t (TN-AP-67-148) documenting the l a u n c h vehicle p r e l i m i n a r y r e f e r e n c c t r a j e c t o r y f o r the U P - 2 m i s s i o n is b e i n g reviewed p r e p a r a t o r y to t r a n s m i t t a l f o r r e p r o d u c t i o n . (DAP) �b. Mission Timeline T r a d e Study A s t u d y is i n progress t o e s t a b l i s h the t r a d e - o f f resulting f r o m t h r e e different crew duty cycles assumptions as they affect t h e arnounr. of experiment: time available on t h e 56-day A D 4 m i s s i o n . Three d i f f e r e n t scheduling philosophies w i l l be used to es tab1 i s h t h e b e s r way to combine the Am and biomedical experiments. (~AHJLockheed) 3. O r b i t a l Workshop a. AAP-1 O r b i t a l Workshop Pass i v a t i o n A preliminary inves t i g a r i o n to m i n i m i z e perturbations to i n i t i a l injection orbit due to passivating the S-IV3 workshop is n e a r i n g completion. The i n i t i a l o r b i t u n d e r study is 250 nautical m i l e s c i r c u l a r . R e s i d u a l s r e p r e s e n t i n g the + 3 0 , nominal, and - 3 values ~ are being s t u d i e d . Injection i n t o an e l l i p t i c a l o r b i t and circularizing at the proper a l t i t u d e by the passivation i m p u l s e is b e i n g investigated. This method y i e l d s the minimum perturbations from the t a r g e t o r b i t ; howe v e r , these p e r t u r b a t i o n s a r e acceptable. (DAP) b . Orb ital Workshop A t t i t u d e S t u d i e s A r i g i d body a n a l y s i s of the a t t i t u d e h i s t o r y of t w o uncontrolled orbiting cluster configurations has been documented in memo R-AERO-D-7-67. The s t u d i e s c o n s i d e r e d the c o n f i g u r a t i o n planned f a r the 23-day p r i m a r y m i s s i o n and the c o n f i g u r a t i o n af rhe 6-month orbital s t o r a g e p e r i o d . The r e s u l t s , which are very p r e l i m i n a r y , were based on f i r s t e s t i m a t e s of aerodynamics far the workshop. Various i n t t i a l values were assumed f o r the a t t i t u d e and angular rates of the configurations investigated. The r e s u l t s of these studies show t h a t the motion of rhe vehicle is s t r o n g l y dependent on the i n i t i a l c o n d i t i o n s , and even when t h e s e c o n d i t i o n s are known reasonably well a small amount of u n c e r t a i n t y in the angular rates is sufficient to change the vehicle motion c o n s i d e r a b l y . F r a a this prel-kminary a n a l y s i s , it was concluded that, unless the v e h i c l e is s t a b i l i z e d in a g r a v i t y g r a d i e n t condition by u s e of external c o n t r o l forces, the motion of the v e h i c l e is likely r o d e v e l o p a random tumblfng motion which w i l l continue far the d u r a t i o n of t h e f l i g h t . @C) �4. Cluster a. Mission Profile (1) P r e l irninary Miss i o n Prof iEe Documentation A report (TN-A?-67-173) d o c u m e n t k g the p r e l i m i n a r y f l i g h t p r o f i l e s for U P - 1 , 2, 3 , and & l a u n c h vehicles was received by WSFC February 17, 1 9 4 7 . (DAP/ChrysPer) (2) UP-3/AAP-4 Mission P r o f i l e s Baseline m i s s t o n profiles f o r UP-3/AAF-4 have been p r e p a r e d u s i n g the co-orbital rendezvous scheme. Two c a s e s are under consideration: (a) separate rendezvous of t h e zM/Am and CSM with the works h o p and ( b ) rendezvous of a c o u p l e d LMIATM-CSM to workshop. These profiles were p r e s e n t e d at the A T 4 Q u a r t e r l y Review in early Farch. (DAO) (3) 1969 AAP M i s s i o n Praf iles Mission profiles have been m a d e a n d r e v i s e d w i t h l a t e s t l i f e t i m e data for missions AAP-5, 6 , 7, and 8. These p r o f i l e s assume the use of four 90-day CSM's to achieve a year in space by r e u s i n g t h e o r b i t a l workshop and ATM from the 1 9 6 8 c l u s t e r m i s s i o n . (DAD) (43 1969 AAP M i s s ion D e c i s i o n L o g i c Effort is being expended to produce a 1969 mission d e c i s i o n l o g i c nefmork. Work on t h i s task has progressed for one month. The b a s i c goal of the overall 1969 mission is t o k e e p men in space cant i n u o u s l y for one y e a r w i t h periodic replacement and exchange of crews. The S-TVB Orbital Workshop is to f u r n i s h a space scation environment for t h e crews who will perform various experiments. A preliminary version of the d e c i s i o n l o g i c f o r this complex m i s s i o n has b e e n completed and i s to b e p r e s e n t e d Lo the Mission P l a n n i n g Task Force at NASA H e a d q u a r t e r s , IJashington, in e a r l y A p r i l . This d i s p l a y has been k e p t as g e n e r a l zs p o s s i b l e w i t h o n l y a feu r e s t r i c t i n g ground r u l e s , such a s t h e p o s s i b l e a v a i l a b i l i r y of a n o t h e r O r b i t a l Workshop a n d ATM. In the present v e r s i o n , a nominal path i s d e t a i l e d w i t h the various b r o a d d e c i s i o n s ar-d a c t i o n s necessary to c a r r y o u t the planned m i s s ion. In a d d i t i o n , off-nominal d e c i s i o n and action routes are i n c l u d e d which p r o v i d e p o s s i b l e alternatives when there i s an off-nominal occurrence. In t h i s preliminary v e r s i o n , several paths are prematurely terminated because of Lack of manpower and time, and mare expansion is needed before completion. It i s f o r e s e e n :hat the f i n a l v e r s i o n of t h i s d e c i s i o n l o g i c w i l l c o n s i s t of a vast number of d e c i s i o n s and a c t i o n s resembling a PERT network. The use of such a n e t m r k when coupled w i t h a m i s s i o n success p r o b a b i l i t y a n a l y s i s can be developed i n t o a nominal and alternate mission design tool. Further �i* ~ C ~ L O U T C a P r~l a l y s i s psograa ( h z s d r . r z r ~ , s c L e d u l e , and iu; l y d e v e i o p e d s y s t e m c o u l d b e ~ s r r as l a SASA H e a d q u a r t e r s r u t u r c s p a c c program planning tool. (DAD) LTJII;,! L ~ J: rncjnkyl, ~ it l h ttic . Dynamics and C o n t r o l (11 Clus ter S tructural Dynamics Work is underway ac Lockheel. Huntsv$?te, u n d e r s u p p o r t contract to d e v e l o p computer programs f o r the s h o r t term d y n a m i c r e s p o n s e of p l a n n i n g o r b i t a l w o r ~ s h o p - c l u s t e r c o n f i g u r a t i o n s , A g e n e r a i m z ~ h c m a t i c a l model far calculating l i n e a r vibrarion charact e r i s t i c s a n d r e s p o n s e of the c l u s t e r s is b e i n g formulared. A p a r t i a l c h e c k o u t of t h e d i g i t a l program r.:as s u c c e s s f u l Ly p e r Eclrmed , Routines t;.hich g e n e r a t e s t i f r ' n e s s , damping, and mass c o e f f i c i e n t s a n d asszmble rhem into matrices f o r the overall s y s t e m were s u c c e s s f ~ l l yr u c , znd routines which c m p u t e n a t u r a l f r e q u e n c i e s a n d modes f o r t h e s y s t e m zre being debugged. (DDS/Lockheed) (2) Csmbincd hTorkshop/~i?!S ~a tionkecping Docurnenta L i o n of a p a r t k u l a r s o l u r i o n to the soft terher stationkeeping p r o b l e m -has b e e n d i s r r l b u t e d a s memorandum 3 - X R O - D A D - 2-67. In t h i s solution, an i m p u l s e is i m p a r t e d t h r o u g h t h e t e t h e r e v e r y 3 112 o r b i t s to compensate f a r the aerodynamic d r a g dcccleration. The d i f f e r e n t i a l e q u a t i o n s of motion f o r the W.I/ A D 1 were w r i t t e n in a c o o r d i n a t e s y s t e m fixed in the ~iroskshop. Assuming t h a t the d r a g d e c e l e r a t i o n is a c o n s t a n t , a closed form s o l u t i o n to t h e s e equations was found. Another p a r t i c u l a r s oLut i o n to t h e so?t t e t h e r p r o b l e m has b e e n found which does noE e x h i b i t t h e o s c l i l a t i o n s in t h e r a d i a L a n d t a n s e n t i a l d i r e c t i o n s found i n t h e p r e v i o u s s o l u t i o n . This w i l l g r e a t l y r e d u c t . t h e accuracy n e c e s s a r y f o Y the magnitude and t h i n g o f t h e p u l l s on the techcr. A l s o t h e magnitude o f t h e p u l l s was only v e r y ~ ~ ~ c a kdependent ly upon t h e d i f f e r e n c e in drag dzcelera~ions between ' L ~ F~.:orkshop and S l / I Z T X . On t h e s u b j e c t of t e t 5 e r r e t r i e v a l , t c t n t e r e s t i n g conccpt was found in the L i t z r a t u r e wherein a t h i r d m a s s i s e x t e n d e d o n a n o t h e r t e t h e r f r o m rhe body S e i n g r c c r i e v e d . The r a t e of recrfeval is c o n t r o l l e d in s u c h a manner t h a t most of t h e angular m o m e n t u m is p u n p e d i n t o the t h i r d mass rrhicll may b e d i s p e r s e d of a f t e r retrieval o f t h e GI, (DAO) �(3) Rigid Body Response of O r b i t i n g S p a c e c r a f t Thc b e h a v i o r of an ear t h - o r b i t i n g v e h i c l e when subjected ro an impul.sive farce such as encountered in docking maneuvers h a s been documented and d i s t r i b u t e d in Memo No. R-AERO-DCA-1-67. The o n l y restoring t o r q u e c o n s i d e r e d to act on the v e h i c l e was hat r e s u l t i a g from the gradient in the earth's gravitational field with altitude. The a n a l y s i s was r e s t r i c t e d t o m o t i o n i n the o r b i t p l a n e o n l y . Presented in the memo are the e q u a t i o n s t h a t d e s c r i b e t h e maximum value of impulsive t o r q u e t h a t the vehicle can s u s t a i n b e f o r e tumbling occurs. Numerical examples were p r r s e n t e d far t h e s p e c i a l case in which the vehicle has no i n i t i a l a n g u l a r v e l o c i t v . The i n e r t i a and mass parameters u s e d f o r the numerical examples are t y p i c a l f o r the S-IVB workshop c l u s tcr configuration. (DC) 5. Odyssey An estimate of the propellant and b u r n time r e r l u i r e d to t r a n s f c r t : ~ e p r o p o s e d O d y s s e y p a y l o ~ dpackage f r o m a 240 hl. c l r c u l a r ~ r b i tto a 160 Ian by 1750 h e l l i p s e u s i n g a c l u s t e r of 4 C - 1 e n g i n e s has b e e n dscumented (DAO) . E m General Methods - Dynamics and C o n t r o l Design C r i t e r i a for C o n t r o l of Space Vehicles: Two monographs w e r e received in f i n a l farm: (1) "Component Dynamics" by J . G. R o l l a n d Collette and (2) " A t t i t u d e C o n t r o l DurFng Launch" by A r t h u r L. G r e e n s i t e . In t h e f i r s t monograph t h e t h r e e b a s i c f u n c t i o n s to b e c o n s i d e r e d f o r the operation of a c o n t r o l s y s t e m a r e d i s c u s s e d : (1) s e n s i n g , ( 2 ) s i g n a l processing and ( 3 ) a c t u a r i o n . E q u a t i o n s are d e v e l o p e d f o r the motion of gyroscopes and accelerometers. T y p i c a l schematics and flow charts which a r c m a d e for the actuating elements are discussed in d e t a i l . The s e c a n d monograph discusses t h e usual s t a b i l i z a t i o n t e c h n i q u e s a s well a s the i n l l u e n c e o f v a r i o u s n o n l i n e a r i t i e s . A l l of the influencing f e a t u r e s (Elexibility,propel l a n t s l o s h i n g , e t c . ) a r e c o n s i d e r e d in the t r e a t m e n t of the p r o b l e m . The a i m , as with a n y a n a l y s i s , i s to formulate t h e s i m p l e s t m o d e l that w i l l a c c o u n t for a i l significant phenomena. Two o t h e r monographs were r e c e i v e d : " ~ t t i t u d e C o n t r o l in S p a c c f ' and "Adaptive Control These have been reviewed. (DCAIOA) ." �I FLIGHT TEST A X A T 2 S T S D I V I S I O N A. Special Projects Office A p r e s e n t a t i o n on the s t a t u s of p l a n n i n g and p r e p a r a t i o n f a r S a t u r n V f l i g h t t e s : e v a l u a t i o n was g i v e n by Mr. L i n J b e r g to the Saturn V Program O f f i c e on F e b r u a r y 14, 1967. The m a s t s i g n i f i c a n t problem d i s c u s s e d was the i m p a c t on f l i g h t evaluation of nearly s i m u l taneous S a t u r n IB and S a t u r n V l a u n c h e s , a n d acce?tance tes t i n p . T h i s i m p a c t is not$ b e i n g investigated by the FEWG and will again be p r e s e n t e d to t h e p r o g r a m o f f i c e during A p r i l . It now appears t'nat the i m p a c t en computer c a p a b i l i t y at MSFC, S l i d e l l , DAC, and SLID w o u l d not b e s c r i o u s , b u t the i m p a c t : on manpower f o r analyses at: DAC, ~ ~ C / M i c h o u dand , IBM may be a signiiicant problem. The S a t u r n V F l i g h t T e s t Evaluation i s a b o u t 90 p e r c e n t cornpletc a n d s h o u l d be p u b l i s h e d by A p r i l 10, 1967. FEVG-Payf oad organizatiirna 1 e f f o r t s h a v e continued d u r i n g t h i s p e r i o d . The second g e n e r a l meeting Ims b2en h e l d , a n d t h e second d r a f E af t h e PEWG-Payload P l a n h a s b e e n completed. This document contains the ovcrall scopc and f u n c t i o n for the g r o u p applicable to all payloads. The f i r s t d r a f t of the Eirst m i s s t o n p l a n document, A A P - ~ I A A P - payload ~ evaluation plan, i s nearing completion. Otherwise, the development of t h i s working g r o u p is proceeding along the same l i n e s as for the S a t u r n IB and S a t u r n V Launch v e h i c l e s . 3. Seminar Plans for a seminar on "~nvironment-Induced O r b i t a l Dynamics" s p o n s o r e d by Aero-As trodynamfcs L a b o r a t o r y t o b e h e l d at XSFC on June 6 and 7 , a r e e s s e n t i a l l y c o m p l e t e . The four technical s e s s i o n s are: a. Mechanics of O r b i t a l Decay b. Aerodynamic C o e f f i c i e n t P r e d i c t i o n Methods c. Amospheric Models �The p l a n s are to l i m i t the group to 7 0 to 80 i n v i t e d p a r t i c i p a n t s s o that a seminar atmosphere may be o b t a i n e d . The purposes for t h e seminar a r e to ( a ) h i g h l i g h t the degree of s o p h i s t i c a t i o n of the t e c h n o l o g y , (b) improve the i n t e r f a c e s between the d i s c i p l ines i n v o l v e d , (c) p o i n t the d i r e c t i o n f o r advancing the technology, and (d) develop i n t e r e s t and s u p p o r t for i n d i c a t e d programs. B. Tracking and O r b i t a l A n a l y s i s Branch 1. Saturn V/Voyager A memorandum (R-AERO-FT-4-67] on the S a t u r n V/Vayager t r a c k i n g and communications coverage for the launch phase and the earth-pasking o r b i t s f o r various i n c l i n a t i o n s was d i s t r i b u t e d . The coverage of the t r a n s f e r trajectory and Mars o r b i t w i l l be analyzed at some l a t e r time when trajecrory p r o f i l e s are available. Parametrkc o r b i t a l L i f e t i m e studies b e i n g c o n d u c t e d for a Mars o r b i t i n g s a t e l l i t e w i l l be expanded to include the Voyager s p a c e c r a f t i n v a r i o u s Mars o r b i t s , 2. Saturn V L e t t e r s have been t r a n s m i t t e d to t h e Boeing Company Listi n g the various s i t e s a n d i n s t r u m e n t a t i o n to b e used i n the AS-501, AS-502, and AS-504 t r a c k i n g and telemetry a n a l y s Fs d o c u m e n t s , The AS-501 t r a c k i n g a n d telemetry a n a l y s i s document on the operational Era j e c t o r y lzas been received f r m TBC and is b e i n g prepared for dis tribution. The Boeing Company w a s requested t o a p p r o x i m a t e t h e A S - 5 0 1 S I C t r a j e c t o r y a n d determine the s e p a r a t i o n angle and d i s Lance from t h e t i m e of S-IVB/SC separation t o 5 hours flight t i m e (near apogee) u s i n g the Ascension I s l a n d s t a t i o n c o o r d i n a t e s . This s e p a r a t i o n information was r e q u e s t e d by I-YO-R to help d e t e r m i n e beacon requirements acd assignments f o r the Ascension I s l a n d s t a t i o n . received from TBC and t r a n s m i t t e d LO I-MO-R. 3. The i n f o r m a t i o n 'has been Saturn 13 Letters have been t r a n s m i t t e d to CCSD 1is t i n g the v a r i o u s s i t e s and i n s trumentation to be u s e d in the AS-204 (LM m i s s i o n ) , AS-205, AS- 206, AS-208, and S M - 1 tracking and telemetry analys is documents. The p r e d i c t e d o r b i t a l lifetime f o r the S - I ~ J B / X s t a g e s on the d u a l AS- 2 0 5 / ~ S -208 m i s s i o n was d i s tr Fbu t e d in memorandum R-AERO- FT13-67. �A request: was made to MSC through M r . Crernin, Go-Chairman, G&P Subpanel for the A S - 2 0 6 o p e r a t i o n a l s p a c e c r a f t t r a j e c t o r y to b e sent to R-AERO-FT as soon as p o s s i b l e . I-MO has stressed t h e f a c t t h a t t h e s e p a r a t i o n angle and d i s t a n c c information would be e s p e c i a l l y h e l p f u l in t h e AS-206 m i s s i o n s u p p o r t planning. Tracking and telemetry i n f o r m a t i o n o n the AS-206 "specialt' o r b i t a l trajectory has been transmitted to Mr. Sims, R-AERO-P, in memorandum R-AERO-FT-21-67. This t r a j e c t o r y , which w a s done by CCSD under direction of J. C r a f t s , R-AERO-lW, i n c l u d e s passivation impulse. Tracking end telemetry information on t h i s trajectory was a l s o done by CCSD. P r c l irninary tracking and communieatiana s c q u i s -ition a n d l o s s times based on the AS-205 operational trajectory were recelved from CCSD on Marc11 14, 1967. These data have been s u p p l i e d to ASTR Lab and F&VE Lab to meet t h e i r contractual deadlines. This information is necessary to complete the AS-205 F l i g h t Program p r e p a r e d by IBN f o r d e l i v e r y to KSC. Studies are p r e s e n t l y underway to establish the l i f e t i m e of t h e S-IVB on the new AS-204 mission assuming char p a s s i v a ~ i c r nis performed. A l i f e t h e of at l e a s t one o r b i t is required a f t e r the passivation. Studies to identify the attitude of rhe S-IVB during passivation to guarantee rhis lifetime are b e i n g carried on. I n a d d i tion, the separation d i s t a n c e between the LM and the S-IV13 on the new AS-204 m i s s i o n will be e s t a b l i s h e d . This s t u d y will be performed from S-IVBJLY separation to at l e a s t one o r b i t a£ ter the S-TVB passivation, A magnetic tape of t h e LM trajectory a£t e r s e p a r a t i o n from t h e S-IVB i s being f o r ~ m r d e dby MSC f o r u s e i n t h i s srudy. P r e l i m i n a r y tracking and communications a c q u i e ition and l o s s times b a s e d on the AS-208 Preliminary Operational Trajectory were r e c e i v e d from CCSD on Yarch 2 1 , 1967. . AAP A n o f f i c e m m n o r a n d u m , R-AERO-FT-11-67, entitled "Power FL i g h t a n d Orbital Tracking and Communications Coverage for l i p r a t c d S a t u r n I Nominal Trajectories in ar, 80 x 200 N.M. Elliptical and a 200 N.M. Circular Polar O r b i t , " has been d i s t r i b u t e d . S t u d i e s have been perfarmed to determine the o r b i t a l decay and l i f e t i m e of SIA panels releasec from 'chc 5-IVB. The panels were assumed t o b e released from the S-IVB with no energy impaxted to then. They would then d r i f t away f r o m the S-IV13 p r i m a r i l y d u e to atmospheric drag f o r c e s . These d a t a were analyzed for the workshop mission with t h e S-IT9 in a 480 krn circular orbit. A d d i r i o n a l information used in t h e a n a l y s i s is a s fallows: �(a) Mass of the f o u r p a n e l s ranged from 252.20 kg to 294,83 kg. (b) Aerodynamic parameters for various o r b i t a l o r i e n t a t ion: nose-on AC,, = 3.68 m2; b r o a d s i d e , C$i. = 4 8 . 3 3 m2; tumbling, C+ = 30.79 m2, (R-AERO-A d a t a ) . A r e p e a t presentation on the s u n i n t e r f e r e n c e problem of the S y s t e m was given to A s t r i o n t c s personnel on F e b r u a r y 10, 1 9 6 7 . LM Relay C m u n i c a t i o n s P r e s e n t MSFC e f f o r t s on the CM r e l a y experiment have b e e n completed a n d r e s u l t s g i v e n to NASA Headquarters OTDn. personnel. - . P r e l h i n a r y STADAN tracking t i m e l i n e s were given to Plr L l v , R-ASTR-IR, on the AlIM m i s s i o n . As t r i o n i c s Lab is invcs t i g a t i n g the use of t h e STADAN network to return t h e large amounts of experimental d a t a that: will b e c o l l e c t e d on the Am m i s s i o n , A memorandum documenting t h e s e t h.e 1i n e s is b e l n g prepared. The o r b i t a l analysis r e l a t e d to the Odyssey 1 experiment w a s presented to Aero-Astrodynamics L a b o r a t o r y p e r s o n n e l on March 8 , 1967. This p r e s e n t a t c o n i n c l u d e d a d i s c u s s ion o n the Baker-Kunn camera s y s t e m , O r b i t Determinatian u s i n g Saker-Nunn camera data, and an e r r o r a n a l y s i s on t h e proposed Odyssey I experiment. 5. L i f e t i m e and O r b i t a l Analysis Mr. Bensan made a presentation on the E a r t h O r b i t a l L i f e time Program to a p p r o x i m a t e l y 25 MSC personnel on F e b r u a r y 1 7 , 1967. M S C personnel were very e n t h v s i a s t i c a b o u t r e c e i v i n g and u s i n g t h i s program. P l a n s have been made for the use ef t h e Lifetime program in conjunction w i t h r e a l time m i s s i o n o p e r a r i o n s . MSC a l s o expressed t h e i r d e s i r e s to i n c o r p o r a t e t h e atmospheric model (1962 U. S . S t a n d a r d s h i f t c d f o r s o l a r h e a t i n g effects) into all r e a l time computer programs. I; F7aS p o i n t e d o u t that the model has been v e r i f i e d u s i n g aerodynamic parame t e r s r e c e i v e d from R-AERQ-A. It was M S C f s i n t e n t i o n to r e q u e s t R-AERO-A to s u p p l y them w i t h s imilar a e r o d y n a m i c data on a l l m i s s i o n c o n f i g u r a t i o n s . Mr. Fleischman r e t u r n e d to WSC on F e b r u a r y 23 and 24 with CSC programer r e s p o n s i b l e f o r t h e lifetime program, to d e l i v e r the l i f e t i m e program, to make s u r e it was operable o n NSC corn- Mr. Boykin, p u t e r f a c i l i t i e s , a n d to i n s t r u c t XSC personnel a b o u t i t s use a n d f lexibilities . �A memorandum lms been prcpared to Mr. Yarbrough, R-COMP-RDS, to authorize transmirtal of t h e Lifetime Program to E e l Lcomm af W a s h i n g t o n , D. C., who had r e q u e s t ~ da copy of t h i s pragram. A confract w i t h Honeywell o f M i n n e a p o l i s ta inves tigate t h e feas i b $1ity of us i n g linear p r o g r a m i n g in s ched ul i n g exper iments for t h e APlP m i s s i o n has been s i g n e d . The c o n t r a c t w i l l d e r e r m i n e if 1inear psog r a m i n g can b e incorporated in the sequencing O p t i m i z a t i o n A u t o m a t i c Program (SOAP) as a second s c h e d u l i n g methad. S t u d i e s are being made to e s t a b l i s h e l l i p t i c o r b i t s which will p r o v i d e i n c r e a s e d l i f e t i m e f o r the proposed SAh-1 through S k i - 4 m i s s i o n s . These s t u d i e s are being performed over various i n c l i n a t i o n s a n d w l l l r e f l e c t performance capabiliries s u p p l i e d by K-MKO-HA. C. F l i g h t E v a l u a t i o n Branch 1. Saturn I 3 a. General A meeting was a t t e n d e d to d f s c u s s s l e d t e s t s of the trap-down) g u i l a n c e s y s tern. A t t e n d i n g were represents tives from Holloman A D , ASTR, COMP-RRM, and AERO-FF. Holloman personnel were concerned with what t e s t dara t h e y were expected to f u r n i s h MSFC and i f any analysis of rhe guidance system was expected. It was d e c i d e d thar Bolloman would f u r n i s h MSFC with the r a w telemetry tape of the g u i d a n c e measurements v e r s u s time a n d processed space-time d a t a of the track system. R-ASTR and AEBO-FFR w i L l perform the system analyses. C W - R will r e d u c e the telemetry. SD-53 (s A package of data showing angular acceleration data seen by t h e S-LB c o n t r o l s y s t e m has been p r e p a r e d for A s t r i o n i c s Lab. I n s t r u m e n t s analyzed were the p i t c h , yaw and r o l l rate gyros f o r A S - 2 0 1 . Data were o b t a i n e d by passing the measured a n g u l a r v e l o c i t y data t h r o u g h a d i g i t a l derivative f i l t e r . The roll rate gyro i n d i c a t e d the l a r g e s t accelerarions reaching 1200 d e g / s e c 2 peak-to-peak at: 63 seconds Range Time. Maximum a c c e l e r a t i o n s m e a s u r e d near body bend Tng f r e q u e n c i e s were 13'/sec2 peak-to-peak at 4 H e r t z . A power s p e c t r a l d e n s i t y a n a l y s i s of the data i n d i c a t e d t h a t most o f the c o n t r r i b u t i o n s to t h e h i g h total r a t e were d u e to i n d i v i d u a l frequency components c e n t e r e d between 10 and 25 Hertz. 2. Saturn V a. Lift-off C o n t r o l A s i m p l i f i e d stabFLity a n a l y s i s of the AS-501 c o n t r o l s y s tern was performed t e e v a l u a t e the u s e of i , and 9,; g u i d a n c e g a i n s �to a l l e v i a t e the LUT clearance problem. With t h e p r e s e n t A, and A l c o n t r o l gains and c o n t r o l filters, the s t a b i l i t y m a r g i n with :,L and d l i n c l u d e d i n the s y s t e m was r a t h e r r e s tsicted. The range on the g a i n s was d e t e r m i n e d to be approximately the f o l l o w i n g : Sample runs w i t h a .34-degree thrust m i s a l i g n m e n t i n d i c a t c d that a 2.5 2.7 meter r e l i e f in d r i f t can b e o b t a i n e d w i t h t h e p r e s e n t l y dcf i n e d control s y s tern. - b. L i f t - o f f Motion An a i r scaop t a r g e t camera has been r e q u e s t e d f o r 504 to observe a i r scoop motion r e l a t i v e to the s o f t r e l e a s e mechanism. An a d d i t i o n a l t a r g e t camera has been requested for AS-5025 0 4 . These a d d i t i o n a l cameras w i l l r e s u l t in a b e t t e r definition of v e h i c l e motion d u r i n g the i n i t i a l phase of f l i g h t (2 s e c ) . T h i s r e q u e s t is contained in Memo No. R-AERO-FF-15-67, " L i f t o f f T a r g e r Camera S u p p o r t R e q u i r e d for S a t u r n V" dated F e b r u a r y 24, 1 9 6 7 . AS-501 - c. E f f e c t s of S-IVB I g n i t i o n Weight Error There appeared t o be a problem e x i s t i n g for the f l i g h t s i m u l a t i o n s e c t i o n s in determining the propulsion s y s t e m performances f o r S - I C and S-IT s t a g e s 0 5 the S a t u r n V f l i g h t vehicles. The S - I C and 5-11 s t a g e c o n t r a c t o r s asked if t h e r e was a way in w h i c h they c o u l d p r o c e e d with p o s t f 1i g l ~ t . a n a l y s i s o f p r o p u l s ion sys tems p e r f onnance w i t h o u t waiting f o r the f i n a l vehicle i n i t T a l mass, The f i n a l mass will not be d e t e r m i n e d u n t i l a l l of the S-IVB 2nd b u r n and v e n t i n g data have b e e n reviewed. n i s may require most of the time allowed the f l i g h t simulation sections f o r t h e i r a n a l y s i s . A f t e r s t u d y i n g the e f f e c t s of a mass error on an u p p e r s t a g e to the s tage b e i n g evaluated , it becomes apparent t h a t a mass error of t h i s nature would be i d e n t i c a l in e f f e c t to a d r y weight error on the s t a ~ eb e i n g evaluated. Many s t u d i e s have been m a d e of t h e e f f e c t s of a d r y weight error on p r o p u l s i o n system p e r f onnance o b t a i n e d b y E l i g h r simulation rechniques These s t u d i e s showed that: the p r o p u l s i a n sys tern performance would have the correcl: r a t i o of thrust-ro-mass flow r a t e b u t the levels of magnitudes of thrust a n d propellant flow rates would be in error b y zhe same percentage as t h e e r r o r in initial mass of the v e h f c l e being evaluated. It was t h e r e f o r e concluded that flight s i m u l a t i o n sections of T B C a n d TJM could p r o c e e d with p o s t f l i g h t evaluations w i t h an assumed i n i t i a l mass as soon a s they receive the recons e r u c t e d p r o p u l s Lon performance and the observed mass p o i n t trajectory. Once the final mass is o b t a i n e d , rhe f l i g h t s i m u l a t e d t h r u s t and propellant f l o w r a t e averages can be s h i f r e d b y . �the same percentage as t h e change i n i n i t i a l mass, Ir was a l s o s u g g e s t ~ d t h a t a s u b - g r o u p to t h e F l i g h t : Evaluation Working Group (FEWG) b e forrntcr of the c o n t r a c t o r a n d Marshall p r o p u l s i ~ nand weights group representatives. T h i s s u b - g r o u p would meet as r e q u i r e d to work out i n c o n s i s t e n c i e s in mass h i s t o r y of the e n t i r e v e h i c l e . d . Powered F l i g h t PQS t f light Trajectory Techniques The MARLOCK program, which is one a £ t h e maFn t o o l s in postflight E r a j e c t o r y cons t r u c t i o n , has been e x t e n s iveLy mod if i e d . To a v o i d c o n f u s i o n , t h i s u p d a bed program has been renamed Guidance and T r a c k e r Evalua~ion (GATE). The r e s u l t s of Con t r a c t Bo. NAS8-20249 with G c r r c r a l Dynamics a1ong r,rith the T r a c k e r E r r o r Model S t u d y b e i n g perfom,;-d at Y S Y C p r o v i d c d the following i n f u r m a t i o n t h a t was essentiaL b e t o r e t h e s c n o d if i c a c ions could be i n i t i a t e d : (I) The guidance error model c o e f f i c i e n t s and ;he t r a c k e r error model coef f i c l e n t s are r e l a K i v e l y u n c o r r e l a t e d (correlation c o e f f i c i e n t s of . 2 1 a r less). (2) The s y s t e m a t i c e r r o r s in a c t u a l radar d a t a can be r e p r e s e n t e d b y a n error m o d e l which has b e e n t r u n c a t e d down to LO terms. $3) A rruncated t r a c k e r error m o d e l can r e p r e s e n t t h e systematic e r r o r regardless of the r e l a t i o n s h i p between the flight path of the vehicle and the l o c a t i o n of t h e t r a c k e r s i t e . This program uses t h e Kalman f i l ~ e tro d e t e r m i n e a "bes t - e s timate" f i t of the teleme t e r e d guidance v e l o c i t y d a t a to he t r a c k i n g data b y s o l v i n g f o r up to 18 guidance e r r o r model c o e f f i c i e n t s a n d up to 10 C-Band r a d a r e r r o r model c o e f f i c i e n t s f o r e a c h radar sit€-. By a p p l y i n g t h e guidance error model c o e f f i c i e n t s b a c k to t h e celenetered guidance d a t a , smooth continuous t r a jeceory rcsul cs . T h i s has b e e n successfully rricd on SX-203 dara. Although t h e mdthod c o n L i n ~ e sto b e s o r u t r w l l a t s ~ r i ist i v e tu the clloict: oL L i l e trLror c u c - E f i c i e n t s CQ b e s o l v e d for, the v z r i a n c e s p l a c e d o n the coefficients, a n d the w c i g h f s p l a c e d on t h e t r a c k i n g d s t a , i L still produces ex cell en^ r e s u l t s . Extensive inves Kiga t i o n a n d analysis are b e i n g perforned a; o r d e r t 3 a c t i r ~it11 1 capabilities a f t h i s program can be accurately u t i l i z e d on AS-501. A p a p e r un t h i s s u b j c c t e n t i t l e d "Towered r i i g h r T r a j e c t o r y D e t e r m i n a t F o n Techniques as Applied t o S a t u r n V vehiclts" IIZS b e e n a c c e p t e d f o r p r e s e n t a t i o n a t the A m G u i d a n c e , C o n t r a L and F i i g h t Dynamics Conf e r e n c c in Huntsville in Augus t. A r ~ u g hd r a f t of t h i s paper w i l l be completed in t h e very near f u t u r e . �e. Orbir Detcrmina t i o n w i t h V c n ~ i n g h p r o c e d u r e has been i m p l e m e n t ~ d to p c r f o r n a n c detelrmination of thc p a r k i n g orbit on S a t u r 2 17 v e h i c l e u s i n g p o l ) nomials o b t a i n e d from t h e tulemetered g u i d a n c c d a t a which w i l l in all n o n - g r a v i t y forces f e l t by t h e v e h i c l e . These d a t a w i l l be 0 rect e s c c p t for acce~crometcrbias in each componcnt. I n t h e p r o r implemented, considerable e f f o r t is s p e n r processing t h c g u i d a n c e and p r e p a r i n g accel e r a t i o n polynomials f o r ezch componcnt of t h e g u i d a n c e coot-dFnatc system. The O r b i t Carrcction Program (OCP) rri transform t h e s e accelerations t o t h e g e o c e n t r i c i n c ~ s r i a ! coordinat6 s y s tern (Apollo S t a n d a r d C o o r d i n a t e S y s tern No. L.) a n d a d d rhem c!irec t o the Cetirel L equa Lions of notion. The c a p a b i l i t y to s o l v e for the b i a s e s in t h e g u i d a n c e accelerations has a l s o b e ~ nfrnplenented. Th p r o c e d u r e h a s bccn successfully c h c c k ~ d o u t on t h c S A - 2 0 3 d a t a . Tht acceleration b i a s e s o b t a i n e d f r m t h i s progrzm si~ouiclb e h e l p f u L iil t h e g u i d a n c e error a n a l y s i s . MSC will implement a s i m i l a r procedure f o r t h e i r p o s t f l i g h t o r b i t cletermination. YSC, who will u s e the guidance acceleration polynomials o b t a i n e r l by MS'FC, are a l s o consid?: i n g s o l v i n g Eor the b i a s e s i n a similar f a s h i o n . If t h i s is done, i t should help c o n s i d e r a b l y in the trajectory c o o r d i n a t i o n between MS?C a n d MSC. 3. Contracts a. - Boeing Company Contract NAS8-5608, Schedule i Emergency Detection S y s t e m T h e r e s u l t s of a s p e c i a l s ~ u d yr c q u e s t (SSR-117 a s s i g n e d undcr C o n t r a c t KAS8-5608, Schedule 1 1 , P a r t V , E x h i b i t LAUZ, Task 1 . 0 . ) were r e c e i v e d from TBC. The p u r p o s e of this s t u d y was t o determine t h e i m p a c t of rcmoving t h e fins from the S a t u r n V Paunch v e l l i c l c f r o m s t a b i l i t y , E l i g h t dynamics, a n d crnergcncy ~ l c t e c r i o n sys tcm viewpoints The c o n c l u s i o n reachecl i s t h a t Sins a r e r e 1 u i r i l 3 . ! i i E l > f i n s rrrnovrrt, n e i t j ~ e rc o n t r o l g a i n a c l j c l s h e n t nor t!lr u ? e of c o n t r o l accelcromcter can p r o v i d e s u f f i c i e n t s t a b i l i t y m r y i n s :or a ma1 f u n -t i a n v e h i c l e ; and i n g e n e r a l , f o r malfunction f l i g i ~ : , ; L J d < t l 1 3 c a l vehicle loss cs waulcl occur w i t h o u t impravcmcna: is: ~ . ~ ~ cin2 ' - r n time . . h. C l u s t e r e d E n g i n e Performance TEC has i n i t i a t e d four d i f f e r s n t : proqrams whLi.3 will b e u s e d by t h e i r f l i g h t s i m u l a t i o n s e c t i o n t o deternixe t h e cltls t e r c d engines analysis f o r the S - I C s t a g c of thc S a t u r c 1' vehicles. The f i r s t progran is v e r y simple and c a l c u l a t e s o n l y t h e t o r a l e f ? c c t i v ~ f o r c e a c t i n g on t h c v e h i c l e and t h s t o % l vehicie r a s s v c r s u s r i m e . Thc second and third programs are t h e PISFC Tra j ~ c c o r yX p n i i c a ~ i o n Me thod (TAM) a n d s i x - d e g r e e s -of freedom Leas t s q u a r e s program, r e s p e c t i v e l y . The f o u r t h program, o r i g i n a t e d by T C 5 , u s e s t h e - �t e l e m e t r y d a t a as t h e basic data types a n d combines them in an o p t i o r r a l f a s h i n n t n n h t a i n r m p a r i s o n s between the d e r i v s d data s e t s . This program only being considered a n d has noE yet been p r o g r a m e d . D. F l i g h t Mechanics Branch A re-work of the AS-204 m i s s ion w i t h t:?e 206 s p a c e c r a f t The S-TB rilt program, S - I m g u i d a n c e p r z s e t t i n g s , and end c o n d i t i o n s of flight w i l l b e availnble fur deliver:: to R-XSTR on A p r i l 1 4 , 1 9 6 7 . The range s a f e t y and a b ~ r at n d altern:-, m i s s i o n documents will be complete b y June 1, 1967. Work on meetizg t h r~l ~ i7 . v ~ r ydate f o r s u p p o r t i n g rhe 204 m i s s i o n will take priori;.? over a l l other work. (Dl) has been i n i t i a ' e d . Tnc revised r e f e r e n c e trajectory f o r 205 has b e e n d i s t r i ' n u ted h y R-AERO-FMR- 52-67, d a t e d F e b r u a r y 13 1967 - The r a n g e s a f e t y 2nd d i s p e r s i o n a n a l y s i s have been reviewed and f o u n d a c c e p r able. These do cum en:^ s h o u l d be d i s t r i b u t e d by A p r i l 1 4 , 1967. The f i n a l AS-205 operational t r a j e c t o r y has been completed. The AS-208 preliminary o p e r a t i o n a l trajectory which presents d a t x f o r t h e f i r s t and second o p p o r t u n i t i e s Fs a l s o complete. R-P&VE-E" l a s requested t h a t t h e PU (valve o f f the s to a ) s h i f t time be moved from 280 to 250 seconds on AS-208 to p r o v i d e a higher w e l i a b i l i t y of g e t t i n g t h r u s t slopes c a l l e d o u t by rhe guic2. x c e r e s t r i c t i o n guidelines. Concurrence to t h i s proposal l r a s g i v e n . R ~ c e n t l y , a decision was made t o l-iave t h e AS-2'35 l a u n h v e h i c l c c a r r y a Block I1 spacecraft on a m i s s i o n simi1, r to t h e 0171 8 5 - 2 0 4 m i s s i o n . Work will b e g i n shortly to s u p p o r t th s effort, The AS-206 d i s p e r s i o n a n a l y s i s r c p o r t :bzs bczn d i s t r l i l u r ~ d by memorandzlm R-AERO-FM-49-67, F e b r u a r y 9, 1 3 6 7 . Tne rasge s a f ~ t y a n a l y s i s is pub1 ished i n R-AERO-FMR-57-67, F e b r u a r y 2 3 , i 9 ~ 7 . The f i n a l operational, t r a j e c t o r y document: has b e e n r c t u ~ n c d L Q C C S 3 fo-re-publication. IL Td2s "accepter?, when cormnents are i n c o r p o r a ~ e d . " A d r a f t of the a b o r t and alternate m i s s i o n document r e L e i v e d from CCSD i s b e i n g reviewed. S e v e r a l t r a j e c t o r i e s have been generated r o s u p p a r t E p o s s i b l c passtvation c x c s c i s c on AS-206. LC �The AS-201 preliminary operational t r a j e c r o r y r e p o r t is b e i n g s h i p p e d from CCSD. The S - I B tilt and end c o n d i t i o n s of f l i g h t have b e e n r e c e i v e d on AS-209. These v e h i c l e s were targeted to the 2051208 rendezvous end c o n d i t i o n s . 5. Orbital D e b r i s Memorandum R-AERO-FM- 25-67, "Debris Hazard A n a l y s i s P r i o r i t y , I f was p u b l i s h e d in response to " ~ e b r i sk z a r d A n a l y s i s f o r O r b i t a l Reentry," I-MO-3-67, J a n u a r y 5 , 1967. A draft of the final r e p o r t an S a t u r n IB Risk Hazard, received from Lockheed, appears K O b e a c c e p r a b l e . A new s t u d y c o n t r a c t covering March 31, 1967 through March 3 1 , 1 9 6 8 t o analyze o r b i t a l d e b r i s problems r e l a t e d to S a t u r n IB and S a t u r n V l a u n c h v e h i c l e s has been a p p r o v e d . The Boeing Company' s f i n a l operational Era jectory document has been r e v i e w ~ d . It has been found s a t l s f a c ~ o r yif they re-submit t h e docurnenc correcting many a d m i n i s t r a t i v e e r r o r s . Several of the S - I n AS-501 b y R-AERO-FMT to v e r i f y Boeing results. and h i g h m i x t u r e r a t i o d i s p e r s i o n s . The mately 9200 pounds of f l i g h t performance d i s p e r s i o n c a s e s have been r u n Of most concern were S-IVB ].ow low MR c a s e r e q u i r e d approxireserve. A p r e s e n t a t i o n prepared f o r D r . Geissler on opfrational l u n a r rargeting and p~sformancereserve requirements for S a t u r n V AS-501 was g i v e n by M r . Gerald W i t t e n s t e i n of R-AERO-MT. MSC has b e e n s u p p l l e d with the d a t a t h a t they r e q u e s t e d f o r Q = 1 PSF. They have also been s u p p l i e d S-IVB t h r u s t h i s t o r y for their simulations. A s p e c l a 1 work r e q u e s t has b e e n generaLed Lor TBC to perlorm an S-IVB l u n a r i m p a c t p r o b a b i l i t y s t u d y and the AS-502 two-opportunity problem. The f i n a l ground r u l e s for AS-502 r a n g e s a f e t y have been agreed upon. �A rough d r a f t of the AS-502 abort and a l t e r n a t e m i s s i o n documene has been r e c e i v e d from TBC. T h i s has been reviewed a n d comments made in a memo. Red limit l i n e s f o r AS-502 have been e s t a b l i s h e d between TEC, KSC (Range), and R-AERO-FNT. The AS-SO2 u p d a t e d guidance presettings from TBC have been r e v i e w e d and found s a t i s f a c t o r y . The AS-502 p r e l i m i n a r y o p e r a t i o n a l trajectory document r e c e i v e d from TBC is b e i n g v e r i f i e d . The trajeckory has been v e r i f i e d and is a c c e p t a b l e . The AS-502 final operational trajectory g r o u n d r u l e s have been a g r e e d upon. U s i n g 502 data a n d sample 5 0 4 rargzting, operational t a r g e t i n g p r o c e d u r e s for LLM e f f o r t are being established. R-AERO-FMT has received a copy of t h e s o u r c e deck of the j o i n r s p a c e program s o t h a t m o d i f i c a t i o n s can be made for f u r t h e r a u t o m a t ion. 9. M i s c e l laneous The required Cape t a p e parameters have been p r o g r a m e d in Fartran IV f o r R-AERO-FMT' s 6-D MARWS s i m u l a t i o n . A copy of t h e S a t u x n V plot deck has been given to the Boe ing Company. �W i l h o l d , G. A * , "S-TVB Forward S k i r t Panel F l u t t e r w i t h Respect to t h e S a t u r n V Vehicle Series ,I1 Office Memo R-AERO-RU-67-6, J a n . 25, 1967. Walkex, R. W., " P r e d i c t e d Drag C o e f f i c i e n t a n d C e n t e r of Pressure Needed in Conducting D r i f t S t u d i e s f o r the Saturn V Vehicle at Launch," O f f i c e Memo R-AERO-AU-67-10, Feb. 1 7 , L967. Schutzenhofer, L. A . , "Prelftninary, F l u c t u a t i n g Pressure Data from the AEDC 4 P e r c e n t Saturn V Model E ~ p e r i m e n t , ~Office ' Memo R-AEROAU-67-12, Feb. 21, 1967. Reed, T. G., "Accuracy of the Ground W i n d s , Wind Tunnel Model ~ a t a , " O f f i c e Memo B-AERO-AU-67-15, Feb. 2 4 , L967. " ~ c o u s t i c a lE f f e c t s Produced by V a r i a t i o n of C l u s t e r C o n f i g u r a t i o n , " O f f ice Memo R-AERO-Au-67-16, Feb, 2 4 , 1967. G u e s t , S., Schutzenhofer, I,. A , , "Preliminary, One-third Octabe Fluctuating Pressure Spectrums f r o m the AEDC 4 P e r c e n t Saturn V Model E x p e r i ment," Office Memo R-AERO-RU-67-19, March 1, 1 9 6 7 . Walker, R. W., '"redicted R e s u l t a n t : Bending Moments due to Graund W i n d s f o r Saturn IB (AS-206) Unfueled and Fueled Weight CondFti~ns,~' O f f i c e Hem0 R-AERO-AU-61- 24, March 8, 1967. Walker, R. Id., "Extrapolation of Saturn D Graund Winds Wind Tunnel Test: Data to a Wind Magnitude of 100 Knots," R-AERO-AU-67-29, March 2 0 , 1 9 6 7 . G u e s t , S . , f I B l a s t Overpressure vs D i s t a n c e from a Propellant Loaded S - I C a n d S-I1 S t a g e Separately P o s i t i o n e d in he S-IC S t a t i c T e s t S t a n d (MSFC F a c i l i t y 4 6 7 0 ) , " Off ice Memo R - A E R O - A L ! - ~ ~ - ~ ~March , 27, 1967. Rochelle, W, C., "Review of Thermal R a d i a t i o n from L i q u i d and S o l i d Propellant Rocket Exhausts,'QASA 'I1M X-53597, Feb. 20, 1967. McCarter, James W., "Analog SirnuPation of 21-11 S t a g e P r o p e l l a n t U t i l f z a t i o n System," NASA TM X-53580, Feb. 2 3 , 1 9 6 7 . Worley, R. Eugene, W. L. Brady, and George F. YcDonough, "Preliminary A n a l y s i s of a Cablc R e t r i e v a l Technique for the T e t h e r e d Am Workshop,' NASA TM X-53583, March 1, 1967. �BIl3ZIOGRAPITY {Continued) 13. Glasgow, Robert M., " S t a t i c Aerodynamic Characteristics of the Aborted Apollo-Saturn V Vehicle," NASA TH X-53587, March 9, 1 9 4 7 . 14. Duncan, J. Reynolds, "Preliminary S a t u r n VJVoyager T r a j e c t o r y f r o m E a r t h to Mare," NASA TN X-53588, Maxch 10, 1 9 b 7 , 15. Scissum, J e a n e t t e A . , "'Survey of Solar Cycle P r e d i c t i o n Models ," KASX P I X-53593, March 30, 1967. 16. S h e a t s , 5 . I?. , "Trajectory A p p b i c a t t o n Nethod ," Aero-As tradynarnics Internal Note No, 1-67, March 21, 1967, �APPROVAL 7, = I 7, 7 , 1 -- E. D. Geisslcs D i r e c t o r , Aeso-As trrodynamics L a b o r a t o r y D ISTRIBETION R-AERO-DIR D r . Geissler Mr. Jean R-AERO-R Nr. B u t l e r (4) Mrs. High towcr R-AFRO-P (8) R-AERO-D (16 ) R-AERO-A ( 2 0 ) R-AERO-G (20) R-AERO-Y R-AEIIO-F R-AERO-X R-DIR (5) (8) (2) . PAO, Mr. R u r t t MS-H, I-V-P, I-V-P Miss Jerre1.l ( 3 ) Harold P r i c e Mr. Jennings R-AERO-T Mr. von Puttkamer Mr. Murphreo Mr. C m i n g s Mr. Dickey N r . Heybey Mr. L a v e n d e r Mr. J a n d ebeur Dr. iiu D r . Krause � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000041 Title A name given to the resource "Aero-Astrodynamics Laboratory Bimonthly Progress Report: February - March 1967." Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center Date A point or period of time associated with an event in the lifecycle of the resource 1967-04-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) NASA space programs Project management Type The nature or genre of the resource Progress reports Text Source A related resource from which the described resource is derived Saturn V Collection Box 21, Folder 22 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050 https://digitalprojects.uah.edu/files/original/20/989/spc_stnv_000042.pdf 9ab40e2f3f0b55a8c7a082a15a4ff56a PDF Text Text AERO-ASTRODWICS LABORATOTY BIMONTHLY PROGRESS REPORT P I? December 12. 1966 7 . - \ . INDEX Page I ............................ PROJECTS OFFICE ........................................... ADVANCED STUDIES' OFFICE ................................... AEROSPACE ENVIRONMENT DIVISION ............................ ASTRODYNAMICS AND GUIDANCE THEORY DIVISION ................ A . O p t i m i z a t i o n Theory Branch ............................ B . Astrodynamics Branch .................................. C . Guidance Theory Branch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . D . S c i e n t i f i c A d v i s o r y Committee . . . . . . . . . . . . . . . . . . . . . . . . . AEROPHYSICS DIVISION ...................................... A . F l u i d Mechanics R e s e a r c h O f f i c e ....................... B. M e c h a n i c a l Design O f f i c e .............................. C . Aerodynamic Design Branch ............................. D . E x p e r i m e n t a l A e r o p h y s i c s Branch . . . . . . . . . . . . . . . . . . . . . . . E . Thermo Environment Branch ............................. . TECHNICALAND SCIENTIFIC STAFF . 11 . 111 . v. IV VI . F VII . . DYNAMICS AND FLIGHT MECHANICS DIVISION . . . . . . . . . . . . . . . . . . . . A . Multi-Projects B Saturn V C S a t u r n IB D S a t u r n A p o l l o A p p l i c a t i o n Program E. Other P r o j e c t s F General . . . VIII Unsteady Aerodynamics Branch . . . . . . . . . . . . . . . . . . . . . . . . . . . ........................................ ............................................. ...................................... ..................... ........................................ ............................................... . FLIGHT TEST ANALYSIS DIVISION ............................. A . S p e c i a l P r o j e c t s O f f i c e ............................... B . F l i g h t E v a l u a t i o n Branch .............................. C . F l i g h t Mechanics Branch ............................... D . T r a c k i n g and O r b i t a l A n a l y s i s Branch .................. 1 9 13 16 18 18 22 23 25 30 30 31 32 36 41 46 49 49 51 54 57 62 62 66 66 66 70 71 �AERO-ASTRODYNAMICS LABORATORY BIMONTHLY PROGRESS REPORT December 1 2 , 1966 I. TECHNICAL AND SCIENTIFIC STAFF A. M r . Lavender 1. A p o l l o T e l e s c o p e Mount A c t i v i t y c e n t e r e d on t h e combined AS 209-212 ATM/OWS e f f o r t . P r e s e n t a t i o n s were g i v e n t o D r . M u e l l e r on October 7 and October 20. The MSFC e f f o r t h a s b e e n s u c c e s s f u l . Our recommendations have b e e n a p p r o v e d i n c l u d i n g t h e unmanned l a u n c h o f t h e OWS, t h e m u l t i p l e docking a d a p t e r , r e s u p p l y module, and t h e L,M/ATM. The f i r s t r e l e a s e of G e n e r a l System O p e r a t i n g Requirements f o r t h e S a t u r n - A p o l l o Specification A p p l i c a t i o n s Combined M i s s i o n O r b i t a l Workshop/Apollo T e l e s c o p e Mount, d a t e d November 28, h a s b e e n p r e p a r e d by T e c h n i c a l Systems O f f i c e , R-TO. M r . Teague, R-AERO-P, w i l l now assume t h e AERO p r o j e c t e n g i n e e r i n g r e s pons ibj.1 i t i e s f o r t h e combined m i s s i o n . - 2. P r o j e c t Able Mid- t e r m p r e s e n t a t i o n s were g i v e n by t h e f i v e c o n t r a c t o r s on O c t o b e r 4-7 a t MSFC and t o NASA H e a d q u a r t e r s on October 11. M r . C a r t e r , R-AS, gave a summary p r e s e n t a t i o n t o DOD on October 26. F i n a l p r e s e n t a t i o n s were g i v e n by t h e c o n t r a c t o r s on November 15-17. An e x e c u t i v e b r i e f i n g t o D r . von Braun was g i v e n November 9. F i n a l r e p o r t s a r e due from t h e c o n t r a c t o r s i n e a r l y December. An MSFC r e p o r t i s planned t o e s t a b l i s h o u r p o s i t i o n . P r o j e c t Thermo During a P r o j e c t Thermo s t a t u s b r i e f i n g b y P&VE t o D r . von Braun and t o p MSFC t e c h n i c a l management on O c t o b e r 3 , 1966, D r . v o n Braun s u g g e s t e d t h a t a n i n v e s t i g a t i o n b e made on combining t h e P r o j e c t Thermo o r b i t a l o p e r a t i o n w i t h t h e S-IVB workshoplATM combinat i o n . R-P&VE-A ( w i t h R-AERO' s a s s i s t a n c e ) i s i n v e s t i g a t i n g v a r i o u s P r o j e c t Thermo m i s s i o n o p e r a t i o n s modes, i n c l u d i n g t h e one s u g g e s t e d by D r . von Braun. We i n t e n d t o r e p o r t t h e r e s u l t s o f t h i s i n v e s t i g a t i o n t o D r . von Braun a t a n e a r l y d a t e . On O c t o b e r 1 7 , 1966, a P r o j e c t Thermo s t a t u s b r i e f i n g ( s i m i l a r t o t h e one g i v e n t o D r . von Braun) was g i v e n t o OMSF. The r e c e p t i o n was q u i t e f a v o r a b l e . A follow-on b r i e f i n g t o D r . G. E. Mueller is a n t i c i p a t e d i n t h e n e a r f u t u r e . �The t h i r d c o n t r a c t i n t e r f a c e m e e t i n g was h e l d i n November between MSFC, DAC, and GAEC. The Phase C f i n a l d e f i n i t i o n i s due t o b e g i n i n March 1967 and w i l l r e q u i r e i n c r e a s e d i n - h o u s e p a r t i c i p a t i o n . 4. ESMRO (Experiments f o r S a t e l l i t e and M a t e r i a l Recovery from O r b i t ) S t u d y C o n t r a c t NAS8-18119 (R-AS-VO) On September 28, 1966, R-COMP-RDS t r a n s f e r r e d t h e Sequenci n g O p t i m i z a t i o n A u t o m a t i c Program (SOAP) f o r a s t r o n a u t time1 i n e a n a l y s i s and t h e I t e r a t i v e S o l u t i o n Program ( o r b i t a l t r a n s f e r ) , a s a u t h o r i z e d i n R-AERO-FT-37-66, d a t e d August 31, 1966, t o Emerson E l e c t r i c Company (EEC;' s u b c o n t r a c t o r t o B a l l B r o t h e r s R e s e a r c h Corporat i o n on t h i s s t u d y ) . EEC w i l l u s e t h e s e programs, and a n y EEC improvements a r e t o b e r e t u r n e d t o MSFC a t t h e end o f t h e s t u d y . On O c t o b e r 7 , 1966, R-COMP-RDS t r a n s f e r r e d t h e FORTRAN I V Cowell Program (SOAP l o a d i n g program) and t h e s u n and moon ephemeris t a p e ( a s a u t h o r i z e d i n R-AERO-FT-46-66, d a t e d September 30, 1966) t o EEC. T h i s m a t e r i a l supplements t h e e a r l i e r t r a n s m i s s i o n t o EEC. An ESMRO midterm program r e v i e w b r i e f i n g was h e l d a t MSFC on November 8 , 1966. Most r e c e n t a c t i v i t y h a s b e e n d i r e c t e d toward p l a n n i n g a v i s i t t o t h e u n s u c c e s s f u l OAO s a t e l l i t e . B. Mr. Cummings 1. S t a t i s t i c a l Data P r o c e s s i n g Cons i d e r a b l e c o o r d i n a t i o n and d e t a i l e d i n v e s t i g a t i v e work was r e q u i r e d t o overcome t h e problems a s s o c i a t e d w i t h c a l i b r a t i o n s i g n a l s and r e c o r d i n g c o n v e n t i o n s on t h e m a g n e t i c t a p e s c o n t a i n i n g t h e a n a l o g d a t a from D r . F i s c h e r , I I T . However, once t h i s was s t r a i g h t e n e d o u t , t h e d a t a p r o c e s s i n g proceeded a s p l a n n e d . The c o r r e l a t i o n s o b t a i n e d w e r e , i n g e n e r a l , v e r y low a s D r . F i s c h e r had t o some e x t e n t a n t i c i p a t e d . The p r e s e n t program performed w e l l i n d e t e c t i n g t h e s e small c o r r e l a t i o n s . The c o m p l e t e s e t o f d a t a h a s b e e n c o m p l e t e l y p r o c e s s e d and r e t u r n e d i n good c o n d i t i o n t o D r . F i s c h e r . 2. Computer Program E v a l u a t i o n The t e s t c a s e s which h a v e p r e v i o u s l y b e e n m u t u a l l y a g r e e d upon by a l l concerned p a r t i e s as n e c e s s a r y t o a d e q u a t e l y e v a l u a t e t h e c o n c e p t s , a p p r o x i m a t i o n s , and a s s u m p t i o n s c o n t a i n e d i n t h e computer p r o gram p r e v i o u s l y p r e p a r e d by R-COMP-RRV and R-AERO-AM a s d i s c u s s e d i n t h e September 1966 monthly p r o g r e s s r e p o r t w i l l s t i l l n o t b e completed. R e s u l t s of t h e r e m a i n i n g r e q u e s t e d r u n s a r e needed t o f i n i s h t h e e v a l u a t i o n and t o document t h e s e new t e c h n i q u e s and t h e i r r e l a t i v e performance a s compared t o more c o n v e n t i o n a l t e c h n i q u e s . �3. Program f o r S p e c t r a l Decomposition The f i r s t c u t o f a computer program f o r t h e s p e c t r a l d e c o m p o s i t i o n of c r o s s - c o r r e l a t i o n f u n c t i o n s , a s o b t a i n e d from t h e p r o gram d i s c u s s e d i n i t e m ( 2 ) above f o r t h e p i e c e w i s e e s t i m a t i o n o f c o r r e l a t i o n f u n c t i o n s , h a s been d e v e l o p e d and i s b e i n g w r i t t e n up a s t h e b a s i s o f a programming r e q u e s t t o R-COMP-RRV. The w r i t e - u p w i l l c o n t a i n t h e p e r t i n e n t e q u a t i o n s , t h e l o g i c a l f l o w c h a r t s , and v e r y d e t a i l e d sample c a s e s which w e r e c a r e f u l l y c h o s e n and e v a l u a t e d t o s e r v e a s a s p e c i f i c check o f a l l p r e s e n t l y c o n c e i v e d major a s p e c t s o f t h e program. A r o u g h d r a f t o f t h i s document was f i n i s h e d b e f o r e t h e l o s s o f M r . Q . D. P e a s l e y t o R-RP-N. 4. S c a n n i n g Geometry The i n i t i a l i n v e s t i g a t i o n s o f t h e g e o m e t r i c c o n s i d e r a t i o n s i n v o l v e d i n t h e e x p e r i m e n t a l s e t - u p and t h e s c a n n i n g o p e r a t i o n s f o r t h e v a r i o u s p l a n n e d c r o s s e d - b e a m e x p e r i m e n t s h a s b e e n o n l y p a r t i a l l y comp l e t e d and e v a l u a t e d . The r e m a i n i n g work h a s b e e n l a i d a s i d e f o r t h e e a r l y and t i m e l y i n v e s t i g a t i o n o f o t h e r problems o f o u r p r o p o s e d measurement o f a t m o s p h e r i c w i n d s . 5. N o n - S t a t i o n a r y Winds A sequence o f experiments i s being planned f o r s i m u l a t i o n on t h e IBM 7094 computer t o i n v e s t i g a t e a n d / o r d e t e r m i n e t h e v a r i o u s t y p e s o f l i m i t a t i o n s t h a t may be r e q u i r e d i n a p p l y i n g o u r p r e s e n t l y a v a i l a b l e and p l a n n e d programs t o t h e s t a t i s t i c a l d e t e c t i o n and m e a s u r e ment o f n o n - s t a t i o n a r y wind d a t a . A s e t o f c l e a r p o s i t i v e r e s u l t s from t h e s e e x p e r i m e n t s may n o t be o b t a i n e d , b u t i f t h e y a r e , much t i m e and expense w i l l be saved i n p r e p a r i n g f o r o u r atmospheric t e s t s ; i f n o t , t h e n we w i l l have g a i n e d , a t l e a s t , needed i n s i g h t i n t o s e v e r a l o f t h e c h a r a c t e r i s t i c s and a r e a s o f g e n e r a l i t y t h a t must be b u i l t i n t o t h e f u t u r e programs f o r s u c h n o n - s t a t i o n a r y measurements. C. D r . Heybey Some o f t h e more i m p o r t a n t p o i n t s which have emerged from t h e s t u d y o f e a r l i e r p a p e r s o n t h e crossed-beam method a r e l i s t e d below. 1. The method, i n p r i n c i p l e , c a n employ any form o f e n e r g y t h a t c a n be b u n d l e d i n t o beams and u n d e r g o e s l o s s e s when t h e s e p a s s thro-ugh a medium w i t h o u t a f f e c t i n g i t t h e m s e l v e s . The beams may be c r e a t e d o u t s i d e t h e medium o r t h r o u g h p h y s i c a l p r o c e s s e s ( r a d i a t i o n ) i n s i d e i t . I n t h e l a t t e r c a s e , d e t e c t o r s o n l y a r e needed. The e n e r g y e m i t t e d may i n c i r c u m s t a n c e s t r a v e l o n c u r v e d p a t h s whose c o u r s e i t m i g h t be d i f f i c u l t t o assess. I f i t d o e s n o t , t h e s t r a i g h t l i n e o f s i g h t m a y be t a k e n a s t h e a x i s o f t h e beam. The method r e m a i n s a p p l i c a b l e s i n c e i t d o e s n o t c a l l f o r t h e knowledge o f t h e s o u r c e i n t e n s i t y . �2. The i n t e n s i t y l o s s p e r u n i t l e n g t h o f t r a v e l i s t a k e n a s proportional t o the local intensity. The p r o p o r t i o n a l i t y f a c t o r , o r e x t i n c t i o n c o e f f i c i e n t , K , w i l l depend o n t h e n a t u r e o f b o t h t h e e n e r g y employed and t h e medium t r a v e r s e d . It i s r e q u i r e d t h a t any f l u c t u a t i o n s i n t h e magnitude o f K a r e c a u s e d by f l u c t u a t i o n s i n t h e medium a l o n e ( a b o u t w h i c h o n e w a n t s i n f o r m a t i o n ) . A c a r e f u l c o n s i d e r a t i o n must be g i v e n i n any i n s t a n c e t o p o s s i b l e e n e r g y f l u c t u a t i o n s of t h e s o u r c e . 3 . It i s assumed t h a t , a t any i n s t a n t , t h e s t a t e o f t h e medium i s t h e same o v e r a g i v e n c r o s s s e c t i o n o f t h e beam (which t h e r e f o r e must be n a r r o w , s t r i c t l y s p e a k i n g , o f d i f f e r e n t i a l w i d t h ) . One c a n t h e n d e f i n e ( b u t n o t m e a s u r e ) t h e t e m p o r a l mean v a l u e , i?, o f K a t a g i v e n " s t a t i o n " o f t h e beam. I n d e r i v i n g t h e m a t h e m a t i c a l a p p a r a t u s t h e major a s s u m p t i o n i s made t h a t t h e i n t e g r a l o v e r t h e d i f f e r e n c e , k = K = I?, t a k e n a l o n g t h e beam l e n g t h , i s a l w a y s much l e s s t h a n u n i t y . This a p p e a r s a s w a r r a n t e d i f t h e ( p o s i t i v e and n e g a t i v e ) d e v i a t i o n s o f K from t h e t e m p o r a l mean a r e s m a l l a t e v e r y s t a t i o n , a s c a n be e x p e c t e d , f o r i n s t a n c e , i n boundary l a y e r o r f r e e - j e t t u r b u l e n c e . More d o u b t f u l i s t h e a p p l i c a t i o n of t h e c u r r e n t mathematics t o w i l d l y f l u c t u a t i n g , e . g . , s e p a r a t e d o r r o c k e t exhaust flows. 4. The t i m e - r e c o r d produced o n t h e d e t e c t o r s i d e e x h i b i t s t h e e x t i n c t i o n c o e f f i c i e n t f l u c t u a t i o n s superimposed by t h o s e g i v e n o u t by t h e i n s t r u m e n t a t i o n . The t e c h n i c a l problem o f e x t r i c a t i n g s i g n a l from n o i s e c a n be t a k e n a s s o l v e d i n a t h e o r e t i c a l i n v e s t i g a t i o n . 5 . M a t h e m a t i c a l l y , two beams, 1 and 2 , a r e c r o s s e d by m u l t i p l y i n g t h e l i n e i n t e g r a l s o v e r k a l o n g t h e two p a t h s . P h y s i c a l l y , t h e two beams c a n be a l l o w e d t o t r a v e l a t some d i s t a n c e from e a c h o t h e r (no actual crossing taking place). The beam d i r e c t i o n s a r e c o n v e n i e n t l y a l i g n e d p a r a l l e l t o two a x e s o f a r e c t a n g u l a r C a r t e s i a n s y s t e m . It i s assumed t h a t t h e s h o r t e s t c o n n e c t i o n between t h e beams ( p a r a l l e l t o t h e t h i r d a x i s ) d e f i n e s c o o r d i n a t e d p o i n t s ( o r r a t h e r v o l u m e s ) o n t h e beams. The p r o p e r p l a c i n g o f t h e t h r e e a x e s i s a t h i n g t o ponder i n e v e r y experimentation. It i s , o f c o u r s e , n o t n e c e s s a r y t h a t t h e y a r e m u t u t a l l y orthogonal. 6 . I f t h e beam d i r e c t i o n s a r e d e s i g n a t e d by x l and x,, t e m p o r a l c o v a r i a n c e o f t h e two i n t e g r a l s can be w r i t t e n a s the �p r o v i d e d a n exchange i n t h e s e q u e n c e o f i n t e g r a t i o n p r o c e s s e s i s l e g i t i mate. T h i s f o r m u l a i s t h e main r e s u l t of t h e c u r r e n t m a t h e m a t i c a l development. The f a c t o r of p r o p o r t i o n a l i t y l e f t u n w r i t t e n h e r e i s t h e wroduct o f t h e t i m e - a v e r a g e d i n t e n s i t i e s measured a t t h e d e t e c t o r s i d e . The v a l u e of R can b e found e x p e r i m e n t a l l y ; i t w i l l v a r y when t h e beams a r e d i s p l a c e d . The a v e r a g i n g o f t h e (kl, k 2 ) - p r o d u c t b e g i n s a t a f r e e l y c h o s e n t i m e t + c and i s c o n t i n u e d u n t i l t h e r e s u l t , from a c e r t a i n T o n , remains v i r t u a l l y c o n s t a n t . ( I f t h i s could n o t b e a c h i e v e d , t h e p r e s e n t method would b r e a k down.) I n g e n e r a l , t h e v a l u e of R, f o r a g i v e n beam c o m b i n a t i o n , w i l l depend on t h e c h o i c e of t9:. So w i l l a n y p h y s i c a l q u a n t i t y e l i c i t e d from i t . The b e s t one c a n hope f o r i s t h a t i t w i l l v a c i l l a t e w i t h i n t h e e r r o r m a r g i n i n h e r e n t i n t h e measurement and t h u s can b e a s s i g n e d a s u i t a b l e c o n s t a n t v a l u e . O t h e r w i s e , one may a r r i v e a t a mean v a l u e by a v e r a g i n g o v e r t 9 ~ . 7 . The c o v a r i a n c e , Rk of t h e ( k l , k,) - p r o d u c t , i . e . , t h e i n n e r ( l i m i t - ) i n t e g r a l i n t h e e x p r e s s i o n f o r R, c a n b e w r i t t e n i n form of a ( q u a d r u p l e ) F o u r i e r i n t e g r a l . The i n t e g r a n d i n i t i s t h e mathem a t i c a l e x p r e s s i o n of a p l a n e wave; t h e i n t e g r a t i o n g o e s o v e r a t r i p l y i n f i n i t e s e t of wave numbers (and o v e r t i m e ) . Those m a t h e m a t i c a l waves h a v e a l l c o n t i n u o u s l y d i f f e r e n t v e l o c i t i e s , d i r e c t i o n s , and a m p l i t u d e s . It i s n o t w i s e , I b e l i e v e , t o a s s i g n them p h y s i c a l r e a l i t y , a s sometimes seems t o b e done ("The t u r b u l e n t m o t i o n c o n s i s t s of p l a n e waves . I r ) . With d i f f e r e n t beam c o m b i n a t i o n s , t h e d i f f e r e n t v a l u e of Rk w i l l be d e s c r i b e d by a s y s t e m of waves w i t h d i f f e r e n t a m p l i t u d e s . One i s t h u s f a c e d w i t h i n f i n i t e l y many s e t s of i n f i n i t e l y many p l a n e waves o f v a r i e d c h a r a c t e r . I t i s n o t i m p o s s i b l e t h a t some of t h e waves can b e g i v e n p h y s i c a l s i g n i f i c a n c e , b u t t h i s must be d e m o n s t r a t e d b y a r g u m e n t a t i o n i n d e p t h . The v a l u e s o f Rk and R c a n be made d i m e n s i o n l e s s by a s u i t 8. On i n t e g r a t i o n a b l e n o r m a l i z a t i o n , l e t us c a l l them and R* t h e n . o v e r t h e beam l e n g t h s and t h e c o n n e c t i n g l i n e , one o b t a i n s t h r e e c h a r a c t e r i s t i c l e n g t h s c a l e s . As l o n g a s t h e f l u c t u a t i o n s a r e u n c o r r e l a t e d , t h e c o v a r i a n c e Rk w i l l b e z e r o . The i n v e r s e of t h i s s t a t e m e n t i s n o t g e n e r a l l y t r u e ; a nonlinear r e l a t i o n s h i p can e x i s t then. Excluding t h i s p o s s i b i l i t y , one may s a y t h a t t h e c o r r e l a t i o n volume w i l l be c o m p a r a b l e i n s i z e t o t h e volume d e l i n e a t e d by t h e t h r e e l e n g t h s c a l e s , a l t h o u g h , i n comparing them, one m u s t u s e t h e m e a s u r a b l e q u a n t i t y R* i n s t e a d o f R;. I n t h i s way one can judge how f a r t h e m e t h o d ' s o r i g i n a l o b j e c t i v e h a s been achieved: t o e l i c i t local information without disturbing the medium. I n t h e c a s e of s e p a r a t i o n beams, t h e c o r r e l a t i o n volume w i l l e n v e l o p t h e s h o r t e s t s t r a i g h t c o n n e c t i o n between them. I f the l a t e r a l l e n g t h s c a l e s a r e of m i n u t e s i z e , t h e r e e x i s t s a c o r r e l a t i o n more o r l e s s c o n f i n e d t o t h e two e n d p o i n t s of t h e c o n n e c t i n g l i n e . In his r e p o r t s , D r . F. K r a u s e s e t s up s u f f i c i e n t c o n d i t i o n s i n w h i c h , i n t h e c a s e o f t u r b u l e n t f l o w , s u c h a t w o - p o i n t c o r r e l a t i o n c a n b e o b t a i n e d whcn t h e l a t e r a l s c a l e s a r e n o t s m a l l . W i t h medium-sized l a t e r a l s c a l e s , i s o t r o p i c t u r b u l e n c e must b e s t i p u l a t e d . W i t h l a r g e l a t e r a l s c a l e s , t h e r e i s a m a t h e m a t i c a l c o n d i t i o n w h i c h i s a p p l i c a b l e t o o t h e r phenomena a s w e l l , b u t may n o t a l w a y s b e s a t i s f i a b l e i n p h y s i c a l r e a l i t y . RE RE �D r . Liu D. 1. V e h i c l e Dynamics The dynamics o f a s p a c e v e h i c l e due t o t h e v i b r a t i o n s of i t s e l a s t i c e l e m e n t s , mass t r a n s l a t i o n s , d o c k i n g , e t c . , a r e b e i n g s tud i e d . 2. High Speed B a l l o o n Dynamics S t u d y on u s i n g a l a r g e b a l l o o n f o r t h e r e c o v e r y of a The i n t e r a c t i o n between t h e l a r g e r e u s a b l e r o c k e t s t a g e is under way. e l a s t i c d e f o r m a t i o n o f t h e b a l l o o n and t h e aerodynamic p r e s s u r e r e s u l t s i n a v e r y c o m p l i c a t e d dynamic problem. The o b j e c t of t h i s work i s t o d e t e r m i n e t h e s i z e , maximum s t r e s s , and t h e s p e e d of t h e b a l l o o n . E. M r . von P u t t k a m e r 1. Advanced Launch V e h i c l e T r a j e c t o r y R e s e a r c h (Nor t h r o p C o n t r a c t S .O. 1 5 ) a. Rocket P r o p u l s i o n Models The computer r o u t i n e p r e v i o u s l y developed t o s i m u l a t e t h e f l i g h t of v e r t i c a l l y launched t w o - s t a g e r o c k e t v e h i c l e s , t h e VTOo n l y program, h a s b e e n u p d a t e d . S p e c i f i c a l l y , t h e sequencing of p r i n t s t a t e m e n t s and t h e program l o g i c used f o r p r i n t - o u t c o n t r o l have been improved. Some f u r t h e r s t r e a m l i n i n g was done i n t h e p r o c e s s . I n g e n e r a l , t h e development o f t h e VTO-only, HTO-only, and HTO-sonic boom computer programs h a s b e e n e s s e n t i a l l y completed. The r e s p e c t i v e d e c k s have been r e c e i v e d from t h e c o n t r a c t o r , a n d a r e p o r t i s b e i n g p r e p a r e d t o document a l l t h r e e programs u n d e r a s i n g l e c o v e r . b . A i r b r e a t h e r P r o p u l s i o n Model Logic h a s b e e n added t o t h e K T O - a i r b r e a t h e r program t o s i m u l a t e t h e c o n s t a n t dynamic p r e s s u r e p h a s e o f t h e l a u n c h t r a j e c t o r y . A s u b r o u t i n e t o c a l c u l a t e t h e i n l e t d u c t p r e s s u r e behind t h e o b l i q u e f u s e l a g e s h o c k h a s b e e n programmed and added. Rather than u s i n g g a s dynamic t a b l e s , t h e shock-wave a n g l e 8 i s computed from a c u b i c e q u a t i o n i n s i n 2 8 , r e q u i r i n g t h e Mach number and t h e e f f e c t i v e a n g l e - o f - a t t a c k , which a l s o h a s t o a c c o u n t f o r t h e wing sweep a n g l e . The P ~ ~ - s u b r o u t i nwe i l l a l s o be needed i n f u t u r e i n v e s t i g a t i o n s o f t h e e f f e c t of t h e p r e c o m p r e s s i o n f i e l d on p r o p u l s i o n performance. �The a d d i t i o n o f t h i s s u b r o u t i n e t o t h e HTO-airbreather d e c k h a s caused t h e program t o exceed t h e SDS-930 s t o r a g e c a p a c i t y . C o n s e q u e n t l y , t h e c o n t r a c t o r h a s b e e n d i r e c t e d t o change t h e program o v e r t o r u n on t h e CDC-3200 computer which h a s c o n s i d e r a b l y l a r g e r s t o r a g e t h a n t h e SDS-930. Logic w i l l b e added t o h a n d l e t h e t r a n s i t i o n from t h e c o n s t a n t - q - p h a s e t o t h e c o n s t a n t - d u c t - p r e s s u r e p h a s e . The l a t t e r phase w i l l t h e n b e programmed. Because o f a change i n p e r s o n n e l p e r f o r m i n g t h e cont r a c t e d e f f o r t , a h o l d h a s developed i n t h e e f f o r t s under c o n s i d e r a t i o n . 2. Advanced Systems and M i s s i o n S t u d i e s a. Solar-Electric were h e l d w i t h e f f o r t s and t o and t r a j e c t o r y S o l a r - E l e c t r i c Mars P h o t o Miss i o n Our s u p p o r t o f R e s e a r c h P r o j e c t s L a b o r a t o r y i n t h e Mars P h o t o M i s s i o n s t u d y h a s made p r o g r e s s . M e e t i n g s RPL p e r s o n n e l on 10114 and 10126 t o c o o r d i n a t e o u r p l a n f u r t h e r i n v e s t i g a t i o n s i n t o t h e f l i g h t mechanics s i t u a t i o n of t h i s m i s s i o n . The work performed d u r i n g t h e r e p o r t i n g p e r i o d i n c l u d e d two-dimensional p l a n e t o c e n t r i c ( s p i r a l - t y p e ) c a l c u l a t i o n s and t h r e e d i m e n s i o n a l h e l i o c e n t r i c low- t h r u s t C. 0 . V. o p t i m i z a t i o n w i t h o u t E a r t h and Mars, by AERO-GG (Causeyl Ingram), a t t i t u d e c o n t r o l a n a l y s e s and o r b i t a l maneuvering and s t a t i o n - k e e p i n g s t u d i e s , a s w e l l a s s o p h i s t i cated three-dimensional c a l c u l a t i o n s o f Earth-to-Mars low-thrust t r a j e c t o r i e s i n c l u d i n g e f f e c t s o f p l a n e t s , s u n , p l a n e c h a n g e s , e t c . , by AERO-GS (Schwaniger/Galloway/~uncan). N o r t h r o p , under t h e m i s s i o n s u p p o r t c o n t r a c t , h a s p r o v i d e d some p r e l i m i n a r y Mars o r b i t - k e e p i n g r e q u i r e m e n t s and l o w - t h r u s t two-dimensional t r a j e c t o r y r u n c h e c k i n g o u t o l d e r EOS d a t a . On November 29, t h e f i f t h c o o r d i n a t i o n m e e t i n g between AERO and RPL t o o k p l a c e . Most of t h e f i n a l r e s u l t s w e r e p r e s e n t e d and d i s c u s s e d i n c o n s i d e r a b l e d e t a i l . Of p a r t i c u l a r i m p o r t a n c e t o t h e f u t u r e f a t e of t h e s o l a r - e l e c t r i c photo-mission concept is a p p a r e n t l y t h e p o l i t i c a l s i t u a t i o n posed by Voyager. Consequently, t h i s p o i n t was d i s c u s s e d e x t e n s i v e l y . A l s o , Aero L a b o r a t o r y recommended emphati c a l l y t h a t RPL'S c o n c e p t n o t be based e x c l u s i v e l y on a n u p r a t e d S a t u r n I B v e h i c l e (260" s o l i d ) , b u t t h a t f u r t h e r i n v e s t i g a t i o n b e cond u c t e d assuming t h e s t a n d a r d v e r s i o n o f t h e S a t u r n IB. T h i s and o t h e r s u g g e s t i o n s by Aero a r e b e i n g c o n s i d e r e d by RPL. Our s u p p o r t of RPL i n t h e s t u d y under d i s c u s s i o n h a s b e e n t e m p o r a r i l y t e r m i n a t e d , w h i l e a p r e s e n t a t i o n t o D r . v o n Braun ( p l a n n e d f o r mid-December) is b e i n g p r e p a r e d . �b. J u p i t e r Fly-By M i s s i o n s On October 11, f o l l o w i n g a n i n v i t a t i o n by J . von P u t t k a m e r , members o f t h e F o r t Worth D i v i s i o n of General Dynamics gave a p r e s e n t a t i o n on t h e i r p a s t and c u r r e n t work i n t h e a r e a o f advanced p l a n e t a r y p r o b e s t o i n t e r e s t e d Aero-Astrodynamics p e r s o n n e l . GD/FW h a s r e c e n t l y f i n i s h e d a s t u d y of " J u p i t e r Fly-by M i s s i o n s " f o r JPL and is p r e p a r i n g f o r t h e b i d on t h e upcoming Advanced P l a n e t a r y Probe (APP) s t u d i e s , which w i l l be c e n t e r e d on J u p i t e r f l i g h t s , m u l t i - p l a n e t f l y b y u l t i m a t e l y - t h e g a l a c t i c m i s s i o n . The d i r e c t i o n o f m i s s i o n s and t h e s e e f f o r t s w i l l be t a k e n o v e r by Goddard Space F l i g h t C e n t e r . - The s t u d y team, which i n c l u d e d D r . L a r r y Hove, D r . Vernon Lee, D r . F r o s t , and M r . J o n e s , u n d e r t h e d i r e c t i o n of D r . Ted Webb, h a s i n v e s t i g a t e d f o u r d i f f e r e n t s p a c e c r a f t d e s i g n c o n c e p t s , t h r e e of w h i c h u t i l i z e t h r e e - a x e s s t a b i l i z a t i o n w h i l e t h e f o u r t h f e a t u r e s s p i n s t a b i l i z a t i o n . Launch v e h i c l e s c o n s i d e r e d r a n g e from ATLAS/Centaur/ HEKS t o S a t u r n V and S a t u r n V/Centaur. Using what a p p e a r s t o b e a cons e r v a t i v e a p p r o a c h , GD/FW conducted a r e l i a b i l i t y a n a l y s i s and d e r i v e d " p r o b a b i l i t y of m i s s i o n s u c c e s s " e s t i m a t e s which a r e g e n e r a l l y below 0.01 f o r t o t a l m i s s i o n a c h i e v e m e n t (Mariner I V Y u s i n g t h e same e v a l u a t i o n p r o c e d u r e s , had 0.11 e x p e c t e d m i s s i o n s u c c e s s p r o b a b i l i t y ) . c. SAE Launch V e h i c l e and M i s s i l e s Committee On O c t o b e r 6 , a t t h e a n n u a l m e e t i n g of t h e SAE Launch V e h i c l e and M i s s i l e s Committee i n Los A n g e l e s , C a l i f o r n i a , i t was d e c i d e d t h a t t h e SAE 2nd Space Technology C o n f e r e n c e , t o be h e l d on May 9-12, 1967, i n P a l o A l t o , C a l i f . , c l o s e t o t h e Ames R e s e a r c h C e n t e r , would h a v e t h e t i t l e "Low C o s t O r b i t a l T r a n s p o r t a t i o n . " It would b e co-sponsored by B r i t a i n ' s " B r i t i s h I n t e r p l a n e t a r y S o c i e t y , " F r a n c e ' s " S o c i e t e F r a n c a i s e d ' As t r o n a u t i q u e ," Germany's "Deutsche Gesel l s c h a f t f u e r R a k e t e n t e c h n i k und Raumfahrt," and I t a l y ' s " A s s o c i a z i o n e I t a l i a n a Razzi," w i t h Eurospace, Junkers, Dassaul t A v i a t i o n , B r i t i s h A i r c r a f t Corp., Rolls-Royce, B r i s t o l - S i d d e l e y , ERNO, and S o c i e t a T r a n s p o r t i M i l l i s t i c i and o t h e r s b e i n g r e p r e s e n t e d . R e p o r t s w e r e g i v e n by t h e s e s s i o n chairmen on t h e p a p e r s s u b m i t t e d f o r c o n s i d e r a t i o n . While t h e d e a d l i n e f o r a b s t r a c t s u b m i t t a l h a s a l r e a d y p a s t , M r . von P u t t k a m e r , who w i l l b e c h a i r i n g t h e s e s s i o n on "Far Term Advanced Launch V e h i c l e s ,I1 proposed t h a t a p a p e r on " C o n t r o l Systems of Advanced Launch V e h i c l e s f ' b y B l a i r and Redus o f AERO-G b e i n c l u d e d i n t h e s e s s i o n on "Pacing Technology I m p l i c a t i o n s . " M r . von Puttkamer a l s o recommended i n c l u s i o n o f a p a p e r by H. Wuenscher of R-ME-DIR i n t h e s e s s i o n on " P a r t i a l l y R e c o v e r a b l e Systems," a c c e p t a n c e o f which is c e r t a i n . A s a p o s s i b l e l o c a t i o n f o r t h e 3rd Space Technology Converence i n 1968, Langley R e s e a r c h C e n t e r was t e n t a t i v e l y s e l e c t e d . �d. Hypersonic A i r c r a f t Technology A d e t a i l e d r e p o r t e n t i t l e d "On t h e C u r r e n t S t a t u s of H y p e r s o n i c A i r c r a f t Technology'' was d i s t r i b u t e d on a l i m i t e d b a s i s . e. Advanced Systems T e c h n i c a l Reviews Technical reviews a t t e n d e d during t h e r e p o r t i n g period i n c l u d e d " H y p e r s o n i c A i r c r a f t B r i e f i n g , " by t h e McDonnell Company, " P r o p u l s i o n A c t i v i t i e s a t A e r o j e t , " by t h e A e r o j e t Corp. , "Over t h e H o r i z o n , B o o s t and R e e n t r y , ' I by N o r t h American, "Apollo Lunar Landing Symposium," by MSC/HOUS t o n , and "Nuclear Rocket Programs , I 1 by Rocketdyne. A l s o , d u r i n g t h i s p e r i o d , two p r e s e n t a t i o n s were g i v e n t o Aero L a b o r a t o r y on t h e " S o l a r - E l e c t r i c Mars P h o t o Mission" and on A e r o j e t ' s in-house a c t i v i t i e s . R e p o r t s e v a l u a t e d i n c l u d e d t h e r e p o r t of t h e Ad Hoc Subpanel on R e u s a b l e Launch V e h i c l e Technology, "Performance P o t e n t i a l of LH2-Fueled A i r b r e a t h i n g C r u i s e A i r c r a f t " and "Design Cons i d e r a t i o n s o f R e u s a b l e Launch V e h i c l e s . " 11. PROJECTS OFFICE A. The S a t u r n V Sys tems E n g i n e e r i n g I n c e n t i v e C o n t r a c t The n e g o t i a t i o n s w i t h t h e Boeing Company (TBC) on t h e Sys tems E n g i n e e r i n g Documentation (Task 8.0) p o r t i o n o f t h e i n c e n t i v e c o n t r a c t i n which t h e Aero-Astrodynamics L a b o r a t o r y was l e a d l a b o r a t o r y w e r e comp l e t e d d u r i n g t h e week o f November 1 4 , 1966. The n e g o t i a t e d p l a n i n c l u d e s motivating incentives i n the following areas: (1) F l i g h t v e r i f i c a t i o n - r e q u i r e s accuracy i n systems i n t e g r a t i o n and c o m p u t a t i o n . (2) Schedule r e q u i r e s prompt d e l i v e r y t o e x i s t i n g o r revised schedules. (3) - Performance - r e q u i r e s q u a l i t y p r o d u c t i o n o f a d e q u a t e s o f t w a r e f o r S a t u r n V program. The s u c c e s s f u l n e g o t i a t i o n s of t h e i n c e n t i v e p l a n c u l m i n a t e s a n The m a j o r d i f f i c u l t i e s extensive e f f o r t i n d r a f t i n g an acceptable plan. e n c o u n t e r e d were ( 1 ) program f l e x i b i l i t y , ( 2 ) a d d i t i o n a l manpower r e q u i r e d t o manage a n i n c e n t i v e c o n t r a c t o f t h i s t y p e , and ( 3 ) p o s s i b l e d e t e r i o r a t i o n of e n g i n e e r i n g working r e l a t i o n s between MSFC and TBC. The p l a n �h a s been c o n s t r u c t e d t o minimize t h e a d v e r s e e f f e c t o f t h e above items i n o r d e r f o r t h e S a t u r n V Systems E n g i n e e r i n g e f f o r t t o c o n t i n u e smoothly and e f f e c t i v e l y . The g r e a t e s t a d d i t i o n a l burden on t h e l a b o r a t o r i e s r e s u l t i n g from t h i s i n c e n t i v e c o n t r a c t w i l l be i n t h e form of added paper work i n c o n n e c t i o n w i t h r e c o r d i n g and m o n i t o r i n g of i n d i v i d u a l TBC documents, added m o n i t o r i n g of s c h e d u l e s of b o t h Government F u r n i s h e d Data (GFD) and TBC document d e l i v e r i e s . B. A p o l l o / S a t u r n V Recycle C a p a b i l i t y A p r e s e n t a t i o n was g i v e n a t t h e Management Council Meeting of November 22, 1966, on t h e c u r r e n t s t a t u s of t h e A p o l l o / S a t u r n V Recycle C a p a b i l i t y f o r t h e f i r s t l u n a r l a n d i n g m i s s i o n . MSFC, KSC, MSC and Bellcomm p e r s o n n e l p a r t i c i p a t e d i n t h i s e f f o r t . A d r y - r u n of t h i s p r e s e n t a t i o n g i v e n t o MSFC p e r s o n n e l on November 1 6 , 1966, i s b r i e f l y summarized as f o l l o w s : - 2 112-hour (1) It a p p e a r s t h a t "holding" w i t h i n t h e l a u n c h window and l a u n c h i n g b e f o r e c l o s i n g of t h e window w i l l pose no b i g problem. I f t h e countdown i s q u i t e c l o s e t o l a u n c h , a r e c y c l e t o L-15 m i n u t e s may be r e q u i r e d . (2) Recycle from one l a u n c h o p p o r t u n i t y t o t h e s u b s e q u e n t one w i l l r e q u i r e a b o u t 48-53 h o u r s , a n d e f f o r t w i l l b e expended t o g e t t h i s time t o 48 h o u r s o r s l i g h t l y l e s s . ( 3 ) The proposed m i s s i o n p l a n n i n g f o r t h e f i r s t l u n a r l a n d i n g m i s s i o n would s u p p o r t t h r e e monthly l a u n c h o p p o r t u n i t i e s spaced This p a t t e r n a p p r o x i m a t e l y 48 h o u r s a p a r t w i t h i n a b o u t a n 8-day p e r i o d . of l a u n c h o p p o r t u n i t i e s w i l l r e p e a t e v e r y month. The a c t i v i t i e s f o r g e n e r a t i n g t h e t a r g e t i n g and o t h e r m i s s i o n r e l a t e d d a t a t o s u p p o r t a t h r e e - m o n t h s p a n o f l a u n c h o p p o r t u n i t i e s ( t h r e e o p p o r t u n i t i e s p e r 8-day p e r i o d f o r e a c h of t h e t h r e e months) w i l l b e g i n a b o u t 7 t o 7 1 1 2 months b e f o r e l a u n c h , and c u l m i n a t e i n f i n a l program v e r i f i c a t i o n and t r a n s m i t t a l t o KSC a t a p p r o x i m a t e l y one month b e f o r e s c h e d u l e d l a u n c h . KSC w i l l be p r o v i d e d " t y p i c a l " m i s s i o n d a t a f o r u s e u n t i l L-1 month. During t h e p r e s e n t a t i o n t h e c e n t e r s were asked t o d e t e r m i n e i f t h e i d e n t i f i e d 7 112-month l e a d time f o r o p e r a t i o n a l d a t a could n o t b e reduced t o a 2-month l e a d time. This is being i n v e s t i g a t e d . C. F l i g h t Mechanics P a n e l and Sub-panels A c t i v i t i e s 1. and 20, 1966. follows: F l i g h t Mechanics P a n e l (FMP) The E i g h t e e n t h FMP Meeting was h e l d a t MSC on October 19 Some of t h e items from t h e m e e t i n g a r e summarized a s �( a ) A t a s k team of t h e FMP i s b e i n g e s t a b l i s h e d t o f o r m u l a t e and implement a p l a n of a c t i o n f o r d e t e r m i n i n g t h e f e a s i b i l i t y of manual b o o s t e r c o n t r o l and a l s o t o d e t e r m i n e i f LV/SC g u i d a n c e s w i t c h o v e r i n e a r t h o r b i t i s indeed w i t h i n t h e c a p a b i l i t y o f t h e v e h i c l e (from a s p e c t s of g u i d a n c e , dynamics, and c o n t r o l , e t c . , d u r i n g S-IVB second b u r n of AS-503 and s u b s ) . (b) A s k e l e t o n p l a n f o r t r a n s f e r r i n g i n t e r f a c e w e i g h t ( i . e . , payload changes) n e a r l a u n c h time due t o L / V payload c a p a b i l i t y changes a n d / o r v a r y i n g m i s s i o n r e q u i r e m e n t s due t o time o f p r o j e c t e d launch d a t a has been prepared. The d e t a i l s of t h e s e p r o c e d u r e s a r e s u b j e c t t o r e f i n e m e n t and w i l l be f u l l y documented. ( c ) The problem of " q u i c k r e t a r g e t i n g " o f t h e L/V and S/C f o r LOR m i s s i o n s caused b y changes (such a s l a n d i n g s i t e s ) a s l a t e as one month b e f o r e l a u n c h h a s been i n v e s t i g a t e d . Computer programs, LV/SC i n t e r f a c e d a t a exchange r e q u i r e m e n t s , and o t h e r p r o c e d u r e s a r e b e i n g planned t o accommodate t h i s c a p a b i l i t y . The "nominal" t i m e r e q u i r e m e n t s a r e c o n s i d e r a b l y l o n g e r , of c o u r s e , and t h e s e p r o c e d u r e s a r e planned o n l y f o r t h e c o n t i n g e n c y c a s e of l a t e changes. Both t h e If nominal" and " q u i c k turn-around" s c h e d u l e s a r e b e i n g documented. ( d ) The FMP h a s o f f i c i a l l y s t a r t e d m i s s i o n p l a n n i n g work f o r AS-209 (AAP) m i s s i o n . The r e s u l t s of t h i s m e e t i n g a r e documented i n MSC memorandum PM2-M2-9-66, d a t e d October 20, 1966. 2. 1966. F l i g h t L i m i t s Sub-panel (FLSP) The S i x t h FLSP Meeting was h e l d a t MSFC on November 9 , The m i n u t e s a r e documented i n MSFC memorandum R-AERO-P-459-66. 3. Guidance and Performance Sub-panel (G&PSP) The Twenty-Second G&P Sub-panel m e e t i n g was h e l d a t MSFC on November 8 , 1966. Among t h e i t e m s d i s c u s s e d was t h e s t a t u s o f t h e m i s s i o n p l a n n i n g a c t i v i t i e s f o r each of t h e ~ p o l l o / S a t u r nm i s s i o n s . It was p o i n t e d o u t t h a t MSC i s c o n s i d e r i n g r e d u c i n g t h e d i f f e r e n c e i n o r b i t a l a l t i t u d e between t h e AS-207 and AS-208 v e h i c l e s from t h e p r e s e n t 20 n.mi. t o a p p r o x i m a t e l y 1 0 t o 15 n.mi. The m i s s i o n a n a l y s i s , b e i n g conducted by MSC, w i l l b e completed by a b o u t December 1 5 , 1966. I f t h e change i s made, t h e a l t i t u d e of t h e CSM w i l l p r o b a b l y b e changed r a t h e r t h a n r e q u i r i n g a change o f t h e LM (AS-208) a l t i t u d e . For AS-209, t h e m i s s i o n r e q u i r e m e n t s , p r e l i m i n a r y m i s s i o n p r o f i l e , and p r e l i m i n a r y r e f e r e n c e t r a j e c t o r y have b e e n d e l a y e d a p p r o x i m a t e l y one month b e c a u s e of t h e r e c e i p t of d i r e c t i o n t h a t AS-209 w i l l b e a n unmanned workshop. MSC p r e s e n t e d d a t a on t h e planned a c t i o n of t h e SC i n t h e e v e n t of e a r l y s t a g i n g of t h e S-IVB from t h e S-11 S t a g e . MSC s t a t e d t h a t , f o r manned m i s s i o n , t h e i r primary c o n c e r n i s a t t a i n i n g a " s a f e " o r b i t from �which a b o r t t o a d e s i r e d recovery a r e a can be i n i t i a t e d . The "safe" o r b i t was d e f i n e d a s a n o r b i t w i t h a p e r i g e e of n o t l e s s than 75 n.mi. For AS-501, i f s t a g i n g is i n i t i a t e d a t a time which w i l l n o t a l l o w t h e S-IVB t o a t t a i n i t s 100 n.mi. e a r t h o r b i t , t h e SM w i l l be s t a g e d from t h e S-IVB a t t h e time of S-IVB c u t o f f , and flown t o a r e e n t r y e l l i p s e which w i l l p r o v i d e some s i m u l a t i o n of t h e r e e n t r y t e s t . CSM w i l l be t a r g e t e d f o r a n e l l i p s e w i t h an apogee of a b o u t 6,000 n.mi. This e l l i p s e can be a t t a i n e d f o r a l l S - I 1 f a i l u r e times a f t e r 164-seconds The t e s t would provide h e a t l o a d s a t r e e n t r y f o r about of S - I 1 burn. 56 p e r c e n t of t h e nominal t r a n s l u n a r r e e n t r y c o n d i t i o n s . For S - I 1 f a i l u r e s b e f o r e 164 seconds of S - I 1 burn, t h e CSM t a r g e t i n g w i l l remain t h e same, and f u r t h e r d e g r a d a t i o n of t h e h e a t s h i e l d t e s t w i l l be a c c e p t e d . The minutes of t h e meeting a r e documented i n MSFC memorandum R-AERO-P-472-66, dated November 1 2 , 1966. Guidance Switchover and Manual Booster Control Task Team On November 15, 1966, MSFC R e p r e s e n t a t i v e s a t t e n d e d t h e f i r s t meeting of t h e Guidance Switchover and Manual Booster Control Task Team Meeting a t MSC. The Apollo Systems S p e c i f i c a t i o n Requirements c a l l s f o r S a t u r n V guidance switchover c a p a b i l i t y i n o r b i t . R-AERO w i l l be involved i n comparing t h e S I C Trans-Lunar I n j e c t i o n (TLI) guidance equations t o the G IM e q u a t i o n s f o r performance and accuracy c a p a b i l i t i e s should switchover be r e q u i r e d . I n t h e a r e a of manual b o o s t e r c o n t r o l , MSC p r e s e n t e d a proposed scheme which b a s i c a l l y monitors a l t i t u d e , a l t i t u d e r a t e , and v e l o c i t y f o r use i n manually c o n t r o l l i n g the b o o s t e r d u r i n g upper s t a g e s of f l i g h t should t h i s be r e q u i r e d . Through a hand c o n t r o l l e r , t h e launch v e h i c l e body r a t e w i l l be commanded. The SIC i s programmed w i t h t h e nominal p r o f i l e (polynomial) which i s used a s a Since t h e IGM can a c t u a l l y be f u n c t i o n i n g guidance/control baseline. p r o p e r l y and t h e p r o f i l e n o t comparing c l o s e t o a p r e - p r o g r a m e d a r t i f i c i a l p r o f i l e , MSFC expressed concern t h a t a s w i t c h i n g d i s c o n t i n u i t y would e x i s t and l a r g e t r a n s i t s would r e s u l t . The scheme was modified t o comp a r e t h e p r e - p r o g r a m e d p r o f i l e t o t h e a c t u a l p r o f i l e and t o b i a s t h e pre-programmed t o match t h e a c t u a l p r o f i l e b e f o r e s w i t c h i n g t o manual control. This w i l l a l l e v i a t e t h e p o t e n t i a l problem. Dynamic s i m u l a t i o n s w i l l be conducted by R-ASTR and R-AERO t o v e r i f y performance, s t a b i l i t y , e t c . , witlh t h e man-in-the-loop. MSC p l a n s t o go ahead w i t h implementing t h e scheme a s modified because of s c h e d u l e c o n s i d e r a t i o n s ; t h e v e r i f i c a t i o n of t h e scheme, a s w e l l a s t h e d e t e r m i n a t i o n of t h e o p e r a t i o n a l p r o c e d u r e s , w i l l be conducted w h i l e t h e scheme i s being implemented. E f f o r t s w i l l be c o n c e n t r a t e d on AS-503 and s u b s . No SC/LV hardware i n t e r f a c e problems o r requirements f o r new c a b l e s , w i r e s , e t c . , were identified. �111. ADVANCED STUDIES OFFICE A. O f f i c e o f t h e Chief The FY-65 S a t u r n Improvement S t u d i e s h a v e b e e n completed and f i n a l c o n t r a c t o r p r e s e n t a t i o n s were made d u r i n g t h e f i r s t week of O c t o b e r . A summary o f t h e i n f o r m a t i o n was p r e s e n t e d by MSFC t o H e a d q u a r t e r s on November 21, 1966. An a b b r e v i a t e d v e r s i o n of t h e H e a d q u a r t e r s r e v i e w was p r e s e n t e d t o t h e L a b o r a t o r y s t a f f o n November 28, 1966. The FY-65 funded s t u d i e s were aimed a t t h r e e a r e a s of u p r a t i n g : t h e S a t u r n IB, S a t u r n V, and a c l a s s c a l 1 e d " i n t e n n e d i a t e s a t u r n ! ' The l a s t c l a s s , i n t e r m e d i a t e S a t u r n , i n v e s t i g a t e d t h e f e a s i b i l i t y of using S a t u r n V s t a g e s i n v a r i o u s ground l a u n c h modes. The s t u d i e s i n v o l v e d s i x c o n t r a c t o r s and i n t e r f a c e d c l o s e l y w i t h p a r a l l e l KSC l a u n c h f a c i l i t y s t u d i e s . The c o n t r a c t o r s and d o l l a r s i n v o l v e d were as f o l l o w s : UTC (United Technology Corp.) NAA ( N o r t h American A v i a t i o n ) TBC (The Boeing Company) DAC (Douglas A i r c r a f t Company) CCSD ( C h r y s l e r C o r p o r a t i o n Space D i v . ) (sub) $1,644K A-JG (Aero-Jet G e n e r a l ) Launch F a c i l i t i e s Study: TMC (The M a r t i n Company) C o n n e l l (A&E) TOTAL $1,894~ The i n - d e p t h a n a l y s e s a c h i e v e d f o r t h e v a r i o u s v e h i c l e c o n f i g u r a t i o n s w e r e d i r e c t l y p r o p o r t i o n a l t o t h e f u n d s expended; t h e c o n t r a c t / d o l l a r v a l u e i s g i v e n t o r e f l e c t man-hours expended. The s t u d i e s were " t o t a l " s y s tems s t u d i e s d e f i n i n g t h e s t a g e m o d i f i c a t i o n and d e s i g n , f a c i l i t y i m p a c t s ( m a n u f a c t u r i n g , t e s t and launch), transportation, resource requirements, e t c . �S i n c e d e t a i l e d d o c u m e n t a t i o n was a r e q u i r e m e n t , much u s e f u l i n f o r m a t i o n i s a v a i l a b l e f o r t h e advanced m i s s i o n p l a n n e r . B. F l i g h t Mechanics and Performance A n a l y s i s Group 1. T h i s g r o u p p a r t i c i p a t e d i n t h e e v a l u a t i o n of p r o p o s a l s f o r "Use o f L a r g e S o l i d Motors i n B o o s t e r A p p l i c a t i o n s . " Of t h e f o u r p r o p o s a l s s u b m i t t e d , D o u g l a s ' a n d ~ o e i n g ' swere a d j u d g e d t o b e p r a c t i c a l l y e q u i v a l e n t i n terms o f t e c h n i c a l a p p r o a c h , and t h e r e f o r e , I. 0. i s i n a bargaining position t o negotiate the contract. 2. A p r e l i m i n a r y t i m e l i n e a n a l y s i s f o r t h e SA4 Synchronous M i s s i o n h a s b e e n g e n e r a t e d by R-AERO-DAM (Mrs. B a u e r ) . R-AERO-FO (Mr. H i l l ) i s f u r n i s h i n g t h e a n a l y s i s of t h e t r a c k i n g and communications r e q u i r e m e n t s r e s u l t i n g from h i s i n v e s t i g a t i o n s . These r e s u l t s have b e e n s u b m i t t e d t o t h e p r i m a r y i n v e s t i g a t o r s , R-P&VE and R-ASTR i n p r e l i m i n a r y form and w i l l b e u p d a t e d . 3 . A memorandum (R-AERO-X-118-66) summarizing t h e performance c a p a b i l i t i e s o f s e l e c t e d c o n f i g u r a t i o n s o f t h e S a t u r n V and S a t u r n I B f o r space s t a r i o n s u p p o r t has been d i s t r i b u t e d . 4. The m i s s i o n s u p p o r t c o n t r a c t o r (Raytheon) h a s s u c c e s s f u l l y implemented t h e IGM i n t h e BOP deck. The p r o c e d u r e i s t o u s e t h e I G M i n o b t a i n i n g t h e f i r s t nominal t r a j e c t o r y ( s h a p i n g o n l y ) on which t h e s t e e p e s t ascent technique is applied t o optimize the vehicle s i z i n g . Using t h e IGM i n t h i s manner ( r a t h e r t h a n g u e s s i n g i n i t i a l c o n d i t i o n s ) h a s r e s u l t e d i n a v e r y a p p r e c i a b l e s a v i n g s i n computer t i m e (up t o 1 1 2 ) . 5 . The f i r s t i t e r a t i o n on e v a l u a t i n g t h e s t u d y p r o p o s a l s f o r S-IVB S p e n t S t a g e U t i l i z a t i o n h a s b e e n made. P a r t i c i p a t i n g w i t h R-AERO-X w e r e R-AERO-F (Mr. Fulmer) and R-AERO-D (Mr. Verderaime). The f i n a l e v a l u a t i o n i s t o b e completed a b o u t December 1, 1966, C. As t r o d y n a m i c s and Miss i o n 1. Manned P l a n e t a r y Flyby M i s s i o n s Based on S a t u r n / A p o l l o Sys tem The f i r s t q u a r t e r l y r e v i e w o f t h i s s t u d y c o n t r a c t w i t h N o r t h American A v i a t i o n was h e l d a t MSFC o n November 2, 1966. T h i s f i r s t p h a s e o f t h e s t u d y was p r i m a r i l y concerned w i t h g e n e r a t i n g p a r a m e t r i c d a t a t o c o v e r t h e s p e c t r u m o f s y s t e m s , modes, and programs b e i n g c o n s i d e r e d . P r i m a r y e f f o r t was expended on d e f i n i n g rendezvous p r o f i l e s f o r t h e two o r b i t l a u n c h v e h i c l e s (S-IVB and S - I I B ) b e i n g s t u d i e d . The s c i e n t i f i c and e x p e r i m e n t s programs a r e a l s o w e l l under way. The s i x s c i e n t i f i c c o n s u l t a n t s , NAA, and t h e i r s u b c o n t r a c t o r , AVCO, h a v e had m e e t i n g s t o d e f i n e a n e x p e r i m e n t s program and t o b e g i n �p r e l i m i n a r y p r o b e d e s i g n c o n c e p t s . A l s o s e v e r a l c a n d i d a t e s u b s y s tems and s y s t e m s have b e e n s e l e c t e d f o r p o s s i b l e i n c l u s i o n i n t h e makeup of complete v e h i c l e / s y s t e m s c o n f i g u r a t i o n s . Presently, there is considerable discussion a s t o the r e l a t i o n s h i p o f t h i s NAA c o n t r a c t e d s t u d y and t h e NASA i n - h o u s e p l a n e t a r y JAG e f f o r t . A m e e t i n g was h e l d a t NASA h e a d q u a r t e r s t o I t was attempt t o s e t f o r t h guidelines t o define the relationship. t e n t a t i v e l y d e c i d e d by D r . Dixon, NASA h e a d q u a r t e r s , t h a t a copy of t h e JAG r e p o r t would b e p r o v i d e d t h e c o n t r a c t o r , t h r o u g h B. G. N o b l i t t , COR f o r t h e f l y b y s t u d y c o n t r a c t . B e f o r e s e n d i n g t h e r e p o r t t o t h e c o n t r a c t o r , D r . Dixon w i l l d i s c u s s w i t h t o p management o f N o r t h American A v i a t i o n c o n c e r n i n g t h e i n t e n t o f NASA t o p r o v i d e them a copy of t h e report. 2. G e n e r a l Theory of R e l a t i v i t y Experiment E f f o r t i s c o n t i n u i n g i n s u p p o r t of RPL t o i d e n t i f y a t t r a c t i v e h e l i o c e n t r i c o r b i t p r o f i l e s t h a t a r e compatible w i t h the e x p e r i m e n t m i s s i o n r e q u i r e m e n t s and t h e S a t u r n V payload c a p a b i l i t y t o meet t h e r e q u i r e d e n e r g y l e v e l s . A l s o o f i m p o r t a n c e i s t h e a t t r a c t i v e n e s s o f t h e o r b i t s f o r t r a c k i n g and o r b i t d e t e r m i n a t i o n p u r p o s e s . R e p r e s e n t a t i v e he1i o c e n t r i c o r b i t s having e c c e n t r i c i t i e s between 0 . 4 and 0.5 and semi-major a x e s between 0.7 and 0 . 8 A . U . ' s have been s e l e c t e d t o b e e v a l u a t e d i n more d e t a i l . Communication d i s t a n c e and a n g l e s a r e b e i n g d e t e r m i n e d f o r t h e s e p r o f i l e s . From t h e v i e w p o i n t o f t h e e x p e r i m e n t s , i t may b e d e s i r a b l e t o have t r a j e c t o r i e s t h a t a r e somewhat i n c l i n e d t o t h e e c l i p t i c p l a n e ; t h e r e f o r e , p r o f i l e s i n c l i n e d t o t h e e c l i p t i c p l a n e by a p p r o x i m a t e l y 20 degrees, a s well a s t r a j e c t o r i e s t h a t a r e i n the e c l i p t i c plane a r e being analyzed. 3. P h o t o g r a p h i c E x p l o r a t i o n o f Mars w i t h S o l a r E l e c t r i c Propulsion T h i s e f f o r t i s c o n t i n u i n g i n s u p p o r t of RPL. A twod i m e n s i o n a l , h e l i o c e n t r i c l o w - t h r u s t computer program h a s b e e n d e v e l o p e d and checked o u t . The program h a s b e e n used t o v e r i f y and e x t e n d d a t a o b t a i n e d by M r . Wood, RPL. O r b i t - k e e p i n g r e q u i r e m e n t s f o r c i r c u l a r o r b i t s a t Mars w i t h a l t i t u d e s between 200 and 5 0 , 0 0 0 km have been generated . Data g e n e r a t e d by R-AERO-XA i n s u p p o r t of t h i s p r o j e c t a r e b e i n g p r e p a r e d f o r M r . Wood, RPL. M r . Wood t e n t a t i v e l y p l a n s t o p r e s e n t t h e r e s u l t s o f t h i s s t u d y t o D r . von Braun i n mid-December. �4. Mars S u r f a c e Sample R e t u r n Probe - MSSR Both t h e in-house s t u d y and t h e c o n t r a c t o r ' s s t u d y a r e s c h e d u l e d f o r c o m p l e t i o n by t h e f i r s t week of December. D. Systems A n a l y s i s Group A memorandum i s t o be p u b l i s h e d t o b r i e f t h e a d d r e s s e e s on t h e aerodynamic d a t a t o be a v a i l a b l e s h o r t l y on t h e improved S a t u r n IB and V v e h i c l e s , and t h e b a s e h e a t i n g t e s t s planned f o r a n improved S a t u r n V configuration. These t e s t d a t a w i l l e n a b l e t h e c o n t r a c t o r s t o p e r f o r m more r e l i a b l e c o n t r o l s t u d i e s , s t r e s s a n a l y s e s , e t c . , i n a n y f u t u r e S a t u r n improvement s t u d i e s . IV. AEROSPACE ENVIRONMENT DIVISION A. Space Environment Branch P r o p o s a l s have b e e n r e c e i v e d and a r e b e i n g e v a l u a t e d on t h e d e f i n i t i o n of a n e x p e r i m e n t t o s t u d y i n t e r a c t i o n s of g a s m o l e c u l e s w i t h a s o l i d s u r f a c e i n t h e ambient s p a c e environment. The e v a l u a t i o n and c o n t r a c t n e g o t i a t i o n s w i l l be completed soon. Two t e c h n i q u e s , b o t h o f which a r e p r o m i s i n g , have b e e n proposed, and b o t h w i l l p r o b a b l y be studied. P r o p o s a l s r e c e i v e d on t h e d e f i n i t i o n o f a n o r b i t a l d e n s i t y , d r a g c o e f f i c i e n t , and gas-molecule s o l i d - s u r f a c e i n t e r a c t i o n e x p e r i m e n t have been e v a l u a t e d . Three s e p a r a t e c o n c e p t s have been p r o p o s e d , and p o s s i b l y a l l t h r e e w i l l be s t u d i e d . Work was i n i t i a t e d on programming a new model of t h e e a r t h ' s upper a t m o s p h e r e f o r u s e as a s t a n d a r d a t MSFC. T h i s i s ~ a c c h i a ' s 1964 model which a p p e a r s t o be t h e b e s t a v a i l a b l e a t t h e p r e s e n t t i m e . A computer program f o r t h i s model i s b e i n g developed. Work i s c o n t i n u i n g on producing a more r e l i a b l e method f o r p r e d i c t i n g f u t u r e s u n s p o t c y c l e s . A F o u r i e r s e r i e s a n a l y s i s i s produci n g some e x c e l l e n t r e s u l t s ; however, a d d i t i o n a l v e r i f i c a t i o n i s r e q u i r e d b e f o r e t h e method can be used. Work is c o n t i n u i n g on r e f i n i n g o u r model of t h e J o v i a n atmosp h e r e . A problem has a r i s e n i n t h e t e m p e r a t u r e computation p o r t i o n of t h e program, however, which h a s d e l a y e d p u b l i c a t i o n . The l a u n c h e s s c h e d u l e d f o r October i n o u r upper atmosphere measurement program have been postponed due t o a problem i n t h e s e n s i t i v i t y of t h e i n s t r u m e n t a t i o n w i t h r e s p e c t t o t h e a t m o s p h e r i c �c o n s t i t u e n t s . G o l d - p l a t e d i n s t r u m e n t s launched i n August were n o t a b l e t o measure a t o m i c oxygen. A c o n c e r t e d e f f o r t t o remedy t h i s d e f i c i e n c y was begun i n September; however, no s o l u t i o n h a s y e t b e e n found. An a r t i c l e e n t i t l e d , " I o n o s p h e r i c R a r e f a c t i o n F o l l o w i n g Rocket T r a n s i t , " w r i t t e n by M e s s r s . F e l k e r and R o b e r t s a p p e a r e d i n October 1 i s s u e o f t h e J o u r n a l o f Geophysical R e s e a r c h . S e v e r a l equipment i t e m s have b e e n p u r c h a s e d i n p r e p a r a t i o n f o r t h e L a b o r a t o r y ' s i o n o s p h e r i c s t u d y program. S i x t r a n s m i t t e r s have been ordered along w i t h a t o t a l of t w e l v e c r y s t a l o s c i l l a t o r s which h a v e a s t a b i l i t y o f one p a r t i n 10". Two t e n t a t i v e s i t e s have b e e n i n s p e c t e d by t h e l a b o r a t o r y p r o j e c t managers. P r e l i m i n a r y approval has been obtained f o r t h e use of t h e s e 1o c a t i o n s . Chances f o r o b t a i n i n g t h e C-4 ionosonde a p p e a r t o b e r e l a t i v e l y good. A v a n is b e i n g r e n o v a t e d s o t h a t t h e ionosonde may b e conveni e n t l y moved t o a n y s i t e o f o u r c h o o s i n g . H o p e f u l l y , t h e program w i l l become o p e r a t i o n a l by F e b r u a r y . B. T e r r e s t r i a l Environment Branch 1. Technical Reports O f f i c e memorandum R-AERO-Y-124-66, "Frequency o f Thunders t o r m O c c u r r e n c e s a t H u n t s v i l l e , Alabama ," d a t e d O c t o b e r 3 , 1966. TM X-53422, " E s t i m a t i o n of P a r a m e t e r s i n Compound W e i b u l l D i s t r i b u t i o n s , " by L. W. F a l l s , March 30, 1966, 2. Analytical Investigations A s t u d y i s b e i n g completed on t h e f r e q u e n c y d i s t r i b u t i o n of t h e l a r g e s t monthly and l a r g e s t y e a r l y mean r e l a t i v e s u n s p o t number. These d a t a w e r e s e l e c t e d t o i l l u s t r a t e t h e u s e o f e x t r e m e v a l u e s t a t i s t i c s , d e v e l o p e d by D r . Gumbel, f o r o t h e r g e o p h y s i c a l d a t a . The r e s u l t s o f t h e s t u d y w i l l be u s e d by t h e Space Environment Branch. A d d i t i o n a l work h a s b e e n done on t h e r e l a t i v e d e v i a t i o n s o f d e n s i t y w i t h r e s p e c t t o t h e P a t r i c k R e f e r e n c e Atmosphere, 1963. A new memo w i l l b e p u b l i s h e d when t h e c o m p u t a t i o n s h a v e b e e n completed g i v i n g v a l u e s of t h e r e l a t i v e d e v i a t i o n s of d e n s i t y f o r a l l months and the annual period. 3. Contracts E l e v e n p r o p o s a l s r e c e i v e d on RFQ' s f o r "world-Wide Cloud Coverage f o r M i s s i o n A n a l y s i s " were e v a l u a t e d , and n e g o t i a t i o n s a r e b e i n g made w i t h a s e l e c t e d c o n t r a c t o r . Responses w e r e from a good �c r o s s s e c t i o n of r e s e a r c h and a e r o s p a c e o r g a n i z a t i o n s . The a e r o s p a c e o r g a n i z a t i o n s , i n p a r t i c u l a r , were s t r o n g i n t h e i r s u p p o r t of t h e proj e c t f o r t h e i r i n t e r n a l and o t h e r m i s s i o n a n a l y s i s a p p l i c a t i o n s . We hope t o i n c o r p o r a t e i n p u t s from o t h e r NASA c e n t e r s (MSC, AMES, GSFC, LRC) and H e a d q u a r t e r s (Bellcomm, OSSA, OART, OMSF) i n t h e s t u d y , and t h e r e b y produce a more c o o r d i n a t e d and g e n e r a l l y u s e f u l f i n a l p r o d u c t . R-AERO-D (Mr. eat on) i s working w i t h u s . , T h i s w i l l h e l p a s s u r e a useable routine f o r mission analysis. V. ASTRODYNAMICS AND GUIDANCE THEORY DIVISION A. O p t i m i z a t i o n Theory Branch 1. A n a l y t i c R e d u c t i o n o f Optimal T r a j e c t o r y Problem The r e p r e s e n t a t i v e o p t i m a l t r a j e c t o r y problem h a s b e e n s i m p l i f i e d , p e r m i t t i n g t h e number o f unknown i n i t i a l c o n d i t i o n s t o b e r e d u c e d from f i v e t o t h r e e . The problem was w r i t t e n i n t r a n s f o r m e d c o o r d i n a t e s and t h e c o o r d i n a t e s y s t e m p h y s i c a l l y i d e n t i f i e d . A comp u t e r program making u s e o f t h i s r e d u c t i o n method i s b e i n g p r e p a r e d . A second t r a n s f o r m a t i o n which f u r t h e r r e d u c e s t h e c o m p l e x i t y of t h e problem i s under s t u d y . D i f f i c u l t y h a s b e e n e n c o u n t e r e d i n d e t e r m i n i n g a n analytical expression f o r a v e c t o r i a l integration constant. If t h i s c o n s t a n t can b e e x p r e s s e d , t h e problem of c h o o s i n g t h e c o r r e c t i n i t i a l v a l u e s n e c e s s a r y t o compute a n o p t i m a l t r a j e c t o r y would b e r e d u c e d t o t h e problem o f i s o l a t i o n of a s i n g l e i n i t i a l c o n d i t i o n . 2. D e s i g n Concept Comparison S t u d y A s t u d y t o compare s e v e r a l p r o m i s i n g c o n t r o l s y s t e m s and t h e i r r e l a t e d s y n t h e s i s t e c h n i q u e s i s i n p r o g r e s s . The o b j e c t i v e i s t o e v a l u a t e t h e e f f e c t i v e n e s s of t h e v a r i o u s c o n t r o l d e s i g n c o n c e p t s i n m e e t i n g p r i m a r y and s e c o n d a r y c o n t r o l s y s t e m g o a l s . The s t u d y h a s b e e n o u t l i n e d and t h e computer program n e c e s s a r y f o r comparison r u n s h a s b e e n programmed. Work h a s b e e n c u r t a i l e d somewhat b e c a u s e o f o t h e r p r o j e c t s , b u t i t i s e x p e c t e d t h a t t h e s t u d y can p e r h a p s b e c a r r i e d on as a s e c o n d a r y e f f o r t . 3. Mars P h o t o O r b i t e r C o n t r o l I n s u p p o r t o f R-RP-N, a p r e l i m i n a r y i n v e s t i g a t i o n was made o f t h e f e a s i b i l i t y o f i o n t h r u s t d i f f e r e n t i a l c o n t r o l f o r a s o l a r e l e c t r i c Mars o r b i t e r v e h i c l e p r e s e n t l y under s t u d y by t h a t l a b o r a t o r y . It was concluded t h a t v a r y i n g t h e t h r u s t o f t h e i o n e n g i n e s i n d i v i d u a l l y would s u p p l y s u f f i c i e n t c o n t r o l t o r q u e s f o r t h e e x p e c t e d m a j o r d i s t u r b a n c e torques. T h r u s t d i f f e r e n t i a l c o n t r o l f o r p i t c h and yaw a x i s c o n t r o l h a s b e e n recommended d u r i n g p e r i o d s of t h r u s t i n g . The s t u d y is documented i n memo R-AERO-G-7-66. �4. AAS P r e s e n t a t i o n An a b s t r a c t f o r a p a p e r e n t i t l e d "A Review o f Some E x i s t i n g L i t e r a t u r e Concerning D i s c o n t i n u o u s S t a t e V a r i a b l e s i n t h e C a l c u l u s of V a r i a t i o n s " was a c c e p t e d by t h e American A s t r o n a u t i c a l S o c i e t y f o r p r e s e n t a t i o n a t t h e December m e e t i n g i n H u n t s v i l l e . 5. New E q u a t i o n s of Motion f o r S t a b i l i t y A n a l y s e s I n t e r n a l Note R-AERO-IN-18-66, e n t i t l e d " S t a b i l i t y of Motion o f a Launch V e h i c l e C o n s i d e r i n g t h e R a t e of Change of t h e P a t h Angle," h a s b e e n w r i t t e n and approved. I n t h i s report, a modification t o t h e p e r t u r b a t i o n e q u a t i o n s of m o t i o n used t o a n a l y z e s t a b i l i t y of t h e l a u n c h v e h i c l e ' s m o t i o n a b o u t t h e nominal t r a j e c t o r y i s p r o p o s e d . I t i s shown t h a t t h e m o d i f i e d (new) e q u a t i o n s p e r m i t more a c c u r a t e p r e d i c t i o n of s t a b i l i t y and s h o r t - t e r m dynamic b e h a v i o r t h a n do t h e c u r r e n t l y u s e d e q u a t i o n s . The r e p o r t recommends t h a t t h e new e q u a t i o n s b e used f o r a l l f u t u r e s t a b i l i t y a n a l y s e s . 6. Saturn voyager Shroud S t u d y R i g i d body c o n t r o l r e s p o n s e s t u d i e s i n s u p p o r t o f t h e r D e s i g n S t u d y a r e a p p r o x i m a t e l y f o u r weeks S a t u r n ~ / ~ o y a g eShroud b e h i n d s c h e d u l e , due t o f a i l u r e t o r e c e i v e mass d a t a from PEEVE. Once mass d a t a a r e r e c e i v e d , i t i s a n t i c i p a t e d t h a t t h e s t u d y w i l l b e comp l e t e d i n t h e four-week p e r i o d o r i g i n a l l y a l l o t t e d . 7. Contractor a. N o r t h r o p S c h e d u l e Order /I26 (1) Voyager S t u d i e s Objectives: To i n v e s t i g a t e l o a d r e l i e f s y s t e m s f o r t h e S a t u r n V/Voyager, and t o p r o v i d e s e p a r a t i o n dynamics s t u d i e s f o r t h e Voyager Shroud Design Study. A s t u d y h a s b e e n made t o d e t e r m i n e t h e f e a s i b i l i t y of implementing t h e proposed l o a d r e l i e f c o n t r o l law d e v e l o p e d f o r t h e S a t u r n V/Voyager w i t h i n e r t i a l p l a t f o r m o u t p u t s i n s t e a d of a c c e l e r o m e t e r o u t p u t s . Although incomplete, t h e s t u d y i n d i c a t e s t h a t i n e r t i a l p l a t form o u t p u t s c a n b e used t o d u p l i c a t e t h e p e r f o r m a n c e of t h e convent i o n a l l y implemented l o a d r e l i e f law. However, t h i s performance i s a c h i e v e d a t t h e e x p e n s e of c o m p l i c a t e d g a i n s c h e d u l e s , l a r g e g a i n s , a n d i n d i v i d u a l l o o p i n s t a b i l i t y ( a l t h o u g h t h e o v e r a l l performance i s stable). �The s e p a r a t i o n dynamics s t u d y h a s o n l y r e c e n t l y been i n i t i a t e d . E f f o r t s t o d a t e have b e e n a s s o c i a t e d w i t h d e t e r m i n a t i o n o f t h e p e r t i n e n t e q u a t i o n s of m o t i o n , p a r a m e t e r v a r i a t i o n s and p r o b a b i l i t y d i s t r i b u t i o n s , and c h a r a c t e r i s t i c s o f s e p a r a t i o n d e v i c e s . Numerical d a t a for the study a r e not yet available. (2) A n a l y t i c Design of V e h i c l e C o n t r o l Systems Objective: t e c h n i q u e s f o r 1i n e a r s y s tems. To i n v e s t i g a t e a n a l y t i c a l d e s i g n The a n a l y t i c d e s i g n t e c h n i q u e under s t u d y a p p e a r s t o work w e l l f o r v a r i o u s s e n s o r l o c a t i o n s ; however, i t a p p e a r s t h a t t h e f i l t e r s d e s i g n e d f o r one time p o i n t w i l l g e n e r a l l y n o t b e s u i t a b l e a t o t h e r t i m e p o i n t s . L i n e a r o p t i m a l c o n t r o l may b e u s e f u l i n r e l i e v i n g t h i s problem. The i n h e r e n t i n s e n s i t i v i t y o f l i n e a r o p t i m a l s y s t e m s may make i t p o s s i b l e t o choose f i l t e r c h a r a c t e r i s t i c s which w i l l p r o v i d e good performance o v e r a wide r a n g e of o p e r a t i n g c o n d i t i o n s . b. N o r t h r o p S c h e d u l e Order #32 (New) Objective: t o r y o p t i m i z a t i o n problems. To a p p l y f u n c t i o n a l a n a l y s i s t o t r a j e c - The proposed f u n c t i o n a l a n a l y s i s methods employed show promise o f s i m p l i f y i n g t h e s p l i t boundary v a l u e problem by a l l o w i n g a u x i l i a r y v a r i a b l e s t o b e i n t r o d u c e d . These v a r i a b l e s , i n t e g r a t e d a s i n g l e time from known i n i t i a l c o n d i t i o n s , y i e l d i n f o r m a t i o n on t h e i n i t i a l v a l u e s t o b e used f o r t h e Lagrange m u l t i p l i e r s . The u t i l i t y o f t h e t e c h n i q u e depends on convergence p r o p e r t i e s which must b e investigated computationally. c. Honeywell (NAS8-11206) (1) S a t u r n V/Voyager Load R e l i e f O b j e c t i v e : To d e v e l o p a n e f f e c t i v e l o a d r e l i e f c o n t r o l s y s tem f o r t h e S a t u r n ~ I ~ o y a g e r . A load r e l i e f c o n t r o l system has been designed f o r t h e S a t u r n VIVoyager which ( f o r t h e 95 p e r c e n t November s y n t h e t i c wind p r o f i l e ) r e s u l t s i n a t o t a l b e n d i n g moment of o n l y 70 p e r c e n t o f t h e a l l o w a b l e v a l u e a t t h e c r i t i c a l s t a t i o n . Parameter v a r i a t i o n s a r e n o t considered i n t h i s value. Terminal t r a j e c t o r y d i s p e r s i o n s a r e a b o u t 7 km, a l i t t l e o v e r t h r e e t i m e s as much a s t h o s e induced by a t t i t u d e control. �Current problems a r e i n t h e a r e a s of s l o s h s t a b i l i t y and r i g i d body g a i n margin. E f f o r t s w i l l be made t o a r r i v e a t s a t i s f a c t o r y s o l u t i o n s f o r t h e s e s i t u a t i o n s i n t h e coming month. (2) Development of T o l e r a n t C o n t r o l Systems O b j e c t i v e : To develop c o n t r o l l e r s which maximize t h e t o l e r a n c e t o v e h i c l e and environmental parameter v a r i a t i o n s . A n a l y s i s w i t h r i g i d body dynamics has developed a c a n d i d a t e system w i t h a d e q u a t e l y t o l e r a n t c h a r a c t e r i s t i c s over t h e f i r s t s t a g e f l i g h t . However, t h e a d d i t i o n of t h e v e h i c l e bending modes has produced t r a j e c t o r y r e g i o n s where d i f f e r e n t c o n t r o l charact e r i s t i c s a r e needed t o a c h i e v e t h e d e s i r e d t o l e r a n c e s . The c a n d i d a t e system i s being a d j u s t e d t o meet t h e new c o r r e l a t i o n s . d. North American A v i a t i o n A f u r t h e r e x t e n s i o n of t h e o r b i t a l t r a n s f e r work accomplished by t h e c o n t r a c t o r under NAS8-20238 has been r e q u e s t e d . (1) t h r e e This work w i l l involve e x t e n s i o n s t o . dimensional f i n i t e t h r u s t t r a n s f e r s between o r b i t s ; ( 2 ) a parameter s t u d y t o i l l u s t r a t e d i f f i c u l t o r l i m i t i n g c a s e s of t h e o r b i t a l t r a n s f e r scheme of p a r t (1) ; (3) t h e e x t e n s i o n of q u a s i - l i n e a r i z a t i o n t e c h niques t o t h e c a s e of f i n i t e burn time, r e s t r i c t e d three-body maneuvers, and t r a n s f e r s A Denbow f o r m u l a t i o n i n v o l v i n g s t a g i n g w i l l be included i n p a r t (3). . e. C o r n e l l A e r o n a u t i c a l Lab (NAS8-18054) O b j e c t i v e : To determine t h e f e a s i b i l i t y of a p p l y i n g l i n e a r optimal c o n t r o l t h e o r y t o t h e s y n t h e s i s of launch v e h i c l e cont r o l s y s tems . Work i s i n p r o g r e s s on a method of i n c o r p o r a t i n g a s e n s i t i v i t y measure i n t h e performance index s o a s t o reduce s e n s i t i v i t y of performance t o parameter v a r i a t i o n s . A major problem w i t h t h e curr e n t f o r m u l a t i o n i s t h a t , f o r a n n t h o r d e r system, each parameter being considered adds n h y p o t h e t i c a l s t a t e s t o t h e s y s tem and consequently r e q u i r e s n a d d i t i o n a l measurements. This problem might be reduced by u s i n g f i l t e r d e s i g n techniques t o approximate t h e "states:' b u t , even s o , t h e i n c r e a s e d o r d e r of t h e c o n t r o l l e d system would r e s u l t i n h i g h - o r d e r filters. �B. Astrodynamics Branch 1. I n t e r p l a n e t a r y Trans i t S t u d i e s (In-House) a . Work i s n e a r i n g completion on two double p r e c i s i o n , power s e r i e s i n t e g r a t i o n decks. One of t h e decks i n t e g r a t e s n-bodies w i t h interdepende n t g r a v i t a t i o n a l f i e l d s and c o n t a i n s a p o t e n t i a l f u n c t i o n f o r t h e c e n t r a l body ( u s u a l l y t h e e a r t h ) which i n c l u d e s t h e second, t h i r d , and f o u r t h s p h e r i c a l harmonics. I n p u t t o and o u t p u t from t h i s deck can be i n most any one of t h e commonly used C a r t e s i a n c o o r d i n a t e systems. An i s o l a t i o n r o u t i n e capable of computing t h e i n i t i a l v e l o c i t y a s a f u n c t i o n of t h e f l i g h t time and t a r g e t p l a n e t a r r i v a l parameters i s p r e s e n t l y being added t o t h e deck; a n d , o u t p u t of a s s o c i a t e d c o n i c elements i s a l s o being implemented. The o t h e r deck i n t e g r a t e s t h r e e b o d i e s plus t h e probe and i s s i m i l a r t o t h e one d e s c r i b e d above e x c e p t t h a t t h i s deck c o n t a i n s thrust capability. I n t h i s deck, t h e t h r u s t i n g a n g l e may be s p e c i f i e d o r computed by t h e deck. I f computed by t h e deck, t h r u s t can be d i r e c t e d p e r p e n d i c u l a r t o t h e probe-sun l i n e o r a l o n g t h e v e l o c . i t y v e c t o r . The t h r u s t and mass flow r a t e a r e n o t c o n s t a n t , b u t d e c r e a s e a s a f u n c t i o n of r ' l o 7 (where r i s t h e probe-sun d i s t a n c e ) . The Research P r o j e c t s Laboratory h a s i n d i c a t e d t h a t t h i s should g i v e a good r e p r e s e n t a t i o n of t h e d e c r e a s e i n t h e power o u t p u t of s o l a r c e l l s . Isp i s cons i d e r e d a cons t a n t . b. An i n i t i a l f a m i l i a r i z a t i o n s t u d y of t h e work done by and f o r J P L i n t h e phase A and phase B s t u d i e s of Voyager has been comp l e t e d , and a comprehensive, in-depth survey of t h i s and r e l a t e d m a t e r i a l i s now underway. c , I n s u p p o r t of a f e a s i b i l i t y s t u d y of s o l a r e l e c t r i c p r o p u l s i o n f o r i n t e r p l a n e t a r y v e h i c l e s being sponsored by t h e Research P r o j e c t s Laboratory, a program designed t o i n v e s t i g a t e t h e e f f e c t s of o b l a t e n e s s on a s a t e l l i t e i n a Martian o r b i t was formulated f o r use on S t u d i e s using t h i s program have i n d i c a t e d that, t h e IBM 1130 computer. i f the c o r r e c t i n c l i n a t i o n i s used, a s a t e l l i t e w i l l remain f o r an extended p e r i o d of time i n a sun shychronous o r b i t of Mars a t a l t i t u d e s r a n g i n g from 1 , 0 0 0 t o 5,500 k i l o m e t e r s . I n a d d i t i o n , t h e beginning and ending d a t e s of t h e M a r t i a n seasons f o r t h e y e a r s from 1970 t o 1980 have been determined. �d. I n s u p p o r t of t h e Mars S u r f a c e Sample and Return Probe (MSSR) s t u d i e s being d i r e c t e d by t h e Advanced S t u d i e s O f f i c e , a deck was w r i t t e n f o r t h e IBM 1130 computer t o examine t h e v a r i o u s parameters associated with hyperbolic o r b i t a l t r a n s f e r s i n the g r a v i t a t i o n a l f i e l d of Wars. Also, a p a r a m e t r i c a n a l y s i s of t h e impulsive v e l o c i t y r e q u i r e ments f o r launching a probe from a f l y b y s p a c e c r a f t a t some time b e f o r e p e r i a p s i s s o t h a t t h e probe a r r i v e s a t Mars b e f o r e t h e f l y b y s p a c e c r a f t In addition, an analysis i s a r r i v e s a t p e r i a p s i s i s being conducted. being made of e n t r y a n g l e and v e l o c i t y c o n d i t i o n s of t h e probe a s i t e n t e r s t h e Martian atmosphere plus a s t u d y of t h e communication d i s t a n c e s between t h e s p a c e c r a f t and t h e probe from time of launch from t h e s p a c e c r a f t t o t h e p r o b e ' s impact w i t h Mars. The d a t a n e c e s s a r y f o r t h e s e a n a l y s e s have been o b t a i n e d . 2. Support C o n t r a c t a. Cislunar Orbit Studies The s t u d y t o determine t h e v e l o c i t y requirements f o r m a i n t a i n i n g o r b i t s t a b i l i t y i n c i s l u n a r s p a c e over long time i n t e r v a l s has been completed, and w i l l be documented soon. b. Interplanetary Transit Studies Work is c o n t i n u i n g on t h e problem of adding powered f l i g h t c a p a b i l i t y t o t h e Modified Marshall interplanetary Conic Tra ject o r y Program. C. Guidance Theory Branch 1. Support C o n t r a c t S t u d i e s a. Low T h r u s t Guidance R e s u l t s show t h a t a n a d a p t i v e d e l t a minimum guidance scheme does not s a t i s f a c t o r i l y c o n t r o l t h e range a n g l e a t i n j e c t i o n i f p e r t u r b a t i o n s occur d u r i n g t h e s p i r a l phase of a low t h r u s t t r a j e c t o r y . A new technique was developed which uses t a n g e n t i a l t h r u s t u n t i l t h e energy approaches w i t h i n LY~ of t h e d e s i r e d l e v e l . AE is chosen such t h a t i t can be gained i n l e s s than one r e v o l u t i o n of t h e s p i r a l phase. A 90-degree a n g l e of a t t a c k (no energy b u i l d u p ) i s used d u r i n g p a r t of t h e l a s t r e v o l u t i o n i n o r d e r t o c o n t r o l t h e range a n g l e a t i n j e c t i o n . A t t h e proper time t h e a n g l e of a t t a c k i s reduced back t o z e r o u n t i l escape. �b. Power S e r i e s S o l u t i o n f o r I n i t i a l Lagrange M u l t i p l i e r s Work h a s c o n t i n u e d on a s e r i e s s o l u t i o n f o r t h e i n i t i a l L a g r a n g i a n m u l t i p l i e r s f o r optimum t r a n s f e r from a f i x e d p o i n t t o a n ellipse. The s i x t e r m i n a l c o n d i t i o n e q u a t i o n s h a v e b e e n expanded i n T a y l o r s e r i e s of o r d e r f o u r , and programs have b e e n w r i t t e n f o r e a c h s e r i e s t o n u m e r i c a l l y t e s t t h e i r a c c u r a c y u s i n g d a t a from a numerically.*' integrated calculus of v a r i a t i o n s trajectory. Debugging and f i n a l checko u t o f t h e s e t e s t programs have c o n t i n u e d . c. Voyager P r o j e c t S u p p o r t S t u d i e s A new nominal S a t u r n V / ~ o y a g e r t r a j e c t o r y was computed u s i n g new aerodynamic and w e i g h t d a t a . A s t u d y h a s b e e n i n i t i a t e d t o d e t e r m i n e t h e performance of t h e I G M a p p l i e d t o t h e S a t u r n V/Voyager m i s s i o n . An IGM d e c k i s now b e i n g p r e p a r e d f o r u s e i n t h i s s t u d y . 2. In-House S t u d i e s a . The c o d i n g n e c e s s a r y t o i n c l u d e c o r n e r c o n d i t i o n s i n t o t h e program t o compute o p t i m a l o r b i t t r a n s f e r s w i t h o p t i m a l c o a s t i n g t i m e s h a s been completed. The program i s b e i n g checked o u t and t h e n u m e r i c a l d i f f i c u l t i e s i n h e r e n t i n t h i s t y p e o f problem a r e b e i n g investigated. b. During t h i s r e p o r t i n g p e r i o d , a s t u d y of t h e b r a k i n g p h a s e i n t o c a p t u r e o r b i t a b o u t Mars f o r t h e Mars P h o t o O r b i t e r M i s s i o n , r e q u e s t e d by R e s e a r c h P r o j e c t s L a b o r a t o r y , was i n i t i a t e d and f i n i s h e d . S e v e r a l a p p r o a c h a l t i t u d e s were used a l o n g w i t h s e v e r a l d i f f e r e n t C 3 v a l u e s t o i n v e s t i g a t e t h e c a p t u r e maneuver a b o u t Mars. c . A s u r v e y of g u i d a n c e c o n c e p t s whic'h could p o s s i b l y b e used f o r t h e "Mars S u r f a c e Sample and R e t u r n P r o b e Mission" h a s b e e n conducted. R e s u l t s o f t h i s s t u d y w i l l b e f o r w a r d e d t o R-AERO-X i n the near future. 3. Contracts a. Boeing - Rendezvous Guidance During t h i s r e p o r t i n g p e r i o d , i t was shown t h a t t h e c o r r e c t i v e scheme f o r r e l a t i v e g u i d a n c e h a s t h e c a p a b i l i t y of hand1 i n g t h r u s t v a r i a t i o n ofJ+3 percent. A switching f u n c t i o n h a s been developed which p r e d i c t s e n g i n e i g n i t i o n t i m e f o r t h e f i n a l s t a g e . The i d e a employed i n t h e r e l a t i v e g u i d a n c e scheme was e x t e n d e d t o f o r m u l a t e t h e switching function. Programming i s complete on t h e i t e r a t i v e g u i d a n c e scheme f o r a b u r n - c o a s t - b u r n t r a j e c t o r y and c h e c k o u t i s underway. �b. Lockheed - Rendezvous Guidance A f i r s t burn p o l i c y ("time-to-go" and d i r e c t i o n ) is being formulated a s a f u n c t i o n of t h e system s t a t e , i . e . , of t h e s e p a r a t i o n a n g l e , i n t e r c e p t e r r a d i u s , v e l o c i t y and f l i g h t p a t h a n g l e . The c o n t r o l law i s g i v e n by a s e t of f o u r t r a n s c e n d e n t a l a l g e b r a i c e q u a t i o n s which a r e s o l v e d f o r time-to-go of t h e f i r s t burn and t h e t h r u s t d i r e c t i o n . A s a f i r s t approximation, t h e assumption of c o n s t a n t mass has been made. F u r t h e r m o d i f i c a t i o n w i l l i n c l u d e t h e case of a v a r y i n g mass. c. General P r e c i s i o n A computer program f o r a p p l y i n g quasi-optimum feedback guidance f o r t h e h e l i o c e n t r i c phase of t h e low t h r u s t problem has been completed. A few numerical checks a r e b e i n g made t o determine t h e e f f e c t i v e n e s s and a c c u r a c y of t h i s program b e f o r e c o n t i n u i n g w i t h t h e p l a n e t - c e n t e r e d phase and t h e matching problem f o r t h e d i f f e r e n t phases. d. Vanderbil t U n i v e r s i t y E f f o r t i s being continued on developing s u f f i c i e n c y c o n d i t i o n s f o r m u l t i s t a g e c o n t r o l problems and on determining sequences of sub-optimal s o l u t i o n tending toward a n optimal s o l u t i o n . D. S c i e n t i f i c Advisory Committee 1. A paper, " I n t e r p r e t a t i o n of Liapunov S t a b i l i t y Regions, I ' has been a c c e p t e d f o r p u b l i c a t i o n by t h e AIAA J o u r n a l . 2. Work is c o n t i n u i n g on e x i s t e n c e and uniqueness theorems of o r d i n a r y d i f f e r e n t i a l e q u a t i o n s and t h e r e l a t i o n s between t h e s e theorems and those r e l a t i n g t o p e r i o d i c s o l u t i o n b e h a v i o r . A r e c e n t paper by Moyer c o n t a i n s a theorem which i n c l u d e s a l l known uniqueness theorems. A n o t e i s b e i n g prepared showing t h a t t h i s r e s u l t i s contained i n papers by Okamura p u b l i s h e d i n t h e 1 9 4 0 ' s . 3. Hamil t o n i a n Sys tem S t a b i l i t y The s t a b l e l i b r a t i o n p o i n t s of t h e r e s t r i c t e d three-body problem a r e being i n v e s t i g a t e d by u s i n g Liapunov t h e o r y . R e s u l t s o b t a i n e d i n d i c a t e t h a t q u a r t i c Liapunov f u n c t i o n s can be reduced t o q u a d r a t i c f o r determining s u f f i c i e n t c o n d i t i o n s f o r s t a b i l i t y . �4. The new r e s u l t s obtained f o r t h e l ' C o n t r o l l a b i l i t y of S i n g l e - I n p u t Systems" s t u d y w i l l be published soon a s a NASA Technical Note. 5. C o n t r o l l a b i l i t y of General M u l t i - I n p u t L i n e a r Systems Work i n t h i s a r e a has been c o n c e n t r a t e d on s o l v i n g t h e f o l l o w i n g problems: (a) Given a g e n e r a l l i n e a r s y s tem, determine t h e minimal number of independent i n p u t f u n c t i o n s r e q u i r e d f o r t h e complete c o n t r o l l a b i l i t y of t h e system. (b) Having determined t h e minimal number of i n p u t f u n c t i o n s , determine t h e i n p u t coding-ma t r i x . The f i r s t problem has been completely s o l v e d and a p r a c t i c a l method o b t a i n e d which s p e c i f i e s t h e corresponding coding-matrix of problem (b). These r e s u l t s a r e being prepared f o r p u b l i c a t i o n . 6. Q u a l i t a t i v e Methods f o r Determininp t h e Behavior of T r a j e c t o r i e s of Nonlinear D i f f e r e n t i a l Equations over a F i n i t e Time I n t e r v a l While t h i s s t u d y i s i n i t s e a r l y s t a g e s , s e v e r a l new r e s u l t s have a l r e a d y been obtained which i n d i c a t e t h e approach t a k e n should l e a d t o u s e f u l methods. 7. Contracts a. Brown U n i v e r s i t y (NAS8-11264) Objective: dynamical systems. Research i n t h e g e n e r a l a r e a of n o n l i n e a r I n f a n t e and Slemrod have a p p l i e d t h e d i r e c t method of Liapunov t o a c l a s s of problems of n o n l i n e a r p a r t i a l d i f f e r e n t i a l e q u a t i o n s of the same n a t u r e a s t h e beam e q u a t i o n , and they have o b t a i n e d s t a b i l i t y r e s u l t s t h a t g e n e r a l i z e t h o s e o b t a i n e d by Morchan. H a l l and I n f a n t e a r e c o n t i n u i n g t h e i r work on t h e e x i s t e n c e of p e r i o d i c s o l u t i o n s of weakly n o n l i n e a r s y s tems of p a r t i a l d i f f e r e n t i a l e q u a t i o n s of t h e h y p e r b o l i c type. M i l l e r has been working on some r e s u l t s i n t h e q u a n t i t a t i v e t h e o r y of i n t e g r a l e q u a t i o n s . This work c o n s i s t s p r e s e n t l y of checking t h e d e t a i l s of t h e proof t h a t t h o s e e q u a t i o n s can be viewed a s dynamical systems. He i s a l s o s e a r c h i n g f o r f u r t h e r examples t o which t h i s theory a p p l i e s . �M i l l e r i s a l s o s t u d y i n g some problems i n p a r t i a l d i f f e r e n t i a l e q u a t i o n s . It appears t h a t one can g e t weak s o l u t i o n s of n o n l i n e a r h y p e r b o l i c c o n s e r v a t i o n laws using a n analog of an o r d i n a r y It i s hoped t h a t t h e s o l u t i o n s d i f f e r e n t i a l e q u a t i o n s technique. o b t a i n e d i n t h i s manner w i l l be t h e p h y s i c a l l y i n t e r e s t i n g ones. Weiss i s c o n t i n u i n g h i s work on t h e t h e o r y of m a t r o i d s and on c o n d i t i o n s f o r c o n t r o l l a b i l i t y of d e l a y - d i f f e r e n t i a l e q u a t i o n s . The work of Minty on t h i s s u b j e c t i s being i n t e g r a t e d w i t h e a r l i e r work of Idhitney and T a t t e , and t h e main theorems of Minty have been reproved s t a r t i n g w i t h t h e more u s u a l axioms d e f i n i n g m a t r o i d . The connections between T a t t e ' s work and t h e problem of e x i s t e n c e and uniqueness of s o l u t i o n s t o e l e c t r i c a l network e q u a t i o n s a r e b e i n g worked o u t . F u r t h e r r e s u l t s on c o n t r o l l a b i l i t y c o n d i t i o n s f o r d e l a y - d i f f e r e n t i a l e q u a t i o n s beyond those r e p o r t e d on i n e a r l i e r p r o g r e s s r e p o r t s a r e under development. Meyer has been working on t h e problem of c h a r a c t e r i z i n g s t r u c t u r a l l y s t a b l e systems by means of a g l o b a l Liapunov f u n c t i o n . I n g e n e r a l , a s t r u c t u r a l l y s t a b l e system i s a system of d i f f e r e n t i a l e q u a t i o n s whose g l o b a l phase p o r t r a i t does n o t change under s m a l l pert u r b a t i o n s . Meyer has e s t a b l i s h e d some l o c a l lemmas t h a t w i l l be needed f o r t h e g l o b a l c h a r a c t e r i z a t i o n . ,. b. General P r e c i s i o n (NAS8-20062) O b j e c t i v e : I n v e s t i g a t e s t a b i l i t y p r o p e r t i e s of p e r i o d i c and alrnos t p e r i o d i c o r b i t s . A computer program which w i l l normalize a timedependent Hamiltonian i s p r e s e n t l y being prepared. The development of t h i s program i s d i v i d e d i n t o two phases: second o r d e r n o r m a l i z a t i o n , and h i g h e r o r d e r n o r m a l i z a t i o n s The r o u t i n e f o r hig'her o r d e r normal i z a t i o n s i s n e a r l y complete. Emphasis w i l l t h e n t u r n t o t h e second o r d e r normal i z a t i o n which w i l l i n c l u d e t h e symbolic r e p r e s e n t a t i o n of t h e s o l u t i o n of a system of l i n e a r d i f f e r e n t i a l e q u a t i o n s w i t h p e r i o d i c coefficients . . c. Grumnan A i r c r a f t Engineering Corp (NASB-20306) Objective: l i n e a r dynamical s y s terns. Determine s t a b i l i t y domains f o r non- During October and November, add i t i o n a l improvements were made i n t h e computer program f o r e s t i m a t i n g t h e domain of a t t r a c t i o n ( s t a b i l i t y domain) of t h e e q u i l i b r i u m s o l u t i o n of n o n l i n e a r dynamical �systems. The second q u a r t e r l y p r o g r e s s r e p o r t has been i s s u e d . Part i c u l a r items d i s c u s s e d i n t h e r e p o r t a r e a s follows: (1) Some e x p e r i mental r e s u l t s o b t a i n e d by means of t h e procedures developed d u r i n g t h e f i r s t q u a r t e r ; (2) r e f o r m u l a t i o n of t h e procedure t o avoid comput a t i o n a l d i f f i c u l t i e s encountered d u r i n g t h e experiments; ( 3 ) development of a p a r a m e t e r i z a t i o n of t h e s e t of p o s i t i v e d e f i n i t e n x n m a t r i c e s ; and (4) a n a l y s i s of a s y s tem w i t h time-dependent closed-loop guidance. d. Drexel I n s t i t u t e of Technology (NAS8-20347) Objective: Research i n methods of g e n e r a t i n g Liapunov functions. During t h e c u r r e n t r e p o r t i n g p e r i o d , s e v e r a l l i n e s of i n v e s t i g a t i o n were followed. (1) E v a l u a t i o n of t h e work done by D r . J e s s e Clay d u r i n g t h e s u m e r of 1966 (see monthly r e p o r t s f o r J u l y and August). It was decided t h a t t h i s l i n e of i n v e s t i g a t i o n is f a r t o o g e n e r a l t o produce any p r a c t i c a l r e s u l t s a t t h i s s t a g e of our knowledge. Perhaps i t would be f r u i t f u l t o r e t u r n t o t h i s work a f t e r g a i n i n g more d e t a i l e d knowledge of some p a r t i c u l a r Liapunov f u n c t i o n s . (2) An a t t e m p t was made t o f i n d some s o r t of connect i o n between some of t h e v a r i o u s methods of g e n e r a t i n g Liapunov funct i o n s . S p e c i f i c a l l y , examples were chosen (from among t h e worked examples i n R. rake's r e p o r t ) i n which Liapunov f u n c t i o n s were found by t h e v a r i a b l e g r a d i e n t t e c h n i q u e , and an a t t e m p t was made t o o b t a i n Liapunov f u n c t i o n s by t h e use of one o r a n o t h e r of t h e i n t e g r a t i o n by p a r t s techniques and by t h e use of I n f a n t e ' s i n t e g r a l method. Fair s u c c e s s was achieved w i t h autonomous systems, 5 = f ( z ) , when t h e o r d e r of the s y s tem was two o r t h r e e and t h e f i ( s ) were polynomials i n t h e xi's. But no s u c c e s s a t a l l f o r h i g h e r o r d e r systems o r f o r more comp l i c a t e d forms of t h e f i ( z ) % . The s u c c e s s of any g i v e n method a p p e a r e d , from our e f f o r t s , t o depend most h e a v i l y on t h e i n g e n u i t y of t h e i n v e s t i g a t o r and v e r y l i t t l e on t h e form of t h e system of e q u a t i o n s a t hand. The v a r i o u s methods t r i e d seem t o be i s o l a t e d from each o t h e r i n t h e s e n s e t h a t i t i s impossible t o t e l l a p r i o r i which method i s l i k e l y t o b e s u c c e s s f u l f o r a g i v e n system of e q u a t i o n s . e. Lockheed M i s s i l e s and Space Company, H u n t s v i l l e Research and Engineering Center (NAS8-20323) Objective: p e r i o d i c motions. Perform r e s e a r c h i n t h e s t a b i l i t y of �During October and November t h e Recurrence Theorem comprising Chapter 30 of S i e g e l and t h e mapping theorem of Moser were s t u d i e d . I n the former we proceed, a s u s u a l , from a system of d i f feren t i a l equations i n which t h e f u n c t i o n s f k ( x ) need n o t be r e g u l a r b u t mus: be d i f f e r e n t i a b l e i n t h e r e a l domain, R , considered. A p p l i c a t i o n s t o t h e r e s t r i c t e d t h r e e body problem and t o t h e n-body problem a r e g i v e n i n S i e g e l . Siege1 men-cions t h a t t h e method i s f r a u g h t w i t h problems which appear d i f f i c u l t even compared t o o t h e r methods of determining s t a b i l i t y . However, s i n c e S i e g e l f s t e x t was p u b l i s h e d , two n o t a b l e s t e p s have been made, one by Arnold and t h e o t h e r by Moser. That of Moser h a s been b r i e f l y s t u d i e d and concerns t h e e x i s t e n c e of i n v a r i a n t curves i n a n a r e a - p r e s e r v i n g mapping. We have s e e n t h z t trle e l l i p t i c c a s e of t h e a r e a - p r e s e r v i n g mapping i s , i n t h e n ~ r m a iform, a t w i s t mapping*and hence a l l c i r c l e s c e n t e r e d a t t h e o r i g i n a r e i n v a r i a n t . Now Moser c o n s i d e r s a p e r t u r b e d mapping and g i v e s suf f i c i e n t c o n d i t i o n s f o r t h i s p e r t u r b e d mapping t o have i n v a r i a n t curves n e a r c o n c e n t r i c c i r c l e s . We know t h a t , i n a s u f f i c i e n t l y small n e l g k borhood a n e l l i p t i c type mapping can be bought a r b i t r a r i l y c i o s : ? t o a t w i s t mapping by a convergent t r a n s f o r m a t i o n s o t'mt we can conside: i t a p e r t u r b a t i o n of a t w i s t mapping. Moser then continues ic r e c l ~ c ~ t h e s t a b i l i t y problem t o one of f i n d i n g two numbers, Z, 3 , and shcijs s t a b i l i t y f o r (3 # 0. This paper w i l l s t i l l be under s t u d y d u r i n g December and w i l l be commented on more f u l l y i n a l a t e r p r o g r e s s r e p o r t . - f. The U n i v e r s i t y of Texas (NAS8-18120) Objective: guidance s y s tems . Study of s ~ a b i l . i t yand sensitivity of The s t u d y has been d i v i d e d e s s e n t i a l l y i n t o chred parts: ( a ) A comprehensive s t u d y i s being made of t h e meaning of s e n s i t i v i t y a s r e l a t e d t o c o n t r o l systems. This s t u d y has r e c e n c l y produced d e f i n i t i o n s of s e n s i t i v i t y , p r a c t i c a l i t y and f e a s i b i l i t y f ~ r c o n t r o l systems f o r b o t h l a r g e and small v a r i a t i o n s i n s e l e c t e d parame t e r s . A complete formalism i s expected t o be e s t a b l i s h e d i n t h e ned, future. (b) The second a r e a of work has been i n t h e development of c r i t e r i a of s t a b i l i t y d e t e r m i n a t i o n of coupled suboptimal nonl i n e a r systems. The aim i s t o o b t a i n methods of a n a l y s i s by means of which i t can be determined how t h e coupling of simple sub-systems w i l l d f i c ~ c �t h e s t a b i l i t y of t h e system t o w h i c h they belong. ( c ) The t h i r d a r e a of work i s i n e s t a b l i s h i n g n e c e s s a r y a n a l y s i s and c o m p u t a t i o n a l p r o c e d u r e s f o r s t u d y i n g t h e s t a b i l i t y o f g u i d a n c e s y s t e m s and t h e o p t i m i z a t i o n problems a s s o c i a t e d w i t h A p o l l o - t y p e m i s s i o n s . The a t t e m p t w i l l b e made t o e s t a b l i s h methods whereby t r u l y optimum t r a j e c t o r i e s could b e obtained f o r Apollo-type lunar t r a j e c t o r i e s . VI. AEROPHYSICS DIVISION A. F l u i d Mechanics R e s e a r c h O f f i c e 1. O r b i t a l Gauge Response I n O c t o b e r , M r . B a l l a n c e met w i t h Goddard Space F l i g h t C e n t e r p e r s o n n e l t o d i s c u s s t h e i n - s i t e measurements of t h e u p p e r a t m o s p h e r e by d e n s i t y and mass s p e c t r o m e t e r gauges of E x p l o r e r X V I I and X X X I I . M r . B a l l a n c e p o i n t e d o u t t r e n d s i n t h e i r p u b l i s h e d d a t a w h i c h h e c o n s i d e r e d t o be a n obvious i n d i c a t i o n of t h e s o u r c e o f e r r o r i n t h e measurements, and d e m o n s t r a t e d some p r e l i m i n a r y r e s u l t s o f a Monte C a r l o a n a l y s i s made of t h e Redhead gauge which c o r r e l a t e d v e r y w e l l w i t h t h e f l i g h t d a t a . The Goddard p e r s o n n e l d i d n o t a c c e p t t h e a r g u ment i n i t s e n t i r e t y , b u t d i d a g r e e t h a t i t seemed r e a s o n a b l e . They r e q u e s t e d t h a t a p a r a m e t r i c s t u d y o f b o t h t h e Redhead d e n s i t y gauge and t h e B a y a r d - A l p e r t d e n s i t y gauge b e made. It a p p e a r e d t o be e a s i e r and q u i c k e r t o m o d i f y t h e d e c k s and o b t a i n t h e d a t a h e r e a t M a r s h a l l t h a n t o t r y t o t r a i n t h e Goddard p e r s o n n e l i n t h e l o g i c and o p e r a t i o n of t h e program. A c c o r d i n g l y , a program o f a p p r o x i m a t e l y 160 h o u r s of CDC 3200 time was e s t a b l i s h e d . Mr. Ballance monitors t h e d a t a a s they a r e o b t a i n e d , t o v e r i f y p r o p e r o p e r a t i o n , and f o r w a r d s t h e r e s u l t s t o Goddard f o r a n a l y s i s . About 85 h o u r s of t h e program i s c o m p l e t e . A summary r e p o r t of t h e d a t a i s b e i n g p r e p a r e d f o r o u r r e c o r d s . 2. Sounding Rocket Gauge Response A program s i m i l a r t o t h a t b e i n g conducted f o r Goddard was done l a s t s p r i n g and summer on t h e mass s p e c t r o m e t e r b e i n g used on t h e MUMP ( M a r s h a l l Upper Atmosphere Measuring P r o b e ) . A r e p o r t i s b e i n g p r e p a r e d showing t h e r e s u l t s . It i s i n t e r e s t i n g t o o b s e r v e t h a t , s i n c e i t was d i f f i c u l t t o program t h e e x a c t p h y s i c a l geometry of t h e p r o b e , a s imp1 i f i e d g e o m e t r y , which t h e U n i v e r s i t y of Michigan i s now a d o p t i n g i n t o t h e d e s i g n o f t h e s e n s o r , was u s e d . 3. O r b i t a l Aerodynamic C a l c u l a t i o n s R e s e a r c h The commonly a c c e p t e d method f o r aerodynamic c a l c u l a t i o n s f o r a n o r b i t i n g s y s tem i s t h a t t h e l e a d i n g e l e m e n t c a s t s i t s "shadow" o n t o a n y t r a i l i n g e l e m e n t s and removes t h a t a r e a from c o n t r i b u t i o n t o �the calculations. I n a Monte C a r l o program a n a l y z i n g two c o a x i a l d i s c s , t h e s e a s s u m p t i o n s a r e b e i n g examined, a s w e l l as a n y m u l t i p l e c o l l i s i o n e f f e c t s w i t h r e f l e c t i n g molecules. Some v e r y i n t e r e s t i n g r e s u l t s , which show t h a t p r e s e n t a s s u m p t i o n s a r e s i g n i f i c a n t l y i n e r r o r , a r e being obtained. For p r e s e n t e n g i n e e r i n g c a l c u l a t i o n s f o r t h e S a t u r n o r b i t i n g s y s t e m no change i s p r e s e n t l y p l a n n e d ; however, t h e computer d e c k s a r e b e i n g m o d i f i e d s o t h a t t h e "shadowing" f a c t o r s can b e machinec a l c u l a t e d r a t h e r t h a n h a n d - c a l c u l a t e d a s done i n t h e p a s t . T h i s i s made p o s s i b l e by i n c o r p o r a t i n g t h e c o n c e p t s of r a d i a t i o n h e a t t r a n s f e r v i e w f a c t o r c a l c u l a t i o n s i n t o t h e program. B. M e c h a n i c a l Design O f f i c e A s t u d y model of t h e G r a v i t y S i m u l a t i o n Workbench i s b e i n g b u i l t , f o r u s e i n e x p e r i m e n t a l l y d e t e r m i n i n g t h e optimum work s u r f a c e and i n l e t c o n f i g u r a t i o n , s c r e e n s i z e s , e t c . D e s i g n of a s i n g l e component m i c r o f o r c e b a l a n c e f o r u s e i n t h e Low D e n s i t y Chamber h a s p r o g r e s s e d beyond t h e i n i t i a l c o n c e p t stage. Work h a s c o n t i n u e d i n s u p p o r t of t h e d e s i g n of t h e High Reynolds Number F a c i l i t y w i t h p a r t i c u l a r emphasis p l a c e d on t h e diaphragm c u t t e r a s s e m b l y . The f o l l o w i n g is a p a r t i a l l i s t o f a d d i t i o n a l p r o j e c t s and their current status: Viscous C r o s s Flow F o r c e Model and B a l a n c e Delivered. Updated S a t u r n V F o r c e Model - 14" W.T. M o d i f i c a t i o n o f Nozzles f o r S.T.S. - - - 14" W.T. - Delivered. 14" W.T. P l e x i g l a s s Models f o r C r o s s Beam i n S.T.S. Delivered. F i n and Asymmetric Body and B a l a n c e s t ion. - - - Delivered. 14" W.T. 14" W.T. - Sidewall-Mounted I n n e r s t a g e Ring Model and B a l a n c e 14" W.T. - F a b r i c a t i o n . - Fabrica- - Updated S a t u r n IB Tank Loads F o r c e Model and B a l a n c e 14" W. T. - D r a f t i n g completed ( f a b r i c a t i o n c a n c e l l e d ) . �8' O.D. Vacuum Exhaust Plenum b e c a u s e of l a c k of f u n d s ) . - D r a f t i n g (holding P e r f o r a t e d F l o o r and C e i l i n g Assembly, T.T.S. 14" W. T. Fabrication. - - P r e s s u r e Models f o r Cross Beam i n S.T.S. Fabrication S a t u r n I B Thin S k i n Heat T r a n s f e r Model Base H e a t i n g Model C. - IBFF - - - 14" W.T. JPL - Des i g n . Fabrication. Aerodynamic Design Branch 1. SaturnV a . A p o l l o / S a t u r n V s t a t i c aerodynamic l o c a l l o a d d i s t r i b u t i o n s were d e f i n e d a t Mach numbers of 0, 0 . 5 , 4.0 and 7.0 f o r 6, 8 , 1 0 , 1 2 , 1 4 and 1 6 d e g r e e s a n g l e of a t t a c k by e x t r a p o l a t i n g e x i s t i n g S a t u r n V aerodynamic d e s i g n c r i t e r i a . These d a t a , which were d e f i n e d by TBC i n C o o r d i n a t i o n S h e e t No. AT-H-027, e x t e n d t h e p r e s e n t d e s i g n The Boeing document i s b e i n g p u b l i s h e d c r i t e r i a i n NASA TM X-53517. a s d e s i g n c r i t e r i a i n O f f i c e Memorandum R-AERO-AD-66-52. b. The Boeing Company h a s r e c e n t l y completed a n i n - f l i g h t v e n t i n g a n a l y s i s of t h e major compartments on t h e S-IC s t a g e . I n t e r n a l p r e s s u r e h i s t o r i e s have been g e n e r a t e d f o r t h e b a s e compartment, t h e i n t e r t a n k compartment, and t h e S-IC/S-I1 i n t e r s t a g e compartments. These d a t a a r e b e i n g reviewed by MSFC f o r a p p r o v a l as d e s i g n d a t a . c. The c o n t r o l f a c t o r s and v a r i a t i o n a l a n a l y s i s f o r A p o l l o S a t u r n 502 w i l l be a v a i l a b l e by J a n u a r y 1967. The d a t a a r e b e i n g s u p p l i e d by t h e Boeing Company f o r d i s t r i b u t i o n by R-AERO-AD. d. Aerodynamic h i n g e moments f o r A p o l l o / S a t u r n V S-IC e n g i n e were d e f i n e d f o r each e n g i n e a c t u a t o r a t Mach numbers from 0 . 5 t o 3.5 f o r a n g l e s of a t t a c k from 0 t o 15 d e g r e e s , e n g i n e d e f l e c t i o n s from 0 t o 4 d e g r e e s , and v e l o c i t y r o l l a n g l e s of 0 t o 45 d e g r e e s . These d a t a a r e b a s e d on t h e h i n g e moment t e s t (AD-3-64) conducted i n t h e Lewis R e s e a r c h c e n t e r ' s 1 0 x 1 0 - f o o t s u p e r s o n i c wind t u n n e l and 8 x 6 - f o o t t r a n s o n i c wind t u n n e l . These d a t a , which were d e f i n e d by TBC i n C o o r d i n a t i o n S h e e t No. AT-H-016, a r e b e i n g e s t a b l i s h e d a s d e s i g n c r i t e r i a i n a n R-AERO-AD o f f i c e memorandum t o be pub1 i s h e d i n t h e n e a r f u t u r e . Hinge moments f o r e a c h v e h i c l e w i l l be d e f i n e d by TBC based on t h i s document and t r a j e c t o r y and c o n t r o l s t u d i e s f o r t h e particular vehicle. �e . The aerodynamic c h a r a c t e r i s t i c s of t h e S a t u r n V a b o r t c o n f i g u r a t i o n a r e b e i n g d e t e r m i n e d . V e h i c l e s t a b i l i t y and d r a g have been d e f i n e d , and l o c a l normal f o r c e d i s t r i b u t i o n s a r e b e i n g b a l a n c e d w i t h s t a b i l i t y d a t a . The d a t a from t h i s a n a l y s i s w i l l cover t h e same f l i g h t c o n d i t i o n s a s t h o s e i n TM X-53517 f o r S a t u r n V. The a b o r t a e r o dynamics w i l l s o o n b e p u b l i s h e d i n a n o f f i c e memorandum. . f P r e l i m i n a r y aerodynamics f o r t h e S a t u r n ~ / ~ o y a g e r (54' s h r o u d l e n g t h ) a r e b e i n g p r e p a r e d . I n a d d i t i o n t o t o t a l a e r o dynamics, d i s t r i b u t e d aerodynamics w i l l b e p r e s e n t e d f o r Mach numbers o f 1 . 0 0 , 1.20, 1 . 4 3 , 1.70 and 2.00 f o r a n g l e s of a t t a c k up t o 15 d e g r e e s . These d a t a w i l l soon be p u b l i s h e d i n a n o f f i c e memorandum. A wind t u n n e l t e s t h a s b e e n conducted i n t h e MSFC 1 4 - i n c h T r i s o n i c Wind Tunnel t o d e t e r m i n e t h e s t a t i c s t a b i l i t y and a x i a l f o r c e c h a r a c t e r i s t i c s of t h e S a t u r n V Voyager l a u n c h v e h i c l e w i t h a 4 5 - f o o t Voyager payload e n v e l o p e . A 0.3366 p e r c e n t s c a l e model was t e s t e d a t Mach numbers from 0.50 t o 5.00 and a t a n g l e s of a t t a c k up t o 1 6 d e g r e e s . The d a t a a r e b e i n g i n c o r p o r a t e d i n a n aerodynamic d e s i g n memorandum. g. S a t u r n V/Voyager I n - F l i g h t Venting: P r e l i m i n a r y i n t e r n a l p r e s s u r e time h i s t o r i e s a r e b e i n g d e f i n e d f o r t h e f i v e i n t e r i o r compartments i n t h e r e g i o n of t h e Voyager Shroud. Because of s t e r i l i z a t i o n r e q u i r e m e n t s , t h e two Voyager compartments w i l l b e v e n t e d w i t h v a l v e s i n t o a d j o i n i n g compartments, which w i l l , i n t u r n , be v e n t e d by f l a t p l a t e c u t - o u t s i n t o t h e e x t e r n a l s t r e a m . An e x i s t i n g two-compartment v e n t i n g program h a s been m o d i f i e d t o p r e d i c t t h e i n t e r n a l p r e s s u r e time h i s t o r i e s f o r t h i s t y p e of v e n t i n g scheme. h. Cone-Cylinder Frustum-Cylinder T r i s o n i c Study: The f i n a l r e p o r t from Lockheed, " T r i s o n i c Loads Study,'' h a s been r e c e i v e d and i s s a t i s f a c t o r y . This r e p o r t (LMSC/HREC8783468) c o n t a i n s t h e r e s u l t s of a p a r a m e t r i c wind t u n n e l t e s t o f cone-cyl i n d e r - f l a r e - c y l i n d e r models. The l o a d d i s t r i b u t i o n s o v e r t h e s e models were d e t e r m i n e d by i n t e g r a t i n g p r e s s u r e s around t h e c i r c u m f e r e n c e of t h e body. The l o c a l normal f o r c e d i s t r i b u t i o n s were t h e n i n t e g r a t e d and compared w i t h e x p e r i m e n t a l f o r c e d a t a . T h i s r e p o r t i s a n advance i n t h e s t a t e - o f t h e - a r t i n t h a t t h e aerodynamic d e s i g n e r can now d e f i n e l o a d d i s t r i b u t i o n s i n t h e t r a n s o n i c Mach regime (0.7 t o 2.0). T h e o r e t i c a l methods, s u c h as second o r d e r shock e x p a n s i o n s , l i n e a r i z e d t h e o r y , Van ~ y k e ' s above Mach 1 . 5 and h y p e r s o n i c impact t h e o r y above Mach 5 . 0 can be used t o d e f i n e l o a d d i s t r i b u t i o n s . A s u b s o n i c t h e o r y , which h a s a l s o b e e n d e v e l o p e d , i s u s e f u l up t o Mach numbers of 8 . 0 . However, r e l i a b l e t h e o r e t i c a l methods i n t h e t r a n s o n i c Mach number regime d o n o t e x i s t . The r e s u l t s of t h i s Lockheed s t u d y a r e i n t e n d e d t o f i l l t h e v o i d i n t h e t r a n s o n i c Mach number regime. �i. Q - B a l l E r r o r A n a l y s i s : A r e p o r t d e s c r i b i n g t h e use and accuracy of EDS Q - B a l l was published d u r i n g November. The t i t l e is " Q - B a l l E v o l u t i o n , Emergency D e t e c t i o n System A p p l i c a t i o n , and E r r o r Analysis a s Applied t o t h e A p o l l o / S a t u r n , " R-AERO-AD-66-40, dated September 1 5 , 1966. j. S-IC/S-11 I n t e r s t a g e Aerodynamic I n v e s t i g a t i o n : Data from t h e s u p e r s o n i c t e s t s conducted i n t h e MSFC 1 4 x 14" TWT i n June 1966 a r e b e i n g a n a l y s e d on a p a r t - t i m e b a s i s w h i l e p r e p a r a t i o n s a r e being made f o r t h e s u b s o n i c and t r a n s o n i c t e s t s . These t e s t s w i l l use a technique i n which one-half of t h e model i s mounted on a s p l i t t e r p l a t e , which i s , i n t u r n , mounted t o t h e t u n n e l s i d e w a l l . The models and b a l a n c e s being f a b r i c a t e d should be ready f o r t e s t s scheduled f o r e a r l y January. k. The o r i f i c e flow c o e f f i c i e n t i n v e s t i g a t i o n , which s u p p o r t s t h e S a t u r n V v e n t i n g program, was conducted i n t h e Ames Research c e n t e r ' s 6 x 6-foot s u p e r s o n i c t u n n e l from October 17, 1966 t o November 1 8 , 1966. Because of model hardware problems caused by poor f a b r i c a t i o n and i n s t r u m e n t a t i o n , t h e t e s t o b j e c t i v e s were n o t reached. Although o n l y a l i m i t e d amount of d a t a was o b t a i n e d , it should be s u f f i c i e n t t o s u p p o r t t h e f i r s t S a t u r n V f l i g h t . P r e s e n t p l a n s a r e t o complete t h e t e s t The model w i l l b e r e d e s i g n e d and r e b u i l t t o program a t Ames i n A p r i l . c o r r e c t e r r o r s and d e f i c i e n c i e s t o i n s u r e t h a t t h e t e s t time w i l l be used e f f i c i e n t l y . The c o n t r a c t w i t h Northrop Space L a b o r a t o r i e s w i l l be extended t o a l l o w completion of t h e planned t e s t program, a l o n g w i t h a d d i t i o n a l work which i n c l u d e s a s t u d y of o r i f i c e flow c o e f f i c i e n t s f o r g a s e s o t h e r than a i r and a s h o r t program i n t h e MSFC 1 4 x 1 4 - i n c h TWT. This program w i l l determine t h e f e a s i b i l i t y of running v e n t i n g s t u d i e s i n t h e MSFC f a c i l i t y . 1. S a t u r n V Load D i s t r i b u t i o n Report: Lockheed has comp l e t e d a r e p o r t p r e s e n t i n g t h e r e s u l t s of s t a t i c p r e s s u r e measurements o b t a i n e d on a 4 p e r c e n t s c a l e model of t h e S a t u r n V launch v e h i c l e i n t h e AEDC 1 6 - f o o t t r a n s o n i c wind t u n n e l . This r e p o r t c o n t a i n s l o c a l p r e s s u r e d i s t r i b u t i o n s , l o c a l normal f o r c e c o e f f i c i e n t s , l o c a l normal f o r c e c o e f f i c i e n t g r a d i e n t s ( f o r a = 0°), and boundary l a y e r p r o f i l e s f o r Mach numbers from 0.6 t o 1.45 and a n g l e s of a t t a c k up t o 10 d e g r e e s . The r e p o r t should be a v a i l a b l e by December 15, 1966. 2. Uprated S a t u r n I B Hypersonic s t a t i c s t a b i l i t y and a x i a l f o r c e t e s t s of t h e AS-206 c o n f i g u r a t i o n have been completed i n t h e AEDC Tunnel E . Data were o b t a i n e d a t Mach numbers of 5 , 6, 7 , and 8 through an a n g l e of These d a t a a r e being analyzed and a t t a c k range from - 3 t o +12 degrees. a s t a t i c aerodynamic r e p o r t covering t h e f l i g h t Mach range of t h e AS-206 w i l l be published soon. �Aerodynamic design d a t a f o r t h e S a t u r n IB/LEM a l o n e v e h i c l e a r e being r e v i s e d , based on t h e r e s u l t s of s e v e r a l wind tunnel The r e v i s e d s t a t i c s t a b i l i t y and a x i a l f o r c e c h a r a c t e r i s t i c s tests have been documented i n R - A E R O - A D - ~ ~ - ~ s~u, p e r s e d i n g R-AERO-AD-66-25. Maximum/minimum and z e r o a n g l e - o f - a t t a c k e x t e r n a l p r e s s u r e d i s t r i b u t i o n s f o r the upper s t a g e , documented i n CCSD TB-AP-66-62, a r e being approved f o r use a s d e s i g n c r i t e r i a . . Wind t u n n e l t e s t s i n t h e MSFC 1 4 x 14-irich TWT t o d e t e r mine t a n k l o a d s , s t r a p - o n l o a d s , and s t a t i c s t a b i l i t y of s e v e r a l proposed u p r a t e d S a t u r n I B c o n f i g u r a t i o n s have been completed. T e s t con£ i g u r a t i o n s included b o t h two and f o u r UTC-120 seven-segment s o l i d r o c k e t motor s t r a p - o n u n i t s . S t a t i c s t a b i l i t y and s t r a p - o n l o a d s were much a s expected; however, tank l o a d s on t h e 70-inch diameter S-IB b o o s t e r tanks were i n c r e a s e d by a f a c t o r of two i n f o r c e s and a f a c t o r It was of t h r e e i n moments from t h e o p e r a t i o n S-IB c o n f i g u r a t i o n . found t h a t t h e s e l o a d s could be s i g n i f i c a n t l y reduced by u s i n g a d i f f e r e n t nose shape on t h e s t r a p - o n u n i t s . Forthcoming r e p o r t s a r e expected t o be ready f o r t h e phase I11 C h r y s l e r c o n t r a c t . S t a t i c tank l o a d s f o r t h e 70-inch d i a m e t e r S a t u r n I B tanks were determined f o r s i m u l a t e d ground winds by t e s t i n g a 0.55 p e r c e n t s c a l e d model i n t h e Wyle low speed wind t u n n e l . The primary purpose of t h e i n v e s t i g a t i o n was t o v a l i d a t e t h e f e a s i b i l i t y of using s m a l l s c a l e d models f o r measuring tank l o a d s . The r e s u l t s of t h e s e t e s t s compare q u i t e f a v o r a b l y w i t h d a t a o b t a i n e d from l a r g e s c a l e models. Tank l o a d s were a l s o determined f o r one of t h e u p r a t e d S a t u r n I B conf i g u r a t i o n s which has f o u r UTC-120 s o l i d r o c k e t motor s t r a p - o n u n i t s . 3. General a. O r b i t a l Aerodynamics: A p a r a m e t r i c s t u d y was conducted on t h e S a t u r n I/SA-5 o r b i t a l v e h i c l e t o i n v e s t i g a t e t h e s e n s i t i v i t y of body-to-ambient temperature r a t i o (from 0.2 t o 0.5) and molecular speed r a t i o (from 7 t o 10) on o r b i t a l aerodynamic p r o p e r t i e s . For p e r f e c t thermal accommodation, a 150 p e r c e n t i n c r e a s e i n t h e temp e r a t u r e r a t i o i n c r e a s e d t h e aerodynamic d r a g c o e f f i c i e n t a b o u t 2 p e r cent. S i m i l a r l y , a 43 p e r c e n t i n c r e a s e i n t h e molecular speed r a t i o decreased t h e drag c o e f f i c i e n t l e s s than 3 p e r c e n t . An a n a l y s i s has been completed t o i n v e s t i g a t e t h e e f f e c t s of t h e c o n c a v i t y of a s p h e r i c a l s u r f a c e on t h e aerodynamic p r o p e r t i e s . By comparing t h e r e s u l t s w i t h i t s corresponding convex s u r f a c e , t h e change i n t h e aerodynamics due t o c o n c a v i t y was about 1 p e r c e n t (assuming a g a i n p e r f e c t thermal accommoda t i o n ) . �b. O r b i t a l Aerodynamics: Lockheed has c a l c u l a t e d t h e o r b i t a l aerodynamics f o r t h e SA-504 o r b i t a l c o n f i g u r a t i o n i n a 188.4 km c i r c u l a r e a r t h o r b i t . A p r e l i m i n a r y d a t a r e p o r t should soon be a v a i l able. Lockheed i s p r e s e n t l y c a l c u l a t i n g o r b i t a l aerodynamics f o r t h e LM/ATM c l u s t e r c o n f i g u r a t i o n . Some d a t a should be a v a i l a b l e i n rough form by December 9 , 1966. D. Experimental Aerophysics Branch 1. 14 x 14-Inch T r i s o n i c Wind Tunnel a . An i n v e s t i g a t i o n i s being made f o r t h e s t u d y and r e f i n e m e n t of h i g h a n g l e - o f - a t t a c k t e s t i n g u s i n g t h e r e f l e c t i o n plane technique f o r Apollo s p a c e c r a f t and a r i g h t c i r c u l a r c y l i n d e r c o n f i g u r a tion. This t e s t used a new s idewall-mounted b a l a n c e and a n g l e - o f - a t t a c k mechanism. A f u l l 360-degree range of a l p h a i s provided by t h e s y s tem. T o t a l runs: 68. b. An i n v e s t i g a t i o n t o determine t h e i n f l u e n c e of wake d i r e c t i n g and n o n d i r e c t i n g s o u r c e s on t h e S a t u r n I B and V Apollo command and s e r v i c e modules i s being made by Lockheed f o r R-AERO-AU. A body such a s a cone, mounted upstream of the model, i s forced t o o s c i l l a t e a t v a r i o u s amplitudes and f r e q u e n c i e s up t o 200 cps. The t e s t model i s submerged i n t h e wake of t h e o s c i l l a t i n g body, and t h e unsteady f o r c e s a r e r e c o r d e d . C o r r e l a t i o n w i l l y i e l d a "convective v e l o c i t y " of t h e wake. These d a t a w i l l become p a r t of t h e "quasi-steady" method of determining s t a t i c s t a b i l i t y d e r i v a t i v e s . The i n s t r u m e n t a t i o n and r e c o r d i n g systems f o r t h i s t e s t were designed and f u r n i s h e d by R-AERO-AE. Much d i f f i c u l t y and l o s t t e s t time were experienced d u r i n g t h e t e s t because of model hardware f a i l u r e and t h e i n a b i l i t y t o f u n c t i o n p r o p e r l y under t e s t c o n d i t i o n s . The hardware i s now b e i n g r e e v a l u a t e d and modified f o r t h e n e x t t e s t p e r i o d , which i s scheduled f o r mid-January 1967. T o t a l runs t o d a t e : 110. The d a t a o b t a i n e d were analyzed by R-AERO-AE and Lockheed p e r s o n n e l , u s i n g our analog c o r r e l a t o r and a t a p e loop machine borrowed from R-COMP-R. c. The v i s c o u s cross-flow e f f e c t s on v a r i o u s b o d i e s of r e v o l u t i o n a t h i g h a n g l e s of a t t a c k a r e being s t u d i e d . The vapor s c r e e n method of flow v i s u a l i z a t i o n , which i s t o be t r i e d l a t e r i n t h i s t e s t , has n o t been p r e v i o u s l y used a t MSFC; some p i l o t s t u d i e s were conducted i n t h e 7- x 7-inch wind t u n n e l . A s m a l l l a s e r was used a s a l i g h t s o u r c e w i t h encouraging r e s u l t s . �d. An i n v e s t i g a t i o n t o determine t h e r e p e a t a b i l i t y of d a t a a t overlapping a n g l e s of a t t a c k using s t i n g s which m a i n t a i n t h e same model c e n t e r of r o t a t i o n i s being made. T o t a l runs: 10. e. The s t a t i c l o n g i t u d i n a l s t a b i l i t y and a x i a l f o r c e c h a r a c t e r i s t i c s of s e v e r a l S a t u r n V Voyager c o n f i g u r a t i o n s a r e being 49. determined. T o t a l runs: 2. 7- x 7-Inch B i s o n i c Wind Tunnel The i n v e s t i g a t i o n by R-AERO-T i n t o t h e use of l a s e r s i n measuring gas v e l o c i t i e s w a s terminated d u r i n g October. The t e r m i n a t i o n of t h e i n v e s t i g a t i o n was due i n p a r t t o t h e c o r r o s i v e a c t i o n of t h e t r a c e r m a t e r i a l on t h e t u n n e l components. R-AERO-AT w i l l c o n t i n u e t h e i r i n v e s t i g a t i o n i n Bldg. 4311 u s i n g small 3-dimens i o n a l n o z z l e s . 3. Thermal-Acous t i c J e t F a c i l i t y The Cold Flow Duct was busy d u r i n g October concluding t h e f i n a l f a c i l i t y checks b e f o r e t h e IITRI p e r s o n n e l a r r i v e d . The f i r s t p r o d u c t i v e t e s t i n g was done i n November i n c o n j u n c t i o n w i t h IITRI p e r s o n n e l ; t h e cross-beam c o r r e l a t i o n technique was used a s a flow analysis tool. The e a r l y t e s t r e s u l t s were v e r y s a t i s f a c t o r y . Addit i o n a l flow a n a l y s e s of t h e j e t s t r e a m a r e now being made by means of h i g h speed movies. An 8000-frame-per-second movie camera was i n s t a l l e d i n t h e s c h l i e r e n s y s tem; a b o u t 25 runs were made t o s e e i f t h e r e i s a n uns t e a d i ness i n t h e shock s t r u c t u r e . F u r t h e r t e s t s a r e scheduled i n which p r e s s u r e surveys a r e t o be made of s i n g l e and c l u s t e r n o z z l e a r r a y s . A l i m i t e d sound-pressure l e v e l survey was t a k e n around t h e n o z z l e e x i t . (See memo d a t e d November 1, 1966 from John Heaman t o Ken Johnston, R-AERO-AM. ) The helium h e a t e r h a s been assembled and i s being checked out. The c o n t r a c t o r , Fuel Engineering Company, has had a d d i t i o n a l p r e s s u r e c o n t r o l l e r problems which a r e now s o l v e d . This has delayed t h e d e l i v e r y s c h e d u l e a n a d d i t i o n a l t h r e e weeks. D e l i v e r y i s s t i l l u n c e r t a i n . 4. Hot and Cold Flow T e s t F a c i l i t i e s A cover was made f o r t h e pebble bed h e a t e r t o provide a 1i g h t - s h i e l d e d a r e a f o r shadowgraph s t u d i e s i n t h e i n v e s t i g a t i o n of Mach wave r a d i a t i o n a s a n o i s e s o u r c e i n a s u p e r s o n i c r o c k e t e x h a u s t . This cover allowed completion of t h e t e s t . A d d i t i o n a l t e s t i n g i s planned f o r e a r l y n e x t y e a r . �5. Data Reduction and Process in% Boeing personnel were t r a i n e d i n t h e u s e of some of our analog a c o u s t i c and v i b r a t i o n a n a l y s i s equipment t o a n a l y z e ground wind data. The program t o reduce t h e Cold Flow Duct c a l i b r a t i o n d a t a The program reduces was completed, and more than 50 runs were reduced. measured p r e s s u r e s and temperatures t o e n g i n e e r i n g u n i t s , and c a l c u l a t e s l o c a l Mach number, v e l o c i t y , d e n s i t y , Reynolds number, and v i s c o s i t y from t h e measurements. Data have been r e c e i v e d i n magnetic t a p e form from t h e R-AERO-AD t e s t of t h e v i s c o u s c r o s s flow models a t LTV. A program was developed t o t r a n s c r i b e t h e d a t a o n t o c a r d s , and t h e c a r d s were used f o r f u r t h e r r e d u c t i o n w i t h our programs and f o r p l o t t i n g . S t a t i c p r e s s u r e d a t a from t h e S a t u r n V 4 p e r c e n t a c o u s t i c t e s t a t AEDC, which have been r e c e i v e d on magnetic t a p e , was converted t o cards f o r p l o t t i n g . The conversion program may be used f o r any AEDCg e n e r a t e d d a t a . A l l conversion uses t h e CDC 3200 computer i n Bldg. 4200. ~ x c e l l e n ta s s i s tance was g i v e n by R-COMP. Three d i f f e r e n t p r e s e n t a t i o n s have been g i v e n by R-COMP on t h e i r f h i r d - g e n e r a t i o n computer system. S e v e r a l problems which have a l r e a d y been discovered a r e being r e s o l v e d by M r . Jandebeur. Two wide-band magnetic t a p e systems a r e being used t o make d u p l i c a t e d a t a t a p e s of t h e f i r s t phases of t h e S a t u r n V 4 p e r c e n t R-AERO-AE i s reducing 11 runs o r 1200 sound-pressure acoustic test. l e v e l s from t h e s e dubbed t a p e s . R e s u l t s of t h e reduced d a t a w i l l be a v a i l a b l e t o -AU i n e a r l y December. 6. Low D e n s i t y Chamber C a l i b r a t i o n of t h e Mach 4 low d e n s i t y n o z z l e has c o n t i n u e d , and s u c c e s s i v e c a l i b r a t i o n runs have been made t o e s t a b l i s h r e p e a t a b i l i t y of the Mach number a t t h e n o z z l e e x i t plane. These r u n s have been comp l e t e d , and t h e d a t a a r e being reduced. C a l i b r a t i o n runs w i t h t h e impact p r e s s u r e probe downstream and upstream of t h e n o z z l e e x i t a r e being made t o e s t a b l i s h t h e Mach number g r a d i e n t . Experiments a r e being designed f o r measuring drag f o r c e s on s p h e r e s , hemispheres, c y l i n d e r s and wedges i n t h e low d e n s i t y flow. Drag f o r c e s w i l l f i r s t b e measured by v a r i o u s simple techniques such a s displacement measurement and t o r s i o n b a l a n c e technique. A pendulum-type b a l a n c e has been designed and i s i n t h e shop f o r f a b r i c a t i o n . �The f i r s t s e r i e s of experiments w i t h t h e molecular beam i s completed. Molecular beam i n t e n s i t i e s have been s u c c e s s f u l l y measured w i t h a VEECO RG-75 h o t cathode i o n i z a t i o n gauge, thus d e f i n i n g a w e l l c o l l i m a t e d beam f o r t h e c a p t u r e c o e f f i c i e n t experiments. The maximum i n t e n s i t y recorded was 8.8 x loL3 molecules p e r second f o r a carbon d i o x i d e s t a g n a t i o n p r e s s u r e of 3850 t o r r . T e s t s u s i n g t h e Sloan Quartz Microbalance a t LN, temperature t o d e t e c t condensing CO, have been comp l e t e d , and t h e d a t a a r e being analyzed. Work has been delayed on t h e t i t a n i u m pumping experiment i n f a v o r of t h e molecular beam experiment. 7. IBFF - The North American A v i a t i o n Dual Plane S e p a r a t i o n T e s t (AT-62) conducted f o r AERO-AT was completed. A l l d a t a were t r a n s m i t t e d t o North American viat ti on' s Space and I n f ormation Sys tems Divis i o n f o r a n a l ys is. Hot flow f o r c e d a t a g e n e r a l l y a g r e e d w i t h t h e cold flow f o r c e d a t a o b t a i n e d p r e v i o u s l y a t Langley. However, a t s m a l l i n t e r s t a g e s e p a r a t i o n d i s t a n c e s , t h e f o r c e d a t a were h i g h e r t h a n expected, according t o N.A.A. Some p r e s s u r e and h e a t t r a n s f e r d a t a were o b t a i n e d . A l l p r e s s u r e d a t a g e n e r a l l y agreed w i t h t h e o r e t i c a l p r e d i c t i o n s . Heat t r a n s f e r d a t a on t h e h e a t s h i e l d were much h i g h e r t h a n expected f o r a l l s e p a r a t i o n di s tances . A h i g h Reynolds number model f a c i l i t y was f a b r i c a t e d and tested a t an e a r l i e r date. The f o l l o w i n g g e n e r a l d a t a t r e n d s were established: (1) Flow e s t a b 1 ishment time a t s u b s o n i c , t r a n s o n i c and s u p e r s o n i c speeds. (2) S t a r t time and s t a r t load comparisons w i t h t h e primary diaphragm l o c a t e d upstream and downstream of t h e t e s t s e c t i o n . A 0.5 s c a l e t e s t s e c t i o n of t h e h i g h Reynolds number model f a c i l i t y has been f a b r i c a t e d and i s b e i n g t e s t e d t o o b t a i n d a t a t r e n d s on a s c a l e d f a c i l i t y . �8. Heat T r a n s f e r I n s trumenta t i o n The h e a t t r a n s f e r work on t h e 1000°F gauges h a s been t e r m i n a t e d f o r t h e p r e s e n t . Upon a r r i v a l and t e s t i n g of t h e f i r s t u n i t s , e v a l u a t i o n s w i l l resume. E v a l u a t i o n s of t h e performance of newer t y p e s h e a t t r a n s f e r gauges a r e c o n t i n u i n g i n t h e IBFF. 9. M i s c e l laneous a . A low-speed t a n k l o a d s t e s t of t h e S a t u r n IB and p o s s i b l e u p r a t e d s t r a p - o n c o n f i g u r a t i o n s was conducted by R-AERO-AD a t Wyle L a b o r a t o r i e s u s i n g t h e i r low s p e e d wind t u n n e l . A d i g i t a l d a t a a c q u i s i t i o n s y s tem, c a r d punch, and a s s o c i a t e d s i g n a l c o n d i t i o n i n g equipment were t a k e n t o Wyle and used f o r t h e t e s t . The d a t e f o r t h e second phase of t h e S a t u r n V 4 p e r b. c e n t a c o u s t i c model t e s t a t AEDC h a s s l i p p e d t o J a n u a r y 9 , 1967. Checkout and p r e l i m i n a r y c a l i b r a t i o n s o f t h e model and i n s t r u m e n t a t i o n w i l l be done a t MSFC b e f o r e shipment t o AEDC., The equipment w i l l be shipped b e f o r e t h e Christmas holidays. c. Forced o s c i l l a t i o n b a l a n c e No. 208 has b e e n i n c o r p o r a t e d i n t o a t e s t j i g t o d e t e r m i n e t h e e f f e c t s of l i f t and d r a g l o a d s upon t h e a c c u r a c y o f s t r a i n gauge a n g u l a r d i s p l a c e m e n t t r a n s d u c e r s . P r e l i m i n a r y t e s t s have i n d i c a t e d t h a t t h e i n a c c u r a c y of t h e d i s p l a c e ment t r a n s d u c e r i s a b o u t two p e r c e n t o r l e s s . 10. G r a v i t y S i m u l a t i o n Workbench \ P r e l i m i n a r y work h a s begun i n t h e d e f i n i t i o n of t h e comp o n e n t s of t h e workbench. Hardware i s b e i n g d e s i g n e d f o r a p r e l i m i n a r y i n v e s t i g a t i o n of t h e g r a v i t y s i m u l a t i o n workbench c o n c e p t . T h i s t e s t w i l l u s e a p r e s e n t l y a v a i l a b l e c e n t r i f u g a l blower t o i n c l u d e f l o w t h r o u g h t h e f u l l s c a l e workbench model. The t e s t , t o be conducted a t a t m o s p h e r i c p r e s s u r e , w i l l a l s o use a t u r b i n e - t y p e f l o w m e t e r t o measu r e t o t a l mass f l o w t h r o u g h t h e bench work s u r f a c e . The t e s t s c h e d u l e i s i n d e f i n i t e b e c a u s e of t h e b o t t l e n e c k s a n t i c i p a t e d i n d e l i v e r y of t h e hardware from ME L a b o r a t o r y . 11. S a t u r n V High Angle-of-Attack Loads I n v e s t i g a t i o n High Reynolds Number With encouragement from t h e NASA R e s e a r c h A d v i s o r y Comm i t t e e on Space V e h i c l e Aerodynamics, t h e Aerophys i c s D i v i s i o n h a s submitted a t e s t requirement f o r obtaining Saturn V load d i s t r i b u t i o n a t h i g h a n g l e of a t t a c k and v e r y h i g h Reynolds number ( a b o u t 500 x 10"' �based on model l e n g t h ) t o R&DO f o r funding. This requirement has a l s o been included i n t h e Lab's S a t u r n V " s o f t s p o t " l i s t . Action i s s t i l l pending on t h i s item, and a subsequent p r e s e n t a t i o n t o t h e MSFC Direct o r ' s o f f i c e w i l l be made i n t h e n e a r f u t u r e . C e r t a i n hardware and l e g a l d e t a i l s a r e being worked o u t w i t h F a c i l i t i e s and Design O f f i c e and t h e Chief Counsel, r e s p e c t i v e l y . E. Thermo Environment Branch 1. Saturn I B a. Aerothermodynamics The SA-204 launch v e h i c l e thermal environment was p u b l i s h e d d u r i n g October. The aerodynamic h e a t i n g p o r t i o n of t h e SA-204 launch v e h i c l e environment was found t o be approximately 2 p e r c e n t l e s s s e v e r e than t h e SA-201 environment. Corresponding b a s e thermal environments were found t o be comparable i n s e v e r i t y t o t h o s e environments experienced by SA-202. As a r e s u l t of t h e s e f i n d i n g s , no thermal problems a r e a n t i c i p a t e d d u r i n g t h e SA-204 f l i g h t . The SA-206 maximum aerodynamic h e a t i n g environmental r e p o r t i s being p u b l i s h e d . R e s u l t s contained i n t h i s r e p o r t were based on t h e maximum aerodynamic h e a t i n g t r a j e c t o r y f o r SA-206 published October 1 2 , 1965. This t r a j e c t o r y r e s u l t e d i n a n environment t h a t was a b o u t 8 p e r c e n t and 1 8 p e r c e n t more s e v e r e t h a n t h e corresponding environments f o r SA-201 and SA-202, r e s p e c t i v e l y . However, a new SA-206 r e f e r ence t r a j e c t o r y i s now being computed by MSFC. E s t i m a t e s by MSFC i n d i c a t e t h a t t h e new t r a j e c t o r y i s more s e v e r e than t h e previous maximum h e a t i n g t r a j e c t o r y . P r e p a r a t i o n s a r e now being made t o determine t h e new more s e v e r e maximum SA-206 aerothermodynamic h e a t i n g environment. Analyses w i l l begin a s soon a s t h e new maximum h e a t i n g t r a j e c t o r y i s a v a i l a b l e . b. Base Heating Analyses t o determine maximum b a s e and e x h a u s t plume h e a t i n g environments f o r t h e SA- 206 v e h i c l e have been completed. R e s u l t ing maximum environments were published d u r i n g October. Also included i n t h i s document a r e d i s c u s s i o n s concerning b o t h t h e c o n v e c t i v e and plume r a d i a t i o n models developed a t CCSD. I n t e r s t a g e h e a t i n g , a s produced by r e t r o and u l l a g e motor exhaust plume impingement, i s a l s o c o n s i d e r e d . Base and aerodynamic h e a t i n g d a t a o b t a i n e d from model t e s t s and a n a l y t i c a l p r e d i c t i o n s a r e being c o r r e l a t e d w i t h S a t u r n I B flight test results. This c o r r e l a t i o n was done f o r aerodynamic h e a t i n g environments , H- 1 engine exhaus t r a d i a n t h e a t i n g r a t e s , and S-IB s t a g e base region convective h e a t t r a n s f e r c o e f f i c i e n t s . I n addition, correl a t i o n of r e t r o - r o c k e t plume impingement h e a t i n g d a t a h a s been i n i t i a t e d . �A r e p o r t documenting t h e r e s u l t s of t h e s e e f f o r t s w i l l be r e l e a s e d i n December f o r t h e SA-203 v e h i c l e . A s i m i l a r r e p o r t f o r t h e SA-201 and SA-202 v e h i c l e s i s s c h e d u l e d f o r p u b l i c a t i o n d u r i n g J a n u a r y 1967. I n s u p p o r t of v e h i c l e d a t a c o r r e l a t i o n , work i s cont i n u i n g on r e f i n i n g t h e t u r b u l e n t j e t mixing w i t h a f t e r b u r n i n g comp u t e r program, which was developed t o p r e d i c t l o c a l thermochemical p r o p e r t i e s i n t h e j e t wake f l o w f o r a c o n s t a n t p r e s s u r e e q u i l i b r i u m c h e m i s t r y plume. The p r e s e n t r e f i n e m e n t s i n v o l v e ( a ) i n c l u s i o n o f a n eddy v i s c o s i t y f o r t h e f a r - j e t - m i x i n g c a s e , ( b ) d i r e c t c o u p l i n g of NASA/LEWIS thermochemical s u b r o u t i n e t o p r o v i d e t h e r e q u i r e d e q u i l i b r i u m c h e m i s t r y d a t a , and ( c ) w r i t i n g a s u b r o u t i n e t o a n a l y t i c a l l y p r e d i c t spot concentrations. I t e m s ( a ) and ( b ) a r e a b o u t 50 p e r c e n t c o m p l e t e , b u t item ( c ) has only been o u t l i n e d i n theory. P a r a m e t r i c runs w i l l b e conducted u s i n g t h e program, and t h e r e s u l t s w i l l b e compared w i t h s i m i l a r i n t e g r a l s o l u t i o n s p r e s e n t e d i n t h e l i t e r a t u r e . T h i s work s h o u l d b e completed by mid-December. E x i s t i n g computer programs and t e c h n i q u e s used t o d e t e r m i n e r a d i a t i o n form f a c t o r s a r e b e i n g r e v i e w e d . These programs a r e a v i t a l p a r t o f d e t e r m i n i n g thermal e n v i r o n m e n t s t o a r e a s o f t h e S a t u r n IB v e h i c l e a f f e c t e d by e x h a u s t plume r a d i a t i o n . c. Thermodynamic F l i g h t E v a l u a t i o n - S-IB S t a g e P r e l i m i n a r y p r e p a r a t i o n s f o r t h e e v a l u a t i o n of SA- 204 t h e r m a l d a t a a r e b e i n g made. Meanwhile, a n a l y s i s o f d a t a from t h e SA-203 s p e c t r o m e t e r i s c o n t i n u i n g . Two r e c e n t changes w e r e i n t r o d u c e d i n t h e s p e c t r o m e t e r d a t a r e d u c t i o n program b e c a u s e of a n a p p a r e n t s h i f t i n a m p l i f i c a t i o n of t h e o u t p u t s i g n a l t h a t occurred a t approximately 75 s e c o n d s of f l i g h t . The program c a l c u l a t e s t h e i n t e g r a t e d a v e r a g e d i n t e n s i t y o f e a c h c h a n n e l f o r e a c h of t h e t h r e e s p a t i a l s c a n s and f o r t h e c a l i b r a t i o n c y c l e . An a t t e m p t i s b e i n g made t o c o r r e l a t e t h e change i n t h e i n t e n s i t y l e v e l s of t h e s p a t i a l s c a n s w i t h t h e change i n t h e l e v e l s of t h e c a l i b r a t i o n c y c l e a s a f u n c t i o n of t i m e . T h i s c o r r e l a t i o n s h o u l d y i e l d a time-dependent compensation f a c t o r t h a t would ad j u s t t h e i n t e n s i t y l e v e l s of t h e d a t a i n l i n e w i t h changes i n t h e l e v e l o f t h e c a l i b r a t i o n c y c l e . A r e p o r t on t h e s p e c t r o m e t e r d a t a s h o u l d b e completed soon. d. S-IB High Angle o f A t t a c k The i n a b i l i t y of t h e JPL H y p e r s o n i c Wind Tunnel t o The e s t a b l i s h t u r b u l e n t f l o w a t Mach number 6 i s c r e a t i n g problems. l a m i n a r h e a t i n g r a t e i s low, and t h e r e s u l t i n g s k i n t e m p e r a t u r e r i s e a p p e a r s t o be t o o s m a l l t o a l l o w a n a c c u r a t e t e m p e r a t u r e - t i m e s l o p e measurement. The p o s s i b i l i t y of r u n n i n g a s h o r t t e s t i n t u n n e l A of AEDC a t t h e h i g h e r Mach numbers i s b e i n g s t u d i e d . The JPL f a c i l i t y w i l l s t i l l b e used f o r t h e lower Mach numbers. �An a n a l y t i c a l a p p r o a c h t o t h e h e a t i n g problems of b o d i e s o f r e v o l u t i o n a t h i g h a n g l e o f a t t a c k i s underway. 2. Saturn V a. S a t u r n V/Voyager Thermal Environment An a n a l y s i s was s t a r t e d t o p r e d i c t t h e t h e r m a l e n v i r o n ment of t h e S a t u r n VIVoyager. Data f o r t h e f i r s t 250 s e c o n d s o f f l i g h t , which a r e b e i n g i n p u t t o t h e SHORE/CATCH computer program, c o n s i s t o f c o n f i g u r a t i o n d a t a , m a t e r i a l p r o p e r t i e s , h e a t s i n k d e s c r i p t i o n , and f l o w f i e l d ( p r e s s u r e ) d a t a . R e s u l t s o f a p r e l i m i n a r y r u n a r e b e i n g checked f o r p o s s i b l e i n p u t e r r o r s . When t h e i n p u t d a t a a r e found t o b e c o r r e c t , t h e e n t i r e 250 s e c o n d s w i l l b e r u n . Results of t h i s run w i l l provide h e a t t r a n s f e r c o e f f i c i e n t s , recovery temperatures, wall temperatures, and h e a t r a t e s f o r t h e f i r s t 250 s e c o n d s o f t h e S a t u r n V l ~ o y a g e rf l i g h t . b. Design Assurance - S-IC Two a n a l y s e s have b e e n completed and a r e now b e i n g i n c o r p o r a t e d i n t o t h e d e s i g n a s s u r a n c e document: (1) Energy t r a n s f e r from s o l i d m o t o r p a r t i c l e s t o s u r f a c e s using experimental t e s t d a t a . (2) An a n a l y t i c a l d e t e r m i n a t i o n o f t h e f l o w f i e l d r e s u l t i n g from a r o c k e t motor e x h a u s t i n g i n t o a n oncoming s tream. P u b l i c a t i o n s "Thermal Environment o f t h e Confined D e t o n a t i n g Fuse and t h e R e t r o Rockets" and "Revised C o n v e c t i v e Heat T r a n s f e r C o e f f i c i e n t f o r I U R e t r o ~ e f l e c t o r "w i l l b e i n c l u d e d i n t h e d e s i g n a s s u r a n c e document. c. O p e r a t i o n a l Thermal Environment - SA-501 The document " S a t u r n V Launch V e h i c l e F i n a l Thermal Environment SA-501 , I f which c o n t a i n s e s t i m a t e s o f t h e e n v i r o n m e n t s f o r s p e c i f i c f l i g h t c a l o r i m e t e r s , g a s p r o b e s , t h e r m o c o u p l e s , and p r e s s u r e t a p s on t h e S a t u r n SA-501 f l i g h t v e h i c l e , h a s b e e n completed. 3. Miscellaneous a. Base P r e s s u r e and Environment The p o r t i o n s of t h i s s t u d y now under i n v e s t i g a t i o n i n v o l v e t h e t u r b u l e n t boundary l a y e r g r o w t h on n o z z l e w a l l s w i t h mass i n j e c t i o n and t h e r e a c t i n g s h e a r l a y e r a t t h e plume boundary. �The GASL f i n i t e - r a t e s h e a r l a y e r program i s being used t o i n v e s t i g a t e t h e e f f e c t of e x i t plane j e t temperature on t h e a f t e r b u r n i n g flame s tand-of f d i s tance. A hand c a l c u l a t i o n procedure is being e s t a b l i s h e d t o p r e d i c t h e a t i n g r a t e s downstream of Hz v e n t s on S a t u r n c l a s s v e h i c l e s . It i s expected t h a t t h e r e s u l t s from computer program i n v e s t i g a t i o n s of t h i s problem can be condensed t o a few simple formulas t o be used w i t h one o r two p a r a m e t r i c c h a r t s . R e s u l t s of t h e t e s t f i r i n g of C o r n e l l ' s 1 / 2 0 s c a l e model F-1 engine a r e s t i l l pending. b. A b l a t i v e M a t e r i a l s Analysis Work i s c o n t i n u i n g on t h e decomposition-in-depth comp u t e r program. A problem has been found i n t h e c o n t i n u i t y of t h e flow between time s t e p s . A d d i t i o n a l e q u a t i o n s a r e being added t o t h e s e t which i s solved s i m u l t a n e o u s l y i n a n e f f o r t t o c o r r e c t t h i s . Also, work has s t a r t e d on t h e h e a t i n g a n a l y s i s f o r t h e Mars S o i l Sample R e t r i e v a l Study. c. S t a g e S e p a r a t i o n Thermodynamics The computer program t o p r e d i c t impingement p r e s s u r e s a l o n g a s o l i d boundary i n t h e s t r o n g shock r e g i o n of a r o c k e t exhaust impingement flow f i e l d has been completed and t h e r e s u l t s checked a g a i n s t b o t h experimental d a t a and v a l u e s o b t a i n e d i n t h e p a s t by hand c a l c u l a t i o n s . For comparison, a s e c t i o n was added t o t h e program which computes t h e t h e o r e t i c a l Newtonian p r e s s u r e s a t t h e same p o i n t s a l o n g t h e boundarywhere t h e s t r o n g shock c a l c u l a t i o n s a r e made. A new a r e a of i n t e r e s t i n impingement h e a t i n g has been e x p l o r e d . When a r o c k e t exhaust plume impinges on a s o l i d boundary a t v e r y h i g h a l t i t u d e s , i t seems c e r t a i n t h a t p o r t i o n s of t h a t boundary w i l l e x p e r i e n c e f r e e molecular h e a t i n g . A t p r e s e n t , t h e r e a r e s e v e r a l programs a v a i l a b l e t o c a l c u l a t e t h i s h e a t i n g i f t h e medium i s "cold" a i r , which, of c o u r s e , i s a poor assumption i n a r o c k e t e x h a u s t . Thus, a new c a l c u l a t i o n scheme was devised t o handle f r e e molecular h e a t i n g i n high temperature e x c i t e d g a s e s . This new scheme has been i n c o r p o r a t e d method of characi n t o a computer program which depends on t h e LMSC/HREC t e r i s t i c s (MOC) d e s c r i p t i o n of t h e plume flow f i e l d f o r i n p u t . S i n c e no experimental d a t a on f r e e molecular h e a t i n g r a t e s i n h i g h temperat u r e g a s e s a r e a v a i l a b l e , i t was decided t o i n p u t t h e c a s e of a f l a t p l a t e a t a n a n g l e of a t t a c k i n "cold" a i r and check t h e r e s u l t s of t h e program a g a i n s t t h e o u t p u t of a conventional f r e e molecular h e a t i n g program. The agreement was e x c e l l e n t . This agreement i s n e c e s s a r y b u t n o t s u f f i c i e n t proof of t h e v a l i d i t y of t h e c a l c u l a t i o n scheme. It w i l l be s t u d i e d i n more d e t a i l . �d. Nozzlc and J c t Wakc Sttidy Measured and c a l c u l a t e d p i t o t p r e s s u r e s i n t h e plume of a c o l d f l o w 1 / 5 6 s c a l e model F-1 e n g i n e h a v e b e e n compared. The a n a l y t i c a l c a l c u l a t i o n s were made u s i n g t h e method o f c h a r a c t e r i s t i c s R e s u l t s , which i n d i c a t e f a i r agreement, w i l l be published i n t h e near future. 5-2 e n g i n e f l o w f i e l d s w i t h e x t e n s i o n s k i r t s h a v e been studied. S k i r t h a l f - a n g l e s were v a r i e d from 4 . 9 d e g r e e s i n 2 - d e g r e e i n c r e m e n t s . I n e a c h c a s e , t h e c a l c u l a t i o n s w e r e c o n t i n u e d downstream t o a n a r e a r a t i o of 200. A r e p o r t h a s b e e n p r e p a r e d documenting t h e work p e r formed t o d a t e on a new method f o r computing s u p e r s o n i c f l o w f i e l d s . T h i s method computes t h e f l o w f i e l d a l o n g s t r e a m l i n e s and n o r m a l s . The u l t i m a t e g o a l o f t h i s t y p e o f a p p r o a c h i s t o h a n d l e m u l t i p l e s h o c k s i n the flow f i e l d . e. E q u i l i b r i u m Real Gas/Normal Shock Program f o r S t a g n a t i o n P o i n t Heating Mass i n j e c t i o n e f f e c t s h a v e b e e n added t o t h e b o u n d a r y l a y e r s o l u t i o n , and t h e r e s u l t i n g computer program i s b e i n g checked o u t . A l s o , e f f o r t was d e v o t e d t o p r e d i c t i n g c o n v e c t i v e h e a t r a t e s f o r e n t r y of a v e h i c l e i n t o t h e M a r t i a n atmosphere. E n t r y t r a j e c t o r i e s have been e s t a b l i s h e d , and b o u n d a r y c o n d i t i o n s d e t e r m i n e d f o r i n p u t t o t h e convective heating routines. Shock l a y e r r a d i a t i o n p r e d i c t i o n t e c h n i q u e s a r e b e i n g r e v i e w e d , and t h e m o s t a p p l i c a b l e w i l l b e used i n t h i s s t u d y . f . Thermal R a d i a t i o n Memorandum A p r o p o s e d NASA TM X e n t i t l e d "Theory o f Thermal R a d i a t i o n from L i q u i d and S o l i d P r o p e l l a n t Rocket E x h a u s t s ," h a s b e e n w r i t t e n . I n t h i s 200-page memorandum, n e a r l y 600 r e f e r e n c e s a r e d i s c u s s e d , and n e a r l y 500 e q u a t i o n s a r e p r e s e n t e d which d e s c r i b e t h e d e t a i l s of g a s e o u s r a d i a t i o n , r a d i a t i o n from c a r b o n p a r t i c l e s , and r a d i a t i o n from A1 ?03 p a r t i c l e s . The e q u a t i o n o f r a d i a t i o n t r a n s f e r i s d e r i v e d i n d e t a i l , and s o l u t i o n s a r e g i v e n w h i c h i n c l u d e t h e e f f e c t s o f s c a t t e r i n g (Mie and R a y l e i g h ) , a s w e l l a s e m i s s i o n and a b s o r p t i o n . The a n a l y s e s o f s p e c t r a l l i n e b r o a d e n i n g and band models a r e p r e s e n t e d f o r g a s e o u s r a d i a t i o n and f o r m a t i o n and s i z e s o f c a r b o n . Al,O3 p a r t i c l e s a r e d i s c u s s e d f o r p a r t i c l e r a d i a t i o n . Numerous methods of p r e d i c t i n g g a s and p a r t i c l e e m i s s i v i t i e s and r a d i a t i v e h e a t i n g a r e c r i t i c a l l y r e v i e w e d and a n a l y z e d , and t h e m o s t a c c u r a t e methods c u r r e n t l y a v a i l a b l e a r e d i s c u s s e d . Although t h e a p p l i c a t i o n of t h e g e n e r a l theory is d i r e c t e d toward r a d i a t i o n from t h e e x h a u s t s o f t h e S a t u r n H - 1 , F-1, 5 - 2 , and RL-10 l i q u i d p r o p e l l a n t m o t o r s ( f o r s t a g e - s e p a r a t i o n h e a t i n g ) , t h e �b a s i c t h e o r y a p p l i e s t o r a d i a t i o n from t h e exhaust of any l i q u i d propell a n t engine o r s o l i d p r o p e l l a n t motor. g. O r b i t a l Heating Analysis of t h e S-IVB Workshop The o r b i t a l h e a t i n g a n a l y s i s of the S-IVB workshop has been completed and a memo w r i t t e n p r e s e n t i n g t h e r e s u l t s . Total r a d i a t i v e h e a t r a t e d i s t r i b u t i o n s about t h e workshop a r e p r e s e n t e d f o r 175- and 259-nautical-mile o r b i t s f o r s e v e r a l p o s s i b l e o r i e n t a t i o n s and launch d a t e s , June 2 2 and December 22. F. Unsteady Aerodynamics Branch 1. I n f l i g h t F l u c t u a t i n g P r e s s u r e and Acoustic Environments a . The 4 p e r c e n t S a t u r n V f l u c t u a t i n g p r e s s u r e model i s being prepared a t Marshall f o r use i n t h e AEDC 1 6 - f o o t s u p e r s o n i c wind t u n n e l on January 3 , 1967. The p r e s s u r e c o e f f i c i e n t s and boundary l a y e r v e l o c i t y p r o f i l e s from the t r a n s o n i c phase of t h e t e s t a r e being p l o t t e d . The n e c e s s a r y p r e p a r a t i o n s a t t h e Computation Laboratory a r e being made t o a n a l y z e t h e dynamic p r e s s u r e d a t a o b t a i n e d d u r i n g t h e t r a n s o n i c phase. b. P r e l i m i n a r y "quick-look" e v a l u a t i o n of t h e f l u c t u a t i n g p r e s s u r e d a t a o b t a i n e d on t h e 4 p e r c e n t model a t AEDC a r e being conConcurrent w i t h ducted. A t t h i s time, t h e r e s u l t s a r e encouraging. t h e d a t a e v a l u a t i o n , experiments a r e being conducted t o d e l i n e a t e d a t a a c q u i s i t i o n system c h a r a c t e r i s t i c s . c. A "quick-look" method f o r a s s e s s i n g t h e response of t h e S a t u r n V s t r u c t u r e t o f l u c t u a t i n g p r e s s u r e f o r c e s has been completed. It i s planned t o use t h e d a t a from t h e 4 p e r c e n t model t e s t a t AEDC i n t h e s e s t r u c t u r a l response e s t i m a t i o n s , which w i l l be made by R-P&VE-S. 2. Launch S i t e A c o u s t i c Environment a. The j e t impingement program i n s u p p o r t of o f f s h o r e , launch f a c i l i t y f e a s i b i l i t y , w i t h r e s p e c t t o a c o u s t i c energy p r o d u c t i o n , i s continuing. The v e h i c l e e l e v a t i o n changes w i t h r e s p e c t t o t h e water l e v e l i n f luence, t h e a c o u s t i c environmental c o n d i t i o n s and i s being monitored i n t h e a r e a s c r i t i c a l t o f a c i l i t y , v e h i c l e , and f a r f i e l d . b. The AS-202 a c o u s t i c d a t a e v a l u a t i o n has been delayed because of problems of i n t e r p r e t i n g t h e t e l e m e t r y system s i g n a l s . More s t u d y i s r e q u i r e d i n t h i s a r e a , depending on ~ s t r i o n i c s ' r e e v a l u a t i o n of t h e problems. The e r r o r s a r e p o s s i b l y dependent on s i g n a l amplitude and c e r t a i n s y s tem n o n l i n e a r i t i e s . �c. The a c o u s t i c r e s e a r c h model programs a t t h e T e s t L a b o r a t o r y a r e b e i n g a c c e l e r a t e d b e c a u s e o f t h e newly a c q u i r e d m u l t i p l e x s y s t e m f o r a c o u s t i c d a t a . This s y s t e m w i l l p r o v i d e s e v e r a l phase c o r r e l a t a b l e c h a n n e l s w i t h i n a month o r s o a f t e r t h e i n s t a l l a t i o n i s completed i n March 1967. A phase c o r r e l a t i o n t e c h n i q u e f o r d e t e r m i n i n g sound s o u r c e d i s t r i b u t i o n s t r e n g t h s , a s t u d y f o r e v a l u a t i n g e n g i n e b e l l e x p a n s i o n e f f e c t s on a c o u s t i c power g e n e r a t i o n , and a n e x p e r i m e n t a l d e t e r m i n a t i o n of t h e e f f e c t s of nozzle e x i t p r e s s u r e v a r i a t i o n a r e among t h e p r o j e c t s o f c u r r e n t i n t e r e s t . d . The f i n a l r e p o r t under C o n t r a c t No. NAS8-11441 e n t i t l e d " I n v e s t i g a t i o n t o D e f i n e t h e P r o p a g a t i o n C h a r a c t e r i s t i c s of a F i n i t e A c o u s t i c P r e s s u r e Wave ," h a s b e e n completed. (The p r i n c i p a l i n v e s t i g a t o r i n t h i s e f f o r t was M r . A. C. P e t e r s . ) T h i s r e p o r t i s concerned w i t h t h e c o n t r i b u t i o n o f t h e e n t r o p y - p r o d u c i n g r e g i o n s t o t h e mechanism o f n o i s e g e n e r a t i o n i n a s u p e r s o n i c e x h a u s t flow. T h i s a n a l y s i s shows t h a t , even though t h e e n t r o p y v a r i a t i o n f o r weak s h o c k s i s o f a t h i r d o r d e r m a g n i t u d e , t'he e f f e c t s o f e n t r o p y p r o d u c t i o n c a n n o t b e d i s r e g a r d e d when c o n s i d e r i n g t h e a c o u s t i c p r e s s u r e s i n c e , i n t h e g o v e r n i n g d i f f e r e n t i a l e q u a t i o n , e n t r o p y e f f e c t s a r e of a f i r s t o r d e r m a g n i t u d e because of a n a d d i t i o n a l f a c t o r appearing i n t h e a n a l y s i s . This r e s u l t p o i n t s f o r t h e f i r s t time t o t h e s h o c k s t r u c t u r e o f a s u p e r s o n i c e x h a u s t as t h e main n o i s e - g e n e r a t i n g mechanisms. When v e r i f i e d , t h i s w i l l r e s u l t i n a major c o n t r i b u t i o n t o t h e understanding of t h e n o i s e g e n e r a t e d by s u p e r s o n i c e x h a u s t s . e . The e n c l o s u r e f o r t h e j e t f l o w shadowgraph s t u d y h a s b e e n c o m p l e t e d , and a d d i t i o n a l shadowgraph e x p e r i m e n t s have b e e n cond u c t e d . The r e s u l t s o f t h e s e e x p e r i m e n t s a r e b e i n g documented. f . Task Order No. 8 f o r Baganoff ~ s s o c i a t e s ' d a t a r e d u c t i o n on t h e MSFc/~mes s e p a r a t e d f l o w e x p e r i m e n t h a s b e e n i s s u e d t o p r o v i d e f o r n a r r o w band time c o r r e l a t i o n s on d a t a from t h r e e s t e p configurations. Completion o f t h i s t a s k o r d e r i s e x p e c t e d i n s i x weeks. 3. Aeroelas t i c i t y a. Panel F l u t t e r The d a t a from t h e wavy-wall p a n e l f l u t t e r t e s t s cond u c t e d i n t h e ARC 2 x 2 - f o o t t r a n s o n i c wind t u n n e l h a v e b e e n r e c e i v e d by MSFC, and f u r t h e r d a t a r e d u c t i o n w i l l b e c a r r i e d o u t i n t h e n e a r future. The f l u t t e r p h a s e o f t h e p a n e l f l u t t e r t e s t s f o r t h e L i m i t a t i o n s o f t h e AEDC S a t u r n IVB forward s k i r t h a s b e e n completed. 1 6 - f o o t t r a n s o n i c wind t u n n e l made i t i m p o s s i b l e t o a c h i e v e i n f l i g h t �c o n d i t i o n s i n a l l c a s e s , and a c o m p r e s s i v e l o a d l i m i t , e s t a b l i s h e d by R-P&VE, made i t i m p o s s i b l e t o o b t a i n f l u t t e r d a t a f o r t h e f u l l y b u c k l e d condition. However, p a n e l f l u t t e r was e n c o u n t e r e d , a s e x p e c t e d , below f l i g h t c o n d i t i o n s . A memorandum is b e i n g p r e p a r e d (R-AERO-AU-66-105), and r e d u c t i o n o f t h e f l u t t e r d a t a w i l l c o n t i n u e . b. P i t c h Damping A new dynamic b a l a n c e s y s t e m is b e i n g d e s i g n e d f o r u s e i n t h e MSFC 1 4 - i n c h t r i s o n i c wind t u n n e l . The new d e s i g n is meant t o r e d u c e t h e c o u p l i n g between t h e t w i s t i n g d e f l e c t i o n caused by t h e p i t c h i n g m o t i o n o f a n o s c i l l a t i n g model and the b e n d i n g d e f l e c t i o n caused by a x i a l f o r c e s a p p l i e d t o t h e model which o c c u r r e d on a p r e v i o u s p i t c h damping t e s t . There i s ample r e a s o n t o b e l i e v e t h a t t h i s c o u p l i n g would a l s o o c c u r on t h e proposed pitch-damping t e s t . It may t h e r e f o r e b e n e c e s s a r y t o d e s i g n new models c o m p a t i b l e w i t h t h e new b a l a n c e s y s t e m . A r u n s c h e d u l e , a s c h e d u l e f o r t h e d e s i g n and c o n s t r u c t i o n of new models ( i f n e c e s s a r y ) , and a d a t a r e d u c t i o n p r o c e d u r e w i l l s o o n b e forthcoming . c. Quas i - S t e a d y O s c i l l a t i n g Wake S t u d y The equipment f o r t h i s t e s t was i n i t i a l l y i n s t a l l e d on O c t o b e r 7 , 1966. The week of October 10-14 was p r i m a r i l y used i n t e s t i n g t h e wake s o u r c e equipment and mod i f y i n g v a r i o u s components t o s a t i s f y t u n n e l r e q u i r e m e n t s . ( F r i d a y a f t e r n o o n and Monday morning (Oct. 1 4 and 1 7 ) were used i n work f o r NASA's open h o u s e week e n d . ) A d d i t i o n a l r u n s were made t o s t u d y what e f f e c t s t h e s t r u t may have on f l o w c o n d i t i o n s , t u n n e l b l o c k a g e , and Mach number v a r i a t i o n s , s i n c e t h i s s t r u t must b e p l a c e d i n t h e t e s t s e c t i o n c l o s e t o t h e t e s t models. R e s u l t i n g d a t a compared f a v o r a b l y w i t h d a t a o b t a i n e d from models p r e v i o u s l y t e s ted . Tunnel t i m e was l o s t q u i t e f r e q u e n t l y b e c a u s e o f problems w i t h t h e t u n n e l c o m p r e s s o r s , t h e h i g h p r e s s u r e v a l v e , and t h e temperature control valve. The t e s t , which was d i s c o n t i n u e d b e c a u s e o f o t h e r t u n n e l commitments, w i l l b e resumed a t a l a t e r d a t e . 4. S a t u r n V Ground Winds R e d u c t i o n o f t h e l a t e s t S a t u r n V wind t u n n e l t e s t d a t a is continuing. F u l l - s c a l e b a s e b e n d i n g moments f o r 2 . 0 , 3 . 1 , and 4 . 5 p e r c e n t o f c r i t i c a l damping have b e e n p r e d i c t e d and f u r n i s h e d t o R-P&VE-S. R-P&VE-S h a s a l s o b e e n f u r n i s h e d p r e d i c t e d f u l l - s c a l e bendi n g moments a t t h e upper v e h i c l e s t a t i o n s f o r 3.1 p e r c e n t of c r i t i c a l damp ing . �VII. DYNAMICS AND FLIGHT MECHANICS DIVISION A. Multi-Pro j e c t s 1. Guidance a. D i r e c t A s c e n t Rendezvous A s t u d y t o d e t e r m i n e a r e l i a b l e d i r e c t a s c e n t rendezvous scheme a l l o w i n g t h e f l e x i b i l i t y of a l a u n c h window t h a t i s r e s t r i c t e d o n l y by v e h i c l e performance, Van A l l e n r a d i a t i o n b e l t , and s y s t e m s l i f e T h i s t e c h n i q u e p e r m i t s rendezvous t i m e is b e i n g p u b l i s h e d a s a NASA TM X. w i t h a n y v e h i c l e of a known ephemeris p r o v i d e d t h e e n e r g y r e q u i r e m e n t i s w i t h i n t h e performance c a p a b i l i t y o f t h e p u r s u i t v e h i c l e . This approach t o rendezvous t a k e s a d v a n t a g e of t h e unique f e a t u r e s o f t h e S a t u r n I B and S a t u r n V g u i d a n c e s y s t e n ( i t e r a t i v e g u i d a n c e scheme) t o compensate f o r any i n f l i g h t performance v a r i a t i o n s t h a t would r e s u l t i n a t i m i n g e r r o r a t rendezvous by making a c u t o f f e n e r g y c o r r e c t i o n t o i n s u z e rendezvous s o l u t i o n . A scheme a c c u r a c y o f two n a t u i c a l m i l e s a t rendezvous a c r o s s a 30-minute l a u n c h window i s i n d i c a t e d b y s t u d y r e s u l t s a t t h i s time. (-DG) b. G e n e r a l i z e d H y p e r s u r f a c e f o r t h e S a t u r n I B and Saturn V Missions The problem of s t a n d a r d i z i n g t h e i n p u t c o n s t a n t s and g u i d a n c e e q u a t i o n s t o h a n d l e t h e l u n a r o r b i t a l rendezvous m i s s i o n , as w e l l a s a n y e a r t h - o r i e n t e d m i s s i o n w i t h t h e same l a u n c h v e h i c l e d i g i t a l computer program, h a s been r e s o l v e d . This f l e x i b i l i t y allows t h e miss ion t o undergo changes w i t h o u t h a v i n g a s o f t w a r e problem p r o v i d e d t h e l a u n c h v e h i c l e d i g i t a l computer c a n h a n d l e t h e s c a l i n g f o r t h e m i s s i o n change. These changes w i l l b e made t o t h e AS-504 g u i d a n c e e q u a t i o n s . They a r e a l s o t o be made i n t h e AS-209 and s u b s e q u e n t f l i g h t s . Documentation of a " G e n e r a l i z e d H y p e r s u r f a c e f o r t h e S a t u r n I B and S a t u r n V Missions" has b e e n r e c e i v e d from N o r t h r o p ; b u t b e f o r e d i s t r i b u t i o n w i l l b e made, o t h e r methods and comparisons f o r s i m p l i c i t y w i l l b e s u r v e y e d t o d e t e r m i n e which i s more e a s i l y implemented i n t o t h e S a t u r n V s y s t e m . (~~INorthrop) c. P a r a m e t r i c T r u n c a t i o n of I n t e l l i g e n c e Used i n IGM S t e e r i n g Angle Computation The s i g n i f i c a n t d i g i t s of t h e n a v i g a t i o n a l i n f o r m a t i o n used i n t h e IGM s t e e r i n g e q u a t i o n s , as w e l l a s t h e f u n c t i o n s used i n t e r n a l l y by IGM, were p a r a m e t r i c a l l y t r u n c a t e d u n t i l t h e s y s t e m became i n d e t e r m i n a t e , o r performance and a c c u r a c y were s i g n i f i c a n t l y penalized. The m i s s i o n s s i m u l a t e d a r e as f o l l o w s : �(3) S a t u r n V t o a c i r c u l a r o r b i t a t 100 NM, (4) S a t u r n V t o a c i r c u l a r o r b i t a t 300 NM, (5) S a t u r n V t o a c i r c u l a r o r b i t a t 400 NM, (6) S a t u r n V t o a c i r c u l a r o r b i t a t 500 NM, (7) LOR parking o r b i t t o t r a n s l u n a r i n j e c t i o n , (8) S a t u r n V t o a n 80 NM p e r i g e e through c o a s t t o synchronous o r b i t a l t i t u d e , (9) S a t u r n V Venus probe. The d a t a have been c o l l e c t e d f o r a r e p o r t , which w i l l g i v e some i n s i g h t i n t o t h e number of s i g n i f i c a n t d i g i t s r e q u i r e d f o r IGM t o perform i n a s a t i s f a c t o r y manner and which w i l l i n d i c a t e how much t h e m i s s i o n can be changed w i t h o u t needing t o r e s c a l e t h e f i x e d p o i n t launch v e h i c l e (DG/Northrop) d i g i t a l computer. d. Thrust F i l t e r i n g f o r IGM A s t u d y has been undertaken t o determine i f a t h r u s t f i l t e r would perform b e t t e r t h a n t h e p r e s e n t l y implemented M / F (mass over t h r u s t ) f i l t e r . S i n c e t h r u s t i s supposedly a c o n s t a n t v a l u e i n t h e upper s t a g e s of S a t u r n I B and S a t u r n V v e h i c l e s , e x c e p t f o r t h e t r a n s i t p e r i o d d u r i n g p r o p e l l a n t mixture s h i f t , i t seems r e a s o n a b l e t o assume t h a t a c o n s t a n t v a l u e would be more e a s i l y f i l t e r e d t h a n a s l o p e s u c h a s M/F. The raw v a l u e of t h r u s t (F) i s computed by assuming t h a t flow r a t e (fi) i s c o n s t a n t . The measured F/M is t h e n m u l t i p l i e d by t h e c a l c u l a t e d mass t o g i v e a raw F v a l u e t o be f i l t e r e d by a d i g i t a l f i l t e r . The F f i l t e r has been analyzed on t h e reduced AS-201 d a t a and a comparison made t o t h e M / F f i l t e r . The F f i l t e r w i l l a l s o be a p p l i e d t o t h e AS-501 second S-IVB burn period and compared t o t h e M / F f i l t e r . Docu(DG/~orthrop) m e n t a t i o n i s expected by mid-December. 2. Dynamics and Control A method has been developed f o r f i n d i n g t h e n a t u r a l f r e The quencies and mode shapes of a v e h i c l e w i t h suspended masses. v e h i c l e i s i d e a l i z e d a s a system of one beam and up t o t e n suspended masses. A v i b r a t i o n a n a l y s i s i s f i r s t made of t h e beam, o m i t t i n g t h e masses, by a modified S t o d o l a method. The e q u a t i o n s f o r t h e connected �system a r e t h e n d e r i v e d u s i n g Lagrange's e q u a t i o n . These e q u a t i o n s have been programmed f o r the I B M 7090 by t h e Computation Laboratory. This program i s b e i n g used t o s t u d y t h e e f f e c t of t h e f l e x i b i l i t y of (DDS) t h e LEM on t h e bending c h a r a c t e r i s t i c s of a v e h i c l e . B. Saturn V 1. Mission P r o f i l e Nonlinear Accelerometer Feedback f o r S a t u r n V w i t h F l e x i b l e Dynamics a. A previous s t u d y (Ref: TM-54130-7 2 , LMSCIHRECA71 2744, Nonlinear Accelerometer Feedback f o r Load R e l i e f , " December 1965) has i n d i c a t e d t h a t t h e bending moment may b e reduced a p p r e c i a b l y d u r i n g t h e b o o s t f l i g h t of t h e S a t u r n V v e h i c l e by means of a l i m i t e d a c c e l e r o m e t e r feedback and a p p r o p r i a t e g a i n s c h e d u l e s . This previous s t u d y d i d not i n c l u d e t h e f l e x i b l e body e f f e c t s introduced by bending and s l o s h modes. During t h e p r e s e n t s t u d y , t h e same load r e d u c t i o n approach was extended t o i n c l u d e bending modes, f u e l s l o s h i n g , s t a b i l i z i n g f i l t e r s , and engine a c t u a t o r dynamics i n a n analog s i m u l a t i o n of t h e S a t u r n V. II The s t u d y r e s u l t s documented i n TM-54130-111, LMSC/ HREC A783386, "Nonlinear Accelerometer Load R e l i e f F l e x i b l e Body Study," October 1966, i n d i c a t e t h a t , w i t h minor system m o d i f i c a t i o n s , bending moment r e d u c t i o n s of t h e same o r d e r of magnitude a s t h o s e i n t h e r i g i d body system may b e obtained. Under a t t i t u d e and a t t i t u d e r a t e c o n t r o l , t h e f l e x i b l e body system y i e l d s a bending moment of 31.0 x l o 7 i n - l b f o r t h e 70 second wind, w h i l e t h e load r e l i e f g a i n s w i t h n o n l i n e a r a c c e l e r o m e t e r feedback produce a moment of 13.0 x l o 7 i n - l b , a reduct i o n of 58 p e r c e n t . These bending moment v a l u e s a r e taken from timev a r y i n g t r a j e c t o r y s i m u l a t i o n s . Although t h e maximum v a l u e s occurred f o r t h e 70 second wind peak, s i m i l a r r e d u c t i o n s were i n d i c a t e d f o r o t h e r time p o i n t s . However, s e v e r a l a d d i t i o n a l f a c t o r s should be cons i d e r e d b e f o r e a d e f i n i t e s t a t e m e n t can be made on t h e f e a s i b i l i t y of using t h e system i n a n a c t u a l launch v e h i c l e . For example, t h e bending moments were recorded a t only one s t a t i o n where t h e bending moment coeff i c i e n t s peak, b u t n o t n e c e s s a r i l y where t h e v e h i c l e s t r u c t u r a l l i m i t i s most c r i t i c a l . The bending moment c o n t r i b u t i o n from t h e f l e x i b l e modes was n o t c o n s i d e r e d , a f a c t o r which could be s i g n i f i c a n t a t s t a t i o n s n e a r t h e v e h i c l e nose. F i n a l l y , a more thorough i n v e s t i g a t i o n of t h e p o s s i b l e winds t h a t could be encountered i s n e c e s s a r y , s i n c e a l a r g e shear reversal which i s conceivable could produce l a r g e r moments (DcA/ f o r t h e load r e l i e f system than f o r a n a t t i t u d e c o n t r o l system. Lockheed) - - �2. Guidance S a t u r n V Manual Guidance Backup The Boeing Company hybrid computer has been s e l e c t e d t o determine t h e f e a s i b i l i t y of manual guidance take-over d u r i n g t h e S - I 1 and S-IVB s t a g e s of t h e S a t u r n V v e h i c l e f l i g h t i n t o e a r t h parking o r b i t and a n a l y z e t h e M I T s y s tem f o r takeover d u r i n g t h e e a r t h parking o r b i t and t r a n s l u n a r i n j e c t i o n power f l i g h t . A l l of t h e o r i g i n a l e f f o r t w i l l be placed on t h e AS-503 mission. A ground r u l e was e s t a b l i s h e d w i t h MSC t h a t manual guidance takeover would be ac6.&nplished i n such a f a s h i o n t h a t no s t e e r ing command d i s c o n t i n u i t i e s would e x i s t , and t h e r e f o r e , no t r a n s i t problemwould e x i s t . (DG) 3. Dynamics and Control a. S t a b i l i t y A n a l y s i s , SA-501 A s t a b i l i t y a n a l y s i s has been completed on SA-501 : r e f l e c t i n g t h e changes caused by t h e use of o p e r a t i o n a l t r a j e c t o r y w i t h new t o l e r a n c e s , updated aerodynamics d a t a and t o l e r a n c e s , updated s l o s h damping, and updated bending and s l o s h model t o l e r a n c e s . The r e s u l t s of t h e a n a l y s i s a r e a s follows: (1) The S-IC p i t c h c o n t r o l system aerodynamic margin was reduced from 4.9 db t o 3.7 db d u r i n g maximum dynamic p r e s s u r e . This d i f f e r e n c e i s caused by a change i n aerodynamic d a t a . This v a l u e degrades t o 2.4 db under 30 c o n d i t i o n s . ( 2 ) The p e r i o d i n which v e h i c l e f a i l u r e occurs a s a r e s u l t of a n S-IC engine o u t has i n c r e a s e d by approximately 10 seconds, This c o n d i t i o n i s a s s o c i a t e d w i t h f a i l u r e s of i/1 and i/4 engines d u r i n g t h e 60- t o 90-second f l i g h t p e r i o d . This change i s a l s o due t o t h e updated aerodynamic d a t a . (3) The S-IC p i t c h c o n t r o l system g a i n margin was reduced from 4.8 db t o 5.2 db under r e f e r e n c e c o n d i t i o n s and t h e s l o s h peak g a i n margin has changed from -3.6 db t o -1.25 db under 30 c o n d i t i o n s . (DDD/ These changes a r e due t o new s l o s h damping v a l u e s and t o l e r a n c e s . Boe i n g ) �b. Saturn V - Umbilical Tower Analysis A program i s being developed t o c a l c u l a t e t h e damped modes of a c o m p l e x ~ s t r u c t u r a lsystem w i t h lumped damping. The f i r s t a p p l i c a t i o n w i l l be a n a l y s i s of the S a t u r n V-Launcher combination. This s t r u c t u r e has a damping mechanism between t h e v e h i c l e and u m b i l i c a l tower t o provide damping and t h u s reduce t h e amplitude of wind-induced o s c i l l a t i o n s . The program has been checked o u t f o r a simple t e s t problem. Generation of t h e u m b i l i c a l tower mass and s t i f f n e s s d a t a i s , expected t o t a k e a b o u t t h r e e months. (DDS/~ockheed) c. Dynamic Analysis of t h e S e r p e n t u a t o r The dynamic a n a l y s e s of t h e f i v e - l i n k S e r p e n t u a t o r has been completed. These S e r p e n t u a t o r l i n k s a r e t h r e e f e e t long and f o u r inches i n d i a m e t e r . A s t r o n a u t p o s i t i o n c o n t r o l i s maintained by e l e c t r o mechanical motors sequenced a t each h i n g e . Dynamic l o a d s caused by s t e p p i n g one motor and c u t t i n g o f f t h e motor a t preceding hinge (sequenci n g ) have been computed. This dynamic c o n d i t i o n c r e a t e s h i g h t r a n s i e n t loads and d e s i g n s t h e motor-gear t r a i n c h a r a c t e r i s t i c s . Astro-Space, I n c . , i s completing assembly of t h i h f i v e - l i n k S e r p e n t u a t o r , which w i l l be a v a i l a b l e f o r dynamic t e s t i n g n e x t month. (DD) d. AS-504 S l o s h i n g An a t t e m p t was made t o a n a l y t i c a l l y determine t h e damping r a t i o which might b e expected when t h e f r e e f l u i d s u r f a c e l i e s w i t h i n t h e upper bulkhead of the S-IC f u e l tank. This method cons i d e r e d t h e d e c r e a s i n g r a d i u s w i t h i n t h e bulkhead t o be analogous t o t h e i n t r o d u c t i o n of r i n g b a f f l e s of i n c r e a s i n g width. This approach l e f t much t o be d e s i r e d . A survey of t h e l i t e r a t u r e has shown t h a t t h e damping r a t i o s f o r t h i s tank geometry can b e s t be o b t a i n e d by experimental methods. Data have been compiled f o r a h e m i s p h e r i c a l l y domed t a n k w i t h and w i t h o u t a r i n g b a f f l e . Although t h e S-IC f u e l tank has a n e l l i p s o i d a l dome, t h e d a t a should g i v e good comparison between t h e two t a n k s . Results w i l l be published n e x t month. (DDD) 4. P r o j e c t Information A p p l i c a b l e t o Many Vehicles a. S a t u r n V Current Performance S a t u r n V c u r r e n t performance based on November 1966 c u r r e n t weight and v e h i c l e performance d a t a was computed and t r a n s m i t t e d t o I n d u s t r i a l O p e r a t i o n s . S i g n i f i c a n t payload d e c r e a s e s were o b t a i n e d due p r i m a r i l y t o l a r g e i n c r e a s e s i n p r o p e l l a n t r e s i d u a l s . (~AP/Boeing) �b. been concluded. (DAP/BO ing ~) 5. LOR Performance Reserves The f l i g h t performance r e s e r v e and f u e l b i a s s t u d y has F i n a l documentation w i l l be r e l e a s e d i n December. P r o j e c t Information A p p l i c a b l e t o I n d i v i d u a l Vehicles a. A e r o e l a s t i c Analysis of S a t u r n V An a e r o e l a s t i c a n a l y s i s i s being performed on t h e S a t u r n V t o determine t h e e f f e c t of v e h i c l e e l a s t i c i t y on f l i g h t l o a d s . I n t h e p a s t , f l e x i b i l i t y has been l i m i t e d t o i n c l u s i o n of t h e v e h i c l e ' s bending modes. This accounts f o r bending mode coupling of t h e c o n t r o l s e n s o r s . The a e r o e l a s t i c a n a l y s i s e v a l u a t e s t h e aerodynamic l o a d i n g which i s induced by t h e d e f l e c t e d v e h i c l e shape. E a r l y i n d i c a t i o n s a r e t h a t t h i s l o a d growth o r s t a t i c a e r o e l a s t i c i t y i s a p p r e c i a b l e (10 p e r c e n t of t o t a l aerodynamic load f o r h i g h l o a d i n g c o n d i t i o n , and a c o n s i d e r a b l y h i g h e r percentage i n terms of l o c a l bending moment). b. 503 Dynamic Analysis The f i n a l r e s u l t s of t h e dynamic a n a l y s i s of 503 using t h e new n o n l i n e a r aerodynamics have been delayed f o r two weeks. This r e p o r t should be r e c e i v e d by t h e middle of December. P r e s e n t r e s u l t s show no engine-out c a p a b i l i t y f o r z e r o wind between approximately 60 and 80 seconds f l i g h t time. (DDD) C. SaturnIB 1. Guidance a. S-IVB Stage Guidance t o Fuel D e p l e t i o n f o r t h e S a t u r n I B Vehicle The e f f e c t s of going t o f u e l d e p l e t i o n f o r t h e AS-209 m i s s i o n have been s t u d i e d ; r e s u l t s show t h i s t o be u n f e a s i b l e e i t h e r from s o f t w a r e impact o r from accuracy r e q u i r e m e n t s . The following methods were i n v e s t i g a t e d : (1) The t r a j e c t o r y can be shaped t o a t t a i n o r b i t w i t h f u e l d e p l e t i o n based on t h e p r e d i c t e d performance of t h e v e h i c l e . This r e q u i r e s a r e g e n e r a t i o n of t h e f i r s t s t a g e t i l t polynomial and i s a s o f tware impact. This method cannot t a k e i n t o a c c o u n t t h e i n f l i g h t performance of t h e S-IB s t a g e and t h e S-IVB s t a g e . �(2) A performance i n d i c a t o r a t S-IB s t a g e c u t o f f t o a s s e s s t h e performance of t h e S-IB s t a g e and then t o change t e r m i n a l c o n d i t i o n s t o account f o r S-IB s t a g e performance d e v i a t i o n s can be used; however, t h i s r e q u i r e s s u b s t a n t i a l a d d i t i o n a l programming i n t h e onboard computer and i s a major s o f t w a r e impact. The performance of d e v i a t i o n s i n t h e S-IVB s t a g e i s n o t taken i n t o account. S i n c e AS-209 (unmanned workshop) i s a rendezvous miss i o n , t h e a c c u r a c y requirements a r e v e r y s t r i n g e n t . I f , f o r t h e nominal m i s s i o n of 80 n. m i . by 175 n. m i . , t h e v e h i c l e burns t o f u e l d e p l e t i o n i n c l u d i n g 1 , 5 0 0 l b 30 f l i g h t performance r e s e r v e , t h e apogee of the o r b i t I f t h e v e h i c l e should have 30 h i g h peri s i n c r e a s e d t o 354.4 n. m i . formance i n each s t a g e and burns t o f u e l d e p l e t i o n , t h e apogee i s r a i s e d These wide d i s p e r s i o n s i n o r b i t a r e unacceptable f o r a t o 492 n. m i . rendezvous miss ion. The conclusion was t h a t burning t o f u e l d e p l e t i o n r a t h e r t h a n a v e l o c i t y c u t o f f i s u n f e a s i b l e f o r AS-209. (~G/Northrop) b. S a t u r n I B AS-208 D i s p e r s i o n Analysis The f i n a l s e t of p a r t i a l d e r i v a t i v e s f o r performance and n a v i g a t i o n e r r o r s have been d e l i v e r e d t o MSC, a s r e q u i r e d , through t h e Guidance and Performance Subpanel, based on t h e AS-208 r e f e r e n c e trajectory. (DG) 2. Dynamics and Control SA-203 Low G r a v i t y S l o s h R e s u l t s : A r e p o r t e n t i t l e d "An Experimental I n v e s t i g a t i o n of Large Booster P r o p e l l a n t Dynamics i n Orbit'' has been prepared and i s being reviewed. This r e p o r t w i l l p r e s e n t t h e low g r a v i t y s l o s h i n g d a t a o b t a i n e d from t h e AS-203 f l i g h t . These d a t a showed t h a t t h e s l o s h b a f f l e and d e f l e c t o r prevented l a r g e amplitude p r o p e l l a n t motion a f t e r i n j e c t i o n and t h a t t h e p r o p e l l a n t s l o s h i n g d u r i n g o r b i t was n o t e x c e s s i v e . (DD) 3. P r o j e c t Information A p p l i c a b l e t o Many Vehicles November Current Performance: Current performance was c a l c u l a t e d and t r a n s m i t t e d t o I n d u s t r i a l O p e r a t i o n s . Payload c a p a b i l i t i e s of v e h i c l e s AS-206 through AS-208 r e f l e c t a 55, 39, and 42 pound reduct i o n , r e s p e c t i v e l y , when compared t o l a s t month's performance. These (~AP/Chrysler) payload d e c r e a s e s were due t o d r y weight i n c r e a s e s . �4. P r o j e c t Information A p p l i c a b l e t o I n d i v i d u a l Vehicles a. AS-204 Second Fl. i g h t S t a g e S t a b i l i t y Analysis The r e s u l t s of t h e second f l i g h t s t a g e s t a b i l i t y a n a l y s i s v e r i f i e d t h a t a l l modes a r e s t a b l e f o r the time p o i n t s chosen e x c e p t t h e LH2 s l o s h mode d u r i n g e a r l y p o r t i o n s of second-stage f l i g h t . This mode was u n s t a b l e a t 20 seconds of second-stage f l i g h t and s t a b l e a t 120 seconds of f l i g h t ; no f l i g h t times between t h e s e two were i n v e s t i g a t e d . Because of t h e s m a l l s l o s h mass and t h e r e l a t i v e l y long time r e q u i r e d t o double t h e amplitude of t h e i n s t a b i l i t y , a c o r r e c t i o n (~Cl~ockheed) was not considered necessary. b. AS-206 Nose Cone S e p a r a t i o n f o r Abort This s t u d y has determined t h a t a s p r i n g s e p a r a t i o n system s i z e d t o g i v e a s e p a r a t i o n v e l o c i t y of seven f e e t per second f o r a normal s e p a r a t i o n ( n e g l i g i b l e dynamic p r e s s u r e ) w i l l a l l o w t h e nose, cone t o be r e l e a s e d f o r a n a b o r t s i t u a t i o n t o permit launch of t h e LEM a s e a r l y a s 186 seconds a f t e r l i f t - o f f (approximately 40 seconds of second s t a g e f l i g h t and corresponding t o a dynamic p r e s s u r e of roughly one pound per s q u a r e f o o t ) w i t h l i t t l e p r o b a b i l i t y of r e c o n t a c t w i t h t h e S-IVB/LEM combination. No motion of t h e LEM s e p a r a t i o n from t h e S-IVB has been considered f o r t h i s s t u d y . F u l l t h r u s t decay b e f o r e i n i t i a t i o n of a b o r t was assumed. A memorandum d e s c r i b i n g t h e s t u d y i s being i s s u e d . (DC) c. AS-206 Control Responses An a n a l y s i s t o determine t h e maximum expected response envelopes a p p l i c a b l e f o r t h e AS-206 and AS-208 v e h i c l e s u s i n g d r i f t minimum a n g l e - o f - a t t a c k c o n t r o l during f i r s t s t a g e f l i g h t has been completed. The r e s u l t s of t h i s s t u d y have been documented i n Memo No. R-AERO-DCC-18-66. Vehicle responses were a l s o determined a t s e l e c t e d f l i g h t times i n t h e maximum dynamic p r e s s u r e r e g i o n u s i n g t h e c o n t r o l system s p e c i f i e d f o r t h e AS-206 v e h i c l e by R-ASTR-F. For some f l i g h t t i m e s , gimbal a n g l e requirements u s i n g a c c e l e r o m e t e r feedback exceeded t h o s e f o r a n g l e of a t t a c k c o n t r o l . However, t h e i n c r e a s e (6.3 t o 6.9 d e g r e e s a t maximum p) i s n o t enough t o p r e s e n t a c o n t r o l l a b i l i t y problem f o r a nonmalfunctioned v e h i c l e even when s u b j e c t e d t o t h e 95 p e r c e n t i l e d e s i g n winds. Because of t h e i n c r e a s e d computer time r e q u i r e d , i t i s n o t considered t o be c o s t e f f e c t i v e t o determine t h e response envelopes d u r i n g complete f i r s t s t a g e f l i g h t using t h e s p e c i f i e d c o n t r o l system u n t i l t h e v e h i c l e d a t a become more r e f i n e d . �A s t u d y t o update c o n t r o l responses f o r u s e i n a n a l y s i s of l o a d s i s t e m p o r a r i l y h a l t e d u n t i l r e c e i p t of r e v i s e d aerodynamic d i s t r i b u t i o n s f ram R-AERO-AD. (DC) Based on t h e Launch Vehicle Reference T r a j e c t o r y documented i n C h r y s l e r Report TN-AP-66-85, and upon r e c e i p t of updated three-sigma t o l e r a n c e s r e c e i v e d from MSFC, t h e launch v e h i c l e performance a n a l y s i s and guidance e r r o r a n a l y s i s a r e c o n t i n u i n g . A l l r e q u i r e d S-IB s t a g e engine-out d a t a have been r e c e i v e d , and t h e p r e l i m i n a r y a b o r t and a 1 t e r n a t e miss i o n s t u d i e s have begun. (DA) D. S a t u r n Apollo A p p l i c a t i o n Program 1. Able a . A s t u d y has been completed t o determine t h e minimum t o t a l v e l o c i t y increment r e q u i r e d t o t r a n s f e r from a 100 NM c i r c u l a r o r b i t w i t h a n i n c l i n a t i o n of 28.5 degrees t o a 6,000 NM c i r c u l a r equat o r i a l o r b i t . An impulsive Hohmann t r a n s f e r technique was used w i t h t h e t o t a l plane change d i s t r i b u t e d between t h e p e r i g e e and apogee burn. The minimum t o t a l v e l o c i t y increment was found t o occur w i t h a f i r s t p l a n e change of 4.34 d e g r e e s , w i t h t h e remaining 24.15 degrees made wFth t h e apogee burn. The t o t a l v e l o c i t y increment was found t o be 3,852 meters p e r second. The s t u d y was made a s a n i n p u t i n t o a S a t u r n V performance c a p a b i l i t y e s t i m a t e f o r P r o j e c t Able. (DAO) b. The f i n a l c o n t r a c t o r p r e s e n t a t i o n s on P r o j e c t Able were It was noted t h a t Goodyear Aerospace Corporation was unable attended. t o f i n d s t a b l e o r b i t s f o r t h e c a s e of a one-sided r e f l e c t o r . This d i s crepancy has been r e s o l v e d i n a s p l i n t e r meeting w i t h t h e c o n t r a c t o r . It was concluded t h a t , w i t h a s l i g h t l y more r e a l i s t i c s i m u l a t i o n , s t a b l e (DAO) o r b i t s could be found f o r t h i s c a s e . c. Pressure Perturbations A paper on s o l a r p r e s s u r e p e r t u r b a t i o n s w r i t t e n by M r . S c o t t P e r r i n e was accepted f o r p r e s e n t a t i o n a t t h e American A s t r o n a u t i c a l S o c i e t y S o u t h e a s t Regional S e c t i o n Symposium, December 5 - 7 , h e l d i n H u n t s v i l l e , Alabama. S t a b l e o r b i t parameters were g e n e r a t e d f o r m i r r o r s of .03 and .06 pounds p e r s q u a r e f o o t weight t o r a t i o f o r o r b i t a l p e r i o d s of 6, 12, and 24 hours. The r e s u l t s were included i n a p r e s e n t a t i o n by M r . C a r t e r , R-ASO, t o t h e Department of Defense. (DAO) �2. ATM a. AIM-Solar E c l i p s e O b s e r v a t i o n An e l l i p t i c a l o r b i t h a s b e e n d e t e r m i n e d f o r t h e ATM which y i e l d s a maximum time of a b o u t 4 . 5 h o u r s d u r i n g w h i c h t h e ATM i s i n t h e umbra of t h e moon. P l a n e changes and v e l o c i t y changes t h a t w i l l be r e q u i r e d t o i n s e r t t h e ATM i n t o t h i s o r b i t u n d e r t h e p r e s e n t l y (DAO) known v e h i c l e c o n s t r a i n t s a r e b e i n g c o n s i d e r e d . ATM 3-D S i m u l a t i o n b. A s t u d y of t h e e f f e c t s of e n v i r o n m e n t f o r c e s and t o r q u e s on t h e A'IIM was begun. A 3-D computer s i m u l a t i o n i n c l u d i n g g r a v i t y g r a d i e n t t o r q u e s and a e r o d y n a m i c f o r c e s i s p l a n n e d . A p r e l i m i n a r y b l o c k d i a g r a m o f t h e E u l e r i a n e q u a t i o n s o f m o t i o n and t h e Work i s b e i n g r e q u i r e d o r t h o g o n a l t r a n s f o r m a t i o n s h a s b e e n completed done on a 1 t e r n a t e methods of t r a n s f o r m i n g and s imp1 i f y i n g a l l e q u a t i o n s for ease i n simulation. (DCA) . The d i g i t a l program t o c a l c u l a t e t h e a n g u l a r a t t i t u d e This of a n o r b i t i n g s p a c e s t a t i o n s u c h a s t h e ATM h a s b e e n c o m p l e t e d . program assumes a r i g i d v e h i c l e s u b j e c t e d t o g r a v i t a t i o n a l and a e r o dynamic t o r q u e s e n c o u n t e r e d i n a c i r c u l a r o r b i t . The a t t i t u d e i s g i v e n by t h e d i r e c t i o n c o s i n e s o f t h e p r i n c i p a l a x i s of t h e v e h i c l e r e l a t i v e t o s p a c e - f i x e d c o o r d i n a t e s y s t e m . The a n g u l a r v e l o c i t y from w h i c h t h e d i r e c t i o n c o s i n e s a r e c a l c u l a t e d i s o b t a i n e d f r o m ~ u l e r ' se q u a t i o n s w h i c h d e s c r i b e t h e r o t a t i o n a l dynamics. One sample problem f o r which t h e s o l u t i o n i s known was a n a l y z e d u s i n g t h e d i g i t a l program, and a r e s u l t i n g a m p l i t u d e was found t o b e i n a g r e e m e n t t o w i t h i n 3 p e r c e n t f o r a small o s c i l l a t i o n about an equilibrium point. The p e r i o d of 3 1 , 5 0 0 . s e c o n d s was a b o u t 1 . 5 p e r c e n t i n e r r o r . (DC) c. Work S t a t e m e n t f o r ATM T i m e l i n e A n a l y s i s and R e s o u r c e Requirements Lockheed h a s b e e n d i r e c t e d t o work w i t h R-AERO-D i n e s t a b l i s h i n g m i s s i o n t i m e l i n e and r e s o u r c e r e q u i r e m e n t s f o r i n c o r p o r a t i o n i n t h e ATM D e s i g n R e f e r e n c e M i s s i o n Document. To e n s u r e a g r e e m e n t on m i s s i o n d e f i n i t i o n , we w i l l r e v i e w and r e v i s e t h e e x i s t i n g Lockheed ATM ephemera, a c t i v i t y , and r e s o u r c e d e f i n i t i o n s . A f t e r t h i s r e v i e w , a work s t a t e m e n t w i l l b e e s t a b l i s h e d . (DAM) d . Combined ~ o r k s h o p / A T M A b r i e f s t u d y was made t o d e t e r m i n e t h e s e p a r a t i o n d i s t a n c e h i s t o r y between t h e S-IVB o r b i t a l workshop and ATM due t o d i f The workshop and ATM f e r e n t i a l d r a g d e c e l e r a t i o n s and o r b i t a l p l a n e s . �were i n s e r t e d i n t o e l l i p t i c a l o r b i t s w i t h v e r y s m a l l e c c e n t r i c i t i e s . Along t h e m a j o r a x i s , t h e o r b i t s were s e p a r a t e d by 30 m e t e r s . The o r b i t s had a s l i g h t l y d i f f e r e n t i n c l i n a t i o n s u c h t h a t t h e maximum l a t e r a l (normal t o t h e o r b i t p l a n e ) s e p a r a t i o n was 30 m e t e r s . Because of t h e d i f f e r e n c e i n d r a g between t h e ATM and workshop, t h e s e b o d i e s become p e r t u r b e d from t h e i r o r i g i n a l o r b i t s . The l o n g i t u d i n a l , l a t e r a l , and a l t i t u d e s e p a r a t i o n d i s t a n c e s and r e q u i r e d t e t h e r l e n g t h ( s l a n t r a n g e ) were computed f o r two h o u r s . It was e x p e c t e d t h a t s t a t i o n k e e p i n g would be performed once p e r o r b i t w h i l e t h e b o d i e s were i n t h e e a r t h ' s shadow. F u r t h e r s t u d y h a s b e e n i n i t i a t e d t o d e t e r m i n e t h e f e a s i b i l i t y of u s i n g t h e t e t h e r between t h e ATM and S-IVB workshop a s a station-keeping device. The r e q u i r e m e n t s a r e t o r e s t r i c t t h e s e p a r a t i o n of t h e ATM by u s i n g a r e e l i n g d e v i c e on t h e t e t h e r between t h e two b o d i e s when t h e y a r e on t h e n i g h t - s i d e o f t h e e a r t h and l e t t i n g them d r i f t d u r i n g o b s e r v a t i o n of t h e s u n . The f i r s t a p p r o a c h t a k e n was t o compute t h e t e t h e r f o r c e s r e q u i r e d t o i n c r e a s e t h e e n e r g y of t h e ATM o r b i t a s s u m i n g t h e S-LVB workshop t o b e o f i n f i n i t e m a s s . It was found t h a t e n e r g y o f t h e ATM c o u l d be i n c r e a s e d b y t h e S-IVB a p p l y i n g a n i m p u l s e t h r o u g h t h e c a b l e . T h i s i m p u l s e can b e a p p l i e d a n y t i m e d u r i n g a 19-minute p e r i o d on t h e d a r k s i d e o f t h e o r b i t when t h e S-IVB l e a d s t h e ATM. The AV r e q u i r e d i s between 0 . 3 and 2 . 2 m e t e r s p e r s e c o n d . The r e s u l t i n g e l l i p s e h a s i n c r e a s e d e n e r g y and momentum, b u t t h e m a j o r a x i s i s r o t a t e d . An i n v e s t i g a t i o n t o f i n d t h e p r o p e r p o s i t i o n on t h e r e s u l t i n g e l l i p s e t o r o t a t e t h e major a x i s back i n t o t h e e a r t h - s u n l i n e i s underway. (DA) The c o n c e p t o f s t a t i o n - k e e p i n g by u s e o f a s o f t t e t h e r between t h e Workshop and ATM is b e i n g i n v e s t i g a t e d . The problem i s b e i n g a p p r o a c h e d by s e e k i n g a s e t of i n i t i a l c o n d i t i o n s s u c h t h a t a t u g on t h e t e t h e r w i l l i n t r o d u c e p e r t u r b a t i o n s t o t h e o r b i t j u s t o p p o s i t e t o t h o s e o f a t m o s p h e r i c d r a g . The e f f e c t o f b o t h t h e m a g n i t u d e and d i r e c t i o n of t h e t u g on t h e p e r i o d and e c c e n t r i c i t y o f t h e r e s u l t i n g o r b i t i s b e i n g p a r a m e t e r i z e d o v e r t h e i n i t i a l o r i e n t a t i o n s o f t h e two o r b i t s a n d t h e p o s i t i o n s a t which t h e t u g s o c c u r . A computer r o u t i n e w r i t t e n f o r t h i s p r o b l e m h a s been f o r m u l a t e d , coded, and checked o u t . The f i r s t r e s u l t s a r e being analyzed. (DAO) 3. Synchronous O r b i t a . A p r e l i m i n a r y working p a p e r t y p e m i s s i o n a n a l y s i s and g r o s s t i m e l i n e have b e e n g i v e n t o t h e r e p r e s e n t a t i v e s o f t h e p r i n c i p a l i n v e s t i g a t o r s f o r r e v i e w and comment. The a n a l y s i s and t i m e l i n e cont i n u e t o b e r e f i n e d a s more i n f o r m a t i o n i s a s s e m b l e d and new e x p e r i m e n t s a r e cons i d e r e d A t p r e s e n t , o n l y t h e p r i m a r y e x p e r i m e n t s ( t h o s e which r e q u i r e o r p r e f e r a synchronous o r b i t ) a r e being c o n s i d e r e d . P l a n s a r e t o s e l e c t a c o m p a t i b l e s e t of p r i m a r y e x p e r i m e n t s , t h e n t h r o u g h f u r t h e r m i s s i o n a n a l y s i s , c h o o s e a s e t o f s e c o n d a r y e x p e r i m e n t s t o f i l l any t i m e and r e s o u r c e s u r p l u s . A l t h o u g h t h e a n a l y s i s i s now b e i n g done by hand f o r q u i c k - l o o k i t e r a t i o n , ~ o c k h e e d ' s t i m e l i n e program now b e i n g s e t (DAM) up w i l l be used f o r t h e f i n a l i t e r a t i o n s . . �b. The u l t r a v i o l e t e x p e r i m e n t h a s b e e n dropped from t h e l i s t of c a n d i d a t e e x p e r i m e n t s and r e p l a c e d w i t h a number o f OSSA-proposed candidates. Data a r e s t i l l l a c k i n g on t h e s e e x p e r i m e n t s . Another g r o s s t i m e l i n e w i l l b e g e n e r a t e d a s t h i s i n f o r m a t i o n becomes a v a i l a b l e . (DAM) 4. Thermo a. P r o j e c t Thermo An e f f o r t i s b e i n g expended on a p r o j e c t proposed by P&VE L a b o r a t o r y c a l l e d "Thermo," which i n v o l v e s t h e performance of f l u i d mechanics and h e a t t r a n s f e r e x p e r i m e n t s under c o n t r o l l e d low g c o n d i t i o n s i n o r b i t . The p r o j e c t i s b e i n g c o n s i d e r e d a s a p a r t o f t h e combined S-IVB workshop/ATM c o n c e p t of D r . M u e l l e r . Thermo would cons i s t o f a CSM, LM, RACK, and Thermo e x p e r i m e n t package b e i n g b r o u g h t up on some v e h i c l e l a t e r t h a n 212. The v e h i c l e w i t h t h e Thermo e x p e r i m e n t s would i n i t i a l l y dock w i t h t h e S-IVB workshop i n a 260 NM c i r c u l a r o r b i t . The Thermo e x p e r i m e n t r e q u i r e s m a i n t a i n i n g a c c e l e r a t i o n l e v e l s of lo-", lo-.', and 10'" g ' s , which a r e r e q u i r e d f o r p e r f o r m i n g t h e e x p e r i m e n t s . The method c o n s i d e r e d i n t h i s s t u d y t o a c c o m p l i s h t h e s e a c c e l e r a t i o n l e v e l s i s f o r t h e ~ ~ / R A c ~ / ~ h et romcoa s e o f f from t h e S-IVB workshop and t h r u s t normal t o t h e o r b i t a l p l a n e . T h i s method r e s u l t s i n a r e s t o r a t i o n of t h e o r i g i n a l o r b i t a f t e r a s p e c i f i e d time. A f t e r l e a v i n g t h e workshop i n a f r e e mode and t h r u s t i n g a t a p r e s c r i b e d g l e v e l f o r a p p r o x i m a t e l y two h o u r s , r e t u r n t o t h e workshop i s made by p e r f o r m i n g a v e r y small p l a n e change c o r r e c t i o n . A f t e r a s p e c i f i e d t i m e f o r s e t t l i n g o u t t r a n s i e n t s i n t h e e x p e r i m e n t f l u i d s , t h e p r o c e d u r e would b e r e p e a t e d u n d e r a new g l e v e l . The AV c o r r e c t i o n i s made when t h e two b o d i e s a r e a t t h e i r n e a r e s t a p p r o a c h - a p p r o x i m a t e l y 160 m e t e r s f o r t h e l o m 3 g l e v e l c a s e , which o c c u r s a p p r o x i m a t e l y two h o u r s a f t e r l e a v i n g the workshop. Maximum s e p a r a t i o n i n t h e two-hour p e r i o d i s approxima t e l y g l e v e l , 1 . 5 km f o r t h e lo-" g l e v e l and .15 km f o r 15 km f o r t h e t h e 10'" g l e v e l a c c e l e r a t i o n . Maximum s e p a r a t i o n may b e a f a c t o r s i n c e Thermo i s b e i n g c o n s i d e r e d a s a manned LM. Atmospheric d r a g o f a p p r o x i m a t e l y l o - " g ' s m a g n i t u d e i s c o n s i d e r e d t o be a c t i n g on b o t h b o d i e s i n o r b i t . T h i s method o f p r o d u c i n g t h e r e q u i r e d a c c e l e r a t i o n l e v e l s f o r t h e e x p e r i m e n t s , a l o n g w i t h s p i n up and i n - p l a n e t h r u s t i n g modes, i s b e i n g e v a l u a t e d by t h e P r o j e c t Thermo P a n e l . The a d v a n t a g e s o f t h e normal t h r u s t method i n c l u d e p o s i t i o n r e p e a t a b i l i t y i n o r b i t w i t h s m a l l e r AV c o r r e c t i o n s t o rendezvous and a l e s s complex g u i d a n c e and c o n t r o l . A d i s a d v a n t a g e i s t h e added w e i g h t o f t h r e e s e p a r a t e t h r u s t l e v e l motors. (DAO) A s i n g l e l a u n c h v e h i c l e f e a s i b i l i t y s t u d y was made on a CSM/MSFC f u l l r a c k c o n f i g u r a t i o n . L o n g i t u d i n a l t h r u s t made f o r a 14-day m i s s i o n was c o n s i d e r e d ; t h e w e i g h t o f t h i s con£ i g u r a t i o n exceeded t h e s i n g l e l a u n c h c a p a b i l i t y o f a n u p r a t e d S a t u r n I v e h i c l e by a l m o s t - �2 , 0 0 0 pounds. System t r a d e o f f s ( i . e . , f u e l c e l l s v s b a t t e r i e s and r o t a t i o n a l v s l o n g i t u d i n a l a c c e l e r a t i o n s y s t e m s ) and m i s s i o n d u r a t i o n r e d u c t i o n s ~ w o u l db e r e q u i r e d t o make t h e s i n g l e l a u n c h Thermo m i s s i o n feasible. (DAO) b. O r b i t a l S l o s h T e s t Requirements A memorandum d e t a i l i n g t h e low g s l o s h t e s t r e q u i r e m e n t s of t h e Aero-Astrodynamics L a b o r a t o r y h a s b e e n p u b l i s h e d . These r e q u i r e m e n t s would a p p l y t o t h e p r o p o s e d P r o j e c t Thermo o r a n y o t h e r o r b i t a l f a c i l i t y i n w h i c h t h e o p p o r t u n i t y f o r low g t e s t i n g m i g h t e x i s t . To o b t a i n t h e n e c e s s a r y i n f o r m a t i o n , a minimum o f t h r e e t e s t s was s p e c i f i e d . A p p r o x i m a t e l y e i g h t e e n h o u r s o f low g t e s t t i m e would b e required. A memorandum i s b e i n g p r e p a r e d w h i c h documents t h e r e s u l t s t o d a t e o f a low g l o n g i t u d i n a l a c c e l e r a t i o n s t u d y . A s p l i n t e r m e e t i n g between P&VE, Advanced S y s t e m s , and Aero-Astrodynamics p e r s o n n e l was h e l d t o d e t e r m i n e t h e r e s p o n s i b i l i t i e s and r e q u i r e m e n t s o f t h e Aero-Astrodynamics L a b o r a t o r y i n P r o j e c t Thermo. Mission p r o f i l e s a r e t o be s t u d i e d f o r the following: a dual launch i n t e g r a t e d w i t h the c l u s t e r ; a s i n g l e launch i n t e g r a t e d w i t h t h e c l u s t e r ; a d u a l 1-aunch i n d e p e n d e n t of t h e c l u s t e r ; and a s i n g l e l a u n c h i n d e p e n d e n t of the c l u s t e r . The p r i m a r y c a r r i e r v e h i c l e con£ i g u r a t i o n s t i l l r e m a i n s t h e CSM/LEM (A/S) and MSFC h a l f r a c k , v i a d u a l l a u n c h , s i n c e i t e x c e e d s t h e s i n g l e l a u n c h c a p a b i l i t y o f t h e S a t u r n IB b y more t h a n 7 , 0 0 0 pounds. The a b o v e memorandum w i l l b e p u b l i s h e d t o p r o v i d e t r a j e c t o r i e s i n c o r p o r a t i n g l o n g d u r a t i o n low g a c c e l e r a t i o n e x p e r i m e n t t i m e l i n e a s o u t l i n e d i n a Douglas A i r c r a f t C o r p o r a t i o n (DAC) p r o g r e s s r e p o r t on P r o j e c t Thermo. Even t h o u g h DAC h a s p r o v i d e d a n e x p e r i m e n t timeline with d e t a i l e d s h o r t duration a c c e l e r a t i o n pulsing, i t was decided t o d e a l o n l y w i t h broad a c c e l e r a t i o n h i s t o r i e s a t t h i s time. T h i s d e c i s i o n was made b e c a u s e t h e p r e s e n t e x p e r i m e n t t i m e i s e x p e c t e d t o be d r a s t i c a l l y a l t e r e d i n e a r l y December. (DD) 5. Odyssey S u p p o r t i s b e i n g g i v e n t o t h e P r o j e c t Odyssey P a n e l d u r i n g t h e f e a s i b i l i t y and c o n c e p t u a l d e s i g n p h a s e . By a s u r v e y of t h e p r e v e h i c l e s , it appears t h a t the s e n t l y p r o p o s e d combined ~ o r k s h o p / ~ T M Odyssey I package c a n b e i n t e g r a t e d i n t o t h e 212 m i s s i o n i f t h e t o t a l S i n c e t h e 212 m i s s i o n package w e i g h t c a n r e m a i n below 5 , 0 0 0 pounds. would be unmanned and w i l l g o t o a 240 NM c i r c u l a r o r b i t (20 NM below t h e workshop t o a l l o w r e n d e z v o u s ) , t h e p r o c e d u r e would b e t o j e t t i s o n t h e n o s e cone and s e p a r a t e t h e Odyssey p a c k a g e f r o m t h e t o p of SLA. �I t would t h e n be o u t o f t h e way when t h e CSM,brought up on 2 1 1 r e n d e z v o u s , docks and e x t r a c t s t h e LM/RAcK/ATM. S i n c e t h e d e s i r e d Odyssey o r b i t i s a n e l l i p s e o f 180 km by 1220 km, t h e package would c o n t a i n a s o l i d p r o p e l l a n t motor. The package would b e a t t i t u d e - s t a b i l i z e d , and t h e motor would be ground-commanded t o t r a n s f e r t h e Odyssey package t o t h e d e s i r e d o r b i t . An i m p u l s i v e s t u d y t o d e f i n e t h e t r a n s f e r p a t h a n g l e , v e l o c i t y i n c r e m e n t , and t h e r e s u l t i n g motor s i z i n g i s under way. A p e r t u r b a t i o n s t u d y o f p a t h a n g l e a c c u r a c y and motor impulse t o l e r a n c e s may be b e n e f i c i a l t o h e l p i n t h e s e l e c t i o n of o f f - t h e - s h e l f g u i d a n c e e l e m e n t s and s o l i d p r o p e l l a n t motor. A t r a d e o f f of o r b i t a l p a r a m e t e r s may b e r e q u i r e d t o f i t o f f - t h e - s h e l f motors. (DAO) As a r e s u l t of t h e November 17 m e e t i n g of t h e P r o j e c t Odyssey p a n e l w i t h D r . C . L u n d q u i s t of t h e S m i t h s o n i a n A s t r o p h y s i c a l Observatory ( p r i n c i p a l i n v e s t i g a t o r f o r the atmospheric s t r u c t u r e e x p e r i m e n t ) , t h e planned o r b i t was changed. The p e r i g e e a l t i t u d e was lowered from 180 km t o 160 km and t h e apogee was r a i s e d from 1 , 2 2 0 km t o 1 , 7 5 0 km. The r e a s o n f o r t h i s change i s t o g i v e a t m o s p h e r i c d e n s i t y d a t a o v e r a g r e a t e r r a n g e of a l t i t u d e s . As a r e s u l t , t h e P r o j e c t Odyssey e x p e r i m e n t package t o t a l v e l o c i t y i n c r e m e n t (AV) i n c r e a s e d from 521 m/s t o 6 9 9 m/s. The major p o r t i o n of t h i s l a r g e A , i s t h e r e q u i r e d f l i g h t p a t h a n g l e change o f 4.78 d e g r e e s r e s u l t i n g a t t h e i n t e r s e c t i o n of h i g h e n e r g y e l l i p s e w i t h t h e 240 NM c i r c u l a r o r b i t p r e s e n t l y planned f o r t h e 211 v e h i c l e t h a t w i l l b e c a r r y i n g P r o j e c t Odyssey a s a piggyback payload. As t h e m i s s i o n s and payloads of v e h i c l e s 212 and s u b s e q u e n t a r e made f i r m , i t m i g h t be p o s s i b l e t o c a r r y P r o j e c t Odyssey i n a v e h i c l e w i t h a lower p e r i g e e o r c i r c u l a r o r b i t . T h i s would r e d u c e somewhat t h e t o t a l v e l o c i t y i n c r e m e n t (AV) r e q u i r e d . (DAO) 'E. Other P r o j e c t s Development of Math Models f o r R-AERO-D Use: The U s e r ' s Document f o r m a t h e m a t i c a l models and e n g i n e e r i n g t e c h n i q u e s used i n t h e modules f o r R-AERO-D, p r e p a r e d under c o n t r a c t by Lockheed, h a s been comp l e t e d and checked, by R-AERO-DM, f o r a c c u r a c y and c o m p l e t e n e s s . The s c o p e o f work r e q u i r e s t h a t math models be developed f o r r i g i d and f l e x i b l e body a n a l y s i s . I t h a s become e v i d e n t d u r i n g development t h a t t h e u s e r document f o r m a t makes i t manageable f o r t h e programmer t o a s s i g n and keep t r a c k of t h e v a r i o u s l a b e l common s t o r a g e a r e a s needed by any s u b r o u t i n e (DMILockheed) i n t h e MARVESS s ys tem. F. General Mission P r o f i l e M a r t i n Timeline A n a l y s i s Program: One of t h e decks of t h e s e t of MArtin T i m e l i n e A n a l y s i s Programs, t h e S c h e d u l i n g A n a l y s i s Model, �i s r u n n i n g and h a s b e e n checked o u t w i t h a sample s e t of i n p u t . The O r b i t P o s i t i o n A n a l y s i s Model, t h e Grouping A n a l y s i s Model, and t h e AAP Data Bank r e m a i n t o b e checked o u t . Martin-Denver is sending a r e p r s s e n t a t i v e t o d i s c u s s t h e s y s tem problems e n c o u n t e r e d and t o a s s i s t i n implementing t h e r e m a i n i n g d e c k s . (~AM/~artin) 2. Dynamics and C o n t r o l a. D e s i g n C r i t e r i a f o r C o n t r o l o f Space V e h i c l e s : A d r a f t of t h e monograph "Rendezvous and ~ o c k i n g "by D a n i e l C h i a r a p p a h a s b e e n r e v i e w e d , and a l i s t o f s u g g e s t e d r e v i s i o n s and c o r r e c t i o n s was p r e p a r e d and r e t u r n e d t o t h e c o n t r a c t o r . Only minor r e v i s i o n s were s u g g e s t e d f o r t h i s i n £o r m a t i v e monograph. Of t h e s i x t e e n monographs b e i n g p r e p a r e d under C o n t r a c t NAS8-11494, s e v e n have b e e n r e c e i v e d i n a form s a t i s f y i n g c o n t r a c t u a l o b l i g a t i o n s . These have b e e n documented a s a c o n t r a c t o r p u b l i c a t i o n , and a r e a v a i l a b l e t o C e n t e r p e r s o n n e l : (1) S h o r t P e r i o d Dynamics GDC-DDE-65-055 O c t . 1965 (2) T r a j e c t o r y Equations GDC-DIIE-65-058 Nov. 1965 (3) L i n e a r Systems GDC-DDE-66-019 A p r i l 1966 (4) Nonl i n e a r Sys tems GDC-DDE-65-056 S e p t . 1965 (5) Stochastic Effects GDC-DDE-66-006 Feb. 1966 (6) O p t i m i z a t i o n Methods GDC-DDE-66-026 J u l y 1966 (7) Man i n t h e Loop GDC-DDE-66-023 May 1966 NASA comments and s u g g e s t e d r e v i s i o n s have b e e n s e n t t o t h e c o n t r a c t o r f o r two a d d i t i o n a l monographs. Two o f t h e monographs a r e b e i n g r e v i e w e d by NASA, and f i v e a r e s t i l l i n v a r i o u s s t a g e s o f p r e p a r a t i o n by t h e cont r a c t o r . A l l o f t h e s i x t e e n monographs w i l l b e e d i t e d f u r t h e r f o r i n c l u s i o n w i t h o t h e r monographs i n t o one o f a s e r i e s of volumes e n t i t l e d " S t a b i l i t y , Guidance, and C o n t r o l Design C r i t e r i a " by E l e c t r o n i c s Research Center. ( ~ C A / ~ e n e r a~ly n a m i c s / ~ o n v a i r ) The monograph,"Component ~ y n a m i c ,sI 1 by J . G. Rolland C o l l e t t e was r e c e i v e d November 23, 1966. The p u r p o s e s of t h i s mono(1) t o p r e s e n t t h e f o r m u l a t i o n of m a t h e m a t i c a l graph a r e twofold: models f o r s e n s o r s ( g y r o s c o p e s , a c c e l e r o m e t e r s , e t c . ) and a c t u a t i n g e l e m e n t s which a r e a p p l i c a b l e t h r o u g h o u t t h e f r e q u e n c y r a n g e of i n t e r e s t and (2) t o a c c o u n t f o r phenomena t h a t can i n f l u e n c e t h e r e s u l t s o f a n a l y s e s . Copies of t h i s monograph w i l l b e d i s t r i b u t e d t o a p p r o p r i a t e p e r s o n n e l f o r t h e i r comments and s u g g e s t e d r e v i s i o n s . (DcA/ ~ e n e r a l~ y n a m i c/s~ o n v iar ) �b. Assessment of S l o s h Coupling w i t h Space Vehicles A f i n a l r e p o r t documenting t h i s s t u d y was r e c e i v e d t h i s month. A v e r y r i g o r o u s d e r i v a t i o n of t h e v e h i c l e e q u a t i o n s of motion was performed, i n c l u d i n g l i q u i d p r o p e l l a n t , by using a summation of p e r t u r b a t i o n from a known r e f e r e n c e motion i n which v e h i c l e body axes remain c o i n c i d e n t w i t h the r e f e r e n c e a x i s . The e f f e c t s of the l i q u i d i n t h e p e r t u r b a t i o n e q u a t i o n s were i s o l a t e d and i d e n t i f i e d . On r e p l a c i n g t h e l i q u i d motion by a simple mechanical system, t h e p l a n a r p e r t u r b a t i o n e q u a t i o n s of motion f o r t h e v e h i c l e were a g a i n d e r i v e d . Comparison of t h e two s e t s of e q u a t i o n s showed t h a t t h e p r e s e n t model d u p l i c a t e d t h e r e s u l t s o b t a i n e d from t h e o r i g i n a l hydrodynamical simulat i o n . The o n l y d i s c r e p a n c i e s i n t h e MSFC p r e s e n t f o r m u l a t i o n i s a term i n t h e cons tancy-of - p r e s s u r e e q u a t i o n p r o p o r t i o n a l t o t h e a n g u l a r d i s placement o f the body axes w i t h r e s p e c t t o t h e r e f e r e n c e a x i s . This e r r o r a r o s e when t h e e q u a t i o n s of motion were n o t p e r t u r b e d , b u t were (~~S/Convair) a r b i t r a r i l y l i n e a r i z e d w i t h r e s p e c t t o body r a t e s . c. Drift-Minimum and Load Minimum C o n t r o l An analog computer s i m u l a t i o n was i n i t i a t e d t o s t u d y t r a n s i e n t s and s t e a d y - s t a t e v a l u e s of r e s u l t a n t v e h i c l e v a r i a b l e s when e i t h e r drift-minimum o r load-minimum c o n t r o l laws a r e used. The equat i o n s of motion, w r i t t e n i n body-fixed c o o r d i n a t e s , have been programmed. Graphs of t h e v a r i a b l e s of i n t e r e s t ( a t t i t u d e e r r o r , a n g l e of a t t a c k , e t c . ) were o b t a i n e d f o r b o t h c o n t r o l laws, a s w e l l a s f o r normal gyro c o n t r o l , t o compare t h e r e s u l t s . The t h e o r e t i c a l s t e a d y - s t a t e v a l u e of each v a r i a b l e was c a l c u l a t e d and checked w i t h t h e r e s u l t o b t a i n e d (DC) from the computer. d. A Method f o r t h e Determination of Empirical Formulas f o r Launch Vehicle Angle of A t t a c k and Engine Deflection The i n t e r n a l n o t e , "A Method f o r t h e Determination of Empirical Formulas f o r Launch Vehicle Angle of A t t a c k and Engine D e f l e c t i o n , " October 6 , 1966, IN-AERO-16-55, has been d i s t r i b u t e d . The computational procedure developed i n t h i s n o t e i s based on c l a s s i c a l l a r g e sample l e a s t s q u a r e s methods. The f e a s i b i l i t y of extending t h i s method t o t h e d e t e r m i n a t i o n of e m p i r i c a l formulas f o r t h e maximum bending moment w i t h t h e system being f o r c e d by an ensemble of winds i s being i n v e s t i g a t e d . (DM) e. Paper f o r AIAA 5 t h Aerospace Science Meeting A paper e n t i t l e d , "The I n f l u e n t i a l Aspects of Atmosp h e r i c D i s t u r b a n c e s on Space Vehicle Design Using S t a t i s t i c a l Approaches f o r A n a l y s i s , " has been prepared f o r p r e s e n t a t i o n a t t h e AIAA 5 t h �Aerospace Sciences Meeting i n New York, January 23-26, 1967. This paper i s t o be p r e s e n t e d i n t h e Atmospheric F l i g h t Mechanics s e s s i o n , Wednesday, (DD) January 25. f. Paper f o r P u b l i c a t i o n i n J o u r n a l of S p a c e c r a f t and Rockets A paper e n t i t l e d , "A Technique f o r Analyzing C o n t r o l Gains Us ing Frequency Response Methods ," has been a c c e p t e d f o r p u b l i c a t i o n by J o u r n a l of S p a c e c r a f t and Rockets. (DD) g. C o n t r a c t w i t h General Dynamics The c o n t r a c t w i t h General Dynamics on s l o s h i n g a n a l y s i s has been completed. F i n a l r e p o r t s have been o b t a i n e d : (1) " B a f f l i n g of F l u i d S l o s h i n g i n C y l i n d r i c a l Tanks ." This r e p o r t p r e s e n t s a complete t h e o r e t i c a l d i s c u s s i o n of t h e e f f e c t s of a n a n n u l a r r i n g b a f f l e on t h e behavior of l i q u i d w i t h i n a r i g h t c i r c u l a r c y l i n d e r . The problem i s solved by assuming two p o t e n t i a l f u n c t i o n s , one v a l i d i n t h e r e g i o n above t h e b a f f l e , t h e o t h e r v a l i d i n t h e r e g i o n below t h e b a f f l e . Matching t h e two f u n c t i o n s i n t h e p l a n e of t h e b a f f l e l e a d s t o a d u a l s e r i e s . Having t h e s o l u t i o n of t h e s e s e r i e s , we can c a l c u l a t e t h e displacement of t h e f r e e s u r f a c e a s w e l l a s t h e l i q u i d s p r e s s u r e , f o r c e s and moments. ( 2 ) "Analysis of F l u i d Sloshing.'' This r e p o r t extends previous work by d e s c r i b i n g t h e behavior of p r o p e l l a n t due t o o r b i t i n g motion w i t h s i x d e g r e e s of freedom when t h e c e n t e r of r o t a t i o n i s o f f t h e a x i s of the v e h i c l e . Some work i s included on t h e e f f e c t of b a f f l e s and tank e l a s t i c i t y . A d i g i t a l r o u t i n e f o r computing the s l o s h param( I I D / ~ e n e r a lDynamics) e t e r s i s included. h. C o n t r a c t w i t h Southwest Research I n s t i t u t e The f i n a l r e p o r t "Experimental and T h e o r e t i c a l S t u d i e s of Liquid S l o s h i n g a t Simulated Low G r a v i t i e s " has been r e c e i v e d . This work i s unique i n t h a t i t p r e s e n t s t h e f o r c e s and moments a c t i n g on t h e p r o p e l l a n t tank f o r Bond numbers between 10 and 200. The r e s u l t s a r e compared w i t h t h e o r e t i c a l p r e d i c t i o n s of t h e mechanical model, and good c o r r e l a t i o n between t h e o r y and experiment i s shown. A f i n a l r e p o r t , "A Comparison of F l e x i b l e and Rigid Ring B a f f l e s f o r S l o s h Suppression," has been r e c e i v e d . A t e s t program t o determine t h e e f f e c t i v e n e s s of f l e x i b l e r i n g b a f f l e s a s l i q u i d s l o s h s u p p r e s s o r s was conducted. A comparison of f l e x i b l e and r i g i d r i n g b a f f l e s i s p r e s e n t e d i n terms of l i q u i d damping, f i r s t mode s l o s h i n g �r e s o n a n t frequency, and maximum b a f f l e d e p t h f o r no r o t a t i o n a l s l o s h . R e s u l t s show t h a t f l e x i b l e b a f f l e s can reduce b a f f l e weight by a cons i d e r a b l e amount; however, t h e p r o p e r t i e s of t h e b a f f l e m a t e r i a l a t It may a l s o be necescryogenic temperatures should be b e t t e r known. s a r y t o i n v e s t i g a t e t h e s t r e s s e s a t t h e b a f f l e i n n e r edge t o i n s u r e t h a t t h e b a f f l e does n o t t e a r . (DD) i. C o n t r a c t w i t h Lockheed The f i n a l r e p o r t , " S o l u t i o n s of Systems of Nonlinear Equations," p r e s e n t s t h e r e s u l t s of a s t u d y t o develop a method and computer program f o r s o l v i n g an a r b i t r a r y , simultaneous system of nonl i n e a r a l g e b r a i c and t r a n s c e n d e n t a l e q u a t i o n s . The f i n a l r e s u l t i s a composite computer program which encompasses a " l i m i t e d " spectrum of b a s i c a l l y d i f f e r e n t numerical methods g r a d i e n t , m i n i m i z a t i o n , and s e a r c h t e c h n i q u e s . T e s t r e s u l t s a r e included a s a b a s i s f o r comparison of t h e d i f f e r e n t methods. (DD) - VIII. FLIGHT TEST ANALYSIS DIVISION A. Special Projects Office 1. The AS-203 and AS-202 ~ l i ~ Ehv at l u a t i o n Reports were distributed recently. 2. A review copy of t h e S a t u r n V F l i g h t T e s t E v a l u a t i o n P l a n , which has been d i s t r i b u t e d , p r e s e n t s e v a l u a t i o n procedures and i n t e r f a c e s , and t h e a n a l y s i s and r e p o r t i n g r e s p o n s i b i l i t i e s of the v a r i o u s o r g a n i z a t i o n s r e p r e s e n t e d on t h e S a t u r n F l i g h t E v a l u a t i o n Working Group. The p l a n i s being reviewed by a l l elements of t h e FEWG i n c l u d i n g s t a g e c o n t r a c t o r s . FEWG s p l i n t e r meetings a t DAC and S&ID have been scheduled f o r t h e week of December 5 , 1966 t o d i s c u s s proposed changes. B. F l i g h t E v a l u a t i o n Branch 1. Saturn F I3 a. S-IB P r e s s u r e Environment A d i g i t a l program, which has been w r i t t e n t o complement p r e s e n t e v a l u a t i o n programs f o r t h e S a t u r n IB p r e s s u r e environment, w i l l be used t o e v a l u a t e b u r s t i n g l o a d s i n t h e forward compartment (SM, SLA, e t c . ) u s i n g measured i n t e r n a l p r e s s u r e s w i t h t h e experimental e s t e r n a l flow f i e l d . R e s u l t s from t h i s a n a l y s i s w i l l be p r e s e n t e d i n a memorandum a l o n g w i t h measured AS-203 p r e s s u r e d i f f e r e n t i a l s . �The Tracker E r r o r Model Study (TEMS) on AS-202 t r a c k i n g d a t a i s b e i n g p u b l i s h e d . This s t u d y i s o l a t e s t h e i n d i v i d u a l e r r o r s t h a t may have been p r e s e n t i n t h e a c t u a l t r a c k i n g d a t a r e c e i v e d from the E a s t e r n T e s t Range on each v e h i c l e . By accumulating t h i s i n f o r m a t i o n f o r s e v e r a l v e h i c l e s , we w i l l be a b l e t o use t h e d a t a more e f f e c t i v e l y , determine r e a l i s t i c t r u n c a t e d e r r o r models t o i n c o r p o r a t e i n t h e t r a j e c t o r y programs, and perhaps g i v e some feedback t o t h e E a s t e r n T e s t Range on t h e a c t u a l performance of t h e t r a c k i n g systems. On AS-202, d a t a from f i v e r a d a r s , P a t r i c k , M e r r i t t I s l a n d , Grand Bahama, Grand Turk, and Antigua, a l o n g w i t h d a t a from GLOTRAC S t a t i o n I, were a n a l y z e d . The r e s u l t s were q u i t e encouraging i n t h a t , f o r most of t h e systems a n a l y z e d , t h e r e were s i m i l a r i t i e s between t h e r e s u l t s o b t a i n e d on AS-202 and t h e r e s u l t s o b t a i n e d on AS-201. The SA-203 t r a c k i n g d a t a a r e being a n a l y z e d ; p r e l i m i n a r y r e s u l t s should be a v a i l a b l e soon. (1) Emergency D e t e c t i o n System The d e a c t i v a t i o n time f o r two-engines-out a u t o m a t i c a b o r t on AS-204 w i l l be l i f t - o f f p l u s 100 seconds. I f one engine f a i l s b e f o r e 40 seconds, t h e two-engines-out a u t o m a t i c a b o r t s i g n a l t o d i s a b l e w i l l be delayed u n t i l 120 seconds. This d e c i s i o n was made i n the E i g h t e e n t h Crew S a f e t y Panel meeting. (2) P r e f l i g h t Control AS-204 i s t h e f i r s t S a t u r n 1B v e h i c l e w i t h a " c h i - f r e e z e " program. This program w i l l b e a c t i v a t e d by a n engine f a i l u r e which occurs b e f o r e 65 seconds of f l i g h t . Engine-out s t u d i e s i n d i c a t e no s e v e r e c o n t r o l o r l o a d s problem i n t h e S-IB s t a g e and no u n d e s i r a b l e p o s t s e p a r a t i o n S-IVB s t a g e dynamic t r a n s i e n t s f o r a s i n g l e engine f a i l u r e . No c o l l i s i o n o r c o n t r o l problem e x i s t s f o r t h e nominal o r off-nominal S-IBIS-IVB s e p a r a t i o n . A 99 p e r c e n t p r o b a b i l i t y of successful separation exists with a single retro-rocket failure. 2. Saturn V a. Emergency D e t e c t i o n System Eleven S a t u r n V f a i l u r e modes have been i n v e s t i g a t e d by TBC. The a n a l y s i s shows t h a t no EDS auto-.abort l i m i t is s a t i s f a c t o r y f o r a l l f a i l u r e modes. Engine and a c t u a t o r m a l f u n c t i o n s a l l o w no p o s i t i v e warning time. TBC recommendations a r e a s f o l l o w s : �b. (1) V e r i f y t h e launch v e h i c l e s t r u c t u r a l c a p a b i l i t y . (2) Determine a combination of c o n t r o l system d e s i g n and " c h i - f r e e z e " schedule t h a t improves v e h i c l e c o n t r o l l a b i l i t y and reduces l o a d s f o r malfunctioned vehicle. AS-501 - P r e f l i g h t Control TBC has d e l i v e r e d copies of t h e AS-501 dynamics a n a l y s i s r e p o r t . The r e p o r t i s s a t i s f a c t o r y and i s expected t o be d i s t r i b u t e d soon. I n f l i g h t wind l i m i t s f o r t h e AS-501 have been r e c e i v e d from TBC. A t t h e most c r i t i c a l a l t i t u d e (10 km), t h e v e h i c l e i s wind-limited t o 25, 100 and 40 m/s f o r head, t a i l and c r o s s winds, r e s p e c t i v e l y . The p r o b a b i l i t y of n o t exceeding t h e s e l i m i t s i s 99 p e r c e n t f o r t h e months of February and March. These wind l i m i t s may be s l i g h t l y decreased because of a r e v i s i o n of s t r u c t u r a l l i m i t s (based on a, f3 and Mach) p r e s e n t e d i n memorandum R-P&VE-SJ-66-264, " I n f l i g h t S t r u c t u r a l Limits f o r S a t u r n V AS-501, AS-502, and AS-503," dated November 21, 1966. Launch r e l e a s e wind r e s t r i c t i o n s imposed by t h e s p a c e c r a f t s t r u c t u r e a r e a peak wind of 28 k n o t s (95 p e r c e n t ) . A t p r e s e n t , two a r e a s a r e b e i n g i n v e s t i g a t e d f u r t h e r : l i f t o f f and c h i - f r e e z e program. 3. S a t u r n Apollo A p p l i c a t i o n s A proposed p l a n f o r p r o c e s s i n g and handling of d a t a f o r Apollo A p p l i c a t i o n s Experiments i s being prepared. There i s a n a p p a r e n t need f o r a n organized system of p r o c e s s i n g and handling of t h i s e x p e r i ment d a t a because of t h e l a r g e q u a n t i t y and t h e complexity of d a t a involved. Once a n o r g a n i z a t i o n i s s e t u p f o r t h i s purpose, i t can o p e r a t e more e f f i c i e n t l y f o r a l l experiments than t h e i n d i v i d u a l e x p e r i ments done independently. Problems faced on each i n d i v i d u a l experiment can c o n t r i b u t e t o improvements on succeeding experiments i f t h e same o r g a n i z a t i o n handles a l l of t h e experiments. This would n o t be t r u e i f each experiment were handled by d i f f e r e n t o r g a n i z a t i o n s s i n c e they would n o t have t h e advantage of p a s t e x p e r i e n c e . The proposed p l a n f o r p r o c e s s i n g and handling of e x p e r i mental d a t a c a l l s f o r R-AERO-F and R-COMP t o be "base" o r g a n i z a t i o n s of a working group on a l l experiment d a t a . These o r g a n i z a t i o n s w i l l be supplemented by o r g a n i z a t i o n s concerned w i t h each i n d i v i d u a l experiment. This means t h a t ,from one experiment t o t h e n e x t , t h e o r g a n i z a t i o n s w i l l change e x c e p t f o r t h e two "base" o r g a n i z a t i o n s (R-AERO-F and R-COMP) . �4. Contracts a. S a t u r n IB Systems C o n t r a c t (CCSD, New O r l e a n s ) (1) AS-202 P o s t f l i g h t T r a j e c t o r y CCSD has p u b l i s h e d t h e p o s t f l i g h t t r a j e c t o r y r e p o r t on AS-202. It was due O c t o b e r 25 ( l a u n c h p l u s 60 d a y s ) . It was completed f o r MSFC r e v i e w a week e a r l y . The r e p o r t was e x c e l l e n t , d e m o n s t r a t i n g t ' h a t CCSD h a s t h e c a p a b i l i t y t o assume r e s p o n s i b i l i t y o f t h e i n t e r m e d i a t e t r a j e c t o r y (7 d a y s ) , f i n a l t r a j e c t o r y (14 d a y s ) and t h e t r a j e c t o r y r e p o r t (60 d a y s ) b e g i n n i n g w i t h AS-204. (2) AS-202 S-IB S t a g e P r o p u l s i o n F l i g h t S i m u l a t i o n The AS-202, S-IB performance a n a l y s i s of t h e s t a g e p r o p u l s i o n s y s tem conducted by CCSD (Michoud) and MSFC (AERO-FFR) w i t h Some d i f f i c u l t y was t h e f l i g h t s i m u l a t i o n programs has b e e n completed. e n c o u n t e r e d i n m a t c h i n g t h e Observed Mass P o i n t T r a j e c t o r y (OMPT) b e c a u s e o f t h e r o u g h n e s s o f t h e a c c e l e r a t i o n s from OMPT d u r i n g t h e f i r s t 25 s e c o n d s of f l i g h t . The problem was s o l v e d by u s i n g a c c e l e r a t i o n s from t h e ST-124M g u i d a n c e s y s tem. The a c c e l e r a t i o n s d u r i n g t h i s from OMPT produced a n u n r e a l i s t i c s h a p e i n t h e aerodynamic d r a g c o e f f i c i e n t which i n t u r n a f f e c t e d t h e p r o p u l s i o n p a r a m e t e r c o r r e c t i o n s . CCSD and MSFC a g r e e w i t h i n a b o u t 0 . 1 p e r c e n t on t h e p r o p u l s i o n s y s t e m performance a n a l y s i s . This agreement demonstrates t h a t CCSD has t h e c a p a b i l i t y t o assume t h e r e s p o n s i b i l i t y f o r d e t e r mining p r o p u l s i o n s y s t e m performance by f l i g h t s i m u l a t i o n f o r a l l f u t u r e S a t u r n IB v e h i c l e s . b. S a t u r n V Systems C o n t r a c t (The Boeing Company) TBC i s s c h e d u l e d t o assume t h e p o s t f l i g h t t r a j e c t o r y Only r e s p o n s i b i l i t y on t h e S a t u r n V v e h i c l e s b e g i n n i n g w i t h AS-504. r e c e n t l y h a s TBC r e a l i z e d a l l of t h e d e t a i l s and c o m p l e x i t i e s i n v o l v e d i n t h i s r e s p o n s i b i l i t y . Biweekly m e e t i n g s a r e now b e i n g h e l d t o r e v i e w work done by TBC and t o e n s u r e t h e i r moving i n t h e p r o p e r d i r e c t i o n . TBC i s s c h e d u l e d t o do a p a r a l l e l e f f o r t w i t h MSFC on AS-501. They w i l l u s e MSFC-developed programs i n t h e p o s t f l i g h t t r a j e c t o r y a r e a . Much work r e m a i n s t o b e done t o d e v e l o p t h e TBC c a p a b i l i t y t o t h e p o i n t where a p a r a l l e l e f f o r t c a n be performed. �C. F l i g h t Mechanics Branch 1. Saturn V The Boeing Company h a s s u p p l i e d R-AERO-FM w i t h a "Cape tape" and t h e accompanying p r i n t - o u t , t h e r e v i s e d g u i d a n c e p r e s e t t i n g s , and t h e f i n a l r a n g e s a f e t y document. The g u i d a n c e p r e s e t t i n g s have b e e n d i s t r i b u t e d t o R-ASTR-NG. The Boeing Company h a s s u p p l i e d R-AERO-FM w i t h t h e p r e l i m i n a r y d i s p e r s i o n a n a l y s i s document and a n e r r a t u m o f t h e d i s p e r s i o n a n a l y s i s . A l l n e c e s s a r y d a t a have b e e n g i v e n t o t h e Boeing Company s o t h a t t h e y c a n complete t h e f i n a l o p e r a t i o n a l t r a j e c t o r y r e p o r t and dispersion analysis. A l l n e c e s s a r y i n f o r m a t i o n h a s been g i v e n t o TBC s o t h a t t h e y c a n b e g i n work on t h e g u i d a n c e p r e s e t t i n g s . The Boeing Company h a s s u p p l i e d R-AERO-FM w i t h t h e g u i d a n c e p r e s e t t i n g s , which a r e b e i n g v e r i f i e d . The Boeing Company h a s s u p p l i e d R-AERO-FM w i t h a "Cape t a p e " and t h e accompanying p r i n t - o u t and t h e p r e l i m i n a r y r a n g e s a f e t y document. d. General Work h a s begun on r e v i s i n g o u t p u t i n t h e new f o r m a t of t h e B-7 t a p e as a r e s u l t o f m e e t i n g s w i t h MSC r e p r e s e n t a t i v e s , who h a v e r e q u e s t e d us t o add a b o u t 40 words t o t h e t a p e . The B-7 t a p e f o r m a t r e v i s i o n has b e e n completed and t h e f o r m a t h a s b e e n d i s t r i b u t e d . A t h r e e - s t a g e Marves s i m u l a t i o n w i t h IGM i n t o o r b i t h a s b e e n checked o u t and is i n p r o d u c t i o n . 2. S a t u r n IB The d i s p e r s i o n a n a l y s i s i s r e a d y f o r d i s t r i b u t i o n . The f i n a l "Cape t a p e " h a s b e e n r e c e i v e d from CCSD b u t was r e t u r n e d f o r c o r rection. It s h o u l d b e r e t u r n e d by O c t o b e r 31 and r e a d y t o s h i p t o KSC and MSC. �A memo h a s b e e n p u b l i s h e d on AS-204 t w o - e n g i n e - o u t c a p a b i l i t y and what s h o u l d b e e x p e c t e d i f t h e S-IB LOX v e n t v a l v e f a i l s t o open. Graphs were f u r n i s h e d t o show t h e e n g i n e - o u t c a p a b i l i t y , which i n c l u d e d SPS b u r n t o o r b i t . Should t h e LOX v e n t v a l v e f a i l t o o p e n , t h r u s t would d r o p 3 p e r c e n t and m i x t u r e r a t i o would d r o p by 2 p e r c e n t . The t o t a l e f f e c t would be 2,400 pounds o f S-IVB r e s e r v e s consumed. The "AS-204 Launch V e h i c l e O p e r a t i o n a l T r a j e c t o r y D i s p e r s i o n A n a l y s i s ," h a s b e e n d i s t r i b u t e d . The f i n a l "Cape t a p e " and r a n g e s a f e t y r e p o r t have a l s o b e e n d i s t r i b u t e d . New p r o p u l s i o n and mass p r e d i c t i o n s h a v e b e e n r e c e i v e d , and t h e i r e f f e c t s on S-IVB r e s e r v e s a r e being inves t i g a ted. Two hundred and t h i r t y c o p i e s of t h e p r e l i m i n a r y o p e r a t i o n a l t r a j e c t o r y have b e e n r e c e i v e d from CCSD. The f i n a l o p e r a t i o n a l t r a j e c t o r y has been g e n e r a t e d . The o p e r a t i o n a l t r a j e c t o r y , d i s p e r s i o n a n a l y s i s , and r a n g e s a f e t y a n a l y s i s have b e e n completed based on t h e o l d m i s s i o n . The e f f e c t s caused by p l a c i n g t h e 205 i n t o t h e 207 m i s s i o n a r e b e i n g evaluated . Two hundred and t h i r t y c o p i e s o f t h e p r e l i m i n a r y o p e r a t i o n a l t r a j e c t o r y have b e e n r e c e i v e d from CCSD. The d i s p e r s i o n a n a l y s i s and r a n g e s a f e t y r e p o r t s a r e a b o u t 5 0 p e r c e n t c o m p l e t e . D. T r a c k i n g and O r b i t a l A n a l y s i s Branch 1. M r . R. Benson a t t e n d e d t h e F l i g h t Mechanics P a n e l M e e t i n g O c t o b e r 19-20, 1966, a t MSC. The d e c a y and l i f e t i m e p r e d i c t i o n s f o r AS-209 were p r e s e n t e d . Memorandum R-AERO-FT-50-66 documents t h e AS-209 presentation. 2 . A d e c a y a n a l y s i s of t h e SA-8, SA-9, and SA-10 o r b i t s f o r t h e p e r i o d J u l y 15 t h r o u g h August 1 , 1966, h a s been d e l i v e r e d by Lockheed under t h e M i s s i o n S u p p o r t C o n t r a c t . The p u r p o s e o f t h i s r e p o r t is t o determine t h e r a t i o of the apparent atmospheric d e n s i t y t o t h e 1959 ARDC d e n s i t y i n t h e p e r i g e e a l t i t u d e r e g i o n 490-520 km and f o r t h e p e r i o d s t u d i e d . The r e s u l t s i n d i c a t e t h a t t h e 1959 ARDC d e n s i t y i s a p p r o x i m a t e l y 8 t o 20 t i m e s t h a t o f t h e a p p a r e n t d e n s i t y under t h e SA-8, SA-9, and SA-10 o r b i t a l c o n d i t i o n s . The s p r e a d i n t h e r a t i o i s due t o t h e d i f f e r e n c e s i n t h e p o s i t i o n of t h e p e r i g e e s and t h e d i u r n a l b u l g e . These r e s u l t s c o n f i r m t h e d e n s i t y p r o f i l e c u r r e n t l y b e i n g used by t h i s b r a n c h f o r t h e l i f e t i m e and d e c a y p r e d i c t i o n s of o t h e r s p a c e miss ions . �3. R-AERO-FT p r e s e n t e d a summary of t h e l i f e t i m e work and a s s o c i a t e d s u b j e c t s t o D r . G e i s s l e r on October 26. The b a s i c t h e o r y of t h e l i f e t i m e model, t h e e q u a t i o n s , t h e a t m o s p h e r i c d e n s i t y model, and t h e s o l a r c y c l e p r e d i c t i o n t e c h n i q u e used by R-AERO-FT were discussed. R-AERO-FT recommended t h a t more e f f o r t s h o u l d b e expended i n t h e a r e a s of s o l a r c y c l e p r e d i c t i o n , c o e f f i c i e n t of d r a g d e t e r m i n a t i o n , and o r b i t a l a t t i t u d e p r e d i c t i o n . 4. The r e s t u d y on t h e l i f e t i m e p r e d i c t i o n s of t h e 39 s a t e l l i t e s u s i n g a p r e d i c t i o n o f t h e s o l a r a c t i v i t y c y c l e was completed. Only 2 o f t h e 39 c a s e s produced l i f e t i m e p r e d i c t i o n s w h e r e i n t h e a c t u a l l i f e t i m e f e l l o u t s i d e t h e k22a l i m i t s . The mean o f t h e r a t i o of t h e a c t u a l l i f e t i m e t o t h e p r e d i c t e d l i f e t i m e was 0.978 w i t h a s t a n d a r d d e v i a t i o n of 1 1 . 7 p e r c e n t . This compares f a v o r a b l y w i t h t h e mean and s t a n d a r d d e v i a t i o n o b t a i n e d when t h e a c t u a l s o l a r c y c l e was used i n the lifetime predictions. The mean and s t a n d a r d d e v i a t i o n s f o r t h i s s t u d y w e r e 1.00 and 8 . 2 p e r c e n t , r e s p e c t i v e l y . These r e s u l t s were included i n a l e t t e r t o D r . Mueller. ' . 5 . During t h e Guidance and Performance Subpanel Meeting h e l d November 8 , 1966, a t MSFC, a d i s c u s s i o n of AS-205 o r b i t a l l i f e t i m e r e v e a l e d a n MSC i n t e r e s t i n t h e a t m o s p h e r i c model used by R-AERO t o o b t a i n t h i s i n f o r m a t i o n . The MSC r e p r e s e n t a t i v e s s t a t e d t h a t , by u s i n g R-AERO'S method o f m o d i f y i n g t h e 1962 U . S . S t a n d a r d , e x c e l l e n t r e s u l t s had b e e n o b t a i n e d f o r t h e Gemini m i s s i o n s . They were v e r y i n t e r e s t e d i n u s i n g o u r deck a s t h e i r s t a n d a r d and wanted t o i n v e s t i g a t e t h e p o s s i b i l i t y o f u s i n g i t a t t h e Cape f o r r e a l - t i m e a n a l y s i s . They s t a t e d t h e y would c a l l s o o n t o a r r a n g e a m e e t i n g on t h e s u b j e c t . 6. T r a c k i n g c o v e r a g e f o r t h e s p e c i a l AS-501 t r a j e c t o r y p r o f i l e s was p r e p a r e d f o r p r e s e n t a t i o n t o t h e O p e r a t i o n S u p p o r t Requirements Subpanel a t KSC (December 1 - 2 , 1 9 6 6 ) . M r . Benson i s a t t e n d i n g t h i s meeting. 7 . Memorandum R-AERO-FT-53-66 was s e n t t o R-AERO-YS, M r . S m i t h , s p e c i f y i n g t h e maximum and minimum e x p e c t e d d e n s i t i e s which could be e x p e c t e d from t h e R-AERO-FT O r b i t a l L i f e t i m e Model. �PUBLICATIONS I. Fox, P . A . and D . W. Camp, " P e r c e n t a g e L e v e l s of Wind Speed D i f f e r e n c e s Computed b y Using Rawinsonde Wind Data from S a n t a Monica, C a l i f o r n i a , NASA TM X-53528, O c t o b e r 21, 1966, U n c l . 2. H a u s s l e r , J . B . , " S a t u r n SA-203 P o s t f l i g h t T r a j e c t o r y , " NASA TM X-53554, November 4 , 1966, Uncl. 3. K r a u s e , F . R . , S . S . Hu, and A . J. Montgomery, "On Crossed-Beam M o n i t o r i n g o f Atmospheric Winds and T u r b u l e n c e w i t h Two O r b i t i n g T e l e s c o p e s , " NASA TM X-53538, November 1 4 , 1966, U n c l . 4. W a l k e r , W. H. , "A Method f o r t h e D e t e r m i n a t i o n of E m p i r i c a l Formulas f o r Launch V e h i c l e Angle of A t t a c k and Engine D e f l e c t i o n , " Aero-Astrodynamics I n t e r n a l Note 16-66, O c t o b e r 6 , 1966, Unclassified. 5. York, Randy J . , "A Method f o r t h e S e n s i t i v i t y A n a l y s i s o f R i g i d Body S a t u r n V Dynamics," Aero-Astrodynamics I n t e r n a l Note 17-66, O c t o b e r 6 , 1966, Uncl. 6. Redus, J . R . , " S t a b i l i t y of Motion o f a Launch V e h i c l e C o n s i d e r i n g t h e R a t e o f Change of t h e P a t h Angle," Aero-Astrodynamics I n t e r n a l Note 18-66, November 1 7 , 1966, Uncl. �AERO-ASTRODYNAMICS LABORATORY BIMONTHLY PROGRESS REPORT December 1 2 , 1966 APPROVAL: ,. D e p u t y 6 i r e c t o r , Aero-As t r o d y n a m i c s L a b o r a t o r y L E . D. G e i s s l e r D i r e c t o r , Aero-As t r o d y n a m i c s L a b o r a t o r y DISTRIBUTION R-AERO-DIR Dr. G e i s s l e r Mr. J e a n R-AERO-A (20) R-AERO-G (5) R-AERO-R M r . B u t l e r (4) Mrs. Hightower R-AERO-Y (5) R-AERO-F (8) R-AERO-T Mr. Murphree M r . Cumrnings Mr. D i c k e y Dr. Heybey Mr. L a v e n d e r Mr. Jandebeur Dr. L i u Dr. Krause M r . von P u t t k a m e r R-AERO-X (2) R-AERO-P (8) R- AERO-D (16) R-DIR, M r . C o o k PAO, M r . K u r t z MS-H, M i s s J e r r e l l (3) I-V-P, Harold Price � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000042 Title A name given to the resource "Aero-Astrodynamics Laboratory Bimonthly Progress Report: December 12, 1966." Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center Date A point or period of time associated with an event in the lifecycle of the resource 1965-12-12 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) NASA space programs Project management Type The nature or genre of the resource Progress reports Text Source A related resource from which the described resource is derived Saturn V Collection Box 19, Folder 44 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050 https://digitalprojects.uah.edu/files/original/20/990/spc_stnv_000043.pdf b19b01e420bc4d1180a282e116827fca PDF Text Text AERO-ASTRODYNBMIGS LABOKATQRY MONTHLY PROGRESS REPORT November 2 . 1965 Page . 11%. O.............O.+.*.IIO4........ . . . IV . V. . . . .. . ... .. . .. % VI ............................. ............ ............................................. ............................................... .............................. .................... .......... ......................... ...................... ........................... ................ ................................., ................................ ............................ .............. ............................. ......................................... .. ........................................ ........................................e.. .............................. ..................................... ............................ .. ........................................ ......................................... .................................. ....................................... .......................................... .......................... .................... .............................. .......................................... 1 TECHNICAL AND SCIENTIFIC STAFF 1 PROJECTS OFFICE 1 1 Saturn HB 2,, Saturn V . . . . . . . . . . . . . . . . . . . ~ . O I D . o . . . . . . . . . . . . . . . . ~ . . . .1 2 3 General 3 AEROSPACE E3SVIRQWENT OPFHGE 3 A. Space Environment Group 4 B T e r r e s t r i a l E n v i m m e n t Group 4 C Environmental Applications Group 5 D. Atmospheri.e Pleasuring Group 5 ASTRODYNmHCS AhD GUHDAXCE THEORY DIVISIOX 5 A Astrodynamfcs Branch 6 B. Guidance Theory Branch 8 C Optimization Theory Branch 10 AERODYNAMICS DIVISION . . . . e u . . . u . . . . . o . . . . . 10 A Aerodynamic Design Branch 10 l 8 Saturn BB 11 2 Saturn V 12 3 General 12 B. E l e c t r o m ~ c h a n i c a l Branch 14 C F a c i l i t i e s Branch 15 D. Thermal Environment Branch 15 P Saturn 1 15 2 Saturn I B 17 3 Saturn centaur 18 4 Saturn V 19 5 General 22 E Unsteady Aerodynamics Branch 24 DYNAMICS AND FLIGHT MECJ3AlYPCS DIVISION 24 A Dynamics Analysis Branch 24 1 Saturn I B 25 2 Saturn V . . . . . . . . . . . . . . . . . . . O O e . . . . . . . . . . . . . . . . . . . . . 26 3 General 26 4 Contractors 27 B Control Theory Branch 27 1 Saturn HB 28 2 Saturn ~ ~ / ~ e n t a u r 28 3 Saturn V 29 4 General 29 5. Contractors .. . . .. .. . ........................................... ....................................... .............................. .......................................... ................................. .. ..................,......,.............. .......................................... ...................................... �.......... 3434 ........................................ .......................................... 36 . ........................................... 37 . ....................................... 38 ......................... 42 . ......... V I I. 43 ............................... 43 .............................. 44 . .......................................... 44 .................... 464 6 . ......................................... ............................... 4747 .. ......................................... ......................................... 49 . . .............................. 50 ......................................... 50 . .......................................... 50 ........................................... 50 51 PUBLICATIONS ................................................. . 1. 2. Applied Guidance and F l i g h t Mechanics Branch Saturn I B Saturn V 3 General 4 Contractors D Advanced P r o j e c t s Study Branch FLIGHT EVALUATION ANI> OPERATIONS STUDIES DIVISION A. Special Projects Office B e P l i g h t Evaluation Branch 1 Saturn I 2 . Saturn PI3 and V Data Processor 3 Contracts C. F l i g h t Mechanics Branch 1 Saturn PB 2 Saturn V D Operations Studies Branch 1 Saturn HB 2 Saturn V 3 0 General C �AERO-ASTRODYNAMICS LABORATORY MONTHLY PROGRESS REPORT November 2, 1965 I. TECHNICAL AND SCIENTIFIC STAFF 1. A paper on a c o u s t i c a l zero l e v e l f o c i formed by r a y s r e t u r n i n g from t h e t h i r d atmospheric l a y e r has been r e v i s e d and w i l l be p u b l i s h e d s h o r t l y . A computer program based on t h i s i n v e s t i g a t i o n has been developed and t r i e d (Beybey). 2. The Fehlberg power s e r i e s method has been a p p l i e d ' t o t h e r e s t r i c t e d problem of t h r e e bodies. P e r i o d i c s o l u t i o n s of 2 2 - d i g i t accuracy ( f o r t h e i n i t i a l c o n d i t i o n s ) a f t e r one f u l l p e r i o d were produced d e s p i t e t h e f a c t t h a t t h e t r a j e c t o r i e s were s e n t p u r p o s e l y c l o s e t o and below t h e s u r f a c e of t h e moon. These r e s u l t s exceed what has been r e p o r t e d i n t h e l i t e r a t u r e and i l l u s t r a t e t h e power of t h e Pehlbesg methods when coupled w i t h t h e extended p r e c i s i o n f e a t u r e of t h e IBM I620 Computer ( P e a s l e y ) . 11. PROJECTS OFFICE 1, S a t u r n PB CCSD A e r o b a l l i s t i c s Q u a r t e r l y Review: The f i r s t FY-66 Q u a r t e r l y Review of t h e C h r y s l e r C o r p o r a t i o n Space D i v i s i o n " (CCSD) e f f o r t i n s u p p o r t o f t h e Aero-Astrodynamics Laboratory was h e l d a t MSFC on October 19, 1965. This t e c h n i c a l review covered t h e work performed under mod 208, item I H I b of c o n t r a c t NAS8-4016. CCSD has 126 personnel onrboard o u t of t h e 128 a u t h o r i z e d . A l l t e c h n i c a l a n a l y s e s a r e p r o g r e s s i n g smoothly. 2. Saturn V a. D i r e c t Ascent Mode The p r e s e n t a t i o n of t h e r e s u l t s of t h e d i r e c t a s c e n t s t u d i e s t o D r , von Braun has been delayed because of t h e heavy work load w i t h i n t h e Laboratory. A new d a t e f o r t h e d i r e c t a s c e n t d r y r u n and p r e s e n t a t i o n i s being c o o r d i n a t e d . b, Engine Out The major problems a s s o c i a t e d w i t h S a t u r n V engine-out a r e being f u l l y i n v e s t i g a t e d . They a r e i n t h e a r e a s of s t r u c t u r a l l o a d s and t h e S - I 1 h e a t s h i e l d , The s t a g e c o n t r a c t o r s have been asked t o impact �t h e c o s t and s c h e d u l e s f o r i n c r e a s i n g d e s i g n l o a d s c a p a b i l i t y f o r engine-out. Since t h e S - I 1 s t a g e h e a t s h i e l d w i l l be t e s t e d f o r engine-out c o n d i t i o n s about t h e f i r s t of 1966, S a t u r n V engine-out e f f o r t s a r e being f i n a l i z e d . 3. General a. Incentive Contracts - Performance C r i t e r i a The S-IVB p l a n f o r i n c o r p o r a t i n g f l i g h t performance i n t o t h e i n c e n t i v e c o n t r a c t i s n e a r i n g completion. This p l a n w i l l p r o v i d e f o r a measure of t h e payload c a p a b i l i t y , t h e m i s s i o n accomplishment, and t h e t e l e m e t r y d a t a r e c e i v e d , The miss i o n accomplishment p o r t i o n of t h e p l a n w i l l i n c l u d e a s s u r a n c e o f sub-system performance. The S-IC and S - I 1 p l a n s a r e n o t a s w e l l developed a s t h e S-IVB a t t h i s time; however, p l a n s t o a s s u r e f l i g h t performance f o r t h e s e s t a g e s a r e being formulated w i t h t h e a s s i s t a n c e o f o t h e r l a b o r a t o r i e s . b. F l i g h t Mechanics Panel A c t i v i t i e s The Fourteenth F l i g h t Mechanics Panel Meeting was h e l d on October 5 and 6 , 1965. The minutes of t h i s meeting a r e documented i n ~ ~ 6 / ~ 3 3 d a1t e,d October 6 , 1965. c. P r o p e l l a n t U t i l i z a t i o n System - Guidance System I n t e r a c t i o n Recent r e s u l t s from t h e S-IVB b a t t l e s h i p t e s t s and t h e S-IVB 201 s t a g e acceptance f i r i n g have r e v e a l e d t h r u s t o s c i l l a t i o n s o f peak-to60 seconds. peak magnitude o f up t o 12,000 pounds w i t h a p e r i o d of 50 The o s c i l l a t i o n s r e s u l t from n o n l i n e a r i t i e s i n t h e p r o p e l l a n t u t i l i z a t i o n probe. The i t e r a t i v e guidance mode (IGM) developed f o r S a t u r n i s based on c o n s t a n t t h r u s t . The IGM s t e e r i n g program i s a s t r o n g f u n c t i o n o f F/M, and t h u s t h e v e h i c l e e x p e r i e n c e s an a t t i t u d e h i s t o r y , X, v e r y similar t o the thrust history. The commanded a t t i t u d e r a t e , X, i s restricted to one degree p e r second. Therefore, t h e t h r u s t o s c i l l a t i o n r e s u l t s i n d e v i a t i o n s from t h e optimized p a t h which cannot always be c o r r e c t e d by t h e commanded a t t i t u d e program. For t h e S a t u r n I B program, s o f t w a r e m o d i f i c a t i o n s t o t h e guidance mode r e s u l t i n a f i x t h a t seems a c c e p t a b l e f o r AS-201 s i n c e guidance accuracy and performance a r e n o t v e r y s t r i n g e n t f o r t h i s f l i g h t . M o d i f i c a t i o n of system g a i n s by R-P&VE a f f o r d some a l l e v i a t i o n f o r AS-202 and subsequent f l i g h t s ; however, i t was f e l t a t a r e c e n t S-IVB Technical Review t h a t t h e t h r u s t o s c i l l a t i o n s must be reduced d r a s t i c a l l y b e f o r e f l i g h t o f AS-204. En t h e S a t u r n V program, + 10,000 pound peak-to-peak t h r u s t o s c i l l a t i o n s i n t h e burn-out o f o r b i t by t h e S-IVB r e s u l t i n i n j e c t i o n f l i g h t p a t h a n g l e e r r o r s o f about 0.75 d e g r e e s ( s i x times t h e hardware e r r o r ) . When t r a n s l a t e d t o t h e l u n a r r a d i u s t h i s r e s u l t s i n 4,000 krn e r r o r , t h u s c a l l i n g f o r a AV c o r r e c t i o n o f about 50 m/sec. Since t h i s i s e s s e n t i a l l y t h e t o t a l AV - + �budget s e t a s i d e f o r t h e l u n a r m i s s i o n , it i s t o t a l l y unacceptable. T h i s problem has been brought t o t h e a t t e n t i o n of t h e top management o f MSFC and DAC andanMSFC-DAC t a s k team has gone t o Minneapolis-Honeywell, t h e probe m a n u f a c t u r e r , t o e x p e d i t e a s o l u t i o n . PHI. AEROSPACE ENVIRONMENT OFFICE A, Space Environment Group 1. M r . Robert E. Smith a t t e n d e d a meeting on t h e thermosphere probe program ( o r b i t a l a l t i t u d e d e n s i t y measurements) a t Kennedy Space Center w i t h p e r s o n n e l from t h e U n i v e r s i t y of Michigan, Thiokol Chemical C o r p o r a t i o n and r e p r e s e n t a t i v e s from ETR and KSC. F a c i l i t i e s and s e r v i c e s t o be provided by KSC and ETR were d i s c u s s e d i n d e t a i l , e s p e c i a l l y t h e c a p a b i l i t y of t h e ETR i n t r a c k i n g t h e Nike Tomahawk, and were found t o be satisfaetsry. P l a n s a r e being formulated t o Paunch s i x o r seven probes on a s i n g l e day i n May o r J u n e , depending upon t h e a v a i l a b i l i t y o f t h e ETR, f o r maximum use of d a t a measurements. 2. M r . R. E. Smith and M r . J. 0. B a l l a n c e , R-AERO-A, v i s i t e d t h e U n i v e r s i t y o f Michigan t o d i s c u s s p r o g r e s s o f t h e thermosphere probe program and a s s o c i a t e d problems concerning d a t a r e d u c t i o n and i n t e r p r e tation. Progress i s s a t i s f a c t o r y . 3. The d r a f t copy of t h e r e p o r t on t h e Space Environment C r i t e r i a c o n t r a c t was r e t u r n e d t o A e r o j e t General C o r p o r a t i o n f o r revision. The f i n a l r e p o r t should be p u b l i s h e d by December 1, 1965. 4. A paper e n t i t l e d "Decrease i n E l e c t r o n Density i n t h e Ionosphere Following t h e Passage of S a t u r n I , " by M r . J, K. F e l k e r and M r . W. T. Roberts has been accepted f o r p r e s e n t a t i o n a t t h e Second AAS Symposium on I n t e r a c t i o n of Space Vehicles w i t h an Ionized Atmosphere t o be h e l d i n Miami Beach, F l o r i d a , i n November. 5 , A r e p o r t e n t i t l e d 'Neasurement o f Winds by Chemical R e l e a s e s i n t h e Upper Atmosphere," by M r . Hugh Morgan i s being prepared f o r publication. 6. A r e p o r t e n t i t l e d "An Environmental Model f o r Van A l l e n B e l t P r o t o n s , " by M r , W. T. Roberts was completed and i s being reviewed. 7. A model o f a c o l d t r a p gauge f o r measuring t h e mass d e n s i t y a t o r b i t a l a l t i t u d e s was d e l i v e r e d by t h e C e l e s t i a l Research Corporation. The f i n a l r e p o r t on t h i s f e a s i b i l i t y s t u d y i s b e i n g completed and w i l l be p u b l i s h e d a s a c o n t r a c t o r r e p o r t i n December. �B. T e r r e s t r i a l Environment Group 1, The f i n a l r e p o r t ( P a r t IV), "Mathematical Wind P r o f i l e s ' " has been r e c e i v e d from t h e Lockheed C a l i f o r n i a Company. This r e p o r t , which p r e s e n t s d e t a i l e d procedures f o r p r e d i c t i n g a f u t u r e v e c t o r wind p r o f i l e from p r e s e n t and p a s t wind p r o f i l e s f o r a p p l i c a t i o n a t Cape Kennedy, F l o r i d a , i s being reviewed, along w i t h t h e o t h e r t h r e e p a r t s , f o r NASA p u b l i c a t ion. 2. A r e v i s i o n t o TM X-53023, v n T e r r e s t l - i a lEnvironment ( C l i m a t i c ) C r i t e r i a G u i d e l i n e s f o r u s e i n Space Vehicle DeveBopment, i s being prepared i n f i n a l form. This r e p o r t , a l o n g w i t h a s i m i l a r r e p o r t on space environment c r i t e r i a , i s used by MSFC i n program d e s i g n s t u d i e s . C, Environmental A p p l i c a t i o n s Group 1, Work ccntinued cn t h e i n v e s t i g a t i o n of atmospheric t u r b u l e n c e f c r space v e h i c l e s , S p e c t r a of s m a l l - s c a l e motions p r e s e n t En t h e d e t a i l e d wind p r o f i l e s t h a t a r e n o t included i n t h e r a w i ~ s o n d emeasurements have been c a l c u l a t e d far a s i z e a b l e sample, and t h e p r o b a b i l i t y o f energy c o n t e n t a s a f u n c t i o n of frequency has been e s t a b l i s h e d , This w i l l permit t h e s p e c i f i c a t i o n of s p e c t r a l d e n s i t i e s of t h e s m a l l - s c a l e motions on a p r o b a b i l i t y b a s i s . S i m i l a r s p e c t r a a r e a l s o being computed f o r t h e t o t a l wind speed p r o f i l e s up t o wave l e n g t h s of 4000 meters, A j o i n t program i s under way w i t h R-AERO-D t o i n v e s t i g a t e v a r i o u s methods f o r h a n d l i n g t u r b u l e n c e i n p u t s f o r v e h i c l e response c a l c u l a t i o n s . 2. It was r e c e n t l y r e q u e s t e d t h a t t h e T r a v e l e r s Research C e n t e r , I n c . , under c o n t r a c t NAS8-18450, p r e p a r e a complete t e s t p l a n i n c l u d i n g equipment, number o f personnel needed, number and type of experiments, methods o f s o u r c e s i m u l a t i o n , and c o s t s f o r conducting f u l l - s c a l e atmospheric d i f f u s i o n f i e l d t e s t s . This t e s t p l a n w i l l be completed by December 31, 1965, and forwarded t o NASA Headquarters (OART and OSSA) f o r t h e i r review and comments, Such t e s t s a r e r e q u i r e d t o p r o p e r l y e v a l u a t e t h e atmospheric hazards a s s o c i a t e d w i t h t h e u s e of toxic propellants. The r e s u l t s o f t h e f i e l d t e s t s , i f conducted, w i l l s e r v e t o v e r i f y t h e atmospheric models formulated by TRC under t h i s contract. D e f i n i t i v e i n f o r m a t i o n on t h e d i f f u s i o n of t o x i c exhaust byproducts i s q u i t e l i m i t e d , e s p e c i a l l y w i t h r e g a r d t o t h e p o s s i b l e use of f l u o r i n e a d d i t i v e t o f u e l s a s i s being proposed. I f FLOX i s used, t h e f i e l d t e s t s must be conducted t o b e t t e r d e f i n e such problems a s atmospheric chemistry a s s o c i a t e d w i t h FLOX, buoyant t r a n s p o r t , downwind p a r t i c u l a t e d i s p e r s i o n , i n t e g r a t e d and peak c o n c e n t r a t i o n s w i t h r e l a t i o n t o d i s t a n c e , and lower atmospheric c o n d i t i o n s . 3 . NASA" 150-meter Meteorological Tower F a c i l i t y l o c a t e d on t h e ' M e r r i t t I s l a n d Launch Area (MILA) i s o n l y p a r t i a l l y o p e r a t i o n a l . E l e c t r o n i c and mechanical d i f f i c u l t i e s r e l a t e d t o i n s t a l l a t i o n and �o p e r a t i o n of t h e anemometers have caused l e n g t h y d e l a y s . When winds reached magnitudes of 10-20 m/sec, t h e anemometer cups s e p a r a t e d from t h e i r transducer units. The manufacturer s p e c i f i e s t h a t t h e s e cup A l l cup systems a r e a b l e t o w i t h s t a n d approximately 40 m/sec winds. u n i t s had t o be r e d e s i g n e d causing s e v e r a l weeks delay. Other f a c t o r s such a s e l e v a t o r m a l f u n c t i o n s , s e v e r e weather, low p r i o r i t y o f work, e t c . , have c o n t r i b u t e d t o t h e p r e s e n t i n o p e r a t i v e n e s s of t h i s met tower f a c i l i t y . A c o n c e r t e d e f f o r t i s being made t o g e t t h e f a c i l i t y o p e r a t i o n a l . D. Atmospheric Measuri.ng Group No c o n t r i b u t i o n received. HV. ASTRBDPNA&llCS A. Am G U I D m C E TBEORY DBVSS ION Astrodynamics Bran.& 1. Cislunar Trajectory Studies - a , Contractor A r e p o r t "Ephemeral Design Parameters f o r C i s l u n a r O r b i t a l T r a j e c t o r i e s " has been prepared by Lockheed. T h i s r e p o r t documents much of t h e d a t a generated i n t h e c i s l u n a r o r b i t s t u d y and d i s c u s s e s t h e v a r i o u s parameters which have major e f f e c t s on t h e o r b i t The study has a l s o been extended t o a n a n a l o g i n v e s t i perigee history. g a t i o n o f parameters (such a s o r b i t a l elementq), which have n o t y e t been c o n s i d e r e d , and a c o n c u r r e n t r e e v a l u a t i o n of p r e v i o u s l y g e n e r a t e d d a t a i n terms of new parameters. - In-House An e r r o r found i n t h e T r i c e computer program b. f o r t h e e l l i p t i c a l - t h r e e - b o d y model i s bei.ng c o r r e c t e d . The s t u d y .of s e p a r a t e p e r t u r b a t i o n s on c i s l u n a r o r b i t s u s i n g t h e e l l i p t i c a l three-body model i s c o n t i n u i n g w i t h t h e use o f IBM 7094 d i g i t a l o u t p u t programs; however, t h i s approach i s slower w i t h o u t t h e T r i c e program t o p r o v i d e t h e groundwork. - A preliminary c a l c u l a t i o n of 2. Conic I n t e r p l a n e t a r y Program Earth-to-Mercury t r a j e c t o r i e s u s i n g t h e new c o n i c t r a j e c t o r y program i s continuing. This s t u d y i s s t i l l uncovering p a r t i c u l a r l y small e r r o r s i n t h e program which a r e n o t r e v e a l e d by t h e b a s i c checkout procedure. It i s a l s o p r o v i d i n g f a m i l i a r i z a t i o n of new branch p e r s o n n e l w i t h t h e deck and w i t h i n t e r p l a n e t a r y t r a j e c t o r y c a l c u l a t i o n . - I n connection 3 . P r e c i s i o n I n t e r p l a n e t a r y T r a j e c t o r y Program w i t h t h e c o n t r a c t which was awarded Auburn U n i v e r s i t y f o r i n c l u d i n g t h r u s t i n a p r e c i s i o n i n t e r p l a n e t a r y program, t h e program was formulated t o be s u i t a b l e f o r a d a p t a t i o n and was given t o Auburn. I n a d d i t i o n some e d u c a t i o n of d i v i s i o n p e r s o n n e l i n t h e formation of r e c u r s i o n r e l a t i o n s h a s been provided s o t h a t e f f e c t i v e c o n t r a c t monitoring w i l l be p o s s i b l e . �B. Guidance Theory Branch a. Northrop Schedule Order No. 7 A comprehensive t r a j e c t o r y and guidance system e r r o r a n a l y s i s of t h e Centaur Voyager m i s s i o n t o p a r k i n g o r b i t has been completed under t h e assumption t h a t I G M c o n t r o l s t h e Centaur s t a g e . The launch window T h i s work w i l l be p u b l i s h e d a s a Northrop r e p o r t . and launch azimuth v e r s u s time problem i s being s t u d i e d , and computer r u n s w i l l be made on t h e Centaur c o n f i g u r a t i o n t o g a i n experience. Machine time demands a r e c o n s i d e r a b l e s i n c e t h e f l i g h t must go from pad t o Mars, and p r i o r i t y r e q u e s t s do not seem j u s t i f i e d . b. S t u d i e s were continued on s t a t i s t i c a l a n a l y s i s of guidance systems. P a r t i c u l a r emphasis i s being placed on Monte C a r l o a n a l y s i s a s a p p l i e d t c ~s i m u l a t i o n . S t u d i e s of s t a t i s t i c a l a n a l y s i s o f midcourse maneuvers a r e a l s o being c a r r i e d o u t . A t p r e s e n t , t h i s e f f o r t i s l a r g e l y one of r e a d i n g and study t o develop background i n c o r r e c t s t a t i s t i c a l a n a l y s i s o f guidance systems and t r a j e c t o r y e r r o r s . 2. &ow Thrust Guidance and Performance Northrop Schedule Order No. 6: Attempts have been made t o measure t h e l o s s of e f f i c i e n c y i n f o l l o w i n g low t a n g e n t i a l t h r u s t t o Thus f a r , i t has escape by computing a n optimum COV escape t r a j e c t o r y . been impossible t o converge w i t h t h e COV deck i f no end c o n d i t i o n s o t h e r t h a n escape energy a r e s p e c i f i e d , a l t h o u g h t h e computation i s being c a r r i e d o u t i n o r b i t element c o o r d i n a t e s . An a t t e m p t i s being made t o s p e c i f y a d d i t i o n a l c o n d i t i o n s a t t h e end, such a s p a t h a n g l e , t o s e e i f convergences can be o b t a i n e d f o r a l e s s optimum t r a j e c t o r y . This problem i s being attempted in-house i n r e c t a n g u l a r c o o r d i n a t e s u s i n g a more e f f i c i e n t i s o l a t i o n procedure t o see i f convergence can be o b t a i n e d . There i s no p r o g r e s s t o r e p o r t i n t h e low t h r u s t guidance a r e a . 3. Implementation S t u d i e s a. M o d i f i c a t i o n s t o ~ e w t o n ' smethod ( w i t h e x a c t v a l u e s f o r t h e p a r t i a l d e r i v a t i v e s ) t o i n c l u d e f i x e d s t a g i n g times have been completed. The computer program s o l v e s t h e boundary v a l u e problem a s s o c i a t e d w i t h t h e o p t i m i z a t i o n of t r a j e c t o r i e s from b o o s t e r c u t o f f t o o r b i t w i t h up t o 10 s t a g e s allowed, M o d i f i c a t i o n s f o r s w i t c h i n g f u n c t i o n s t o allow t h e d e t e r m i n a t i o n of optimal s t a g i n g p o i n t s a r e a l s o b e i n g programmed. b. The a p p l i c a t i o n o f ~ e w t o n ' smethod t o t h e d e t e r m i n a t i o n of an o p t i m a l g e o c e n t r i c low t h r u s t t r a j e c t o r y from o r b i t t o escape i s being attempted. Some problems w i t h ' t h e accuracy of t h e i n t e g r a t i o n of �t h e d i f f e r e n t i a l e q u a t i o n s have been encountered. More e f f i c i e n t numerical i n t e g r a t i o n techniques a r e b e i n g s t u d i e d t o overcome t h e prob lem. 4. Contracts a. Aeronutronics (NAS8-20150) P r i n c i p a l i n v e s t i g a t o r , M r . Rishard AuePmann, v i s i t e d MSFC on October 2 1 t o d i s c u s s work on t h e c o n t r a c t . P r i n c i p a l l y , t h e c o n t r a c t has provided t h e r e s u l t s of s i m p l i f i e d s t e e r i n g e q u a t i o n s f o r t h e performance problem and o r b i t t r a n s f e r miss i o n w i t h one c o a s t period. This o p p o r t u n i t y was t a k e n t o r e o r i e n t t h e work along l i n e s of d e t e r m i n i n g a feedback l o g i c f o r t h e guidance problem i n t h e hope t h a t a simple sub-optimal guidance procedure w i l l be found f o r t h e p l a n a r o r b i t t r a n s f e r problem. While p r e v i o u s work has been o f good q u a l i t y i n t h e development o f p e r t u r b a t i o n s o l u t i o n s t o t h e e q u a t i o n s of motion, i t seems t o be somewhat academic. C e r t a i n a c t i v i t i e s i n c o n n e c t i o n w i t h e s t a b l i s h i n g t h e accuracy of t h e p e r t u r b a t i o n s o l u t i o n s w i l l continue. The s i m p l i f i c a t i o n of c o n s t a n t engine a c c e l e r a t i o n has been assumed i n a l l work t h u s f a r and may be somewhat u n r e a l i s t i c f o r t h i s reason. b. Auburn U n i v e r s i t y (NAS8-1548) This c o n t r a c t has been r e - d i r e c t e d t o t h e a r e a of low t h r u s t t r a j e c t o r y o p t i m i z a t i o n . A t p r e s e n t , no p r o g r e s s has been r e p o r t e d . c, Hayes I n t e r n a t i o n a l (NAS8-20176) Many d i f f i c u l t i e s i n o b t a i n i n g a s o l u t i o n t o t h e low t a n g e n t i a l t h r u s t problem i n a form simple enough f o r the a p p l i c a t i o n o f a p e r t u r b a t i o n procedure have been r e p o r t e d . These d i f f i c u l t i e s have l e d t o study o f a p e r t u r b a t i o n procedure u s i n g t h e t a r g e t o r b i t f o r the o r b i t t r a n s f e r mission as a reference. The p r e s e n t problem r e q u i r e s t h e e v a l u a t i o n s f s e v e r a l i n t e g r a l s which i s now under study. There i s l i t t l e p r o g r e s s t o r e p o r t i n low t h r u s t guidance pending a more s a t i s f a c t o r y s ~ l u t i o nt o t h e t r a j e c t o r y computation problem. Numerical s t u d y o f p a t h a d a p t i v e guidance polynomials i s c o n t i n u i n g t o a t t e m p t t o d i s c o v e r t h e r e l a t i o n s h i p between nonconvergent p e r t u r b e d c a s e s and t h e t r a j e c t o r y volume used t o d e f i n e t h e guidance polynomial, d. I l l i n o i s I n s t i t u t e of Technology (NAS8-20129) It has been found t h a t t h e l a s t two t u r n s o f a s p i r a l escape t r a j e c t o r y can be approximated f a i r l y c l o s e l y by simple e x p o n e n t i a l f u n c t i o n s . Using t h e s e approximations, a velocity-to-be-gained s t e e r i n g �has been formulated t o be checked o u t i n t h e f u t u r e . The c o n t r o l w i l l a t t e m p t t o s a t i s f y v e l o c i t y d i r e c t i o n v e r s u s d e p a r t u r e time w i t h v e l o c i t y magnitude remaining f r e e . A r e l a t i v e l y simple velocity-to-be-gained s t e e r i n g h a s a l s o been formulated f o r t h e r e v e r s e c a p t u r e s p i r a l - t o c i r c u l a r o r b i t . Numerical work w i l l begin on t h e s e and some o t h e r f a i r l y simple sub-optimum s t e e r i n g laws. e, U n i v e r s i t y sf North C a r o l i n a (lVAS8-20106) Work was continued o n t h e development of a n o v e r - a l l a l g e b r a i c m a n i p u l a t i o n package, and s e v e r a l l a r g e - s c a l e t e s t s on product i o n were run. The t r i g o n o m e t r i c simpkif i c a t i s n s were extended t o change f u n c t i o n s of n e g a t i v e q u a n t i t i e s t o t h e corresponding f u n c t i o n s of positive quantities. The f a c t o r i n g a l g o r i t h m was extended t o f a c t o r o u t t r i g o n o m e t r i c f u n c t i o n s and t o a l s o r e c o g n i z e e q u i v a l e n t p a r e n t h e s i z e d e x p r e s s i o n s a s t h e same, The m a j o r i t y sf t h e m o d i f i c a t i o n s were made due t o a d e t a i l & e v a l u a t i o n cf t h e e n t i r e e f f o r t f o r p r e p a r a t i o n of a techlfcal report. C. O p t i m i z a t i o n Theory Branch 1. Mininax Des ign Technique A minimax d e s i g n technique f o r c o n t r o l systems w i t h d i s t u r b a n c e s i s being developed based on a theory of d i f f e r e n t i a l games. The p r i n c i p a l advantage o f t h i s technique i s t h a t t h e e f f e c t s of a worst d i s t u r b a n c e i n a c e r t a i n c l a s s can be i n c o r p o r a t e d i n t o t h e i n i t i a l s y n t h e s i s o f t h e c o n t r o l system, By use of t h i s technique, c o n v e n t i o n a l d e s i g n a i d s such a s t h e r o o t l o c u s method can be a d j u s t e d t o i n c l u d e d i s t u r b a n c e e f f e c t s . The technique i s being a p p l i e d t o launch v e h i c l e models, and t h e study i s b e i n g documented. 2. Northrop Schedule Order No. 1 O b ~ e c t i v e s : ( a ) To i . n v e s t i g a t e aria-design techniques f o r l i n e a r systems; and ( b ) t o i n v e s t i g a t e Load r e l i e f systems f o r a h i g h l y aerodynamically u n s t a b l e v e h i c l e . ~ u g h e s ' and ~ o r t h r o p ' sa n a l y t i c d e s i g n methods have been a p p l i e d t o a f i f t h o r d e r b o o s t e r model. The systems designed by each method were e v a l u a t e d by s t a n d a r d a n a l y s i s techniques. Both achieved t h e s p e c i f i e d performance. However, i n g e n e r a l , t h e systems designed by Hughes method were sounder i n t h e sense o f being l e s s s e n s i t i v e t o Some e x p e r i e n c e parameter v a r i a t i o n s and being e a s i e r t o implement. was n e c e s s a r y even w i t h t h e Hughes method t o achieve good e n g i n e e r i n g design. An a t t e m p t w i l l be made t o determine what s p e c i f i c a t i o n s should be made i n the Hughes method t o a s s u r e soundly designed systems. As soon a s t h e n e c e s s a r y programs a r e r e a d y , Hughes method w i l l be extended �t o h i g h e r o r d e r systems t o determine i f i t r e t a i n s i t s a t t r a c t i v e f e a t u r e s . Because t h e Northrop method r e q u i r e s l e s s computation, i t would be more d e s i r a b l e , i f i t s l i m i t a t i o n s could be overcome. M o d i f i c a t i o n s t o t h e method were suggested t o Northrop, which t h e y a r e attempting t o incorporate. Bending moment r e d u c t i o n g o a l s based on l o a d i n g e q u i v a l e n t t o burnout c o n d i t i o n s were e s t a b l i s h e d f o r t h e s t u d y v e h i c l e , and bending moments were computed f o r t h e s t a n d a r d wind p r o f i l e and load r e l i e f c o n t r o l systems. These bending moments were about 200 p e r c e n t s f t h e d e s i g n goal. Allowable winds f o r which t h e g o a l i s met w i l l be e s t a b l i s h e d ; a l s o , work w i l l c o n t i n u e i n reducing t h e bending moment f o r t h e s t a n d a r d wind p r o f i l e , a l t h o u g h i t i s c l e a r t h a t t h e g o a l cannot be reached f o r t h i s wind. 3. Contracts O b j e c t i v e : To i n v e s t i g a t e t h e f e a s i b i l i t y and o p e r a t i o n o f t h e d i g i t a l a d a p t i v e f i l t e r , a c u r v e - f i t t i n g procedure f o r e l i m i n a t i n g f l e x u r e components from t h e c o n t r o l s i g n a l . The d r a f t of t h e f i n a l r e p o r t was r e c e i v e d . Although i t i s a thoroughly documented r e p o r t , i t i s d i f f i c u l t t o r e a d and important c o n c l u s i o n s a r e n o t c l e a r l y s t a t e d . Quite an e x t e n s i v e r e w r i t i n g would be d e s i r a b l e . Review i s continuing. b. North American A v i a t i o n (NAS8-20056) O b j e c t i v e : To improve t h e accuracy and speed o f t h e d i g i t a l frequency i d e n t i f i c a t i o n system an a d a p t i v e s t a b i l i z a t i o n system and t o extend i t s a p p l i c a t i o n t o a c t i v e s t a b i l i z a t i o n o f f l e x u r e modes. - - Trajectory simulations reported i n the l a t e s t progress r e p o r t show l a r g e e x c u r s i o n s of both a n g l e - o f - a t t a c k and engine d e f l e c t i o n . I n v e s t i g a t i o n i s being conducted t o determine the cause of t h e s e e x c u r s i o n s , It i s f e l t t h a t t h e s e a r e probably not due t o t h e a d a p t i v e f i l t e r . However, system r e d e s i g n t o reduce t h e engine a n g l e might p l a c e more s e v e r e r e s t r i c t i o n s on t h e f i l t e r s t h a n e x i s t a t p r e s e n t . c. C o r n e l l A e r o n a u t i c a l L a b o r a t o r i e s (NAS8-20067) O b j e c t i v e : To determine t h e f e a s i b i l i t y of a p p l y i n g l i n e a r o p t i m a l c o n t r o l t h e o r y t o t h e s y n t h e s i s of launch v e h i c l e c o n t r o l systems. �A meeting was h e l d w i t h C o r n e l l r e p r e s e n t a t i v e s a t which t h e r e s e a r c h was summarized and f u t u r e d i r e c t i o n of t h e work was d i s c u s s e d . A d e s i g n procedure was p r e s e n t e d f o r a two-bending-mode model which i n c l u d e s measures o f a t t i t u d e e r r o r , both bending mode d e f l e c t i o n s , and c o n t r o l v a r i a b l e i n t h e performance index, Two s y n t h e s i s methods f o r t h e r e s u l t i n g o p t i m a l c o n t r o l law were p r e s e n t e d . One depends on proper placement of two blended r a t e gyros t o a c h i e v e t h e d e s i r e d g a i n r a t i o s between t h e v e h i c l e parameters. The o t h e r method i n v o l v e s reformul a t i o n o f t h e s t a t e v a r i a b l e s t o i n c l u d e measurable q u a n t i t i e s . This second method appears t o be p r e f e r a b l e . Some p r e l i m i n a r y w ~ r khas been done o n t h e c o n s t r a i n e d feedback g a i n problem, and a f e a s i b l e s o l u t i o n technique i s being sought Future e f f o r t s w i l l i n c l u d e an. i n v e s t i g a f o r one promising formulation. t i o n of t h e model-in-performance-index approach. A. Aerodynamic Design Branch 1. Saturn I B a. Apollo-Saturn LB S p a c e c r a f t Compartment Venting: During t h e p a s t week, P&VE and v a r i o u s c o n t r a c t o r s have i n v e s t i g a t e d t h e e f f e c t of r e d u c i n g t h e i n - f l i g h t v e n t a r e a i n the s p a c e c r a f t compartment o f t h e AS-201 and AS-202 v e h i c l e s . The r e s u l t s show t h a t i n no c a s e i s the s t r u c t u r a l b u r s t c a p a b i l i t y o f t h e s e r v i c e module LEM a d a p t e r , I U , o r S - I n forward s k i r t exceeded. However, MSC has s t a t e d t h a t t h e AP load on t h e s e a l between t h e command module and s e r v i c e module i s marginal and h a s s t i p u l a t e d t h a t i f t h e v e n t a r e a i s reduced t o 100 square i n c h e s , Since t h e t h e I U leakage should n o t be reduced from 15.4 s q u a r e inches. maximum p r e d i c t e d i n t e r n a l p r e s s u r e i s n o t dependent on l e a k a g e s , MSC has been asked t o determine i f t h e i r s t r u c t u r e can w i t h s t a n d t h e maximum compartment p r e s s u r e h i s t o r y f o r a 100-square-inch v e n t a r e a a s p r e s e n t e d i n R-AERO-AD-65-46. Based on the S a t u r n V t e s t d a t a , t h e e x t e r n a l p r e s s u r e s over t h e S-IVB forward s k i r t a r e somewhat h i g h e r on t h e S a t u r n V v e h i c l e interstage t h a n a n t h e S a t u r n I B because of t h e i n f l u e n c e o f t h e S-II/S-IV frustum, Since t h e S a t u r n I B and S a t u r n V v e h i c l e d e s i g n maximum and minimum e x t e r n a l p r e s s u r e s a r e p r e s e n t l y based on t h e PSTL-2 ( S a t u r n IB) d a t a , t h e S a t u r n V d i s t r i b u t i o n s w i l l be updated t o c o r r e c t t h i s p o r t i o n of t h e d a t a . P&VE has been n o t i f i e d o f t h i s d i s c r e p a n c y and w i l l i n c o r p o r a t e t h e c o r r e c t e d d i s t r i b u t i o n i n t o t h e r e d e s i g n o f t h e S-IVB forward skirt, �b. Apollo-Saturn I B Aerodynamic C h a r a c t e r i s t i c s : The f i n a l aerodynamic c h a r a c t e r i s t i c s of t h e Apollo-Saturn I B v e h i c l e s a r e complete. Included i n t h i s r e p o r t w i l l be t o t a l v e h i c l e s t a t i c s t a b i l i t y and a x i a l f o r c e c h a r a c t e r i s t i c s , l o a d d i s t r i b u t i o n s , and component This w i l l be a c o m p i l a t i o n and r e f i n e m e n t aerodynamic c h a r a c t e r i s t i c s o f t h e d a t a t o be used f o r design confirmation. These d a t a a r e being p u b l i s h e d i n a NASA TMX. . c. AmesD S a t u r n ~ ~ I C e n t a uP r e s s u r e Test: The l a r g e s c a l e S a t u r n centaur p r e s s u r e t e s t scheduled f o r Ames wind t u n n e l f a c i l i t i e s has been postponed because of t h e r e c e n t changes i n t h e Voyager spacec r a f t requirements. These t e s t s t o be conducted by CCSD w i l l be rescheduled f o l l o w i n g a d e c i s i o n o n t h e Centaur payload c o n f i g u r a t i o n . d. S a t u r n I ~ / C e n t a u rMod i f i c a t i o n Study: As r e q u e s t e d by JPL, MSFC r e c e n t l y conducted a s t u d y t a determine the f e a s i b i B i t y of i n c r e a s i n g t h e payload volume of the Saturn 1 8 I ~ e n t a u r v e h i c l e . Because of t h e l imited time a l l o t t e d f o r t h e s t u d y , o n l y two o f t h r e e proposed c o n f i g u r a t i o n s were s t u d i e d , one b e i n g s i m i har t o the p r e s e n t S a t u r n PB/ Centaur v e h i c l e w i t h a 176-inch c y l i n d r i c a l shroud extension. and t h e o t h e r having a hammerhead (298-inch d i a m e t e r ) payload shroud. The aerodynamic c h a r a c t e r i s t i c s f o r t h e s e v e h i c l e s were e s t i m a t e d , and the d a t a a r e being prepared f o r p u b l i c a t i o n . 2. Saturn V a. Load D i s t r i b u t i o n s : Pre liminary load d i s t r i b u t i o n s f o r t h e S a t u r n V v e h i c l e with a Voyager payload have been r e q u e s t e d by t h e Dynamics and P l i g h t Mechanics D i v i s i o n . These d i s t r i b u t i o n s a r e being assembled by the Northrop Space L a b o r a t o r i e s , Three c o n f i g u r a t i o n s a r e being considered; 260-inch c y l i n d e r s of 20, 40, and 60 f e e t a r e being i n s e r t e d between t h e I U and t h e Voyager payload. A Mach 1 . 7 i s b e i n g considered. r a n g e of 1.5 - be S-Hc/s-II I n t e r s t a g e T e s t : T e s t s w i l l be conducted i n t h e MSFC 14-inch t u n n e l to determine t h e s t a t i c aerodynamic c h a r a c t e r i s t i c s of t h e S a t u r n V S-PC/S-11 i n t e r s t a g e ring. These d a t a a r e r e q u i r e d f o r p r e d i c t i o n of impact a r e a s . P r e l i m i n a r y model d e s i g n i s i n p r o g r e s s . Based on e s t i m a t e d hardware d e l i v e r y d a t e s , the t e s t s w i l l be conducted i n February 1966. c. Hinge Moment: A p r e l i m i n a r y a n a l y s i s r e p o r t of t h e Phase II Lewis h i n g e moment t e s t r e s u l t s has been r e c e i v e d from Boeing. The r e p o r t i s being reviewed by t h e Experimental Aerodynamics Section. The model f o r t h e Phase I11 t e s t a t Lewis i s n e a r l y complete, Plans a r e t o s h i p t h e model t o Lewis t h e week o f October 1 8 , 1965. T e s t i n g i s scheduled t o b e g i n approximately December 1, 1965. �d. Fin-Shroud I n t e r f e r e n c e - F r e e Aerodynamics : A meeting was h e l d a t C o r n e l l A e r o n a u t i c a l Laboratory t o d i s c u s s d e t a i l s o f t h e forthcoming S a t u r n V fin-shroud i n t e r f e r e n c e - f r e e aerodynamic i n v e s t i g a t i o n i n t h e 8 - f o o t t r a n s o n i c t u n n e l . The meeting was concerned mainly w i t h model d e s i g n , c o n s t r u c t i o n , and t e s t i n g . The scheduled t e s t d a t e w i l l be dependent upon t h e time r e q u i r e d f o r C o r n e l l t o d e s i g n and b u i l d They now have a 6-week t u n n e l s c h e d u l i n g l e a d time t h e r e q u i r e d models. which could p o s s i b l y correspond t o t h e time n e c e s s a r y f o r model d e s i g n and c o n s t r u c t i o n once t h e c o n t r a c t i s f i n a l i z e d . 3. General a. O r i f i c e C o e f f i c i e n t Study: A r e v i s e d t e s t program and p r e t e s t r e p o r t a r e being prepared by Northrop Space L a b o r a t o r i e s . This document w i l l i n c l u d e t h e changes and a d d i t i o n s which were d i s c u s s e d d u r i n g t h e p r e s e n t a t i o n made t o the branch by Nsrthrop. This r e p o r t w i l l r e p r e s e n t t h e b a s i s f o r o u r j u s t i f i c a t i o n t o Ames d u r i n g t h e planned f e a s i b i l i t y conference which w i l l be scheduled t o t a k e p l a c e a t Ames w i t h i n approximately two weeks. b. Lockheed T r i s o n i c Program: The f i n a l t e s t phase which began September 24, 1965, i n t h e MSFC 14-inch t u n n e l i s c o n t i n u i n g satisfactorily. T e s t s a r e scheduled t o be completed by October 27, 1965. Data a n a l y s i s and p r e s e n t a t i o n a r e t o be f i n a l i z e d by September 1966. c. J P L ' t o o l Wall" T e s t : Model checkout and b a l a n c e c a l i b r a t i o n a r e i n p r o g r e s s a t JPL f o r t h e forthcoming S a t u r n IBIS-ID s t a g e "cool w a l l " s t a t i c s t a b i l i t y i n v e s t i g a t i o n , T e s t s a r e scheduled i n t h e 21-inch hypersonic t u n n e l beginning November 22, 1965. B. Electromechanical Branch 1. TASF Equipment Development A memorandum d a t e d October 25, 1965, gave t h e s t a t u s s f equipment being developed f o r t h e Thermo-Acoustic Simulation F a c i l i t y (TASF). The major items a r e a s follows: I n s t r u m e n t a t i o n Systems Tank Farm I n t e r c o n n e c t i o n s Cold Flow Duct Cold Flow C o n t r o l Cold Flow Models Cold Flow Measuring C a r t Hot Flow Models Hot Flow Measuring C a r t Equipment Foundation Flow V i s u a l i z a t i o n Gas Sampling Temperature Pressure A l l items a r e about t w o - t h i r d s complete and should be f i n i s h e d near t h e end o f t h e year. �2. 50K H e r t z Data A c q u i s i t i o n A s i x - c h a n n e l magnetic t a p e system f o r r e c o r d i n g d a t a t o 50K Hertz w i t h time f i d e l i t y s u f f i c i e n t f o r c r o s s c o r r e l a t ion on playback has been checked o u t . The s i g n a l - t o - n o i s e r a t i o of approximately 36db i s v e r y good f o r t h e wide band (1.5 Mega H e r t z ) e l e c t r o n i c s . 3. Residual Gas Analyzer The d e s i g n has been completed f o r a gas m o n i t o r i n g system f o r t h e Low Density Chamber, This r e s i d u a l gas a n a l y z e r i s designed t o o p e r a t e a t p r e s s u r e s i n t h e range of 1 0 " ~ t o r r when t h e chamber i s o p e r a t i n g a t p r e s s u r e s up t o 1 0 " t~o r r w i t h v a r i o u s g a s e s i n t h e n o z z l e in-flow. A unique d e s i g n concept i s i n t r o d u c e d f o r a d j u s t i n g t h e conduct a n c e t o p r o v i d e t h e a p p r o p r i a t e p r e s s u r e drop. 4. Automatic Boundary Layer Probe This probe, designed f o r t h e 14" t u n n e l , has completed checkout and i s scheduled f o r use w i t h i n 30 days. A r e p o r t on t h e equipment w i l l be i s s u e d b e f o r e use. This p r e c i s i o n - c o n t r o l led probe has a 2-inch t r a v e r s e w i t h m u l t i p l e a d j u s t a b l e p r e s e l e c t e d p o s i t i o n s a c c u r a t e t o P 0.001 inches, To account f o r t u n n e l w a l l motion i n t h e porous w a l l t r a n s o n i c t e s t s e c t i o n , t h e probe w i l l a u t o m a t i c a l l y s e n s e t h e w a l l and r e f e r e n c e a l l measurements from t h e a c t u a l p o s i t i o n . 5. Image Plane Model Support The d e s i g n o f a m i r r o r image model s u p p o r t f o r t h e 14" t u n n e l i s 60 p e r c e n t complete. The system w i l l i n c l u d e a s p l i t t e r p l a t e s u p p o r t f o r comparative and supplementary t e s t i n g . T h i s technique i s needed f o r 0 180 d e g r e e a n g l e - o f - a t t a c k t e s t s and o t h e r work. The e l i m i n a t i o n o f m u l t i p l e models and s t i n g s and s t i n g e f f e c t s i s p o s s i b l e . It i s a n t i c i p a t e d t h a t t h e image model w i l l produce b e t t e r r e s u l t s t h a n t h e c o n v e n t i o n a l h a l f model. The most s e v e r e problem w i l l be s u i t a b l e gap c o n t r o l between t h e model halves. Completed equipment i s expected i n February 1966. - 6. Dynamic Damping Balance Continued development o f e l e c t r i c a l l y d r i v e n dynamic damping balance has brought t h e frequency t o 130 cps a t r e a s o n a b l e amplitudes. The s t r u c t u r a l i n t e g r i t y i s t h e most d i f f i c u l t a s p e c t o f r a i s i n g t h e o p e r a t i n g frequency. Following p r e l i m i n a r y t e s t i n g d u r i n g t h e month of November, o t h e r models and r o t a t i o n a l c e n t e r s w i l l be d e v i s e d f o r a f u l l t e s t range c a p a b i l i t y . �C. F a c i l i t i e s Branch 1. Impulse Base Flow F a c i l i t y The S - I 1 program was completed i n e a r l y October. This program confirmed h i g h nozzle-wall h e a t i n g r a t e s f o r small gimbal angles. The model High Reynolds Number F a c i l i t y was then i n s t a l l e d . Checkout of t h e t r a n s o n i c f e a s i b i l i t y i s underway. Although flow t r e n d s i n t h e supply tube a r e a s expected, some p e c u l i a r i t i e s do e x i s t . E x p l o r a t i o n of t h e s e p e c u l i a r i t i e s i s expected a f t e r i n s t a l l a t i o n o f a d d i t i o n a l p r e s s u r e i n s t r u m e n t a t i o n . Subsonic and s u p e r s o n i c t e s t s a r e expected t o b e g i n i n e a r l y November. 2. 1 4 X 14-Tach T r f s o n i c Wind T u m e % Phase I1 of 'TWT 295 occupied t h e 14-Fneh t u n n e l d u r i n g October. This was a n i n v e s t i g a t i o n by Lockheed t o determine t h e e f f e c t s of a s y s t e m a t i c v a r i a t i o n of geometric parameters on t h e l i n e a r aerodynamic l o a d s of a cone-cylinder f r u s t u m - c y l i n d e r model c o n f i g u r a t i o n . Radial and s u r f a c e p r e s s u r e d i s t r i b u t i o n s a r e t o be determined f o r a n g l e s o f attack. The t e s t i s i n p r o g r e s s w i t h a n a n t i c i p a t e d completion d a t e of e a r l y November. T o t a l r u n s t o d a t a a r e 1028, 3. 7 X 7-Inch B i s o n i c Wind Tunnel An i n v e s t i g a t i o n by Wyle L a b o r a t o r i e s i s c o n t i n u i n g i n t h e BWT on t h e s e r i e s o f w a l l mounted, s e m i c i r c u l a r s e c t i o n c y l i n d e r - f l a r e c y l i n d e r models t o determine, by flow v i s u a l i z a t i o n methods, t h e r e g i o n s o f s e p a r a t e d flow and o s c i l l a t i n g shocks. T o t a l r u n s t o d a t e a r e 127. 4. Thermal and Acoustic Simulation F a c i l i t y Work i s s t e a d i l y p r o g r e s s i n g on support items such a s f a c i l i t y h i g h p r e s s u r e p i p i n g and e l e c t r i c a l power i n s t a l l a t i o n , The c o n c r e t e pads t o mount t h e r e c e n t l y a c q u i r e d s u r p l u s high p r e s s u r e t a n k s should be f i n i s h e d i n time t o accommodate tank d e l i v e r y . D e l i v e r y o f t h e h e a t e r i s s t i l l scheduled f o r mid-November, b u t i t i s expected t o s l i p a t l e a s t one week because o f mechanical It i s expected t h a t f i n a l p l a n t checkout problems i n t h e f i n a l assembly. Because of t h e a d d i t i o n of t h e h e a t e r w i l l be made around mid-November, o f a c o l d flow f a c i l i t y t o t h e same b u i l d i n g occupied by t h e helium h e a t e r , c e r t a i n m o d i f i c a t i o n s have been requested. These items i n c l u d e an a d d i t i o n a l r o l l - u p door i n s t a l l e d i n t h e middle bay, a l a r g e c o n c r e t e pad r e q u i r e d t o support a s s o c i a t e d heavy equipment, and a n a c o u s t i c a l l y i n s u l a t e d i n s t r u m e n t a t ion room, �5. Hot Flow T e s t F a c i l i t y F i n a l m o d i f i c a t i o n s have been completed t o t h e h e a t e r . T e s t i n g i s scheduled by R-AERO-AT a s t e s t hardware becomes a v a i l a b l e . 6. Hypersonic Shock Tunnel Diaphragms i n both C o r b l i n compressors were r e p l a c e d t o avoid contaminating t h e g a s h a n d l i n g system w i t h o i l . Upon removing t h e diaphragms, it was discovered t h a t two o f t h e t h r e e i n t h e 15,000 p s i machine had a l r e a d y f a i l e d . New diaphragms r e c e i v e d from t h e manufacturer were i n s p e c t e d and r e t u r n e d because of i n f e r i o r q u a l i t y . A s t u d y i s b e i n g conducted t o determine t h e b e s t m a t e r i a l a v a i l a b l e w i t h t h e thought i n mind of f a b r i c a t i n g diaphragms in-house. The helium p u r i f i c a t i o n system has n o t worked p r o p e r l y It appears t h a t t h e timing mechanism i n s i d e t h e u n i t i s thus f a r . v e r y c r i t i c a l and was shaken o u t o f p o s i t i o n d u r i n g t r a n s p o r t a t i o o . A f a c t o r y r e p r e s e n t a t i v e i s r e p a i r i n g the unit. The 20 mm shock tube f a c i l i t y was p u t i n t o o p e r a t i o n a l s t a t u s i n p r e p a r a t i o n f o r experimental t e s t i n g r e q u e s t e d by R-AERO-AE, a s s o c i a t e d w i t h measurement of shock t u n n e l s t a g n a t i o n temperature by o p t i c a l means. Work i s c o n t i n u i n g on development o f an e x t e r n a l l y a c t i v a t e d n o z z l e plug v a l v e . I n i t i a l r e s u l t s a r e q u i t e promising. D. Thermal Environment Branch 1. Saturn I The summary r e p o r t of t h e thermal d a t a e v a l u a t i o n f o r t h e S a t u r n I v e h i c l e s has been d r a f t e d . An p r e l i m i n a r y copy was forwarded t o MSFC f o r review. P u b l i c a t i o n of t h i s r e p o r t (CCSD TN-AE-65-115) i s scheduled f o r November. P r e p a r a t i o n s have been i n i t i a t e d f o r t h e AS-201 flight. 2. Saturn I B a. Stage S e p a r a t i o n Thermodynamics Work i s p r o g r e s s i n g on p r e d i c t i n g p r e s s u r e on f l a t p l a t e s caused by t h e impingement of a r o c k e t motor exhaust; axisymmetric and two-dimensional models a r e being used i n an e f f o r t t o match e x i s t i n g experimental d a t a . Moderate s u c c e s s has been o b t a i n e d w i t h t h e axisymm e t r i c model i n t h a t t h e p r e s s u r e p r o f i l e shape i s matched r e a s o n a b l y w e l l ; however, t h e magnitudes o f t h e p r e s s u r e s a r e too l a r g e . �Heat r a t e s and p r e s s u r e d i s t r i b u t i o n s on t h e S-IBIS-IVB i n t e r s t a g e caused by impingement o f t h e S-IB retro-motor were p r e d i c t e d . The p r e s s u r e d i s t r i b u t i o n s were o b t a i n e d u s i n g a Newtonian flow assumption; h e a t i n g r a t e s were p r e d i c t e d u s i n g a f l a t p l a t e t u r b u l e n t flow a n a l y s i s . A more e x t e n s i v e a n a l y s i s ~ f t h e problem i s under way. b. Thermal Environmental A n a l y s i s An a n a l y s i s determining t h e maximum aerodynamic h e a t i n g environment f o r t h e SA-207 v e h i c l e w i t h 205K t h r u s t engines was completed. R e s u l t s show t h a t t h e magnitude o f t h e thermal environment w i l l be about 3 p e r c e n t g r e a t e r t h a n t h a t p r e v i o u s l y determined f o r t h e S a t u r n v e h i c l e (200K e n g i n e s ) , Because o f t h e s i m i l a r i t y between t h e 205K environment w i t h t h e 20QK d e s i g n c r i t e r i a environment, s e p a r a t e environmental d e s i g n c r i t e r i a f o r t h e 205K s e r i e s o f v e h i c l e s w i l l n o t be established. An i n v e s t i g a t i o n s f aerodynamic h e a t i n g p r e d i c t i o n t e c h n i q u e s f a r hypersonic v e h i c l e s a t high a l t i t u d e s has been delayed. The a p p r o p r i a t e e q u a t i o n s f o r c a l c u l a t i n g aerodynamic h e a t i n g i n f r e e molecular and s l i p f l a w w i l l be programmed a s time permits. Continuum flow w i l l be assumed a t p r e s e n t f o r c a l c u l a t i n g t h e upper s t a g e environments, T h i s procedure w i l l y i e l d s l i g h t l y c o n s e r v a t i v e h e a t i n g r a t e s . Engine b e l l and a s p i r a t o r d a t a r e c e i v e d from c a l o r i m e t e r s mounted o n t h e SA-9 and SA-10 v e h i c l e s have been i n v e s t i g a t e d and compared w i t h p r e d i c t e d thermal environments used i n p r i o r a n a l y s e s (CCSD TB-AE-65191). S l i g h t adjustments were made i n t h e p r e v i o u s l y proposed a s p i r a t o r and h e a t exchanger environments, I n a d d i t i o n , environments have been e s t a b l i s h e d f o r each o f t h e s u p p o r t i n g bands on both the inboard and outboard engines. These proposed H-1 engine environments on t h e S a t u r n I B a r e scheduled t o be published i n November. A more complete examination of t h e d a t a o b t a i n e d d u r i n g t r a n s o n i c o p e r a t i o n a t AEDC has i n d i c a t e d t h a t t h e expected Mach number and a l t i t u d e were n o t o b t a i n e d . T r a n s i e n t e x t e r n a l flow d u r i n g t h e combustion e v e n t makes a l l d a t a q u e s t i o n a b l e , The t e s t i s c o n t i n u i n g , and a t t e m p t s w i l l be made t o o b t a i n v a l i d i n f o r m a t i o n a t a Mach number o f 1,6. A r e p o r t describing the r e s u l t s of the thin-film r e s i s t a n c e thermometer c a l i b r a t i o n t e s t s r u n a t Hy-Cal Engineering i s n e a r i n g completion, This r e p o r t w i l l be p u b l i s h e d a s CCSD TN-AE-65-113, A t e c h n i c a l n o t e concerned w i t h t h e H-1 engine r a d i a t i o n f o r nonequilibrium c o n d i t i o n s was completed i n rough d r a f t form. Several mathematical and computational d i f f i c u l t i e s encountered i n t h e c a l c u l a t i o n o f t h e e m i s s i v i t y f o r s o l i d carbon p a r t i c l e s have been overcome. Form f a c t o r s f o r t h e g e n e r a l r a d i a t i o n program a r e being formulated. �The s t u d y of t u r b u l e n t j e t mixing w i t h a f t e r b u r n i n g i s continuing. P r e l i m i n a r y r e s u l t s have been o b t a i n e d f o r t h e c o n s t a n t p r e s s u r e a n a l y s i s assuming chemical e q u i l i b r i u m c o n d i t i o n s . A t e c h n i c a l b u l l e t i n t o be i s s u e d i n December p r e s e n t s t h e d e t a i l s o f t h e a n a l y s i s , a s w e l l a s a comparison of r e s u l t s f o r t h e f r o z e n and f l a m e - f r o n t chemistry c a s e s . c. R e t r o r o c k e t Impingement Heating o n S-IB/S-IVB Interstage Aft Heating r a t e s on t h e S-PB/S-IVB a f t i n t e r s t a g e due t o r e t r o r o c k e t exhaust impingement have been analyzed f o r P&VE by t h i s branch (memo R-AERO-AT-65-3O),to determine whether t o add K o r ~ t h e r mi n s u l a t i o n Since t h e h e a t i n g r a t e s agreed f a i r l y w e l l w i t h to the a f t interstage. Douglas-calculated h e a t i n g r a t e s , i t was decided t o add i n s u l a t i o n t o v e h i c l e 201 and p o s s i b l y 202, A more d e t a i l e d a n a l y s i s of h e a t i n g t o t h i s r e g i o n w i l l be performed i n a n a t t e m p t t o reduce h e a t i n g r a t e s . There i s a danger t h a t , i f t h e i n s u l a t i o n i s l e f t on t h e f i r s t o r b i t a l c o a s t m i s s i o n ( v e h i c l e 2 0 3 ) , t h e r e t r o r o c k e t s w i l l a b l a t e and e r o d e t h e Korotherm i n s u l a t i o n such t h a t t h i s m a t e r i a l w i l l impinge upon and contaminate t h e S-IVB t a n k w a l l s , This w i l l i n c r e a s e t h e a b s o r p t i v i t y o f t h e p o i n t on t h e w a l l s r e s u l t i n g i n more s o l a r h e a t i n g t o t h e S-IVB, t h u s i n c r e a s i n g t h e amount of hydrogen b o i l - o f f , R e s u l t s of t h e C o r n e l l r e t r o r o c k e t t e s t s (memo R-AERO-AT-65-20) a r e expected t o be a v a i l a b l e by February; it i s hoped t h a t t h i s experimental i n v e s t i g a t i o n , a s w e l l a s t h e more d e t a i l e d a n a l y t i c a l study, w i l l b r i n g the h e a t i n g r a t e s down. 3. Saturn ~B/Centaur a. Thermal Envi ronmental A n a l y s i s An a n a l y s i s was s t a r t e d t o determine t h e maximum aerodynami c h e a t i n g environment a s s o c i a t e d w i t h t h e proposed S a t u r n U B / ~ e n t a u r c i s l u n a r Pegasus t r a j e c t o r y , C a l c u l a t i o n s show t h a t the t o t a l aerodynamic h e a t i n g r e s u l t i n g from t h i s t r a j e c t o r y w i l l be l e s s t h a n h a l f t h a t produced by t h e d e s i g n c i r t e r i a environment f o r t h e AS-201 and AS-202 v e h i c l e s . Analyses were i n i t i a t e d i n an e f f o r t t o r e f i n e t h e p u b l i s h e d aerodynamic h e a t i n g environment o f t h e S a t u r n I ~ / ~ e n t a uVoyager r miss ion. b. H a Venting Study The hazards a s s o c i a t e d w i t h t h e v e n t i n g of gaseous hydrogen from t h e Centaur s t a g e o f t h e S a t u r n P ~ / ~ e n t a uhave r been studied. The r e s u l t s i n d i c a t e no flame hazard t o t h e v e h i c l e from t h e vented H2 gas and v i r t u a l l y no p o s s i b i l i t y o f d e t o n a t i o n r e s u l t i n g from e n t r a i n i n g t h e gaseous plume i n t h e c l u s t e r e d tank r e g i o n of t h e S-IB stage. These r e s u l t s w i l l be used i n determining t h e v e n t scheme t o be used on t h e v e h i c l e . �4. Saturn V a. Plume R a d i a t i o n Study A computer program has been w r i t t e n which a r r a n g e s a l a r g e number of axisymmetric and two-dimensional m e t h o d - o f - c h a r a c t e r i s t i c s plume s o l u t i o n s i n t o a n approximation o f t h e plume flow f i e l d f o r t h e S-IC and S - I 1 s t a g e s , The o u t p u t from t h i s flow f i e l d program w i l l be used i n t h e a n a l y s i s o f plume r a d i a t i o n , A flow f i e l d has r e c e n t l y been c a l c u l a t e d and w r i t t e n on t a p e t o a s s i s t GE i n t h e development and checkout of t h e r a d i a t i o n computer program, b. Base P r e s s u r e and Environment The p o r t ion o f t h i s s t u d y cur r e n t l y under i n v e s t i g a t i o n i n v o l v e s t h e t u r b u l e n t boundary l a y e r growth on nozzle w a l l s w i t h mass injection. The e f f e c t on t h e boundary l a y e r growth due t o t u r b i n e exhaust gas i n j e c t i o n i n t h e F-1 engine i s being examined. The F-1 c u r r e n t l y i n j e c t s t h e t u r b i n e exhaust i n t o t h e nozzle over approximately t h e downstream h a l f of t h e contour through a s e r i e s o f 24 s l o t s . A t u r b u l e n t boundary l a y e r program, i n c o r p o r a t i n g mass i n j e c t i o n through d i s c r e t e s l o t s , w i l l be u t i l i z e d t o g e t an i n i t i a l approximation o f t h e e f f e c t of the injection. Because o f t h e e x t e n s i v e approximations i n t h i s a n a l y s i s , a n o t h e r method assuming continuously d i s t r i b u t e d i n j e c t i o n w i l l be programmed and t h e r e s u l t s compared w i t h t h e d i s c r e t e s l o t a n a l y s i s . An e x t e n s i v e s e a r c h i s being conducted f o r the nozzle and t u r b i n e exhaust c o n d i t i o n s a s r e q u i r e d f o r r e a l i s t i c i n p u t t o t h e above programs. The d i s c r e t e s l o t i n j e c t i o n program i s ready t o r u n and w i l l be used a s soon a s the n e c e s s a r y i n p u t d a t a a r e assembled. A s u b r o u t i n e w i l l then be w r i t t e n t o i n c o r p o r a t e t h e d i s t r i b u t e d i n j e c t i o n a n a l y s i s i n t o t h e program, c, Heat T r a n s f e r and P r e s s u r e Measurements i n a Cavity Formed by a Rocket Engine Exhaust The l u n a r c a v i t y experimental program i s proceeding a c c o r d i n g t o schedule, The t e s t s w i l l s t a r t immediately a f t e r completion of t h e h i g h Reynolds number p i l o t s t u d y , which i s expected t o be November 15. I n i t i a l h e a t t r a n s f e r and p r e s s u r e c a l c u l a t i o n s have been s u p p l i e d t o R-AERO-AFG f o r c a l i b r a t i o n purposes, and a drawing o f t h e sample l u n a r c a v i t y has been g i v e n t o F a b r i c a t i o n f o r c o n s t r u c t i o n . �d. S-IC Stage ( S h o r t D u r a t i o n Base Heating T e s t ) The d e t a i l e d a n a l y s i s o f t h e t e s t d a t a from t h e Lewis Research @ e n t e r \ 8 by 6 Foot Supersonic Tunnel has been completed and w i l l soon be r e l e a s e d . A document i s now being w r i t t e n which w i l l i n c l u d e a l l d a t a o b t a i n e d u s i n g t h e s h o r t d u r a t i o n S-IG model. e. S - I I Stage (Base Heating T e s t s ) The S - I 1 base h e a t i n g t e s t s a t MSFC were completed on October 15, It i s planned t h a t t h e S-I1 model w i l l be used i n r e s e a r c h t e s t s on c r a t e r h e a t i n g and then be r e t u r n e d to CAL f o r t e s t s t o d e t e r mine t h e f o r c e and p r e s s u r e on t h e i n t e r s t a g e s k i r t d u r i n g second p l a n e separation. 5. General a. A b l a t i o n Program A d i g i t a l computer program i s being formulated f o r a n a l y z i n g a b l a t i n g thermal p r o t e c t i o n systems, The program i s being developed i n two phases. Phase 1 w i l l produce a "Working Toolq>rogram t o handle m a t e r i a l s f o r which experimental d a t a a r e a v a i l a b l e , w h i l e Phase 11 w i l l produce a program having d i v e r s i f i e d t h e o r e t i c a l capabilities. The "Working Tool" program i s n e a r i n g product i o n s t a t u s . Numerous checkout r u n s a r e being made t o e x e r c i s e a l l c a p a b i l i t i e s o f t h e program, and t o a s c e r t a i n t h a t t h e l o g i c t o r u n c a s e s "back-to-back" i s o p e r a t i n g properly. The u s e r " Manual i s being published. Two problems have r e c e n t l y been analyzed u s i n g t h i s program. The f i r s t involved d e t e r m i n a t i o n o f temperatures a t v a r i o u s l o c a t i o n s on an R. O.T, type v e h i c l e f o r two r e - e n t r i e s . Angle-of-attack e f f e c t s were included. The second involved determining c o n v e c t i v e h e a t i n g r a t e s on t h e Apollo Command Module f o r two S a t u r n V AS-501 re-entry trajectories. Also, a s e p a r a t e h e a t p r o t e c t i o n system weight t r a d e - o f f s t u d y i s being conducted u s i n g t h e "Working Tool? program. b. Thermo-Methods Analysis - Flat-Plate Modification F u r t h e r p r o g r e s s has been made i n o b t a i n i n g t r a n s f o r m a t i o n s which can be a p p l i e d t o f l a t - p l a t e s o l u t i o n s of t h e t u r b u l e n t momentum i n t e g r a l e q u a t i o n t o o b t a i n axisymmetric s o l u t i o n s . Comparisons a r e being made between t h i s transform method o f determining t h e t u r b u l e n t momentum t h i c k n e s s on axisymrnetric bodies and a more complicated computer method based on an i t e r a t i v e s o l u t i o n of t h e momentum i n t e g r a l equation. P r e l i m i n a r y comparisons have i n d i c a t e d t h a t t h e transforms appear v a l i d . More e x a c t and e x t e n s i v e comparisons a r e t o follow. �c. E q u i l i b r i u m Real Gas/Normal Shock Program f o r S t a g n a t i o n P o i n t Heating The g o a l of t h i s s t u d y i s t o develop t h e * c a p a b i l i t y t o c a l c u l a t e s t a g n a t i o n p o i n t h e a t i n g - r a t e s f o r a blunt> body i n an e q u i l i b r i u m r e a l gas flow f i e l d . E f f o r t was dev6ted t o s o l v i n g t h e laminar boundary Two numerical l a y e r e q u a t i o n s i n t h e s t a g n a t i o n r e g i o n o f t h e b l u n t body. t e c h n i q u e s were used t o s o l v e the two-point boundary v a l u e problem r e s u l t i n g from t h e f o r m u l a t i o n o f t h e boundary l a y e r e q u a t i o n s . D i g i t a l computer programs were w r i t t e n f o r b o t h t e c h n i q u e s , and t h e r e s u l t i n g programs were checked o u t . S e v e r a l t e s t c a s e s were examined, and the r e s u l t s were found t o a g r e e w i t h r e s u l t s p u b l i s h e d by o t h e r workers, T r a n s p o r t p r o p e r t y c o r r e l a t i o n s were added t o both programs t o allow p r e d i c t i o n s of h e a t i n g r a t e s i n a i r . Work continued on t h e g e n e r a l problem of p r e d i c t i n g t r a n s p o r t p r o p e r t i e s f o r an a r b i t r a r y gas m i x t u r e , d, Thermal Analysis s f t h e LFV P a r t i a l l y Enclosed Engine Cluster An a n a l y s i s has been i n i t i a t e d t o p r e d i c t t h e s t e a d y s t a t e temperature d i s t r i b u t i o n s on r a d i a t i v e l y cooled r o c k e t n o z z l e s which a r e c l u s t e r e d and p a r t i a l l y enclosed. The v a r i o u s d i g i t a l computer programs t o be used i n t h i s a n a l y s i s a r e being checked o u t on t h e MSFC computer system. Version 1 3 ) . (Fortran I V - e. Cold Flow-Base Flow V i s u a l i z a t i o n T e s t s An experimental program i s t o begin a t AEDC i n the s p r i n g of 1966 which w i l l be used t o e v a l u a t e i n s t r u m e n t a t i o n techniques i n t h e s e v e r e environment of t h e h i g h s h e a r , t u r b u l e n t flow r e g i o n c r e a t e d by a four-nozzle c l u s t e r . A s p e c i a l t e s t c e l l w i l l be c o n s t r u c t e d t h a t w i l l a l l o w r a t i o s of the c e l l ambient p r e s s u r e t o nozzle t o t a l p r e s s u r e o f t h e o r d e r of 10 x lom4., This p r e s s u r e r a t i o i s s u f f i c i e n t t o achieve a f u l l y "choked" c o n d i t i o n i n the base r e g i o n , Design c o n s i d e r a t i o n s and c r i t e r i a o f t h e model and t e s t c e l l a r e d i s c u s s e d i n MsFc/NASA Memorandum R-AERO-AT-65-18. I n s t r u m e n t a t i o n techniques t h a t w i l l be e v a l u a t e d i n t h i s t e s t program a r e a s follows: (1) - developing r e l a t i v e l y Boeing (NAS8-20079) c o n v e n t i o n a l i n s t r u m e n t s t o measure p r e s s u r e , d e n s i t y , and flow d i r e c t ions. �f. - (2) P h i l c o (NAS8-20503) developing a two-wire h o t w i r e probe t o measure v e l o c i t y and flow d i r e c t i o n . (3) Brown (NAS8-20145) developing a system t o measure flow v e l o c i t y by doppler s h i f t of l i g h t s c a t t e r e d from a l a s e r beam d i r e c t e d through t h e flow f i e l d . (4) Other systems and techniques a r e being e v a l u a t e d f o r p o s s i b l e a p p l i c a t i o n t o t h e AEDC t e s t d . - Thermodynamics and Chemistry o f Reacting Gases The s t u d y o f t h e gas mixing problem i s being conducted along t h e following l i n e s : (1) Determine what a r e t h e m e c h a n i s t i c chemical e q u a t i o n s d e s c r i b i n g t h e combustion p r o c e s s . (2) Determine which o f t h e two major methods o f h a n d l i n g t h e chemistry o f t h e mixing problem i s most r e a d i l y g e n e r a l i z e d . (3) Determine how t h e ~AsA/Lewis thermochemical program can be segmented, (A computer program d e s c r i b i n g t h e dynamics of mixing w i l l use a segment of t h e Lewis program f o r t h e s o l u t i o n t o t h e chemistry p a r t of t h e problem.) A f i n i t e r a t e chemistry computer program was o b t a i n e d through ~AsA/Lewis. T h i s program i s being made o p e r a t i o n a l on MSFC'S computers f o r use i n t h e study o f I3rayqs f r e e z i n g c r i t e r i a . g. Computer Programs An e n g i n e e r i n g r e p o r t i s b e i n g prepared t o document t h e u t i l i z a t i o n o f a computer program, o b t a i n e d from NASA Lewis Research C e n t e r , f o r the computation o f chemical e q u i l i b r i u m compositions of r o c k e t exhaust plumes, P u b l i c a t i o n of t h i s r e p o r t i s scheduled f o r December. Work i s c o n t i n u i n g on t h e m o d i f i c a t i o n t o t h e c a l o r i m e t e r d a t a r e d u c t i o n computer program (CU0014) on a low p r i o r i t y b a s i s . During t h e p r e c e d i n g month, a l l o f t h e SA-10 s l u g c a l o r i m e t e r d a t a and one SA-10 membrane c a l o r i m e t e r d a t a were reduced w i t h t h e modified program. A c u r s o r y examinat ion o f t h e d a t a i n d i c a t e s t h a t t h e r e d u c t i o n p o r t i o n of t h e program i s o p e r a t i o n a l . To d a t e , t h e p l o t r o u t i n e s have n o t been added. P u b l i c a t i o n o f t h e s e m o d i f i c a t i o n s i s scheduled f o r December 1965, a s CCSD TN-AE-65-82. �Documentation of c@NDA i s c o n t i n u i n g on a low p r i o r i t y b a s i s , and i s approximately s i x t y p e r c e n t complete. E. Unsteady Aerodynamics Branch 1. I n f l i g h t F l u c t u a t i n g P r e s s u r e and Acoustic Environment Preliminary estimates of the Saturn V i n f l i g h t a c o u s t i c environments have been completed. The environments cover a Mach range of - 8 t o 2.2 f o r t h e v e h i c l e a t zero a n g l e o f a t t a c k , These environments a r e being prepared f o r publication, Wind f l a r e b o d i e s have t e s t s the effects on s e p a r a t e d flow t u n n e l s t u d i e s of s e p a r a t e d flow on cone c y l i n d e r been i n i t i a t e d i n t h e MSFC 7-inch t u n n e l , From t h e s e o f Reynolds number, Mach number, and model geometry w i l l be d e l i n e a t e d , Base p r e s s u r e f l u c t u a t i o n measurements have been implemented o n t h e t e s t "Saturn V Cold Flow Nozzle Aerodynamic Hinge Moment T e s t AD3-64." There w i l l be e i g h t f l u c t u a t i n g p r e s s u r e measurements l o c a t e d i n one quadrant o f t h e base. 2. Launch S i t e Acoustic Environment The p r e d i c t i o n program f o r t h e s p a t i a l c o r r e l a t i o n f u n c t i o n s on t h e v e h i c l e s u r f a c e f o r both t h e s t a t i c f i r i n g and launch, engine g e n e r a t e d a c o u s t i c environment has been completed, Attempts t o reduce t h e computing time have n o t been s u c c e s s f u l . The fundamental e q u a t i o n i s being s i m p l i f i e d , A technique f o r p r e d i c t i n g t h e sound p r e s s u r e l e v e l r e c e i v e d a t a f a r - f i e l d l o c a t i o n from a n a c o u s t i c , broadband, d i r e c t i o n a l , p o i n t s o u r c e r a d i a t i n g i n t o a n inhomogeneous medium has been developed. I n i t i a l r e s u l t s from t h i s program, r e c e i v e d t h i s week, a r e being compared t o measured v a l u e s , P r e d i c t e d and measured r e s u l t s w i l l be compared under a wide v a r i e t y o f c o n d i t i o n s t o e v a l u a t e t h e accuracy o f t h i s technique. 3. Panel F l u t t e r Aerodynamics P r e l i m i n a r y p a n e l f l u t t e r t e s t s were conducted a t Langley Research Center October 18 through October 22, 1965, on p a n e l s s i m i l a r t o t h o s e on t h e S-IVB forward s k i r t . The p a n e l s t e s t e d had an a s p e c t r a t i o (L/w) of 4.5 and were .032 inch t h i c k , The t e s t s were conducted a t Mach 1.96 under v a r i o u s compressive s t r e s s and b u r s t i n g d i f f e r e n t i a l pressure conditions. �The r e s u l t s show t h a t t h e p a n e l s f l u t t e r e d w e l l below dynamic p r e s s u r e s encountered d u r i n g f l i g h t (maximum dynamic p r e s s u r e b e i n g 780 p s f ) . With z e r o p r e s s u r e d i f f e r e n t i a l , f l u t t e r was encountered a t 180 p s f when t h e p a n e l was loaded t o c r i t i c a l buckling c o n d i t i o n s . Applying a p r e s s u r e d i f f e r e n t i a l o f .25 p s i had no e f f e c t on t h e minimum f l u t t e r q , and a A p of .35 p s i had l i t t l e e f f e c t . However, when a p r e s s u r e d i f f e r e n t i a l of .40 p s i t o .50 p s i was a p p l i e d , f l u t t e r was o b t a i n e d a t a q of 720 p s f , b u t t h i s i s n o t t h e minimum f l u t t e r q s i n c e t h e p a n e l s could n o t be loaded t o t h e c r i t i c a l buckling Bsad w i t h t h i s pressure d i f f e r e n t i a l applied. The a d d i t i o n o f a v i s c o - e l a s t i c compound was a l s o t e s t e d . When a compound t h i c k n e s s o f .070 inch was a p p l i e d , t h e p a n e l f l u t t e r e d a t 400 p s f , under c r i t i c a l buckling load and z e r o p r e s s u r e d i f f e r e n t i a l conditions. No n o t i c e a b l e e f f e c t was recorded when t h e p r e s s u r e d i f f e r e n t i a l was increased. 4. S a t u r n V Ground Winds A p r e s e n t a t i o n was g i v e n t o c e n t e r management by R-AERO and R-P&VE on t h e S a t u r n V ground wind problem, The r e s u l t i n g a c t i o n items a r e summarized below: a. A l l v e h i c l e f r e e - s t a n d i n g c o n d i t i o n s a t KSC should be used t o measure wind-induced o s c i l l a t i o n . b. P&VE w i l l i n v e s t i g a t e t h e a d d i t i o n o f mechanical dampers f o r use a s s a f e t y devices. c. R-AERO w i l l i n v e s t i g a t e t h e a d d i t i o n o f aerodynamic " f i x e s " t o r e l i e v e t h e problem. d. The bending moments f o r 1.5 p e r c e n t s t r u c t u r a l damping w i l l be p r e d i c t e d . e. MSC w i l l be n o t i f i e d o f t h e probable ground winds program. f . Wind r e s t r i c t i o n s f o r S a t u r n v e h i c l e s 501, 502, and 503 should be analyzed and e v a l u a t e d . 5. S a t u r n I ~ / ~ e n t a uGround r Winds Model R-AERO-AU has r e c e i v e d a d e s i g n drawing o f t h e S a t u r n m / c e n t a u r ground winds model from Atkins and M e r r i l l , Inc. Upon approval of t h e drawing by R-AERO-AU, Atkins and M e r r i l l w i l l s t a r t c o n s t r u c t i o n of t h e model. �Atkins and M e r r i l l has r e q u e s t e d a t h i r t y - d a y e x t e n s i o n t o t h e model d e l i v e r y d a t e . This was approved by R-AERO-AU because Marshall was approximately one month l a t e i n supplying them w i t h f u l l s c a l e d e s i g n information. The d e l i v e r y d a t e i s now s e t f o r January 30, 1966. 6. A e r o e l a s t i c C h a r a c t e r i s t i c s o f Vehicle 203 Correspondence was r e c e i v e d from M r . E r i c i s s o n r e l a t i n g t o It i s M r . E r i c i s s o n o s o p i n i o n t h a t a p o t e n t i a l problem of v e h i c l e 203. i f t h e v e h i c l e f l i e s a t a nominal 4 O a n g l e s f a t t a c k through t h e Mach 1.0, t h e v e h i c l e w i l l e x p e r i e n c e s e v e r e aerodynamic number range o f 0,8 i n s t a b i l i t y . The p r o b a b i l i t y o f occurrence o f i n s t a b i l i t y d u r i n g 203 a s c e n t i s f a i r l y low s i n c e t h e v e h i c l e must meet t h e c o n d i t i o n s o u t l i n e d above. N e v e r t h e l e s s , a l i m i t e d experimental program has been i n i t i a t e d t o v e r i f y M r . Ericisson's hypothesis. - 7. Two-Dimens i o n a l Cylinder Data r e d u c t i o n i s c o n t i n u i n g a t t h e M a r t i n Company. Recent correspondence on MSFC c o n t r a c t s i n d i c a t e s t h a t t h e c o n t r a c t o r e x p e c t s o v e r r u n o f approximately $30,000. Since t h e o v e r r u n was n o t a n t i c i p a t e d , no allowance was made i n t h e ranch's budget. It i s p o s s i b l e t h a t a p o r t i o n of t h e amount may be o b t a i n e d from t h e Center fund f o r c o n t r a c t overruns VI, DYNAMICS AND FZIGHT MECHANICS DIVISION A. Dynamics A n a l y s i s Branch 1. Saturn I B a. A memo has been completed r e p o r t i n g t h e r e s u l t o f a d d i t i o n a l s l o s h i n g parameters f o r S a t u r n LB. A bending a n a l y s i s of AS-205 f i r s t f l i g h t s t a g e has been completed and w i l l be d i s t r i b u t e d A mem d e s c r i b i n g the e f f e c t o f t h e w i t h i n t h e n e x t r e p o r t period. c o n t r o l system on v e h i c l e n a t u r a l f r e q u e n c i e s has been published. Sloshing parameters f o r t h e two s t a g e s of f l i g h t o f t h e b. AS-205 v e h i c l e i s n e a r i n g completion. The parameters t h u s f a r c a l c u l a t e d i n c l u d e ( 1 ) parameters of t h e f i r s t mode o f o s c i l l a t i o n f o r t h e 70" Lox Tanks, 70" Fuel Tanks and 105" Lox Tank and ( 2 ) parameters o f t h e f i r s t , second, and t h i r d modes f o r t h e S-IVB s t a g e tanks. A r e p o r t w i l l be d i s t r i b u t e d w i t h i n t h e n e x t month according t o t h e schedule agreed upop by R-AERO-D and R-ASTR-F. A s i m i l a r s t u d y f o r AS-206 has been s t a r t e d and w i l l be completed w i t h i n t h e n e x t month. A bending a n a l y s i s o f t h e second f l i g h t s t a g e o f AS-202 and AS-203 i s n e a r i n g completion. �2. Saturn V a. A s t u d y has been made u s i n g t h e computer program developed e a r l i e r which c a l c u l a t e s t h e c o n t r o l g a i n s w i t h f i l t e r s f o r t h e rigid-body A case. The m i s s i l e c o n f i g u r a t i o n used was t h e S a t u r n AS-504 v e h i c l e . comparative s t u d y was made a t t = 75.117 and 83.633 sec. f o r t h e c a s e w i t h o u t f i l t e r s and f o r a body-fixed accelerometer u s i n g two d i f f e r e n t The c o n t r o l frequency was v a r i e d between 0.85 cps f i l t e r configurations. and 0.20 c p s , and t h e e f f e c t s f v a r y i n g t h e accelerometer h o e a t i o n and t h e damping was shown. The r e p o r t i s being prepared. b, The RSS bending moment d e s i g n d a t a f o r AS-506 a r e being computed f o r a nominal t r a j e c t o r y u s i n g a new s y n t h e t i c wind p r o f i l g f o r which t h e l i n e a r wind buildup begins a t ground l e v e l and blends t a n g e n t i a l l y i n t o t h e s h e a r buildup envelope. The g u s t i s r e p r e s e n t e d by a one-minusc o s i n e b u i l d u p and t a i l - o f f w i t h a c o n s t a n t p l a t e a u i n between, Ten time p o i n t s have been chosen f o r i n v e s t i g a t i o n f o r t h i s s t u d y , which i s being conducted t o determine t h e wind p r o f i l e e f f e c t on t h e d e s i g n response values. c. A t r a j e c t o r y - c o n t r o l s i m u l a t i o n program on t h e h y b r i d computer i s being developed, A major problem caused by t h e s h o r t a g e o f memory l o c a t i o n s i n t h e p r e s e n t equipment i s t h e s i m p l i f i c a t i o n of t h e assumptions and e q u a t i o n s normally used. A more complete s i m u l a t i o n f o r t h e new hybrid computer scheduled t o a r r i v e i n June i s a l s o being developed. d. A complete f i r s t s t a g e t r a j e c t o r y has been r u n on t h e DYNASAR six-degrees-of-freedom t r a j e c t o r y - c o n t r o l s i m u l a t i o n . A few programming and d a t a i n p u t e r r o r s found a r e b e i n g c o r r e c t e d . A good r u n i s a n t i c i p a t e d s h o r t l y , completing t h e f i r s t phase o f t h e program. e. Work i s c o n t i n u i n g on an e l a s t i c body response program which c o n s i d e r s g u s t p e n e t r a t i o n e f f e c t s . f , The study o f t h e S a t u r n V d e t a i l wind p r o f i l e s i s c o n t i n u i n g on h i g h speed computers. The purpose o f t h i s s t u d y i s two-fold: (1) t o determine t h e c h a r a c t e r i s t i c s and e v a l u a t e t h e v a r i o u s S-V c o n t r o l systems, and ( 2 ) t o h e l p develop a b e t t e r wind p r o f i l e and s t a t i s t i c a l approach f o r v e h i c l e response s t u d i e s . B a s i c r e s u l t s show t h a t accelerometer c o n t r o l y i e l d s 5-7 p e r c e n t bending moment r e d u c t i o n w h i l e A minimum guidance y i e l d s about 2-4 p e r c e n t bending moment r e d u c t i o n . g. Phase r o o t l o c i s t u d i e s f o r t h e v a r i o u s c o n t r o l system f o r AS-501 have been completed. The r e s u l t s a r e being p l o t t e d , and a r e p o r t i s being w r i t t e n , �h. A bending mode and s h e l l - f l u t t e r a n a l y s i s o f t h e S - I D s h e l l s t r u c t u r e i s i n progress. Plans a r e n e a r i n g completion f o r f u r t h e r t e s t i n g o f the Apollo s p a c e c r a f t t o e s t a b l i s h t h e bending c h a r a c t e r i s t i c s S e r v i c e Module I n t e r f a c e . These t e s t s w i l l be o f t h e Command Module performed by C h r y s l e r ; t e s t requirements a r e b e i n g s e t by t h e CDSF committee. T e s t d a t a from t h e o n e - f o r t i e t h s c a l e Langley model have been r e c e i v e d . P r e p a r a t i o n s a r e underway t o analyze t h i s model i n support of t h e ground winds e f f e c t s t u d i e s of R-AERO-AU. - i, A study has been made t o determine t h e e f f e c t s o f i n c l u d i n g t h e LEM f l e x i b i l i t y v i b r a t i o n a n a l y s e s of t h e S a t u r n V vehicle. A l l f l i g h t s t a g e s were included i n t h e study. The r e p o r t on t h i s s t u d y w i l l be d i s t r i b u t e d w i t h i n t h e n e x t r e p o r t p e r i o d , The p r e t e s t a n a l y s i s o f t h e Conf. III (S-IVIB and above) dynamic t e s t s has been r e c e i v e d from Boeing f o r review, S e v e r a l e r r o r s were found, which t h e c o n t r a c t o r was i n s t r u c t e d t o c o r r e c t . j, A bending mode and s h e l l - f l u t t e r a n a l y s i s , i n c l u d i n g t h e e f f e c t s of r i n g s and s t i n g e r s , has been completed f o r t h e forward s k i r t o f t h e S - I 1 s t a g e s , R e s u l t s o f t h i s a n a l y s i s have been published. 3. General a. A s t u d y i s being made t o c a l c u l a t e t h e c o n t r o l g a i n s w i t h f i l t e r s t h a t i n c l u d e t h e bending v i b r a t i o n of t h e v e h i c l e . The e q u a t i o n s a r e being d e r i v e d , and e v e n t u a l l y a computer program w i l l be w r i t t e n t o c a l c u l a t e t h e c o n t r o l gains. A study w i l l t h e n be made t o c a l c u l a t e t h e c o n t r o l g a i n s and t h e r i g i d body case w i l l be compared with t h e e l a s t i c case, b. The r o t a r y s l o s h problem w i t h a n o n l i n e a r s p r i n g and o s c i l l a t i n g mass p o i n t s r o l l i n g on a guided s u r f a c e of p a r a b o l i c form i s b e i n g i n v e s t i g a t e d f o r S a t u r n V, The r e p o r t was s t u d i e d f o r g e n e r a l i n f o r m a t i o n and t h e e q u a t i o n s of motion were w r i t t e n f o r a r i g i d v e h i c l e study. The e q u a t i o n s a r e being programmed f o r t h e analog computer, c, A study t o determine optimum g a i n s f o r r i g i d body r e s p o n s e i s n e a r i n g completion, The f i n a l computer r u n s w i l l be made s h o r t l y and t h e r e s u l t s r e l e a s e d i n a r e p o r t . d. A program i s b e i n g checked o u t which w i l l i n c l u d e t h e e l a s t i c e f f e c t s i n t h e d e t e r m i n a t i o n of optimum g a i n s f o r v e h i c l e response. 4. Contractors a. Northrop Work i s c o n t i n u i n g on t h e low g s l o s h study d u r i n g S-IVB o r b i t , No r e s u l t s have been o b t a i n e d a t t h i s time. An e x t r a p o l a t e d low g s l o s h model i s used f o r t h i s s t u d y , �b, General Dynamics The work on t h e n o n l i n e a r c h a r a c t e r is t i c s o f s l o s h i n g p r o p e l l a n t i s c o n t i n u i n g , b u t no new r e s u l t s a r e y e t a v a i l a b l e . A c o n t r a c t was l e t t o conduct a parameter s t u d y o f t h e low g s l o s h models d u r i n g S - I n o r b i t t o determine a more r e a l i s t i c s l o s h model, c. North American A semi-annual r e p o r t c o n t a i n i n g r e s u l t s f o r t h e f r e e o s c i l l a t i o n i n a c y l i n d r i c a l tank was r e c e i v e d . The b a s i c r e s u l t s i n d i c a t e t h a t t h e frequency i s n o n l i n e a r o n l y i n t h e second o r d e r ; t h e f i r s t o r d e r form i s missing. The development o f a numerical procedure f o r s o l v i n g n o n l i n e a r a l g e b r a i c e q u a t i o n s i s proceeding. Some d i f f i c u l t y i s being experienced i n g e t t i n g good convergence of some r o o t s . A multi-beam bending program was d e l i v e r e d d u r i n g t h e work p e r i o d . There a r e s t i l l e r r o r s i n t h e program which should be c o r r e c t e d soon. B. C o n t r o l Theory Branch 1. Saturn I B a. A s t u d y o f AS-206 t o determine t h e e f f e c t o f d i r e c t i o n a l winds o n bending moments and v e h i c l e r e s p o n s e s f o r t h e max q a time p o i n t i s i n progress. The d a t a o b t a i n e d from t h i s s t u d y w i l l be f u r n i s h e d P&VE t o determine i f t h e s t r u c t u r a l a j p l i m i t s a r e changed due t o t h e v a r i a t i o n i n Mach number and dynamic p r e s s u r e r e s u l t i n g from t h e v a r i o u s wind d i r e c t i o n s and wind speeds. Upon r e c e i p t of t h e a l p l i m i t a t i o n s , wind speed r e s t r i c t i o n s ( i f any) w i l l be determined f o r each wind d i r e c t i o n . ~ mff3, b, Using t h e AS-206 d a t a , t h e c o e f f i c i e n t s , m ' and have been i n v e s t i g a t e d t o g a i n some i n s i g h t i n t h e i r u s e s and t o determine t h e e f f e c t s of s m a l l changes i n i n p u t d a t a . The behavior o f m ' f 3 / ~ ' a s a f u n c t i o n o f mass l o s s was determined. Also, methods f o r e a s i e r h a n d l i n g of t h e aerodynamic d i s t r i b u t i o n s f o r p e r t u r b e d v a l u e s o f normal f o r c e c o e f f i c i e n t and c e n t e r o f p r e s s u r e have been i n v e s t i g a t e d . c. Vehicle responses and bending moments f o r f l i g h t times corresponding t o Mach 1, max q , a n d j u s t b e f o r e inboard engine c u t o f f a r e b e i n g determined f o r a cross-wind a t v a r i o u s wind speeds. These d a t a w i l l s u p e r s e d e d a t a p r e v i o u s l y published i n R-AERO-DCC-26-65, August 1 2 , 1965. �d , A g e n e r a l updating of t h e S a t u r n I B r i g i d body c o n t r o l r e s p o n s e s t u d i e s w i l l be i n i t i a t e d when new mass and t r a j e c t o r y d a t a based on updated c o n t r o l w e i g h t s a r e r e c e i v e d , e. A study has been i n i t i a t e d t o determine t h e maximum i n f t i a l c o n d i t i o n s a t s e p a r a t i o n due t o a c r i t i c a l l y timed engine f a i l u r e i n t h e I B s t a g e , T h i s s t u d y w i l l be s i m i l a r t o t h a t performed on S a t u r n V, f , The documentation of t h e SA-203 s e p a r a t i o n c o n t r o l s t a t i s t i c a l a n a l y s i s has been completed, The r e s u l t s show t h a t b i a s i n g t h e a n g l e of a t t a c k s t r o n g l y i n f l u e n c e s t h e s t a t i s t i c a l c h a r a c t e r i s t i c s o f t h e p o s t s e p a r a t i o n a t t i t u d e and a t t i t u d e r a t e e x c u r s i o n s , The documentation c a r r Fes a recommendat ion t h a t t h e SA-203 £1i g h t p r o f i l e be shaped such a s t o b i a s o u t t h e no-wind a n g l e of a t t a c k a t f i r s t stage separation. g. S t a b i l i t y s t u d i e s a r e s t i l l i n p r o g r e s s on v e h i c l e s SA-203 and AS-204 u s i n g p r e l i m i n a r y g a i n s and f i l t e r s , 2. u rt S a t u r n 1 ~ / ~ ea n Estimated r i g i d body c o n t r o l responses and bending moments September 30, 1965. have been documented i n Memo No. R-AERO-DCC-30-65, These d a t a a r e f o r time p o i n t s corresponding t o max qCl and max q f o r t h e proposed c o n f i g u r a t i o n s I I B ( t h e lengthened v e r s i o n ) and 111 ( t h e lengthened and widened v e r s i o n ) . 3. Saturn V a. A s t u d y has been performed t o i n v e s t i g a t e t h e maximum t r a n s i e n t s o c c u r r i n g a t S-Ic/s-11s e p a r a t i o n due t o a n engine f a i l u r e o c c u r r i n g a t such a time b e f o r e s e p a r a t i o n a s . t o cause t h e l a r g e s t magnitude o f t h e t r a n s i e n t t o occur a t t h e time o f p h y s i c a l s e p a r a t i o n . R e s u l t s o f t h e study i n d i c a t e t h a t maximum p i t c h r a t e s r e a c h approximately 4 d e g r e e s p e r second and the a t t i t u d e e r r o r approaches 12 d e g r e e s a t separation. The s t u d y was documented i n Memo No, R-AERO-DCC-34-65. b. An i n v e s t i g a t i o n h a s been made t o determine t h e impact t h a t a s t a g g e r e d shutdown sequence f o r t h e S-IC s t a g e e n g i n e s might have on s t a g e s e p a r a t i o n . As was expected, t h e s t a g g e r e d shutdown sequence has no s i g n i f i c a n t e f f e c t on t h e s e p a r a t i o n dynamics. The r e s u l t s of t h e i n v e s t i g a t i o n have been documented, c. The s t u d y t o determine t h e maximum e x c u r s i o n s a t s e p a r a t i o n due t o a c r i t i c a l l y timed engine f a i l u r e b e f o r e s e p a r a t i o n i s b e i n g extended t o determine t h e engine f a i l u r e i n t e r v a l which w i l l l e a d t o second s t a g e a t t i t u d e e x c u r s i o n g r e a t e r than 35 d e g r e e s , t h e p l a t f o r m l i m i t i n yaw. �4. General a. The development o f a d i g i t a l program t h a t w i l l compute t h e e x a c t c o n t r o l g a i n s f o r any s p e c i f i e d c o n t r o l frequency and damping and a l s o t h e r e s u l t i n g t r a n s i e n t response t o a g i v e n wind i n p u t has been initiated. The feedback ( c o n t r o l law) can c o n t a i n any combination o f t h e f o l l o w i n g sensed v a r i a b l e s : a t t i t u d e , a t t i t u d e r a t e , a c c e l e r a t i o n , v e l o c i t y , p l a t f o r m a c c e l e r a t i o n , p l a t f s r m v e l o c i t y , and a n g l e o f a t t a c k . The t r a n s f e r f u n c t i o n s t h a t w i l l be used i n t h i s program a r e being d e r i v e d . b. A c o n t r o l system w i t h bending c o o r d i n a t e feedback and a n i d e a l t h r u s t v e c t o r c o n t r o l was e f f e c t i v e i n reducing t h e bending moment. However, w i t h t h e a d d i t i o n o f engine dynamics, t h e system becomes u n s t a b l e f o r the g a i n s v a l u e s r e q u i r e d t o reduce t h e bending moment. The i n c l u s i o n of a second o r d e r f i l t e r d i d n o t e f f e c t i v e l y s t a b i l i z e t h e system w i t h a c t u a t o r dynamics, The r e s u l t s s f t h i s s t u d y have been summarized i n a memorandum, c. An Aero I n t e r n a l Note d e s c r i b i n g t h e a n a l y t i c a l method and t h e d i g i t a l program used i n t h e s e p a r a t i o n c o n t r o l s t a t i s t i c a l a n a l y s i s i s being w r i t t e n , d o A four-week course i n d i g i t a l computer l o g i c was a t t e n d e d . An i n s i g h t i n t o t h e o p e r a t i o n of d i g i t a l c o n t r o l s was gained by t h e a t t e n d e e through s t u d y o f g a t i n g , l o g i c , and a r i t h m e t i c c i r c u i t s . e , The d i g i t a l runs f o r t h e minimum d r i f t c o n s t r a i n e d bending moment problem have been e s s e n t i a l l y completed, and t h e d a t a are b e i n g reduced, P r e l i m i n a r y work on a write-up has been s t a r t e d . f . The problem o f d e s i g n i n g i d e a l c o n t r o l systems f o r nonautonomous p l a n t s w i t h q u a d r a t i c performance c r i t e r i a i s b e i n g continued. The d i g i t a l program f o r t h e IBM 7094 i s being debugged and a t e s t c a s e r u n f o r a checkout. I n p u t d a t a a r e being prepared f o r a system i n c l u d i n g two bending modes and a c t u a t o r dynamics. The p o s s i b i l i t y o f u s i n g Ericksons method o f unsteady g. a i r l o a d s i n t h e r e s p o n s e and s t a b i l i t y c a l c u l a t i o n s was i n v e s t i g a t e d . P r e l i m i n a r y s t u d i e s i n d i c a t e t h a t i t w i l l be p o s s i b l e t o i n c l u d e t h e e f f e c t o f flow s e p a r a t i o n i n response s t u d i e s f o r t h e S a t u r n I B v e h i c l e and good agreement between t h e o r y and experiment w i l l r e s u l t . Preliminary r e s u l t s were covered b r i e f l y i n t h e l a s t q u a r t e r l y review. 5. Contractors a. Lockheed The S a t u r n ~ ~ / @ e n t a iunrs u l a t i o n p a n e l s s e p a r a t i o n s t u d y has been completed. Results indicate t h a t the panels w i l l separate satisfactorily. �Documentation of t h e f i l t e r s and o t h e r m o d i f i c a t i o n s t o t h e B-2 deck has been d r a f t e d , Copies o f t h e d i g i t a l deck which produces t h e n e c e s s a r y f i l t e r i n p u t d a t a t o t h e B-2 deck have been r e c e i v e d . A t a s k assignment h a s been made t o e v a l u a t e t h e e f f e c t o f t h e f i l t e r s on t h e r i g i d body responses so t h a t e s t i m a t i o n s of t h e f i l t e r e f f e c t s can be a p p l i e d t o p r e v i o u s s t u d i e s performed without t h e f i l t e r simulations, Lockheed has developed a n o n l i n e a r f i l t e r t h a t p r o v i d e s i n f i n i t e a t t e n u a t i o n of s i g n a l s whose frequency i s above t h e f i l t e r c u t o f f frequency. The purpose of t h i s s t u d y i s t o (1) improve t h e f i l t e r , ( 2 ) d e f i n e f i l t e r l f m i t a t i o n s , ( 3 ) e v a l u a t e t h e f i l t e r 5 performance, and ( 4 ) i n v e s t i g a t e t h e f i l t e r f o r u s e i n t h e c o n t r o l system o f a S a t u r n type v e h i c l e . Since t h i s s t u d y has j u s t begun, no p r o g r e s s r e p o r t s have been r e c e i v e d . b. - Northrop NAS8-20082, (Schedule Order 4/71, "Bending and S l o s h i n g Analysf s , S a t u r n I B V e h i c l e , SA-203 Booster F l i g h t ' " The o b j e c t i v e o f t h i s study i s t o determine t h e s t a b i l i t y requirements f o r t h e SA-203 v e h i c l e f o r f i r s t s t a g e f l i g h t . The f o l l o w i n g t a s k s were accomplished b e f o r e t h i s r e p o r t i n g p e r i o d : (1) Raw d a t a was processed t o o b t a i n parameters f o r i n p u t t o r o o t l o c u s d i g i t a l program. (2) S e v e r a l computer programs were modified and checked t o handle a d d i t i o n a l bending modes and s l o s h modes. (3) The h i g h e r bending modes and s l o s h modes were i n v e s t i g a t e d f o r coupling e f f e c t s and a p r a c t i c a l s t a b i l i t y a n a l y s i s procedure was devised. (4) S t a b i l i t y and g a i n requirements f o r gyro c o n t r o l a t t h e 20 s e c . , 80 sec., and 100 sec. time p o i n t s were determined and t h e s t a b i l i t y o f t h e upper bending modes was v e r i f i e d . The f o l l o w i n g t a s k s were accomplished d u r i n g t h i s r e p o r t i n g period: (1) Gain s e l e c t i o n and f i l t e r d e s i g n a t t h e 60 sec. time p o i n t was completed and the s t a b i l i t y o f t h e upper bending modes checked. �c. (2) A r o o t l o c u s study t o determine g a i n and f i l t e r requirements a t t h e 60 sec. and 80 sec. time p o i n t s f o r accelerometer c o n t r o l and t h e 140 sec. time p o i n t f o r gyro c o n t r o l i s p r o g r e s s i n g s a t i s f a c t o r i l y . (3) A s t u d y t o determine t h e i n p u t requirements f o r t h e f l e x i b l e body t r a n s i e n t response program was i n i t i a t e d . Lockheed - NAS8-20082, (Schedule Order #2) (1) Task A ( a ) , "Study t o Reduce Bending Moments Via C o n t r o l System Design, " Constant C o e f f i c i e n t Case Converged r u n s have been made f o r a t e n t h degree performance c r i t e r i o n over a 38-second i n t e r v a l . The i n p u t d i s t u r b a n c e The was of t r i a n g u l a r form w i t h t h e 8.5' peak o c c u r r i n g a t 15 seconds. c o n t r o l f o r t h i s r u n a t t a i n e d a m a x i m u m v a l u e o f 52 p e r c e n t o f t h e l i m i t v a l u e and produced a maximum d r i f t r a t e of 1.74 m/s, A comparative r u n u s i n g a t t i t u d e c o n t r o l produced maximm d r i f t r a t e o f 20 m/s, A curve f i t o f t h e c o n t r o l a s a f u n c t i o n o f t h e s t a t e v a r i a b l e s produced a t h i r d - d e g r e e polynomial (no c r o s s product terms were allowed) w i t h a v e r y good f i t except a t t h e upper end p o i n t s . E f f o r t s w i l l be continued t o f i n d a curve f i t t h a t i n c l u d e s t h e c r o s s product terms. A r u n w i l l be made t o o b t a i n t h e system r e s p o n s e t o t h e wind i n p u t u s i n g a d r i f t minimum c o n t r o l . The responqes o b t a i n e d by use of d r i f t minimum and performance c r i t e r i a w i l l be compared f o r performance c h a r a c t e r i s t i c s . (2) Task A(b) , V a r i a b l e C o e f f i c i e n t Case A comparison was made of t h e r e s u l t s o b t a i n e d from t h e Ames deck, which u s e s an i t e r a t i o n procedure t o o b t a i n a s o l u t i o n , and t h e continuous i n t e g r a t i o n s o l u t i o n o f the d i f f e r e n t i a l e q u a t i o n s . This comparison i n d i c a t e d t h a t t h e u s e o f a r e l a t i v e l y s h o r t time s t e p i s r e q u i r e d i n t h e Ames deck f o r c o r r e c t r e s u l t s . F u r t h e r u s e of t h e Ames deck w i t h t h e s h o r t t i m e s t e p s n e c e s s i t a t e s a reprogramming o f t h e t a p e s t o r a g e i n p u t - o u t p u t procedure t o p r o v i d e more e f f i c i e n t use o f machine time. ( T h i s work i s b e i n g performed.) Also, t h e p r e v i o u s l y used r e l a t i v e w e i g h t i n g s i n t h e performance c r i t e r i o n a r e i n e r r o r and must b e r e d e f i n e d , Runs w i l l be made u s i n g t h e r e d e f i n e d we i g h t i n g s and o t h e r t y p i c a l i n p u t winds t o determine t h e degree o f s e n s i t i v i t y o f t h e c o n t r o l law t o t h e i n p u t . �(3) Task B , "Generation o f a Graphical o r A n a l y t i c a l Formulation o f Peak Vehicle ~ e s p o n s e s " The o b j e c t i v e of t h i s study i s t o determine a It was determined g e n e r a l method f o r p r e d i c t i n g peak v e h i c l e responses. t h a t t h e maximum moment u s i n g r i g i d body e q u a t i o n s w i t h c o n s t a n t c o e f f i c i e n t s w i l l occur a t t h e f i r s t break i n t h e wind curve ( t l ) o r a t a l a t e r time ( t 2 ) depending onby on t h e c o n t r o l frequency and v e h i c l e v e l o c i t y , Maximum v a l u e s o f t h e a n g l e of a t t a c k and t h e engine gimbal a n g l e a t t h e s e two times can t h e n be o b t a i n e d from a l i n e a r combination o f t h r e e s t a t e variables. The s t a t e v a r i a b l e s a r e e v a l u a t e d from c o e f f i c i e n t s p l o t t e d v e r s u s c o n t r o l frequency, v e h i c l e v e l o c i t y , and a s p e c i f i e d d r i f t r o o t . Use of t h e s e g r a p h i c a l d a t a p e r m i t s d i r e c t c a l c u l a t i o n of bending moments, This study i s almost complete, and t h e r e s u l t s a r e being documented, (4) Task D, "Nonlinear Accelerometer f o r b a d ~ e l i e f " The o b j e c t i v e o f t h i s t a s k i s t o determine t h e bending moment r e d u c t i o n o b t a i n a b l e through t h e use o f n o n l i n e a r accelerometer feedback. The f o u r t h and s i x t h o r d e r systems w i t h v a r i o u s g a i n combinations and accelerometer l i m i t s e t t ings has been i n v e s t i g a t e d . Bending moment r e d u c t i o n between t h e one-lag ( f o u r t h o r d e r system) and t h e t h r e e - l a g ( s i x t h o r d e r system) systems i s comparable. A f i n a l r e p o r t i s b e i n g prepared. (5) Task E (Schedule Order $ / l o ) , " U t i l i z a t i o n of V e l o c i t y Feedback from P l a t f o r m Mounted Accelerometer f o r Control o f S a t u r n V-LOR1' The g e n e r a l o b j e c t i v e o f t h i s study i s t o determine t h e l i m i t a t i o n s and/or a d d i t i o n a l problems encountered i n r e p l a c i n g t h e body-mounted accelerometer by t h e platform-mounted accelerometer and i n t e g r a t i n g t o o b t a i n v e l o c i t y feedback f o r c o n t r o l of t h e S a t u r n V. A s e t o f r o o t l o c u s p l o t s was made t o determine t h e p o s i t i o n o f t h e r i g i d body r o o t s a s a f u n c t i o n o f t h e g a i n s a o s a l and the v e l o c i t y g a i n el. Rigid body responses were r u n f o r both c o n s t a n t and time-varying c o e f f i c i e n t s u s i n g t h e MSPC d e s i g n wind p r o f i l e . The v e l ~ c i t yfeedback appears t o be o n l y moderately e f f e c t i v e i n r e d u c i n g bending moments. The b e s t l o a d r e d u c t i o n was about 15 p e r c e n t below t h e bending moments o c c u r r i n g w i t h a t t i t u d e and a t t i t u d e r a t e feedback, It a p p e a r s t h a t a d d i t i o n a l compensation w i l l be r e q u i r e d i n t h e v e l o c i t y feedback loop i f a d d i t i o n a l load r e d u c t i o n i s r e q u i r e d . �d. Chrysler I n t h e a r e a of g e n e r a l s t u d i e s f o r S a t u r n I B r i g i d body c o n t r o l , s e p a r a t i o n motion a n a l y s e s were continued f o r double engine f a i l u r e and e a r l y shutdown o f a l l engines w i t h a d e l a y between t h e inboard and outboard engines. Three major m o d i f i c a t i o n s have been i n c o r p o r a t e d i n t o (1) e q u a t i o n s t h e B-2 S i x DOP t r a j e c t o r y r o u t i n e and a r e checked o u t : f o r s i m u l a t i n g c o n t r o l system f i l t e r s , (2) e q u a t i o n s d e s c r i b i n g n o n l i n e a r aerodynamics, and ( 3 ) e q u a t i o n s f o r computing a x i a l l o a d s and " c r i t i c a l " bending moments. Ten p a r c e l s s f e q u a t i o n s , each c o n s t i t u t i n g a subprogram, have now been submitted f o r programming i n t h e development o f t h e new six-degrees-of-freedom t r a j e c t o r y r o u t i n e , The two p a r c e l s submitted i n October a r e "The G r a v i t a t i o n a l Force, t h e Canting o f Thrust Vectors, and t h e Summation o f Forces and Momentsooand "Variable I n t e r v a l o f I n t e g r a t i o n s . " A t e s t problem was submitted f o r programming checkout o f t h e f o u r t h p a r c e l , "Control System Equations, Guidance and Control Table Look-@ and Manipulat i o n * The engine-out c o n t r o l P a b i P i t y s t u d i e s f o r t h e SA-203 v e h i c l e a r e near completion. The d a t a a r e being processed and prepared f o r publication. The study o f l i f t - o f f motion f o r the S a t u r n 1?3/~entaur v e h i c l e was completed. The r e p o r t was w r i t t e n and should be p u b l i s h e d i n t h e f i r s t week o f November. A s t u d y was made t o compare f l e x i b l e body l o a d s w i t h r i g i d body l o a d s f o r t h e AS-201 v e h i c l e . Two r e a l winds were s e l e c t e d These r e s u l t s from January winds measured w i t h FPS-16 radar/Jimsphere. w i l l be documented i n a C h r y s l e r Technical B u l l e t i n t o be p u b l i s h e d i n t h e e a r l y p a r t o f n e x t month. e. - General Dynamics /Convair NAS8-11494, "Design C r i t e r i a f o r Space V e h i c l e s During t h e Launch Phase o f F l i g h t " The d r a f t copy of t h e monograph, $701. 11, P a r t 2, "Nonlinear Systems," has been reviewed. The document, a l o n g w i t h t h e suggested r e v i s i o n s and c o r r e c t i o n s , has been r e t u r n e d t o GD/C t o be r e w r i t t e n and r e s u b m i t t e d i n t h e f i n a l form, i n accordance w i t h c o n t r a c t u a l requirements. The d r a f t monograph, Vol. I, P a r t 1, "Short P e r i o d Dynamics," has been r e c e i v e d , b u t has n o t been reviewed. This monograph c o n t a i n s d a t a on g e n e r a l e q u a t i o n s o f motion, E u l e r a n g l e s , f o r c e s and moments, e q u a t i o n s o f p e r t u r b e d motion, and s i m p l i f i e d t r a n s f e r f u n c t i o n s . �I n a n t i c i p a t i o n of work on t h e monographs 'Nan i n t h e Loop" and "Abort," t h e names o f s e v e r a l people f o r c o n t a c t s were forwarded t o M r . A. L. G r e e n s i t e , t h e p r i n c i p a l i n v e s t i g a t o r f o r t h i s study. f. - Douglas NAS8-20087, "Study of Bending Feedback C o n t r o l System," Via ~ a l m a n ' sP r e d i c t i o n and F i l t e r i n g Methods The s t a t e - s p a c e e q u a t i o n s p r e s e n t e d i n t h e second (August) p r o g r e s s r e p o r t were i n c o r r e c t , p r imar i l y i n the terms i n v o l v i n g s l o s h modes. These e q u a t i o n s were c o r r e c t e d , and the r e v i s e d v e r s i o n s were p r e s e n t e d t o D r . T, R. Blackburn, t h e p r i n c i p a l i n v e s t i g a t o r , i n a subsequent phone c o n v e r s a t i o n ; a c o r r e c t e d copy of t h e e q u a t i o n s was a l s o s e n t t o Douglas. During t h e t h i r d (September) p e r i o d , s i m p l i f i e d models were i n v e s t i g a t e d t o develop i n s i g h t i n t o t h e l a r g e r system behavior. Linear t r a n s f o r m a t ions were made on t h e s t a t e so t h a t the measurable system o u t p u t s and d e r i v a t i v e s o f o u t p u t appear a s s t a t e v a l u e s ; t h e r e f o r e , any unobservable s t a t e v a r i a b l e s a r e r e p l a c e d by measurable v a r i a b l e s . The Kalman f i l t e r e q u a t i o n s can be a p p l i e d t o t h e transformed s t a t e . g. - Honeywell NAS8-20155, "Design o f a Load R e l i e f Control System, I ' Via S t a t i s t i c a l Techniques The purpose o f t h i s s t u d y i s t o develop a c o n t r o l l e r t h a t w i l l maximize t h e p r o b a b i l i t y of m a i n t a i n i n g t h e bending moment w i t h i n a c c e p t a b l e bounds d u r i n g f l i g h t and of a c h i e v i n g a n a c c e p t a b l e terminal s t a t e , A s t a t i s t i c a l wind p r o f i l e of a n e x p o n e n t i a l - c o s i n e - s i n e form has been g e n e r a t e d by f i t t i n g the c o r r e l a t i o n s o b t a i n e d from NASA TN D-561. The computer s o l u t i o n was o b t a i n e d by minimizing t h e e r r o r between t h e computed c o r r e l a t i o n and t h e d a t a c o r r e l a t i o n , weighted by the number o f o b s e r v a t i o n s . P l o t s contained i n t h e August P r o g r e s s Report, Honeywell Report 12013-PR 3 , show t h e g i v e n and t h e computed East-West c o v a r i a n c e s v e r s u s a l t i t u d e . As expected, t h e computed covar iances a r e smoother t h a n t h e a c t u a l covar i a n c e s . Computat i o n a l d i f f i c u l t i e s have been encountered i n g e n e r a t i n g t h e q u a d r a t i c c o e f f i c i e n t s f o r t h e performance index t h a t w i l l be used f o r t h i s study. C. Applied Guidance and F l i g h t Mechanics Branch 1. Saturn I B a , The payload c a p a b i l i t y o f S a t u r n I B v e h i c l e s . , based upon October c u r r e n t w e i g h t s , was t r a n s m i t t e d t o I n d u s t r i a l O p e r a t i o n s , �b. Optimized t r a j e c t o r i e s f o r S a t u r n HB p o l a r o r b i t s have been generated f o r b o t h a t h r e e - s t a g e d i r e c t a s c e n t i n t o a 200 n. m i . c i r c u l a r p o l a r o r b i t and f o r a f l i g h t p r o f i l e w i t h a s u b o r b i t a l s t a r t o f t h e S e r v i c e Module i n t o an 80 n. m i . x 200 n. m i . e l l i p s e c i r c u l a r i z e d a t apogee u s i n g a second burn o f the SM. Documentation i s b e i n g reviewed, Work c o n t i n u e s t o i n c l u d e a 14-day o r b i t and d e - o r b i t t o t h e r e - e n t r y point. c , T r a j e c t o r i e s have been completed f o r a S a t u r n IB v e h i c l e two s t a g e d i r e c t a s c e n t i n t o a 200 n. m i . c i r c u l a r o r b i t f o r Apollo a p p l i c a t i o n s o r b i t a l experiments. One v e h i c l e would be used f o r a f u e l t r a n s f e r experiment, w h i l e t h e o t h e r v e h i c l e would house an o r b i t a l workshop i n t h e empty S-IVB p r o p e l l a n t tanks. d. SA-203 O r b i t a l Venting Tracking Analysis: Work t o determine t h e e f f e c t s o f S-IVB and Instrument Unit d i s c r e t e and continuous v e n t s upon t r a c k i n g s t a t i o n a c q u i s i t i o n time i s i n p r o g r e s s . e. A s t u d y has been i n i t i a t e d t o d e f i n e the m o u n t s f f l i g h t performance r e s e r v e s r e q u i r e d t o g u a r a n t e e S a t u r n 93 payloads when t h e S e r v i c e Module i s used a s a t h i r d s t a g e . A nominal t r a j e c t o r y has been determined based upon a n 80.,n.m, by 107 n. m i . e l l i p s e and t h e f l i g h t performance r e s e r v e s t u d y i s beginning. f. Extensive s t u d i e s were made w i t h t h e extremely c o o p e r a t i v e h e l p of R-AERO-FM and R-P&VE t o demonstrate t h e e f f e c t o f t h e n o n l i n e a r i t y o f t h e LOX probe i n t h e PU system on t h e t h r u s t p r o f i l e and subsequently on t h e t h r u s t a t t i t u d e p r o f i l e . The e x c u r s i o n s on t h e t h r u s t p r o f i l e caused a d e g r a d a t i o n i n t h e n e a r p e r f e c t accuracy and performance o f t h e guidance scheme. The e q u a t i o n s f o r AS-201 have been modified such t h a t t h e guidance scheme does n o t sense t h e s e extreme t h r u s t o s c i l l a t i o n s and such t h a t the a l t i t u d e c o n s t r a i n t i s r e l a x e d approximately 50 seconds before cutoff. S i n c e t h e AS-201 f l i g h t is imminent, t h e m o d i f i c a t i o n o f t h e guidance e q u a t i o n s i s t h e o n l y s o l u t i o n without schedule s l i p p a g e . The r e s u l t s were p r e s e n t e d t o t h e S-HW review (Dr. Rees) October 20, 1965 and a g a i n t o Douglas A i r c r a f t C o r p o r a t i o n October 21, 1965. Vehicle d a t a f o r AS-207 have been f u r n i s h e d t o MIT t o s i m u l a t e i n t h e i t e r a t i v e guidance scheme e q u a t i o n s which have been programmed s u c c e s s f u l l y by MIT f o r backup s t u d i e s , Close communication i s being maintained i n t h e e v e n t t h a t problem a r e a s may a r i s e . The payload c a p a b i l i t y o f S a t u r n 1 ~ I C e n t a u rv e h i c l e s , based upon October c u r r e n t w e i g h t s , was computed and t r a n s m i t t e d t o I n d u s t r i a l Operations. Performance changes due t o i n d i v i d u a l p e r t u r b a t ions of t h e s t a g e a n d v e h i c l e c h a r a c t e r i s t i c s o f t h e S a t u r n ~ ~ / ~ e n t av euhri c l e have been determined. Docunentation i s t o be included i n a NASA Technical �Memorandum covering t h e g e n e r a l performance survey. Release of t h e NASA a u r Technical Memorandum w i l l complete t h e S a t u r n ~ ~ / ~ e n t performance analysis effort, 2. Saturn V a , The payload c a p a b i l i t y of S a t u r n V v e h i c l e s , based upon October c u r r e n t weights, was t r a n s m i t t e d t o I n d u s t r i a l Operations. b, The p r o b a b i l i t y o f t h e S-HVB impacting t h e moon s t u d y i s complete and i s being documented. c. S-IVB p l a n e change c a p a b i l i t y : An e x i s t i n g c a l c u l u s of v a r i a t i o n s computer r o u t i n e w i t h m o d i f i c a t i o n s to c u t o f f on C 3 and i s o l a t e a n i n j e c t i o n p l a n e has been checked o u t , Work w i l l resume when a n a l y s e s o f h i g h e r p r i o r i t y problems have been completed. d. The e f f e c t s upon continuous o p e r a t i o n of t h e S-I'D oxygen-hydrogen b u r n e r (modified S-IV helium h e a t e r ) upon t h e LOR m i s s i o n p a r k i n g o r b i t a r e b e i n g i n v e s t i g a t e d , The burner w i l l be i n s t a l l e d on AS-503 and subsequent p r i m a r i l y f o r r e p r e s s u r i z a t i o n of t h e S-IVB s t a g e . I f t h e r e s u l t s o f SA-203 l i q u i d hydrogen experiment d a t a r e q u i r e continuous t h r u s t t o s e t t l e S-IVB p r o p e l l a n t s , the LOX-LH,burner w i l l be used c o n t i n u o u s l y , The burner has a t h r u s t l e v e l of 15 t o 22 pounds. e. A s t u d y i s being conducted t o d e f i n e t h e payload c a p a b i l i t y of t h e S a t u r n V v e h i c l e f o r a synchronous e q u a t o r i a l o r b i t . The p a r k i n g o r b i t a l t i t u d e i s 100 n. m i . , and o r b i t a l and s u b o r b i t a l s t a r t of t h e S-IVB s t a g e i s being i n v e s t i g a t e d . The p l a n e change i s b e i n g performed a f t e r t h e p a r k i n g o r b i t . A new v e r s i o n of t h e e x i s t i n g three-degrees-of-freedom c a l c u l u s - o f - v a r i a t i o n s t r a j e c t o r y r o u t i n e i s b e i n g checked o u t . Problems o f o b t a i n i n g convergence have delayed t h e g e n e r a t i o n o f a n optimum t r a j e c t o r y . f , A study i s being completed t o d e f i n e the payload c a p a b i l i t y o f t h e S a t u r n V v e h i c l e f o r a 200 n. m i . a l t i t u d e p o l a r o r b i t . The document, R-AERO-DAP-104-65, i s being prepared. g, 5-2 t h r u s t o s c i l l a t i o n t o l e r a n c e s : P a r a m e t r i c s t u d i e s were made t o f i n d t h e a l l o w a b l e t h r u s t o s c i l l a t i o n f o r t h e S a t u r n V m i s s i o n due t o t h e same n o n l i n e a r i t y of t h e LOX probe mentioned under S a t u r n IB. This LOX probe, b u i l t by Minneapolis Honeywell, i s c u r r e n t l y i n t h e S-IVB and S - I 1 p r o p e l l a n t u t i l i z a t i o n s y s tem. P&VE recommended t h a t a t y p i c a l t h r u s t p r o f i l e (approximately 10,000 l b s of t h r u s t peak-to-peak v a r i a t i o n ) which was assumed i n a d i r e c t a s c e n t study be used, It was found t h a t t h e S-I1 b u r n and t h e f i r s t burn o f t h e S-IVB i n t o a 185.2 km c i r c u l a r o r b i t s t i l l maintained s u f f i c i e n t guidance accuracy, a l t h o u g h a l o s s of payload of approximately 700 l b s i n o r b i t was observed. The nondegradation o f accuracy can be e x p l a i n e d i n t h a t a t t h e beginning of t h e f i r s t burn o f �t h e S-IVB t h e p a t h a n g l e i s merely 0.6" a g a i n s t l o c a l h o r i z o n t a l and t h e Therefore, a l t i t u d e i s w i t h i n 3 km of t h e d e s i r e d i n j e c t i o n a l t i t u d e . t h e requirement upon t h e guidance scheme i s mainly t o g a i n t h e n e c e s s a r y v e l o c i t y magnitude f o r i n s e r t i o n . The second S-HVB burn shows a h i g h e r s e n s i t i v i t y t o these t h r u s t o s c i l l a t i o n s . Their e f f e c t on t h e guidance scheme w i t h o u t major m o d i f i c a t i o n w i l l be a n i n j e c t i o n a n g l e e r r o r of approximately 0 . 6 Q , which c a u s e s a 4000 km e r r o r a t t h e r a d i u s of c l o s e s t approach t o t h e moon and i s r e f l e c t e d i n t o a r e q u i r e d midcourse v e l o c i t y c o r r e c t i o n of approximately 40 m/s. These r e s u l t s were a l s o p r e s e n t e d a t t h e S-IW review on October 20, and t o Douglas p e r s o n n e l October 29. It was agreed t h a t t h e LOX probe should have a hardware f i x t o improve i t s l i n e a r i t y . A v i s i t was made t o Minneapolis-Honeywell October 25 w i t h r e p r e s e n t a t i v e s of 10, Center Labs, and Douglas i n a t t e n d a n c e t o d i s c u s s p o t e n t i a l f i x e s . Honeywell agreed t h a t a f i x on t h e LOX probe could be made a v a i l a b l e i n approximately 12 weeks w i t h 2K l b peak-to-peak a s an e x c u r s i o n l i m i t . The c o s t o f such a f i x i s n o t known, h. S-IC Guidance and T r a j e c t o r y Shaping: Extensive s t u d i e s have been made i n t h e i n v e s t i g a t i o n of c l o s e d loop guidance i n t h e S-HC s t a g e , w i t h emphasis on t h e i t e r a t i v e guidance mode's b e i n g i n i t i a t e d a t 1 2 seconds. i. The S-BC t r a j e c t o r y was optimized w i t h load c o n s t r a i n t s , t h e r e s u l t s o f which gave a p r e l i m i n a r y t r a d e - o f f of payload v e r s u s s t r u c t u r a l (bending) loads. A s i g n i f i c a n t payload g a i n can be achieved w i t h moderate s t r u c t u r a l load i n c r e a s e . However, because o f t h e n o n l i n e a r i t y o f t h e t r a d e - o f f f u n c t i o n , t h e s t r u c t u r a l load r e d u c t i o n f o r a f i x e d payload i s small. 3. General a. The o p e r a t i o n a l c o n s t r a i n t s a f f e c t i n g l u n a r launch windows f o r t h e 1967-72 time p e r i o d s t u d y have been f i n i s h e d f o r about two months. The d e l a y i n p u b l i c a t i o n i s due t o t h e l a r g e amount of It i s expected graphs (72) t o be p u t i n a form s u i t a b l e f o r p u b l i c a t i o n . t h a t t h i s work w i l l be documented about t h e l a s t of November. b. Launch windows f o r c i s l u n a r type m i s s i o n s s t u d i e s have been f i n i s h e d . The r e s u l t s should be p u b l i s h e d soon. c. A r e f e r e n c e m i s s i o n p r o f i l e f o r AAP l u n a r mapping m f s s i o n has been e s t a b l i s h e d . This p r o f i l e i s t o be used by North American A v i a t i o n and Gruman A i r c r a f t i n t h e Apollo A p p l i c a t i o n Program payload i n t e g r a t i o n document. d. A computer program i s being developed t o determine closed-form s o l u t i o n f o r r e c t a n g u l a r c o o r d i n a t e s of t h e two-body problem �and t h e i r p a r t i a l d e r i v a t i v e s w i t h r e s p e c t t o t h e i r i n i t i a l v a l u e s , The program w i l l be used t o g e n e r a t e p e r t u r b e d t r a j e c t o r i e s and t o determine AV c o r r e c t i o n s . S t i l l a n o t h e r problem e x i s t s w i t h t h e second burn, While t h e v e h i c l e i s i n parking o r b i t , l i q u i d hydrogen i s b o i l i n g o f f and being v e n t e d , t h e amount depending on which p a r k i n g o r b i t t h e v e h i c l e l e a v e s , As a r e s u l t , an unknown amount of hydrogen w i l l be Thus, t h e PU system w i l l cause a p r e s e n t a t i g n i t i o n of t h e S-IVB. step-down i n m i x t u r e r a t i o t o consume t h i s excess hydrogen u n t i l t h e o r i g i n a l r e f e r e n c e 5.0 i s reached. S t u d i e s a r e now being made t o determine t h e e f f e c t on t h e time of s t e p and how t h e guidance w i l l perform due t o t h i s u n c e r t a i n t y , e. S t u d i e s a r e being made t o determine t h e e f f e c t of uncoupling the yaw a t t i t u d e command w i t h t h e p i t c h a t t i t u d e command, b o t h g e n e r a t e d by t h e i t e r a t i v e guidance mode, Such uncoupling h a s no impact f o r small plane changes; however, t h e e f f e c t on accuracy and performance f o r l a r g e p l a n e changes (up t o p o l a r o r b i t s ) i s being i n v e s t i g a t e d , The uncoupling w i l l s i m p l i f y the e q u a t i o n s and d e c r e a s e computer time. The a c t u a l s i m p l i f i c a t i o n and r e d u c t ion t o a s i g n i f i c a n t degree must be c a r e f u l l y e v a l u a t e d b e f o r e any p o s i t i v e recsmmendation can be made. 4 , , Contractors a. Boeing The S a t u r n V payload c a p a b i l i t y based upon October c u r r e n t weights was computed and t r a n s m i t t e d , The performance e f f e c t s of S-IC and S - I I s t a g e t h r u s t decay and t h e e f f e c t s o f c o n s t a n t p i t c h a t t i t u d e a n g l e from S-IC c e n t e r erg ine c u t o f f t o LES j e t t i s o n were added t o t h e v e h i c l e simulation. The AS-501 a b o r t and a l t e r n a t e m i s s i o n document was r e c e i v e d , has been reviewed, and w i l l be d i s t r i b u t e d i n November, The isomax polynominal i s o l a t i o n and maximization scheme and wind p r o f i l e have been added t o t h e t r a j e c t o r y o p t i m i z a t i o n ( s t e e p e s t a s c e n t ) program, The study has been extended t o i n c l u d e o p t i m i z a t i o n s t a r t times a t v a r i o u s i n t e r v a l s a f t e r l i f t - o f f . Work i s c o n t i n u i n g on d e t e r m i n a t i o n o f the AS-501 reference trajectory. The t r a j e c t o r y i s being updated to i n c l u d e r e v i s e d v e h i c l e aerodynamic c h a r a c t e r i s t i c s . �An AS-503 p r e l i m i n a r y m i s s i o n pro f i l e which does n o t i n c o r p o r a t e long c o a s t p e r i o d s i n the h i g h r a d i a t i o n b e l t s i s being A s t u d y comparing the r a d i a t i o n exposure o f the AS-503 m i s s i o n reviewed. Preparations required t o w i t h t h e nominal LOR m i s s i o n i s i n p r o g r e s s . g e n e r a t e t h e AS-503 p r e l i m i n a r y launch v e h i c l e r e f e r e n c e t r a j e c t o r y a r e under way, P r e p a r a t i o n s a r e being made and deck mod i f i c a t ions a r e being i n c o r p o r a t e d i n t o t h e j o i n t r e f e r e n c e t r a j e c t o r y deck t o g e n e r a t e an AS-504 p r e l i m i n a r y Paunch v e h i c l e r e f e r e n c e t r a j e c t o r y , Boost t o o r b i t phase i s complete. T a r g e t i n g D e f i n i t i o n and S i m p l i f i c a t i o n : Work i s p r o g r e s s i n g on t h e g e n e r a t i o n of t h e d e s i r e d number o f f r e e r e t u r n t r a j e c t o r i e s f o r a l u n a r c y c l e . These d a t a a r e t o be used t o i n v e s t i g a t e p a r k i n g o r b i t t a r g e t i n g parameters t h a t a r e m i s s i o n dependent. The major e f f o r t t o d a t e i s concerned w i t h the i g n i t i o n c r i t e r i a , When t h e d e s i r e d i g n i t i o n c r i t e r i a a r e chosen, the r e s u l t i n g m i s s i o n dependent parameters w i l l be i n v e s t i g a t e d f o r v a r i a t i o n s and methods o f mechanization f o r t h e onboard computer. P r e p a r a t i o n o f AS-504 Spectrum: A l l t r a j e c t o r i e s have There i s remaining work on been completed f o r two azimuths ( 7 z 0 , 85'). t h e 98-degree azimuth. T h i s e f f o r t i s i n r e s p o n s e t o an a c t i o n item from t h e r e f e r e n c e t r a j e c t o r y subpanel, Documentation w i l l be a j o i n t e f f o r t between MSPC and MSC, The guidance e q u a t i o n s f o r t h e AS-501 have been documented approximately two months behind schedule because t h e c o n t r a c t o r changed the guidance e q u a t i o n s provided by R-AERO w i t h o u t good r e a s o n s and w i t h o u t a u t h o r i z a t i o n . F u r t h e r s l i p p a g e i n docurnentat i o n w i l l r e s u l t , u n l e s s t h i s procedure i s changed. U n f o r t u n a t e l y , t o g e t any u s e f u l r e s u l t s under t h e p r e s e n t arrangement p l a c e s an e x c e s s i v e work load on c i v i l s e r v i c e personnel. The S a t u r n I B payload c a p a b i l i t y f o r a l l m i s s i o n s and v e h i c l e s , based upon October c u r r e n t w e i g h t s , was computed and t r a n s m i t t e d . AS-204 launch v e h i c l e r e f e r e n c e t r a j e c t o r y : The f l i g h t c o r r i d o r , d e s i g n t r a j e c t o r i e s , and f l i g h t performance r e s e r v e requirements document i s being reviewed b e f o r e p u b l i c a t i o n . The documentation o f the AS-205 and 206 launch v e h i c l e p r e l i m i n a r y r e f e r e n c e t r a j e c t o r i e s has been completed. Work i s i n p r o g r e s s t o g e n e r a t e a f l i g h t c o r r i d o r , d e s i g n t r a j e c t o r i e s , and f l i g h t performance r e s e r v e requirements f o r AS-206. The AS-206 d e s i g n t r a j e c t o r i e s , £1i g h t c o r r i d o r , e t c . , have been t r a n s m i t t e d . �An SA-203 r e v i s e d launch v e h i c l e r e f e r e n c e t r a j e c t o r y has been g e n e r a t e d , and d o c m e n t a t i o n has been received. Work t o p r e p a r e a f l i g h t c o r r i d o r , d e s i g n t r a j e c t o r i e s , and f l i g h t performance r e s e r v e requirements i s under way, An AS-207 p r e l i m i n a r y launch v e h i c l e r e f e r e n c e t r a j e c t o r y has been determined, Documentat i o n has been r e c e ived. Work t o determine a f l i g h t c o r r i d o r , d e s i g n t r a j e c t o r i e s , f l i g h t performance r e s e r v e s requirements i s under way. Documentation of t h e r e s u l t s of t h e s i n g l e and d u a l S-IB engine-out s t u d i e s f o r t h e SA-203 and AS-204 v e h i c l e s i s i n p r o g r e s s . A p r e l i m i n a r y d r a f t of t h e SA-203 engine-out a n a l y s i s has been r e c e i v e d and i s be ing r e v iewed , Three-degrees-of-freedom computer r o u t ine: c o n t i n u i n g t o i n c o r p o r a t e o u t p u t and p r o c e s s i n g modules. Work i s S a t u r n 6B guidance e q u a t i o n s and guidance scheme ( n o t i n c l u d i n g hardware) e r r o r a n a l y s e s a r e being produced on a n e a r - r o u t i n e bas i s . Since C h r y s l e r has a deck which s i m u l a t e s i n d e t a i l the PU system, a l a r g e amount o f t h e i r d a t a was used i n t h e argument f o r a f i x on t h e LOX probe, Guidance hardware e r r o r a n a l y s e s f o r each S a t u r n I B a r e b e i n g generated, c, Northrop The Monte Carlo technique h a s been a p p l i e d t o a guidance system hardware e r r o r a n a l y s i s f o r S a t u r n V, The r e s u l t s i n terms o f The midcourse v e l o c i t y d i f f e r from t h e "root-sum-square" by 0 - 1 m / s . c l o s e n e s s of t h e s e r e s u l t s l o o b a s i f every i n p u t had a normal d i s t r i b u t i o n , which i s n o t c o r r e c t , I n v e s t i g a t i o n s a r e being made t o determine t h e v a l i d i t y o f t h e s e numbers, A program s i m u l a t i n g braking maneuvers i n t o a l u n a r o r b i t u s i n g t h e i t e r a t i v e guidance mode has been completed. Programming f o r an e a r t h o r b i t a l rendezvous deck has been completed, The hardware e r r o r a n a l y s i s deck i s being modified t o s i m u l a t e two guidance system6 f o r t h e Apollo backup guidance s t u d y , Abort and a l t e r n a t e m i s s i o n s t u d i e s i n t h i s same v e i n a r e being investigated. �E r r o r a n a l y s e s a r e being made on braking i n t o l u n a r o r b i t and on t h e e a r t h o r b i t a l rendezvous study. d, Lockheed The r e s u l t s o f a study u s i n g t h e i t e r a t i v e guidance scheme i n t h e S - I n and t h e s e r v i c e module look g u e s t i s n a b l e w i t h r e s p e c t t o accuracy check e a s e s and w i l l have tis he r u n inhause t o t r y t o a s c e r t a i n t h e problem. Work c o n t i n u e s on improving t h e guidance scheme f o r v a r i o u s miss ion pro f i l e s . However, u n t i l t h e problems Lockheed has w i t h t h e b a s i c i t e r a t i v e guidance scheme a r e r e s o l v e d , t h e r e s u l t s on e x t e n d i n g i t a r e meaningless. e, North American Aviation The f i r s t monograph o f t h e Guidance Design C r i t e r i a Handbook was d e l i v e r e d on schedule and deemed a c c e p t a b l e by R-AERO-DA. However, NASA Headquarters judged i t nonacceptable because a c e r t a i n format o f headings was n o t followed. This r e s t r i c t i o n d i d not appear i n t h e c o n t r a c t , The format of t h e monograph follows the r e q u i r e d format w i t h r e s p e c t t o s u b j e c t m a t t e r b u t s t r i c t adherence t o headings was n o t maintained. A s a r e s u l t , t h e c o n t r a c t must be changed t o r e q u i r e t h i s s t r i c t adherence and t o l e t t h i s monograph s l i p t o November 2 ( f o r m e r l y August 2 7 ) t o conform w i t h Headquarters' p o l i c y . f . Ling-Temco-Voug h t Lunar Launch Window Study: The mid-term review f o r t h i s s t u d y was h e l d on October 23. It i s f e l t t h a t t h e c o n t r a c t o r i s somewhat behind s c h e d u l e , probably because o f personnel problems. They have l o s t two people who were assigned t o t h e study. They should be a b l e t o g e t back on schedule, however, because t h e y have been a b l e t o d e c r e a s e t h e computer r u n time on t h e program used t o do t h e study. g. ~ o r t h r o p / ~ o c k h e e(Miss d ion Support) A l l S a t u r n JB and S a t u r n ~ B / ~ e n t a uperformance r c a p a b i l i t y d a t a f o r p l a n a r launches have been completed. The d e t e r m i n a t i o n of nonplanar performance c a p a b i l i t y i s almost complete. P r e l i m i n a r y documents t i o n i s expected e a r l y i n November. The payload c a p a b i l i t y of t h e S a t u r n ~ B / ~ e n t a uf ro r t h e Voyager m i s s i o n , based upon October c u r r e n t w e i g h t s , was c a l c u l a t e d and transmitted, Rapid performance r o u t i n e deve lopmenta The comparison o f machine t ime v e r s u s accuracy o f v a r i o u s e x i s t i n g performance r o u t i n e and t h e Lockheed developed PRESTO r o u t i n e i s near completion, P r e l i m i n a r y documentation i s expected i n November. �The u s e o f switching f u n c t i o n theory t o determine optimum s t a g i n g p o i n t s i s b e i n g i n v e s t i g a t e d . The s w i t c h i n g f u n c t i o n e q u a t i o n s have been w r i t t e n and have been i n c o r p o r a t e d i n t o a n e x i s t i n g two-dimensional vacuum computer r o u t i n e . Checkout and a n a l y s i s a r e under way. D. Advanced P r o j e c t s Study Branch 1. Apollo A p p l i c a t i o n Program (AAP) The October meeting o f the Mission Planning Task Force was a t t e n d e d a t MSC on October 12 by s e v e r a l r e p r e s e n t a t i v e s o f MSFC. Aero-Astrodynamics p e r s o n n e l were prepared t o g i v e a p r e s e n t a t i o n on f l i g h t s 211, 507, 509, and 511 f o r t h e m i s s i o n s s p e c i f i e d i n schedule ML65-1. Time was n o t a v a i l a b l e f o r t h e planned d i s c u s s i o n s because t h e NAA and GAEC p r e s e n t a t i o n s consumed t h e day. To i n j e c t broader planning i n t o t h e AAP s t u d i e s a t MSC, a group o f MSFC r e p r e s e n t a t i v e s headed by M r . F, L. Williams went t o MSC on October 19 and 20, where the concept of t h e S-IVB workshop was p r e s e n t e d . The meeting was termed a s u c c e s s , and o t h e r exchanges o f i n f o r m a t i o n and i d e a s of t h i s type were encouraged, The l a t e s t AAP t h i n k i n g i n Headquarters was r e c e i v e d i n the form o f s c h e d u l e ML-65-2 from M r . W, B. Taylor. A response t o t h e new f l i g h t and m i s s i o n assignment was r e q u e s t e d i n t h e form o f a p r e s e n t a t i o n t o D r . Mueller on October 28. Aero-Astrodynamics Laboratory s u p p l i e d i n p u t s t o t h e review. A l i m i t e d number of s p e a k e r s were scheduled, p r i m a r i l y from t h e Advanced Systems O f f i c e . 2. S-IVB Workshop The S-IVB workshop i s going through t h e second i t e r a t i o n w i t h R-P&VE, Aero-Astrodynamics and A s t r i o n i c s L a b o r a t o r i e s involved. A r e f e r e n c e t r a j e c t o r y has been c a l c u l a t e d which g i v e s a 14-day l i f e t i m e w i t h 3 0 d i s p e r s i o n s . Purged s t a g e weight and payload have been r e l e a s e d t o R-P&VE. A f t e r t h e moments of i n e r t i a and CG l o c a t i o n a r e r e t u r n e d t o Aero-Astrodynamics Laboratory, a c o n t r o l a n a l y s i s w i l l be performed t o determine i f t h e s p a c e c r a f t ( s e r v i c e module) can s t a b i l i z e t h e workshop o r i f t h e APS on t h e S-IVB w i l l be r e q u i r e d f o r t h e d u r a t i o n o f t h e mission. I f t h e S-IVB must f u r n i s h a t t i t u d e c o n t r o l , t h e n methods w i l l be sought t o implement e i t h e r a "tack-ontt v a r i e t y o r an e x t e n s i o n of t h e c u r r e n t S-IVB APS. Through t h e S-IVB workshop team, an a r t i f i c i a l g r a v i t y experiment i s being i n v e s t i g a t e d . The S-IVB would be used a s a counter-weight w i t h t h e CSM on t h e o t h e r end of c a b l e s o r on a system of t e l e s c o p i n g tubes. MSC has placed a requirement f o r a 100-foot �r a d i u s arm from t h e c e n t e r of g r a v i t y t o t h e working a r e a . The range of The team i s asking A s t r i o n i c s g r a v i t y s i m u l a t i o n i s from 0.1 t o 1.0 g k . and Aero-Astrodynamics Laborator i e s t o develop t h e requirements f o r a n a t t i t u d e c o n t r o l system and a spin-up and d e s p i n system. The team i s a l s o a s k i n g A s t r i o n i c s and Aero-Astrodynamics L a b o r a t o r i e s i f t h e CSM can perform t h e complete t a s k . When t h e proper deployment system has been d e r i v e d by R-P&VE, t h e n t h e c o n t r o l systems w i l l be i n v e s t i g a t e d . 3. Voyager Vehicle Comparison A comparat ive a n a l y s i s of l auatch v e h i c l e a l t e r n a t i v e s f o r t h e Voyager m i s s i o n has been completed. Vehicles compared i n terms o f performance, c o s t , s c h e d u l e s , e t c . , were t h e S a t u r n V, S a t u r n IB/"O" s t a g e , and t h e S a t u r n ~ ~ / G e n t a u r .A p r e s e n t a t i o n was g i v e n t o MSFG management on October 24, 1965, The r e s u l t s a r e being documented and w i l l be p u b l i s h e d i n memorandum form. 4, Saturn V l ~ o y a g e r An in-house e f f o r t has been i n i t i a t e d t o d e f i n e t h e S a t u r n V launch v e h i c l e t h a t w i l l be r e q u i r e d f o r t h e Voyager program. Close c o o r d i n a t i o n w i t h JPL i s a n t i c i p a t e d . G u i d e l i n e s and p l a n s f o r t h e s t u d y w i l l be d i s c u s s e d a t a ' k i c k - o f f " meeting t h e f i r s t week i n November. VII. FLIGHT EVALUATEON AND OPERATIONS STUDIES D PVIS I O N A. Special Projects Office 1. A summary r e p o r t o f the S a t u r n I launch v e h i c l e f l i g h t t e s t has been prepared and i s b e i n g reviewed by t h e FEWG b e f o r e p u b l i c a t i o n . This r e p o r t summarizes i n f o r m a t i o n gained from t h e S a t u r n I program i n performance t a b l e s , graphs, and i l l u s t r a t i o n s . The r e p o r t emphasizes t h e performance o f t h e v e h i c l e systems compared t o a c t u a l c r i t e r i a used i n d e s i g n i n g t h e system, A l l t e n S a t u r n I v e h i c l e s a r e included i n t h e r e p o r t . D i s t r i b u t i o n i s planned b e f o r e January 1, 1966. 2. An FEWG meeting w i t h DAC r e p r e s e n t a t i v e s was h e l d a t MSFC f l i g h t evaluation responsibilities on October 6 , 1965. The S a t u r n IBIS-IVB of DAG were d i s c u s s e d i n d e t a i l . Agreements reached a t t h i s meeting have been inco r p o r a t e d i n t o t h e AS-201 /204 F l i g h t E v a l u a t i o n Plan. 3 . The AS-2011204 F l i g h t E v a l u a t i o n P l a n d r a f t has been reviewed by a l l segments o f t h e FEWG. This p l a n g i v e s d e t a i l e d proeedures t o be followed by b o t h MSFG and c o n t r a c t o r e v a l u a t i o n groups i n c o n t r i b u t i n g t o t h e t o t a l e n g i n e e r i n g e v a l u a t i o n of t h e a f f e c t e d v e h i c l e s . �4. Data requirements f o r AS-201 f l i g h t e v a l u a t i o n have been Requirements have been c o o r d i n a t e d and w i l l submitted by CCSD and DAC. be p u b l i s h e d i n t h e Program Support Requirements Document and t h e Processed Data Requirements Document t o o b t a i n c o r r e c t implementation. 5. A meeting o f t h e FEWG f o r S a t u r n I B f l i g h t e v a l u a t i o n o r i e n t a t i o n and p l a n n i n g h a s been scheduled a t MSFC f o r November 30, 1965. A l l c o n t r a c t o r and MSFC e v a l u a t i o n groups w i l l b e r e p r e s e n t e d . 6. A computer program has been e s t a b l i s h e d f o r r e t r i e v a l of The program has major h i g h l i g h t s of t h e S a t u r n I f l i g h t t e s t program. been implemented and o n l y l a c k s f i n a l i n p u t o f compiled d a t a . The program o u t p u t e n t i t l e d "SAFER," S a t u r n F l i g h t E v a l u a t i o n R e t r i e v a l , w i l l be made a v a i l a b l e t o MSFC segments w i t h i n approximately 2 weeks. Major headings of t h e o u t p u t format a r e a s follows: I I1 I11 IV V VI VII Test O b j e c t i v e Malfunctions and D e v i a t i o n s Launch O p e r a t i o n s Mass C h a r a c t e r i s t i c s Event Times Trajectory Propulsion VIII IX X XI XI1 XIII Guidance Control Structure Environment Electrical I n s t r u m e n t a t ion A complete l i s t i n g of t h e o u t p u t format w i l l be i s s u e d t o o r g a n i z a t i o n s w i t h i n MSFC b e f o r e f u l l u t i l i z a t i o n of t h e program. The program c o n t a i n s h i g h l i g h t s of t h e t e n S a t u r n I f l i g h t s i n t a b u l a r form o n l y ; i n f o r m a t i o n can be r e t r i e v e d from the program f o r any one o r more v e h i c l e s and from any one o r more systems, A s i m i l a r format i s b e i n g e s t a b l i s h e d f o r f u t u r e Saturn I B f l i g h t s . B. F l i g h t E v a l u a t i o n Branch 1. Saturn I (1) CCSD D e t a i l e d F l i g h t E v a l u a t i o n Reports f o r SA-10 The f o l l o w i n g r e p o r t s have been p u b l i s h e d by CCSD under c o n t r a c t t o t h e Branch. (a) R e s u l t s o f t h e Aerodynamic F l i g h t E v a l u a t i o n S a t u r n SA-10 CCSD TN-AE-65-117, d a t e d September 10, 1965 (b) F l i g h t E v a l u a t i o n of S a t u r n SA-10, S-I Stage Base and Aerodynamic Heating Data, CCSD TN-AE 65-111, dated September 1 5 , 1965. �be S-I Stage (1) P r o p u l s i o n Summary A p r o p u l s i o n swnmary r e p o r t has been prepared f o r SA-6 was e l i m i n a t e d t h e S-I s t a g e o f t h e S a t u r n H Block I1 v e h i c l e s . from t h e a n a l y s i s because of e a r l y shutdown. The average p r o p u l s i o n system v a l u e s from p r e d i c t e d , engine a n a l y s i s (P&vE), and f l i g h t s i m u l a t i o n (AERO) a r e t a b u l a t e d below, along with t h e p e r c e n t a g e d e v i a t i o n s of t h e p o s t f l i g h t a n a l y s e s from p r e d i c t e d . c The i f a c t t h a t t h e two independent methods o f e v a l u a t i o n y e i l d e s s e n t i a l l y i t h e same s o l u t i o n g i v e s c o n s i d e r a b l e confidence i n t h e p r o p u l s i o n e v a l u a t i o n procedures. The s t a n d a r d d e v i a t i o n s o f t h e average p r o p u l s i o n system parameters and t h e i r p e r c e n t a g e d e v i a t i o n from the mean a r e given be low : Only one major engine m a l f u n c t i o n o c c u r r e d o u t of 48 e n g i n e s flown on Block 11 v e h i c l e s f o r a 97.9 p e r c e n t s u c c e s s f u l r a t i n g . c. S-IV Stage ( C o r n e l l Short D u r a t i o n S-PV Base P r e s s u r e Tests) Base p r e s s u r e h o t flow t e s t s a t C o r n e l l A e r o n a u t i c a l Laboratory (CAI,) designed t o o b t a i n a complete p i c t u r e o f t h e S-IV b a s e flow f i e l d and g i v e some e x p l a n a t i o n f o r t h e engine performance d e v i a t i o n s observed on p a s t f l i g h t s a r e e s s e n t i a l l y completed. The r e s u l t s without �secondary (helium h e a t e r ) flow a r e a s expected, based on p r e v i o u s 4- and 6-engine d a t a , There i s an i n c r e a s i n g p r e s s u r e g r a d i e n t from t h e engine l i p t o t h e h e a t s h i e l d , r e s u l t i n g i n a p o s i t i v e p r e s s u r e t h r u s t . The r e s u l t s of t h e secondary (helium h e a t e r ) flow must be c o n s o l i d a t e d and finalized. 2. S a t u r n I B and V Data Processor As t h e S a t u r n v e h i c l e s become l a r g e r and more complex and a s t h e m i s s i o n s become more v a r i e d , t h e amount o f d e t a i l e d i n p u t d a t a needed i n a six-degree-of-freedom f l i g h t s i m u l a t i o n program i n c r e a s e s d r a s t i c a l l y . The i n p u t problem i s f u r t h e r complicated by t h e v a r i e t y o f s o u r c e s from which t h i s d a t a must be o b t a i n e d , An a t t e m p t was made on S a t u r n I, Block I1 v e h i c l e s t o c o n s o l i d a t e a l l o f t h e time v a r y i n g d a t a f o r a given s t a g e on one magnetic tape, However, c o n s t a n t changes i n s o u r c e d a t a formats and u n i t s r e q u i r e d s e v e r a l r e d e f i n i t i o n s of t h e t a p e g e n e r a t i o n A d i f f e r e n t procedure w i l l be used on f u t u r e S a t u r n v e h i c l e s . programs. Requirements f o r s p e c i f i c d a t a , d a t a formats and u n i t s w i l l be placed on t h e v a r i o u s s o u r c e s , i . e . , s t a g e c o n t r a c t o r s , e t c . , such t h a t a l l d a t a a r e c o n s i s t e n t w i t h t h e d a t a p r o c e s s o r program. Manual h a n d l i n g of t h e d a t a w i l l be minimized, and manpower requirements, a s w e l l a s c o s t l y The d a t a p r o c e s s o r o r g a n i z e s a l l d a t a e r r o r s , w i l l be g r e a t l y reduced. into three categories: ( 1 ) s t a g e c o n s t a n t s , ( 2 ) d a t a which a r e a f u n c t i o n of Mach number, ( 3 ) d a t a which a r e a f u n c t i o n of time, The d a t a p r o c e s s o r t h e n o u t p u t s a m u l t i p l e f i l e FORTRAN magnetic t a p e c o n t a i n i n g 3 n f i l e s of d a t a , where n i s e q u a l t o t h e number of s t a g e s , A p r e f l i g h t and a p o s t f l i g h t t a p e w i l l be permanently saved f o r each v e h i c l e i n t h e Comp Lab t a p e l i b r a r y and w i l l be a v a i l a b l e f o r g e n e r a l use, This c o n s o l i d a t i o n of d a t a w i l l a l s o e x p e d i t e v e h i c l e block s t u d i e s and summary r e p o r t s . 3. Contracts a. r General ~ y n a m i c s / ~ o n v a iNAS8-20249 This i s a six-month c o n t r a c t t o e v a l u a t e and t r u n c a t e t r a c k i n g system e r r o r models f o r u s e on S a t u r n I B and S a t u r n V p o s t f l i g h t trajectories. During t h e p a s t month, a misunderstanding o f beginning and t e r m i n a t i o n d a t e s was discovered, As a r e s u l t o f t h i s and t h e continued absence o f t h e GD/C p r o j e c t l e a d e r due t o i l l n e s s , t h e work i s approximately It was mutually agreed t h a t a 2-month no-cost 5 weeks behind schedule, e x t e n s i o n was n e c e s s a r y t o complete t h e task. The paper work f o r t h i s e x t e n s i o n h a s been i n i t i a t e d . The r e v i s e d c o n t r a c t t e r m i n a t i o n d a t e i s February 28, 1966. The s t a t u s o f work being performed and t h e d e t a i l e d t a s k d e s c r i p t i o n f o r t h e second h a l f of t h e c o n t r a c t p e r i o d were d i s c u s s e d w i t h GD/C p e r s o n n e l on October 26, 1965. GD/c p l a c e d too much emphasis on computer c o r e s t o r a g e and r e a l time computation r e s t r i c t i o n s . As a r e s u l t , o n l y c o n s t a n t b i a s terms were included i n t h e t r a c k e r e r r o r models. The t a s k f o r t h e second h a l f of t h e c o n t r a c t p e r i o d has been d e f i n e d w i t h �complete emphasis on t o t a l t r a c k e r e r r o r models. These models w i l l be t r u n c a t e d c o n s i d e r i n g o n l y c r o s s - c o r r e l a t i o n and numerical s i g n i f i c a n c e . The i n t e r r e l a t i o n s h i p s between the t r a c k e r e r r o r s and t h e guidance e r r o r s w i l l a l s o be e v a l u a t e d . b. Saturn Stage C o n t r a c t o r (CCSD, New Orleans) CCSD has a l l t h e computer programs needed t o c o n s t r u c t a p o s t f l i g h t t r a j e c t o r y u s i n g a l l e x t e r n a l and onbsard t r a c k i n g d a t a . They w i l l assume prime r e s p o n s i b i l i t y f o r t h e p o s t f l i g h t t r a j e c t o r y from f i r s t motion through S-PVB c u t o f f p l u s 10 seconds beginning w i t h A t r a j e c t o r y r e p o r t has been i s s u e d on SA-9 and SA-8 v e h i c l e AS-205. t o demonstrate the c a p a b i l i t y t o e f f e c t i v e l y use t h e s e programs. The t r a j e c t o r i e s a g r e e extremely w e l l w i t h the t r a j e c t o r i e s e s t a b I i s h e d f o r t h e s e v e h i c l e s by R-AERO-FF. CCSD i s g a i n i n g f u r t h e r experience by p r o c e s s i n g SA-10 t r a c k i n g d a t a on a r e l a x e d schedule, P a r a l l e l t r a j e c t o r y e f f o r t s w i l l begin on v e h i c l e AS-201, and w i l l c o n t i n u e u n t i l CCSD assumes prime t r a j e c t o r y r e s p o n s i b i l i t y . c. S a t u r n V C o n t r a c t o r (The Boeing Company) The A e r o b a l l i s t i c s U n i t s o f TBC was a s s i g n e d t h e t a s k o f developing a t r a c k i n g - d a t a e d i t i n g and f i l t e r i n g computer program i n November 1964. This t a s k has been completed, approximately 5 months behind schedule. This program i s now o p e r a t i o n a l . SA-8 a c t u a l t r a c k i n g d a t a were used a s t h e f i n a l check case. A new t a s k assignment was i s s u e d t o i n c o r p o r a t e a r e f r a c t i o n c o r r e c t i o n r o u t i n e and a measured parameter t o e a r t h - f ixed plumbl i n e t r a n s f o r m a t i o n r o u t i n e i n t o t h e o p e r a t i o n a l e d i t program. T h i s t a s k i s t o be completed by December 1. The range i n s t r u m e n t a t i o n a n a l y s i s of S a t u r n I Block 11 t e s t f l i g h t s i s a l s o being done by TBC. The t r u n c a t e d t r a c k e r e r r o r models f o r ground-based r a d a r and Mark 11 azusa have been used t o a n a l y z e t h e d a t a from v e h i c l e s SA-5, SA-6, SA-7, and SA-9. A report entitled "Error Model S t u d i e s o f t h e E a s t e r n T e s t Range Tracking Systems" .has been i s s u e d which d e s c r i b e s the r e s u l t s o f t h e s e a n a l y s e s . The SA-8 and SA-10 t r a c k i n g d a t a have been p r o c e s s e d , and t h e r e s u l t s a r e being c o n s o l i d a t e d and documented. O, F l i g h t Mechanics Branch 1. S a t u r n PB ( 1 ) The nominal S-IVB p r o p u l s i o n d a t a became a v a i l a b l e on October 8 , 1965, w i t h a s s o c i a t e d complete v e h i c l e mass c h a r a c t e r i s t i c s a v a i l a b l e t h e n e x t day. S p a c e c r a f t mass c h a r a c t e r i s t i c s and S-IB s t a g e p r o p u l s i o n and mass c h a r a c t e r i s t i c s had p r e v i o u s l y become a v a i l a b l e . The �o p e r a t i o n a l t r a j e c t o r y , update 2, was generated during t h e p e r i o d October 9 t o October 20, 1965, w i t h a n o f f i c i a l t r a n s m i t t a l o f t h e S-IVB i n s e r t i o n c o n d i t i o n s t o MSC on F r i d a y , October 22, t h e d e a d l i n e date. The extended overtime was r e q u i r e d f o r t h e g e n e r a t i o n of t h i s t r a j e c t o r y d u r i n g t h i s period, G r e a t e r confidence of o v e r a l l accuracy i s achieved under a l e s s s t r i n g e n t time requirement, A memrandum p r e s e n t i n g the r e v i s e d o p e r a t i o n a l t r a j e c t o r y i s b e i n g expedited w i t h d e t a i l e d p r i n t o u t being made a v a i l a b l e t o v a r i o u s p e r t i n e n t o r g a n i z a t i o n s . A more comprehensive review o f t h e t r a j e c t o r y w i l l be subsequently published i n t h e '"S-201 Launch Vehicle F l i g h t Mechanical Summary. " A comparison of the s t a t e parameters a t S-I'VB c u t o f f between t h e f i r s t and second o p e r a t i o n a l t r a j e c t o r i e s i s a s follsws: Parameter P . Time Altitude Range P a t h Angle P r o p e l l a n t Reserve P i t c h Command Rate 601.4 s e c 260.44 km 1632,4 km 82.070 deg 8000.00 l b s -.56 d e g l s e c 592.6 s e c 260.54 km 1592.4 krn 82.073 deg 6245.00 l b s -.I3 d e g l s e c Work has begun on t h e d i s p e r s i o n a n a l y s i s . should be completed w i t h i n two weeks, This ( 2 ) The range s a f e t y t r a j e c t o r i e s w i l l be r e v i s e d and t r a n s m i t t e d t o KSC and MSC on magnetic t a p e based upon t h e f i n a l o p e r a t i o n a l t r a j e c t o r y . An a n a l y s i s was performed which determined t h e s t e e p e s t t r a j e c t o r y the v e h i c l e could f l y during the e a r l y launch phase ( f i r s t 100 seconds), The u n r e s t r i c t e d aerodynamic d a t a have been t r a n s f e r r e d t o o u r l a t e s t t u r n i n g r a t e deck, and w i l l be used t o compare the t u r n i n g r a t e s o f t h e o p e r a t i o n a l t r a j e c t o r y w i t h t h o s e published i n Data Report #5-65 f o r t h e r e f e r e n c e t r a j e c t o r y . ( 3 ) The c o n t r o l s t u d y f o r AS-201 i s near completion. Wind l i m i t s f o r t h e maximum dynamic p r e s s u r e time o f f l i g h t should be e s t a b l i s h e d n e x t week, M r . Showers, R-P&VE-S, has s t a t e d o r a l l y t h a t t h e s t r u c t u r a l l i m i t s of t h e v e h i c l e a r e t h e l i m i t i n g f a c t o r f o r v e h i c l e s AS-201 and 202. He s t a t e d t h a t f l e x i b l e body motions have been considered i n e s t a b l i s h i n g t h e s e l i m i t s and has promised t o document t h i s i n a memorandum. �(4) C h r y s l e r has agreed t o d e l i v e r t h e l i f t - o f f and s e p a r a t i o n s t u d i e s on AS-201 on o r about November 8. These r e p o r t s w i l l be i n t e g r a t e d i n t o work b e i n g conducted on t h i s f l i g h t i n R-AERO-FMS. F i r s t s t a g e p r o p u l s i o n d a t a became a v a i l a b l e October 18, 1965. The S-IVB p r o p u l s i o n d a t a t a p e became a v a i l a b l e October 26, b u t d i f f i c u l t y by P&VE i n g e n e r a t i n g mass d a t a c a r d s has prevented p r o g r e s s on AS-202 t r a j e c t o r y g e n e r a t i o n . S p a c e c r a f t mass c h a r a c t e r i s t i c s have been a v a i l a b l e s i n c e October 18, 1965, Deadline f o r f i r s t o p e r a t i o n a l t r a j e c t o r y i s November I o r 30 days a f t e r r e c e i p t o f s p a c e c r a f t d a t a , whichever i s l a t e r . The Aerospace Physics S e c t i o n , CCSD, i s p r e p a r i n g t h e r a n g e s a f e t y package (Cape t a p e and d a t a r e p o r t ) f o r t h e r e f e r e n c e The Cape t a p e , which w i l l c o n t a i n 8 range s a f e t y t r a j e c t o r i e s trajectory. a s r e q u i r e d by ETR, w i l l be ready f o r check by t h e f i r s t week i n November. CCSD i s g e n e r a t i n g t h e range s a f e t y package f o r t h e l a t e s t r e f e r e n c e t r a j e c t o r y . The Cape t a p e i s t o be r e a d y by t h e l a s t of October, and t h e d a t a r e p o r t i n November. e. T h r u s t O s c i l l a t i o n S t u d i e s : A l l t h r u s t o s c i l l a t i o n c a s e s from P&VE of amplitude l e s s t h a n 5k peak-to-peak have been run and r e s u l t s t a b u l a t e d , Analysis i s n o t y e t complete. 2. Saturn V The range s a f e t y d a t a r e p o r t which i s almost completed, contains turning r a t e s , e f f e c t s o f d e s t r u c t , drag data, i n j u r y probabili t i e s , and o t h e r p e r t i n e n t range s a f e t y information. The r e p o r t w i l l be d i s t r i b u t e d i n November. Boeing i s making s t u d i e s t o e s t a b l i s h impact and i n j u r y p r o b a b i l i t i e s f o r malfunctioning vehicles. Performance parameters a r e being i n v e s t i g a t e d , and the r e s u l t s w i l l be used i n e s t a b l i s h i n g t h e composite t r a j e c t o r y t o use f o r range s a f e t y l i m i t s . Documentation i s i n progress. �D. O p e r a t i o n s S t u d i e s Branch 1. Saturn I B a. A memorandum p r e s e n t i n g t h e expected dynamic p r e s s u r e and atmospheric d e n s i t y f o r AS-201 and AS-202, assuming a f i r s t q u a r t e r 1966 launch f o r AS-201 and a second q u a r t e r 1966 launch f o r AS-202, has been d i s t r i b u t e d , Both t h e nominal and +30 v a l u e s were given, b. A d r a g c o e f f i c i e n t and an atmospheric d e n s i t y s h i f t c u r v e , which transforms t h e a l t i t u d e dependent atmospheric d e n s i t y i n t o a time and a l t i t u d e dependent atmospheric d e n s i t y , were s u p p l i e d t o R-AERO-DA f o r use w i t h t h e SA-283 P r e l i m i n a r y O r b i t a l Reference T r a j e c t o r y , The s h i f t curve i s t h e r a t i o of a time and a l t i t u d e dependent atmosphere ( d e f i n e d f o r R-AERO-FO from p r e v i o u s o r b i t a l decay h i s t o r y ) t o t h e 1962 US Standard Atmosphere, c. A memorandum p r e s e n t i n g t h e aerodynamic t o r q u e s a s a f u n c t i o n o f a n g l e of a t t a c k f o r SA-203 and SA-204 has been d i s t r i b u t e d . Both t h e nominal and +30 expected t o r q u e s were p r e s e n t e d . The d a t a f o r SA-203 were based on a f i r s t q u a r t e r 1967 launch d a t e , and t h e d a t a f o r SA-204 were based on a l a s t q u a r t e r 1967 launch d a t e . M r . B a l l a n c e , R-AERO-AT, s u p p l i e d t h e n e c e s s a r y aerodynamic d a t a . d. A memorandum has been w r i t t e n concerning t h e communication coverage f o r SA-203 o r b i t a l sequencing. This memorandum g i v e s t h e o r b i t a l coverage f o r SA-203 f o r Radar O r b i t a l Coverage, Telemetry O r b i t a l Coverage, and T e l e v i s i o n and Update O r b i t a l Ground Communications. The i n f o r m a t i o n assumes no v e n t i n g w h i l e i n o r b i t . As soon a s new o r b i t a l d a t a which i n c l u d e v e n t i n g and performance d i s p e r s i o n s a r e g e n e r a t e d , a new memorandum w i l l be w r i t t e n t o i n c l u d e t h e s e p e r t u r b a t i o n s , e. R-AERO-DA was supplied w i t h a d e t a i l e d o r b i t a l t r a j e c t o r y p r i n t on SA-211 f o r t h e 1 3 t h t o 1 6 t h day i n o r b i t . This p r i n t was f u r n i s h e d a t t h e i r request, 2. Saturn V A memorandum d e f i n i n g t h e minimum o p e r a t i o n a l t r a c k i n g c o n s t r a i n t s a s s o c i a t e d w i t h t h e S a t u r n V d i r e c t a s c e n t mode has been distributed. Since continuous coverage of t h e e n t i r e burn of t h e S a t u r n V d i r e c t a s c e n t mode t r a j e c t o r y was not p r a c t i c a l , an a l t e r n a t e mode o f communication coverage was p r e s e n t e d . More work i s being done on t h e p o s t - f l i g h t e v a l u a t i o n requirements f o r t h e d i r e c t a s c e n t mode. 3. General A study i s being conducted t o compare t h e a c c u r a c i e s of v a r i o u s t r a c k i n g systems a s a r e s u l t of a n a c t i o n item i n a memorandum, R-ASTR-IP-433-65, from C o - S e c r e t a r i e s , Instrumentation/~ommunicationP a n e l , �Minutes o f t h e 1 6 t h Meeting o f t h e Instrumenta~ion/~ommunication Panel. This a c t i o n gave MSFC t h e r e s p o n s i b i l i t y t o i n i t i a t e a s t u d y on t h e p o s s i b i l i t y s f r e p l a c i n g t h e Azusa system w i t h a n S-Band system compatible w i t h t h e USB. Data a r e now being prepared u s i n g t h e G-DOP (Geometric D i l a t i o n of P r e c i s i o n ) technique which w i l l p r e s e n t t h e 1, 2, and 3 0 e r r o r s i n determing t h e v e l o c i t y components from t r a c k i n g d a t a of t h e v a r i o u s system t a k e n i n d i v i d u a l l y and j o i n t l y , 1. Heybey, W, H., "Ground Level A c o u s t i c a l Foci i n a Three-Layered Atmosphere,'VASA Tt-3 X-53344, October 7 , 1965, U n c l a s s i f i e d . 2. Weichel, R. J., "SA-10 F l i g h t T e s t Data Report," NASA TM X-53345, October 7 , 1965, U n c l a s s i f i e d . 3. Nunkey, B. W., " S t a t i c Aerodynamic C h a r a c t e r i s t i c s o f the Apollo S a t u r n I B V e h i c l e , " HASA TM X-53348, October 13, $965, U n c l a s s i f i e d . 4. G i l l i s , W. T o , and T. T e l f e r , "AS-204 Launch Vehicle Reference T r a j e c t o r y , " NASA TI4 X-53349, October 1 9 , 1965, U n c l a s s i f i e d , 5. R o b e r t s , W. T., "An Environmental Model f o r Van A l l e n B e l t Protons ," NASA 7% X-53351, October 21, 1965, U n c l a s s i f i e d . 6. P i t c o c k , Robert E., " E f f e c t s of Minuteman Cant Angles on t h e S t a t i c L o n g i t u d i n a l S t a b i l i t y and Axial Force C h a r a c t e r i s t i c s of t h e S a t u r n ~~/Apol%o/~inutem Conf a n Fguration, '' Aero I n t e r n a l Note 24-65, October 25, 1965, U n c l a s s i f i e d . 7. Burns, R. E . , "Note on t h e Conditions o f W e i e r s t r a s s , Legendre, J a c o b i and Clebsch i n V a r i a t i o n a l C a l c u l u s , ' ~ e r oI n t e r n a l Note 24-65, October 25, 1965, U n c l a s s i f i e d . 8. K i e f l i n g , L a r r y , " T h e o r e t i c a l P l i g h t Bending Response of a S a t u r n I Vehicle t o a SinusofdaP," Aero I n t e r n a l Note 25-65, October 28, 1965, Unclassified. 9. Jones, J e s s H. , q ' I n v e s t i g a t i o n o f A c c i d e n t a l Explosion i n Connection w i t h C o n t r a c t NAS8-20223," O f f i c e Mem R-AERO-AU-65-48, d a t e d October 11, 1965, U n c l a s s i f i e d . 10, Schutzenhofer, L., "Preliminary Estimate of the Unsteady Base P r e s s u r e F l u c t u a t i n g Environment f o r t h e S a t u r n W V e h i c l e , " O f f i c e Memo R-AERO-AU-65-44, U n c l a s s i f i e d . �11. Young, James C., "The A e r o e l a s t i c C h a r a c t e r i s t i c s of t h e S a t u r n I B SA-202 Launch Vehicle; Des ign Environment, I' Off i c e Memo R-AERO-AU65-33, October 20, 1965, U n c l a s s i f i e d . 12. Young, James C., "Design Environment A e r o e l a s t i c C h a r a c t e r i s t i c s of t h e S a t u r n V e h i c l e , " Of £ i c e Memo R-AERO-AU-65-54, U n c l a s s i f i e d . 13. P l a t z e r , Maximillian, "Panel F l u t t e r on S a t u r n I B and V Vehicles ,'I O f f i c e Memo R-AERO-AU-65-61, October 29, 1965, U n c l a s s i f i e d . APPROVAL " -- E. D. G e i s s l e r D i r e c t o r , Aero-Astrodynamics Laboratory Aero-Astrodynamics Laboratory DISTRIBUTION R-AERO-DIR Dr. Geissler Mr. Jean R-AERO-P (8) R-AERO-S (8) R-AERO-R M r . B u t l e r (4) M r s High tower . R-AERO-D (16) R-AERO-A (20) R-AERO-G (5) R-AERO-F (20) R-AERO-T M r . Murphree M r . Cummings D r . Heybey Dr. Sperling M r . Dickey M r . Jandebeur M r . Lavender D r . Liu R-DIR D r . McCall PA0 M r , Kurtz MS-H Mrs. J e r r e l l ( 3 ) � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000043 Title A name given to the resource "Aero-Astrodynamics Laboratory Bimonthly Progress Report: November 2, 1965." Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center Date A point or period of time associated with an event in the lifecycle of the resource 1965-11-02 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) NASA space programs Project management Type The nature or genre of the resource Progress reports Text Source A related resource from which the described resource is derived Saturn V Collection Box 15, Folder 31 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050 https://digitalprojects.uah.edu/files/original/20/991/spc_stnv_000044.pdf e55f3eb1bec9e645d9260f5a1e49b9b3 PDF Text Text AERO-ASTRODYNANICS LABORATORY MONTHLY PROGRESS REPORT December 13. 1965 Page ........................... .......................................... ............................. ............... ................................. .......................O.O..... ....................O...... .................................... ............................ ..........................O............. ................................ ............................O............ .......................................... ............................. ...................... ........................... ......................................... ........................................ ........................O....... ......................................... ....................................O..... ......................... ................... ......... ...................O~.................... .......................................... .................... ...................................... ... ........................................ ................................ .............................O...O....... ...................................... I* TECHNICAL AND SCIENTIFIC STAFF' 11 PROJECTS OFFICE III AEROSPACE ENVIROXMENT OFFICE IV. ASTRODYNAMECS AND GUIDANCE THEORY DIVISION A Astrodynamics Branch B Guidance Theory Branch C Optimization Theory Branch V AERODHNA.NH@S DIVISION A Aerodynamic Design Branch 1. Saturn IB 2 Saturn ~ ~ J ~ e n t a u r 3 0 Saturn V 4 - General B Electromechanical Branch C F a c i l i t i e s Branch ..........o.O.De..... D. F l u i d Mechanics Research O f f i c e E Thermal Environment Branch I n Saturn I 2 Saturn I B 3 Saturn P ~ I ~ e n t a u r 4 Saturn V 5 0 General F Unsteady Aerodynamics Branch vl DYNAMICS PLIGHT MECHANICS DIVISION A Applied Guidance and P l i g h t Mechanics Branch 1- S a t u r n I B 2 Saturn V 3 General 4 Advanced Apollo Program ( U P ) 5 Contractors B Control Theory Branch ...................,......9. 1 Saturn I B 2 Saturn ~ B l c e n t a u r 3 0 Saturn V 4* General 5. C o n t r a c t o r s . . . . . . . . .. . . . . . . . . .. . . . . ~ ~ ~ ~ ~ ~ . . . . . . . . . . . . . . . . . . . P P O O O O e ~ . O . . . . . . . . . ~ ~ ~ ~ ~ ~ o ~. e ~ rn ~ ~ ~ o ~ ~ ~ �. .. 4 2 42 .................................. 4 2 .......................................... 42 .......................................... 43 ...............................o....... 44 ......................... 4 6 .......... 48 .. 48 ............................... 49 49 .... 49 ........................................... 5 0 .......................................... 5 0 Dynamics Analysis Branch .........................CI.O 1 Saturn I B 2 Saturn I ~ / ~ e n t a u r Saturn V 3 4 General 5 Contractors D Advanced P r o j e c t s study Branch VII FLIGHT EVALUATION AND OPERATIONS STUDIES DIVISION A Special P r o j e c t s O f f i c e ...........................o.e B F l i g h t Evaluation Branch 1 Saturn H ..........eO~o.eD.e. 2 Saturn I B ...................................ee 3 - Saturn V Contracts 4 C F l i g h t Mechanics Branch 1 Saturn HB ................................e.~e.o... 2 General D Operations Studies Branch l o Saturn I ..................................O.OO. Saturn I B .......................D...O...~P..... 2 3 Saturn V 4 General PUBLICATIONS C . . .. .. .. . . . . . . . . . . . . . . o O . e . . . O . . . . . e . e e . e . O . O . O O . . . . D . . . . . ................................ .............................. ...............................o.qO.OoD... @... 51 51 53 53 53 54 54 55 56 ......................................o.. .. ............................................ . ......00..0.............D......O....l.D............ �AERO-ASTRODYNAMLCS LABORATORY MONTHLY PROGRESS REPORT December 13, 1965 I. TECHNICAL AND SCIENTIFIC STAFF 1. A computer program to determine focal points in a three-layered atmosphere has been written and checked out. Work is in progress on a systematic survey of variations in focal points resulting from variations in atmospheric parameters (Mabry) . 2. A multistage optimization procedure, being programmed for the CDC-3208, is being documented and a report 03 Linear guidance techniques is being prepared (Dickey). TI. PROJECTS OFFICE 1. Incentive Contracts Discussions of the Saturn EB, S-IVB Stage Flight Performance Incentive Plan have resulted in modification of the plan to include direct measurement of subsystem performance during flight. The effort to include this direct measurement was hampered by a lack of defined tolerances for each of the major subsystems. The incentive plan was subsequently modified to include subsystem performance under an award fee concept. The total Flight Performance Plan, which is being reviewed before final typing, includes predicted payload capability, mission performance capability, and telemetry performance under the incentive fee concept and subsystem performance under the award fee concept. 2. Fl ighL Mechanics Sub-Panel Activities a. The Eighth Reference Trajectory Sub-Panel Meeting, held at MSC on November 4, 1965, is documented in R-AERO-P-472-65. b. The Fifteenth Guidance and Performance Sub-panel Meeting, held at MSG on November 5 , 1965, is documented in R-AERO-P-473-65. 111. AEROSPACE ENVIRONMENT OFFICE 1. The final report (Part IV), '"Mathematical Wind Profiles'' has been received from the Lockheed California Company. This report presents detailed procedures for predicting a future vector wind profile from present and past wind profiles, for appl.icat.ionat Cape Kennedy, Florida. It is being reviewed, along with the other three parts, for NASA publication. �2. NASA TM X-53023, " T e r r e s t r i a l EnvFromen.t ( C l i m a t i c ) C r i t e r i a g u i d e l i n e s f a r u s e i n Space Vehicle Deve10prnent,'~ i s being r e v i s e d . This r e p o r t , along w i t h a s i m i l a r r e p o r t on space e n v i r o m e n t c r i t e r i a , i s used by MSPC i n o u r program d e s f g a studies. 3 . Two r e p o r t s a r e being pu5lished a s NASA Technical Memorandums. The f i r s t i s an environmental model of Vsn Alley b e l t p r o t o n s and t h e second i s an a n a l y s i s of l a t e s t d a t a o 2 upper atmospheric winds. During November a paper e n t i t l e d , "Decrease in E l e c t r o n Density i n t h e Ionosphere Following t h e Passage s f S a t u r n I," by N r - Fehker and M r . Roberts of t h e Space E n v i r o m e n t Group, was p r e s e n t e d by M r . P e l k e r a t t h e Second U S Symposium en I ? t e r a e t f o w s o f Space Vehicles with an Ionized Atmosphere. M r . P e l k e r has beem i n v i t e d t o an ARPB/IDA m e e t i ~ gi n P e b r t a r y t o p r e s e n t t h e s u b j e c t s f t h i s paper i n more d e t a i l . 1. Cislunar T r a j e c t o r y S t u d i e s a. Contractor 2 2 a d d i t i o n t o t h e p u b l i c a t i o n named in t h e October p r o g r e s s r e p s r t , a n o t h e r r e p o r t , "Launch Windows f o r C i s l u n a r T r a j e e t o r i e s , " was p u b l i s h e d . This r e p o r t d i s c u s s e s t h e t r a j e c t o r y c o n s t r a i n t s and r e l a t e d e f f e c t s on launch window by g e o m e t r i c a l c o n s i d e r a t i o n s and t h e mathematical model which was used t o g e n e r a t e launch c o n d i t i o n s f o r t h e t r a j e c t e r i e s r e p o r t e d on i n t h e e a r l i e r p u b l i c a t i o n . The s t u d y of c i s l u n a r o r b i t s i n t h e e l l i p t i c a l three-body model c o n t i n u e s a t a slow r a t e on t h e d i g i t a l o u t p u t program. Since c o r r e c t i o n s t o t h e program f o r t h e t r i c e a n a l o g o u t p u t computer a r e n o t y e t p r o v i d i n g a c c u r a t e c a l c u l a t i o n s from t h a t program, use of a n o t h e r a n a l c g o u t p u t computer capable of more a c c u r a t e computation i s being considered. 2. Conic I q t e r p h a n e t a r y Program A s t u d y of Earth-to-Mercury t r a j e c t o r i e s being conducted t o check o u t t h e new c o n i c i n t e r p l a n e t a r y program and f a m i l i a r i z e branch p e r s o n n e l w i t h t h e deck i s n e a r l y complete f o r t h e y e a r 1969. The minimtun C3 f o r t h a t p e r i o d i s about 43 km2/sec2. A C 3 of about 55 km2/sec2 i s needed t o p r o v i d e a Pauxch window of 30 days. The s t u d y w i l h ' b e continued t o i n c l u d e t h e y e a r 9970. No new d i f f i c u l t i e s have been experienced r e c e n t l y w i t h t h e program i n d i c a t i n g t h a t it i s now i n c o r r e c t working o r d e r . �B. Guidance Theory Branch 1. Saturn I- centaur Voyager (Northrop Schedule Order NQ. 7) A f i r s t - d r a f t copy of t h e Northrop r e p o r t on a l a r g e s c a l e u r guidance system e r r o r a n a l y s i s has been S a t u r n ~ ~ / ~ e n t aVoyager reviewed. The a n a l y s i s i s t o parking o r b i t under t h e assumption t h a t IGM c o n t r o l s t h e Centaur s t a g e . The r e p o r t w i l l be c i r e u E a t e d . The s c h e d u l e o r d e r has been modified so t h a t f u t u r e s t u d i e s w i l l c o n s i d e r t h e S a t u r n V v e h i c l e t o be t h e Voyager launch v e h i c l e . 2. LOW Thrust Guidance and Performance (Northrop Schedule Order No. 6 ) Computer progra.ming has been i ~ i t f a t e dt o determine t h e f e a s i b i l i t y s f a guidance technique for t h e s p i r a l escape t r a j e c t o r y suggested ill Aero I n t e r n a l Note .?'! 14-65, Gsnsi.derabhe in-house e f f o r t has been p u t i n t o t h e p r o o f r e a d i n g sf guidance e q u a t i o n s of an HG,M type f o r p o s s i b l e use around t h e sun; a f e w c l e r i c a l m i s t a k e s have been found. Since t h i s work i s t e d i o u s , X o r t h r o p i s making an independent check of t h e guidance e q u a t i o n development b e f o r e a t t e m p t i n g t o program t h e s e e q u a t i o n s f o r a f e a s i b i l i t y s t u d y which w i l l probably be done i n house, Attempts t o compute an optimum low t h r u s t s p i r a l escape t r a j e c t o r y a r e c o n t i n u i n g ; a s y e t , i t has been impossible t o o b t a i n convergence. It i s p o s s i b l e t h a t end c o n d i t i o n s i n a d d i t i o n t o zero energy have t o be s p e c i f i e d t o produce a r e a s o n a b l e t r a j e c t o r y and t h a t t h e s p e c i f i c a t i o n s f escape end c o n d i t i o n s a l o n e i s n o t enough. 3. Implementation a . The t r a n s v e r s a l i t y c o n d i t i o n s t o be used f o r t h e d e t e r m i n a t i o n o f an o p t i m a l t r a j e c t o r y from a c i r c u l a r o r b i t around t h e e a r t h t o escape v e l o c i t y have been added t o t h e ~ e w t o n ' smethod i s o l a t i o n computer program. When t h e p r o g r a m i n g is completely checked o u t , t h e deck can be used t o determine escape t r a j e c t o r i e s f o r g r a d u a l l y d e c r e a s i n g t h r u s t l e v e l s . As t h e t h r u s t l e v e l f o r a p a r t i c u l a r v e h i c l e d e c r e a s e s , t h e t r a j e c t o r y begins t o r e q u i r e more and more s p i r a l s about t h e e a r t h t o r e a c h escape v e l o c i t y . This c h a r a c t e r i s t i c of t h e problem has r e q u i r e d t h e i n v e s t i g a t i o n of more e f f i c i e n t numerical i n t e g r a t i o n p r o c e s s e s , but a t t h e p r e s e n t t i m e , none of t h e methods y i e l d s u f f i c i e n t l y a c c u r a t e r e s u l t s . The i n v e s t i g a t ion i s continuing. b. The m o d i f i c a t i o n s t o t h e ~ e w t o n ' smethod i s o l a t i o n r o u t i n e t o allow t h e i n c l u s i o n of s w i t c h i n g f u n c t i o n s have been programmed and a r e being checked o u t . These m o d i f i c a t i o n s w i l l allow t h e determinat i o n of o p t i m a l s t a g i n g p o i n t s f o r m u l t i s t a g e v e h i c l e s o r t h e d e t e r m i n a t i o n of o p t i m a l o r b i t a l t r a n s f e r t r a j e c t o r i e s w i t h c o a s t i n g phases. �c . Recursion r e l a t i o n s h i p s have been developed f o r t h e computation of optimum low t h r u s t i n t e r p l a n e t a r y t r a j e c t o r i e s . The v a r i a b l e s i n t h e e q u a t i o n s of motion were expanded a s power s e r i e s i n t i m e , and r e c u r s i o n formulas were developed f o r t h e Euler-Lagrange e q u a t i o n . P e r t u r b i n g f o r c e s i n c o r p o r a t e d i n t o t h e e q u a t i o n s of motion were t h e e a r t h , t h e e a r t h ' s o b l a t e n e s s , t h e moon, t h e sun, and t a r g e t P l a n s a r e t o i n c o r p o r a t e t h e e a r t h ' s t h i r d and f o u r t h harmonic planet. terms i n t o t h e e a r t h ' s g r a v i t a t i o n a l f i e l d and extend t h e use of t h e program t o a more g e n e r a l i n t e r p l a n e t a r y deck by addfng more terms f o r t h e r e m a h l n g p l a n e t s . Programming of t h e r e h t i f o n s h i p was i n i t i a t e d . d. A s t u d y has been. i n i t i a t e d t o determine t h e f e a s i b i l i t y of n u m e r i c a l l y i n t e g r a t i n g t h e e q u a t i o n s s f motion and Euler-Lagra3ge equations (using a l a r g e i n t e g r a t i o n s t e p s i z e ) f o r possible use as a low t h r u s t guidance scheme. Newton's method i s beEng used t o determine t h e i n i t i a l m u l t i p l i e r s . A computer program i s being i n c o r p o r a t e d . The f e a s i b i l i t y of t h i s approach w i l l f i r s t be determined f o r more c o ~ v e n t i c l n a lh i g h o r medium t h r u s t v e h i c l e s . a. Aeronutronics Contract No. NAS8-20150 Work i s c o n t i n u i n g t o e v a l u a t e t h e range of v a l i d i t y o f f i r s t and second o r d e r p e r t u r b a t i o n s o l u t i o n s f o r t h e c o n s t a n t low a c c e l e r a t i o n t r a j e c t o r y w i t h t h e t h r u s t i n e i t h e r t h e r a d i a l o r circumf e r e n t i a l d i r e c t i o n . The e v a l u a t i o n i s being made f o r v a r i o u s t h r u s t a c c e l e r a t i o n l e v e l s . Future work w i l l c o n s i d e r t h r u s t a t an a r b i t r a r y constant angle t o t h e radius vector. b. Hayes I n t e r n a t i o n a l - NAS8-20176 A p e r t u r b a t i o n technique r e c e n t l y r e p o r t e d seems u n s a t i s f a c t o r y f o r t h e low t h r u s t t r a j e c t o r y computation problem because of t h e d i f f i c u P t i e s i n o b t a i n i n g i n t e g r a l s of h i g h e r o r d e r terms. Also, i t seems t h a t i n i t i a l v a l u e s of Lagrange m u l t i p l i e r s must c o n t i n u e t o be determined by i t e r a t i o n . During t h i s r e p o r t p e r i o d , a major e f f o r t has been d i r e c t e d t o a p o s s i b l e means of s o l u t i o n f o r t h e low t h r u s t guidance problem. The r e c t a n g u l a r c o o r d i n a t e e q u a t i o n s of motion a r e expanded t o second o r d e r t o r e p r e s e n t t h e g f o r c e w i t h h i g h e r o r d e r terms d e l e t e d ; cakcuPus of v a r i a t i o n s i s a p p l i e d t o t h i s simple s e t . F u r t h e r s t u d i e s w i l l e x p l o r e t h e p o s s i b i l i t y of d e v i s i n g a guidance technique based o n these equations, i f possible. c. I l l i n o i s I n s t i t u t e o f Technology - NAS8-20129 S e v e r a l d i f f e r e n t s t e e r i n g laws a r e being programmed and e v a l u a t e d f o r t h e s p i r a l a s c e n t and c a p t u r e phase. The keynote of t h i s c o n t r a c t i s s i m p l i c i t y and e a s e of implementation. Techniques, such a s �f i t t i n g an approximate t a n g e n t i a l t h r u s t t r a j e c t o r y through p r e s e n t p o s i t i o n and t h e d e s i r e d t e r m i n a l ccmdition t o d e f i n e v e l o c i t y r e q u i r e d followed by Vg s t e e r i n g t o remove t h e v e l o c i t y e r r o r , a r e used. Another approach a t t e m p t s t o c o n t r o l t h e e c c e n t r i c i t y v e c t o r in d i r e c t i o n and magnitude. S i m i l a r approaches a r e being i n v e s t i g a t e d f o r t h e c a p t u r e s p i r a l w i t h s t e e r i n g and t h r u s t c o n t r o l based cn approximate c h a r a c t e r i s t i c s s f t h e nominal t r a j e c t o r y . For t h e s e simple approaches t o work, i t i s n e c e s s a r y t o command t h e a c c e l e r a t i e n v e c t o r . d. U n i v e r s i t y of North C a r o l i n a - NAS8-20106 This c o n t r a c t has t e r m i n a t e d , and t h e f i n a l r e p e r k i s being prepared. e. United A i r c r a f t - ;;AS8-20k19 D f f f i c u l t i e s have been experienced i n t h e implementation o f t h e Newton-Raphson f ~ w i t e2%fferen-cce a l g o r i t h m a s t h e v e h i c l e approaches a p l a n e t . The major diEficuBty i s i n prcvidewg c l o s e r t i m e s t e p s o r mesh p o i n t s a s r e q u i r e d , A procedure t o provide program control o f mesh p o i n t s p a c i n g has been d e v i s e d , and programnigg has begun. A s u b r o u t i n e which computes t h e p o s i t i o c and t h r e e time d e r f v a t i v e s of each p l a n e t has been It i s planned t o hold a meeting a t MSPC w i t h United A i r c r a f t checked o u t . t o d i s c u s s t h e c o n t r a c t and p o s s i b l e s i m p l i f i c a t i o n s which may be made. C. O p t i m i z a t i o n Theory Branch I. A n a l y t i c s t u d i e s on t h e a p p l i c a t i o n of opti.mal c o n t r o l t o load r e l i e f system d e s i g n have been concerned w i t h d e t e r m i n a t i o n of t h e o p t i m a l c o n t r o l f o r d e t e r m i n i s t i c dl.sturbances. Two d i f f e r e n t formulat i o n s of t h e optimum contrsE have r e s u l t e d f o r l i n e a r p l a n t s w i t h q u a d r a t i c performance indexes: a. Control a s a f u n c t i o n s f time, i n v o l v i n g a simple two-point boundary v a l u e problem w5ich i s s o l v a b l e w i t h o u t i t e r a t i o n . b. Control having two components, feedback g a i n s which a r e s o l u t i o n s t o t h e corresponding r e g u l s t o r problem, and an irn~tegralf u n c t i o n of t h e d i s t u r b a n c e and t h e c l o s e d loop p l a n t response. An i n v e s t i g a t i o n i s being made t o determine i f t h e same c o n t r o l can be achieved p u r e l y by feedback of the s t a t e w i t h t h e g a i n s now dependent on t h e d i s t u r b a n c e . A s e a r c h w i l l be made u s i n g t e c h n i q u e s suggested by Whitbeck of Corner1 and t h o s e suggested by Shridhar a s '"pecific Optimal Control" t e c h n i q u e s . Apparent e r r o r s p r e v i o u s l y undetected i n t h e computer progra-m a s s o c i a t e d w i t h t h i s s t u d y a r e being c o r r e c t e d . �2. An a t t e m p t has been made t o apply t h e Kopp-Moyer n e c e s s a r y c o 2 d i t i o n f o r o p t i m a l i t y t o a s i n g u l a r s o l u t i o n of a g e n e r a l i z e d one-stage t r a j e c t o r y o p t i m i z a t i o n problem. D i f f i c u l t y has been encountered i n g e n e r a t i n g t h e r e q u i r e d h i g h e r o r d e r d e r i v a t i v e s , so t h a t r e s u l t s a r e i n c o n c l u s i v e t o d a t e . The t e s t would i n d i c a t e whether o r n o t t h e s i n g u l a r s o l u t i o n , f o r which a n a n a l y t i c a l e x p r e s s i o n has been developed, i s a candidate f o r the optimal t r a j e c t o r y . 3. b h r t h r o p Schedule Order No. 2 Objective: f o r l i n e a r systems. To i n v e s t i g a t e analytFcaE d e s i g n techniques M o d i f i c a t i o n s suggested by MSPC t o ~ o r t h r o p ' sa n a l y t i c a l d e s i g n method t o reduce t h e s e n s i t i v i t y of t h e systems designed t o It a p p e a r s , parameter v a r i a t f s n s were i n c o r p o r a t e d i n t o t k e program. a t Beast i n i t i a l l y , t h a t no improvement has beer. made s i n c e t h e program i s now f r e e t o s p e c i f y urrdesirable ope^^ 130p f F l f e r p o l e s , and i t does so. 4. Systems Technology I n c o r p o r a t e d - NAS8-11419 O b j e c t i v e : A ~ a l y t i c a ls t u d i e s of t h e c o n t r o l of h i g h l y coupled launch v e h i c l e s , i n c l u d i n g t h e development o f s i m p l i f i e d dynamics r e p r e s e n t a t i o n f o r d e s i g n purposes, d e t e r m t n a t i o n of c o n v e n t i o n a l system performance l i m i t a t i o n s , e v a l u a t i o n of advanced c o n t r o l t e c h n i q u e s , and s e n s i t i v i t y analysis. The f i r s t l i s t e d o b j e c t i v e bas been met and t h e r e p o r t on t h i s p o r t i o n of t h e s t u d y i s t o be published s h o r t l y . C o n t r a c t funds have been expended w i t h o u t t h e b a s t t h r e e o b j e c t i v e s being met in f u l l ; t h e c o n t r a c t o r i s s u b m i t t i n g a p r o p o s a l f o r about a f o u r o r f i v e manmonth e x t e n s i o n t o complete t h e c o n t r a c t . O b j e c t i v e : To i n v e s t i g a t e t h e f e a s i b i l i t y and o p e r a t i o n of t h e d i g i t s l a d a p t i v e f i l t e r , a c u r v e - f i t t i n g procedure f o r e l i m i n a t i n g f l e x u r e components from t h e c o n t r o l s i g n a l . The d r a f t of t h e f i n a l r e p o r t was reviewed d u r i n g t h i s period. Four pages of e r r a t a , and s e v e r a l s u g g e s t i o n s on rearrangement o f t h e r e p o r t t o improve i t s r e a d a b i l i t y , were t r a n s m i t t e d t o McDonnell. The c o n t r a c t o r i s c o r r e c t i n g t h e o r i g i n a l r e p o r t , and has agreed t h a t an accompanying summary r e p o r t would h e l p c l a r i f y t h e achievements of t h e contract. �cn u ha, 6, 4 s 5 e U rn 4 a, o 3 $ Z 2a us 2m da, h .,-I �b. A f l i g h t c o n t r o l system has been d ~ s i g n e dt o meet performance s p e c i f i c a t i o n s a t f o u r nominal f l i g h t c o n d i t i o n s , and t h e accepted range of i d e a l bending mode s l o p e s a t r a t e gyro l o c a t i o n s has been d e f i n e d . Work d u r i n g t h i s p e r i o d has r e s u l t e d i n a r e d u c t i o n i n complexity o f t h e system. c . E v a l u a t i o n of t h e m u l t i p l e b l e n d e r c o n f i g u r a t i o n has shown t h a t performance s p e c i f i c a t i o n s can be met f o r t h e zmesmfnal system, b u t complexity and peed f o r a c c u r a t e knowledge of mode s l o p e s make t h i s a n i m p r a c t i c a l c o n f i g u r a t i o n . Recent e f f o r t has been d i r e c t e d toward development o f a new b l e n d e r l o g i c f o r a two-gyro system. V. AERODYXAMSCS DIVISION A. Aerodynamic Design Oranch 1. S a t u r n IB a. Aerodynamic c h a r a c t e r i s t i c s o f t h e Apollo-Saturn I B v e h i c l e s f o r range s a f e t y d e f i n i t i o n a r e b e i ~ gr e f i n e d . Data w i l l be p r e s e n t e d f o r t h e f i r s t and second s t a g e f l i g h t and a b o r t c o n f i g u r a t i o n s f o r t h e power-on and power-off c o n d i t i o n s . These d a t a i n c l u d e t h e 8.0. a n g l e of a t t a c k range of Co t o 180' and Mach number range 0 Also included a r e d r a g d a t a f o r v a r i o u s s t a g e s and components a s a f u n c t i o n of Mach number. b a d d i s t r i b u t i o n s f o r high a n g l e s of a t t a c k a r e g i v e n t o d e f i n e break-up i n c a s e of l o s s of c o n t r o l . These d a t a w i l l be p u b l i s h e d i n a RASA 'B"blX i n t h e near f u t u r e . - b. Small s c a l e model f o r c e t e s t s were conducted i n t h e MSFC 14-inch t u n n e l t o determine some e f f e c t s of t h e S a t u r n I B t a i l b a r r e l ramp on f i n l i f t c h a r a c t e r i s t i c s . T e s t s were conducted w i t h and w i t h o u t t h e t a i l b a r r e l ramp. P r e l i m i n a r y r e s u l t s i n d i c a t e t h a t t h e t r a n s o n i c recompression shock generated by t h e t a i l b a r r e l ramp has an i n s i g n i f i c a n t e f f e c t on f i n l i f t c h a r a c t e r i s t i c s . Vehicle forebody a x i a l f o r c e was reduced. Some i n t e r e s t i n g t r a n s o n i c d a t a t r e n d s were observed d u r i n g t h i s i n v e s t i g a t i o n which have been a t t r i b u t e d t o model shock reflections. These r e s u l t s , which can be a p p l i e d t o t r a n s o n i c t e s t i n g o f f i n n e d S a t u r n shapes i n a l a r g e number of f a c i l i t i e s , w i l l be published. c . Interna.8 p r e s s u r e h i s t o r i e s f o r t h e S a t u r n HB s p a c e c r a f t compartment have been computed f o r v a r i o u s v e n t a r e a s and PU leakages. The d a t a , documented i n R-AERO-AD-65-65, w i l l be used t o r e s i z e t h e v e n t a r e a a n t h e AS-201 and AS-202 v e h i c l e s and t o provide r e v i s e d compartment p r e s s u r e s f o r t h e AS-204 and subsequent v e h i c l e s w i t h t h e HW leakage reduced t o 5.0 in2. �d. Data f o r t h e ApoPlo-Saturn IB have been p u b l i s h e d i n XASA TM X-53348. This r e p o r t i n c l u d e s t o t a l v e h i c l e s t a t i c s t a b i l i t y , axial f o r c e c h a r a c t e r i s t i c s , load and p r e s s u r e d i s t r i b u t i o n s , s e p a r a t i o n aerodynamics, and l i f t - o f f aerodynamics. These d a t a a r e being recommended a s f i n a l d e s i g n c r i t e r i a a d w i l l supersede p r e v i o u s l y used memorandums. S i n c e t h e s e d a t a w i l l r e p r e s e n t p r i m a r i l y a c o m p i l a t i o n and r e f i n e m e n t o f p r e v i o u s c r i t e r i a , t h e y should have no e f f e c t on v e h i c l e hardware design o r f l i g h t schedules. 2, Saturn ~ ~ / ~ e n t a u r The aerodyximic c h a r a c t e r i s t i c s of two proposed S a t u r n IB/ Centaur v e h i c l e s have been documented in R-AERO-AD-65-66, These v e h i c l e s a r e two s t u d y c o n f i g u r a t i o n s used i.9 an a 2 a l y s i s to determine t h e e f f e c t o f i n c r e a s i n g t h e payload volume by v a r i o u s meam. 3. Saturn V a . Hir~ge>!cment Program: Yesti?& EY &he LeRG BO x 10-Soot f a c i l i t y i s scheduled t o begfF on November 2 9 , 1965. ? k d e l h s t a k l a t b o n l . s complete. Static tnozzle p r e s s u r e d a t a w i l l be o b t a i n e d t o d e f i n e hinge moments. TBC i s r e s p o n s i b l e f o r t e s t i n g and a n a l y s i s . b. S a t u r n V/Voyager: The p r e l i m i n a r y aerodynamics f o r four p r e l i m i n a r y c o n f i g u r a t i o n s s f t h e S a t u r n V Voyager a r e being determined. The f o u r c o n f i g u r a t i o n s have c y l i n d e r l e n g t h s of 22.7 f e e t , 4 % f e e t , 5 4 f e e t , and 7 5 f e e t between t h e BU and t h e g e n e r a l i z e d nose shape. A c y l i n d e r l e n g t h o f 54 f e e t i s considered t o be t h e optimum a t t h i s t i m e , and t h e aerodynamics f o r t h i s c o n f i g u r a t i o n have been g i v e n top priority. c . LOR S t a t i c S t a b i l i t y a r d Axial Force C h a r a c t e r i s t i c s : All r e q u e s t e d d a t a have been r e c e i v e d from Geseral ~ y n a m i c s / ~ o n v a i r e x c e p t t h e c u r v e - f i t t e d p l o t s and t h e f i n a l d a t a r e p o r t . The Ecefng Company i s a n a l y z i n g t h a t p a r t of t h e d a t a which i s b e l f e ~ n x lt o be s f s u f f i c i e n t accuracy t o m e r i t an a n a l y s i s . These d a t a ilaeabude t h e rclPEsg moment d a t a , t h e p r e s s u r e r a k e d a t a o n t h e t a i l b a r r e l , t h e upper s t a g e d a t a , and p o s s i b l y t h e a sop,tributiom to s t a t i c s t a b i l i t y end a x i a l f o r c e c h a r a c t e r i s t i c s bekween POo and 2 0 Q . d. I n t e r f e r e n c e - F r e e Fin Program: Plans a r e being f i ~ a l f z e d f o r conducting S a t u r n V fin-shroud i n t e r f e r e v c e - f r e e load programs in e a r l y 1966. The c o n t r a c t i s being n e g o t i a t e d w i t h Cornell f o r model d e s i g n , f a b r i c a t i o n , and t e s t i n g i n t h e C o r n e l l t r a n s o n i c wind t u n n e l . Supersonic d a t a w i l l be o b t a i n e d i n t h e Axes 9 x 7-foot t u n n e l FT A p r i l 1966. Ames has t e n t a t i v e l y accepted t h i s program. �4. General a . O r i f i c e Flow C o e f f i c i e n t Study: A conference concerning t h e f e a s i b i l i t y of conducting t h e o r i f i c e c o e f f i c i e n t experimental program i n t h e Ames 6-foot wind t u n n e l was h e l d a t Ames Research Center on November 3 , 1965. Marshall p r e s e n t e d t h e h i s t o r y and j u s t i f i c a t i o n f o r t h e s t u d y , w h i l e Northrop (who was conducting t h e i n v e s t i g a t i o n f o r MSFC) p r e s e n t e d t h e proposed approach and t e s t program. Ames was q u i t e i n t e r e s t e d i n t h i s s t u d y and has recommended acceptance to t h e i r management. We a r e g u a r a ~ t e e dt e s t time i n J u l y 1966, w i t h t h e p o s s i b i l i t y of t e s t i n g i n A p r i l 1966, provided Ames can n e g o t i a t e t h e f a c i l i t y o p e r a t i n g c o n t r a c t by t h e f i r s t o f t h e y e a r . b . J e t Simulation Study: The Thfokol j e t s i m u l a t i o n c o n t r a c t was completed on November 1 2 , 1965. A r n i ~ i m a lfo8Pow-on p r o p o s a l has b e e ~ ir e c e i s e d . This e f f o r t would b e ccncesmed p r i m a r i l y w i t h s i m u l a t i e c of the F-l e w g i ~ . eturbine e x h s ~ s tand i t s e f f e c t on eagfne plume c h a r a c t e r i s t i c s t o a dfscanee of two e x i t d i a m e t e r s downstream. Some e f f o r t would be a v a i l a b l e t o determine engine s i m u l a n t base c h a r a c t e r i s t i c s f a r i n p i t t o a n a l y t i c a l prolgrams b e i r g developed by t h e Thermal Environme:2f S r a ~ c h . The c o s t of t h i s seven-month p r o j e c t would be approximately $18,080.00. The proposed work would be a l o g i c a l follow-on t o t h e c o n t r a c t j u s t completed. However, b e f o r e a c c e p t i n g t h e p r o p o s a l , a t e c h n i c a l r e p r e s e n t a t i v e from Thiokol w i l l p r e s e n t t o MSPC t h e f i n a l r e s u l t s of t h e complete c o n t r a c t and d i s c u s s w i t h i n t e r e s t e d MSPC p e r s o n n e l t h e d e t a i l s of t h e follow-on e f f o r t . c. Viscous Cross-Plow Study: Models and b a l a n c e s n e c e s s a r y f o r i n i t i a l t e s t s i n t h e MSFC 14-inch t u n n e l a r e a v a i l a b l e . T e s t s a r e t e n t a t i v e l y scheduled t o begin i n January 1966. This phase of t h e v i s c o u s cross-flow i n v e s t i g a t i o n w i l l b e concerned w i t h t h e normal f o r c e c h a r a c t e r i s t i c s of t h e S a t u r n V shapes The of v a r y i n g s c a l e and one o g i v e c y l i n d e r a t a n g l e s of a t t a c k t o 36". e f f e c t s of Reynolds number on h i g h a l p h a v i s c o u s cross-flow L i f t w i l l be s t u d i e d . The ogive c y l i n d e r d a t a w i l l be compared w i t h e x i s t i n g t h e o r i e s a3d experimental d a t a . R e s u l t s of t h e i n i t i a l MSFC i n v e s t i g a t i o n w i l l p r o v i d e g u i d e l i n e s f o r t h e follow-on l a r g e s c a l e LTV t e s t t o be conducted i n t h e second q u a r t e r o f 1966. d. Compartment Venting Methods Documentation: A p r e s e n t a t i o n of t h e method used by t h e Aerodynamic Design Branch t o compute compartment i n - f l i g h t p r e s s u r e h i s t o r i e s has been completed. This p r e s e n t a t i o n i s t o be r e l e a s e d i n an Aers-Astrsdynamics I n t e r n a l Note. Documentation of t h e g e n e r a l procedure w i l l p r e s e n t e l a b o r a t e d e s c r i p t i o n s of procedure now necessary in a l l design reports. �e. T r i s s n i c Gone-Cylinder-Frustum-Cylinder Study: T e s t i n g has been completed on a s e r i e s of cone-cylinder-frustum-cylinder bodies f o r a p a r a m e t r i c s t u d y t o d e f i n e l o c a l normal f o r c e c o e f f i c i e n t d i s t r i b u t i o n s over frustum and c y l i n d e r s . The c o n t r a c t o r , MSG, bas completed about 90 p e r c e n t o f t h e d a t a r e d u c t i o n , which i n v o l v e s i n p u t t i n g p r e s s u r e d a t a i n t o a computer program and i n t e g r a t i n g t o determine t h e l o c a l normal d i s t r i b u t i o n s . B. ElectromechanicaE Branch 1. Force Measurement Development Dynamic damping f o r c e measurements w i t h t h e p r o t o t y p e f o r c e d o s c i l l a t i o n model have been r u n i n t h e 14-inch kna2eL. Performance has been q u i t e s a t i s f a c t o r y w i t h approximately 260 d a t a p s i g t s taken. Improvements needed are b e t t e r t o r q u e spreng clanping far t h e h i g h e r f r e q l ~ e n c i e sand more a l p h a o f f s e t capabfL%t:s for t h e Iswer frequency spring. Future models w i l l improve t k s e arid a l l o w f ~ vra r i a b l e c e n t e r of rotation. The second p r o t o t y p e o f t h e i.mpuhse f o r c e b a l a n c e f o r t h e hypersonic shock t u n n e l , which has been through p r e l i m i n a r y c a l i b r a t i o n , appears t o meet a l l r e q u i r e m e n t s , This b a l a n c e , i.199, w i l l be used w i t h t h e f i r s t S a t u r n c o n f i g u r a t i o n i n t h e t u n n e l i n mid-January. A second b a l a n c e , i.203 (1.00 inch d i a m e t e r ) , now being f a b r i c a t e d i s scheduled f o r t h e same model of reduced s i z e i n mid-February, A micro-force balance d e s i g n f o r t h e low d e n s i t y chamber flow n o z z l e i s proceeding f o r measuring t h e s e l o a d s i n micro-pounds, 2. P r e s s u r e Measurement Development A r e s o n a n t tube c a l i b r a t o r f o r a c o u s t i c p r e s s u r e s i s b e i n g developed. D r i v e r s have been chosen and coupling horns f o r t h e t u b e have been made. Frequencies a t a nominal 170db have been g e n e r a t e d t o approximately 40K Hertz. Acoustic p r e s s u r e t r a n s d u c e r s s u i t a b l e For t h e v a r i e t y o f a p p l i c a t i . o n s in modeling a r e being developed. Adequake t r a n s d u c i n g t e c h n i q u e s a r e a v a i l a b l e f o r t h e sound p r e s s u r e Levels of . 0 0 l t o 2.00 p s i (110 t o 175db) nominally and f r e q u e n c i e s t o l O O K Hertz. Problems being r e s o l v e d a r e t h o s e of s i z e ; i . e . , s p a c i n g i s l i m i t e d i n small models and allows wave-length c a n c e l l a t i o n s a t h i g h e r v e l o c i t i e s . T a i l o r e d o r i f i c i n g o f .030 inches t o .200-inch diameter diaphragm t r a n s d u c e r s i s allowing up t o 23K Hertz f l a t response. With helium f i l l , 45K H e r t z f l a t response i s expected. Manufacturing t e c h n i q u e s and u n r e l i a b i l i t y i n use have a s y e t made d i r e c t m i n i a t u r e (.015 t o .030 i n c h d i a m e t e r ) p i e z o e l e c t r i c c r y s t a l a p p l i c a t i o n s i m p r a c t i c a l , A s m a l l s c a l e t e s t i s underway a t Lewis Research Center u s i n g t h e t a i l o r e d o r i f i c e technique. �3. Thermal Measurement Development The t h i n - f i l m b e a t gages used i n t h e v a r i o u s f a c i l i t i e s a r e being improved i n q u a l i t y , i n t h e number o f t y p e s b e i a g made, and i n developing s o u r c e s of supply. High temperature u n i t s o p e r a t i n g t o 1 0 0 0 ° ~a r e i n t h e p r o t o t y p e s t a g e . 4. Dynamic Data A c q u i s i t i s x ~acd Air-aBysis The 50K Hertz d a t a r e c o r d e r w i t h c r o s s - c o r r e l a t i o n c a p a b i l i t i e s has been shipped t o HITRH f o r t e s t s u p p o r t . The system w i l l be r e t u r n e d w i t h t h e cross-beam c o r r e l a t i o n t o t h e Thermal and Acoustic Simulation F a c i l i t y (TASF) h e r e e a r l y n e x t y e a r . Two analog c o r r e l a t o r s , which a r e t o be d e l i v e r e d soon, w i l l be used f a r d a t a in all frequency ranges; t h e lower f r e q u e n c i e s (below 50K H e r t z ) w i l l be analyzed a t I g c r e a s e d t a p e speeds. 5. Flow V i s u a l i z a t i o n Development The s i x - i n c h s c h l i e r e n and c l o s e d c i r c u i t TV systems f o r t h e Thermal and Acoustic Simulation F a c i l i t y a r e t o be d e l i v e r e d about December 15. The h i g h a c o u s t i c n o i s e w i l l i n most c a s e s p r o h i b i t d i r e c t viewing o f t h e s c h l i e r e n , A l i g h t - w e i g h t overhead c a r r i a g e i s being provided f o r t h e systems f o r l o n g i t u d i n a l and v e r t i c a l adjustment and t r a n s f e r between v a r i o u s flow d u c t s . Work i s c o n t i n u i n g on v a r i o u s flow v i s u a l i z a t i o n schemes i n t h e low d e n s i t y chamber. R a d i a t i o n s t i m u l a t i o n and gas r a d i a t i o n The d e n s i t i e s normally e l c o u n t e r e d a r e w e l l t e c h n i q u e s a r e being used. below t h e r a n g e o f t h e more conventional system. 6. Gas Analysis Developments A r e s i d u a l gas a n a l y z e r , which has been designed f o r t h e low d e n s i t y chamber, w i l l analyze the gas composition i n t h e chamber a t v a r i o u s in-flow c o n d i t i o n s and be a d a p t a b l e t o a wide range of chamber p r e s s u r e s , A t e c h n i q u e has been developed f o r t h e helium a n a l y z e r t o be used t o measure t h e helium-air r a t i o i n t h e j e t mixing zone i n t h e Thermal and Acoustic Simulation F a c i l i t y . 7. Remo t e Sensing Developments Remote s e n s i n g of d e n s i t y and v e l o c i t y has been pursued w i t h electron-beam s c a t t e r i n - g and s t i m u l a t e d u l t r a v i o l e t r a d i a t i o n . Laser equipment has been purchased f o r s i m i l a r experiments under various division contracts. �8. Model and Component Development An a u t o m a t i c boundary l a y e r t r a v e r s e probe f o r t h e 14-inch t u n n e l has been completed and checked o u t . This probe, which i s s t i n g mounted, has a t r a v e l of 1.500 i n c h e s a c c u r a t e t o .OOP inch. Automatic programmed p o s i t i o n i s provided. The m i n i a t u r e probe can c a r r y t o t a l t e m p e r a t u r e , p r e s s u r e o r o t h e r types of s e n s o r s . The d e s i g n of a n image model f o r c e system f o r t h e 14-inch t u n n e l i s about 50 p e r c e n t complete. This w i l l be a s i d e - w a l l supported model s i m i l a r t o a s p l i t t e r p l a t e concept except t h a t a f i x e d image of t h e h a l f model w i l l r e p l a c e t h e s p l i t t e r p l a t e , A s p l i t t e r p l a t e w i l l be provided a l s o f o r comparative t e s t i n g . The f o r c e d o s c i l l a t i o n model system used w i t h t h e p r o t o t y p e dynamic damping model w i l l be improved f o r more f l e x i b l e appl%eati.on t o t h i s type of work and t o d r i v e a p r e s s u r e - i n s t r u m e n t e d model, This work, which i s w e l l underway, w i l l i n c l u d e i m p r o ~ e r n e ~ tisn d i c a t e d by t h e p r e s e n t t e s t o f t h e damping model. A s i d e - w a l l f o r c e system f o r t h e 14-inch t u n n e l has been It i s equipped w i t h au.tomatic programmed completed and checked o u t . a l p h a c o n t r o l . F i r s t use i s t o be f o r a s e r i e s of f i n load s t u d i e s . Two b a l a n c e ranges a r e provided w i t h 5 f o r c e o r moment components measured. A VKF base flow t e s t c e l l , which w i l l i n c l u d e i n a d d i t i o n t o t h e c e l l a v e h i c l e base model and 3 - d i r e c t i o n instrument probe m a n i p u l a t o r , i s being designed and w i l l be adapted t o t h e AEDC f a c i l i t y f o r v a r i o u s flow s t u d i e s . Design i s e s s e n t i a l l y complete on a l l TASP mechanical components i n c l u d i n g t h e c o l d d u c t and c o n t r o l s , models, i n s t r u m e n t a t i o n c a r t s and survey probes. The f a b r i c a t i o n and checkout w i l l c o n t i n u e through December and January. Other major model systems underway a r e a s follows: SBPP Nozzle P a r a m e t r i c Models ( E a r l y Design) P i l o t Hi-Re Force Model and M o d i f i c a t i o n s ( E a r l y Design) Sat. V Open I n t e r s t a g e Force Model ( F i n a l Design) S a t . V I n t e r s t a g e Ring Force Model ( F i n a l Design) Sat. IB 14-Inch Tank Loads Model ( F i n a l F a b r i c a t i o n ) Low Density Chamber Flow Nozzle ( F i n a l F a b r i c a t i o n ) Wavy-Wall Models ( F i n a l F a b r i c a t i o n ) Lunar Erosion Model ( D e l i v e r e d ) Sat. V Forebody Force Model f o r HST (Design) Q-Ball P r e s s u r e Models f o r 14-Inch Tunnel ( D e l i v e r e d ) �9. F a b r i c a t i o n Resources The work of t h e AEC shops a t Oak Ridge was r e c e n t l y i n s p e c t e d . The low d e n s i t y flow n o z z l e s f d i f f i c u l t - t o - m a c h i n e s o f t copper was i n e x c e l l e n t c o n d i t i o n . Thin-film gage f a b r i c a t i o n was beginning t o flow v e r y r e l i a b l y and looked good. P o s s i b i l i t i e s of e l e c t r i c a l f a b r i c a t i o n from c o a r s e l a y o u t s appeared t o be v e r y promising. Astro Space i s f a b r i c a t i n g f o r c e b a l a n c e s , t h i n f i l m gages, and o t h e r s p e c i a l items v e r y s a t i s f a c t o r i l y . Hayes I n t e r n a t i o n a l w i l l f a b r i c a t e most of t h e TASP Cold Flow Duct and o t h e r components. Micro G r a f t w i l l f a b r i c a t e t h e Lqage Model Force System f o r t h e 14-inch t u n n e l as s c o n a s t h e d e s i g c i s complete. The wavy-wall f a b r i c a t i o n s on 5 w a l l s , d o l e by Republic A v i a t i o n , were unacceptable. These a r e beiqg r e - d o x in-house. These f a b r i e a t i c n s e r v i c e s a r e provided through ME Lab and a r e q u i t e s a t i s f a c t o r y w i t h t h e e x c e p t i o n of t h e Republic work, A t e c h n i c i a n has been provided a t JPL f o r 4 weeks t o check Two t e c h n i c i a n s a r e a t Lewis Research o u t a n LN-cooled f o r c e model. Center on base a c o u s t i c and n o z z l e hinge moment t e s t . C. F a c i l i t i e s Branch 1. Hmpulse Base Plow F a c i l i t y The High Reynolds Number F a c i l i t y model s t u d i e s were continued. A l l planned t e s t s have been conducted u s i n g t h e upstream diaphragm p o s i t i o n . However, problems w i t h t h e downstream diaphragm p o s i t i o n have been encountered w i t h both t h e t r a n s o n i c and s u p e r s o n i c t e s t s e c t i o n s . C s n p l e t i o n of t h e downstream diaphragm t e s t s i s pending a d d i t i o n a l hardware f a b r ic a t ion. During f a b r i c a t i o n of t h i s hardware, t h e HBFF i s scheduled f o r about one month w i t h a n R-AERO-AT p r o j e c t , "Heat T r a n s f e r and P r e s s u r e Measurements i n a Cavity Formed by a Rocket Engine Exhaust." This s t u d y i s t o compare experimental d a t a t o t h e o r e t i c a l p r e d i c t i o n a s a p p l i e d t o an eroded c a v i t y of t h e l u n a r s u r f a c e . Hardware f o r t h i s t e s t was r e c e i v e d November 24, and i n s t a l l a t i o n began November 29, 1965. 2. Hypersonic Shock Tunnel S e v e r a l r u g s were made i n t h e hypersonic shock t u n n e l t o check r e p e a t a b i l i t y u s i n g b e t t e r q u a l i t y h e a t t r a n s f e r i n s t r u m e n t a t i o n . Although r e s u l t s a r e much improved over previous d a t a , some problems i n th.is a r e a remain unsolved. �After several visits by the manufacturer's representatives, the helium purification system seems to be mechanically satisfactory; however, from all available means of analyzing the gas, it does not seem to be removing air from the helium-air mixture. The manufacturer and Purchasing Office have been informed of all our testing results; however, their course of action to remedy the problem has not yet been determined. Several modifications are underway to automate the operation of the 20mm shock tube facility to be ready to start testing as requirements of R-AERO-AE are made available. Hardware requirements for a static stability test on the Saturn IB-V upper stages have been given t o R-MRB-LIE. It la expected that initial testing will begin about January 15, 1966. 3. 14 X 14-Inch T r f s o n i c Wind Tw~neB The following tests were conducted during November: a. An investigation to determine static stability a2d axial force data sf several S a t u r n IB configurations using scalloped and cylindrical tanks in the S-IB stage. Total runs: 7 2 . b. An investigation of the pressure distribution on a cone-frustum-cylinder general payload configuratiin at high angles of attack. Total runs: 49. c. An investigation to obtain rigid body upper stage aerodynamic damping characteristics of the Apolls-Saturn HB and V vehicles. This test is in progress. 4. 7 X 7-Inch Bisonic Wind Tunnel An investigation to evaluate a technique for measuring gas velocities through the use of a small gas laser was resumed. This test is being performed by Brown Engineering for R-AERB-AT. The i,nvestigationof separated flow and oscillating shocks associated with a series of semi-circular section cylinder-flare-cylinder models was completed. This work is being done by Wyle Laboratories for R-AERO-AU. 5. Thermal and Acoustic Simulation Pacili.ty The contractor has delayed delivery sf the helium heater until mid-February. Although this slippage will delay the system checkout test program, it appears that the heater will be available when the support equipment and model hardware becomes available. �6. Hot Plow T e s t F a c i l i t y The a i r c o n t r o l v a l v e i s being modified t o i n c r e a s e t h e r e s p o n s e time. A l i m i t e d weight flow c a l i b r a t i o n was conducted on t h e h e a t e r s o t h a t maximum weight flow through t h e h e a t e r could be e s t a b l i s h e d f o r c e r t a i n d e s i g n c r i t e r i a f o r R-AERO-AT. D. F l u i d Mechanics Research O f f i c e 1. AL~aPysisof Density M e a s u r h g Systems: Analytical. s t u d i e s s f impact p r e s s u r e p r s b e s by Monte Carlo techniques a g r e e completely w i t h t h e p u b l i s h e d r e s u l t s o f t h e U n i v e r s i t y of Toronto I n s t i t u t e of Aerospace S t u d i e s . To v e r i f y t h e s e s t u d i e s f o r complex probe d e s i g n s which cannot be analyzed by t h e U n i v e r s i t y s f Toronto t e c h n i q u e s , f l i g h t c o n f i g u r a t i o n s and fXigbt d a t a f o r d e 2 s i t y probes used on Explorer 17 and from GSFC thermosphere F l i g h t s a r e being examined. 2. O r b i t a l Aerodynamic C o e f f i c i e n t s , AAP: P r e l i m i n a r y d a t a f o r o r b i t a l d r a g c o e f f i c i e n t s , c e n t e r o f p r e s s u r e l o c a t i o n , and o t h e r o r b i t a l aerodynamic c h a r a c t e r i s t i c s f o r s e v e r a l concepts of a 1/10 g r a v i t y space s t a t i o n conf i g u r a t i o n have been d e r i v e d . V a r i a b l e parameters included v a r i o u s r o t a t i o n a l modes w i t h r e s p e c t t o t h e v e l o c i t y v e c t o r . These c a l c u l a t i o n s , which were made by Eockheed under NASA C o n t r a c t NAS8-21230, p o i n t e d o u t s e v e r a l problems i n t h e Lockheed programs. P r i n c i p a l l y , t h e s e problems a r e concerned w i t h t h e c o u p l i n g of many m u l t i s i z e d elements. Since f u r t h e r s t u d i e s w i l l most l i k e l y r e q u i r e more d a t a of thi.s t y p e , t h e computer programs a r e being expanded t o handle t h e more complicated b o d i e s . 3 . D i g i t a l a n a l y s i s of random processes: R-AERO-AM and R-COMP-RRV a r e developing j o i n t l y a computer program f o r a d i g i t a l a o a l y s i s of random v a r i a b l e s which ( a ) can use an u n l i m i t e d amount o f d a t a , ( b ) g i v e s s t a t i s t i c a l and numerical e r r o r s of a l l d e s i r e d p r o p e r t i e s and ( c ) reduces computation and p r i n t - o u t times. The u s u a l s t o r a g e l i m i t a t i o n s a r e avoided by a c c e p t i n g t h e d a t a i n small p i e c e s . Comparing t h e e s t i m a t e s from i n d i v i d u a l p i e c e s a l l o w s a c a l c u l a t i o n of s t a t i s t i c a l and numerical e r r o r s . Cost s a v i n g , r e d u c t i o n of sample l e n g t h , number of l a g s , number of f r e q u e n c i e s , e t c . , a r e t h e n i n t r o d u c e d by checking t h e accumulated e r r o r s a g a i n s t p r e s c r i b e d e r r o r The program i s w r i t t e n i n two p a r t s . The f i r s t covers c r o s s margins. c o r r e l a t i o n e s t i m a t e s , and t h e f i r s t t e s t examples have been r u n s u c c e s s f u l l y . The second covers cross-power s p e c t r a and w i l l be submitted f o r coding. A p p l i c a t i o n s t o o p t i c a l measurement o f t u r b u l e n t f P u c t u a t i o n s and a c o u s t i c model t e s t s a r e being prepared. �4. Cold Flow Duct: A f a c i l i t y which p r o v i d e s high p r e s s u r e a i r (up t o 3500 p s i ) e x h a u s t i n g through n o z z l e s i n t o t h e atmosphere i s r e q u i r e d by R-AERO-AM t o s t u d y t u r b u l e n c e and n o i s e g e n e r a t i o n i n s u p e r s o n i c e x h a u s t s . The r e c e n t l y developed o p t i c a l crossed-beam S i n g l e and c o r r e l a t o r w i l l be used f o r t h e t u r b u l e n c e measurements. c l u s t e r e d n o z z l e s w i l l be a t t a c h e d t o a s e t t l i n g chamber i n which s c r e e n s can be i n s t a l l e d a t d i f f e r e n t l o c a t i o n s t o v a r y t u r b u l e n c e i n t h e exhaust. Aerodynamic d e s i g n i s complete, a d . mechanical d e s i g n and f a b r i c a t i o n ( t h r o u g h R-AERB-AE) a r e underway. The a p p a r a t u s wb%B be c a l l e d t h e Cold Flow Duct and w i l l be housed in t h e TASP (Thermal and Acoustic Simulation F a c i l i t y ) . F i r s t t e s t s using the o p t i c a l c o r r e l a t o r a r e scheduled f o r March 1966. 5. Contracts a. NAS8-11208: The IIT Researc? I ~ s t l t u t ef s r m d l a t e d t h e t h e o r y behind t h e "correlatieln gunsswhich c r a s s c o r r e l a t e s t h e s i g n a l s from two microphones t h a t a r e adgusted t o t h e same l i n e of s i g h t , producing a "narrow f i e l d of viewrYd e t e c t o r . T h i s d e t e c t o r f i n d s t h e s t r e n g t h , s c a l e s , and f r e q u e n c i e s o f dorninazt soead s o u r c e s i.2 engine exhausts . b. NAS8-l'h.299 and In-House: The paper "Hkeat T r a n s f e r Below R e a t t a c h i n g Turbulent Flows1-as been accepted f o r p r e s e n t a t i o n a t t h e AIAA Aerothermochemistry o f Turbulent Flows Conference, Temperature, h e a t t r a n s f e r and h o t w i r e measurements i n t h e r e c i r c u l a t i o n a r e a behind a b l u n t t r a i l i n g edge show ( a ) a dominant h e a t flow r e s i s t a n c e i n t h e newly d i s c o v e r e d base boundary l a y e r , (b) t u r b u l e n c e l e v e l s i n e x c e s s of 100 p e r c e n t , and ( c ) l a r g e t u r b u l e n c e e f f e c t s on base h e a t i n g r a t e s . E. Thermal E n v i r o m e n t Branch 1. Saturn I The S a t u r n I thermal d a t a e v a l u a t i o n summary r e p o r t has been completed and i s being published a s CCSD TM-AE-65-115. A s t u d y was i n i t i a t e d t o determine t h e e f f e c t s of r a d i a t i o n on t h e gas temperature d a t a r e c e i v e d from thermocouples flown on t h e S a t u r n v e h i c l e s . R e s u l t s s f t h i s s t u d y should be o b t a i n e d i n December. P r e p a r a t i o n s a r e being made t o e v a l u a t e t h e AS-201 f l i g h t data. 2. S a t u r n EB The maximum aerodynamic h e a t i n g environment f o r t h e AS-207 v e h i c l e w i t h 205K t h r u s t engines has been determined. The magnitude of t h e thermal environment w i l l be approximately 3 p e r c e n t g r e a t e r t h a n �t h a t p r e v i o u s l y determined f o r t h e S a t u r n HB v e h i c l e (200K e n g i n e s ) . Because of t h e s i m i l a r i t y between t h e 205K d e s i g n c r i t e r i a e n v i r o m e n t w i t h t h e 200R d e s i g n c r i t e r i a environment, s e p a r a t e environmental d e s i g n c r i t e r i a f o r t h e 205K s e r i e s of v e h i c l e s w i l l n o t be e s t a b l i s h e d . A r e p o r t p r e s e n t i n g t h e above r e s u l t s w i l l be published in December. A S a t u r n HB thermal environment handbook i s being developed. Design c r i t e r i a f o r t h e b a s i c s t a g e s , f i n s and protuberances have been compiled and e d i t e d . F r c v i s i o n has been made f o r i n c o r p o r a t i n g f u t u r e o r replacement d a t a a s s o c i a t e d w i t h performance and/or t r a j e c t o r y changes. This manual w i l l be published i n mid-December. The i n c r e a s e d aerodynamic h e a t i n g e n v i r o m e n t induced by t h e S a t u r n PB p r o t u b e r a n c e s f o r v a r i o u s d e s i g n t r a j e e t o r i e s i s being determined. These d a t a w i l l be included f z ~t h e S a t u r n 13 t h e r m a l e w f r s m e n t a l handbook. The a e r o d y ~ a m i ch e a t i n g r e l a t l o - s h i p s a r e being formulated i n t o a g e n e r a l aerodynamic h e a t i n g s u b r o u t i n e , which w i l l be used i n an advanced thermal a r a l y z e r computer prcgram. The s e p a r a t e d f l o w s t u d y i s being csntimued. Empirical r e l a t i o n s h i p s which a c c u r a t e l y p r e d i c t t h e s e p a r a t i o n geometry have been o b t a i n e d . An empirhea1 r e l a t i o n s h i p which can d e f i n e t h e l i m i t s of t h e geometry of s e p a r a t i o n i s being formulated. S e v e r a l methods have been determined and a r e being examined. P u b l i c a t i o n of t h e s e r e s u l t s w i l l be delayed t o allow a more i n t e n s i v e i n v e s t i g a t i o n of t h e s e methods. Thermal e n v i r o ~ m e n t sf o r t h e S-LIE s t a g e B-P engine components d u r i n g f l i g h t have been p u b l i s h e d a s CCSD 7%-AE-65-288. These environments were based on SA-9 and SA-10 f l i g h t d a t a r e c e i v e d from c a l o r i m e t e r s mounted on t h e engine b e l l and a s p i r a t o r s u r f a c e s . The R-B engine s u p p o r t band temperatures d u r i n g f l i g h t have been determined u s i n g t h e s e environments. In a d d i t i o n , a p p r o p r i a t e m o d i f i c a t i o n s were made t o p r e d i c t t h e S-IB-3 s t a t i c t e s t engine s u p p o r t band temperatures. Good c o r r e l a t i o n w i t h t h e t e s t d a t a was o b t a i n e d . The c a l o r i m e t e r c a l i b r a t i o n d a t a from Wyle Laboratory a r e being analyzed. However, i t i s b e l i e v e d t h a t t h e d i g i t a l t a p e t h a t was s e n t t o GCSD from t h e Wyle t e s t c o n t a i n s i n a c c u r a t e l y t r a n s c r i b e d d a t a . Wyle L a b o r a t o r i e s i s checking t h i s p o s s i b i l i t y . A f i n a l report of the w i l l n o t be pubhished u n t i l a l l d a t a have been p r o p e r l y processed. results The s t e a d y s t a t e temperature d i s t r i b u t i o n a c r o s s t h e c y l i n d r i c a l d i s c of a membrane c a l o r i m e t e r i s being determined. Varied temperature d i s t r i b u t i o n s have been o b t a i n e d by imposing s e v e r a l c o n v e c t i v e and r a d i a t i v e environments. It i s e s s e n t i a l t o f u t u r e S a t u r n EB f l i g h t e v a l u a t i o n t h a t t h e membrane c a l o r i m e t e r t e m p e r a t w e d i s t r i b u t i o n be a c c u r a t e l y determii-ed, s i n c e a l l scheduled S a t u r n I& c a l o r i m e t e r i n s t a l l a t i o n s a r e o f t h e membrane t y p e . �T e s t i n g o f t h e S a t u r n S-IB and S - I , Block 11, c o n f i g u r a t i o n s w a s t e r m i n a t e d a t AEDC o n November 4 , 1965. The e f f e c t s o f o n e i n o p e r a t i v e e n g i n e and t h e removal o f t h e e n g i n e s h r o u d s were i n v e s t i g a t e d . A complete examination o f t h e d a t a obtained during t h e t r a n s o n i c t e s t i n g phase has i n d i c a t e d t h a t t h e e x p e c t e d Mach number and a l t i t u d e were n o t o b t a i n e d . T r a n s i e n t e x t e r n a l f l o w d u r i n g combustion f n v a l l d a t e d t h e d a t a . The Mach 1.6 d a t a a r e b e i n g a n a l y z e d and w i l l be documented. A r e p o r t descri.b%ng t h e t h i n - f i l m r e s i s t a n c e thermometer c a l i b r a t i o n t e s t s r u n a t My-CaP E n g i n e e r i n g w i l l be p u b l i s h e d a s CCSD TN-AE-65-113. Model b u i l d u p and model rnodificati.on s f the S-I, Block I1 i n t e r m e d i a t e d u r a t i o n t e s t model a t AEDC have heen completed. T e s t i n g i s now underway a t Mach 1.63 2nd 3 8 , 0 8 0 f e e t a l t i t u d e . T e s t s of t h e Satelrn S-9B short duratis_7i model En t h e Cornell. A e r o n a u t i c a l L a b o r a t o r y (GAL) 8 x 8 t r a n s o n i c wi3d t e n n e l a r e being prepared. A rough e s t i m a t e of c e l l occupancy f a r t h i s t e s t i s A p r i l 1, 1965. An e m p i r i c a l c a n v e c t i v e b a s e h e a t i n g model and a g e n e r a l i z e d computer program t o c a l c u l a t e approximate S a t u r n S-IB s t a g e c o n v e c t i v e b a s e h e a t i n g v a l u e s a r e b e i n g developed. The computer, b e i n g c o n s t r u c t e d i n segments, i s o n s c h e d u l e . The p o r t i o n o f t h i s program which w i l l c a l c u l a t e r e v e r s e d mass f l o w i s complete w i t h p r e l i m i n a r y r e s u l t s b e i n g c a l c u l a t e d . A t e c h n i c a l b u l l e t i n w i l l be p u b l i s h e d . A t e c h n i c a l n o t e concerned w i t h t h e M-1 e n g i n e r a d i a t i o n f o r n o n e q u i l f b r i u m c o n d i t i o n s h a s been d r a f t e d , The computer program p r e v i o u s l y b u i l t t o c a l c u l a t e a b s o r p t i o n and s c a t t e r i n g c r o s s s e c t i o n s o f carbon p a r t i c l e s i s being a l t e r e d t o allow p a r t i c l e d i s t r i b u t i o n i n p u t and t h e c a l c u l a t i o n s f plume r a d i a n c e , T h i s program w i l l t h e n be used t o p r o v i d e i n p u t t o t h e s i n g l e plume r a d i a t i o n program b e i n g d e v e l o p e d f o r t h e S-IB s t a g e . T u r b u l e n t j e t mixing w i t h a f t e r b u r n i n g i s b e i n g s t u d i e d . R e s u l t s have been o b t a i n e d f o r t h e main j e t under chemical e q u i l i b r i u m c h e m i s t r y c o n d i t i o n s u s i n g t h e c o n s t a n t p r e s s u r e a n a l y s i s . Also b e i n g i n v e s t i g a t e d i s t u r b i n e e x h a u s t g a s mixing w i t h a i r under chemical equilibrium conditions. I n i t i a l r e s u l t s i n d i c a t e t h e presence s f a l a r g e amount o f s o l i d c a r b o n . A r e p o r t d e s c r i b i n g t h e method and r e s u l t s w i l l be i s s u e d . 3. Saturn ~ ~ / ~ e n . t a u r An a n a l y s i s t o d e t e r m i n e t h e maximum a e r o d y r a n i e h e a t i n g environment a s s o c i a t e d w i t h t h e S a t u r n 1 ~ / 6 e n t a u s C i s l u n a r Pegasus t r a j e c t o r y was t e r m i n a t e d , P r e l i m i c a r y r e s u l t s p r e v i o u s l y o b t a i n e d show �t h a t t h e t o t a l aerodynamic h e a t i n g would be l e s s t h a n h a l f t h a t f o r t h e AS-201 and AS-202 v e h i c l e s . These r e s u k t s w i l l be p u b l i s h e d . 4. Saturn V Rocketdyne p l a n s t o f i r e twa S - I 1 u l l a g e motors a t t h e i r McGregor, Texas, f a c i l i t y about t h e end of December o r e a r l y January. The Thermal Envirorment Eranch p l a n s ts f z s t a l l a T e f l o 2 probe and a copper probe i n t h e exhaust f a r t h e f i r s t and second f i r i n g s , r e s p e c t i v e l y . These p r o b e s , which a r e being f a b r i c a t e d by Beat Technology Laboratory, w i l l be composed o f a 3-inch diameter c y l i n d e r w i t h a h e m i s p h e r i c a l nose cap and w i l l be m o ~ n t e dabout 2% f e e t from t h e e x i t p l a n e ( j u s t i n f r o n t of t h e f i r s t Mach d i s c ) . $be Teflon probe w i l l have about 4 o r 5 a b l a t i o n s e n s o r s t o be used in a? a t t e m p t t o measure a b l a t i o n arid p a r t i c l e e r o s i o n caused by t h e exhaust %rnpiv.gemenk. The coFper probe w i l l have thermocouples i n s t a l l e d a t v s ~ i o u sd e p t h s %2 a copper slug i n e-- a t t e m p t t o measure t h e h e a t t r a ~ s f e rr a t e a t the s u r f a c e ~ P Zt h e temperature d i s t r i b u t i o n through t h e s l u g . These experimental dara will be cempared w i t h t h e c r e t i c a f h e a t i n g and n b l a t f o i , calc.~llakfel?s. a. A b l a t i o n Program TFe e q u s t i o n s a r e being formulated and a d i g i t a l computer program w r i t t e n f o r a n a l y z i n g a b l a t i n g thermal p r o t e c t i o n systems. The program i s being developed i n two phases: Phase H w i l l produce a "working t o o l " program t o handle m a t e r i a l s f o r which experimental d a t a a r e a v a i l a b l e ; Phase Il w i l l produce a program having d i v e r s i f i e d theoretical capabilfties . The "-\n70rking tooB'"roogram bas now reached p r o d u c t i o n s t a t u s , and t h e u s e r ' s Manual has been p ~ b l i s h e da s LYSC/BREC document A712574. An o r a l p r e s e n t a t i o n on t h e program's c a p a b i l i t i e s a ~ n d i t s u s e w i l l b e g i v e n t~ t h e customer ir t h e near f u t u r e . Work has resumed on Phase 11 o f t h e p r c g r a m , which w i l l i n v o l v e a n a l y s e s of decomposi.tfon-in-depth and s o l i d p a r t i c l e impingement from r o c k e t e x h a u s t s . The "worki.ng t o o l ? program i s being used t o a n a l y z e s e v e r a l a b l a t i v e models t o be t e s t e d i n t h e S-I'\% u l l a g e motor e x h a u s t s f o r R-AERB-AT . be Thermo Methods Ar?..alysis - Plat-Plate Modification Two b a s i c v e r s i o n s of t h e f l a t - p l a t e t r a n s f o r m a t i o n s have been d e r i v e d and t e s t e d . The mast r e c e n t has been found t o g i v e erroneous r e s u l t s i n a r e g i o n o f n e g a t i v e v e l o c i t y d i s t r i b u t i o n . The �former v e r s i o n , now being t e s t e d msr'e e x t e n s i v e l y , has been found t o be q u i t e s i m i l a r t o an approximate s o l u t i o n f o r t h e momentum t h i c k n e s s o b t a i n e d by E. Truckewbrodt from a l e n g t h y d e r i v a t i o n based on t h e energy i n t e g r a l e q u a t i o n . Such c l o s e s i m i l a r i t y w i t h t h e more l e n g t h y s o l u t i o n l e n d s s u p p o r t t o t h e t r a n s f o r m s o k u t i o n based on a simple f l a t - p l a t e momentum t h i c k n e s s s o l u t i o n . c. Equilibrium Weal ~ a s J ~ o r r n aShock 1 Program f o r S t a g n a t i o n P o i n t Heating The g o a l of t h i s s t u d y i s to develop t h e c a p a b i l i t y t o c a l c u l a t e s t a g n a t i o n p o i n t h e a t i n g r a t e s for a b l u n t body in an e q u i l i b rium r e a l gas flow f i e l d . Tvo numerical techniques were used t o s o l v e t h e laminar bot~ndary l a y e r e q u a t i o ~ s8 3 t h e s t s g - ? a t i o n r e g t o n s s f t h e b l u n t body. D i g i t a l colnputer programs were w r i t t e r for b o t h t e c h n i q u e s , and t h e r e s u l t i n g programs were cheeked c u t . Tbe behavior o f t h e numerical s o k u t i o n s was e x p l o r e d , and t h e r e s d l t s for h e a t i n g r a t e s i n air compared f a v o r a b l y w i t h r e s u l t s publistsed by o t h p r s . A computer program, generated by Lewis Research C e n t e r , f o r p r e d i c t i o n o f t r a n s p o r t p r o p e r t i e s of multicompsnent r e a c t i n g g a s e s was checked o u t , and a number of t e s t c a s e s were examined. do Thermal Analysis of t h e LPV P a r t i a l l y Enclosed Engine Cluster The c l u s t e r e d LFV engines a r e being s t u d i e d . The r a d i a n t h e a t i n t e r c h a n g e c o n f i g u r a t i o n f a c t o r s have been c a l c u l a t e d f o r b o t h t h e c l u s t e r e d and i n - l i n e engine c o n f i g u r a t i o n s . Meat t r a n s f e r c o e f f i c i e n t s a t t h e n o z z l e w a l l s a r e being c a l c u l a t e d based on engine t e s t d a t a . Using t h e above d a t a , t h e s t e a d y s t a t e temperature d i s t r i b u t i o n s f t h e c l u s t e r e d engine c o o f i g u r a t i o n w i l l be determined. e, Base P r e s s u r e and Envfromewt The p o r t i o n s f t h i s s t u d y now u?der i ~ v e s t i g a t i o n i n v o l v e s t h e t u r b u l e n t boundary l a y e r growth on aszzke w a l l s w i t h mass i n j e c t i o n c o o l i n g . The accumulation of d a t a on t h e P-1 engine has reached a p o i n t where r e a s o n a b l y a c c u r a t e i n p u t s t o t h e boundary l a y e r program can be made. These d a t a have been documented i n a Technical Data Release. A m u l t i p l e - s l o t mass i n j e c t i o n scheme has been i n c o r p o r a t e d i n t o t h e boundary l a y e r program; one r u n has been made f o r boundary l a y e r growth over t h e e n t i r e P-B nozzle. In a d d i t i o n , s u f f i c i e n t approximate �d a t a were c o l l e c t e d t o allow one r u n f o r t h e boundary l a y e r growth on t h e H-l n o z z l e . As y e t , almost no experimental i n f o m a t i o n a n t h i s engine has been l o c a t e d . Additional runs with the multiple-slot i n j e c t i o n boundary l a y e r program w i l l be made t o v e r i f y i t s o p e r a t i o n . A s u b r o u t i n e t o i n c o r p o r a t e a d i s t r i b u t e d mass i n j e c t i o n technique i n s t e a d of t h e m u l t i p l e - s l o t scheme i s being w r i t t e n . Technical Data Releases s i m i l a r t o t h e one r e f e r e n c e d abave w i l l be prepared f o r t h e H - l and 5 - 2 engines. f . Stage S e p a r a t i o n Thermodyn,amics A method of p r e d i c t e d r o c k e t nozzle exhaust impingement p r e s s u r e s on a f l a t p l a t e has been developed by making use of a methodo f - c h a r a c t e r i s t i c s computer program which i n v a l v e s ~ c k e z t ' st u r b u l e n t f l a t p l a t e t h e o r y and a computer program wbEch s o l v e s t h e turbulenmt momentum i n t e g r a l e q u a t i o n by av. i t e r a t i v e method a ~ dt h e n p r e d i c t s h e a t r a t e s u s i n g ~ e ~ n o l d a' s~ a l o g y . Other s m a l l t a s k s i n p r o g r e s s or r e c e n t l y completed a r e as fallows: (1) P r e d i c t i o n s f plume p r o p e r t i e s and shape a t 350,000 f e e t a l t i t u d e f o r shock impingement l o c a t i o n a s s o c i a t e d w i t h experimental t e s t s a t Cornell. ( 2 ) Obtaining s e v e r a l s e t s of thermo-chemical d a t a a s s o c i a t e d w i t h v a r i o u s p r o p e l l a n t s used i.n c u r r e n t probl.ems. ( 3 ) P r e d i c t i o n s f r e a l gas flow f i e l d and b e a t t r a n s f e r a s s o c i a t e d w i t h h o t flow r o c k e t exhaust impingeme~t t e s t s scheduled a t NASA-MSPC (Centeur r e t r o - m o t o r s ) . g. h?cnzzke a,nd J o t Wake Study The program has once a g a i n been debugged and i s o p e r a t i n g properly. The SC-4028 p l o t program i s now o p e r a t i o n a l . The e f f e c t i v e n e s s of t h i s t y p e s f o u t p u t i s r e s t r i c t e d by t h e graph s i z e which i s i n h e r e n t t o t h e SC-4020 p l o t t e r . Ameans of photo-enlarging t h e pl.ots has been attempted and was s u c c e s s f u l . A new photographic enlargement p l a t e i s on o r d e r and should a r r i v e in a few weeks. It w i l l t h e n be p o s s i b l e t o e n l a r g e t o ll" x l8". h. M u l t i p l o Shock A new t e c h r i q u e , being proposed t o i n v e s t i g a t e t h e r e g u l a r shock r e f l e c t i o n from t h e a x i s of symmetry, i s used t o determine t h e r e f l e c t e d shock wave near t h e a x i s of symmetry by making use of t h e e x i s t i n g s i n g l e shock flow f i e l d program t o g e t h e r w i t h an o v e r a l l �c o n s e r v a t i o n balance technique. P r e l i m i n a r y r e s u l t s from t h e f i r s t few t r i a l s seem t o i n d i c a t e t h a t such a technique might l e a d us t o completely s o l v e t h e axisymmetric flow f i e l d under r e g u l a r r e f l e c t i o n c o n d i t i o n s . i. Thermodynamics and Chemistry of Reacting Gases E r r o r s were found i n t h e f i n i t e r a t e chemistry program o b t a i n e d from ~ A % ~ / ~ e w iAs replacement . espy o f t h e chemistry program was shipped from N A S A I L ~ Wt o~ ~#RE@ ow Xovember 1 2 , 1965. This program w i l l be made o p e r a t i o n a l on HSPC" computers when i t i s r e c e i v e d . The N A S A / L ~thermodynamic ~ ~ ~ d a t a (i.nclsadFng i o n i c s p e c i e s ) have been r e c e i v e d . A f t e r t h e s e d a t a have been v e r i f i e d , t h e y thermochemieal equilibri.um program. w i l l be used by t h e ~ A s ~ / ~ e w is 9. Cold Plow-Sase Flow Test Planning for t h e c o l d flow t e s t i s c o n t i n u i n g . The t e s t i s t e n t a t i v e l y scheduled t o begin a t AEDC i n March 1966 in t h e Tunnel E a r e a of t h e vsn Karman Gas Dyiiamies F a c i l i t y (WP). Design and f a b r i c a t i o n of t h e model d i f f u s e r and t h e enc8asiEg s t r u c t u r e a r e being c o o r d i n a t e d by R-AERO-AEM. k. Perform Research i n t o t h e Problem of I n t e r a c t i o n of Axisymmetric J e t s The purpose of t h i s p r o j e c t i s t o develop a computer program t~ p r e d i c t t u r b u l e n t mixing and combusticn c h a r a c t e r i s t i c s of a r o c k e t exhaust plume w i t h t u r b i n e g a s e s e x h a u s t i n g p e r i p h e r a l l y about t h e n o z z l e e x i t and w i t h an e x t e r n a l gas stream surrounding t h e plume. This p r o j e c t was i n i t i a t e d d u r i n g t h e preceding c o n t r a c t y e a r . The mathematical procedure has e s s e n t i a l l y been developed and i s being o u t l i n e d i n a t e c h n i c a l r e p o r t . The computer program which w i l l use t h i s mathematical procedure, however, i s n o t y e t complete. 1. T h e o r e t i c a l Techniques f o r P r e d i c t i n g Sase Plow Environment i n t h e V i c i n i t y of t h e Bluff Base of ar- AxFsynmetric Body The purpose of t h i s p r o j e c t i s t o develop a computer program t o c a l c u l a t e base flow p r o p e r t i e s f o r an axisymmetric body w i t h a b l u f f base. Thus f a r , t h e work has c o n s i s t e d p r i m a r i l y of a s t u d y o f l i t e r a t u r e d e s c r i b i n g c u r r e n t techniques f o r d e a l i n g w i t h problems of t h i s n a t u r e . The method of Zumwalt (Zumwabt, 6 . W., "AnahyticaH and Experimental Study of t h e Axially-Symmetric Supersonic Base P r e s s u r e Problem," U n i v e r s i t y o f I l l i . n o i s , PI3.D. T h e s i s , 1959. ) lases an a x i s p e t r i c model w i t h a "sting.'-his mathematical model begins to break down a s t h e sting-to-base-diameter r a t i o approaches zero. T h e r e f o r e , a l i m i t i n g I1 s t i n g " diameter i s found below which t h e model i s no longer a p p l i c a b l e and t h e c a l c u l a t e d p r e s s u r e reaches a maximum v a l u e . An i n v e s t t g a t i o n i s being made of t h e p o s s i b i l i t y of r e p l a c i n g t h e s t i n g by a v i s c o u s c o r e o r neck, �m. Gray-Body C a l i b r a t i o n F a c i l i t y This i s a c a n t i ~ u a t i s nof e f f o r t i n i t i a t e d d u r i n g t h e p r e c e d i n g c o n t r a c t y e a r . The d e s i g n and f a b r i c a t i o n o f t h e Gray-Body C a l i b r a t i o n F a c i l i t y a r e s t i l l u ~ d e r w a y . The d e t a i l e d d e s i g n f o r t h e h e a t s o u r c e module i s 96 p e r c e n t completed. The c o o l i n g and vacuum r e q u i r e m e n t s have been determined, and a l l components have been s e l e c t e d . n. Plow F i e l d VisuaPEzatFon kangley Research Center was v i s i t e d t o c o n f e r w i t h Langley personnel c s n c e r n i l g t h e i r work i n t h e a r e a of flow f i e l d v i s u a l i z a t i o n . Primary i n t e r e s t was i n flow f i e l d measurement t e c h n i q u e s a p p l i c a b l e t o t h e base flow model t e s t s t o be conducted e a r l y n e x t y e a r by R-AERB-AT, A c o n f e r e ~ c ewas h e l d with p e r s o n n e l i n t h e Gas T h e i r main Measurements S e c t i o ? of t h e Instrument Research Division. e f f o r t s a r e c u r r e n t l y d i r e c t e d toward developing e l e c t r o n beam and s p a r k d i s c h a r g e d e v i c e s f o r measurfrig d e n s i t y , ~ 7 e l o e % t y and , temperature They a r e l i m i t e d ts I c w defisity flows. i n a hypersonic E l - w . Meetings were a l s o h e l d w i t h people engaged i n measuring s k i n t e m p e r a t u r e , and a b l a t i o n and aerodynamic h e a t i n g on l i f t i n g r e e n t r y bodies. Also d i s c u s s e d was systems a n a l y s i s s f hypersonic c r u i s e v e h i c l e s t o determine t h e s t a t u s of work and t o e s t a b l i s h c o n t a c t s f o r f u t u r e use. This i s i n s u p p o r t of o u r e f f o r t t o develop t h e c a p a b i l i t y t o a n a l y z e problems expected i n f u t u r e b o o s t e r development. F. Unsteady Aerodynamics Branch 1. J n f l i g h t F l u c t u a t i n g P r e s s u r e and Acoustic Erkviroment P r e l i m i n a r y e s t i m a t e s of t h e S a t u r n V i n f l i g h t a c o u s t i c environments, which cover a Mach range of .8 t o 2,2 f o r t h e v e h i c l e a t zero a n g l e of a t t a c k a r e being p u b l i s h e d . S t u d i e s of s e p a r a t e d flow on cone c y l i n d e r f l a r e bodies have been completed i n t h e MSPC 7-inch t u n n e l . These t e s t s w i l l d e l i n e a t e t h e e f f e c t s of Reynolds number, Mach number, and model geometry on s e p a r a t e d flow. Ease f h u c t u a t i n g p r e s s u r e s a r e being o b t a i n e d on t h e t e s t There " s a t u r n V GoEd FPOW Xozzle Aerodynamic Hinge Moment T e s t m3-64." w i l l be e i g h t f l u c t u a t i n g p r e s s u r e measurements l o c a t e d i n one quadrant of the base. Reports by M r . K e l l y and M r . T h r a l l s f Measurement Analysis It i s planned t o c o n t i n u e t h i s c o n t r a c t . C o r p o r a t i o n a r e being reviewed. �I n t h e meeting " ~ e v i e wof Panel F l u t t e r and Aerodynamic Noise Problems on S a t u r n I B and V , l D on November 15, 1965, R-AERO-AU made a p r o p o s a l t o o b t a i n f l u c t u a t i n g p r e s s u r e d a t a from a f u l l - s c a l e f l i g h t experiment and a 6 p e r c e n t wind t u n n e l model t e s t . 2. Launch S i t e Acoustic Environment The p r e d i c t i o n program f o r t h e s p a t i a l c o r r e l a t i o n f u n c t i o n s on t h e v e h i c l e s u r f a c e f o r b o t h t h e s t a t i c f i r i n g and launch engineg e n e r a t e d a c o u s t i . ~e n v i r o m e n . t has been completed. Attempts t o reduce t h e computing time have n o t been s u c c e s s f u l . An a t t e m p t i s being made t o s i m p l i f y t h e fundamental e q u a t i o n . A technique f o r p r e d i c t i n g t h e sound p r e s s u r e l e v e l r e c e i v e d a t a f a r - f i e l d I s c a t i o n from an a c o u s t i c , broadband, d i r e c t i o n a l , p o i n t s o u r c e r a d i a t i n g i n t o an inhomogeneous media bas been developed. I n i t i a l r e s u l t s from t h i s program r e c e i v e d r e c e n t l y a r e being compared t o measured v a l u e s . P r e d i c t e d and measured r e s u l t s a r e being compared under a wide v a r i e t y o f c o n d i t i o n s t o e v a l u a t e t h e accuracy o f t h i s technique. 3. Acoustic Model Test F a c i l i t y P l a n s a r e being made t o i n i t i a t e a n a c o u s t i c model t e s t a t t h e Acoustic Model T e s t F a c i l i t y a t t h e T e s t Laboratory. P r e l i m i n a r y "checkout" t e s t s a r e planned f o r January 1966. A s s i s t a n c e i s being o b t a i n e d from R-AERO-Y t o d e f i n e t h e m e t e o r o l o g i c a l c o n d i t i o n s which e x i s t a t t h e Acoustic Model T e s t F a c i l i t y . This i n f o r m a t i o n w i l l be used t o determine t h e e f f e c t s o f m e t e o r o l o g i c a l c o n d i t i o n s on t h e a c q u i r e d a c o u s t i c d a t a . 4. Panel F l u t t e r Aerodynamics A meeting was h e l d November 3 , 1965, w i t h M r . C l i n e , PGcVE-DIR, t o d i s c u s s t h e p o t e n t i a l paneb f l u t t e r hazard on t h e S-EVHP s t a g e and t~ d i s c u s s t h e p o s s i b i l i t y of modifying f l i g h t v e h i c l e AS-201. M r . C l i n e s t a t e d t h a t P&VE was prepared t o apply t h e v i s c o - e l a s t i c m a t e r i a l t e s t e d i n t h e Langley f l u t t e r t e s t s , but s i n c e t h e t e s t r e s u l t s showed few b e n e f i c i a l e f f e c t s , they decided n o t t o apply t h e m a t e r i a l . Aero-Astrodynamics Laboratory concurs w i t h t h i s d e c i s i o n . A t t h i s time, P&VE b e l i e v e s t h a t t h e f l u t t e r hazard i s n o t s e r i o u s enough t o m e r i t s t r u c t u r a l m o d i f i c a t i o n on t h e unmanned v e h i c l e s . However, P&VE would l i k e t o perform f l u t t e r t e s t s on a f u l l - s c a l e segment of t h e S-IWIW s t a g e b e f o r e making any d e c i s i o n p e r t a i n i n g t o t h e manned v e h i c l e s . On November 15, 1965, a p r e s e n t a t i o n was g i v e n t o M r . Weidner, R-DIR, by R-AERO and R-PSsVE reviewing t h e panel f l u t t e r problem on t h e S a t u r n I B and V v e h i c l e s . P r e l i m i n a r y c o p i e s of t h e minutes of t h e meeting have been forwarded t o D r . Rees, M r . Weidner, M r . G e l l e r , M r . C l i n e and D r . Rudolph. , �A m e e t i n g was h e l d November 24, 1965 a t Ames Research Center among r e p r e s e n t a t i v e s of ARC and MSPC t o d i s c u s s t h e f e a s i b i l i t y of conducting f u l l - s c a l e p a n e l f l u t t e r t e s t s on t h e forward s k i r t of t h e S - I I B s t a g e . The proposed f a c i l i t i e s a r e t h e Ames 9 x 7-foot These t e s t s w i l l s u p e r s o n i c and 11 x EB-foot t r a n s c n i c wind t w n e l s . i n v e s t i g a t e t h e e f f e c t s o f d i f f e r e n t i a l p r e s s u r e and i n f l i g h t l o a d i n g c o n d i t i o n s on t h e f l u t t e r c h a r a c t e r i s t i c s s f t h e s e p a n e l s and w i l l d e f i n e t h e f l u t t e r boundaries under t h e s e c o n d i t i o n s . S t r u c t u r a l f i x e s would a l s o be i n v e s t i g a t e d shswBd t h e t e s t r e s u l t s d i c t a t e t h e i r need. Ames p e r s o a n e l s t a t e d that they could n o t support Marshall i n t h e ' k x p l o r a t o r y " t e s t of t h i s r a t u r e because of t u ~ l 3 e ls c h e d u l i n g problems and manpower s h o r t a g e . However, they would a l l o t M a r s h a l l two weeks tuntrlel time t o conduct a "proof'Qest, which would c o n s i s t of s u b j e c t i n g t h e p a r e l s t o t h e most s e v e r e i n f l i g h t aerodynamic and Sf f l u t t e r o c c u r s under t h e s e c o n d i t i o n s , s t r u c t u r a l l a a d i n g condTtfsn.s. immediate emphasis would be placed on s t r u c t u r a l f i x e s . With t h i s t y p e of t e s t , no f l u t t e r bouldary would be d e f i n e d . W-AERB-AD f e e l s t h a t more t h a n a ' " r o s f g g test program i n d i c a t e d by kmes w i l l be r e q u i r e d . The most s e v e r e e o ~ d i t i c n scannot be e s t a b l i s h e d w i t h c e r t a i n t y w i t h o u t some e x p l o r a t o r y e f f c r t . Furthermore, a c e r t a i ~p o r t i o n of t h e f l u t t e r boundary n e a r t h e c r i t i c a l b u c k l i n g s t r e s s should be d e f f ~ e dt o determine t h e minimum dynamic p r e s s u r e f o r f l u t t e r w i t h v a r i o u s d i f f e r e n t i a l p r e s s u r e s , Mach numbers a d combinations of compressive and s h e a r l o a d i n g s . It i s b e l i e v e d t h a t a minimum of f o u r weeks t u n n e l time w i l l be r e q u i r e d t o o b t a i n t h e i n f o r m a t i o n n e c e s s a r y t o d e f i n e t h e f l u t t e r boundaries i n more d e t a i l and allow an assessment of t h e f l u t t e r problem. 5. Satur2 V Ground Winds (AU-5) a . As a r e s u l t of a c t i o n item b in memorandum from I - D I R , " P r e s e n t a t i o n of S t r u c t u r a l . Load Design C r i t e r i a , " d a t e d October 20, 1965, a meeting was h e l d o v October 29, 1965, among Messrs. A. G. Rainey, W. H. Reed 111, C. W. J o n e s , and M. C. Farmer of kangley and M r . R. W. W d k e r of MSFC t o d i s c u s s a d d i t i o ~ a lSaturD V ground winds t e s t s i n t h e Langley 16-foot transonic dynamic t u n n e l . The primary o b j e c t i v e s of such t e s t s were t o i 2 v e s t i g a t e , i n more d e t a i l , aerodynamic f i x e s , w i t h primary emphasis on o p t i m i z i n g t h e "haLosfPp r e v i o u s l y t e s t e d and, a£ t e r completing t h e aerodynamic f i x t e s t s , t o conduct t e s t s w i t h o u t r e d - l i n i n g model t o F r v e s t i g a t e peak response loads. Eangley p e r s o n n e l f e l t t h e proposed t e s t s were u q j u s t i f i e d because: (I), The f e a s i b i l i t y of u s i n g t h e p r e s e n t "halo'" c o ~ . f i g u r a t i s nhas n o t been thoroughly i n v e s t i g a t e d by MSFC. (2) Reduction of "haloq9s i z e would p o s s i b l y reduce t h e e f f e e t i v e r e s s of t h e h a l o s below an a c c e p t a b l e l e v e l . (3) So a d d i t i o n a l r e a s o n a b l e aerodynamic f i x e s have been proposed by MSPC. �( 4 ) I n v e s t i g a t i o n of peak response beyond t h e v a l u e s t e s t e d p r e v i o u s l y would be u s e l e s s because u n d e f i n a b l e changes i n t h e s t r u c t u r a l c h a r a c t e r i s t i c s of t h e model a t h i g h e r l o a d i n g s would invalidate the data. b. I f Langley personnel can be convinced t h a t such t e s t s a r e j u s t i f i e d , they will. r e q u i r e t h e following up-to-date information: ( 1 ) F i r s t n a t u r a l frequency of v e h i c l e on t h e launch pad and c r a w l e r f o r a l l weight c o n f i g u r a t i o n s t o be t e s t e d and c o r r e sponding mode shape and g e n e r a l i z e d mass f o r each c o n d i t i o n . ( 2 ) Allowable base bending moment and bending moment d i s t r i b u t i o n along vehicle. c. The f o l l o w i n g c o u r s e of a c t i o n i s being i n i t i a t e d by R-AERO-AU: (1) A formal memo and l e t t e r w i l l be w r i t t e n t o P & E and Kennedy Space C e n t e r , r e s p e c t i v e l y , r e l a t i n g ~ a n g l e y ' so p i n i o n on conducting such t e s t s and r e q u e s t i n g t h e i r r e a s o 2 s , i f any, why t h e s i z e and l o c a t i o n of t h e '%halos1' p r e v i o u s l y t e s t e d would be u n s a t i s f a c t o r y on t h e v e h i c l e . Also, i f t h e l a r g e l l h a l o s ' h c a n o t be used, R-AERO-AU should be informed of t h e maximum a l l o w a b l e " h a l o l b i z e and t h e l o c a t i o n where t h e y could be a p p l i e d . ( 2 ) Formally r e q u e s t up-to-date c h a r a c t e r i s t i c s and c a p a b i l i t i e s from P&VE. vehicle structural ( 3 ) I f such t e s t s o u t l i n e d above can be j u s t i f i e d , r e q u e s t Langley t o conduct them. d. Action item b w i l l r e q u i r e a d d i t i o n a l a i d from t h e c o n t r a c t o r (Boeing) s i n c e no t e s t i n g o r i g i n a l l y was p r o j e c t e d i n c o n t r a c t p l a n n i n g . M r . McNair i s reviewing p r e s e n t Boeing t a s k assignments t o determine i f t h i s a d d i t i o n a l workload may be absorbed w i t h o u t i n c r e a s i n g t h e o v e r a l l l a b o r a t o r y l e v e l of e f f o r t . This survey should be completed by November 1 7 , 1965. M r . E. D. Deese of KSC, who c o n t a c t e d t h i s o f f i c e on November 1 0 , 1965, r e p o r t e d t h a t KSC was working on o f f i c i a l exposure and r e a c t i o n times f o r t h e S a t u r n V v e h i c l e and t h a t a survey i n d i c a t e s t h a t v e h i c l e d e f l e c t i o n w i l l have t o be h e l d below 36 inches when t h e mobile s e r v i c e s t r u c t u r e (MSS) i s around t h e v e h i c l e . In addition, Mr. Deese suggested t h a t t h e i n f l u e n c e of t h e MSS on v e h i c l e dynamic r e s p o n s e be i n v e s t i g a t e d and t h a t aerodynamic l o a d s on t h e MSS i t s e l f be e s t a b l i s h e d , KSC would d e s i g n and f a b r i c a t e t h e model, and a d e c i s i o n would be needed i n t h e near f u t u r e t o meet a February o r March t e s t d a t e . R-AERO-AU �informed KSC o f ~ a n g l e y ' sp o s i t i o n and of t h e upcoming MSPC r e q u e s t . The KSC s u g g e s t i o n w i l l be i n c o r p o r a t e d i n t o t h e t e s t p l a n , i f f e a s i b l e . 6. S a t u r n 1 3 / ~ e n t a u rGround Winds Although R-AERO-AU has r e l e a s e d a l l scheduled wind t u n n e l r wind s t u d i e s , t h e c o n t r a c t w i t h Atkins time f o r S a t u r n Z ~ / ~ e n t a uground and M e r r i l h , H D ~ . , t o r e d e s i g 3 and c o n s t r u c t a more e x a c t a e r o e l a s t i c ground winds model of t h e S a t u r n ~ / @ e n t a uwas r n o t canceled. R-AERO-AU f e l t i t d e s i r a b l e t o c o n t i x u e w i t h t h e c o n s t r u c t i o n of t h i s model because Atkins and M e r r i l l had almost completed t h e r e d e s i g n o f t h e S-IS and S - I D s t a g e s when R-AERO-AU r e c e i v e d i n s t r ~ c t i o n st o r e l e a s e scheduled wind t u n n e l time. Also, because t h i s model has a more e x a c t mass and s t i f f n e s s d i s t r i b u t i o n , and because of t h e p o s s i b i l i t y o f u s i n g t h i s model w i t h o t h e r f u t u r e payload shapes and w e i g h t s , t h e model would be v e r y h e l p f u l i n u n d e r s t a n d i n g and f i n d i n g f i x e s for t h e g u s u ~ dwinds problem. The M a r t i n Company has prepared a p r e l i m i n a r y r e p o r t o f on.-line d a t a obtain.ed. du.ring the wind t u n n e l t e s t program ( P u b l i c a t i o n , Section 10); these reports a r e not f o r d i s t r i b u t i o n . N r t h e r data r e d u c t i o n by M a r t i n has h a l t e d a w a i t i n g c o n t r a c t n e g o t i a t i o n f o r c o s t overruns. 8. A e r o e l a s t i c C h a r a c t e r i s t i c s of Vehicle 203 Am experiment t o b e t t e r d e f i n e t h e p r e s s u r e d i s t r i b u t i o n i n t h e Mach range of .80 t o .95 has been completed. This i n f o r m a t i o n has been forwarded to Lockheed a s an aid i n determining t h e aerodynamic damping o f v e h i c l e 203. 9. Dynamics o f Separated Plow M r . E r i c i s s o n p r e s e n t e d t h e f i n a l r e s u l t s of c a n t r a c t NAS8-5338 02 November 9 , 1965. This c o n t r a c t w i l l be t e r m i n a t e d upon completion of a f i n a l r e p o r t t o be r e l e a s e d about December 31, 1965. �VI. DPXAMICS AND FLIGHT MECHANICS DIVISION A. Applied Guidance and P l i g h t Mechanics Branch 1. Saturn IB a. A memorandum e n t i t l e d " V e l o c i t y E r r o r Due t o T h r u s t Decay o f t h e S-IVB S t a g e f o r AS-201 and AS-20%80h a s b e e n d i s t r i b u t e d . A v e n t i n g a n a l y s i s f o r t h e AS-203 ( l i q u i d hydrogen e x p e r i m e n t ) h a s b e e n conducted, Preliminary r e s u l t s indicate t h a t variations i n vent force and i n s e r t i o n c o n d i t i o n s c a u s e no s i g n i f i c a n t change i n t h e o r b i t a l conditions. Thus, l i t t l e e f f e c t i s e x p e c t e d on t h e t r a c k i n g a c q u i s i t i ~ n and l o s s t i m e ; t h i s i s b e i n g s t u d i e d by R-AERO-F. b. Performance changes due t o i n d i v i d u a l p e r t u r b a t i o n s o f t h e s t a g e and v e h i c l e c h a r a c t e r i s t i c s sf t h e S a t u r n I ~ / @ e n k a u vr e h i c l e have b e e n d e t e r m i n e d , The NASA T e c h n i c a l Memorandum c o v e r i n g t h e g e n e r a l performance s u r v e y i s b e i n g p r e p a r e d . c. The s t u d y on l a u n c h p r o b a b i l i t y f o r d u a l l a u n c h t y p e m i s s i o n s h a s b e e n f i n i s h e d , and a r e p o r t i s b e i n g p r e p a r e d . 2, Saturn V a. The e f f e c t s o f c o n t i n u o u s o p e r a t i o n o f t h e AS-503 S-IVB oxygen-hydrogen b u r n e r (modified S-IV helium h e a t e r ) upon t h e LOR m i s s i o n parking o r b i t a r e being investigated. The b u r n e r w i l l be i n s t a l l e d o n AS-503 and s u b s e q u e n t p r i m a r i l y f o r r e p r e s s u r i z a t i o n of t h e S-Em s t a g e . However, i f t h e r e s u l t s o f t h e AS-20% e x p e r i m e n t i n d i c a t e t h e r e q u i r e m e n t , t h e b u r n e r w i l l be o p e r a t e d c o n t i n u o u s l y t h r o u g h o u t t h e p a r k i n g o r b i t t o p r o v i d e a d d i t i o n a l t h r u s t f o r s e t t l i n g t h e p r o p e l l a n t s i n t h e S-PVB. The The r e q u i r e d computer r u n s , b u r n e r h a s a t h r u s t l e v e l o f 15 t o 22 pounds. u s i n g p r e l i m i n a r y d a t a , have been s u b m i t t e d . b, The two-volume DM-2 d e s i g n r e f e r e n c e m i s s i o n document i s b e i n g i n s p e c t e d and c o r r e c t e d , and should go t o reproductizhn on December 11, 1965. T h i s document i s t h e p r o d u c t o f a j o i n t working organizations, operating g r o u p , composed o f p e r s o n s from t h e MSFC/TBC/NSC under t h e d i r e c t i o n o f t h e R e f e r e n c e T r a j e c t o r y Subpanel, c. A s t u d y o f t h e f e a s i b i l i t y o f i n i t i a t i n g g u i d a n c e d u r i n g t h e S-IC s t a g e o f t h e S a t u r n V AS-506 v e h i c l e shows t h a t t h e p a y l o a d c a n be i n c r e a s e d c o n s i d e r a b l y by u s i n g l i f t i n g t r a j e c t o r i e s l e a d i n g i n t o t h e r e l e a s e o f t h e HGM e q u a t i o n s between 80 t o 90 s e c o n d s , b u t t h e r e i s a l s o a n a s s o c i a t e d i n c r e a s e i n loads. An o p t i m i z e d z e r o - l i f t t r a j e c t o r y w i t h IGM b e i n g r e l e a s e d a f t e r tower j e t t i s o n was u s e d a s a r e f e r e n c e t r a j e c t o r y . The l o a d s were n o t i n c r e a s e d d u r i n g t h e b o o s t e r s t a g e s i n c e t h e a n g l e o f a t t a c k b u i l d u p came a f t e r t h e max q r e g i o n was p a s s e d . This approach �gave an i n c r e a s e of 1100 pounds i n parking o r b i t , This 1100 pounds could be t r a d e d back i n t o a s t e e p e r t r a j e c t o r y f o r a 3 p e r c e n t r e d u c t i o n i n l o a d s w i t h no payload p e n a l t y over t h e r e f e r e n c e t r a j e c t o r y . d. Openc and c l o s e d loop guidance i n t h e S-IC s t a g e o f t h e S a t u r n V AS-506 v e h i c l e i s being analyzed. The i t e r a t i v e guidance was r e l e a s e d on t h e r e f e r e n c e t r a j e c t o r y a f t e r t h e max q r e g i o n was The passed t o shape t h e t r a j e c t o r y f o r t h e open loop t i l t program. c l o s e d loop guidance approach i n t h e b o o s t e r could n o t be j u s t i f i e d over t h e open loop guidance system from a 3-sigma v e h i c l e and atmospheric p e r t u r b a t i o n study. However, an S-IC engine-out a n a l y s i s shows t h a t t h i s may n o t be the case. The engine-out a n a l y s i s i s completed, and a s i m i l a r a n a l y s i s of engine-out i n t h e S-IC s t a g e f o r l i f t i n g t r a j e c t o r i e s l e a d i n g i n t o IGM r e l e a s e a f t e r max q i s being made. e. The payload c a p a b i l i t y of S a t u r n V v e h i c l e s , based upon November c u r r e n t w e i g h t s , was r e c e i v e d from TBC and t r a n s m i t t e d t o I n d u s t r i a l Operations. 3. General a. A j o i n t working group c o n s i s t i n g of personnel: from t h e MSFC/GE/TBC/MSC/TRW o r g a n i z a t i o n s i s developing a computer program f o r The program employs g e n e r a t i n g " J o i n t Apollo Reference T r a j e c t o r i e s . " ( a s much a s p o s s i b l e ) t h e r e s u l t s of t h e ' V e h i c l e Systems and T r a j e c t o r y Analysis M o d u l a r i z a t i o n t > r o j e c t , and t h e " P r o j e c t Apollo Coordinate System Standards." For c u r r e n t needs, a m a k e s h i f t program i s i n o p e r a t i o n t o g e n e r a t e documents such a s t h e DRM-2, b u t , a t t h e same time, t h e e f f i c i e n t modularized program i s being developed. The modularized program should be e a s i l y modified t o g e n e r a t e o p e r a t i o n a l t r a j e c t o r i e s when t h a t phase o f t h e program i s reached. b. S t u d i e s a r e b e i n g conducted by Boeing, C h r y s l e r , Northrop and in-house personnel i n c o o r d i n a t i o n w i t h AERO-F, P&VE, and ASTR on t h e e f f e c t s of t h r u s t o s c i l l a t i o n r e s u l t i n g from t h e closed-loop a c t i o n of t h e p r o p e l l a n t u t i l i z a t i o n system d u r i n g t h e S-I1 and S-IVB f l i g h t on t h e guidance accuracy and payload. These s t u d i e s c o n s i d e r both p r e d i c t e d t h r u s t h i s t o r i e s (provided by P&VE) and p a r a m e t r i c v a r i a t i o n s i n t h e amplitude and p e r i o d of a s i n e wave r e p r e s e n t a t i o n of t h r u s t . These s t u d i e s , which i n c l u d e b o t h t h e S a t u r n I B and t h e S a t u r n V v e h i c l e s , a r e being g i v e n t o p p r i o r i t y i n t h e guidance work of a l l of t h e i n d i c a t e d groups, w i t h a heavy commitment of manpower and computer time involved. c. The s t e e p e s t d e s c e n t o p t i m a l t r a j e c t o r y program has been completed. The program u s i n g t h e complete a d j o i n t method which f i n d s e x a c t o p t i m a l s i n t h e sense t h a t t h e t r a j e c t o r i e s s a t i s f y t h e n e c e s s a r y c o n d i t i o n i s a l s o completed. It i s planned t o i n c o r p o r a t e i n e q u a l i t y c o n s t r a i n t s i n t o t h e l a t t e r program i n t h e near f u t u r e . Reports on t h e �two t e c h n i q u e s a r e b e i n g prepared a s w e l l a s a summary o f t h e r e l a t i v e advantages and d i s a d v a n t a g e s . This work has been performed t o develop an in-house c a p a b i l i t y i n o p t i m i z a t i o n techniques o t h e r t h a n c l a s s i c a l COV i n a d d i t i o n t o t h e obvious advantage of o b t a i n i n g a good program. d. A study i s being i n i t i a t e d t o s i m p l i f y and reduce t h e g e n e r a l s t a g e i t e r a t i v e guidance e q u a t i o n s by e l i m i n a t i n g t h e c r o s s coupling yaw s t e e r i n g r a t e Q K 4 ) . A memorandum o n the r e s u l t s w i l l be issued. e. The study on the p r o b a b i l i t y o f t h e S-IVB/IU the moon i s complete and a r e p o r t has been prepared. impacttng f. The purpose of t h e l u n a r launch window s t u d y i s t o show the e f f e c t of t h e o p e r a t i o n a l c o n s t r a i n t s o f launch azimuth, Bawnch l i g h t i n g , Lunar l i g h t i n g , launch window w i d t h , and Paunch p e r i o d on t h e l u n a r launch windows f o r t h e 1967-72 time perksd. An I n t e r n a l Note i s being prepared. ?%he c r l n s t r a f n t o f launch l i g h t i n g Fs being removed from t h e c u r v e s , and t h e r e s u l t i ~ gk a ~ n c bwindow d i s p l a y s will be published i n another report. 4. Advanced Apollo Program ( U P ) a. Program). The name MAP seems uncommonly a p p r o p r i a t e i n t h i s c a s e because t h e program d e s i r e d i s t o examine launch o -p-p o r t u n i t i e s and miss i o n c o n s t r a i n t s and 'hap" o u t f o r t h e u s e r t h o s e Launch s p p o r t u n i t i e s and launch c o n d i t i o n s t h a t a l l o w one t o s a t i s f y a l l t h e d e f i n e d c o n s t r a i n t s . Although approximations a r e used i n t h i s p r e l i m i n a r y a n a l y s i s , t h e MAP results are quite reliable. The program i n use a t MSC f o r MAP purposes was picked up l a s t week; no documentation i s a v a i l a b l e . The MSC program i s limited t o lunar applications. Our i n t e n t i s t o p i c k up a program from Goddard t h a t has some g e n e r a l f e a t u r e s d e s i r e d f o r t h e MAP program, p u l l any u s e f u l modules from t h e MSC program, and d e v e l c p o t h e r modules r e q u i r e d t o produce t h e d e s i r e d MAP program. The r e s u l t a n t program should be e s p e c i a l l y u s e f u l f a r AAP s t u d i e s . b. The payload c a p a b i l i t y of Saturn I B v e h i c l e s , based upon November c u r r e n t wei,ghts, was r e c e i v e d from CCSD and t r a n s m i t t e d t o I n d u s t r i a l Operations. c. S a t u r n HB P o l a r O r b i t s . Optimized t r a j e c t o r i e s f o r S a t u r n I B P o l a r O r b i t s have been generated f o r b o t h a t h r e e - s t a g e d i r e c t a s c e n t i n t o a 200 nm c i r c u l a r p o l a r o r b i t and f o r a f l i g h t p r o f i l e w i t h a s u b o r b i t a l s t a r t of t h e S e r v i c e M ~ d u l ei n t o an 80 nm e l l i p s e c i r c u l a r i z e d a t apogee u s i n g a second burn of t h e SM. Work c o n t i n u e s t o i n c l u d e a 14-day o r b i t and d e - o r b i t t o the r e e n t r y p o i n t , b u t p r o g r e s s i s slow because of problems i n t h e computer r o u t i n e . �T r a j e c t o r i e s have been completed f o r a S a t u r n I B v e h i c l e d. two-stage d i r e c t a s c e n t i n t o a 200 m c i r c u l a r o r b i t f o r Apol%a a p p l i c a t i o n s o r b i t a l experiments, One v e h i c l e would be used f o r a f u e l t r a n s f e r experiment, w h i l e the o t h e r would house an o r b i t a l workshop i n t h e D o c m e n t a t i o n has been delayed because empty S-IVB p r o p e l l a n t tanks. of o t h e r work w i t h higher p r i o r i t i e s . e. A study has been i n i t i a t e d t o d e f i n e t h e amount s f f l i g h t performance r e s e r v e s r e q u i r e d t o guarantee S a t u r n I W payloads when t h e S e r v i c e Module i s used a s a t h i r d s t a g e . A nominal t r a j e c t o r y The s t u d y , has been determined based upon an 81 nm by 107 run e l l i p s e . being j o i n t l y conducted w i t h h c k h e e d , i s 50 per c e n t complete. f, An e x i s t i n g caZcuPus o f v a r i a t i o n s computer r o u t i n e l w i t h m o d i f i c a t i o n s t o c u t o f f on C3 and i s o l a t e a n i n j e c t i o n plane has been checked o u t . Wurk w i l l resume when problems of higher p r i o r i t y have been s t u d i e d . The r e q i ~ % r e m e nft o r t h i s program has been r e c s g ~ i z e d fram surveying t h e prap-jsed U P m i s s i o n s . g. A s t u d y i s b e i n g conducted t o d e f i n e t h e c a p a b i l i t y of t h e S a t u r n V v e h i c l e c f p l a c i n g a paylcad i n t o a synchronous e q u a k o r i a l orbit. The s t u d y i n c l u d e s both a s u b o r b i t a l s t a r t of t h e S-It% i n t o a 100 nm p a r k i n g o r b i t and an o r b i t a l s t a r t of t h e S-PVB o u t of 100 run parking o r b i t . The r e q u i r e d plane change i s made a f t e r t h e parktng o r b i t . h. Saturn V Polar Orbit. The pay1,oad c a p a b i l i t y of t h e Saturn V v e h i c l e f o r 200 nm a l t i t u d e p o l a r o r b i t has been d e f i n e d and documented i n R-AEIPO-DAP-104-65. . i. A 1 1 S a t u r n HB and S a t u r n ~ ~ / ~ e n t performance a u r c a p a b i l i t y d a t a have been completed. J. The comparison of machine time v e r s u s accuracy of v a r i o u s e x i s t i n g perfcrrnanee r o u t i n e s and t h e Lockheed-developed PRESTO I f t h e Leckheed claims f o r t h i s program a r e r o u t i n e i s completed. v e r i f i e d , i t should prove t o be an e x c e l l e n t tcoL f o r U P f l i g h t p r o f i l e s . k. A memorandum has been d i s t r i b u t e d which documents t h e m i s s i o n p r o f i l e f o r AAP l u n a r mapping mission. T h i s p r o f i l e was p r e s e n t e d a t t h e AAP M i s s i o n Planning Task Force meeting a t MSC on November 9 , 1. Development s f t h e e a r t h o r b i t a l rendezvous deck u s i n g IGM continued. Two t y p e s o f rendezvous a r e now being attempted. In t h e f i r s t c a s e b o t h t h e p u r s u i t and t a r g e t v e h i c l e s a r e i n c i r c u l a r p a r k i n g o r b i t s w i t h t h e p u r s u i t v e h i c l e i n the inner o r b i t . These two v e h i c l e s have been brought t o w i t h i n 10 k i l o m e t e r s of each o t h e r w i t h small e r r o r s I n the second c a s e t h e t a r g e t v e h i c l e i s i n an e l l i p t i c a l i n velocity, orbit. F a i r l y l a r g e e r r o r s i n p o s i t i o n a r e a l s o being o b t a i n e d i n t h i s case. Continued development and refinement of t h i s deck should e l i m i n a t e t h e s e inaccrlracies i n p o s i t ion. �5. Contractors (1) AS-501 R e f e r e n c e T r a j e c t o r y Document: The Boeing document "AS-581 Launch V e h i c l e R e f e r e n c e ' T r a j e c t c r y s vi s b e i n g reviewed before r e l e a s e . (29 AS-502 R e i e r e n c e T r a j e c t o r y Dosl.m?nf: The AS-582 launch v e h i c l e r e f e r e n c e t r a j e c t o r y i s being prepared, 31e b a s i c t r a j e c E2wevez-, a n a d d i t i o n a l t o r y w i l l be f o r l a u n c h a l o n g an azimuth of 72'. s t u d y w i l l . be made t o d e t e r m i n e t h e e f f e c t of a v a r i a b l e haunch azimuth and a v a r i a b l e c o a s t p e r i o d i n p a r k i n g o r b i t on the ground t r a c k , s p l a s h s i t e , l a u n c h windaw, and t r a c k i n g a v a i l a b k l i t y . (13) AS-363 P x e l i v a n a r q Elnss i ~ Prc n file: Ike AS-563 p r e l i m i n a r y rnissaon p r ~ f i l ewas p r e s e n t e d ks t h e L 2,B sl-&bpa.neIm e e t i n g ? t h a t %ha p r o f i l e a t MSC o n November 5 , 1965, MSt personnel ~ ~ i n k e dt did not completely s a t i s f y a s e t c f r e i e n r l y r e l e a s e d S / C m i s s f ~ n requirements. MSC r e q u e s t e d MSBC serpprlrt i n p r e p a r i n g a s e t ?F l a u n c h v e h i c l e i n j e c t i o n characteristics f o r s e v e r a l p c s s i b l e S / C missLon profiles. Boeing i s p r e p a r i n g t h e d a t a . ( 4 ) AS-504 Spectrum: I n r e s p o n s e t o a r e q u e s t of t h e r e f e r e n c e t r a j e c t o r y s u b p a n e l , a s e t of k r a j e c t a r i e s i s b e i n g g e n e r a t e d f o r t h e AS-504 m i s s i c n , This s e t bncludes f i v e launch a z i m u t h s w i t h a f i r s t and second o r b i t i n j e c t i o n from e a c h , f o r a t c t s l 0 2 P O t r a j e c t o r i e s . The d a t a t o be g e n e r a t e d f o r d a y s o t h e r t h a n t h e primary l a u n c h day have n o t been d e c i d e d upon. T h i s work i s scheduled t o be completed by December 13. (5) T r a j e c t o r y O p t i m i z a t i o n Program: %be document d e s c r i b i n g t h e r e s u l t s of t h e s t e e p e s t a s c e n t t r a j e c t o r y s t u d y f o r maximizing p a y l c a d i n o r b i t s u b j e c t t o Lnequal-ity c ~ n s t r a i n t sd u r i n g a t m o s p h e r i c f l i g h t i s b e i n g c ~ m p l e t e d . A d ~ s c u s s i c n<>f t h e c o m p a t i b i l i t y of t h e r e s u l t s with s t a g i n g requirements i s being ~ n c l u d e d , Application of ISONAX t o t h e a n a l y s i s i s b e t n g s t u d i e d . 6 F l i g h t P l a n Computer Program Develcprnent : T h i s program, which i s a p o r t i o n of t h e J o i n t ApolEc R e f e r e n c e T r a j e c t o r y Program, i s t o be used f o r a d e t a i l e d s s m u l a t i s n ~f the launch v e h i c l e flight. E n g i n e e r i n g a n a l y s i s i s c o n t i n u i n g on t h e p a r k i a g o r b i t and b o o s t - t o - i n j e c t i o n s i m u B a t ~ o n s , Models f 3 r v e n t % n g and u l l a g e t h r u s t have b e e n d e v e l o p e d and coded. The s t u d y o f p a r k i n g o r b i t p e r t u r b a t i o n s caused by t h e moon and s u n , a s w e l l as checkout cf p a r k i n g o r b i t subr o u t i n e s , h a s b e e n d e l a y e d because o f program checkout. �( 7 ) T a r g e t i n g D e f i n i t i o n and S i m p l i f i c a t i o n : The purpose o f t h i s assignment i s t o f i n d t h e b e s t way t o d e f i n e and make a v a i l a b l e t h e t a r g e t i n g parameters a s r e q u i r e d by t h e i t e r a t i v e guidance mode, The t a r g e t parameters r e p r e s e n t o r b i t and l u n a r i n j e c t i o n t e r m i n a l c o n d i t i o n s . An e x p r e s s i o n has been o b t a i n e d f o r launch azimuth v a r i a t i o n a s a f u n c t i o n of time o f launch f o r t h e simple s p h e r i c a l case. Difficulties have been encountered i n g e n e r a t i n g a f u n c t i o n which w i l l make up t h e d i f f e r e n c e i n going from t h e s p h e r i c a l t o the complete case. b. Chrysler (1) AS-203 and AS-204 Engine-Out Analysis: The r e s u l t s of t h e s i n g l e and d u a l S-IB engine-out s t u d i e s f o r t h e AS-203 and AS-204 v e h i c l e s a r e being published. ( 2 ) AS-203 Launch Vehicle Reference T r a j e c t o r y : An AS-203 r e v i s e d launch v e h i c l e r e f e r e n c e t r a j e c t o r y has been g e n e r a t e d , and p r e l i m i n a r y documentation h a s been r e c e i v e d . A f l i g h t c o r r i d o r , d e s i g n t r a j e c t o r i e s , and f l i g h t performance r e s e r v e requirements being prepared should be completed e a r l y i n December. (3) AS-203 I n t e r s t a g e Venting T r a j e c t o r y : P r e l i m i n a r y documentation of a maximum and minimum p r e s s u r e time h i s t o r y has been received. Review o f t h e s e t r a j e c t o r i e s w i l l be a j o i n t e f f o r t w i t h R-AERO-ADD. (4) AS-204 Launch Vehicle Reference T r a j e c t o r y : The f l i g h t c o r r i d o r , d e s i g n t r a j e c t o r i e s , and f l i g h t performance r e s e r v e requirements document i s being published. (5) AS-205 and 206 P r e l i m i n a r y Launch V e h i c l e Reference T r a j e c t o r i e s : The AS-205 and 206 launch v e h i c l e p r e l i m i n a r y r e f e r e n c e t r a j e c t o r i e s have been documented. A f l i g h t c o r r i d o r , d e s i g n t r a j e c t o r i e s , and f l i g h t performance r e s e r v e requirements f o r AS-206 a r e being generated. The AS-205 d e s i g n t r a j e c t o r i e s , f l i g h t c o r r i d o r , e t c . , a r e being published. (6) AS-205 and AS-206 Abort and A l t e r n a t e Missions: P r e l i m i n a r y documentation of AS-205 and AS-206 a b o r t and a l t e r n a t e m i s s i o n p l a n s i s b e i n g reviewed. AS-207 P r e l i m i n a r y Launch Vehicle Reference (7) T r a j e c t o r y : A f l i g h t c o r r i d o r , d e s i g n t r a j e c t o r i e s , and f l i g h t performance r e s e r v e requirements a r e b e i n g determined and should be completed i n December. (8) AS-207 Abort and A l t e r n a t e Missions: A s t u d y i s underway t o d e f i n e the performance c a p a b i l i t y of the AS-207 v e h i c l e w i t h s i n g l e and d u a l e n g i n e s o u t t o perform t h e primary m i s s i o n o r t o d e f i n e an a c c e p t a b l e a l t e r n a t e mission. �( 9 ) T h r e e - D e g r e e s - o f - F r d m Computer Routine: A v e r y a c c u r a t e check o f t h e AS-207 launch v e h i c l e r e f e r e n c e t r a j e c t o r y has been obtained. Work c o n t i n u e s on expanding t h e c a p a b i l i t y of t h i s r o u t i n e , which i s t o r e p l a c e t h e r o u t i n e now being used. c. Lockheed The use o f s w i t c h i n g f u n c t i o n t h e o r y t o d e t e r m i n e optimum s t a g i n g p o i n t s i s being i n v e s t i g a t e d . The s w i t c h i n g f u n c t i o n e q u a t i o n s have been w r i t t e n and have been i n c o r p o r a t e d i n t o a n e x i s t i n g two-dimensional vacuum computer r o u t i n e . Checkout a n a l y s i s i s complete, If t h e and t h e three-dimensional e q u a t i o n s a r e being formulated. s w i t c h i n g f u n c t i o n approach proves t o be p r a c t i c a l f o r g e n e r a l performance c a l c u l a t i . o n s , i t i s planned t o e v e n t u a l l y r e p l a c e o r modify e x i s t i n g performance computer programs u n t i l a l l programs u s e t h i s much more e f f i c i e n t technique. d, Ling-Temco -Vought The l u n a r launch window study,wilP be completed i n December w i t h f i n a l documentation i n January. No major problems have been encountered. e. Northrop (1) The E r r o r P r o p a g a t i o n Computer Program w i l l u s e a Monte C a r l o t e c h n i q u e t o g e n e r a t e a s e t of t r a n s l u n a r i n j e c t i o n e r r o r s ; t h e n , u s i n g a s e t o f two body p a r t i a l d e r i v a t i v e s , t h e s e e r r o r s w i l l be propagated t o p o s i t i o n and v e l o c i t y e r r o r s a t some f u t u r e time a l o n g t h e trajectory. Using t h e s e new p o s i t i o n and v e l o c i t y p o i n t s , a d i s t r i b u t i o n This program w i l l be used t o s u p p o r t of midcourse AV w i l l be g e n e r a t e d . both Apollo and AAP s t u d i e s . The advantage of t h i s program over p r e v i o u s r o u t i n e s i s t h e i n c o r p o r a t i o n of t h e two-body p a r t i a l d e r i v a t i v e s which w i l l a l l o w much f a s t e r and more e f f i c i e n t g e n e r a t i o n of t h e d e s i r e d d a t a a t l i t t l e l o s s i n accuracy. ( 2 ) The second p a r t o f t h e S a t u r n V hardware e r r o r The d a t a a r e being a n a l y z e d , analysis i s i n the d a t a processing stage. using Monte C a r l o t e c h n i q u e s , and a r e b e i n g compared t o t h e r e s u l t s o b t a i n e d from t h e r o o t sum s q u a r e (RSS) s t u d y p r e v i o u s l y completed, A Monte C a r l o a n a l y s i s of t h e p o s i t i o n and v e l o c i t y v e c t o r s a t i n j e c t i o n onto t h e l u n a r t r a n s f e r c o n i c has g i v e n an e r r o r p r e d i c t i o n a l m o s t i d e n t i c a l t o t h a t o b t a i n e d w i t h t h e RSS method. ( 3 ) A guidance p l a t f o r m switchover c a p a b i l i t y has been s u c c e s s f u l l y added t o t h e System A n a l y s i s deck. This deck can now be used t o conduct a study i n which b o t h open l o o p and c l o s e d l o o p t r a j e c It i s hoped t h a t t h i s s t u d y w i l l t o r i e s a r e s i m u l t a n e o u s l y simulated. r e v e a l t h a t open loop guidance can be used f o r checkout of t r a j e c t o r i e s guided by e i t h e r open o r c l o s e d loop methods. �(4) The r e s u l t s of a p e r t u r b a t i o n s t u d y on t h e r e c e n t l y developed l u n a r b r a k i n g deck u s i n g IGM have been g i v e n t o i n t e r e s t e d NASA personnel. Another p e r t u r b a t i o n s t u d y i s underway i n which t h e i n c l i n a t i o n and nodal l o n g i t u d e a r e p r e s p e c i f i e d and f i x e d . B. Control Theory Branch 1. Saturn I B The l o s s of h y d r a u l i c power t o one c o n t r o l engine o f t h e AS-204 v e h i c l e has been i n v e s t i g a t e d from l i f t - o f f t o a f l i g h t time o f 50 seconds. I n c a s e s where t h e r o l l r a t e of t h e v e h i c l e was e x c e s s i v e l y h i g h , t h e t r a j e c t o r y was terminated. This i s i n answer t o an a c t i o n item from t h e F l i g h t Mechanics P a n e l , which r e q u e s t e d t h i s f a i l u r e mode be extended and t h e t r a j e c t o r y p r i n t o u t f u r n i s h e d t o t h e p r o p e r people a t MSC, Houston. Three c a s e s have been chosen. A l l t h r e e c a s e s b u i l d t o a p i t c h and yaw a t t i t u d e r a t e of 1 t o 2 degrees per second. However, t h e r o l l r a t e goes t o 5 degrees p e r second f o r a l l t h r e e c a s e s i n l e s s than two seconds a f t e r t h e f a i l u r e . From t h i s p o i n t t h e behavior of t h e three cases d i f f e r . CASE 1. The r o l l r a t e c o n t i n u e s to b u i l d and t h e p i t c h and yaw r a t e s remain c o n s t a n t o r d e c r e a s e . A t t h e end of 5 seconds, t h e r o l l r a t e i s 11 degrees p e r second and t h e p i t c h and yaw r a t e s a r e o n l y 1%d e g r e e s p e r second. A t 3% seconds a f t e r f a i l u r e , t h e pitch-yaw a t t i t u d e i s 5 d e g r e e s w i t h a r a t e o f 1 314 degrees p e r second. However, t h e r o l l a n g l e i s 19 d e g r e e s w i t h a r o l l r a t e of 7% d e g r e e s per second. CASE 2. The r o l l r a t e remains f a i r l y c o n s t a n t a t 4% t o 5 degrees per second, and t h e p i t c h and yaw r a t e s drop t o 1 d e g r e e per second o r l e s s . A t t h e end of 8 seconds, t h e r o l l r a t e i s 5 degrees per second and t h e pitch-yaw r a t e s a r e % d e g r e e p e r second. A t t h e end of 4 seconds a f t e r f a i l u r e , t h e pitch-yaw a t t i t u d e a n g l e i s 5 degrees w i t h a r a t e o f 1 d e g r e e p e r second; however, t h e r o l l a n g l e i s 17% degrees w i t h a r a t e of 4% d e g r e e s p e r second. CASE 3. The r o l l r a t e goes t o 5 degrees p e r second w i t h i n 1%seconds a f t e r f a i l u r e and t h e n r e t u r n s t o z e r o a f t e r 5% seconds from f a i l u r e . The pitch-yaw r a t e s go t o 1%d e g r e e s p e r second w i t h 2 seconds a f t e r f a i l u r e and t h e n r e t u r n t o z e r o w i t h i n 6 seconds from failure. A t t h e end o f 6 seconds, t h e pitch-yaw r a t e s and t h e r o l l r a t e s a r e z e r o ; however, t h e pitch-yaw a n g l e i s 5 degrees and t h e r o l l a n g l e i s 16 degrees. These t h r e e c a s e s g i v e a good spread o f t h e v e h i c l e behavior under t h e i n £ luence of h y d r a u l i c f a i l u r e t o one c o n t r o l engine. These r e s u l t s s u g g e s t t h a t t h e r o l l r a t e s and a n g l e s a r e b e t t e r i n d i c a t o r s �o f impending t r o u b l e from t h i s f a i l u r e t h a n t h e pitch-yaw s i g n a l s . N o t i c e i n a l l t h r e e c a s e s t h e r o l l r a t e was 5 d e g r e e s p e r second i n l e s s t h a n 2 seconds a f t e r f a i l u r e . At t h e t h e , t h e r o l l r a t e was 5 d e g r e e s p e r s e c o n d , t h e pitch-yaw r a t e s were l e s s t h a n 2 d e g r e e s p e r s e c o n d , and t h e pitch-yaw a n g l e s were e q u a l t o o r l e s s t h a n 2 degrees. (1) C o n t r o l r e s p o n s e s c o v e r i n g f i r s t s t a g e f l i g h t time t o d e t e r m i n e bending moments and c o n t r o l v a r i a b l e e n v e l o p e s e r e b e i n g Wind g u s t s w i l l be a p p l i e d g e n e r a t e d u s i n g c o n t r o l . w e i g h t s mass d a t a . a t a l l a l t i t u d e s t o comply w i t h t h e new d e s i g n c r i t e r i a . ( 2 ) A s t u d y t o d e t e r m i n e t h e e f f e c t o f wind d i r e c t i o n and wind speed o n r i g i d body c v n t r o l r e s p o n s e s and pertinent t r a j e c t o r y November 3 , 1 9 6 5 , i n f o r m a t i o n h a s been documented i n Memo R-AERO-DCC-36-65, ( 3 ) %he r e s u l t s o f a s t u d y t o d e t e r m i n e t h e RSS bending moments and c n r r e s p o n d i n g v e h i c l e c o n t r o l r e s p n n s e s have b e e n documented a s Memo R-AERQ-DCC-37-65. The s t u d y , based e n new c o n t r o l w e i g h t s , w i l l s u p e r s e d e d a t a p u b l i s h e d i n R-AERO-DCC-26-65, August 1 2 , 1 9 6 5 . The d a t a cover time p o i n t s c o r r e s p o n d i n g t o Mach L.0, max q , and j u s t b e f o r e inboard e n g i n e c u t o f f . A b r i e f s t u d y o f t h e c o n t r o l s f t h e AS-207 v e h i e l e w i t h o u t f i n s h a s been made t o o b t a i n d a t a f o r comparison w i t h t h e proposed s t a n d a r d l a u n c h v e h i c l e . The e f f e c t o n s t a g i n g o f s h o r t e n i n g t h e t i m e between d. IECO and OECO f o r t h e S a t u r n PB h a s been examined. The p r e s e n t sequence a l l o w s 6 s e c o n d s between t h e two e v e n t s , c o s t i n g a p p r o x i m a t e l y 200 pounds It was d e t e r m i n e d t h a t one second between t h e two e v e n t s i n payload. would be s u f f i c i e n t f o r s t a g i n g r e q u i r e m e n t s from a c o n t r o l s t a n d p o i n t . e. Using AS-202 d a t a , r i g i d body r e s p o n s e s and bending moment c o e f f i c i e n t s were d e t e r m i n e d f o r time p o i n t s i n t h e h i g h "qs' r e g i o n o f flight. The c o n t r o l system used was DMP w i t h a c c e l e r o m e t e r f e e d b a c k , f o r a n a t u r a l f r e q u e n c y r a n g e o f .O5 t o . 3 and damping r a t i o s f - 5 and .7. The bending moments were d e t e r m i n e d f o r e a c h c a s e t o i n v e s t i g a t e t h e e f f e c t o f t h e c o n t r o l f r e q u e n c y . T h i s s t u d y i s 9 5 p e r c e n t complete. 2. Saturn BB/~entaur a. A s t u d y t o d e t e r m i n e c o n t r o l r e s p o n s e s and b e n d i n g moments t o c o v e r time p o i n t s o v e r t h e f i r s t s t a g e f l i g h t h a s been documented. These d a t a , i n c o n j u n c t i o n w i t h t h e d a t a p r e v i o u s l y p u b l i s h e d f o r t h e c r i t i c a l t i m e p o i n t s , w i l l be used t o d e t e r m i n e e n v e l o p e s o f t h e r e s p o n s e s , T h i s w i l l t e r m i n a t e t h e Centaur e f f o r t . �b. The r e s u l t s of t h e S a t u r n ~ ~ / ~ e n t ai nus u r l a t i o n panels s e p a r a t i o n s t u d y a r e b e i n g documented. 3. Saturn V The c o u p l i n g of h i g h e r modes w i t h t h e r i g i d body p i t c h and d r i f t mode i s being i n v e s t i g a t e d t o determine t h e g a i n s r e q u i r e d t o m a i n t a i n a g i v e n frequency, damping and d r i f t r o o t l o c a t i o n a s h i g h e r modes a r e included i n t h e system. The modes t o be added f i r s t a r e t h e engine, low frequency s l o s h , and t h e f i r s t bending modes. P r e s e n t l y , e i g h t d i f f e r e n t combinations of t h e s e modes have been c a t e g o r i z e d , r a n g i n g from a t h i r d - o r d e r system ( r i g i d body p i t c h and d r i f t modes) t o a n i n t h o r d e r system ( p i t c h , d r i f t , s l o s h , and one The numerator and bending mode w i t h second-order engine dynamicsj,:' denominator pslynomiaks f o r t h e s e e i g h t systems have been o b t a i n e d . Data a r e being p r e p a r e d t o o b t a i n t h e t r a n s f e r f u n c t i o n s from s e n s o r o u t p u t t o engine command. 4. General a. The t r a j e c t o r y , mass bending, s l o s h and aerodynamic d a t a were t r a n s m i t t e d t o Lockheed on November 1 0 t h f o r t h e i r s t u d y , "A Nonlinear slender-body-theory aerodynamic F i l t e r f o r High Frequency Cutoff. "'he c o e f f i c i e n t s a r e being o b t a i n e d . b e The s t u d y of r e a c t i o n j e t c o n t r o l f o r t h e r e c o v e r a b l e S-IC b o o s t e r d u r i n g r e e n t r y i s being r e v i s e d and extended. Newer, more r e l i a b l e aerodynamic d a t a a r e being used t o c a l c u l a t e t h e v e h i c l e parame t e r s f o r t h e forthcoming analog s i m u l a t i o n . Analog computation procedures have been i n i t i a t e d , and t h e programming i s being checked f o r c o r r e c t n e s s . c. F l i g h t s i m u l a t i o n s have been made t o p l o t time t r a c e s of t h e S - I 1 s t a g e gimbal a n g l e over a ten-second p e r i o d f o l l o w i n g f i r s t stage separation ( f i r s t plane). The t r a c e s were r e q u e s t e d by R-P&VE-PTE f o r use i n engine h e a t i n g c a l c u l a t i o n s . The s i m u l a t i o n s a r e being documented. d. The S-IC s t a g e t r a n s i e n t s r e s u l t i n g from an engine f a i l u r e near c u t o f f a r e b e i n g reexamined w i t h r e v i s e d c o n t r o l system data. P r e l i m i n a r y r e s u l t s i n d i c a t e t h a t t h e t r a n s i e n t s w i l l be s i g n i f i Another memo w i l l c a n t l y lower t h a n t h o s e pub1 ished i n R-AERO-DCC-34-65. be i s s u e d t o r e f l e c t t h e change. e. The program t o a p p l y q u a d r a t i c c o s t c o n t r o l , Kalman f i l t e r i n g , and parameter e s t i m a t i o n techniques t o a f l e x i b l e v e h i c l e i s w e l l underway, S u c c e s s f u l o p e r a t i o n o f t h e Automatic S y n t h e s i s Program was achieved. T h i s program was chosen f o r mechanization and s e v e r a l Several o t h e r computer problems a s s o c i a t e d " w i t h ' i t s use were r e s o l v e d , �program a n a l y s i s t o o l s were a l s o p r e p a r e d . This work a s p r e s e n t e d i n t h e f o u r t h (October 1965) p r o g r e s s r e p o r t h a s b e e n c e n t e r e d a b o u t low o r d e r s y s t e m s u s e d a s b u i l d i n g b l o c k s toward more r e a l i s t i c c a s e s . f. The o b j e c t i v e o f t h i s c o n t r a c t f o r d e s i g n c r i t e r i a f o r space v e h i c l e d u r i n g t h e haunch p h a s e o f f l i g h t i s t o p r e p a r e a s e r i e s of monographs o n c o n t r o l and s t a b i l i t y f o r s p a c e l a u n c h v e h i c l e s . The f i r s t r e v i s e d monograph, VoZ. 11, P a r t 2 , "NonEinear S y s t e m s , " R e p o r t Noo GDC-DDE65-056, September I., 1965, h a s been r e c e i v e d . Personnel who a r e i n t e r e s t e d i n t h i s monograph sh?uld c o n t a c t W-AERO-DCA, 876-6917. The rough d r a f t mo~.ograph, V a l . I, P a r t 1, "Short P e r i o d D y n a m i c s , ' 2 a s b e e n reviewed b u t h a s n e t been. r e t u r n e d t o GI)/@. g. Optimum u t i l f z a t i e n , i n t h e RTAS program, 0% t h e t a p e r e a d - a n d - w r i t e pro.jced,~resd i d n o t z e d u c e t b e c 3mputer time s u f f l c i e n t l y Do a l l o w the product lo^ of t h e l a r g e mmber o f r u n s n e c e s s a r y , The system w i l l t h e r e f o r e be s i m p l i f i e d . by removing khe e n g i n e compliance Parallel e q u a t i o n s ; hopefuEly, k h g e w i l l r e d u c e t h e r u n n i n g t i m e . e f f o r t s a r e b e i n g made t e a d a p t a n c t h e r p r o g r a n EOP use i n t h i s s t u d y . 5, Contractors (1) The a n a l y s i s o f t h e AS-203 v e h i c l e s i s r e v e a l i n g few e n g i n e - o u t c a p a b i l i t i e s s f t h i s v e h i c l e because o f t h e l a r g e gimbal a n g l e s r e q u i r e d even f o r t h e nonma1functioning v e h i c l e i n r e s p o n s e t o t h e 95 p e r c e n t d e s i g n winds and t h e l a r g e u n c e r t a i n t i e s i n t h e aerodynamics. begun. (2) Engine-out a n a l y s e s on t h e AS-284 v e h i c l e have Many of t h e r e q u i r e d e n g i n e - o u t t r a j e c t o r i e s have been g e n e r a t e d . ( 3 ) Check-out r u n s on t h e 6D computer program m o d i f i c a t i o n s t o employ c o n t r o l f i l t e r s and n o n l i n e a r aerodynamics are i n progress. Use s f t h e m o d i f i c a t i o n s w i l l b e g i n s h o r t l y , ( 4 ) A s t u d y i s b e i n g made t o d e t e r m i n e t h e d i f f e r e n c e s i n t h e r i g i d body c o n t r o l v a r i a b l e s i n r e s p o n s e t o d e s i g n winds w i t h c o n t r o l f i l t e r s and a c t u a t o r l i m i t s and dynamics i n c l u d e d i n t h e simul a t i o n , a s compared t o s i m i l a r r e s p o n s e s when t h e f i l t e r s and a c t u a t o r dynamics a r e o m i t t e d . A l l d a t a n e c e s s a r y f o r t h e s t u d y have been f u r n i s h e d by MSFC. (5) F l e x i b l e body l o a d s were i n v e s t i g a t e d f o r t h e S a t u r n I B , 201 v e h i c l e u s i n g d e t a i l e d wind p r o f i l e s . Four winds measured w i t h t h e FPS-16 r a d a r / J i m s p h e r e were used f o r t h e a n a l y s i s . me winds o f J a n u a r y 12 ( T e s t No. 0866) and February 1 2 ( T e s t No. 0982) had h i g h �s h e a r s and r e l a t i v e l y Low wfnd speeds; t h e winds of March 9 , 1965 and These s t u d i e s were January 27 had high wind speeds and 1i.w wfnd s h e a r s . done i n c o n j u n c t i o n w i t h f l u t t e r s t u d i e s by D r . P l a t z e r . The s t u d y on ''A Nonlinear F i l t e r f o r High Frequency Gutoffto i s t o e x p l c f t t h e Lockheed GgeveBaped n o n l i n e a r f i l t e r f o r s u p p r e s s i o n n f unwanted f l e x i b l e feedback s i g n a l s i n t h e c o n t r o l loop During t h e f i r s t r e p o r t i n g p e r i o d , p r o g r e s s of the S a t u r n type v e h i c l e . was made i n determining l i n e a r network c h a r a c t e r i s t f c s r e q u i r e d f o r To r e a l i z e smooth passage e f f i c i e n t o p e r a t i e n of t h e n o n l i n e a r f i l t e r . s f a s i g n a l w i t h frequency below the f i l t e r c u t o f f , i t was a s c e r t a i n e d from a n a l y s i s and analog computer r u n s t h a t m u l t i p l e high frequency No s i g n a l s must undergo a s p e c i f i c p a t t e r n o f k i n e a r a t t e n u a t i o n . d i f f i c u l t y i s expected i n determining the law frequency phase and g a i n e f f e c t s of sampling and h y s t e r e s i s . c. Missi,3n S u p p o r t 98) Seqding and Sl3sbing A n a l y s i s , S a t u r n HB Vehicle, AS-233 B ~ o s t e rF l i g h t This study i s to determine t h e s t a b i l i t y requirements f o r t h e AS-203 f a r t h e f i r s t s t a g e o f f l i g h t . The f o l l o w i n g t a s k s have been completed. (2) (a) C:ai,n s e l e c t i o n and f i l t e r d e s i g n f a r gyro c o n t r o l a t t h e 140-second time p o i n t and f o r aft-mounted accelerometer c o n t r o l a t t h e 68-second and 80-second time p o i n t s . (b) S t a b i l i t y of the upper bending modes v e r i f i e d f o r t h e s e c a s e s , and a frequency r e s p o n s e a n a l y s i s completed f o r a l l c a s e s of gyro c a n t r o l and f o r t h e 60- and 80 second time p o i n t s wi.th t h e aft-mounted a c c e l e r o m e t e r . (c) Design of t h e accelerometer f i l t e r and loop f i l t e r i n i t i a t e d f o r t h e forward-mounted accelerometer cases. (d) Wark conti.nued on s e t t i n g up t h e f l e x i b l e body t r a n s i e n t response program. " K t i l i z a t i s n of V e l o c i t y Feedback From P l a t f o n n Mounted Accelerometer for Control of S a t u r n V LOR" An e f f o r t i s being made t o determine t h e l i m i t a t i o n s and problems encountered i n u s i n g v e l o c i t y feedback from a platform-mounted �accelerometer f o r c o n t r o l and load r e d u c t i o n . The v e l o c i t y feedback appears o n l y moderately e f f e c t i v e i n reducing bending moments w i t h o u t a d d i t i o n a l compensation. An a n a l y s i s of q u a n t i z a t i o n e r r o r s from sampling has begun. (3) Study t o Reduce Bending Moments v i a Control System Design The o b j e c t i v e f o r t h i s t a s k i s t o d e s i g n a c o n t r o l l e r t h a t w i l l minimize t h e i n t e g r a l of l a t e r a l v e l o c i t y r a i s e d t o an even power p l u s a q u a d r a t i c i n c o n t r o l e f f o r t . The c o n t r o l l e r has been o b t a i n e d a s a f u n c t i o n of time. Synthesizing t h e c c n t r o l l e r a s a f u n c t i o n of s t a t e v a r i a b l e s has c o n t i n u e d , w i t h c r o s s p r o d u c t s of t h e s t a t e v a r i a b l e s i n c l u d e d , by u s i n g a c u r v e - f i t t i n g procedure. A memorandum d e s c r i b i n g t h e r e s u l t s t o d a t e i s being w r i t t e n . (49 S t u d y t o Reduce Wending Moments v i a Control System Design, Variable C o e f f i c i e n t Case The o b j e c t i v e o f t h i s strmdy i s t o determine t h e degree of s u c c e s s which can be s b t a i n e d by using modern c o n t r o l t e c h n i q u e s t o d e s i g n a c o n t r o l system which w i l l reduce bending moments. Kalman f i l t e r t e c h n i q u e s a r e being used t o design a l i n e a r c o n t r o l system w i t h feedforward and feedback loops. (5) Nonlinear Accelerometer f o r Load R e l i e f The o b j e c t i v e of t h i s t a s k i s t o determine t h e bending moment r e d u c t i o n o b t a i n a b l e through t h e use of a n o n l i n e a r element i n t h e accelerometer feedback. Rigid body t r a j e c t o r y runs over t h e time of b o o s t e r f l i g h t were made w i t h t h e n o n l i n e a r a c c e l e r o m e t e r feedback added t o t h e b a s i c a t t i t u d e c o n t r s P L e ~ . The bending moments o b t a i n e d by a t t i t u d e c o n t r o l o n l y were compared w i t h t h o s e o b t a i n e d by adding a l i m i t e d accelerometer feedback--the Load r e d u c t i o n was approximately 43 p e r c e n t . A f i n a l r e p o r t i n d r a f t form bas been r e c e i v e d , but has n o t y e t been reviewed. (6) Generati.on o f a Graphical. o r Analytfcal. Formulation s f Peak Vehicle Responses The o b j e c t i v e o f t h i s s t u d y i s t o determine a g e n e r a l method f o r p r e d i c t i n g maximum v e h i c l e r e s p o n s e v a l u e s . After reviewing t h e summary o f work t o d a t e , i t was concluded t h a t t h e formulas f o r computing maximum v a l u e s , a l t h o u g h c o r r e c t , were n o t i n t h e d e s i r e d form a s a f u n c t i o n s f p h y s i c a l v e h i c l e parameters. A d d i t i o n a l work w i l l be n e c e s s a r y t o complete t h i s p r o j e c t . E v a l u a t i o n of t h e s e n s i t i v i t y s f t h e c o n t r o l law (7) t o changes i n t h e wind p r o f i l e and o f t h e weighting terms i n t h e q u a d r a t i c c r i t e r i o n w i l l be continued. �(8) The m o d i f i c a t i a n s to t h e B-2 Gape Deck t o i n c l u d e f i l t e r e q u a t i o n s and s t h e r v a r i a t i o n s needed f o r c c n t r o l s t u d i e s h a s been p u b l i s h e d i n L2ekbeed d~czament$) TM-5G-30-71, C. Dynamics AnaPys%s S r a n c h 1. Saturn HB a. The s l o s h model p a r a m e t e r s for AS-205 have been d e t e r m i n e d and a p r e l i m i n a r y copy cf t h e r e s u l t s g i v e n t o R-ASTR-P, f u l . f i l P i n g a s c h e d u l e a g r e e d upon by R-AERO-D an1 R-ASTR-F. b. A memsras-ndum has been d i s t r i b u t e d g i v i n g t h e r e s u l t s o f a bending a n a l y s i s o f AS-205 f i r s t - s t a g e f l i g h t . A mema p r e s e 9 t f " ~ gt h e r e s u l t s sf a bendixg a n a l y s i s s f t h e S a t u r n ~ ~ / ~ e a k af dur w r t % B i g h t s t a g e has E e e ~f s s u e d , 3. S a t u r n t' (1) Tasks t n a s s e s s t h e f i n a l c o n t r n l system d e s i g n f o r t h e S-EG, S - P I , and S-JV3 s t a g e s of t h e AS-SO1 v e h i c l e have been g i v e n Eng%ne o u t , d e t a i l wind p r o f i l e s and g u s t p e n e t r a t i o n a r e t o t o Bseing. be i n c l u d e d . ( 2 ) A c ~ n p a r i s 2 ncf t h e s t a b i l i t y c h a r a c t e r i s t i c s o f t h e v a r i o u s proposed c o n t r o l systems f o r t h e AS-501 s p a c e v e h i c l e h a s been c c n c l u d e d , w i t h a r o u g h d r a f t s f t h e r e p 2 r t a b o u t t w c - t h i r d s esmp l e t e d . (31 A r i g i d bedy t h r e e - d i m c n s i o n a l sirnuPation of t h e AS-501 s p a c e v e h i c l e u s i r l g t b nonlinear, ~ r 7 t a r y s l c s h mcdel d e v e l o p e d by D r . Bauer i s be-irlg s e t up on t h e a a n l s g computer. The e f f e c t o f t h e n o n l i n e a r s l o s h model the S a t u r n 19 r e s p c n s e w E l l be s t u d i e d . ~ j n ('1) A bend%.ng arialbysfs S~zmr AS-50.4 was completed and s e n t t o Bqeing f o r use in c ' n t r ~ Petud%es. ( 2 ) Four e a s e s of t h e r i g i d r e s p o n s e d a t a g e n e r a t e d f o r s t r u c t u r a l l o a d s f a r AS-504 a r e b e i x g compared. Tki,,e e a s e s c o n s i d e r e d are i d e a l e c n t r o E , a t t i t u d e o n l y , and d r i f t minimum c o n t r o l , u s i n g t h e s y n t h e t i c wind p r o f i l e s t a r t i n g a t t h e grqund and a t some i n i t i a l altitude. The v a r i s n s p a r a m e t e r v a r i a t i o n s w i l l be c o n s i d e r e d i n e a c h c a s e a d t h e RSS bendiqg rnGment determined. �c, AS-504, 505 and 506 S l o s h i n g Data The s l o s h model p a r a m e t e r s (mass, f r e q . ) a r e b e i n g c a l c u l a t e d f o r AS-504, 505 and 506 v e h i c l e s , The a r b i t r a r y shaped t a n k program i s b e i n g u s e d , d. D e t a i l e d Wind Study The wind r e s p o n s e s t u d i e s f o r S a t u r n V v e h i c l e u s i n g t h e h i g h speed a n a l o g a r e p r o g r e s s i n g . Various c o n t r o l s y s t e m s a r e being i n v e s t i g a t e d . The winds e x c e e d i n g t h e 95 p e r c e n t l e v e l o n bending moment have b e e n i s o l a t e d f o r i d e a l g y r o c o n t r o l law and a r e ( I ) winds being studied. Several interesting d e t a i l s are noticed: w i t h v e r y s m a l l m a g n i t u d e u n t i l around 10 k i l t m e t e r s t h e n p o s s e s s i n g l a r g e s h e a r s (wind speed change o f 45 m/sec i n 2080 m), b u t o n l y a v e r a g e peak wind magnitude (50 m / s e c ) , cause exceedances o n t h e bending moment; ( 2 ) nominal wind s h e a r s (wind speed change of 20 m/sec i n 9000 ma w i t h l a r g e wind magnitude (above 80 rn/see) a l s o c a u s e exceedances. This is v e r y i n t e r e s t i n g when compared w i t h t h e two s y n t h e t i c wfnd p r o f i l e s used, one s t a r t i n g a t t h e ground and t h e o t h e r a t some a l t i t u d e ( 7 km). The r e s u l t s show a p p r o x i m a t e l y 2 exceedances c u t o f 200 winds i n c a s e one and a p p r s x h a t e l y 4 o u t o f 200 i n c a s e two. The 200 winds used a r e t h e Jimsphere prof i l e s f o r t h i s year. 4. General a. Zero ''GR': The s u p p o r t work f o r t h e low 'kg"' drop t e s t is continuing. Some problems e x p e r i e n c e d i n t h e d r o p mechanism have been i s o l a t e d . C o r r e c t i o n s a r e b e i n g made, and t e s t s s h o u l d b e g i n i n a b o u t 2 weeks. T e s t s w i l l cover t h e i n i t i a l s l o s h problem p l u s r e s p o n s e t o impulse under low 'kg'',Tanks w i t h and w i t h o u t b a f f l e s w i l l be t e s t e d . b. Damping S t u d i e s : A l l v i b r a t i o n t e s t i n g o f t h e l / 5 s c a l e A detailed final t e s t model was completed d u r i n g t h e r e p o r t i n g p e r i o d . r e p o r t i s being prepared, c. Data Tape: The g e n e r a l i z e d aerodynamic f o r c e c o e f f i c i e n t program u s i n g t h e b e n d i n g mode t a p e a s i n p u t t o t h e d a t a t a p e h a s been checked o u t , and h a s b e e n t u r n e d o v e r t o th.e p r o d u c t i o n u n i t i n t h e Comp Lab. d. C o n t r o l Gains w i t h F i l t e r s : A p r o c e d u r e f o r c a l c u l a t i n g t h e c o n t r o l g a i n s w i t h f i l t e r s f o r a r i g i d v e h i c l e h a s been c o m p l e t e d , This r e p o r t shows t h e e f f e c t i n t h e and a r e p o r t i s b e i n g p r e p a r e d , c o n t r o l g a i n s o f v a r y i n g t h e l o c a t i o n of t h e a c c e l e r o m e t e r , t h e damping, a n d t h e c o n t r o l f r e q u e n c y f o r t h e c a s e w i t h o u t f i l t e r s and u s i n g v a r i o u s f i l t e r configurations. Some g r a p h s a r e a l s o i n c l u d e d which show how t h e c o n t r o l g a i n s v a r y w i t h time. . �hbrk i s proceeding i n a s t u d y t o c a l c u l a t e t h e c o n t r o l g a i n s w i t h f i l t e r s t h a t i n c l u d e s t h e bending v i b r a t i o n of t h e v e h i c l e . . Four modes s f v i b r a t i o n a r e included i n t h e a n a l y s i s ; t h e s e e q u a t i o n s of motion a r e now being solved, e. Progress Development (5-D Hybrid Simulat i o n ) : Development of e q u a t i o n s f o r a h y b r i d computer c o n t r o l t r a j e c t o r y s i m u l a t i o n i n c l u d i n g 5 r i g i d body degrees o f freedom and 4 e l a s t i c body modes i n each of p i t c h P r o g r a m i n g of t h e e q u a t i o n s w i l l and yaw p l a n e s 1 s n e a r completion. begin soon. f. Comparison of Bending Frequencies from t h e Dynamic Test t o F l i g h t : An i n t e r n a l n o t e was published showing t h e cause of frequency d i f f e r e n c e between c a l c u l a t e d normal modes and measured f l i g h t frequenc ies. g. Gust P e n e t r a t i o n : A s i m p l i f i e d e l a s t i c body r e s p o n s e program, which c o n s i d e r s t h e e f f e c t s of g u s t p e n e t r a t i o n i n both r i g i d body and e l a s t i e body r e s p o n s e s , i s being checked o u t . The deck should be i n p r o d u c t i ~ nby next month. 5. Contractors a. Boeing A r e p o r t of t h e work done on load r e l i e f schemes f o r Saturn V v e h i c l e s was r e c e i v e d t h i s week. A f t e r t h i s work i s reviewed, a r e p o r t w i l l be d i s t r i b u t e d . Recent s t u d i e s showed a p o s s i b l e i n s t a b i l i t y i n t h e S-I1 and S-IT5 hydrogen t a n k s u s i n g the s l o s h damping p u b l i s h e d i n R-AERO-DDThe problem i s b e i n g a s s e s s e d by , f i r s t , r e e v a l u a t i n g t h e damping 20-65. v a l u e s p u b l i s h e d i n DD-20-65 and, second, conducting response and s t a b i l i t y s t u d i e s t o determine .the e x t e n t of t h e problem. The problem does n o t now seem a s s e v e r e a s f i r s t a n t i c i p a t e d and probably w i l l not require redesign of baffles. b, General E l e c t r i c The six-degrees-of-freedom d i g i t a l c o n t r o l t r a j e c t o r y s i m u l a t i o n program i n c l u d i n g n o n i d e a l c o n t r o l system under development has now g e n e r a t e d a nominal t r a j e c t o r y . This f i r s t phase of t h e development i s being documented, and minor m o d i f i c a t i o n s a r e being made. c. North American Dynamic t e s t i n g o f AS-501 ( c o n f i g u r a t i o n 111) has been completed. S t r u c t u r a l f a i l u r e occurred i n t h e i n t e r f a c e between t h e s e r v i c e module and command module. The cause and time of f a i l u r e a r e being i n v e s t i g a t e d . �d. Northrop Work i s c o n t i n u i n g on t h e f i l t e r s y n t h e s i s problem. A study i s being made t o determine u s a b l e f i l t e r s f o r S a t u r n 501 u s i n g p o s i t i o n and r a t e gyros. The i n i t i a l study t o determine requirements The f i r s t r u n s t o g e t t h e and t h e v e r i f i c a t i o n w i l l be done in-house. requirements have j u s t been completed. (1) During t h e r e p o r t p e r i o d , a computer program was w r i t t e n which computes the n a t u r a l f r e q u e n c i e s o f a space v e h i c l e This program i s now being checked undergoing nonplanar o s c i l l a t i o n s . o u t on two t e s t problems where s o l u t i o n s a r e known. ( 2 ) A procedure for o b t a i n i n g t h e r o o t s of n o n l i n e a r a l g e b r a i c e q u a t i o n s i s b e i n g developed. A program t h a t works w e l l has been checked o u t , and i s being documented. ( 3 ) Data a n a l y s e s d u r i n g t h i s p e r i o d included t h e r e d u c t i o n o f v i b r a t i o n decay r e c o r d f o r each mode and f u e l c o n d i t i o n s from s e v e r a l f o r c i n g a m p l i t u d e s , t h e c a l c u l a t i o n of damping from decay r e c o r d s , frequency s h i f t s due t o added w e i g h t , and t h e a c c u r a t e p l o t t i n g of v i b r a t i o n mode shapes, (4) An approach t o i n c o r p o r a t e s t r u c t u r a l damping i n a mathematical model of space v e h i c l e s has been e s t a b l i s h e d . (5) The e q u a t i o n s governing t h e v i b r a t o r y motion of t h e e l a s t i c tank and t h e f l u i d contained i n t h e tank were d e r i v e d . Work i s b e i n g done t o s o l v e t h e s e e q u a t i o n s by expanding t h e s h e l l displacement components and t h e f l u i d p o t e n t i a l i n a s e r i e s form. f. Hayes Nonlinear s t r u c t u r a l feedback i n b o o s t e r c o n t r o l . The number o f approximate techniques being i n v e s t i g a t e d f a r p o s s i b l e use i n t h e " a n a l y t i c a l model'' has been i n c r e a s e d t o f o u r d u r i n g t h i s r e p o r t period. These approximate techniques have been c a t e g o r i z e d a s f o l l o w s : ( I ) F i n i t e d i f f e r e n c e e q u a t i o n s der ived from t h e p a r t i a l d i f f e r e n t i a l e q u a t i o n of beam l a t e r a l v i b r a t i o n . ( 2 ) F i n i t e difference d i f f e r e n t i a l derived d i r e c t l y from v a r i o u s lumped parameter models of a continuous beam. ( 3 ) D i f f e r e n t i a l . e q u a t i o n s d e r i v e d from t h e p a r t i a l d i f f e r e n t i a l e q u a t i o n of beam v i b r a t i o n s by u s i n g G a l e r k i n ' s Method (modal t y p e s o l u t i o n ) . �( 4 ) F i n i t e d i f f e r e n c e d i f f e r e n t i a l equations obtained from e i t h e r a p a r t i a l d i f f e r e n t i a l e q u a t i o n o r a lumped parameter model by u s i n g d i f f e r e n c e approximaticns t o d e r i v a t i v e s based on e i t h e r Chrysler o r F o u r i e r s e r i e s approximation of t h e d e f l e c t i o n curve. Work i s i n p r o g r e s s on a l l four c a t e g o r i e s . D. Advanced P r o j e c t s S t u d y Branch 1. S-HVB Workshop P r e l i m i n a r y payload and l i f e t i m e spectrums have been generated f o r t h e S-H'~Bworkshop concept. P r e s e n t l y , t h e primary m i s s i o n i s t h e kh-day d i r e c t i n j e c t i o n . Secondary m i s s i o n s a r e t h e 45-day workshop and the a r t i f i c i a l g r a v i t y experiment. P r e l i m i n a r y c o n t r o l s t u d i e s an t h e a r t f f f c i a l experiment have been c o o r d i n a t e d w i t h R-AEWB-PO and R-ASTR-VD. S t u d i e s have been i n i t i a t e d i n R-ASTR and R-P&VE, a t t h e r e q u e s t 0 % R-AERO, t o i n v e s t i g a t e the removal ?r swing-back of LEM shroud p a n e l s . Docking problems, e ~ m u xcfa t i o n s and t o r q u i n g c o n t r o l w i l l be s t u d i e d . 2. Voyager Performance has been analyzed i n support of t h e Voyager progect f o r t h r e e v e h i c l e c o n f i g u r a t i o n s : t h e Saturn V, t h e S a t u r n IB/'Q" s t a g e c o n f i g u r a t i o n , and t h e S a t u r n ~ ~ / ~ e l t a u Ar .memorandum c o n t a i n i n g the r e s u l t s wi13 be i s s u e d . A d d i t i o n a l c c n f i g u r a t i o n work i s being done to i s o l a t e a v e h i c l e which w i l l y i e l d 25,008 I b s n e t payload a t Cg = 25. This c o n f i g u r a t i o n would be a S a t u r n IB backup t o t h e S a t u r n V Voyager. An ApoPEo a p p l i c a t i o n a n a l y s i s i s being conducted t o f i n d an a c c e p t a b l e minimum m o d i f i c a t i o n m i s s i o n p r o f i l e f o r t h e synchronous A t p r e s e n t i t appears t h a t t h e 3-burn S-IVB a l t i t u d e o r b i t mission. p r o f i l e i s o u t because of t h e e x t e n s i v e S-HW m o d i f i c a t i o n . The two-stage Saturn V t o t h e 100 nm parking o r b i t w i t h t h e S-BW i g n i t e d t w i c e , once i n t h e p a r k i n g o r b i t and once a t synchronous apogee, may be o u t because of the p r e s s u r i z a t i o n problem. It appears t h a t a new s k i n p a n e l w i t h helium b o t t l e hangers may have t o be i n s t a l l e d ; t h i s would n o t be a l l o w a b l e f o r t h e e a r l y a l t e r n a t e m i s s i o n concept. The p r e s e n t a n a l y s i s i s concerned w i t h f i n d i n g a p r o f f l e t h a t w i l l f a l l w i t h i n the S-ICVB ApoPlo p r o p e l l a n t budget . 4. Manned Mars and Venus Flyby Study A r e p r e s e n t a t i v e Venus f l y b y t r a j e c t o r y f o r t h e 1975 c o n j u n c t i o n has been computed and i s b e i n g documented. �Work s t a t e m e n t s f o r t h e $600,000 f l y b y s t u d i e s all.otment have been forwarded t o NASA Headquarters. It i s a n t i c i p a t e d t h a t t h e t o t a l sum w i l l be d i v i d e d i n t o t h r e e a r e a s when RFP'S a r e i s s u e d . R-AERO-DP was r e p r e s e n t e d a t a s t u d y review concerning h i g h speed e a r t h e n t r y h e l d a t Ames Research Center on November 16. The review was conducted by Lockheed, Sunnyvale, who had been awarded t h e c o n t r a c t by OART-MAD. En subsequent d i s c u s s i o n s both OAR% and Lockheed i n d i c a t e d t h a t t h e Apollo Command Module could be used f o r e n t r y speeds up t o 50,000 f t l s e c when t h e a p p r o p r i a t e amount s f h e a t s h i e l d i n g m a t e r i a l i s added. Lockheed, under c o n t r a c t t o MSC, i s concluding a s t u d y u s i n g t h e Apollo CN f o r h y p e r b o l i c e n t r y . 5. PRESTO Lockheed, Paho A l t o , has a c o n t r a c t w i t h Langley Research Center t o make c e r t a i n m o d i f i c a t i o n s and e x t e n s i o n s t o t h e t r a j e c t o r y program PRESTO. Langhey w i l l be c o n t a c t e d t o o b t a i n a c l e a r e r p i c t u r e of t h e s i t u a t i o n . 6. C o n t r a c t o r Support a. Northrop (1) Convergence: The convergence r o u t i n e has e s s e n t i a l l y been developed; t h e major p a r t of r e c e n t e f f o r t s i n t h i s a r e a has been d i v e r t e d t o a n a l y s i s of t h e 2-stage COV problem. Recent e f f o r t s have been d i r e c t e d toward f o r m u l a t i n g the problem i n a manner which, f o l l o w i n g a Denbow-type t r a n s f o r m a t i o n , y i e l d s an e q u i v a l e n t probl.em i n t h e c l a s s of problems f o r which t h e maximum p r i n c i . p l e i s a p p l i c a b l e . ( 2 ) Reentry: Phase 1 of t h e i n v e s t i g a t i o n s f r e e n t r y t r a j e c t o r i e s has j u s t been completed, t h e r e s u l t s of which a r e documented i n Technical Memo No. 138. It has been concluded from Phase I t h a t a b u i l d i n g block approach t o t h e r e e n t r y problem should. be undertaken; t h i s i s now underway. (3) Low Thrust: Phase I of t h i s t a s k i s being documented. As a r e s u l t of Phase I, i t has been concluded t h a t w h i l e t h e h e l i o c e n t r i c phase of low t h r u s t has been g i v e n c o n s i d e r a b l e a t t e n t i o n , t h e e a r t h escape and c a p t u r e phases have not. The problem of escape under l o w - t h r u s t a c c e l e r a t i o n w i l l now be s t u d i e d i n d e t a i l . (4) Location o f Lander Probes f o r Maximum Comrnunicati.on Time: T h i s t a s k should be completed d u r i n g t h e coming month. R e s u l t s of launching l a n d e r probes t o Mars from manned f l y b y v e h i c l e s i n d i c a t e t h e following: ( a ) S e p a r a t i o n from f l y b y v e h i c l e must t a k e p l a c e a t extreme distances. ( b ) Guidance requi.rements f o r e n t e r i n g M a r t i a n atmosphere �a r e extremely sensiti-ve. (c) Very l a r g e r e t r o A V ' S a r e n e c e s s a r y . ( d ) Communication time between l a n d e r probe and f l y b y v e h i c l e i s v e r y limited a t best. These r e s a l t s were i n s t r u m e n t a l in e l i m i n a t i n g from MSFC c o n s i d e r a t i o n t h e Eawnching @I l a n d e r p r o b e s from t h e f l y b y v e h i c l e s f o r t h e in-house f l y b y s t u d y . (5) N s r t h r o p i s making a p a r a m e t r i c a n a l y s i s o f g e o c e n t r i c c o a s t i n g o r b i t c h a r a c t e r i s t i c s and launch r e q u i r e m e n t s f o r t h e proposed Voyager m b s s f ~ n s . Thfe t a s k is i n s u p p o r t o f JPL'S r e q u e s t f o r S a t u r n V l a u n c h vehFePes f o r t h e Vcyager s p a c e c r a f t , R e s u l t s a r e e x p e c t e d i n t h r e e weeks. Dnrbng October v e r y l i t t l e work was done on t h e Phase H I add-on e o n t r a c t b e c a u s e of : t h e r e o m i t m e n t ~o f t h e o p e r a t i n g p e r s o n n e l . A g r e a t deal ~ ) pf r L n g r e s swas -nade, however, toward f i n d i n g a t y p i c a l engle-af-att a c k p r @ ,if i e P ~ l pa.n a b c r t t r a j e c t o r y . m e t h e o r y t h a t 1 s borne c u t by some n u m e r i c a l i s t h a t e x t e r n s 1 a b o r t t r a j e c t 3 r l e s ( t ? the terninan. c c n d i t i o n s ~ i c c wirh ~r bank a . ~ g le s~s e n f , l a " r y z e r o . If i t were n o t for t h e e f f e c t s o f e a r t h r c l t a t i o n , t h e bdnk a n g l e would be e x a c t l y z e r o aborts. results used) minor on t h e T%-e r e s u l t s of t h e t a s k t a i n v e s t i g a t e powered f l y b y of Mars d u r i n g t h e 1918 a p p c s i t i o n have been documented i n Lockheed Technical Memo 54-30-69. "Hke p a r a m e t r i c s t u d y o f v a r i o u s o r b i t a l c o n d i t i o n s about Mars i s p r e e e e d f n g on s c h e d u l e and monographs p o r t r a y i n g t h e r e s u l t s a r e being constructed. L h e stud3 of m f d ~ o ~ r sr e q u i r e m e n t s f o r Mars and Venus f l y b y and Venus s w i r g b y qEssE2n.s i s j u s t g e t t i n g underway. 1% w i l l c c n s e r n i t s e l f w i t k t h e a n a l y s i s of t o t a l m i d e c u r s e ,5V r e q u i r e m e n t s and t h e Fncrementing o f t h i s t o t a l for t h e above t y p e s o f m i s s i o n s . W t h owboard g u i d a n c e and ground t r a c k i n g w i l l be c o n s i d e r e d . ?.I 1. A m e e t i n g o f cbe PEWC 0 ~ 7Sakuri-i 13 f l i g h t e v a l u a t i o n t t r % o n t a t i n na d p l a n n i n g h e l d o n b1:vember 39, 1965, a t MSFC i n c l u d e d p r e s e n t a t i : o s by CCSD, 3AC, Rocketdyne, and ISN o n p r e p a r a t i o n f o r t h e �f u t u r e S a t u r n IB f l i g h t e v a l u a t i o n e f f o r t . A l s o , MSFG r e p r e s e n t a t i v e s p r e s e n t e d t h e f u n c t i o n s and a c t i v i t i e s o f t h e FEWG d u r i n g t h e S a t u r n 16B program. 2. A f l i g h t t e s t e v a l u a t i o n p l a n f o r S a t u r n I B haunch v e h i c l e s AS-201 t h r o u g h AS-204 h a s been d i s t r i b u t e d t o a 1 1 members o f t h e F l i g h t E v a l u a t i o n Working Group. T h i s p l a n d e s c r i b e s f u n c t i o n s and r e s p o n s i b i l i t i e s assigned t o t h e v a r i o u s elements involved i n t h e evaluation. P r o c e d u r e s f o r d a t a h a n d l i n g , a n a l y s i s , and r e p o r t i n g a r e o u t l i n e d i n detail. T h i s p l a n w i l l be r e v i s e d a s r e q u i r e d t o r e f l e c t c h a n g e s , a d d i t i o n s o r d e l e t i o n s n e c e s s a r y t o encompass t h e e v a l u a t i o n o f AS-201, AS-202, AS-203 and AS-204. CCSD w i l l p u b l i s h a s i m i l a r p l a n b e f o r e f l i g h t t e s t o f AS-20.5. 3. The s e v e n t h m e e t i n g of t h e Plight E v a l u a t i o n P a n e l (FEP) was h e l d a t Kennedy Space C e n t e r , F l o r i d a , November 9-10, 1965, P l a n s and s c h e d u l e s fear A S - 2 0 1 / ~ ~ ~ - 0 0f l9i g h t e v a l u a t i o n were reviewed. P r e s e n t a t i a n s were made on t h e p r e l a u n c h wind m o n i t o r i n g program, planned AS-201 l a u n c h v e h f c l e and s p a c e c r a f t sequence o f e v e n t s , Apollo-Saturn PB p o s t f l i g h t guidance a n a l y s i s t e c h n i q u e s , and s p a c e v e h i c l e l i f t - o f f and i n f l i g h t w e i g h t e v a l u a t i o n t e c h n i q u e s a n d accuracies. R e p o r t s from t h e Data Exchange C o o r d i n a t i o n and P o s t f l i g h t T r a j e c t o r y Subpanels were h e a r d , a n d a t o u r o f AFETR Cape and KSC f a c i l i t i e s was made. The n e x t FEP m e e t i n g i s t e n t a t i v e l y s c h e d u l e d f o r MSC o n March 1 6 , 1965. B. P l i g h t E v a l u a t i o n Branch 1.. Saturn I The Pegasus o r b i t a l r o l l i n v e s t i g a t i o n was p u b l i s h e d a s T e c h n i c a l Report ~ R ~ ~ / 2 0 0 8 -e1n ,t i t l e d "Analysis of P e g a s u s Fuel Vent Impingement. " Work was performed by LMSC, Hunt s v i P l e , under Miss i o n Support C o n t r a c t NAS8-20082 Appendix C-1, S c h e d u l e Order 5. A n a l y t i c a l l y determined m o t i o n s a r e i n good agreement w i t h t e l e m e t e r e d r e s u l t s , s u p p o r t i n g t h e t h e o r y t h a t t h e r o l l i n g m o t i o n e x p e r i e n c e d by Pegasus was due t o impingement o f v e n t p r o p e l l a n t s upon t h e extended p a n e l s . 2. Saturn I B The l o n g i t u d i n a l t h r u s t s h a p e f o r t h e S-IV s t a g e of Black I1 v e h i c l e s was a d i f f i c u l t p a r a m e t e r t o d e t e r m i n e . Q u i t e o f t e n Douglas A i r c r a f t Company and P r a t t and Whitney c o u l d n o t a g r e e on t h e t r u e t h r u s t shape, a l t h o u g h t h e c h a r a c t e r i s t i c s h a p e o f t h e t h r u s t c u r v e was r a t h e r simple. The p r e d i c t e d l o n g i t u d i n a l t h r u s t f o r AS-201 S-IVB s t a g e c o n t a i n s l a r g e o s c i l l a t i o n s which a r e c a u s e d by '%built-in'" m i x t u r e r a t i o shifts. There a r e s t r o n g i n d i c a t i o n s t h a t , i f t h e S-HV s t a g e t h r u s t s h a p e was d i f f i c u l t t o d e t e r m i n e , t h e S-IVB s t a g e s w i l l be c o n s i d e r a b l y more difficult. �To o b t a i n a r e l i a b l e s o l u t i o n and t o match t h e observed t r a j e c t o r y through t h e use of t h e F l i g h t Simulation Method, i t i s necessary t h a t t h e t r u e t h r u s t shape be known. Therefore, a f e a s i b i l i t y study i s underway f o r computing t h e t h r u s t shape u s i n g measured l o n g i t u d i n a l a c c e l e r a t i o n , an i n i t i a l mass (which may be i n e r r o r ) , and t h e flow r a t e (which w i l . 1 have t h e c o r r e c t shape, b u t may have l e v e l s h i f t s ) . 3. Saturn V An ana l y s i s performed t o d e t e r m i n e t r a c k i n g requirements f o r AS-501. A s i m p l i f i e d method was used t o a s c e r t a i n how many guidance e r r o r s could be s e p a r a t e d i f t h e d e v i a t i o n ( t r a c k i n g minus t e l e m e t e r e d guidance) i n v e l o c i t y components amounts t o a p a r t i c u l a r v a l u e a t S-EVL( c u t a f f. The f i r s t s t e p was t o compute t h e v a r i o u s i n d i v i d u a l guidance e r r o r terms n e c e s s a r y tc~account f o r t h e t o t a l d e v i a t i o n a t S-HVB c u t o f f . A t r a c e was made throughout t h e f l i g h t of t h e s e i n d i v i d u a l e r r o r terms, The next s t e p was t o d i f f e r e n c e each of t h e t r a c e s w i t h every o t h e r t r a c e u n t i l a l l csmbfnaticns had been made, S i x t y - s i x d i f f e r e n c e curves were e s t a b l i s h e d . T3 s e p a r a t e o r d i s t i n g u i s h one e r r o r from a n o t h e r , t r a c k i n g a c c u r a c i e s would have t o be about h a l f a s l a r g e a s t h e d i f f e r e n c e between any two e r r o r c o n t r i b u t i o n s . To i l l u s t r a t e t h i s f u r t h e r , i f t r a c k i n g a c c u r a c i e s o f 2.0 m/s ( i n v e l o c i t y components) a r e a v a i l a b l e , 33 p e r c e n t of the guidance e r r o r s can be d i s t i n g u i s h e d i f t h e d e v i a t i o n a t S-IVB c u t o f f i s 10 m/s. Tf t h e d e v i a t i o n a t S-TVB c u t o f f i s 20 m/s, 64 p e r c e n t s f t h e e r r o r s can be d i s t i n g u i s h e d . 4. Contracts a. Saturn IB System C o n t r a c t (CCSD, New O r l e a n s ) CCSD i s c o n t i n u i n g t o develop t h e c a p a b i l i t y t o e s t a b l i s h a postflight trajectory. They have processed t h e SA-10 t r a c k i n g d a t a and soon w i l l i s s u e a t r a j e c t o r y r e p o r t t o demonstrate t h e a b i l i t y t o use t h e s e t r a j e c t o r y programs e f f e c t i v e l y . It has been decided t h a t CCSD w i l l assume r e s p o n s f b i l i % y f o r t h e i n t e r m e d i a t e t r a j e c t o r y ( 7 days a f t e r launch) and t h e f i n a l t r a j e c t o r y (14 days a f t e r launch) beginning w i t h SA-203. The r e s p o n s i b i l i t y f o r the 24-hour t r a j e c t o r y w i l l remain wFth MSPC f o r t h e e n t i r e S a t u r n I B s e r i e s because of d a t a d e l i v e r y problems. b. S a t u r n V Systems C o n t r a c t (The Boeing Company) The A e r o b a E l i s t i c s Unit of The Boeing Company i s scheduled t o assume the r e s p o n s i b i l i t y f o r the p o s t f l i g h t t r a j e c t o r y commencing w i t h AS-585, Two work assignments were i n i t i a t e d which w i l l h e l p Eoeing develop t h e c a p a b i l i t y t o e s t a b l i s h a p o s t f l i g h t t r a j e c t o r y . The f i r s t work assignment (number R - A E R O - ~ ~ 1 e5 n) t i t l e d "Booster Free �F l i g h t T r a j e c t o r y f s r e q u i r e s Boeing t o develop a computer program which w i l l be used t o e s t a b l i s h t h e t r a j e c t o r i e s f o r t h e d i s c a r d e d S-IC and S-I1 s t a g e s . T h i s program w i l l u s e t r a c k i n g d a t a a s i n i t i a l c o n d i t i o n s , and w i t h t h e six-degrees-of-freedom e q u a t i o n s i n c o n j u n c t i o n w i t h t h e A Least s e p a r a t i o n dynamics, w i l l g e n e r a t e a f r e e f l i g h t t r a j e c t o r y . squares r o u t i n e w i l l t h e n be used t o c o n s t r a i n t h e f r e e f l i g h t t r a j e c t o r y t o any t r a c k i n g d a t a t h a t may be a v a i l a b l e . This work assignment w i l l r e q u i r e one e n g i n e e r and one p r o g r a m e r u n t i l i t s campletton i n December 1966. The second work assignment (nunber R-AEWO-FF/G) e n t i t l e d " P o s t f l i g h t Reference T r a j e c t o r y " r e q u i r e s a'RG t o d e f i n e t h e a n a l y t i c a l methods and f u n c t i o n a l p r o c e d u r e s necessary t o determine t h e p o s t f l i g h t r e f e r e n c e t r a j e c t o r y from any on-board measurements and e x t e r n a l t r a c k i n g d a t a t h a t may be a v a i l a b l e . The m a ~ o re f f o r t under t h i s work assignment w i l l be the development o f a program which w i l l . combine t h e t e l e m e t e r e d guidance d a t a w i t h t h e d a t a from t h e v a r i o u s t r a c k i n g systems. Also r e q u i r e d i s t h a t t h e n e c e s s a r y u t i l i t y programs ( i n t e r p o l a t i o n , curve f i t t i n g , t a p e merge, c o o r d i n a t e t r a n s f o r m a t i o n s , e t c . ) w i l l be a b l e t o use any combination of d a t a t o a r r i v e a t t h e 24-hour, 7-day, and 14-day postflight trajectories. This work assignment w i l l u s e 5 e n g i n e e r s and 2 programmers u n t i l i t s completion i n December 1966. c. C o n t r a c t NAS8-20249 (General Dynamics / ~ o n v a i r ) This i s a s t u d y c o n t r a c t t o e v a l u a t e and t r u n c a t e t r a c k i n g system e r r o r models f o r use i n S a t u r n TB and V p o s t f l i g h t t r a j e c t o r y d e t e r m i n a t i o n . GD/C had emphasized t h e r e a l - t i m e a s p e c t s of t h e c o n t r a c t r a t h e r t h a n t h e t r a c k e r e r r o r models. This misunders t a n d i n g has been c o r r e c t e d and GD/@ personne 1 have r e d i r e c t e d t h e i r efforts. Expanded e r r o r models f o r Azusa, GEOTRAC, and t h e r a d a r systems have been i n c o r p o r a t e d i n t o e x i s t i n g programs. Cases a r e now being c a l c u l a t e d t o determine what t r a c k i n g e r r o r s can be n e g l e c t e d because o f i n s i g n i f i c a n c e and c o r r e l a t i o n . When t h i s i s completed, t h e r e l a t i o n s h i p between t h e remaini.ng t r a c k e r e r r o r terms and t h e guidance e r r o r model terms w i l l be s t u d i e d . This c o n t r a c t i s s t i l l about 5 t o 6 weeks behind schedule b u t should be completed s i n c e a 2-month no-cost e x t e n s i o n has been m u t u a l l y agreed upon and n e g o t i a t e d . C. P l i g h t Mechanics Branch (1) The range s a f e t y t r a j e c t o r i e s a r e ready t o t r a n s m i t to KSC and MSC on magnetic t a p e based upon t h e f i n a l o p e r a t i o n a l t r a j e c t o r y . �( 2 ) The d i s p e r s i o n a n a i y s f s about t h e o p e r a t i o n a l t r a j e c t o r y (update L), whfch i s about 95 p e r c e n t complete, should be f i n a l i z e d seon. Also, a number of d i s p e r s i o n s which a r e o u t s i d e t h e three-sigma t o l e r a n c e s a r e approximately 50 p e r cent complete. ( 3 ) The F l i g h t Mechanical S u m a r y , which i s 25 per c e n t complete, should be a v a i l a b l e by t h e middle of December. ( 4 ) Data a r e b e i n g compiled E c r u s e i n t h e AS-201 p r e f l i g h t review, whfch w i l l be held on December 1 4 t h and 15th. (5) Neither a n S-IB/S-I'ZEs t a g e s e p a r a t i o n impingement n o r a p o s t - s t a g i n g c o n t r o l l a b i l i t y problem e x i s t s f o r a nonmalfunctisning vehicle. However, t h e r e %s no S - I B , S-TIQ s t a g e s e p a r a t i o n c a p a b i l i t y due to r e t r o failures because o f t h e asymmetric plume impingement. A s i n g l e u l l a g e failure dses not consf i t u t e an S-HC3 p r o p e l kant s e a t i n g problen. ( 6 A l ~ f t - ~ fa nf a l y s i s cf AS-ZSI shcws that a nonmalfunctioniqg v e h i c l e w i l l hzve s~ldficfe~~t clo-aratlce f(-r a l l LC-34 s b r t r u c t i ~ n s . O f the f o l hi:wPng naif unctkc~ns, l ~ F Sc.f h y d r a u l i c power fane e n g i v e ) , s i n g l e a c t u a t x h a r d o v e r , and s i n g l e c o n t r o l engine f a i l u r e , t h e most c r i t i c s 1 i s t h e B a t t e r . E(-wever, nominally t h i s f a i l u r e would not e e n s t i t u t e a col L i s i o n problem a f t e r about 2.5 seconds o f f l i g h t time. 7 Wind speed l i m i t s f o r t h e AS-281 v e h i c l e have been determined for t h e p r e d i c t e d maximum d y ~ a m i cp r e s s u r e time p o i n t ( t = '78 seconds). These l i m i t s a r e p r e s e n t e d a s a f u n c t i o n of azimuth i n memorandum R-AERO-FM-38-65, d a t e d November 3, 196'5. A f i r s t - c u t o p e r a t i o n a l t r a j e c t o r y i s now a v a i l a b l e and t h e p r o f i l e w i l l be documented s h o r t l y . MSG has accepted t h e t e r m i n a l cLlnditions by phone. The Aerospace P h y s i c s S e c t i o n , CCSD, i s p r e p a r i n g t h e range s a f e t y package (Cape t a p e and d a t a r e p o r t ) f o r t h e r e f e r e n c e trajectory. CCSD has generated t h e r a l g e s a f e t y package f o r t h e l a t e s t r e f e r e n c e t r a j e c t o r y . The Cape t a p e has been forwarded t o MSC and KSC, and t h e range s a f e t y d a t a r e p o r t w i l l be ready by t h e middle of December 1965. �A meeting was h e l d a t KSC on November 1 8 t o b r i e f ETR Range S a f e t y on t h e AS-206 mission. M r . Leonard p r e s e n t e d t h e launch v e h i c l e f l i g h t p r o f i l e and o t h e r range s a f e t y d a t a . M r , S k s p i n s k i , MSC, presented t h e f l i g h t p l a n f o r t h e spacecraft. S u b o r b i t a l a b o r t and a b o r t - t o - o r b i t p l a n s were d i s c u s s e d . From l i f t - o f f t o j e t t i s o n o f t h e Launch Escape System, t h e a b o r t s a r e performed by t h e EES, r e s u l t i n g i n impacts i n t h e A t l a n t i c Ocean up t o a range of approximately 350 nm. From LES j e t t i s o n up t o approximately 581 seconds, t h e launch a b o r t s c o n s i s t of f r e e - f a l l r e t u r n w i t h t h e e n t r y guidance e s t i v a t e d t o s t e e r t o a t a r g e t a r e a near t h e Canary I s l a n d s , which a r e approximately 3200 nm downrange; from 581 seconds up t o i n s e r t i o n , t h e h a l f - L i f t impact p o i n t i s beyond t h e 3200 nm t a r g e t . The Apollo Guidance Computer, i n t h e event of a b o r t i n t h i s r e g i o n , w i l l command a guided r e t r o g r a d e s e r v i c e p r o p u l s i o n system burn and a c o n t r o l l e d e n t r y t o l a n d a t t h i s t a r g e t . Amanual procedure i s used f o r r e c o v e r y a r e a c o n t r o l i n t h e e v e n t of a guidance and n a v i g a t i o n f a i l u r e . me impacts f r o a a l l s u b o r b i t a l a b o r t s w i l l be i n t h e A t l a n t i c Ocean. Frlm a p p r ~ u i r n a t e l y571 seconds up t o insertion, the capability exists t o safely abort t o o r b i t , using the s e r v i c e p r o p u l s i o n system. Unless there i s a s p a c e c r a f t m a l f u n c t i o n o r a crew s a f e t y problem r e q u i r i n g immediate r e t u r n , t h e a b o r t - t o - o r b i t procedure i s t h e primary a b o r t made i n t h i s r e g i o n of t h e launch trajectory, M r . Leonard made a proposal t o Range S a f e t y , ETR, t o change t h e format of t h e range s a f e t y d a t a r e p o r t s which a r e provided f o r each v e h i c l e . The proposed change would reduce t h e s i z e o f t h e r e p o r t s , t h u s r e d u c i n g t h e c o s t . M r . Cobb and Lt. P e r r i n g , ETR, c a l l e d November 30 t o i n d i c a t e t h e i r i n t e r e s t i n t h e proposal. They p l a n t o come t o MSFC on December 1 3 t o d i s c u s s t h e d e t a i l s . I n the p a s t , i t has been v e r y d f f f i . c u 1 . t to g e t any I t i s hoped t h a t t h e i r decisi,on t o i n f o r m a t i o n from Range Safety. v i s i t h e r e w i l l l e a d t o a b e t t e r understanding and b e t t e r r e l a t i o n s i n the future. 2. General. A memorandum p r e s e n t i n g t h e r e s u l t s s f the t h r u s t o s c i l l a t i o n study w i l l be published soon. D. Operations S t u d i e s Branch 1. Saturn 1 A c l o s e watch o n p r o b a b l e decay d a t a f o r SA-5, 8 , 9 , and 10 i s being maintained. We w i l l r e c e i v e r e a l - t i m e t r a c k i n g d a t a from Goddard on SA-5, which has a nominal decay d a t e of February 1, 1966. �2. S a t u r n HB a. Tracking coverage on AS-281 has been compiled f o r t h e o p e r a t ionah t r a j e c t o r y r e p o r t . This s s ~ t r i b u t i o nincluded t h e e l e v a t i o n h i s t o r i e s of t h e t r a c k i n g and t e l e m e t r y network t o be c a l l e d up on AS-201, a s we19 a s t h e s l a n t range h i s t o r i e s of t h e v e h i c l e through S-IVB impact. b. The R-AERB-EO c o n t r i b u t i o n t o the AS-204 r e f e r e n c e This a n a l y s i s included e l e v a t i o n and t r a j e c t o r y was s e n t t o R-AERB-DA. azimuth h i s t o r i e s o f t h e t r a c k i n g and t e l e m e t r y network a n t i c i p a t e d f o r AS-204. c. The sequencing of a c q u i s i t i o n and l o s s times f o r t h e SA-203 o r b i t a l t r a j e c t s r y have been determined. The sequencing times i n c l u d e t h e p e r t u r b a t i o n o f ~ r b i t a lv e n t i n g . A j o i n t R-AEIPB-DA and R-AERO-PO memorandum wf ll be pub li shed. d. The s e q u e ~ c f n gt i n e s of t r a c k i n g s t % t i o n a c q u i s i t i o n and l o s s due t o v e l o c i t y d e f i c i t s on SA-28% have been published. This memo p r e s e n t e d the d e v i a t i o n s i n s t a t i o n a c q u i s i t i o n times f o r a 5' e l e v a t i o n due to v e l o c i t y d e f i c i t s frnllm 5 t o 24 m/sec, 3. Saturn V a. Tracking and t e l e m e t r y coverage has been g e n e r a t e d f o r AS-581 f o r t h e Qoint r e f e r e n c e t r a j e c t o r y . The d a t a w i l l be included i n t h e J o i n t Reference T r a j e c t o r y Report. The t r a c k i n g a n a l y s i s which has been completed f o r b. AS-582 f o r the L/V p r e l i m i n a r y r e f e r e n c e t r a j e c t o r y w i l l be included i n the L / V p r e l i m i n a r y r e f e r e n c e t r a j e c t o r y r e p o r t . c, Some work has been done o n t h e S a t u r n V d i r e c t a s c e n t mode t o determine t h e expected p o s i t i o n and v e l e c i t y e r r o r s from t r a c k i n g d a t a a v a i l a b l e from Saturn V ground network. d. Runs were made o n t h e o r b i t a l c o r r e c t i o n program t o p r e d i c t t h e a c c u r a c y w i t h which we c a n determine i n s e r t i o n elements f o r AS-581. TWJ e a s e s were c o n s i d e r e d (5 i t e r a t i o n s each): The f i r s t used d a t a o n l y throlugh t h e f i r s t p a s s of the Carnarvon t r a c k i n g s t a t i o n ; t h e second c a s e used d a t a from a l l s t a t i o n s viewing t h e v e h i c l e d u r i n g the e n t i r e f i r s t o r b i t . S t a t i o n s used were a s follows: 1 s t case ---- .= Bermuda I n s e r t i o n Ship Canary I s land Carnarvon 2nd Case A11 f i r s t c a s e s t a t i o n s White Sands M ELA Grand Bahama I s l a n d Bermuda (second p a s s ) �Data f o r a l l t h e s e s t a t i o n s were generated from nominal i n s e r t i o n c o n d i t i o n s , which were p e r t u r b e d and used a s t h e i n i t i a l e s t i m a t e . A f t e r 5 i t e r a t i o n s , r e s i d u a l s were a s follows: I s t Case Range AZ EL 4. 2nd Case - 12m .02" .02" General. a. O r b i t a l Decay A memorandum was s e n t t o R-AERO-DA documenting t h e suggested o r b i t a l decay parameters f o r S4-203 and AS-503 t r a j e c t o r i e s . Included i n t h i s rnemilra~dumwere d a t a f o r t b e cerresponding drag c o e f f i c i e n t , drag a r e a products f o r v a r i o u s v e h i c l e a t t i t u d e s , and t h e expected a t m s p h e r i e d e n s i t i e s f o r lau~chd a t e s of J u l y 1, 1966, and June 15, 1967. The d e n s i t i e s were p r e s e n t e d a s t h e r a t f o s f a timea l t i t u d e dependent a.tmospheris d e n s i t y t o t h e 1962 US Standard atmospheric density. b. AAP (1) A r e q u e s t has been r e c e i v e d from R-AERO-DP t o compute t h e aerodynamic t o r q u e s f o r some p o s s i b l e AS-211 o r b i t a l c o n f i g u r a t i o n s . M r . E a l l a n c e , R-AERO-AM, has c a l c u l a t e d C p and C N a s a f u n c t i o n of a n g l e of a t t a c k . R e s u l t s of t h e s e t o r q u e s w i l l be used by R-ASTR t o c a l c u l a t e c o n t r o l f o r c e s f o r AAP m i s s i o n s . P r e l i m i n a r y d a t a were t r a n s m i t t e d t o R-AERO-DP; a memorandum i s being compiled t o document t h e s e d a t a . ( 2 ) L i f e t i m e s t u d i e s made f o r t h r e e s p e c i a l c o n f i g u r a t i o n s of t h e Manned O r b i t a l Laboratory a r e being documented. ( 3 ) The v a r i a t i o n s i n o r b i t a l l i f e t i m e af t h e manned o r b i t a l workshop due t o t h e e x p u l s i o n of t h e LB, from t h e o r b i t i n g S-IVB a r e being s t u d i e d and w i l l soon be documented. (4) Plans a r e being made t o p r e s e n t t h e work R-AERO-FO has done on l i f e t i m e s and aerodynamic t o r q u e s f o r t h e manned o r b i t a l workshop t o t h e Manned O r b i t a l Workshop Working Group. The t e n t a t i v e agenda i s a s follows: O r b i t a l l i f e t i m e f o r proposed manned o r b i t a l l a b o r a t o r y con£ i g u r a t i o n E. D. Fleischman (15 minutes) �P e r t u r b a t i o n on o r b i t s acd o r b i t a l l i f e t i m e due t o e x p u l s i o n of EB, Aerodyrimic t o r q u e s f o r m a n ~ e d o r b i t a l workshop eonf i g u r a t i o n Lee L7arnado Tracki2g coverage f o r manned o r b i t a l workshop m f s s i o ~ , J e a n SheBton' (15 m i n u t e s ) QEO m i n u t e s ) Baser, E t h e l a n d Larry D. MulEi.-n_s,"Lac-ch WL~do~,rhrsf c r Two Types s f O r b i t s Synchrorous w i t h t h e Ex-ar P?rf>a?id,FWASA'IN X-53354, November 1 , 1965, iZ1lclassified. Dalton, C. C., " ~ t a t i s t i c s k A ~ a L j is, s Phatogrephfa Meteor Data, P a r t 11: ~ e r n i a z i ' sEumi:-ocs E f f l c l e ~ c yand Supplemented n i p p l e Weight: s g , l o USA p"I X-53360, kbvember IS, 1965, V~e1ass-i.f ied. Dickey, Lyle R., "Linear Guidance Techniques, "'ASA November 30, 3.965, t 7 ~ c l a s s i f f e d . TM X-53362, Haws, J. L., AQFeasibkEity Study of a 1.3 Per Cent Groul~dWind Model Which GobEd Be Tested i n a Proposed P u l l - S c a l e R e y ~ o l d s Nmbers T e s t F a c i l i t y , Aero-As t r s d y a m i c s IyqternaE Note {I 26-65> November 8 , 1455, Lr?.classif i e d . MeMair, A. R. z.qd E. P. Woykin, " ~ a r t hO r b i t a l L i f e t i m e P r e d i c t i o n I 2i tcesr n a l Note 27-65, Model and Program," A e r ~ - A s t r ~ d j ~ ~ m November 18, 1965, Vficlassfffed. M d 1 6 3 s , L a r r y D. , ouLaa-r.ckP r o b a b i l t t y A n a l y s i s , " Aero-As t r o d y ~ a m i c s I n t e r r a 1 Note 4 28-65, N~vember 18, 1965, Unclassified. L e s t e r , R. C. and E. H. Bauer, " P r o b a b i l t t y of t h e S-IV-B/IU Lunar Tvpact Due t o C ~ i d a c c eE r r o r s a t t h e Trarilslunar I ? j e c t i o n a s a Furretio-h of Deviatiozls from I n j e c t i o n F a c i 9 h t y , " Aero-Astrodynmics I n t e r m 1 Note +, 29-65, November 24, 1965, C o n f b d e ~ ~ t i a l . Jump, Roger A, and V. K. Henssn, " Z ~ - F S i g h t V e ~ t f n gof Launch Vehicle Compartments, " Aero-As trsdynamics I n t e r n a l h o t e {, 20-65, November 2 9 , 1965, i h c l a s s i f i e d , �9. Jones, Jesse H., "Request for Support in Acquiring Meteorological Data," Office Memo R-AERO-AU-65-60, November 18, 1965, Unclassified. 10, Stahle, C. V., "An Experimental Investigation of Wind Induced Oscillation Effects on Cylinders in Two-Dimensional Flow," ER-14019, October 26, 1965, Unclassified. APPROVAL E. D. Geissler Director, Aero-Astrodynamics Laboratory Aero-Astrodynamics Laboratory DISTRIBUTION R-AERO-DIR Dr. Geissler Mr. Jean R-AERO-P (8) R-DIR -Dr, McCall PA0 Mr, Kurtz MS-H R-AERO-R Mr. Bulter (4) Mrs. Hightower Mrs. Jerrell R-AERO-D (16) R-AERO-A (20) R-AERO-G (5) R-AERO-T Mr. Mr. Mr. Dr. Dr. Mr. Mr. Mr. Dr. Murphree Reed Cummings Heybey Sperling Dickey Jandebeur Lavender Liu (3) � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000044 Title A name given to the resource "Aero-Astrodynamics Laboratory Bimonthly Progress Report: December 13, 1965." Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center Date A point or period of time associated with an event in the lifecycle of the resource 1965-12-13 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) NASA space programs Project management Type The nature or genre of the resource Progress reports Text Source A related resource from which the described resource is derived Saturn V Collection Box 15, Folder 41 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050 https://digitalprojects.uah.edu/files/original/20/992/spc_stnv_000045.pdf ca9d172c51c8c92c47e5900bdc083c16 PDF Text Text AERO-ASTRODYNAMICS LABORATORY BIMONTHLY PROGRESS REPORT J u n e - J u l y 1967 INDEX Page . ......................... I1. ADVANCED STUDIES OFFICE ................................ 111. AEROPWSICS DIVISION ................................... A . F l u i d Mechanics Research. O f f i c e .................... B . Mechanical Design O f f i c e ........................... C . Aerodynamic Design Branch .......................... D . E x p e r i m e n t a l Aerophysics Branch .................... I TECHNICAL AND SCIENTIFIC STAFF E F . . . ......................... ....................... Thermal Environment Branch Unsteady Aerodynamics Branch ......................... ...................... ........................... ..................... .................. v. ASTRODYNAMICS AND GUIDANCE THEORY DIVISION ............. A . O p t i m i z a t i o n Theory Branch ......................... B . Astrodynamics Branch ............................... C . Guidance Theory Branch ............................. V I. DYNAMICS AND FLIGHT MECHANICS DIVISION ................. A . M u l t i - P r o j e c t s ..................................... B . S a t u r n V ........................................... C . S a t u r n IB .......................................... D . AAP ................................................ E . Other P r o j e c t s ..................................... V I I. FLIGHT TEST ANALYSIS DIVISION .......................... A . S p e c i a l P r o j e c t s O f f i c e ............................ B . F l i g h t Mechanics Branch ............................ C . T r a c k i n g and O r b i t a l A n a l y s i s Branch ............... D . F l i g h t E v a l u a t i o n Branch ........................... V I I I . PROJECTS OFFICE ........................................ IV AEROSPACE ENVIRONMENT DIVISION A Atmospheric R e s e a r c h F a c i l i t y B Space Environment Branch C T e r r e s t r i a l Environment Branch D Environmental A p p l i c a t i o n s Branch . . . . �AERO-ASTRODYNAlfICS LABORATORY BIlfONTHLY PROGRESS REPORT June-July 1967 I. TECHNICAL AND SCIENTIFIC STAFF 1. Theory of S e c u l a r P e r t u r b a t i o n s The most g e n e r a l t h e o r y was developed f o r t h e s e c u l a r p e r t u r b a t i o n s of t h e o r b i t of a s a t e l l i t e due t o t h e o b l a t e n e s s of t h e c e n t r a l body and due t o t h e g r a v i t a t i o n a l a t t r a c t i o n of a t h i r d p e r t u r b i n g body under t h e most g e n e r a l assumption f o r t h e o r b i t shapes and i n c l i n a t i o n s of t h e p e r t u r b e d and t h e p e r t u r b i n g b o d i e s . The c o n s t a n t p a r t of t h e perturbations i n the radius vector i s a l s o given a s well a s the d i f f e r e n t d e f i n i t i o n s f o r t h e mean motion and t h e semi-major a x i s , and f i n a l l y , ~ e p l e r ' st h i r d law i n t h e p e r t u r b e d motion. The problem of why a u t h o r s have found d i f f e r e n t second-order terms i s a l s o d i s c u s s e d . I t has been shown t h a t f o r any p l a n e t t h e r e e x i s t s a d i s t a n c e where t h e p e r t u r b a t i o n s of a s a t e l l i t e due t o a t h i r d p e r t u r b i n g body (sun) overcome t h e o b l a t e ness p e r t u r b a t i o n s due t o t h e p l a n e t . The paper was p r e s e n t e d a t t h e 1967 N a t i o n a l Symposium of t h e American A s t r o n a u t i c a l S o c i e t y i n H u n t s v i l l e , Alabama (12 June 1967) under t h e t i t l e "The S e c u l a r P e r t u r b a t i o n s of t h e O r b i t of a S a t e l l i t e Due t o t h e Oblateness of t h e C e n t r a l Body f o r t h e 2m-th Zonal Harmonics and Due t o t h e G r a v i t a t i o n a l A t t r a c t i o n of a Third (H. Icrause) Body ." 2. Research on t h e dynamic problems of two cable-connected s p a c e s t a t i o n s w h i r l i n g about a n a x i s normal t o t h e i r o r b i t a l p l a n e has been performed. D i f f e r e n t i a l e q u a t i o n s of v i b r a t i o n of t h e e l a s t i c c a b l e and t h e a n g u l a r movements of t h e s t a t i o n s have been d e r i v e d . The motions of t h e s t a t i o n s and v i b r a t i o n s of t h e c a b l e a r e coupled dynamically through t h e boundary c o n d i t i o n s of t h e c a b l e . This mathematical d i f f i c u l t y i s r e s o l v e d by u s i n g the concept of c o n c e n t r a t e d , f i c t i t i o u s masses. A g e n e r a l n t h o r d e r d e t e r m i n a n t a l frequency e q u a t i o n of f r e e v i b r a t i o n s of t h e system i s o b t a i n e d by using ~ a l e r k i n ' sapproach. The problem of t h e dynamic responses of t h e system t o e x t e r n a l a p p l i e d moments remains t o be s o l v e d . (Liu) 3. E a r l y E x t r a v e h i c u l a r Engineering A c t i v i t i e s Attended a p r o g r e s s review a t North American A v i a t i o n , I n c . (NAA), Downey, C a l i f o r n i a w i t h members of t h e Advanced Systems O f f i c e on C o n t r a c t NAS8-18128 " E x t r a v e h i c u l a r Engineering A c t i v i t i e s (EVEA) Program Some d i f f i c u l t i e s Requirements w i t h Emphasis on E a r l y Experiments (P-105) . ' I �had been experienced i n having NAA follow t h e c o n t r a c t u a l scope of work and s u b s e q u e n t l y i s s u e d g u i d e l i n e s and d i r e c t i v e s . During t h e review d e t a i l e d d i s c u s s ions were held among MSC and MSFC t e c h n i c a l personnel and NAA i n o r d e r t o o b t a i n u s e f u l end products from t h e s t u d y c o n t r a c t . The midterm review on t h i s s t u d y i s scheduled f o r MSFC on August 9 , 1967 and f o r MSC on August 10, 1967. During t h i s t r i p a v i s i t was made t o General ~ y n a m i c s / ~ o n v a i r , San Diego, C a l i f o r n i a t o review t h e r e l a t e d work on C o n t r a c t NAS8-18118 "Large Space S t r u c t u r e s Experiments f o r AAP" and feed r e s u l t s i n t o t h e NASA.study. 4. SEPTIM No f u r t h e r p r o g r e s s has been made toward i n i t i a t i n g work on t h e ESSA-proposed experiment " S a t e l l i t e E j e c t e d Packages f o r T e r r e s t r i a l I o n o s p h e r i c Measurements (SEPTIM) . I 1 The reasons a r e (1) u n a v a i l a b i l i t y of s t u d y f u n d s , ( 2 ) unwillingness of t h e proposer t o d e v o t e more than 10 p e r c e n t of h i s time t o t h e e a r l y s t a g e s of t h i s e f f o r t , and (3) u n a v a i l a b i l i t y of R-AERO-Y s c i e n t i f i c manpower. (Nathan) 5. ODYSSEY Recent experiment t r a d e s t u d i e s have suggested a package of f o u r e a r t h o r b i t a l aeronomy experiments which i n c l u d e t h e p a s s i v e s p h e r e ensemble, t h e p a d d l e w h e e l / d i f f u s e sphere/smooth s p h e r e combinat i o n , t h e d e n s i t o m e t e r and a mass spectrometer. Reference m i s s i o n p l a n s ( n o t t o be confused w i t h a c t u a l m i s s i o n which r e q u i r e s a launch d a t e ) have been o u t l i n e d and p r e l i m i n a r y p r o j e c t d e f i n i t i o n s t u d i e s of a p o s s i b l e experiment implementation concept have been completed. Thermal a n a l y s e s have been conducted on t h e p a s s i v e s p h e r e ensemble and t h e paddlewheel s a t e l l i t e r e s u l t i n g i n temperature time h i s t o r i e s and h e a t r a t e s f o r s e v e r a l s u r f a c e l o c a t i o n s a t o r b i t a l environments. Unsteady aerodynamic d e s i g n c r i t e r i a have been g e n e r a t e d r e l a t e d t o a p o s s i b l e piggyback experiment c a r r i e r onboard a S a t u r n launch v e h i c l e . A p r e l i m i n a r y NASA Form 1346 has been prepared and i s now being reviewed " P r e - s e l l i n g " d i s c u s s i o n s were h e l d w i t h b e f o r e a formal proposal. M r . Lord and D r . Harvey H a l l , OMSF, MTX. They suggested a more fundamental approach b e taken i n a p r e - s e l l i n g campaign t o i n c l u d e informal d i s c u s s i o n s w i t h members of OSSA. Consequently, M r . Edgar M. C o r t w r i g h t , OSSA Dep. Assoc. Admin., was c o n t a c t e d and arrangements were made f o r (Few) d i s c u s s ions w i t h D r . Fellows i n t h e P l a n e t a r y Atmospheres Off i c e . 6. A progrqm was i n i t i a t e d t o t e s t and, i f n e c e s s a r y and f e a s i b l e , t o improve on a n e x i s t i n g fundamental e v a l u a t i o n technique f o r c r o s s c o r r e l a t i o n e x p e r i m e n t a t i o n ( D i g i t a l Analysis of Random P r o c e s s e s by Curve F i t t i n g Piecewise Estimated C o r r e l a t i o n F u n c t i o n s ) . P a s t e x p e r i ence has made. i t c l e a r t h a t c l o s e s u p e r v i s i o n and guidance of t h e �of t h e c o n t r a c t o r e f f o r t i s c a l l e d f o r i n t h i s v i t a l s e c t o r of t h e crossed-beam a n a l y s i s . The program i s s t i l l i n i t s f i r s t s t a g e s . A paper published on mixed r e f l e c t i o n of s u n l i g h t (NASA TM X53617) clcvclops a mctllod f o r computing t h e l i g h t f o r c e a c t i n g on s a t e l l i t e s a s w e l l as t h e torque a s s o c i a t e d w i t h i t , i f p a r t of t h e r e f l e c t i o n i s s p e c u l a r , p a r t i s d i f f u s e . Energy l o s s e s i n t h e process a r e a l s o t a k e n i n t o a c c o u n t . (Heybey) 6. Advanced Launch Vehicle T r a j e c t o r y Research a. In-House Research E f f o r t s and Northrop C o n t r a c t S. 0.26 (1) A i r b r e a t h i n g Propuls i o n Model The HTO-Airbreather computer model development has cont i n u e d . The s i m u l a t i o n of f l i g h t a t a c o n s t a n t dynamic p r e s s u r e i s o p e r a t i o n a l . The system of smooth convergence of t h e f l i g h t p a t h d u r i n g t h e minimum f u e l p r o f i l e (MFP) f l i g h t phase and t h e c o n s t a n t q f l i g h t p a t h has a l s o been s u c c e s s f u l l y developed. During t h e second r e p o r t p e r i o d , t h e a i r b r e a t h e r model has been extended through t h e c o n s t a n t engine d u c t p r e s s u r e f l c g h t mode. To m a i n t a i n t h e d e s i r e d maximum p r e s s u r e , a continuous t r a d e - o f f i n a l t i tude and v e l o c i t y i s r e q u i r e d . (2) Rocket P r o p u l s i o n Model Equations have been w r i t t e n and a mathematical model f o r three-dimensional maneuvering f l i g h t , s i m u l a t i n g t h e r e - e n t r y and f l y b a c k , i n t h e atmosphere, of t h e f i r s t s t a g e of a two-stage advanced l a u n c h v e h i c l e w i t h r o c k e t p r o p u l s i o n has been c o n s t r u c t e d and t r a n s m i t t e d t o t h e c o n t r a c t o r f o r i n c l u s i o n i n t h e HTO/VTO models. For t h e c o n t r o l of t h e r e c o v e r y t r a j e c t o r y , two c o n t r o l v a r i a b l e s , v i z . , a n g l e of a t t a c k and bank a n g l e , have been chosen, p l u s a number of l o g i c s w i t c h i n g p o i n t s s p e c i f i e d by i n p u t and o p e r a t i n g on t h e s t a t e v a r i a b l e s . Also, weight e q u a t i o n s were o u t 1 ined f o r t h e launch v e h i c l e components p e r t i n e n t t o atmospheric f l i g h t , a s w e l l a s t u r b o j e t and t u r b o f a n j e t performance d a t a , t o be turned over t o t h e c o n t r a c t o r . Benchmark engines chosen were t h e P&W TF33P-7 of t h e C-141, and t h e advanced technology engines of t h e C-5A, Boe ing 747 and Boe ing 27 07. b. Meeting on T r a j e c t o r y Research w i t h GD/C A meeting was h e l d w i t h Louis Tramonti of GD/C t o conduct renewed d i s c u s s ions of t h e i r work i n advanced launch v e h i c l e t r a j e c t o r y r e s e a r c h which has been sparked by r e c e n t i n t e r e s t i n t h e near-term r e u s a b l e launch v e h i c l e of t h e A i r Force. Their model i n c l u d e s p r o v i s i o n s �f o r t h r e e m i x t u r e r a t i o v a l u e s i n t h e upper s t a g e and two t h r u s t l e v e l s i n t h e f i r s t s t a g e ; t h e f l i g h t e q u a t i o n s a r e numerically i n t e g r a t e d i n t h r e e d e g r e e s of freedom, r e f e r e n c e d t o a r o t a t i n g e a r t h , f o r a l l f l i g h t modes, e x c e p t c r u i s e b a c k . I n g e n e r a l , i t appears t h a t t h e i r r e s e a r c h i s l a g g i n g behind AERO' s c u r r e n t s t a t u s . . (v. Puttkamer) 7. Advanced Systems and Mission S t u d i e s a. Low T h r u s t Sys tems Study United A i r c r a f t Research L a b o r a t o r i e s p r e s e n t e d t h e e i g h t h o r a l p r o g r e s s r e p o r t on t h e work performed on a Study of Low-Acceleration Space T r a n s p o r t a t i o n Sys tems (NAS8-11309), mod. 4, c o n s i s t i n g e s s e n t i a l l y of two p a r t s . I n the f i r s t p a r t , t h e n u c l e a r Rankine c y c l e s p a c e power system, c o n s i s t i n g of a n u c l e a r r e a c t o r w i t h 4 t u r b i n e s and 12 g e n e r a t o r s (producing 4 m e ) , i s being i n v e s t i g a t e d t o i d e n t i f y c r i t i c a l technology a r e a s , such a s l o n g - l i f e r e l i a b i l i t y and i t s i m p l i c a t i o n s . For example, i t was shown t h a t e n - r o u t e maintenance and r e p a i r i s v e r y much n e c e s s a r y and a p p e a r s f e a s i b l e f o r most of t h e power p l a n t components. I n t h e second p a r t , a handbook of l o w - t h r u s t t r a j e c t o r i e s and r e l e v a n t informat i o n s u i t a b l e f o r p r e l i m i n a r y m i s s i o n and systems a n a l y s e s i s being compiled (by Ragsac). b. E l e c t r i c P r o p u l s i o n Miss i o n Engineering Study General E l e c t r i c Co. p r e s e n t e d t h e f i n a l r e p o r t of a Mission Engineering Study of E l e c t r i c a l l y Propelled Manned P l a n e t a r y Vehicles.(NAS8-20372), based on a n i n - c o r e thermionic r e a c t o r a t t h e 3 MW l e v e l and c o n c e n t r a t i n g on a manned ~ a r m s i s s i o n f o r t h e 1980 t o 1990 time p e r i o d , w i t h l a n d i n g c a p a b i l i t y . c. P r e s e n t a t i o n t o AS0 M r . Wilson and D r . Farmer of AERO-AT and M r . von Puttkamer met w i t h M r . Hal Becker of AS0 t o p r e s e n t a s h o r t run-down on c u r r e n t r e s e a r c h a p p l i c a b l e t o advanced launch v e h i c l e s and p r o p u l s i o n conducted i n AERO. T r a j e c t o r y and systems s t u d i e s were d i s c u s s e d , a s w e l l as s u p e r s o n i c i n j e c t i o n and mixing i n v e s t i g a t i o n s conducted by D r . Farmer. A r e p o r t on some r e c e n t advanced technology meetings a t t h e West Coast was g i v e n t o M r . Becker by M r . v . Puttkamer. d. Airborne Laser CAT D e t e c t i o n Sys tem A s h o r t s t u d y of che o p e r a t i o n a l i m p l i c a t i o n s of a Laser system f o r c l e a r - a i r t u r b u l e n c e (CAT) d e t e c t i o n on-board t h e SST was conducted i n s u p p o r t of AERO-A (Mr. H u f f a k e r ) . Of p a r t i c u l a r i n t e r e s t i s t h e CO;? pulsed l a s e r . To i n d i c a t e t h e c r i t i c a l i t y of time a v a i l a b l e between d e t e c t i o n and encounter of t h e CAT, a n "evasion number" was �d e f i n e d , g i v i n g t h e r a t i o of t h e mean r a d i u s of t h e d i s t u r b a n c e "bubble" t o t h e d i s t a n c e t o t h e d i s t u r b a n c e from t h e a i r c r a f t a t f i r s t d e t e c t i o n . For t h e SST c r u i s e , i t appears t h a t t h e e v a s i o n number should be s m a l l e r than 0.1. Since t h e i n t e r v a l between p u l s e s a p p e a r s t o be q u i t e l i m i t e d by s u c h c o n s i d e r a t i o n s a s h e a t i n g , pumping c a p a b i l i t y , e t c . , t h e time r e q u i r e d f o r f u l l development of t h e scanning m a t r i x could be c o n s i d e r a b l e , i n t h e o r d e r of t e n s of seconds. For a 1 0 x 10 scanning m a t r i x , f e a s i b i l i t y may be q u e s t i o n a b l e f o r a n SST, i f t h e p u l s e frequency cannot be i n c r e a s e d t o somewhere i n t h e o r d e r of 1 0 t o 20 p u l s e s p e r second, r e s u l t i n g i n 5 t o 1 0 seconds per s c a n . During 10 seconds, t h e SST t r a v e l s 7 1 1 2 km. It i s a l s o a p p a r e n t t h a t f e a s i b i l i t y may depend on a ranging c a p a b i l i t y of t h e (SST) l a s e r of a t l e a s t 100 km, i f n o t 150 km, and on t h e r e l a t i v e abundance of p r o p e r l y d i s p e r s e d p a r t i c u l a t e m a t t e r , as w e l l a s on t h e r e q u i r e d s c a r c i t y of h i g h - a l t i t u d e water ( i c e ) , a t t h e S S T - a l t i t u d e s around and above 70,000 f e e t . Aside from t h e SST, t h e l a s e r CAT d e t e c t i o n system may a l s o be of c o n s i d e r a b l e i n t e r e s t f o r t h e Boeing 747, t h e USAF (v. Puttkamer) C-5A, and o t h e r f u t u r e "Jumbo"-Jets, such a s t h e A i r b u s s e s . 11. ADVANCED STUDIES OFFICE F l i g h t Performance and Miss i o n Analysis Group A. I n s u p p o r t of t h e S a t u r n Improvement S t u d i e s , two memorandums, R-AERO-X-67-60, "Performance C a p a b i l i t y of t h e S a t u r n V U t i l i z i n g Modified F-1 and 5 - 2 Engine C h a r a c t e r i s t i c s f o r Various Miss i o n P r o f i l e s " and R-AERO-X-67-71 "Performance and T r a j e c t o r y Data f o r t h e S a t u r n SA-217 Vehicle Improvement S t u d i e s , " have been i s s u e d . The f i n a l p r e s e n t a t i o n of t h e BOP-03 Computer Program by Raytheon was h e l d J u l y 31, 1967 a t MSFC. The proposals f o r t h e e x t e n s i o n of t h e BOP s e r i e s t o i n c l u d e atmospheric guidance and rendezvous c a p a b i l i t y have been r e c e i v e d and a r s being evaluated. Performance d a t a have been g e n e r a t e d on t h e S a t u r n V t h r e e - s t a g e t o e l l i p t i c a l assembly o r b i t f o r use i n t h e Manned P l a n e t a r y Flyby Studies . Performance a s p e c t s f o r c e r t a i n proposed n u c l e a r v e h i c l e s have R e s u l t s a r e now being documented. been e v a l u a t e d a t t h e r e q u e s t of R-AS-V. �B. Systems A n a l y s i s Group 1. The second performance review of c o n t r a c t NAS8-21051 "Use of Large S o l i d Motors i n Booster A p p l i c a t i o n s " w i t h DAC was conducted a t MSFC on June 22. Personnel of Lockheed P r o p u l s i o n Company, t h e p r o p u l s i o n s u b c o n t r a c t o r , have e s s e n t i a l l y completed t h e i r e f f o r t s on g r a i n d e s i g n , p r o c e s s i n g a n a l y s e s and f i n a l SRM d e s i g n . The remaining t a s k s f o r LPC a r e a s s o c i a t e d w i t h motor a v a i l a b i l i t y and c o s t s . DAC d e s i g n a n a l y s e s have been updated t o r e f l e c t t h e f i n a l SRM d e s i g n . Design of t h e s e l e c t e d c o n f i g u r a t i o n (see April/May Progress Report) i s proceeding on s c h e d u l e w i t h no major problems having developed. Review c o p i e s of t h e p o r t i o n of t h e f i n a l r e p o r t d e a l i n g w i t h t h e TVC s y s tem comparison have been r e c e i v e d by MSFC and a r e b e i n g e v a l u a t e d . 2 . The f i r s t performance review of t h e CCSD s t u d y , NAS8-21107, "Phase 111, S a t u r n I B Improvement Study" ( s e e April/May Progress Report) was conducted a t MSFC on June 28. The work d u r i n g t h e r e p o r t i n g period was concerned w i t h continued development of launch o p t i o n v e h i c l e d e s i g n and t r a j e c t o r y c h a r a c t e r i s t i c s , plus t h e p r o g r e s s i v e evolvement of v a r i o u s performance, environment, and d e s i g n a n a l y s e s . A problem has developed w i t h t h e c o n f i g u r a t i o n employing a "Voyager" type payload shape due t o the l e n g t h r e q u i r e d f o r packaging t h e payload. A payload d e n s i t y of 6 1 b s / f t 3 using t h e f u l l performance c a p a b i l i t y w a s a ground r u l e i n t h e s t u d y . A l o a d s problem and a c o n t r o l problem e x i s t e d , b u t b o t h can be eased by r e l a x i n g t h e payload d e n s i t y requirement t o 8 l b s / f t 3 . CCSD was i n s t r u c t e d t o t a k e t h i s approach i n t h e remainder of t h e s t u d y . Schedules a r e being a d j u s t e d , b u t t h e r e s u l t s should s t i l l be on time t o serve as input t o parallel studies. 3. The r e s u l t s of t h e t r a d e s t u d y p o r t i o n of t h e TBC s t u d y , NAS8-21105, "Saturn V Launch Vehicles w i t h 260-Inch Diameter S o l i d Motors,"were p r e s e n t e d a t MSFC i n t h e f i r s t performance review. A b a s e l i n e v e h i c l e w i t h a payload i n excess of 860,000 pounds i n t o 100 n a u t i c a l m i l e c i r c u l a r o r b i t was recommended. The v e h i c l e cons i s t e d of s t a n d a r d l e n g t h S-IC and S- T I s t a g e s w i t h f o u r 260" SRM's a t t a c h e d t o t h e S-IC s t a g e . Excess S-IC p r o p e l l a n t r e q u i r e d f o r f l i g h t performance o p t i m i z a t i o n i s contained i n f o u r l i q u i d pods mounted over t h e s o l i d motors. This tankage arrangement was d i c t a t e d by t h e h e i g h t l i m i t a t i o n imposed by t h e VAB. Lengthening t h e S-IC tanks w h i l e s a t i s f y i n g t h e o v e r a l l v e h i c l e h e i g h t c o n s t r a i n t would y i e l d u n r e a l i s t i c a l l y h i g h payload d e n s i t i e s . The SRM'S would burn f o r 130 seconds p a r a l l e l w i t h S-IC burn. This recommendation was t e n t a t i v e l y a c c e p t e d by MSFC, b u t f u r t h e r c o n s i d e r a t i o n led t o i t s replacement by a " z e r o s t a g e " concept. The b a s e l i n e v e h i c l e f i n a l l y s e l e c t e d f o r d e t a i l e d s t u d y y i e l d s a payload of over 700,000 pounds i n t o low e a r t h o r b i t . This v e h i c l e has s t a n d a r d l e n g t h s t a g e s , y i e l d s a c c e p t a b l e payload d e n s i t i e s , and a v o i d s the compl i c a t i o n s of t h e a d d i t i o n a l l i q u i d pods. The s t u d y i s now i n the d e s i g n phase, and work i s p r o g r e s s i n g satisfactorily. �C. As trodynamics and Miss i o n Analysis Group I. IIanned P l a n e t a r y Flyby Missions Based on S a t u r n / ~ p o l l o Sys tern The f i n a l review of t h e above s u b j e c t s t u d y ( c o n t r a c t number NAS8-18025) performed by North American A v i a t i o n , Space D i v i s i o n was h e l d a t MSFC on August 2 , L967. More than 100 persons from t h e v a r i o u s NASA c e n t e r s , Headquarters and t h e aerospace i n d u s t r y a t t e n d e d t h e review. The r e s u l t s of t h e s t u d y were w e l l r e c e i v e d . The c o n t r a c t o r developed a recommended program c o n s i s t i n g of two m u l t i p l a n e t f l y b y m i s s i o n s . Based on t h e g u i d e l i n e s used i n t h e course of t h e s t u d y , t h e s t a n d a r d S a t u r n V could n o t meet t h e i n j e c t e d payload and m i s s i o n r e q u i r e ments u n l e s s some compromise was made on t h e payload. The c o n t r a c t o r recommended t h a t an uprated S a t u r n V be developed w i t h a two s t a g e t o low e a r t h o r b i t payload c a p a b i l i t y of 400,000 l b s o r g r e a t e r . Based on t h e development schedule prepared by North American A v i a t i o n , a program "go-ahead" would be r e q u i r e d by 1970. The s t u d y review was g i v e n a t NASA Headquarters on Thursday, August 3 . A t t h e c o n c l u s i o n of t h e summary b r i e f i n g M r . George Trimble, D i r e c t o r of Advanced Manned Missions, OMSF, r e q u e s t e d t h a t t h e summary b r i e f i n g be given t o D r . Seamans. The p r e s e n t a t i o n t o D r . Seamans w i l l be g i v e n a t a l a t e r d a t e . 2. In-House P l a n e t a r y Study Program Plans a r e being f i n a l i z e d f o r a s t a r t of t h e in-house Advanced Voyager S t u d i e s . The s t u d i e s w i l l be conducted by personnel of t h e c o l l o c a t e d elements of t h e A s t r i o n i c s , P&VE, and Aero-Astrodynamics L a b o r a t o r i e s , and t h e MSFC Advanced Systems O f f i c e . M r . Bob E l l i s o n of t h i s o f f i c e w i l l be d i r e c t i n g t h e s e s t u d i e s . 3 . M r . Archie Young of t h i s o f f i c e w i l l p r e s e n t a paper e n t i t l e d , "A Computer Simulation of t h e O r b i t a l Launch Window Problem," a t t h e ATAA Guidance, C o n t r o l , and F l i g h t Dynamics Conference, H u n t s v i l l e , Alabama, August 14-16. 111. AEROPHYSICS DIVISION A. F l u i d Mechanics Research O f f i c e 1. Aerodynamic Crossed-Beam Programs A t r a c e r system has been i n s t a l l e d i n t h e Thermal A c o u s t i c J e t F a c i l i t y d u r i n g June and a s e r i e s of t e s t s was performed u s i n g t h i s system and one beam of a l a s e r cross-beam instrument t o d e t e c t t r a c e r i n t e n s i t y and t h e p e n e t r a t i o n a b i l i t y of t h e l a s e r i n t h e l i q u e f a c t i o n r e g i o n of t h e TAJF nozzles a t high chamber p r e s s u r e s . Satisfactory r e s u l t s were o b t a i n e d . �A t e s t was i n i t i a t e d i n J u l y t o make s c h l i e r e n and shadowgraph p i c t u r e s of t h e plume and i n t e r a c t i o n r e g i o n of t h e S-11 engine c l u s t e r i n the TAJF. These t e s t s were i n s u p p o r t of a program t o measu r e t h e t o t a l p r e s s u r e i n t h e c l u s t e r plumes and s h e a r l a y e r s and t o make f l u c t u a t i n g p r e s s u r e measurements on t h e model b a s e . 2. Atmospheric Crossed-Beam Program P r e l i m i n a r y r e s u l t s have been obtained on t h e a t m o s p h e r i c crossed-beam s y s tern during t h e i n i t i a l c a l i b r a t i o n and t e s t i n g period a t MSFC. Two b a s i c s e r i e s of t e s t s were c a r r i e d o u t . F i r s t , t h e l i g h t i n t e n s i t y f l u c t u a t i o n s induced by t h e atmosphere i n each i n d i v i d u a l photometric d e t e c t o r o r "single-beam" system were recorded on magnetic t a p e . The measured spectrum follows t h e -513 power law a t low f r e quencies which corresponds t o t h a t expected from atmospheric d e n s i t y f l u c t u a t i o n s i n t h e boundary l a y e r of t h e troposphere. Similar data were o b t a i n e d by CSU personnel using hot-wire anemometers a t v a r y i n g h e i g h t s up t o 40 meters on a m e t e o r o l o g i c a l tower. The second s e r i e s of t e s t s was t o determine t h e l e n g t h of t h e d a t a samples r e q u i r e d t o o b t a i n a measurable c o r r e l a t i o n between t h e crossed beams. The d a t a , recorded under i d e a l c l e a r - s k y v i e k i n g c o n d i t i o n s , contained a p p r o x i m a t e l y 85 minutes u s a b l e d a t a which a r e now being e v a l u a t e d . B. Mechanical Design Off i c e 1. S - I 1 I n s u l a t i o n Shedding E f f e c t T e s t Equipment Models, i n s u l a t i o n hopper, and' m o d i f i c a t i o n s of MSFC' s 1 4 x 14-inch wind t u n n e l f o r determining t h e c a t a s t r o p h i c e f f e c t s of t h e shedding of t h e o u t e r i n s u l a t i o n of t h e S - I 1 s t a g e have been d e s i g n e d , f a b r i c a t e d and d e l i v e r e d . 2. Equipment f o r Heat t r a n s f e r T e s t s on S - I 1 S t a g e due t o Protuberance Flow I n t e r a c t i o n s The d e s i g n f o r m o d i f i c a t i o n of Douglas designed "Hot T r a n s f e r Sidewall Assembly" and t h e d e s i g n of new hardware t o o b t a i n h e a t t r a n s f e r d a t a f o r i n t e r a c t i n g protuberance flow f i e l d s on t h e S - I 1 s t a g e have been completed. The t e s t w i l l be conducted by Boeing i n L a n g l e y l s U n i t a r y Wind Tunnel. 3 . The f o l l o e i n g i s a p a r t i a l l i s t of a d d i t i o n a l p r o j e c t s and t h e i r current s t a t i s : Visual Aid Gimbal Assembly (-F) Fabrication Modify Survey Probe Assembly (-AD) Design �O r b i t a l Workshop Model f o r Area and Moment ~e termina t i o n (-AD) Design S l o s h Force Measuring Device (-D) Drafting Odyssey Display Model (-T) Des i g n ~ o d i f i c a t i o n / ~ e - d iegsn of S p e c i a l T e s t S e c t i o n 14-Inch Wind Tunnel f o r 5-inch O.D. Base Flow Models (-AM) Fabrication 5-Inch O.D. S a t u r n V Base Flow Model w i t h Pressure Instrumentation f o r 14" Wind Tunnel (-AM) Crossed-Beam Design - Diaphragm C u t t e r Assembly f o r t h e High Reynolds Assembly (-AE) Fabrication Four-Percent S a t u r n V Force Model - AEDC (-AD) Fabrication Remote Control Hardware f o r Floor and TTS, 14" Wind C e i l i n g Adjustment Tunnel (-AE) - Temperature - Mismatch T e s t S e c t i o n (-AT) P r e s s u r e Probes and Support System 14" Wind Tunnel (-AD) Five-Component, (-AE) 112-1nch O.D. Drafting - Balance V a r i a b l e P o r o s i t y Walls f o r TTS 14" Wind Tunnel (-AE) Drafting Delivered Fabrication - S a t u r n V, Thin Skin Heat T r a n s f e r Model JPL (-AE) - Strap-on Booster f o r S-IC Model (CAL Design CAL) (-AT) - Fabrication Fabrication P a r t i a l Del. & Fabrication F l a t P l a t e Model (NSL Design) (-AD) - AMES Fabrication Free O s c i l l a t i n g Balance and Model Assembly (Lockheed Design) (-AU) Fabrication Three-Cylinder Models f o r Low Density Tes t ing (-AE) Delivered �C. Aerodynamic Design Branch 1. Saturn I B - LEM 1 The a x i a l f o r c e c h a r a c t e r i s t i c s of t h e S a t u r n IB AS-204 v e h i c l e r e f l e c t i n g t h e Lunar Module m i s s i o n and c o n f i g u r a t i o n have been published i n R-AERO-AD-67-56. The d a t a a r e based on previous e s t i m a t e s f o r t h e AS-206 v e h i c l e which have been modified t o account f o r t r a j e c t o r y induced v a r i a t i o n s i n b a s e p r e s s u r e . 2. S a t u r n IB - Minuteman Chrys l e r Corporation Space D i v i s i o n has conducted t e s t s i n t h e hISFC 14" TWT t o determine s t a t i c s t a b i l i t y and a x i a l f o r c e c h a r a c t e r i s t i c s f o r the c u r r e n t S a t u r n IB/MM c o n f i g u r a t i o n s Tests were a l s o conducted t o determine loads on t h e 70-inch diameter S a t u r n IB tanks w i t h t h e Minuteman s t r a p p e d t o t h e S-IB t a i l b a r r e l . . 3. S a t u r n V / ~ o y a g e rS t a b i l i t y Experimental wind t u n n e l t e s t s have been completed i n t h e MSFC 14" TWT of t h e S a t u r n ~ / ~ o y a g ec o r n f i g u r a t i o n . These t e s t s were made u s i n g a 0.3366 p e r c e n t s c a l e d model, and were over a Mach number range of from 0.50 through 4.96. The range of a n g l e s of a t t a c k was from - 3 t o +16 d e g r e e s . The procedures and t h e r e s u l t s of t h i s i n v e s t i g a t i o n a r e presented i n R-AERO-AD-67-65. 4. S a t u r n V L i f t - o f f Aerodynamics Model d e s i g n and f a b r i c a t i o n of a 0.9 p e r c e n t s c a l e d model of t h e S a t u r n V w i t h launch pad and LUT were reviewed on a r e c e n t t r i p t o t h e Vought Aeronautics p l a n t . The d e s i g n i s a c c e p t a b l e , and model d e l i v e r y i s scheduled f o r August 18, 1967, w i t h t e s t i n g t o b e g i n August 2 1 , 1967, i n t h e LTV low speed wind t u n n e l f a c i l i t y . Northrop Space L a b o r a t o r i e s has n e a r l y completed a comp u t e r program which w i l l c a l c u l a t e t h e flow f i e l d surrounding t h e S a t u r n V with engines on i n t h e presence of ground winds. This flow f i e l d w i l l be used t o c a l c u l a t e loads on t h e v e h i c l e d u r i n g l i f t - o f f . The program can handle any wind d i r e c t i o n a t any v e h i c l e launch a l t i tude up t o t h e p o i n t where t h e v e h i c l e c l e a r s t h e tower. The d e l i v e r y d a t e f o r t h i s program and r e s u l t s f o r s e v e r a l v e h i c l e a l t i t u d e s and wind d i r e c t i o n s i s J u l y 28, 1967. �5. Saturn V - S t a t i c S t a b i l i t y and P r e s s u r e T e s t T e s t i n g of a 4 p e r c e n t s c a l e model of t h e S a t u r n V launch v e h i c l e i n t h e AEDC 1 6 - f o o t t r a n s o n i c wind t u n n e l t o determine h i g h a n g l e - o f - a t t a c k s t a t i c s t a b i l i t y and d e t a i l e d load d i s t r i b u t i o n over tllc t a i l b a r r e l i s scheduled f o r November 20, 1967. The model d e s i g n i s complete, and f a b r i c a t i o n i s expected by September 1 5 , 1967. Generation of p r e t e s t i n f o r m a t i o n t o be p r e s e n t e d a t a p r e t e s t conference a t AEDC i s underway. The Computation Laboratory has agreed t o i n t e g r a t e t h e p r e s s u r e d a t a and provide o u t p u t i n g r a p h i c and t a b u l a r form. 6. Aerodynamic C h a r a c t e r i s t i c s of a n Uprated S a t u r n V Vehicle The aerodynamic c h a r a c t e r i s t i c s of a t h r e e - s t a g e , t h r u s t augmented S a t u r n V v e h i c l e have been published i n R-AERO-AD-67-55. These d a t a i n c l u d e normal f o r c e , a x i a l f o r c e , and c e n t e r of p r e s s u r e f o r a S a t u r n V w i t h f o u r seven-segment 120-inch diameter s o l i d r o c k e t motors s t r a p p e d on t h e S-IC s t a g e . These d a t a a r e provided throughout t h e r e q u i r e d Mach number and a n g l e - o f - a t t a c k range. 7. S a t u r n V/S-I1 Sidewall I n s u l a t i o n T e s t s T e s t s a r e b e i n g cohducted i n t h e MSPC 14" TWT t o determine t h e s t r u c t u r a l i n t e g r i t y of S a t u r n V/S-I1 s t a g e i n s u l a t i o n under simul a t e d f l i g h t aerodynamic environment. The t e s t samples f u r n i s h e d by P&VE Laboratory w i l l b e t e s t e d a t f o u r dynamic p r e s s u r e l e v e l s a t a Mach number of approximately 1.80. Also t o be i n v e s t i g a t e d a r e charact e r i s t i c i n s u l a t i o n c r a c k s and debonds a s s p e c i f i e d by P&VE. R e s u l t s of t h e s e t e s t s w i l l be combined w i t h s i m i l a r t e s t r e s u l t s obtained by NAA i n a j o i n t memorandum. 8. Apollo-Saturn V Second S t a g e S t a b i l i t y and Drag Characterist i c s Supplemental aerodynamic s t a t i c s t a b i l i t y and a x i a l f o r c e c h a r a c t e r i s t i c s f o r t h e second s t a g e f l i g h t c o n f i g u r a t i o n of t h e pol lo/ S a t u r n V v e h i c l e have been generated t o s u p p o r t low a l t i t u d e a n a l y s i s of t h e v e h i c l e p r e d i c a t e d by a p o s s i b l e S-IC s t a g e m a l f u n c t i o n . The d a t a a r e p r e s e n t e d i n o f f i c e memorandum R-AERO-AD-67-52. �9. I n - F l i g h t Vehting Analyses f o r t h e S-111s-IVB I n t e r s t a g e of t h e Apollo/Saturn V Vehicle Updated aerodynamic and t r a j e c t o r y i n p u t d a t a f o r t h e S - I I / S - I m i n t e r s tagc i n f l igllt v e n t i n g a n a l y s i s have p r e d i c a t e d new i n f l i g h t i n t e r n a l p r e s s u r e l l i s t o r i c s . These d a t a a r e published i n R-AERO-AD-6758 Tor the 503 and 504 f l i g h t t r a j e c t o r i e s . 10. A p o l l o / S a t u r n V S-IC Stage Compartment I n t e r n a l P r e s s u r e Time H i s t o r i e s f o r t h e SA-504 T r a j e c t o r y I n f l i g h t p r e s s u r e h i s t o r y bands f o r t h e S-IC b a s e , S-IC i n t e r s t a g e compartments, generated f o r t h e i n t e r t a n k , and S-111s-IVB SA-504 t r a j e c t o r y , a r e presented i n R-AERO-AD-67-60. 11. S a t u r n IB/Apollo (Abort) I n t h e e v e n t of a m i s s i o n f a i l u r e f o r t h e S a t u r n I ~ / A p o l l o d u r i n g f i r s t s t a g e f l i g h t , t h e command module i s t o be j e t t i s o n e d . Thus, s t a t i c l o n g i t u d i n a l s t a b i l i t y and a x i a l f o r c e c h a r a c t e r i s t i c s f o r t h e v e h i c l e i n the a b o r t c o n f i g u r a t i o n a r e r e q u i r e d . Plans have been made f o r a n experimental wind t u n n e l t e s t program t o be r u n i n t h e MSFC 14" TWT f a c i l i t y . A 0.55 p e r c e n t s c a l e d model of t h e c u r r e n t S a t u r n pol pol lo (AS-205) v e h i c l e c o n f i g u r a t i o n i s t o be used (MSFC Model No. 3 2 7 ) . T e s t parameters i n c l u d e Mach numbers from 0.50 t o 4.96, a n g l e s of a t t a c k of from -2" t o +16O, and r o l l a n g l e s of 0 ° , 45" a n d 90". The t e s t i s now scheduled t o be completed t h e f i r s t week of August. 12. Apollo/Saturn I B S t a b i l i t y Aerodynamics A r e c e n t i n v e s t i g a t i o n of t h e Saturn I B AS-205 c o n f i g u r a t i o n i n d i c a t e d a forward s h i f t i n c e n t e r of p r e s s u r e a s compared t o AS-201. This s h i f t i.s s i g n i f i c a n t l y g r e a t e r than p r e s e n t aerodynamic t o l e r a n c e s . Wind t u n n e l t e s t s were made a t t h e MSFC 14" TWT and LTV & f o o t wind t u n n e l . New aerodynamic s t a b i l i t y and corresponding load d i s t r i b u t i o n s a r e being generated f o r t h e AS-205 c o n f i g u r a t i o n . The major f a c t o r s t h a t caused t h i s s h i f t a r e (1) removal of t h e t u r b i n e exhaust d u c t , (2) removal of engine shrouds, ( 3 ) i n c r e a s e of t h e Apollo u m b i l i c a l f a i r i n g h e i g h t from 4" t o 15", and (4) i n c r e a s e i n h e i g h t of S-IB r e t r o - r o c k e t s from 15.5" t o 22.9". 13. O r b i t a l Aerodynamics Lockheed p e r s o n n e l , working under Schedule Order No. 83, have c a l c u l a t e d o r b i t a l aerodynamic d a t a f o r s e v e r a l updated O r b i t a l These d a t a , which r e f l e c t Workshop and LM/ATM c l u s t e r con£ i g u r a t i o n s r e c e n t changes i n t h e c o n f i g u r a t i o n geometry of t h e O r b i t a l Workshop and LM/ATM c l u s t e r , a r e presented i n t h e f o l l o w i n g memorandums: . �( a ) O r b i t a l Aerodynamic C h a r a c t e r i s t i c s f o r t h e Lunar ~ o d u l e / A p o l l oTelescope ( ~ I A T Mw)i t h and w i t h o u t t h e Docked Command and S e r v i c e Module (CSM) (MSFC Dwg. SK10-7266, Rev. G ) , R-AERO-AD-67-54, June 1 6 , 1967. (b) O r b i t a l Aerodynamic C h a r a c t e r i s t i c s f o r t h e LM/ATM C l u s t e r C o n f i g u r a t i o n of t h e O r b i t a l Workshop (MSFC Dwg. SK107298), R-AERO-AD-67-63, J u l y 20, 1967. ( c ) O r b i t a l Aerodynamic C h a r a c t e r i s t i c s f o r t h e O r b i t a l Workshop w i t h and w i t h o u t t h e Docked Command and S e r v i c e Module (MSFC Dwg. SK10-7298, Rev. F ) , R-AERO-AD-67-66, J u l y 24, 1967. Lockheed has a l s o c a l c u l a t e d aerodynamic drag d a t a f o r t h e Voyager s p a c e c r a f t i n t h r e e e l l i p t i c o r b i t s around Mars. These d a t a have n o t y e t been p u b l i s h e d . 14. P a r a m e t r i c Strap-on Study One approach t o u p r a t i n g launch v e h i c l e s i s t o use "strap-on" s o l id p r o p e l l a n t t h r u s t a s s i s t . I n s u p p o r t of f e a s i b i l i t y s t u d i e s , p a r a m e t r i c aerodynamic d a t a a r e needed f o r v a r i o u s b a s i c / s e c o n d a r y body combinations. Because of t h e complexity of t h e aerodynamics, a n e x p e r i mental p a r a m e t r i c s t u d y was i n i t i a t e d t o s t u d y n i n e s e p a r a t e parameters i n approximately f i v e phases. Phase I i s t h e s t u d y of t h e e f f e c t of v a r i o u s s i z e s t r a p - o n s on t h r e e b a s i c b o d i e s of d i f f e r e n t f i n e n e s s r a t i o s . Because of t h e l e n g t h of t h e r e q u i r e d t e s t program, i t was n e c e s s a r y t o r u n Phase I i n two p a r t s . P a r t I of Phase I was completed i n t h e MSFC 14" TWT d u r i n g June 1967. Data from t h e f i r s t p a r t w i l l be e v a l u a t e d f o r t r e n d s and used t o s e t g u i d e l i n e s f o r reducing t h e l e n g t h of t h e second p a r t . A f t e r t h e completion of b o t h p a r t s of t h e t e s t program, a n i n t e r i m r e p o r t w i l l be published. 15. Drag T e s t s i n t h e Low Density Wind Tunnel An experimental i n v e s t i g a t i o n has been conducted i n t h e Low D e n s i t y Wind Tunnel, and i t has r e v e a l e d t h e need f o r improvements i n b o t h t h e t e s t f a c i l i t y and t e s t equipment. 'Cwo recommendations f o r improvements which could provide b e t t e r d a t a over a l a r g e range of Knudsen numbers a r e a s follows: (1) Cooling c o i l s which a r e a t t a c h e d t o t h e o u t e r s u r f a c e of t h e wind t u n n e l n o z z l e should be a c t i v a t e d s o t h a t some of t h e n o z z l e boundary l a y e r can be f r o z e n o u t . This could p o s s i b l y ( 2 ) A more s e n s i t i v e p r o v i d e a n i s e n t r o p i c t e s t core a t lower p r e s s u r e s . b a l a n c e i s needed s o t h a t s m a l l e r models could be t e s t e d a t low p r e s s u r e s . T e s t s of s m a l l models a t low p r e s s u r e s would provide d a t a under n e a r l y f r e e - m o l e c u l e flow c o n d i t i o n s . �16. Body of Revolution Viscous Cross -Flow I n v e s t i g a t i o n C o n t r a c t NAS8-21152 has been awarded f o r t h e c o n t i n u a t i o n of t h e v i s c o u s cross-flow i n v e s t i g a t i o n i n t h e LTV high speed wind t u n n e l . The p r e s s u r e model, s t i n g , and a s s o c i a t e d hardware w i l l be provided by MSFC. A t t h i s time, no f i r m t e s t d a t e has been s e t . Model d e s i g n , f a b r i c a t i o n , and assembly a r e expected t o r e q u i r e approximately f i v e months. A s t u d y of i n s t r u m e n t a t i o n requirements, model s i z e , s t i n g to-model-diameter r a t i o s , d a t a accuracy and r e q u i r e d t e s t i n g time i s being conducted f o r f u t u r e u t i l i z a t i o n of t h e proposed h i g h Reynolds number t e s t equipment. D. Experimental Aerophysics Branch 1. Low Dens i t y Wind Tunnel T e s t s have been completed i n t h e Low Density Wind Tunnel on m i c r o f o r c e drag measurements f o r 1 - i n c h t o 3-inch diameter s p h e r e s and d i s c s and f o r 1-inch and 2-inch diameter cones w i t h 9' h a l f - a n g l e s . A second pendulum-type m i c r o f o r c e b a l a n c e No. 220A , which has approximately twice t h e s e n s i t i v i t y of balance No. 220 and extends t h e range down t o 0.001 grams f o r c e , has been c a l i b r a t e d . A t o r s i o n a l m i c r o f o r c e b a l a n c e i s being f a b r i c a t e d f o r measurement of a wider range of drag f o r c e s i n t h e LDWT. Three a d d i t i o n a l LN2 Dewars have been obtained a s excess from R-TEST t o i n c r e a s e s t o r a g e c a p a c i t y and e f f i c i e n c y of t h e cryopumping system i n t h e LDWT. Arrangements a r e being made t o o b t a i n a GHE r e f r i g e r a t o r t o be used a s a cryopumping system. This w i l l provide t h e c a p a b i l i t y of using n i t r o g e n gas a s t h e Low Density Wind Tunnel flow medium. C a l i b r a t i o n has been resumed on t h e Mach 4 low d e n s i t y nozzle. S t a t i c p r e s s u r e s a r e being measured a l o n g t h e n o z z l e a x i s f o r comparison w i t h computed v a l u e s based upon e a r l i e r measurements. 2. Impulse Base Flow F a c i l i t y A s h o r t d u r a t i o n p a r a m e t r i c base h e a t i n g model t e s t was planned s e v e r a l y e a r s ago t o provi.de b a s i c b a s e h e a t i n g d a t a on a number o:f m u l t i - e n g i n e c o n f i g u r a t i o n s . This t e s t was never conducted because of h i g h e r p r i o r i t y work a s s o c i a t e d w i t h t h e v a r i o u s S a t u r n s t a g e s . A t e s t i s now planned t o use some of t h e ha.rdware designed f o r t h e e a r l i e r t e s t , b u t t h e emphasis has been s h i f t e d t o determining t h s e f f e c t of model s c a l e on th.e r e c o v e r y temperatures and h e a t t r a n s f e r c o e f f i c i e i l t s �i n t h e base r e g i o n . The program has f i v e s e p a r a t e phases, t h e purpose and scope of which a r c b r i e f l y d e s c r i b e d i n t h e p r o j e c t summary AT-68. Hardware d e s i g n and f a b r i c a t i o n f o r t h e above t e s t i s comp l e t e and cold flow checkout of t h e model w i l l begin t h e f i r s t week i n Augus t. 3. High Reynolds Number S p e c i a l T e s t Equipment A summary meeting of t h e High Reynolds Number T e s t Equipment s t a t u s was h e l d J u l y 21, 1967. The following is a l i s t of major items and t h e i r expected d e l i v e r y d a t e s : - (a) Supply tube (b) S e t t l i n g chamber (c) Building (d) Sphere (e) Other items - - October 1967. - December 1967. December 1967. January 1968. - May 1968. I n s t r u m e n t a t i o n was t h e major concern of t h i s meeting. Because of quick-response i n s t r u m e n t a t i o n r e q u i r e m e n t s , l o c a t i o n of t h e t r a n s d u c e r w i t h r e s p e c t t o model measuring o r i f i c e i s c r i t i c a l . P r e s e n t p l a n s a r e t o house pressure-measuring i n s t r u m e n t a t i o n w i t h i n t h e s t i n g a s c l o s e t o t h e model a s p o s s i b l e . . Following a s e r i e s of t r a n s d u c e r response t e s t s , i t was concluded t h a t 'tubing of 0.085-inch I . D . and 3 f e e t i n l e n g t h would provide adequate response. Run times of 100 m i l l i s e c o n d s i s expected a f t e r 300 m i l l i s e c o n d s of s t a r t i n g process. Model s t a r t i n g l o a d s a t maximum Reynolds number & 200 x l o 6 per f o o t ) a r e a l s o of concern, e s p e c i a l l y a t h i g h a n g l e s of a t t a c k , s i n c e t h e model must be s e t a t t h e d e s i r e d a n g l e of a t t a c k b e f o r e flow i n i t i a tion. S t u d i e s a r e underway t o e s t a b l i s h t h e maximum number of d a t a channels which may be provided w i t h t h e p r e s e n t model, s t i n g , and transducer constraints . 4. Thermal Acoustic J e t F a c i l i t y A t e s t program i s underway on t h e cold flow d u c t f o r R-AERO-AF t o i n v e s t i g a t e p r e s s u r e f l u c t u a t i o n s i n t h e base r e g i o n of a c l u s t e r e d j e t and t o determine t h e t o t a l p r e s s u r e v a r i a t i o n s i n t h e e x h a u s t plumes. A p r i o r t e s t was r u n t o map t h e flow f i e l d s photog r a p h i c a l l y and t o a i d i n t h e o v e r a l l a n a l y s i s of t h e f i n a l d a t a . �1 i.11111 l i c a t c r c o n t r a c t d e l i v c r y d e a d l i n e of 111id-September 1967 w i l l probably bc mct. T l i c Iic 5. 7 x 7-Inch B i s o n i c Wind Tunnel The BWT has been s u f f i c i e n t l y r e p a i r e d t o a l l o w t e s t i n g . A p r e l i m i n a r y i n v e s t i g a t i o n was run by Wyle f o r R-AERO-AU t o determine the shock l o c a t i o n on s e v e r a l forward-facing wedges of v a r i o u s p e r c e n t a g e s of blockages. The tunnel i s scheduled f o r a complete c a l i b r a t i o n b e f o r e future tests . 6. 1 4 x 14-Inch T r i s o n i c Wind Tunnel The following t e s t s were r u n d u r i n g June and J u l y 1967: a . A t e s t of t h e s t a t i c l o n g i t u d i n a l s t a b i l i t y and a x i a l f o r c e c h a r a c t e r i s t i c s of t h e uprated S a t u r n I (AS-205) f o r R-AERO-AD. T o t a l r u n s : 99. b . A p a r a m e t r i c s t u d y f o r R-AERO-AD of t h e aerodynamic c l l a r a c t e r i s t i c s of s o l i d p r o p e l l a n t "s trap-on" t h r u s t a s s i s t a s a p p l i e d t o S a t u r n - t y p e v e h i c l e s . T o t a l r u n s : 128. c. A t e s t f o r R-AERO-AD by C h r y s l e r t o determine t h e t o t a l f o r c e s and moments on t h e 70-inch diameter tanks on models of t h e S a t u r n IB/LM and Apollo launch v e h i c l e s w i t h Minuteman s t r a p - o n conf i g u r a t i o n s . T o t a l r u n s : 53. d . An i n v e s t i g a t i o n t o determine t h e s t a t i c s t a b i l i t y and a x i a l f o r c e c h a r a c t e r i s t i c s of t h e S a t u r n ~B/LM/Minutemanand S a t u r n IB/ Apoll.o/Minuteman con£ i g u r a t i o n s . This i s a supplemental t e s t t o t h e prev i o u s i n v e s t i g a t i o n . T o t a l runs : 190. e . A t e s t f o r R-AERO-AD, i n c o n j u n c t i o n w i t h P&VE, t o determine t h e s t r u c t u r a l i n t e g r i t y of t h e S a t u r n V/S-I1 s t a g e i n s u l a t i o n a t v a r i o u s t u n n e l dynamic p r e s s u r e s . High 'speed movies were taken of v a r i o u s panel c o n f i g u r a t i o n s , a l o n g w i t h l o c a l mean and f l u c t u a t i n g p r e s s u r e measurements. T o t a l r u n s : 140. The tunnel i s c u r r e n t l y running a t a reduced r a t e because I n t e r n a l combust ion caused t h e t h e main compressor i s i n o p e r a t i v e compressor' s t h i r d s t a g e a f t e r c o o l e r t o blow a p a r t , caus ing c o n s i d e r a b l e damage. A committee from Aerophysics D i v i s i o n i s i n v e s t i g a t i n g t h e causes of t h e combustion t o determine a r e l i a b l e f i x . The compressor w i l l b e down f o r a b o u t two months. P r e s e n t o p e r a t i o n i s from R-TEST'S 3500 p s i air. . �7. O r b i t a l Aerodynamics Scanner Sys tems The d e s i g n , f a b r i c a t i o n , and checkout of t h e improved v c r s i o n of the h i g h speed d i g i t a l T.V. scanner s y s tem have been complctccl. Minor problems were encountered i n p r o p e r l y i l l u m i n a t i n g t h e modcl. Dcsign oE a l i g h t box t o e l i m i n a t e t h e problem is underway. I n t h e p r e s e n t system, t h e d a t a a r e recorded on IBM c a r d s f o r l a t e r r e d u c t i o n i n R-AERO-AE's computer f a c i l i t i e s . A program was w r i t t e n and checked o u t f o r computing moments, a r e a s , and c e n t r o i d s of a body a b o u t b o t h t h e X and Y axes based upon d a t a d i g i t i z e d by t h i s system. A new v e r s i o n of t h e T.V. system i s under c o n s i d e r a t i o n t h a t w i l l compute t h e a r e a s and moments on l i n e , t h e r e b y e l i m i n a t i n g t h e mass of d a t a c a r d s t h a t a r e p r e s e n t l y r e q u i r e d . The p h o t o - c e l l scanner f o r determining moments and p r o j e c t e d a r e a s has been completed and i s about 95 p e r c e n t checked o u t . A few minor items r e q u i r e d rework. The system w i l l be o p e r a t i o n a l w i t h i n 1 0 days. 8. I n s trumenta t i o n P i l o t s t u d i e s of r e a l - t i m e , o n - l i n e d i g i t i z i n g of c r o s s e d beam d a t a have been s t a r t e d . The d a t a s y s tem from t h e shock t u n n e l i s t o be used a s a n a n a l o g - t o - d i g i t a l c o n v e r t e r , and t h e o u t p u t s t o r e d on d i g i t a l magnetic t a p e f o r computer e n t r y . The d a t a system was t o be modified f o r d i g i t a l magnetic t a p e o u t p u t i n a d d i t i o n t o t h e e x i s t i n g card o u t p u t . The d i g i t a l t a p e u n i t was purchased; b u t upon a r r i v a l , i t was dropped on i t s f a c e i n t h e r e c e i v i n g a r e a of Technical S e r c i e s O f f i c e . Because of t h e e x t e n s i v e damage, i t i s being r e t u r n e d t o t h e f a c t o r y f o r r e p a i r , which w i l l t a k e about two months. 9. Data Reduction D i g i t a l magnetic t a p e s of t h e 4 p e r c e n t S a t u r n V model s t a t i c p r e s s u r e d a t a were converted t o c a r d s f o r p l o t t i n g . About twot h i r d s of t h e s t a t i c d a t a have been machine p l o t t e d f o r R-AERO-AU. A program was wriLten t o c o r r e c t the t r a n s o n i c o v e r a l l sound p r e s s u r e l e v e l d a t a from t h e Saturn V 4 p e r c e n t a c o u s t i c model. These c o r r e c t i o n s were f o r human e r r o r s , bad c h a n n e l s , c a l i b r a t i o n c o r r e c t i o n s , e t c . , t h a t became e v i d e n t a f t e r t h e t e s t . Work has n o t s t a r t e d on measuring and d i g i t i z i n g t h e o v e r a l l sound p r e s s u r e l e v e l s from t h e s u p e r s o n i c phase; i t w i l l probably n o t s t a r t u n t i l t h i s w i n t e r . �LO. Miscellaneous A magnetic t a p e r e c o r d e r and e l e c t r o n i c s were s e t up a t R-COMP t o p l a y back ground winds d a t a . S e v e r a l items of e l e c t r o n i c s , which a r e p a r t of t h e ground winds t e s t i n g damper system, and a S a t u r n I ~ / ~ e n t a u model r were s e n t t o Lockheed f o r s y s tem t e s t i n g and checkout. Work has been completed on r e c o n d i t i o n i n g and equipping t h e v a n - t r u c k a s an i n s t r u m e n t a t i o n v e h i c l e f o r f i e l d t e s t i n g of t h e crossed-beam program. The two-telescope t r a i l e r s have been completed, covers made, c a b l e r a c k s i n s t a l l e d , and t h e t e l e s c o p e s mounted. The f a c i l i t i e s have been used by IITRI f o r t h e p a s t f o u r weeks. T e s t i n g a t t h e AMICOM 400-foot tower i s expected t o s t a r t i n mid-August. E. Thermal Environment Branch 1. M u l t i p l e Protuberance T e s t s Wind t u n n e l t e s t i n g of t y p i c a l S a t u r n v e h i c l e protuberance arrangements i s being planned f o r e a r l y f a l l . The o b j e c t i v e of t h e t e s t s i s t o r e s o l v e t h e u n c e r t a i n t y i n p r e d i c t i o n of protuberance h e a t ing e f f e c t s i n r e g i o n s where t h e i n d i v i d u a l protuberance e f f e c t s o v e r l a p o r i n t e r s e c t w i t h a d j a c e n t protuberances. In addition, the t e s t i s designed t o v e r i f y t h e thermal environment r e s u l t i n g from t h e a d d i t i o n of a n t i - f l u t t e r h a t s e c t i o n s on t h e S-IVB s t a g e . The t e s t s a r e t o be run i n t h e Langley Research c e n t e r ' s U n i t a r y P l a n Wind Tunnel. Work on t h e protuberance models and n e c e s s a r y m o d i f i c a t i o n of t h e t e s t p l a t e i s being done a t MSFC. The Boeing Company i s providing e n g i n e e r i n g s u p p o r t . 2. High Angle-of-Attack T e s t s An RFQ has been i s s u e d t o provide e n g i n e e r i n g s u p p o r t f o r wind t u n n e l t e s t i n g of a S a t u r n I B con£ i g u r a t i o n a t h i g h a n g l e s of a t t a c k (15"-25"). The o b j e c t i v e of t h e t e s t i s t o provide aerodynamic h e a t i n g d a t a on a S a t u r n c o n f i g u r a t i o n a t a n g l e s of a t t a c k which would be encountered d u r i n g b o o s t i n t o a p o l a r o r b i t . T e s t i n g i s planned f o r t u n n e l A a t AEDC a t a d a t e y e t t o be determined. C o n s t r u c t i o n of t h e model by MSFC i s e s s e n t i a l l y complete. Work i s c o n t i n u i n g in-house on a d a t a r e d u c t i o n scheme t o be used a s a back-up t o t h e one r e q u e s t e d of the contractor. 3. Strap-on Heating T e s t The aerodynamic h e a t i n g e f f e c t s a s s o c i a t e d w i t h t h e proposed a d d i t i o n of Minuteman s o l i d motors t o t h e S-IB s t a g e i s being i n v e s t i g a t e d . Plans a r e b e i n g formulated i n c o n j u n c t i o n w i t h C h r y s l e r Corporation personnel t o t e s t a s t r a p - o n motor model a t Langley Research �Center u s i n g t h e t e s t p l a t e b u i l t f o r protuberance t e s t i n g . It i s cspcctcd t h a t aerodynamic h e a t i n g d a t a f o r the v e h i c l e and the s t r a p - o n mounting s t r u c t u r e can be obtained r a p i d l y and inexpensively t h i s way. T e s t i n g i s planned f o r l a t e 1967. 4. Compression Corner Heating The h e a t i n g p r e d i c t i o n techniques i n a compression c o r n e r , p a r t i c u l a r l y w i t h s e p a r a t e d flow, c o n t i n u e t o be h i g h l y u n s a t i s f a c t o r y . An e f f o r t has been undertaken t o make a comprehensive survey of t h e l i t e r a t u r e i n t h e hope of d i s c o v e r i n g , i n t h e myriad of r e p o r t s a l l u d i n g t o t h e i n v e s t i g a t i o n of compression corner e f f e c t s , some r e s u l t s wh.ich would a l l e v i a t e the inadequacy. U n f o r t u n a t e l y , t h e amount of h e a t i n g d a t a i s s c a n t y , and i t was n o t p o s s i b l e t o make any s e n s i b l e c o r r e l a t i o n between t h o s e which were a v a i l a b l e . It i s f e l t t h a t a worthwhile t e s t program designed t o c o r r e c t t h e d e f i c i e n c i e s encountered would be of such magnitude a s t o be u n f e a s i b l e a t t h i s time. A r e p o r t documenting t h e l i t e r a t u r e s e a r c h i s being prepared. 5. Voyager Thermal Environments Work i s continuing on thermal environment a n a l y s e s f o r t h e S a t u r n VIVoyager. The a n a l y s i s f o r t h e a s c e n t p o r t i o n i s completed and has been published i n Memo R-AERO-AT-5-67, June 1 2 , 1967. Work on t h e e a r t h o r b i t a l p o r t i o n i s e s s e n t i a l l y complete, and t h e a n a l y s i s of t h e i n t e r p l a n e t a r y p o r t i o n i s w e l l underway. 6. P r e c u r s o r R a d i a t i o n Study Work has begun t o a n a l y z e t h e p r e c u r s o r e f f e c t i n a h i g h e n t h a l p y gas stream. The i n i t i a l e f f o r t i s d i r e c t e d toward e s t a b l i s h i n g t h e r a d i a t i o n e m i t t e d by helium-hydrogen s l a b s w i t h dimensions and prop e r t i e s t y p i c a l of shock l a y e r s around J u p i t e r e n t r y v e h i c l e s . 7. J o v i a n Entry Probe A s t u d y t o determine t h e h e a t p r o t e c t i o n requirements of a J u p i t e r e n t r y probe i s being i n i t i a t e d . Best e s t i m a t e s of t h e J o v i a n atmosphere w i l l b e used i n c o n j u n c t i o n w i t h v a r i o u s h e a t i n g p r e d i c t i o n techniques t o o b t a i n r e a l i s t i c h e a t p r o t e c t i o n requirements. O b j e c t i v e s of t h e s t u d y a r e t o e s t i m a t e s u r v i v a b i l i t y , i n d i c a t e t h e r e q u i r e d t r a j e c t o r y shaping f o r low h e a t i n p u t , and e s t i m a t e the e x t e n t of RF a t t e n u a t i o n communication problems. The r e s u l t s of t h e p r e c u r s o r r a d i a t i o n s t u d y w i l l be a p p l i e d a s a v a i l a b l e . �8. Odyssey Thermal A n a l y s i s A d d i t i o n a l work i s b e i n g performed t o b e t t e r d e f i n e t h e tllermal e n v i r o n m e n t of t h e Odyssey Experiments Package. S p e c i f i c a l l y , t h e o r b i t which p r o d u c e s t h e maximum t e m p e r a t u r e g r a d i e n t s w i l l b e d e t e r m i n e d , e f f e c t s of d i f f e r e n t m a t e r i a l s a n d / o r s u r f a c e f i n i s h e s w i l l b e i n v e s t i g a t e d , and e f f e c t s of d i f f e r e n t s p i n r a t e s w i l l be s t u d i e d . 9. Des i g n A s s u r a n c e A g e n e r a l a n a l y s i s of e x h a u s t plume c o n v e c t i v e h e a t i n g e n v i r o n m e n t s d u r i n g S a t u r n V l i f t - o f f h a s b e e n documented. This a n a l y s i s d e f i n e s t h e c o n v e c t i v e h e a t i n g caused by t h e s e a l e v e l S-IC e x h a u s t f l o w f i e l d impinging a g a i n s t a f l a t p l a t e and v a r i o u s s i z e s of cy L i n d e r s and s p h e r e s . A p r e l i m i n a r y a n a l y s i s was completed which d e f i n e d e x h a u s t plume impingement a r e a s on t h e LUT d e c k . An i n v e s t i g a t i o n was a l s o made o f t h e c o o l i n g p o t e n t i a l o f w a t e r (50,000 GPM) o n t o t h e LUT d e c k . P r e l i m i n a r y r e s u l t s show t h a t t h e w a t e r s h o u l d p r o v i d e more t h a n a d e q u a t e c o o l i n g ; however, l o c a l " h o t s p o t s " on t h e d e c k s u r f a c e w i l l o c c u r . P r e l i m i n a r y s t r u c t u r a l and component t e m p e r a t u r e s and p r e s s u r e s f o r t h e LUT deck and wind damper were r e l e a s e d i n C o o r d i n a t i o n Preliminary review of S h e e t s ATT-E.1-044 and ATT-H-046, r e s p e c t i v e l y . t h e s t r u c t u r a l t e m p e r a t u r e s by t h e S t r e n g t h and V i b r a t i o n s S t r e s s Group has i n d i c a t e d o n l y l o c a l warping of t h e deck panels d u r i n g launch. T h i s a n a l y s i s n e g l e c t e d t h e e f f e c t s o f w a t e r on t h e deck. The component s t u d y h a s i n d i c a t e d t h a t a number of t h e components on t h e wind damper exceed t h e i r d e s i g n o p e r a t i n g t e m p e r a t u r e . The MGSE T r a n s p o r t a t i o n and H a n d l i n g Group i s e v a l u a t i n g t h i s c o n d i t i o n and a s s e s s i n g t h e amount of refurbishment necessary a f t e r each launch. A p r e l i m i n a r y a n a l y s i s was performed t o e v a l u a t e t h e e f f e c t of d e l e t i n g t h e S-IC r e t r o - m o t o r s on f i r s t p l a n e s t a g i n g e n v i r o n m e n t s . R e s u l t s of t h e t h e r m a l a n a l y s i s a r e r e p o r t e d i n Boeing Coordinat i o n S h e e t G&C-H-061, d a t e d J u n e 1 4 , 1967. F. Unsteady Aerodynamics Branch 1. I n f l i g h t F l u c t u a t i n g P r e s s u r e and A c o u s t i c Environments a. The s u p e r s o n i c phase (M = 1 . 6 t o 3 . 0 ) o f t h e 4 p e r c e n t S a t u r n V f l u c t u a t i n g p r e s s u r e t e s t t h a t was conducted i n t h e AEDC 1 6 - f o o t wind t u n n e l h a s been completed. Data r e d u c t i o n f o r t h i s phase o f t h e s t u d y i s p a r t i a l l y complete. �b. Reduction of t h e f l u c t u a t i n g p r e s s u r e d a t a from t h e t r a n s o n i c p o r t i o n 01 t h e AEDC e x p e r i m e n t i s a t t h e f o l l o w i n g s t a g e s : ( I ) O v e r a l l sound p r e s s u r e l e v e l s have been computed and p l o t t e d and a r e b e i n g r e v i e w e d ; (2) s p e c t r u m a n a l y s i s of t h e a v a i l a b l e d a t a i s b e i n g c o n t i n u e d ; and ( 3 ) a c o n t r a c t w i t h Baganoff A s s o c i a t e s , I n c . t o p e r f o r m t h e c o r r e l a t i o n a n a l y s i s of t h e AEDC d a t a has been o b t a i n e d . 2. Launch S i t e A c o u s t i c Environments a . The n o i s e s o u r c e c h a r a c t e r i s t i c s e x p e r i m e n t b e i n g p e r formed under Wyle C o n t r a c t NAS8-21060 ( I n v e s t i g a t i o n of t h e Noise G e n e r a t i o n Mechanisms of D e f l e c t e d and U n d e f l e c t e d S u p e r s o n i c Rocket E x h a u s t ) h a s been completed. Data r e d u c t i o n and a n a l y t i c a l a n a l y s i s of the acoustic data a r e i n progress. b. A c o u s t i c d a t a from AMTF t e s t s a r e being analyzed t o determine t h e d i f r e r e n c e s on t h e a c o u s t i c environment. completed, and now a complete s e t of d a t a cone e n g i n e n o z z l e t e s t s . on t h e b e l l - c o n e e n g i n e n o z z l e e f f e c t s of t h e n o z z l e e x p a n s i o n A d d i t i o n a l t e s t s have been has been o b t a i n e d f o r t h e b e l l - c. Data from t h e planned c l u s t e r t e s t s have n o t y e t b e e n r e c e i v e d b e c a u s e of T e s t L a b o r a t o r y s c h e d u l i n g problems. T h i s informat i o n i s e x p e c t e d w i t h i n two months t o a l l o w a more thorough e v a l u a t i o n o f t h e e f f e c t s of e n g i n e f l o w p r o x i m i t y . A c o u s t i c d a t a from s i n g l e e n g i n e t e s t s w i t h t h e e x i t p r e s s u r e a s a v a r i a b l e have n o t y e t been acquired. d. The 1 1 2 0 t h s c a l e model of t h e S a t u r n V i n v o l v i n g phase c o r r e l a t i o n s f o r t h e s i m u l a t e d v e h i c l e s k i n i s complete and i s a w a i t i n g i n s t r u m e n t a t i o n checkout. The microphones, j u s t r e c e i v e d from LTV, have n o t r i g i d l y met s p e c i f i c a t i o n s b e c a u s e t h e y were more v i b r a t i o n s e n s i t i v e t h a n e x p e c t e d . This problem i s b e i n g c o r r e c t e d and t e s t s a r e e x p e c t e d w i t h i n s e v e r a l months. e. The j e t impingement t e s t d a t a have been r e q u e s t e d f o r t h i r d - o c t a v e band s p e c t r a l a n a l y s i s and time h i s t o r y p r e s e n t a t i o n . S e v e r a l t e s t s which a r e l a c k i n g f o r c o m p l e t i o n of t h e program a r e e x p e c t e d t o be performed soon. f. A m e e t i n g was h e l d June 22 w i t h R-AS-VGand t h e cont r a c t o r s (Douglas and IBM) t o d i s c u s s t h e MLV con£ i g u r a t i o n s o f t h e S a t u r n IB. A r e q u e s t was t h e n made of R-AERO-AU t o p r o v i d e a c o u s t i c This environmental environments f o r s p e c i f i c v e h i c l e con£ i g u r a t i o n s i n f o r m a t i o n was f u r n i s h e d i n memo R-AERO-AU-67-63 "Response t o Request f o r A c o u s t i c Environment f o r S a t u r n IB MLV C o n f i g u r a t i o n s , ' ' August 1, 1967. S p e c t r a and o v e r a l l SPL v a l u e s were p r o v i d e d f o r on-pad and i n f l i g h t c o n d i t i o n s f o r MLV c o n f i g u r a t i o n s of a s i n g l e 260-inch s o l i d p r o p e l l a n t b o o s t e r and a l s o f o r f o u r 156-inch s o l i d p r o p e l l a n t r o c k e t s making up t h e b o o s t e r . . �g . A m e e t i n g was held a t Michoud w i t h C h r y s l e r p e r s o n n e l c o n c e r n i n g t h e three-month s t u d y o f s t r a p - o n Minuteman s o l i d r o c k e t motor t h r u s t a u g m e n t a t i o n f o r tlie S a t u r n I B v e h i c l e . The a c o u s t i c environment, which i s q u i t e s e v e r e f o r p o r t i o n s of t h e v e h i c l e i n c e r t a i n s t r a p - o n c o n f i g u r a t i o n s , i s t o be p r e d i c t e d by C h r y s l e r . P r o g r e s s i n t h a t a r e a was r e v i e w e d ; t h e o n l y problem of c o n c e r n t o b o t h t h e s t r u c t u r a l and a c o u s t i c a r e a s was t h a t KSC had s u g g e s t e d t h a t t h e SRM s t r a p - o n s b e a t t a c h e d a t somewhat h i g h e r p o i n t s on t h e v e h i c l e t h a n was p r a c t i c a l from t h e s t r u c t u r a l v i e w p o i n t . This was due o n l y t o KSC'S l o c a t i o n o f t h e d e f l e c t o r s f o r t h e SRM's f l o w s . It was hoped t h a t KSC c o u l d s o l v e t h e i r d e f l e c t o r problems and p e r m i t t h e s o l i d s t o b e lowered s o t h a t t h e d i s t a n c e between t h e n o z z l e p l a n e s o f t h e S-IB and SRM's would b e m i n i m i z e d , t h u s r e d u c i n g t h e a c o u s t i c problems i n l o c a l a r e a s t o t h e f l o w and a l l e v i a t e c e r t a i n a t t a c h m e n t d i f f i c u l t i e s . A memorandum, "J-2X Program A c o u s t i c Data A c q u i s i t i o n , " h. d a t e d J u l y 1 4 , 1967, was s e n t t o T e s t Lab r e q u e s t i n g t h e s p e c i f i c t e s t s t o b e m o n i t o r e d f o r a c o u s t i c d a t a on t h e f u l l s c a l e h o r i z o n t a l J-2(X) e n g i n e f i r i n g . T e s t s o f chamber p r e s s u r e v a l u e s down t o 5 0 p s i and up t o 750 were r e q u e s t e d a l o n g w i t h t h e t h r o t t l a b l e r u n s t h a t a r e s c h e d u l e d f o r e n g i n e e x p a n s i o n r a t i o s of 1 4 : 1 , 2 7 . 5 : l and 4 0 : l . F l i g h t a c o u s t i c d a t a from AS-201, 202 and 203 have b e e n r e r u n by Comp Lab u s i n g t h e c o r r e c t RACS c a l i b r a t i o n s i g n a l . The program f o r a c o u s t i c d a t a a n a l y s i s p r e v i o u s l y h a v i n g e r r o n e o u s b a n d w i d t h v a l u e s h a s b e e n c o r r e c t e d and now a p p e a r s t o b e o p e r a b l e . i. j. The model t e s t s f o r t h e m u f f l e r scheme f o r t h e High Reynolds Number T e s t Equipment have b e e n completed. S e v e r a l t e s t s i n v o l v i n g ground c o v e r a g e f o r a p o r t i o n of t h e s p h e r e were c o n d u c t e d , and t h e d i r e c t i v i t y of t h e a c o u s t i c f i e l d a b o u t t h e s p h e r e was a l s o a c q u i r e d d u r i n g s e v e r a l t e s t s . The d a t a a r e b e i n g a n a l y z e d and a r e p o r t i s forthcoming . k. The r e v i e w copy of a t e c h n i c a l n o t e " F a r - F i e l d A c o u s t i c E n v i r o n m e n t a l P r e d i c t i o n s f o r Launch o f S a t u r n V and a S a t u r n V MLV Conf i g u r a t i o n " h a s b e e n c o r r e c t e d and h a s b e e n forwarded f o r f i n a l p r i n t . 1. A c o o r d i n a t i o n m e e t i n g w a s h e l d among p e r s o n n e l o f MSFC and Langley R e s e a r c h C e n t e r on J u l y 1 9 , 1967 t o d i s c u s s a p o s s i b l e c o o r d i n a t i o n e f f o r t i n t h e a r e a of a c o u s t i c s c o n c e r n i n g problems a s s o c i a t e d w i t h t h e s u p e r s o n i c t r a n s p o r t (SST). Problem a r e a s o f main conc e r n a r e t h e s u p p r e s s i o n o r r e d u c t i o n of t h e j e t e x h a u s t n o i s e , p r e d i c t i o n methods, s t a n d a r d i z e d methods of s p e c i f y i n g j e t e n g i n e n o i s e , p r i m a r y n o i s e g e n e r a t i n g mechanisms o f j e t e n g i n e f l o w s , and h a z a r d c r i t e r i a . �m. A r e q u e s t was r e c e i v e d from P&VE ( J u l y 28) f o r t h e a c o u s t i c environments f o r t e n MLV c o n f i g u r a t i o n s f o r b o t h S a t u r n I B and S a t u r n V. Because the r e s u l t s were r e q u i r e d w i t h i n one week, t h e v e h i c l e s were d i v i d e d i n t o zones f o r convenience of p r e d i c t i o n . Maximum o v e r a l l sound p r e s s u r e l e v e l s were g i v e n per zone f o r b o t h i n f l i g h t and on-pad c o n d i t i o n s . The magnitude of t h e work was enormous f o r pres e n t i n g s p e c t r a f o r each zone f o r a l l t e n v e h i c l e s w i t h i n one week; t h e r e f o r e , t h e more d e t a i l e d environments a r e t o be provided on r e q u e s t For t h e more l i k e l y c a n d i d a t e s f o r t h e MLV program (Reference memo R-AER~-AU-~~-~~). 3. A e r o e l a s t i c C h a r a c t e r i s t i c s of S a t u r n I B and V a. P i t c h Damping Because of s i g n i f i c a n t s 1ippage of t h e MSFC 14- i n c h t u n n e l s c h e d u l e , p i t c h damping t e s t s on SA-203 and 206 forebody conf i g u r a t i o n s w i l l n o t begin u n t i l . mid-Augus t 1967. Furthermore, t h e proposed aerodynamic p i t c h damping t e s t s of t h r e e - c o n e - c y l i n d e r bodies have been removed from t h e p r e s e n t s c h e d u l e . b. Quasi-Steady O s c i l l a t i n g Wake Study The f o u r t h phase of t h i s s t u d y i s scheduled t o begin i n t h e l a t t e r p a r t of September 1967. Included i n t h i s phase i s a n e x t e n s i v e c a l i b r a t i o n , which w i l l be made i n s u p p o r t of e a r l i e r t e s t s . A d d i t i o n a l t e s t s using a f r e e - o s c i l l a t i o n b a l a n c e w i l l be r u n . c. F l u t t e r and Divergence A f e a s i b i l i t y s t u d y i s being made t o determine t h e p o s s i b i l i t y of running a p a r a m e t r i c t e s t t o a s c e r t a i n t h e t o r s i o n a l f l u t t e r and divergence c h a r a c t e r i s t i c s of t h e S a t u r n I B Minuteman s t r a p ons. I f p o s s i b l e , a e r o e l a s t i c a l l y s c a l e d models w i l l be used i n t h e MSFC 14-inch wind t u n n e l . d. Panel F l u t t e r An i n v e s t i g a t i o n of n o n l i n e a r o s c i l l a t i o n s of a t h r e e dimensional f l u t t e r i n g p l a t e i s underway f o r S a t u r n I B v e h i c l e s 204 t o 207 using the E . H. Dowell a n a l y t i c a l method. The problem of two- and three-dimensional p l a t e s i n a s u p e r s o n i c flow undergoing l i m i t o s c i l l a t i o n s has been s t u d i e d by Dowell over a c o n s i d e r a b l e range of Mach numbers, a i r - t o - p l a t e - m a s s r a t i o s , and p l a t e - l e n g t h - t o - w i d t h r a t i o s . The p r e s e n t s t u d y involves t h e a p p l i c a t i o n of t h e n o n l i n e a r p l a t e t h e o r y and the f u l l y l i n e a r i z e d aerodynamic t h e o r y of ow ell's method t o l a r g e r c h a r a c t e r i s t i c v a l u e s which e x i s t f o r t h e S a t u r n IB v e h i c l e . �4. S a t u r n V Ground Winds The t h r e e - p a r t ground wind t e s t program a t Langley on models 01 t h e MET t o w c r , t h e PIobile S e r v i c e S t r u c t u r e , and t h e S a t u r n V was comp l c t c d J r ~ n c 16, 1967. Tllc S a t u r n V model t e s t program, a v e r y s h o r t o n e , was t o d c t c r m i n c i f tllc dynamic r e s p o n s e o f t h e were s i g n i f i c a n t l y d i f f c r c n t wit11 t h e model s u b j e c t e d t o b o t h a u n i f o r m and a nonuniform ( v e r y l a r g e boundary l a y e r ) wind p r o f i l e . The nonuniform wind p r o f i l e was e s t a b l i s h e d by u s e of a g r i d i n s t a l l e d i n t h e t u n n e l ; however, L a n g l e y p e r s o n n e l a r e a n a l y z i n g t e s t d a t a t o d e t e r m i n e t h e e x a c t boundary l a y e r p r o f i l e . Although problems were e n c o u n t e r e d w i t h m a i n t a i n i n g a c o n s t a n t v a l u e o f model damping d u r i n g t h e t e s t program, i t can b e concluded from p r e l i m i n a r y d a t a a n a y s e s t h a t t h e model dynamic l o a d s were n o t r e d u c e d wit11 t h e nonuniform wind p r o f i l e . In f a c t , the t e s t data indicate the p o s s i b i l i t y of t h e dynamic l o a d s b e i n g l a r g e r w i t h t h e nonuniform p r o f i l e o v e r t h e l o a d s w i t h t h e u n i f o r m wind p r o f i l e . A c o n t r a c t was n e g o t i a t e d t h e l a s t o f J u n e f o r d e s i g n and f a b r i c a t i o n of a S a t u r n ~ I V o y a g e rground winds model, The f a b r i c a t i o n s h o u l d b e completed i n December 1967. A l s o , t h e e l e c t r o m a g n e t i c damper s y s t e m w i l l b e m o d i f i e d f o r i n s t a l l a t i o n i n t h e Voyager model. 5. S a t u r n I B Ground Winds P r e s e n t l y , t h e S a t u r n I ~ I C e n t a u rground winds model, b u i l t by A t k i n s and M e r r i l l C o r p o r a t i o n , i s b e i n g checked o u t by Lockheed o f H u n t s v i l l e t o s e e i f t h e dynamic c h a r a c t e r i s t i c s a r e s u c h t h a t t h e model c a n b e m o d i f i e d t o r e p r e s e n t t h e AS-204 c o n f i g u r a t i o n . The model w i l l b e m o d i f i e d by L a n g l e y and wind t u n n e l t e s t t i m e w i l l b e r e q u e s t e d from them. A l s o , t h e S a t u r n I B / C e n t a u r model w i l l b e used t o c h e c k o u t and modify t h e e l e c t r o m a g n e t i c damper s y s t e m t o b e used f o r t h e AS-204 and S a t u r n V/Voyager ground wind t e s t s . IV. AEROSPACE ENVIRONMENT DIVISION A. Atmospheric R e s e a r c h F a c i l i t y During t h i s p e r i o d , 125 rawinsonde f l i g h t s were made a t t h e Atmospheric R e s e a r c h F a c i l i t y . These f l i g h t s were made i n s u p p o r t o f a c o u s t i c s t u d i e s , s t a t i c t e s t s , and t o e s t a b l i s h a s t a t i o n h i s t o r y . T h e r e were 1 0 f l i g h t s i n s u p p o r t of a c o u s t i c s t u d i e s ; 55 f l i g h t s were made i n s u p p o r t of s t a t i c t e s t s : 37 f l i g h t s f o r t h e F-1 e n g i n e t e s t s ; 17 f o r t h e S-IB t e s t s , and 1 f o r t h e 5 - 2 e n g i n e t e s t . F i f t y - n i n e d a i l y f l i g h t s were made f o r s t a t i o n h i s t o r y . �A l 1 m e t e o r o l o g i c a l requirements f o r T e s t ~ a b o r a t o r ys' a c o u s t i c model f a c i l i t y have been completed. These requirements were t h a t wind s p e e d , wind d i r e c t i o n , and temperature be measured a t t h e 2-meter, 4-meter, 8-meter, and 16-meter l e v e l s . A l l systems have been checked o u t and turned over t o T e s t Laboratory personnel f o r o p e r a t i o n . The CPS-9 Weather Radar components have a r r i v e d a t MSFC w i t h t h e c x c e p t i o n of t h e azimuth u n i t and the tower assembly hardware k i t s . The azimuth u n i t was shipped t o t h e A i r ~ o r c e ' sOrdnance Depot f o r renovation. The hardware k i t s a r e on o r d e r . MSFC's requirements i n t h e i n s t a l l a t i o n of t h e r a d a r system have been completed. These r e q u i r e ments were (1) t o provide e l e c t r i c a l power f o r t h e antenna c o n t r o l u n i t , ( 2 ) t o provide c a b l e r o u t i n g t r a y s from t h e antenna t o t h e console u n i t and (3) t o provide antenna tower p i e r s w i t h grounding system. S p e c i a l t e s t s were conducted i n connection w i t h t h e towerp i b a l wind speed comparison s t u d y . A t o t a l of 172 p i b a l r e l e a s e s were made f o r t h e s e t e s t s . Personnel from r e c o r d i n g equipment and a c o u s t i c wind measuring w i l l be o p e r a t i o n a l f o r t h e Atmospheric Research F a c i l i t y checked power s u p p l i e s and made minor r e p a i r s t o t h e f a c i l i t y a t Kennedy Space Center. The f a c i l i t y t h e n e x t S a t u r n launch. The m e t e o r o l o g i c a l requirements f o r t h e cross-beam program were completed. This included t h e mounting and o r i e n t a t i o n of wind speed and wind d i r e c t i o n s e n s o r s on t h e Army's 400-foot tower l o c a t e d i n T e s t Area No. 1. These s e n s o r s were mounted on t h e southwest c o r n e r a t t h e 1 0 0 - f o o t , 200-foot, 300-foot, and 400-foot l e v e l s w i t h t h e wind d i r e c t i o n s e n s o r o r i e n t a t e d t o magnetic n o r t h . Wind r e c o r d i n g and s i g n a l c o n d i t i o n i n g equipment were mounted i n t h e c r o s s -beam i n s t r u m e n t a t i o n van. A l l systems have been checked o u t and a r e o p e r a t i o n a l . O f f i c e memorandum R-AERO-225-67, "Anemometer I n s t r u m e n t a t i o n f o r Cross-Beam C o r r e l a t i o n Study," has been d i s t r i b u t e d . The ionosphere sounding s t a t i o n a r r i v e d a t MSFC from Kennedy Space C e n t e r . The e n t i r e system has been unpacked and t h e system i s b e i n g checked o u t . A f t e r t h e checkout, t h e system i s scheduled t o be mounted i n a van and moved t o t h e o p e r a t i o n s a r e a near B u i l d i n g 4820. Data a c q u i s i t i o n i s c o n t i n u i n g f o r t h e tower i n t e r f e r e n c e s t u d y and wind p r o f i l e mapping program from t h e 150-meter m e t e o r o l o g i c a l tower a t Kennedy Space C e n t e r . �The maintenance and p r e v e n t i v e maLntenance performed on t h e tower d u r i n g t h i s p e r i o d i n c l u d e d r e o r i e n t a t i o n o f a l l s e n s o r s and i n s t a l l a t i o n of n y l o n b u s h i n g s on t h e s e n s o r mounts on t h e cross-arms The n y l o n b u s h i n g s were i n s t a l l e d i n a n e f f o r t t o e l i m i n a t e c o r r o s i o n of t h e s e n s o r h o u s i n g s and f r e e z i n g t o t h e mounting b a r . levels. B. . Dew c e l l s were mounted a t t h e 3-meter, 60-meter, and 150-meter These w i l l b e used t o measure and r e c o r d dew p o i n t . Space Environment Branch " P r e l i m i n a r y Models and Confidence Envelopes f o r t h e Mars Atmosphere," w r i t t e n by M r . Don K . Weidner was p r e s e n t e d a t t h e second m e e t i n g of T r a j e c t o r i e s , Performance, N a v i g a t i o n and Guidance Working Group (Voyager) and a t t h e June 21, 1967, Voyager S c i e n c e P a n e l m e e t i n g . The model atmospheres p r e s e n t e d i n t h i s paper have been developed f o r u s e i n t h e s p a c e c r a f t d e s i g n and p l a n n i n g of t h e Voyager program. F u r t h e r s t u d y i n t h i s a r e a w i l l p r o v i d e model atmospheres t h a t d e f i n e t h e s e a s o n a l , l a t i t u d i n a l , and d i u r n a l v a r i a t i o n s i n t h e Mars atmosphere and a l s o w i l l c o n s i d e r t h e e f f e c t of s o l a r c y c l e v a r i a t i o n s i n t h e upper a t m o s p h e r e . I n g e n e r a t i n g t h e models, a h i g h l y r e f i n e d p l a n e t a r y atmosphere computer program t h a t may be used f o r any p l a n e t a r y atmosp h e r e was d e v e l o p e d . T h e o r e t i c a l s t u d i e s c o n c e r n i n g t h e f e a s i b i l i t y of o b t a i n i n g p l a n e t a r y a t m o s p h e r i c informati.on through vacuum chamber s i m u l a t i o n e x p e r i m e n t a t i o n a r e c o n t i n u i n g . The most promising p o t e n t i a l e x p e r i ments s t u d i e d t h u s f a r a r e r e l a t e d t o (1) r e a c t i o n r a t e s f o r t h e v a r i o u s a t m o s p h e r i c chemical p r o c e s s e s , (2) t h e time c o n s t a n t f o r C02 s u b 1 i m a t i o n i n t h e M a r t i a n atmosphere, and (3) t h e r e l a t i o n s h i p between t e m p e r a t u r e and c o m p o s i t i o n i n t h e upper atmosphere. The r e s u l t s of t h e s e s t u d i e s w i l l b e used i n d e v e l o p i n g more r e f i n e d p l a n e t a r y atmospheres. A h i g h l y r e f i n e d computer program h a s been e s t a b l i s h e d f o r g e n e r a t i n g p l a n e t a r y atmospheres. Further s t u d i e s r e l a t e d t o p l a n e t a r y atmospheric processes w i l l provide a d d i t i o n a l refinements. A preliminary summary of t h i s computer program i s g i v e n i n R-AERO-IN-5-67. I n f o r m a t i o n r e s u l t i n g from s t u d i e s c o n c e r n i n g t h e r e l a t i o n s h i p s between c o m p o s i t i o n and t e m p e r a t u r e a t h i g h a l t i t u d e s i n p l a n e t a r y a t m o s p h e r e s h a s been used i n t h e development of more r e f i n e d M a r t i a n a t m o s p h e r i c models. These models a r e p r e s e n t e d i n TI4 X-53616, " N a t u r a l Environment Design C r i t e r i a G u i d e l i n e s f o r MSFC Voyager S p a c e c r a f t f o r Mars 1973 M i s s i o n , ' ' which w i l l be d i s t r i b u t e d i n August 1967. T h i s document was developed f o r t h e MSFC Voyager Phase C RFR, b u t t h e r e i s some chance t h a t i t w i l l b e adopted f o r t h e e n t i r e Voyager program by t h e Voyager P r o j e c t O f f i c e . �M r . Robert B. Owen s u p e r v i s e d the f i n a l acceptance t e s t s of tlic cryogcnic d c n s i t o m e t e r . The f i n a l r e p o r t on t h e development of t h i s gilugc i s due t h c f i r s t .i~eelcof August 1967; t h e gauge i t s e l f w i l l bc d c l i v c r e d a t a l a t e r d a t e . Two papers on the r e s i l l t s of t h e thermosphere probe launches i n January 1967 have been prepared and a r e scheduled t o be p r e s e n t e d a t the COSPAR meeting i n London t h e l a s t week of J u l y . One paper conc e r n s t h e n e u t r a l p a r t i c l e measurements, w h i l e t h e o t h e r concerns t h e charged p a r t i c l e measurements. Both s e r i e s of measurements i n d i c a t e g r e a t e r v a r i a b i l i t y i n t h e upper atmosphere than c u r r e n t models p r e d i c t . Measurements of n e u t r a l molecular n i t r o g e n a r e s t i l l a f a c t o r of two o r t h r e e lower than v a l u e s computed from models based on d e n s i t i e s deduced from the a n a l y s i s of s a t e l l i t e o r b i t a l decay. Progress on s t u d i e s of t h e f e a s i b i l i t y of performing gass u r f a c e i n t e r a c t i o n experiments i n f l i g h t continues t o be s a t i s f a c t o r y . A l l t h r e c c o n t r a c t s a r e planned t o be concluded on 20 August 1967. F u t u r e p l a n s , a t t h e p r e s e n t time, a r e f o r a c o n t i n u a t i o n i n t o a Phase B s t u d y of a s p e c i f i c f l i g h t experiment which w i l l combine t h e r c s u l t s of t h e s e t h r e e Phase A s t u d i e s . The model C4 ionosonde from Cape Kennedy t h a t i s t o be used i n t h e s tudy on I o n o s p h e r i c Disturbances Associated w i t h S t a t i c T e s t F i r i n g s has a r r i v e d and i s being t e s t e d b e f o r e i n s t a l l a t i o n i n a modified van s o t h a t t h e equipment can be used a t b o t h MSFC and Cape Kennedy a s r e q u i r e d . A n t i c i p a t e d d a t e f o r t h i s equipment t o go i n t o o p e r a t i o n i s now about August 1 5 , 1967. N e g o t i a t i o n s f o r the a c o u s t i c g r a v i t y wave experimental program have been completed and s i t e equipment i s now being modified and i n s t a l l e d . Thc c r y s t a l c o n t r o l o s c i l l a t o r s a r e being mounted s o t h a t any and a l l combinations of the t h r e e f r e q u e n c i e s may be used. A d d i t i o n a l f a n s a r e being i n s t a l l e d i n t h e t r a n s m i t t e r s f o r temperature c o n t r o l . The antenna tower bases a t b o t h NASA s i t e 1.ocations have been poured, and communicat i o n s equipment and commercial power l i n e s have been i n s t a l l e d . The antenna towers a r e a t t h e s i t e s and w i l l be e r e c t e d w i t h i n t h e n e x t two t o t h r e e weeks. P r e l i m i n a r y a n a l y s i s of s i n g l e s i t e d a t a has proved somewhat i n c o n c l u s i v e f o r t h e p o s i t i v e i d e n t i f i c a t i o n of t r a v e l i n g i o n o s p h e r i c d i s t u r b a n c e s (TIDs) following s t a t i c t e s t f i r i n g s The i n c l u s i o n of two a d d i t i o n a l s i t e s may improve t h i s s i t u a t i o n , b u t t h e ionosonde r e c o r d s should be of g r e a t h e l p i n i d e n t i f y i n g s m a l l s c a l e disturbances. The equipment i s a l s o being r e t r o f i t t e d s l i g h t l y t o i n c l u d e a means of measuring phase p a t h d i r e c t l y i n s t e a d of t h e r a t e of change of phase. There i s a l s o t h e p o s s i b i l i t y of o b t a i n i n g a pulsed-phase sounder which would provide e x c e l l e n t and e x t e n s i v e phase p a t h r e c o r d s t h a t now appear t o be n e c e s s a r y t o t h e s t u d y . . �S o l a r F l a r e P r o b a b i l i t ~ rModels: Methods of developing probable f l u x energy s p e c t r a f o r s o l a r f l a r e s a r e being s t u d i e d . Our c u r r e n t method r e s u l t s i n a t o t a l f l u x model f o r missions l a s t i n g n days. I n a d d i t i o n , we have been examining t h e occurrence of s o l a r f l a r e s i n r e l a t i o n t o tlle g i v e n s o l a r f l a r e index v a l u e s . T e s t s run s o f a r have i n d i c a t e d t h a t a r e l i a b l e long range (up t o one y e a r ) p r e d i c t i o n technicli~cmay be found f o r l a r g e s o l a r f l a r e s . More information on t h i s s cllcme w i l l be forthcoming . C. T e r r e s t r i a l Environment Branch 1. Reports a . "Revised Wind S t a t i s t i c s f o r Apollo S p a c e c r a f t Abort S t u d i e s , " O f f i c e Memorandum R-AERO-YT-19-67, June 1 , 1967. b. 11A Comparison of Shroud Length S t u d i e s Versus 10-14 km Wind P r o b a b i l i t i e s f o r Saturn V/Voyager , I 1 Off i c e Memorandum R-AERO-YT21-67, June 2, 1967. c. "Frequency D i s t r i b u t i o n s of t h e L a r g e s t Monthly and t h e L a r g e s t Yearly Mean R e l a t i v e Sunspot Numbers," O f f i c e Memorandum R-AERO-YT-24-67, June 19, 1967. . d "Frequency Dis t r i b u t i o n s of t h e L a r g e s t Monthly and t h e L a r g e s t Yearly Mean R e l a t i v e Sunspot Numbers," O f f i c e Memorandum I<-AERO-YT-25-67, June 19, 1967. 2 . A computer program i s being prepared f o r the t h e o r y of extreme v a l u e s developed by t h e l a t e E. J . Gumbel f o r use i n g e n e r a t i o n of t h e o r e t i c a l p r o b a b i l i t i e s of encountering v a r i o u s atmospheric cons t r a i n t s f o r S a t u r n v e h i c l e launches and o p e r a t i o n s a t Cape Kennedy, Florida. D . Environmental A p p l i c a t i o n s Branch 1. MSFC1s M e t e o r o l o g i c a l Tower I n t e r f e r e n c e Program A d r a f t of a r e p o r t on t h e o r e t i c a l flow t h e o r y f o r wind flow a b o u t NASA's 150-meter m e t e o r o l o g i c a l tower was r e c e i v e d from t h e c o n t r a c t o r (Boeing Co., H u n t s v i l l e , Ala. ) on June 22, 1967. R-AERO-YE personnel reviewed t h e r e p o r t , and comments were r e l a y e d t o t h e Boeing personnel i n a meeting on J u l y 6 , 1967. It i s expected t h a t t h e t h e o r e t i c a l flow t h e o r y r e p o r t w i l l be made a n appendix t o t h e tower i n t e r f e r e n c e document t o be published soon. �2. Turbulence C h a r a c t e r i s t i c s of NASA's 150-Meter Meteorological Tower Data Data now being a c q u i r e d a t NASA's 150-meter m e t e o r o l o g i c a l tower, 1<SC, Fl oricla, c o n s t i t u t e l>otli r o u t i n e measurements of wind v e l o c i t y , temperature, and o t h e r atmospheric v a r i a b l e s , a s w e l l a s s p e c i a l measurements of wind speed f o r t h e s t u d y of t u r b u l e n c e c h a r a c t e r i s t i c s . So f a r , t h i r t y hours of s p e c i a l wind measurements have been a c q u i r e d and s t o r e d on computer tapes a t t h e MSFC Computation Laboratory. Computer programs a r e being developed, i n a d d i t i o n t o e x i s t i n g programs, t o p r o c e s s t h e s e d a t a s o t h a t they may be analyzed by t h e Environmental A p p l i c a t i o n s Branch (R-AERO-YE) and by t h e Pennsylvania S t a t e U n i v e r s i t y under C o n t r a c t NAS8-21140. These t u r b u l e n c e d a t a have been presented t o v a r i o u s personnel of MSFC. This p r e s e n t a t i o n concerned t h e s p e c t r a l n a t u r e of t u r b u l e n c e and t h e a n a l y s i s of g u s t f a c t o r . 3. Gust Factor Analysis The memorandum R-AERO-YE-10-67, "Some Observed Wind P r o f i l e C h a r a c t e r i s t i c s from NASA' s 150-m Meteorological Tower, KSC, F l o r i d a , " dated February 8 , 1967, presented p r e l i m i n a r y r e s u l t s of a n a n a l y s i s r e l a t i n g g u s t f a c t o r t o h e i g h t and mean wind speed. A more d e t a i l e d a n a l y s i s t o determine the g u s t f a c t o r t o a h e i g h t of 150 meters was p r e s e n t e d i n memorandum R-AERO-YE-51-67, "Gust F a c t o r Analysis from Wind Data Measured d u r i n g September 1966 a t NASA'S 150-m Meteorological Tower F a c i l i t y , ICSC, F l o r i d a , " dated June 8 , 1967. From t h i s a n a l y s i s , i t can be concluded t h a t t h e g u s t f a c t o r d e c r e a s e s w i t h h e i g h t and i n c r e a s i n g wind speed and t h a t a g u s t f a c t o r of 1 . 4 i s a r e p r e s e n t a t i v e d e s i g n v a l u e f o r winds from t h e ground t o 150 m e t e r s . The a n a l y s i s of t h e g u s t f a c t o r i s c o n t i n u i n g f o r o t h e r months of d a t a and v a r i o u s time-averaging p e r i o d s usecl t o d e f i n e t h e mean wind speed. 4. NASAIASCE V i s i t t o NASA-Langley Research Center M r . John IJ. Kaufman, R-AERO-YE, a t t e n d e d and p a r t i c i p a t e d i n a meeting on wind loads on l a r g e s t r u c t u r e s a t NASA-Langley Research Center, Langley S t a t i o n , Hampton, V i r g i n i a , on June 1 4 , 1967. Personnel of t h e A e r o e l a s t i c i t y Branch of LRC and members of t h e American S o c i e t y of C i v i l E n g i n e e r s , S t r u c t u r a l D i v i s i o n , sponsored t h e meeting. M r . Kaufman gave a b r i e f p r e s e n t a t i o n of NASA's 150-m M e t e o r o l o g i c a l Tower F a c i l i t y which i s l o c a t e d on M e r r i t t I s l a n d a t Cape Kennedy. This pres e n t a t i o n cons i s ted of a review of t h e tower f a c i l i t y and t h e type of lower atmospheric d a t a being measured. Much d i s c u s s i o n followed t h e p r e s e n t a t i o n because of t h e g r o u p ' s i n t e r e s t i n lower atmospheric c r i t e r i a which can commonly occur a t t h e Saturn v e h i c l e launch s i t e . �5. Space A p p l i c a t i o n s Summer S t u d y Program M r . K e l l y H i l l a t t e n d e d t h e Space A p p l i c a t i o n s Summer S t u d y Program on J u n e 27-28, 1967 a t t h e N a t i o n a l Academy o f S c i e n c e s i n Woods Hole, M a s s a c h u s e t t s . M r . H i l l , R-AERO-YE, and M r . Ted P a l u d a n , R-ASTR-IM, r e p r e s e n t e d MSFC a s o b s e r v e r s a t t h e g e n e r a l b r i e f i n g s by NASA's Program Managers on OSSA programs. P a n e l p a r t i c i p a n t s i n t h i s s t u d y i n c l u d e d s c i e n t i s t s , e n g i n e e r s and o t h e r e x p e r t s i n f i e l d s r e l a t e d t o m e t e o r o l o g y , e a r t h r e s o u r c e s , geodesy and s e n s o r s f o r s p a c e a p p l i c a t i o n . D r . M o r r i s T e p p e r , D i r e c t o r , OSSA M e t e o r o l o g i c a l Programs, s t a t e d t h a t a l l m e t e o r o l o g i c a l e x p e r i m e n t s i n t h e T i r o s and Nimbus programs a r e a p p r o v e d . Although s u r v e y s a r e b e i n g made, no m i s s i o n h a s b e e n approved f o r t h e e a r t h resources experiments. 6. J i m s p h e r e Temperature S e n s o r Program D r . James R . Scoggins and M r . Dennis W . Camp v i s i t e d GCA C o r p o r a t i o n , Bedford, M a s s a c h u s e t t s , on J u l y 11-12, 1967, t o d i s c u s s t h e c o n t r a c t (NAS8-20588) under which t h e J i m s p h e r e t e m p e r a t u r e s e n s o r i s b e i n g d e v e l o p e d , and t o w i t n e s s a f l i g h t d e m o n s t r a t i o n o f t h e s e n s o r . Problems w i t h b a t t e r i e s , b a l l o o n - b o r n e a n t e n n a , and s e n s o r c a l i b r a t i o n a r e s t i l l p l a g u i n g t h e development o f t h e t e m p e r a t u r e s e n s o r . The f l i g h t t e s t of t h e s e n s o r was p a r t i a l l y s u c c e s . ; f u l , and t h e r e were i n d i c a t i o n s t h a t t h e s e n s o r could b e made t o p e r f o r m s a t i s f a c t o r i l y . Work i s c o n t i n u i n g , a t t h e GCA C o r p o r a t i o n , on t h e t e m p e r a t u r e s e n s o r . V. ASTRODYNAMICS AND GUIDANCE THEORY DIVISION A. O p t i m i z a t i o n Theory Branch 1. Voyager a. Launch V e h i c l e A t t i t u d e C o n t r o l S t u d i e s An Aero I n t e r n a l Note g i v i n g l a u n c h p r o b a b i l i t y v e r s u s wind s p e e d f o r S a t u r n ~ / ~ o y a g ev re h i c l e u s i n g a n a t t i t u d e c o n t r o l s y s t e m is b e i n g p r e p a r e d f o r p u b l i c a t i o n . The l a u n c h p r o b a b i l i t y i s b a s e d on t h e time d u r i n g a g i v e n l a u n c h p e r i o d t h a t a n a l l o w a b l e windspeed w i l l n o t b e exceeded. The a l l o w a b l e wind h a s b e e n d e t e r m i n e d as a f u n c t i o n of s h r o u d l e n g t h , and i s c o r r e l a t e d w i t h t h e wind l e v e l p r o b a b i l i t y f o r t h e g i v e n l a u n c h windows. b. Launch V e h i c l e Load R e l i e f S t u d i e s (NAS8-21171) - Honeywell O b j e c t i v e : To improve t h e performance of t h e l o a d r e l i e f c o n t r o l s y s t e m f o r t h e S a t u r n V l ~ o y a g e rd e s i g n e d by Honeywell under NAS8-11206. �Work under t h e c o n t r a c t began on June 27, 1967. I n i t i a l e f f o r t s have c e n t e r e d on t h e c o o r d i n a t i o n of t h e ground r u l e s of t h e s t u d y , t r a n s m i s s i o n of t h e r e f e r e n c e d a t a , and p r e p a r a t i o n of computer programs. c. S p a c e c r a f t A t t i t u d e Control A r i g i d body parameter s t u d y d i r e c t e d toward t h e prel i m i n a r y f u n c t i o n a l d e s i g n of t h e Voyager s p a c e c r a f t unpowered f l i g h t a t t i t u d e c o n t r o l system has been documented. Further s t u d i e s a r e being made t o examine t h e low-g s l o s h e f f e c t s on t h i s mode of c o n t r o l . d. Lockheed - Schedule Or,der /I45 Coordination meetings were h e l d w i t h Lockheed personnel t o o u t l i n e t h e i r r e s p o n s i b i l i t i e s a s t h e members of t h e s u p p o r t cont r a c t o r team f o r Voyager launch v e h i c l e and s p a c e c r a f t c o n t r o l s t u d i e s . Lockheed i s reviewing t h e a v a i l a b l e i n £orma t i o n t o i d e n t i f y problem a r e a s and t o develop schedules f o r t h e programs under c o n s i d e r a t i o n . e. Northrop (1) - Schedule Order /I45 Shroud S e p a r a t i o n Study O b j e c t i v e : Determination of t h e r e l a t i v e t r a j e c t o r i e s of t h e two s p a c e c r a f t , a f t shroud, and S-IVB f o l l o w i n g s e p a r a t i o n in interplanetary transfer orbit. A p r e l i m i n a r y s t u d y of t h e a n g u l a r displacements of t h e f o u r bodies w i t h r e f e r e n c e t o t h e o r i g i n a l v e l o c i t y v e c t o r r e s u l t ing from i n s t a n t a n e o u s , s e q u e n t i a l s e p a r a t i o n of t h e forward s p a c e c r a f t , a f t shroud, and a f t s p a c e c r a f t a t d i f f e r e n t i n e r t i a l a n g l e s and d i f f e r e n t s e p a r a t i o n v e l o c i t i e s has been completed. From t h i s , d e s i r a b l e o r i e n t a t i o n of t h e S-IVB and minimum s e n s i t i v i t y of t h e o r i e n t a t i o n s t o v a r i a t i o n s i n t h e s e p a r a t i o n v e l o c i t i e s . The s t u d y i s proceeding t o i n c l u d e 3 - D e f f e c t s , f i n i t e times between s e p a r a t i o n s , e f f e c t of r e s i d u a l a n g u l a r r a t e s i n l i m i t c y c l e o p e r a t i o n of t h e S-IVB APS, and d e t e r m i n a t i o n of t h e v e l o c i t y v e c t o r s and p o s i t i o n s of t h e f o u r bodies two t o f i v e days a f t e r s e p a r a t i o n ( a t t h e time of t h e f i r s t midcourse c o r r e c t i o n ) . (2) Spacecraft T h r u s t Vector Control O b j e c t i v e : To d e s i g n and a s s e s s t h e performance of t h r u s t v e c t o r c o n t r o l systems f o r t h e Voyager which o p e r a t e d u r i n g p r o p u l s i v e maneuvers. It was p r e v i o u s l y r e p o r t e d t h a t p r e l i m i n a r y s t u d i e s showed t h a t t h e use of simple a t t i t u d e l a t t i t u d e - r a t e feedback would n o t meet performance requirements i n t h e presence of expected CG o f f s e t s and �. and t h r u s t misalignments F u r t h e r examination has sholan t h a t t h i s r e s u l t i s h i g h l y s e n s i t i v e t o t h e magnitude of CG o f f s e t and t h e t h r u s t lnisalignment assumed For t h e s m a l l e r CG o f f s e t s and t h r u s t m i s a l ignments used by t h e s p a c e c r a f t c o n t r a c t o r s , a t t i t u d e c o n t r o l i s s u f f i c i e n t ; t h i s a g r e e s w i t h t h e conclusions of t h e c o n t r a c t o r s . The q u e s t i o n a s t o wlm t a r e d e s i g n CG o f f s e t s and t h r u s t misalignments should be r e s o l v e d . . 2. T r a j e c t o r y Optimization a . Work on t h e t r a n s f o r m a t i o n of t h e Hamiltonian which d e s c r i b e s t h e optimal t r a j e c t o r y of a r o c k e t i n a p u r e l y K e p l e r i a n g r a v i t a t i o n a l f i e l d i s c o n t i n u i n g . Numerical c a l c u l a t i o n s i n d i c a t e d t h a t a b a s i c problem i n t h e t r a n s f o r m a t i o n e x i s t e d . Consequently, a second t r a n s f o r m a t i o n technique (due t o Hunt) i s being a p p l i e d . I f d i f f e r e n t r e s u l t s a r e obtained from t h e s e p a r a t e methods, s t u d i e s of t h e r e a s o n s Tor t h e s e d i f f e r e n c e s w i l l be made. Improved techniques f o r a n e c e s s a r y i n t e r p o l a t i o n r o u t i n e have been developed. Work on improved numerical i n t e g r a t i o n techniques i s now under way. b. A new problem, which t r e a t s t h e s u p e r p o s i t i o n of a p l a n a r f o r c e f i e l d over a K e p l e r i a n f i e l d , i s being considered. This problem has been solved a n a l y t i c a l l y by s e p a r a t i o n of t h e HamiltonJ a c o b i e q u a t i o n i n p a r a b o l i c c o o r d i n a t e s . Numerical c a l c u l a t i o n s on t h e SDA 930 computer have been coupled w i t h a Calcomp p l o t t e r . This procedure r e s u l t s i n immediate v i s u a l d i s p l a y of d i f f e r e n c e s due t o changes i n i n i t i a l c o n d i t i o n s of s t r e n g t h of t h e p l a n a r f i e l d . c. Northrop - Schedule Order #32 O b j e c t i v e : To determine t h e a p p l i c a b i l i t y of funct i o n a l a n a l y s i s t o t h e o p t i m i z a t i o n of a e r o s p a c e v e h i c l e t r a j e c t o r i e s . The computer program which uses f u n c t i o n a l a n a l y s i s and i s capable of handling optilnum bang-bang c o n t r o l o p t i o n s has been checked o u t . S t u d i e s on s o l v i n g two-point boundary v a l u e problems, i n t h e l a r g e , f o r bang-bang c o n t r o l have been i n i t i a t e d . T h e o r e t i c a l s t u d i e s f o r improving convergence a r e s t i l l i n p r o g r e s s . Future work w i l l i n c l u d e completion of t h e p r e s e n t numerical s t u d i e s . Dependent upon t h e s e r e s u l t s , f u t u r e work w i t h more complex p h y s i c a l models w i l l be i n i t i a t e d . d. North American A v i a t i o n (NAS8-21077) Orb j e c t i v e : To d e v e l o p methods of f i n i t e t h r u s t optimal t r a n s f e r . The two-body, three-dimensional q u a s i - l i n e a r program i s b e i n g checked o u t on t h e IBM 360165. Major r e v i s i o n s of c e r t a i n �s u b r o u t i n c s have bccn r e q u i r e d . Runs a r e now being made on t h e impulsive t r a n s f e r i n t h e r e s t r i c t e d three-body model. Programming on t h e f i n i t e t h r u s t , two-dimensional two-body problem i s continuing. 3. F l i g h t Control a. Cornell (NAS8-18054) O b j e c t i v e : To determine t h e f e a s i b i l i t y of a p p l y i n g optimal c o n t r o l theory t o t h e s y n t h e s i s of launch v e h i c l e c o n t r o l systems. P r e l i m i n a r y copies of t h e f i n a l r e p o r t have been r e c e i v e d A f t e r minor r e v i s i o n , t h e r e p o r t w i l l be d i s t r i b u t e d w i t h a cover memo o u t l i n i n g t h e r e s u l t s of t h e s t u d y . b. Boeing (NAS8-21070) O b j e c t i v e : To s t u d y t h e a p p l i c a t i o n of t h e S a t u r n V/ Voyager load r e l i e f system and o t h e r load r e l i e f sys tems t o t h e S a t u r n V/ Apollo. The rigid-body, f r o z e n c o e f f i c i e n t analog s t u d y i s comp l e t e and a hybrid s t u d y of t h e f l e x i b l e , time-varying v e h i c l e i s being initiated. Three systems have been s e l e c t e d f o r f u r t h e r study: normal a c c e l e r a t i o n c o n t r o l , which y i e l d e d a 2 1 p e r c e n t r e d u c t i o n i n pcalc l o a d s compared w i t h a t t i t u d e c o n t r o l ; t h e system developed by A s t r i o n i c s w i t h a 25 p e r c e n t load r e d u c t i o n ; and a system w i t h s a t u r a t ing elements i n t h e load r e l i e f loop ( e i t h e r of t h e above) which reduced t h c load by 30 p e r c e n t . These f i g u r e s a r e f o r t h e r i g i d body s t u d y and the Apollo d e s i g n wind peaking a t max qa. O b j e c t i v e : To f u r t h e r i n v e s t i g a t e t h e a p p l i c a t i o n of t h e s t a t i s t i c a l o p t i m i z a t i o n technique developed under NAS8-11206. Under t h i s c o n t r a c t , f l e x i b l e - b o d y e f f e c t s w i l l be c o n s i d e r e d , some t h e o r e t i c a l a s p e c t s of t h e technique w i l l be inves tig a t e d , and t h e e f f e c t of parameter v a r i a t i o n s w i l l be c o n s i d e r e d . The c o n t r a c t o r was i n s t r u c t e d t o use t h e S a t u r n V/ Voyager a s h i s s t u d y v e h i c l e because of t h e p o t e n t i a l a p p l i c a t i o n of Since t h e c o n t r a c t o r t h i s technique t o t h e Voyager load r e l i e f problem. MV #2 d a t a , f o r which he had d a t a i n t h e n e c e s s a r y form, t o u s e expected he did n o t i n c l u d e d a t a r e d u c t i o n i n t h e c o s t e s t i m a t e . However, a n o t h e r Honeywell d i v i s i o n i s d e s i g n i n g a c u r r e n t l y f e a s i b l e l o a d - r e l i e f c o n t r o l �system f o r t h e Voyager under NAS8-21171 ( s e e above) and i s having t o do s i m i l a r d a t a r e d u c t i o n , which was included i n t h e i r c o s t e s t i m a t e . To avoid d u p l i c a t i o n of e f f o r t and t o avoid i n c r e a s e d funding, t h e inves t i g a t o r on NAS8-21063 has stopped working on t h e c o n t r a c t t o t a k e advantage of the d a t a r e d u c t i o n being performed under NAS8-21171, and w i l l resume e f f o r t s upon completion of t h e d a t a r e d u c t i o n . A r e q u e s t f o r e x t e n s i o n of t h e c o n t r a c t a t no a d d i t i o n a l c o s t has been submitted by t h e contractor. B . As t r o d ynamics Branch I n t e r p l a n e t a r y Trans i t S t u d i e s (In-House) 1. a . Work on t h e g e n e r a t i o n of t h e n i n e t r a j e c t o r i e s f o r use i n Voyager p r e l i m i n a r y design s t u d i e s has been slowed somewhat by problems w i t h the i s o l a t i o n r o u t i n e being used. S i x t r a j e c t o r i e s have been s u c c e s s f u l l y i s o l a t e d ; i t i s planned t o p u b l i s h t h e s e s i x w h i l e work c o n t i n u e s on i s o l a t i n g t h e o t h e r t h r e e . b . I n g e n e r a l m i s s i o n a n a l y s i s s t u d i e s , p l o t s have been completed showing t r a n s f e r t r a j e c t o r i e s f o r t h e 1975, 77, and 79 launch opportunities. The t r a j e c t o r i e s were s e l e c t e d t o show v a r i a t i o n s i n t r a n s f e r geometry which might b e expected a s a r e s u l t of v a r i a t i o n s i n e a r l y and l a t e launch and a r r i v a l d a t e s . Charts and graphs have been generated and assembled which w i l l a l l o w d e t e r m i n a t i o n of c o a s t times needed f o r Type I t r a j e c t o r i e s f o r 1973, 75, 7 7 , and 79 and a l s o Type I1 t r a j e c t o r i e s f o r 1975 and 1977. c. A program has been developed f o r use on t h e 1130 comp u t e r which w i l l g e n e r a t e i n t e r r e l a t e d parameters a s s o c i a t e d w i t h t r a d e o f f s t u d i e s on Mars o r b i t s i z i n g . The s t u d y i s intended t o produce t r a d e o f f s which can be made w i t h r e s p e c t t o o r b i t s i z e , a r r i v a l energy, and o r b i t i n s e r t i o n AV requirements. This should provide a n easy method f o r s t u d y i n g t r a d e - o f f s between s c i e n t i f i c and e n g i n e e r i n g cons t r a i n t s . d . An a n a l y s i s of t h e two main s e c u l a r p e r t u r b a t i o n s ( t h e motion of t h e l i n e of a p s i d e s and t h e motion of t h e argument of p e r i a p s i s ) on t h e o r b i t a l p a t h of a s a t e l l i t e of Mars due t o t h e Martian o b l a t e n e s s has been conducted, and t h e r e s u l t s published. A l t i t u d e s a t p e r i a p s i s range from 1000 t o 5000 k i l o m e t e r s , and a l t i tudes a t a p o a p s i s range from 2000 t o 20,000 k i l o m e t e r s . 2. I n t e r p l a n e t a r y T r a n s i t S t u d i e s (Support C o n t r a c t o r ) a . Work has continued on t h e g r a p h i c a l p r e s e n t a t i o n of d a t a d e f i n i n g t h e e a r t h launch windows and e a r t h parking o r b i t r e q u i r e ments f o r t h e 1973, 1975, 1977, and 1979 launch o p p o r t u n i t i e s f o r Mars miss ions u s i n g Type I i n t e r p l a n e t a r y t r a n s f e r s . �b. A computer program has been developed by LMSCIHREC f o r de tcrmining t h e o c c u l t a t i o n c h a r a c t e r i s t i c s of v a r i o u s Mars s a t e l l i t e o r b i t s and i s being checked o u t . The program uses a s i n p u t s t h e s i x o r b i t a l elements ( a , e , i, 11, i i , and To) which d e f i n e t h e d e s i r e d Mars s a t e l l i t e o r b i t , and t h e l a t e s t times of p e r i c e n t e r passage of t h e e a r t h and sun p r i o r t o t h e epoch d a t ~To. A l l of t h e s e elements a r e d e f i n e d r e l a t i v e t o a Mars e q u a t o r i a l c o o r d i n a t e system. P l o t r o u t i n e s have been included which p l o t t h e l a t i t u d e - l o n g i t u d e h i s t o r i e s of the o r b i t e r , d e f i n i n g t h e r e g i o n s i n which t h e e a r t h , sun, and Canopus a r e o c c u l t e d . Thus, t h i s computer program i s designed t o permit t h e r a p i d c a l c u l a t i o n and g r a p h i c a l p r e s e n t a t i o n of t h e o c c u l t a t i o n c h a r a c t e r i s t i c s f o r a wide range of Mars s a t e l l i t e o r b i t parameters. c . Work has continued on t h e a n a l y s i s of broken-plane t r a n s f e r s i n a n e f f o r t t o determine t h e f e a s i b i l i t y of modifying some oE t h e o p e r a t i o n a l s i n g l e - p l a n e computer programs t o c o n s i d e r t h e broken-plane cases when near-180-degree h e l i o c e n t r i c t r a n s f e r s a r e encountered. d. I n a d d i t i o n t o t h e optimal t r a n s f e r of a v e h i c l e from a n incoming h y p e r b o l i c o r b i t t o a n e l l i p t i c o r b i t a b o u t Mars, t h e problem of o p t i m a l l y t r a n s f e r r i n g a v e h i c l e from a s l i g h t l y e c c e n t r i c parking o r b i t t o a n outgoing h y p e r b o l i c o r b i t w i t h a g i v e n a s y m p t o t i c v e l o c i t y i s being i n v e s t i g a t e d . To o b t a i n s u f f i c i e n t l y simple equat i o n s , c e r t a i n approximations t o t h e f u e l optimal t r a n s f e r were cons i d e r e d . P r e l i m i n a r y a n a l y s e s have been performed t o f i n d convenient approximations f o r s o l v i n g t h e r e l e v a n t system of e q u a t i o n s . e . Copies of t h e r e p o r t documenting t h e v a r i o u s f l i g h t parameters f o r Type I1 Earth-Mars t r a j e c t o r i e s i n t h e 1973-1979 time period have been r e l e a s e d and a r e now being reviewed. f . The c o n s t a n t energy, f l i g h t parameter p l o t s f o r e n e r g i e s up t o 40 km2/sec2 d u r i n g t h e 1973-1979 time period have been completed and a r e being reviewed. 3. United A i r c r a f t Corporation (NAS~-21091) The l i t e r a t u r e s e a r c h phase of t h e Impulsive T r a n s f e r Study c o n t r a c t i s almost complete w i t h a c u r r e n t l i s t i n g of a p p r o x i m a t e l y 300 e n t r i e s ; a p r e l i m i n a r y c l a s s i f i c a t l o n of impulsive t r a n s f e r t o p i c s i s being d r a f t e d . This c l a s s i f i c a t i o n w i l l undoubtedly be subs t a n t i a l l y a l t e r e d b e f o r e r e a c h i n g i t s f i n a l form. However, i t can s e r v e a s a s t a r t i n g p o i n t i n t h e c l a s s i f i c a t i o n phase of t h e c o n t r a c t . �C. Guidance Theory Branch I. Si~pport Contract S t u d i c s a. Voyager P r o j e c t Support S t u d i e s P o s s i b l e use of t h e Voyager P l a n e t a r y Vehicle a s a "kick" s t a g e t o o b t a i n h i g h e r i n j e c t i o n e n e r g i e s i s being s t u d i e d . The h i g h e r i n j e c t i o n e n e r g i e s would r e s u l t i n longer launch o p p o r t u n i t i e s . e f f e c t of using the the d r i f t injection A guidance a n a l y s i s i s being conducted t o determine t h e t h e l a r g e r d r i f t and d r i f t r a t e s t h a t occur a s a r e s u l t of load r e l i e f c o n t r o l system d u r i n g high winds. The e f f e c t of and d r i f t r a t e s w i l l be determined i n terms of payload and accuracy. Power S e r i e s S o l u t i o n f o r I n i t i a l Lagrange Mu1 t i p l i e r s b. The r e s u l t s of t h i s s t u d y a r e being documented. c. Quasi-Optimal Guidance Study S i m p l i f i e d guidance s i m u l a t i o n s t u d i e s have been undertaken. The scheme works extremely w e l l f o r t y p i c a l c u t o f f s u r f a c e s s u c h a s r , v , 0, i. P r e s e n t l y , a burn-coast-burn o r b i t a l t r a n s f e r c a p a b i l i t y i s b e i n g developed and checked o u t . 2. Contracts a. Vanderbil t U n i v e r s i t y Work has continued on o b t a i n i n g s u f f i c i e n t c o n d i t i o n s f o r t h e extended m u l t i s t a g e Bolza problem w i t h i n e q u a l i t y c o n s t r a i n t s and c o n t r o l v a r i a b l e s . This work has been d i r e c t e d toward f i n d i n g a f o u r t h n e c e s s a r y c o n d i t i o n i n a computationally u s a b l e form. b . Lockheed-Rendezvous Guidance Equations c o r r e c t through f i r s t o r d e r a r e being programmed f o r t h e f i r s t burn. A s e n s i t i v i t y a n a l y s i s of t h e e q u a t i o n s f o r t h e second burn i n d i c a t e t h a t b o t h t h r u s t d i r e c t i o n and magnitude need t o be c o n t r o l l e d t o ensure near-optimum rendezvous. c . General P r e c i s i o n The guidance s i m u l a t i o n computer program developed by General P r e c i s i o n has been used a l o n g w i t h t h e IGM guidance package s u b r o u t i n e t o determine on what type of t r a j e c t o r i e s t h e IGM e q u a t i o n s �a r e inadequate. Also, t h e implementation of t h e quasi-optimal c o n t r o l technique i s n e a r i n g completion s o t h a t t h i s new approach can be evaluated. 3. In-House S t u d i e s a. Voyager S t u d i e s A s t u d y has been i n i t i a t e d t o determine t h e p o s s i b l e g a i n i n launch o p p o r t u n i t y v i a plane change maneuver w i t h t h e S-IVB. P r e l i m i n a r y r e s u l t s i n d i c a t e t h a t two o r t h r e e e x t r a days of launch o p p o r t u n i t y may b e o b t a i n e d . The impact of t h e h e a v i e r MSFC s p a c e c r a f t weight upon t h e 73-79 launch o p p o r t u n i t i e s i s being s t u d i e d . The Mars o r b i t i n s e r t i o n guidance s t u d y has been expanded t o i n c l u d e o r b i t i n s e r t i o n of up t o 20° away from p e r i a p s i s . b . The closed form s o l u t i o n s f o r t h e s t a t e v a r i a b l e s and t h e Lagrange m u l t i p l i e r s a c r o s s a c o a s t a r c have been i n c o r p o r a t e d i n t o a computer program t h a t i s designed t o compute o r b i t a l t r a n s f e r s . A t p r e s e n t , t h e program i s unable t o i s o l a t e t h e s w i t c h i n g times w i t h s u f f i c i e n t a c c u r a c y t o a c h i e v e ccnvergence. The g e n e r a l i z e d s e c a n t i s o l a t i o n procedure may a l l e v i a t e t h i s problem w i t h o u t having t o use extended p r e c i s i o n f o r the computations. c . Various forms of t h e boundary e q u a t i o n s i n two-point boundary v a l u e problems a r e being i n v e s t i g a t e d . Of t h r e e s e t s of t r a n s v e r s a l i t y c o n d i t i o n s d e r i v e d f o r a C 3 c u t o f f s u r f a c e , t h e s i m p l e s t one w i t h r e s p e c t t o t h e number of a r i t h m e t i c o p e r a t i o n s involved r e q u i r e d o n l y - 6 , t h e number of i t e r a t i o n s of t h e most complicated one. T h i s s i g n i f i c a n t r e d u c t i o n i s p a r t l y due t o decreased t r u n c a t i o n and computer round-off e r r o r s . This idea i s being pursued f o r o t h e r t y p i c a l c u t o f f surfaces t o obtain similar reductions. VI. DYNAMICS AND FLIGHT MECHANICS DIVISION A. Multi-Projects 1. Miss i o n P r o f i l e a. Rendezvous Guidance An a n a l y s i s of t h e guidance and phasing problems a s s o c i a t e d w i t h a c h i e v i n g a dual rendezvous of s p a c e c r a f t s has r e v e a l e d s e v e r a l d i f f i c u l t i e s i n e s t a b l i s h i n g a launch window of any s i g n i f i c a n t �d u r a t i o n f o r t h e planned AAP m i s s i o n s . The a n a l y s i s assumed a p a s s i v e o r b i t a l s p a c e s t a t i o n i n a g i v e n o r b i t and two r e s u p p l y l a u n c h v e h i c l e s i n which one would be manned and t h e o t h e r unmanned. The o p e r a t i o n a l p l a n c a l l c d f o r l a u n c h i n g t h e manned c o n f i g u r a t i o n f i r s t i n t o a low c i r c t t l a r o r b i t (: 120 n.mi.) and l a t e r l a u n c h t h e unmanned v e h i c l e i n t o a n elliptical p l ~ a s i n go r b i t w i t h t h e manned c o n f i g u r a t i o n t r a n s f e r r i n g i n t o Lhe unmanned o r b i t a t a g i v e n p o s i t i o n i n t e r c e p t p o i n t . The manned and unmanned docked c o n f i g u r a t i o n would t h e n a c h i e v e a second rendezvous w i t h t h e o r b i t a l s p a c e s t a t i o n ( 2 240 n.mi. c i r c u l a r ) . I n d i c a t i o n s a r e t h a t t h e performance c r i t i c a l manned c o n f i g u r a t i o n could n o t a c h i e v e t h e r e q u i r e d maneuvers t o g e n e r a t e a l a u n c h window of any s i g n i f i c a n t l e n g t h . The unmanned l a u n c h v e h i c l e was a n a l y z e d f o r e q u i v a l e n t performance t o d e t e r m i n e t h e maximum apogee h e i g h t f o r a f i x e d p e r i g e e h e i g h t of 80 n.mi. t h a t would correspond t o t h e performance r e q u i r e d f o r a g i v e n c i r c u l a r o r b i t . The e q u i v a l e n t performance f o r a 120 n.mi. c i r c u l a r o r b i t gave a maximum apogee h e i g h t o f 230 n.mi. and 1 , 5 0 0 n.mi. f o r a 240 n.mi. circular orbit. ( D G / N ot~h r o p ) b. 6-D E l a s t i c Response S i m u l a t i o n C o n t r a c t NAS8-18005, w i t h General E l e c t r i c f o r a d a p t i v e modular a n a l y s i s i s ended a s of J u l y 28, 1967. The c o n t r a c t work has b e e n t o d e v e l o p a 6-D e l a s t i c r e s p o n s e of t h e l a u n c h v e h i c l e c o n s i d e r i n g coinpensat i o n networks a n d n o n l i n e a r aerodynamics. V e h i c l e l o a d i n g may b e o b t a i n e d f o r m a l f u n c t i o n e d f l i g h t such a s e n g i n e o u t . A f i n a l r e v i e w was h e l d on J u l y 21, 1967, and a rough d r a f t of t h e f i n a l documentation was d e l i v e r e d . A l l of t h e o b j e c t i v e s of t h i s one y e a r c o n t r a c t have (DDD/GE) been accomplished. B. Saturn V 1. Guidance a. S a t u r n V Guidance t o E a r t h Synchronous O r b i t Work has been performed t o d e t e r m i n e t h e optimum i t e r a t i v e g u i d a n c e mode i g n i t i o n time f o r t h r u s t i n g from t h e t r a n s f e r c o n i c i n t o a n e a r t h synchronous o r b i t w i t h a n i n c l i n a t i o n e q u a l t o 28.5 d e g s . P r e l i m i n a r y r e s u l t s i n d i c a t e d t h a t i f apogee r a d i u s of t h e t r a n s f e r c o n i c (Ra) i s v e r y c l o s e t o t h e e a r t h synchronous o r b i t r a d i u s (RESO) , t h e i g n i t i o n time f o r t h e apogee burn was n o t c r i t i c a l . The payload i n e a r t h synchronous o r b i t v a r i e d o n l y s l i g h t l y f o r i g n i t i o n time r a n g i n g from 200 s e c o n d s b e f o r e t o 25 seconds a f t e r apogee p a s s a g e . However, i f R, i s g r e a t e r t h a n RESO, t h e maximum payload i n t o o r b i t was o b t a i n e d by b u r n i n g i n t o t h e f i r s t p o i n t of t h e t r a n s f e r c o n i c and RESO i n t e r section. (DG) �b. S a t u r n V AS-504 Guidance E q u a t i o n s The f i n a l g u i d a n c e e q u a t i o n s have been r e c e i v e d and (~G/Boeing) approved w i t h a q u a l i f y i n g cover l e t t e r . c. Guidance Improvements C o n s i d e r a b l e e f f o r t i s b e i n g expended t o s t r e a m l i n e t h e I@fe q u a t i o n s s o t h a t t h e y a r e more f l e x i b l e w i t h r e s p e c t t o t a r g e t v a l u e s r e q u i r e d and t o m i s s i o n s and s o t h a t t h e y a r e i n a form which i s e a s i e r t o program. A new, more a c c u r a t e g r a v i t y p r e d i c t i o n h a s b e e n s i m u l a t e d f o r t h e S a t u r n V i n t o e a r t h p a r k i n g o r b i t . Other m i s s i o n s , p a r t i c u l a r l y w i t h l o n g e r r a n g e a n g l e s t h a n our p r e s e n t l y d e f i n e d m i s s i o n s , a r e b e i n g i n v e s t i g a t e d . Closed l o o p s i m u l a t i o n s of ~ a m b e r t ' stheorem a s t a r g e t i n g f o r IGM have been made f o r a few c a s e s . The e q u a t i o n s have been formul a t e d t o a c h i e v e a n e n e r g y c u t - o f f r a t h e r t h a n t o c o n s t r a i n p o s i t i o n and v e l o c i t y s e p a r a t e l y , which r e d u c e s t h e amount of i n p u t r e q u i r e d . 2. Dynamics and C o n t r o l - S a t u r n V Bending A n a l y s i s Recent a s s e s s m e n t of t h e s p a c e c r a f t t o r s i o n s t r u t d e s i g n change and i n c o r p o r a t i o n of dynamic t e s t r e s u l t s i n t o t h e math mode h a s i n d i c a t e d a need t o r e v i s e t h e bending mode d a t a t o i n c l u d e t h e s e changes. These changes have b e e n i n c o r p o r a t e d i n t o t h e 3-D math model by The Boeing Company and checked a g a i n s t dynamic t e s t r e s u l t s . C o r r e l a t i o n between d a t a o b t a i n e d froin t h e math model and dynamic t e s t was good. The Boeing Company has been committed t o r e l e a s e AS-501 d a t a f o r one s t a g e a t a time d u r i n g August w i t h a t o t a l document b e i n g r e l e a s e d by September 11, 1967. Data f o r AS-503 w i l l be r e l e a s e d a s a t o t a l document by September 7 , 1967. (~~S/~oeing) 3. P r o j e c t Information Applicable t o Individual Vehicles a. SA-504, F l i g h t Dynamics A n a l y s i s The i n i t i a l document on SA-504 f l i g h t dynamics a n a l y s i s has b e e n r e l e a s e d . R e s u l t s of changes a r e shown f o r (1) S-IC f l i g h t c o n t r o l s y s t e m d a t e d 3 / 2 2 / 6 7 , (2) yaw b i a s d u r i n g l i f t - o f f , and (3) e n g i n e m i s a l i g n m e n t s based on s t a t i c f i r i n g d a t a . (~~/Boeing) b. 501 C o n t r o l S t a b i l i t y R e - e v a l u a t i o n Runs have been made on t h e c o n t r o l s y s t e m r e - e v a l u a t i o n and t h e documentation i s b e i n g completed. Some d i f f i c u l t y h a s b e e n e n c o u n t e r e d i n o b t a i n i n g t h e r o o t s f o r t h e l a s t few r u n s on t h i s s t u d y . T h i s d i f f i c u l t y w i l l n o t a r i s e on f u t u r e s t u d i e s when t h e Q-R t r a n s f o r m a t i o n t e c h n i q u e i s i n c o r p o r a t e d i n t h e g a i n and phase r o o t l o c u s program. R e s u l t s show t h a t t h e d e s i g n of t h e 501 c o n t r o l s y s t e m i s a c c e p t a b l e i n a l l a s p e c t s of f l i g h t i n c l u d i n g bending modes and propellant oscillations. (DDD) �c. AS-5011s-IVB Low "g" S l o s h A d r a f t of tile f i n a l documentation of a n a n a l o g s t u d y on Low 'lg" s 10~11on AS-501 11as been d e l i v e r e d by N o r t h r o p . The purpose oL t h i s s t u d y was ( 1 ) t o i n v e s t i g a t e t h e S-IVB r i g i d body and s l o s h b e l u v i o r under l o g "gl' c o n d i t i o n s , ( 2 ) t o i n v e s t i g a t e t h e s y s t e m s t a b i l i t y f o r v a r i o u s i n i t i a l c o n d i t i o n s , and (3) t o compare t h e performance of a n o n l i n e a r s l o s h model t o t h a t of t h e l i n e a r "spring-mass-damper" model n o r m a l l y u s e d . R e s u l t s show t h a t , f o r r e s p o n s e v a l u e s e x p e c t e d i n f l i g h t ( 1 and 2 m e t e r s l o s h a m p l i t u d e ) , t h e l i n e a r model g i v e s s u f f i c i e n t l y a c c u r a t e r e s u l t s t o a l l e v i a t e t h e need f o r l e n g t h y r u n s w i t h t h e n o n l i n e a r model. (DDD/Northrop) d. S a t u r n V Node Change C a p a b i l i t y This s t u d y , made t o i n v e s t i g a t e t h e f e a s i b i l i t y of a n a l t e r n a t e m i s s i o n f o r AS-503, was extended t h i s p e r i o d . The b a s i c p u r pose of t h i s a l t e r n a t e m i s s i o n is t o t e s t t h e r e s t a r t c a p a b i l i t y of t h e S-IVB w i t h o u t b u r n i n g i n t o t h e h i g h apogee e l l i p s e p r e s e n t l y proposed. T h i s i s done by u s i n g t h e S-IVB p r o p e l l a n t t o make a p l a n e changc i n s u c h a way a s t o keep t h e o r b i t a l i n c l i n a t i o n c o n s t a n t and m e r e l y skew t h e l i n e of nodes. By performing t h i s maneuver a t t h e b e g i n n i n g of t h e t h i r d o r b i t , a n a t t r a c t i v e b y - p r o d u c t i s o b t a i n e d i n t h a t t h e r e s u l t i n g ground t r a c k l i e s n e a r t h a t of t h e f i r s t o r b i t , improving t h e t r a c k i n g s i t u a t i o n . During t h i s p e r i o d , a n o p t i m i z e d t r a j e c t o r y and a s s o c i a t e d ground t r a c k was o b t a i n e d f o r t h e node change maneuver and c o a s t . The 44' node change c a p a b i l i t y o b t a i n e d by t h e i m p u l s i v e s t u d y was v e r i f i e d i n t h e o p t i m i z e d t r a j e c t o r y . However, two problem a r e a s were i d e n t i f i e d by t h i s s t u d y . F i r s t , i t was found t h a t i f t h e S-IVB e x p e r i e n c e d a n e a r l y e n g i n e shutdown, t h e v e l o c i t y magnitude d u r i n g t h e b u r n was d e c r e a s e d t o t h e p o i n t of c a u s i n g impact i n l e s s t h a n h a l f a n o r b i t . This problem could be e l i m i n a t e d by c o n s t r a i n i n g t h e v e l o c i t y d u r i n g t h e b u r n a t t h e expense of r e d u c i n g t h e maximum node change c a p a b i l i t y . Secondly, t h e yaw s t e e r i n g r e q u i r e d exceeds t h e p r e s e n t h a r d s t o p s of t h e g y r o p l a t f o r m . T h i s second problem could p o s s i b l y b e a l l e v i a t e d by a n a z i m u t h b i a s a t l a u n c h . D e t a i l s and r e s u l t s of t h i s s t u d y were p r e s e n t e d t o t h e FMP m e e t i n g 21. Documentation h a s been completed. (DAO) C. S a t u r n IB P r o j e c t Information Applicable t o Individual Vehicles AS-204 Nose Cone S e p a r a t i o n f o r Abort: A s t u d y of t h e p o s s i b i l i t y of a n e a r l y s e p a r a t i o n of t h e AS-204 n o s e cone b e f o r e l a u n c h of t h e S-IVB s t a g e p r e m a t u r e l y s h u t down h a s been completed and documented i n Memorandum R-AERO-DCC-6-67, "AS-204 Nose Cone S e p a r a t i o n f o r A b o r t , " J u l y 24, 1967. R e s u l t s of t h e s t u d y i n d i c a t e t h a t , f o r e n g i n e s h u t down �a f t e r 165 seconds of f l i g h t , r e l e a s e of t h e nose cone a f t e r t h r u s t decay would a l l o w t h e LM t o be launched. A s i m i l a r s rudy assuming t h a t t h e S-IVB s t a g e engine never i g n i t e s has bccn initiated. (DCC) D. AAP 1. Cluster a. Mission P r o f i l e (1) Miss i o n Planning Logic Development With regard t o m i s s i o n planning, a master p l a n which can handle a magnitude of AAP miss ions involving a n o r b i t a l workshop has been p a r t i a l l y developed. A f t e r a planned b a s e l i n e m i s s i o n (beginning of a d u a l launch) any sequence of s i n g l e and d u a l launch may be used t o complete the mission. The master p l a n i s n o t dependent on t h e type of o r b i t a l experiments o r any s e t number of v e h i c l e s s i n c e i t c o n t a i n s o n l y high l e v e l d e c i s i o n s and a c t i o n s of a g e n e r a l n a t u r e . The m s t e r p l a n comprises a compressed b a s e l i n e , v a r i o u s contingency expans i o n s , and a r a t h e r unique m i s s i o n c o n t i n u a t i o n planning expansion. Many important c o n s i d e r a t i o n s such a s long and s h o r t CSM o v e r l a p time, e r e c t i o n of two manned v e h i c l e s f o r a s i n g l e launch, and t h e changing of unmanned f o r manned payloads on t h e pad a r e covered i n t h e expansion. Logic has been developed f o r t h e compressed b a s e l i n e m i s s i o n continuat i o n planning. S i n g l e and dual launch ( f o r a manned-unmanned o r d e r ) c o n t i n g e n c i e s s t i l l t o be developed a r e t h e rendezvous and docking d u a l launch ( f o r unmanned-manned o r d e r ) and o r b i t a l experiment performance contingcncies. It i s f e l t t h a t f i n a l development of t h i s master p l a n w i l l r e s u l t i n a v e r y f l e x i b l e and v e r s a t i l e m i s s i o n planning t o o l . (DAO) (2) Uprated S a t u r n I payload Improvement J-2s Engine I d l e Mode Operation: Completion of t h i s t a s k has been delayed f o r e x t e n s i v e m o d i f i c a t i o n s r e q u i r e d t o i n c o r p o r a t e low t h r u s t c a p a b i l i t y i n t o t h e t r a j e c t o r y r o u t i n e . However, one f a c t which has become e v i d e n t i n t h e s t u d y i s t h a t because of l a r g e burn times and r e s u l t a n t g r a v i t y l o s s e s , d i r e c t i n j e c t i o n i n t o a 260 n.mi. o r b i t u s i n g a h i g h - i d l e - h i g h o r h i g h - i d l e mode r e s u l t s i n payload l o s s r a t h e r than g a i n . S-IVB R e s t a r t : This i s being continued by cons i d e r ing t h e payload improvement a s s o c i a t e d w i t h r e s t a r t i n g t h e J- 2s engine i n o r b i t . The mode which involves a p e r i g e e i n j e c t i o n i n t o a 81 x 260 n.mi. o r b i t and a c o a s t t o apogee i s a t t r a c t i v e s i n c e t h e J - 2 s �engine does n o t r e q u i r e l a r g e amounts of r e s t a r t p r o p e l l a n t . A d i s c u s s i o n w i t h P&VI;:p r o p u l s i o n personnel r e v e a l e d t h a t the p r o p e l l a n t r e q u i r e d f o r t h c c i r c u l a r i z a t i o n burn was enough t o i n s u r e r e s t a r t and t h e r e f o r e p r o p e l l a n t r e s i d u a l s necd n o t be i n c r e a s e d . An e s t i m a t e of 2000 l b s of ~lddccl S-TVD system cquipmcnt i s includecl. A p r e l i m i n a r y e s t i m a t e sllovs, \tit11 tllis moclc, a n ~lpproximatcg a i n 01 7,300 l b s over d i r e c t i n j e c t i o n . S-IB S o l i d Strap-Ons: A s t u d y i s under way t o provide a s c r u t i n y of performance g a i n s by t h e a d d i t i o n of f o u r Minuteman s o l i d r o c k e t motors t o t h e S-IB s t a g e . I g n i t i o n sequence, n o z z l e c a n t a n g l e , and j e t t i s o n sequence have been parameterized. Both CSM and unmanned v e h i c l e s a r e being considered. P r e l i m i n a r y e s t i m a t e s show t h a t t h e CSM v e h i c l e payload g a i n i s 6700 pounds i n t o a n 81 x 120 MM e l l i p t i c o r b i t , w h i l e t h e unmanned v e h i c l e g a i n i s 7200 pounds i n t o a 260 NM c i r c u l a r o r b i t . These g a i n s a r e quoted f o r a sequence of two MFI i g n i t e d a t l i f t - o f f and t h e remaining two i g n i t e d a t 70 seconds. Two MM c a s e s a r c j e t t i s o n e d a t 85 seconds and t h e remaining two c a s e s remain f i x e d t o tllc S-IB s t a g e . The f o u r MM were n o t canted w i t h r e s p e c t t o t h e S-IB c c n t e r l i n c . Performance and o t h e r f 1i g h t mechanics s t u d i e s c o n t i n u e . (~A~/~hrysler) (3) S a t e l l i t e Occultation i n Earth Orbit A s t u d y has been i n i t i a t e d t o f i n d t h e o c c u l t a t i o n period of a n e a r t h s a t e l l i t e . The e s s e n t i a l problem solved was t h e d e t e r m i n a t i o n of t h e o r i e n t a t i o n of t h e s a t e l l i t e ' s o r b i t a l p l a n e r e l a t i v e t o t h e e a r t h - s u n l i n e . The s o l u t i o n t o t h i s problem was t h e n used t o determine t h e a n g l e through which t h e s a t e l l i t e moved w h i l e i n t h e e a r t h ' s shadow and, u l t i m a t e l y , t o f i n d t h e f r a c t i o n of t h e t o t a l o r b i t a l p e r i o d t h a t the s a t e l l i t e was i n t h e s u n l i g h t . The s o l u t i o n was then programmed i n such a manner t h a t , i f t h e launch time, i n c l i n a t i o n of t h e o r b i t a l plane and c o o r d i n a t e s of t h e launch s i t e were s p e c i f i e d , t h e t o t a l time i n t h e s u n l i g h t was o b t a i n e d . Regression of t h e nodal l i n e was a l s o taken i n t o account. This s t u d y i s being f u r t h e r used i n a subsequent problem, namely, t h a t of s p e c i f y i n g t h e c o o r d i n a t e s of t h e sun r e l a t i v e t o a s e t of axes f i x e d i n a space s t a t ion. (DAO) (4) High I n c l i n a t i o n P l a n a r and O r b i t a l Phasing Launch Windows This i s a s t u d y of t h e ground launch window and o r b i t a l phasing r e q u i r e d f o r rendezvous a t high i n c l i n a t i o n s . This work i s p r i m a r i l y aimed a t d e f i n i n g m i s s i o n plans f o r t h e second c l u s t e r m i s s i o n . Based upon a t a r g e t body i n s e r t e d i n t o a 260 n.mi. c i r c u l a r o r b i t and i n c l i n a t i o n of 5 0 ° , a 20-minute ground launch window can be c r e a t e d f o r a payload t r a d e o f f of 1,000 pounds. This i s t r u e f o r b o t h n o r t h e r l y and s o u t h e r l y launches; however, t h e n o r t h e r l y f l i g h t s have �impact p o i n t s i n Newfoundland and Europe, w h i l e t h e s o u t h e r l y l a u n c h e s v i o l a t e l a r g e r e g i o n s of S o u t h America. I f s o u t h e a s t e r l y l a u n c h e s a r e r e q u i r e d , l a r g e payload l o s s e s a r e i n c u r r e d by d o g l e g g i n g around t h e e a s t e r n c o a s t of S o u t h America, and t h e l a u n c h window payload t r a d e o f f increases greatly. The o r b i t a l phas i n g r e q u i r e m e n t s f o r l a u n c h opport u n i t i e s (20-minute l a u n c h window) e v e r y day r e q u i r e s from one t o s i x t e e n r e v o l u t i o n s i n a 120 n.mi. c i r c u l a r p a r k i n g o r b i t . I f opportunities a r e chosen e v e r y t h i r d d a y , t h e p h a s i n g r e q u i r e m e n t s can b e k e p t t o l e s s t h a n 8 revolutions. The i n v e s t i g a t i o n of t h e u s e of e l l i p t i c o r b i t s (~AO/~orthrop) t o reduce phasing requirements i s continuing. (5) 1969 (Second C l u s t e r ) Miss i o n D e c i s i o n L o g i c Three l e v e l s of m i s s i o n d e c i s i o n l o g i c were p r e s e n t e d a t t h e M i s s i o n P l a n n i n g Task F o r c e Second C l u s t e r Summary Meeting a t NASA H e a d q u a r t e r s , Washington, D . C . on J u l y 25, 1967. The t h r e e l e v c l s of l o g i c c o n s i s t e d o f a m a s t e r p l a n ( d e s c r i b e d under a n o t h e r t o p i c i n t h i s r e p o r t ) , a b a s e l i n e summary and c o n t i n g e n c y c h a r t , and d e t a i l e d b a s e l i n e and c o n t i n g e n c y d i a g r a m s . The b a s e l i n e summary was a l m o s t a t r i v i a l consequence of c o n s i d e r i n g s i x v e h i c l e s i n a 2-1-2-1 b a s e l i n e and a c c o u n t i n g f o r o n l y s i n g l e v e h i c l e f a i l u r e s . The d e t a i l e d b a s e l i n e c o n t i n g e n c y p o s i t i o n was p a t t e r n e d a f t e r t h e Gemini f l i g h t o p e r a t i o n a l m i s s i o n l o g i c i n t h a t i t c o n t a i n e d countdown, l i f t - o f f , powered f l i g h t , i n j e c t i o n , e t c . However, t h i s second c l u s t e r m i s s i o n l o g i c was more open-ended s i n c e i t r e p r e s e n t e d a n i n t e r m e d i a t e m i s s i o n l o g i c p h a s e . During t h i s r e p o r t i n g p e r i o d , DAO and N o r t h r o p developed and p r e p a r e d (~AO/Northrop) the presentation material. (6) Launch Sequence f o r AAP 1 - 2 A s t u d y h a s b e e n completed on t h e l a u n c h s e q u e n c e f o r l a u n c h s u c c e s s p r o b a b i l i t y of manned f i r s t v s t h e unmanned f i r s t mode. The a s s u m p t i o n s used i n t h e s t u d y and t h e r e s u l t s and c o n c l u s i o n s o f t h e s t u d y a r e p r o v i d e d i n memorandum R-AERO-DAM-10-67. Briefly, the s t u d y showed t h a t t h e h i g h e s t l a u n c h s u c c e s s mode i s manned f i r s t . Howe v e r , i f t h e a u x i l i a r y a t t i t u d e c o n t r o l s y s t e m i s added t o t h e unmanned v e h i c l e , t h e n t h e r e i s no s i g n i f i c a n t d i f f e r e n c e i n l a u n c h s u c c e s s p r o b a b i l i t y u s i n g e i t h e r mode, i . e . , manned f i r s t v s unmanned f i r s t . There i s some g a i n i n l a u n c h s u c c e s s i f t h e IU i s m o d i f i e d t o p r o v i d e g r e a t e r t h a n 7 112 h o u r s l i f e t i m e . However, t h i s g a i n does n o t become s i g n i f i c a n t u n t i l t h e r e i s a t l e a s t 24 h o u r s a d d i t i o n a l l i f e t i m e s i n c e (DAM) t h e l a u n c h windows a r e s e p a r a t e d by 24 h o u r s . �b. P r o j e c t I n f o r ~ n a t i o nApplicable t o Many Vehicles Experimental Determination of the S t a b i l i t y of S p i n n i n g Cable-Connected Space S t a t i o n s : The moment of i n e r t i a a b o u t t h e p r i n c i p a l axes of t h e two models were determined e x p e r i m e n t a l l y by t r e a t i n g .each a s a simplc pendulum. The weight of each of t h e masses t h a t a r e t o be a t t a c h e d t o t h e models t o v a r y t h e i r moments of i n e r t i a has been d e t e r mined, and each model, w i t h o u t t h e a t t a c h e d masses, weighed a c c u r a t e l y . Work has begun on making t h e two models a s n e a r l y i d e n t i c a l a s p o s s i b l e i n order t o coincidc with the e x i s t i n g t h e o r e t i c a l s t a b i l i t y analyses. Design of a new model has begun because t h e e x i s t i n g models do n o t cover the f u l l range of d e s i r e d i n e r t i a r a t i o s . A pneumatic c a t a p u l t i s being f a b r i c a t e d , and arrangements f o r photographic coverage of t h e experiment have been made. The r e s u l t s of a n a n a l y s i s of t h e pneumatic c a t a p u l t system i n d i c a t e d t h a t t h e d e s i r e d payload could be launched t o a n a c c e p t a b l e a l t i t u d e w i t h o u t exceeding t h e d e s i g n p r e s s u r e . The diameter of t h e r e l i e f o r i f i c e f o r c o n t r o l l e d d e c e l e r a t i o n of t h e launching mcchanism was a l s o determined. The computer program used t o develop t h e s c r e s u l t s should be u s e f u l when o p e r a t i o n of t h e launching f a c i l i t y s t a r t s . The p i s t o n and c y l i n d e r assembly, a s w e l l a s c e r t a i n s m a l l e r i t e m s , has been d e l ivered t o R-TEST, and f a b r i c a t i o n should b e g i n soon. (DDS) 2. ATM a. Docking Dynamics The g e n e r a l ecluations o f motion f o r two r i g i d bodies w i t h a p o i n t i n common and coupled by a spring-damper system were d e r i v e d . The e q u a t i o n s i n c l u d e t h e e f f e c t s a t g r a v i t y - g r a d i e n t t o r q u e s , s o l a r p r e s s u r e and aerodynamic t o r q u e s , a s w e l l a s c o n t r o l t o r q u e s . The programming of t h e s e n o n l i n e a r e q u a t i o n s on b o t h t h e d i g i t a l and a n a l o g computers i s approximately 60 p e r c e n t complete. The programs a r e being w r i t t e n i n modular form t o a i d i n parameter s t u d i e s of t h e e f f e c t s of v a r i o u s c o n t r o l laws and parameters. The e q u a t i o n s , s i m p l i f i e d t o two dimensions, have been programmed t o provide a check of t h e g e n e r a l program. A n a l y t i c e x t e n s i o n of t h e two body problem t o i n c l u d e any number of bodies i s about 50 p e r c e n t complete. A t h e o r e t i c a l s t u d y of t h e e f f e c t s of e l a s t i c i t y on v c h i c l e motion d u r i n g docking has begun. This v i b r a t i o n s t u d y i s being pursued i n terms of g e n e r a l i z e d v a r i a b l e mass and s t i f f n e s s m a t r i c e s f o r s i n g l e v e h i c l e and i s t o be extended l a t e r t o a coupled system. (DDD) �b. ATM P o i n t i n g Accuracy Equations of motion f o r t h e ATM have been p a r t i a l l y d e r i v e d u s i n g 2 and 6 hinged-body models. The problem f a l l s i n t o two main p a r t s : 1. S h o r t term behavior: (a) (b) 2. . (1) Disturbances : (2) Control: crew motion. j e t s and moment damping. E l a s t i c body. Two hinged bodies where body #1 i s e l a s t i c and body # 2 i s r i g i d . Consider r o t a t i o n around /I1 and /k3 a x i s . (1) Disturbances: (2) Control: t h e same a s i n l a . t h e same a s i n l a . Long term behavior: (a) 3. Rigid body. R o t a t i o n i n space of 2 and 6 hinged bodies Rigid and el-ast i c body. Cons i d e r t r a n s l a t i o n a l and r o t a t i o n a l motion ( s i x degrees of freedom). (1) Dis turbances : aerodynamics. (2) Control: g r a v i t y t o r q u e g r a d i e n t and same a s i n l a . (DDD) OWS Active Control S t u d i e s The i n v e s t i g a t i o n of space v e h i c l e c o n t r o l u s i n g c o n t r o l moment gyros i s being continued. Liapunov's d i r e c t method i s being used on t h e s e n o n l i n e a r systems t o o b t a i n g l o b a l l y a s y m p t o t i c a l l y s t a b l e cont r o l laws. The c o n t r o l laws chosen a r e l i n e a r combinations of s t a t e v a r i a b l e s which a r e modified by t r i g o n o m e t r i c f u n c t i o n s of t h e c o n t r o l a n g l e d e f l e c t i o n s . This method of a t t a c k g i v e s a means of i d e n t i f y i n g t h e "damping and s p r i n g c o n s t a n t s " i n t h i s r a t h e r complex n o n l i n e a r system. U n f o r t u n a t e l y , some of t h e s e c o n t r o l laws i n v o l v e s e c a n t and t a n g e n t f u n c t i o n s which can become i n f i n i t e f o r a n g l e s of 90 d e g r e e s , b u t t h e s e a n g l e s can be avoided by proper a c q u i s i t i o n c o n t r o l using �c o i i t r o l roclicts. M o d i l i c a t i o n of t h e c o n t r o l laws t o omit some o f t h e i~ill,or~ntlc,tlI u n c t ions i s b e i n g programmed l o r d i g i t a l s i m u l a t i o n of t h e s y s r ~'111. Work i s c o n t i n u i n g on t h e development of a n in-house program t o do a t t i t u d e c o n t r o l s t u d i e s . The dynamic e q u a t i o n s were d e v e l o p e d and t h e v a r i o u s c o o r d i n a t e systems were d e s c r i b e d by Lockheed. T h i s work i s now b e i n g reviewed i n d e t a i l . During t h e development and debugging o f t h e d i g i t a l program, o n l y p a s s i v e c o n t r o l s t u d i e s have b e e n r u n . A c t i v e c o n t r o l systems a r e b e i n g s t u d i e d and i n c o r p o r a t e d i n t o the equations of motion. A d i g i t a l program h a s been developed by Lockheed t o p e r f o r m a p a r a m e t r i c s t u d y o f a CMG SIXPAC u n l o a d i n g t e c h n i q u e t h a t u s e s t h e o u t e r g i m b a l s t o a c h i e v e a l l of t h e d e s a t u r a t i o n . C o n t r o l law s t u d i e s f o r t h e CMG SIXPAC i n c l u d e a d e t a i l e d s t u d y o f t h e s t a b i l i t y of a c o m p l e t e l y uncoupled n u m e r i c a l c o n t r o l law. I f t h i s law h a s a c c e p t a b l e s t a b i l i t y c h a r a c t e r i s t i c s , i t s g a i n c h a r a c t e r i s t i c s w i l l b e compared w i t h some of t h e laws s t u d i e d i n t h e p a s t . Such a comparison s h o u l d i n d i c a t e t h e major s h o r t c o m i n g s of t h e s e (~~Al~ockheed) laws. E. Other P r o j e c t s Drop Tower T e s t s A s e r i e s o f d r o p tower t e s t s i s b e i n g planned which w i l l e x t e n d t h e knowledge o f l i q u i d p r o p e l l a n t o s c i l l a t i o n a t Bond numbers l e s s t h a n 10. The r e s u l t s o f t h i s e x p e r i m e n t s h o u l d b e v a l u a b l e f o r a c c u r a t e p r e d i c t i o n o f t h e l i q u i d p r o p e l l a n t dynamics i n t h e Voyager s p a c e c r a f t d u r i n g i n t e r p l a n e t a r y c o a s t . The models t o b e used a r e ( 1 ) 1 - i n c h d i a m e t e r s p h e r i c a l , ( 2 ) 2-inch d i a m e t e r s p h e r i c a l , and ( 3 ) 2 - i n c h diame t e r by 4 - i n c h t a l l c y l i n d r i c a l . The d a t a needed a r e f i l m r e c o r d s of i n t e r f a c e f o r m a t i o n i n model (1) a t 10-ICgo r l e s s and f i l m r e c o r d s and l a t e r a l f o r c e r e c o r d s of l i q u i d o s c i l l a t i o n s i n models ( 2 ) and ( 3 ) a t t e s t a c c e l e r a t i o n s o f 10-'lg, 1 0 - ' g , and 10-'g. (DDS) �VII. FLIGHT TEST ANALYSIS DIVISION A. Special Projects Office Saturn V The S a t u r n V F l i g h t T e s t E v a l u a t i o n P l a n , i s s u e d on J u l y 31, 1967, d e f i n e d t h e o r g a n i z a t i o n and e s t a b 1 i s h e d t h e r e s p o n s i b i l i t i e s and p r o c e d u r e s f o r f l i g h t e v a l u a t i o n o f v e h i c l e s AS-501 t h r o u g h AS-504. This document, which w i l l b e s u b j e c t t o r e v i s i o n 30 days b e f o r e e a c h o f t h e a f f e c t e d f l i g h t s , i s t o b e used a s a g u i d e l i n e by a l l a g e n c i e s c o n t r i b u t ing t o the t o t a l launch v e h i c l e evaluation. B. F l i g h t Mechanics Branch 1. Saturn I B The 204 o p e r a t i o n a l t r a j e c t o r y document, R-AERO-FM-136-67, d a t e d May 1 7 , 1967, h a s b e e n d i s t r i b u t e d . An u p d a t e t o t h e document, which h a s b e e n completed by CCSD and w i l l b e p u b l i s h e d by mid-August, r e f l e c t s t h e l a t e s t p r o p u l s i o n p r e d i c t i o n s and t h e 270-degree a t t i t u d e f o r t h e p r o p e l l a n t dump e x p e r i m e n t . The r a n g e s a f e t y a n a l y s i s f o r t h e 204/LM-1 m i s s i o n i s documented i n R-AERO-FMR-151-67, d a t e d J u n e 6 , 1967. The a b o r t and a l t e r n a t e m i s s i o n document h a s now b e e n completed and w i l l b e d i s t r i b u t e d b y mid-Augus t . b. AS- 205 Rendezvous Miss i o n A t y p i c a l m i s s i o n p r o f i l e f o r t h e 120 x 150 n a u t i c a l m i l e e l l i p t i c a l o r b i t h a s b e e n g e n e r a t e d , and t h e S-IB s t e e r i n g f u n c t i o n s and second s t a g e IGM p r e s e t t i n g s have b e e n f i n a l i z e d . The t r a j e c t o r y , which r e f l e c t s t h e l a t e s t mass and p r o p u l s i o n p r e d i c t i o n s , w i l l b e used f o r a l l p r e l i m i n a r y s t u d i e s . The s p a c e c r a f t w e i g h t used was 36,300 pounds. With t h i s w e i g h t , t h e S-IVB s t a g e u s e a b l e p r o p e l l a n t s a t i n s e r t i o n a r e a p p r o x i m a t e l y 1500 pounds. C . AS-206 R e s t a r t As d i r e c t e d by t h e S a t u r n I B Program Off i c e , t h e o p e r a t i o n a l t r a j e c t o r y , d i s p e r s i o n a n a l y s i s , and r a n g e s a f e t y a n a l y s i s a r e being generated t o support the r e s t a r t mission. �P r e l i m i n a r y s c h e d u l e s f o r s y s tem e n g i n e e r i n g e f f o r t s have been e s t a b l i s h e d based on the l a t e s t f l i g h t miss i o n assignment document. 2. SaturnV The r e v i s e d o p e r a t i o n a l t h e FFOT, has been r e c e i v e d from TBC (26 d i s t r i b u t e d soon. Work i s c o n t i n u i n g on safety. The four-engine and f i v e - e n g i n e t h e Range has been s e n t t o KSC. t r a j e c t o r y , b e t t e r known a s J u l y 1967) and should be an update f o r t h e AS-501 range t u r n i n g r a t e d a t a r e q u e s t e d by The 501 D i s p e r s i o n Analysis has been r e c e i v e d from TBC. F i n a l review i s being made t o check t h e c o r r e c t i o n s which were t o be i n c o r p o r a t e d by TBC. FMT hopes t o make d i s t r i b u t i o n t h i s week of t h e d i s p e r s i o n a n a l y s i s r e p o r t i f i t i s a c c e p t a b l e . Problems have a r i s e n w i t h t h e p r e s e n t " c o n s t a n t low t h r u s t v e n t model" i n t h a t t h e r e is n o t s u f f i c i e n t p r o p e l l a n t r e s e r v e t o cover t h e 30 low performance u s e s , b u t s t i l l a l l o w s a h i g h confidence ( - 98.3) i n accomplishing t h e m i s s i o n . The v e n t model misleads t h e v e h i c l e computer i n how much energy i s necess a r y t o achieve the prescribed waiting o r b i t . I n a n t i c i p a t i o n of a s l i p i n launch s c h e d u l e , a memo has been w r i t t e n r e q u e s t i n g t h a t t h e p r e v i o u s l y d e r i v e d t i l t program f o r w i n t e r winds be implemented f o r a November launch. The a p p l i c a b i l i t y of t h i s ti1 t program has been checked and found a c c e p t a b l e . The r e v i s e d t i l t program using average J a n u a r y , February, and March winds has been completed and t r a n s m i t t e d t o t h e R-AERO-FFR f o r use i n d i s p e r s i o n a n a l y s i s . A p r e s e t t i n g s r e v i s i o n w i l l be made and d i s t r i b u t e d i n e a r l y August. This r e v i s i o n w i l l c o n t a i n t h e S-IC s t a g e The Abort t i l t program and t h e a b o r t and a l t e r n a t e m i s s i o n p r e s e t t i n g s . and A l t e r n a t e Mission Report was r e t u r n e d t o TBC f o r c o r r e c t i o n s and should be r e s u b m i t t e d by August 1 5 , 1967. The D i s p e r s i o n Analysis Rough D r a f t was r e c e i v e d and has been p a r t i a l l y reviewed. Comments on u n s a t i s f a c t o r y a r e a s which have been noted i n our c r i t i q u e have been forwarded t o TBC f o r incorporat i o n i n t o t h e document b e f o r e i t i s p r i n t e d . It i s hoped t h a t t h e r e p o r t w i l l be found a c c e p t a b l e w i t h o u t any changes when i t i s r e c e i v e d on August 11, 1967. �Work has begun on the S-IC s t a g e t i l t program and on the dcvel opmcnt of a f l i g h t s i m u l a t i o n d a t a deck. There i s a prol,lcm a s s o c i a t e d with t h c new 503 m i s s i o n i n t h a t a l a r g e amount of r e s itlria l s remain i n e a r t h parking o r b i t . This causes a problem i n maintaining a propellant control a s well a s v e h i c l e control f o r t h i s c a s e . S i n c e t h e problem w i l l reappear and i n f a c t was due t o occur on 503 f o r l a r g e r e s i d u a l s remaining a t second S-IVB c u t o f f , P&VE has proposed a second burn f o r t h e S-IVB. A meeting was h e l d on J u l y 1 3 t o d i s c u s s t h e AS-503 m i s s i o n and t h e second s t a r t of t h e S-IVB s t a g e . The conclusions were a s follows: There a r e t h r e e o p t i o n s . (1) The one favored by R-AERO-FM i s t o s e p a r a t e from t.he s p a c e c r a f t and have a d u a l r e s t a r t of the S - I n . As t r i o n i c s s t a t e d a t t h i s time t h a t t h e r e was no problem i n c o n t r o l l i n g w i t h o u t t h e use of t h e s p a c e c r a f t . ( 2 ) Another proposal was t o r e s t a r t w i t h t h e s p a c e c r a f t a t t a c h e d and burn f o r a t l e a s t (3) Another a l t e r n a t i v e was t o burn f o r 40 seconds w i t h 10 seconds. t h e s p a c e c r a f t a t t a c h e d , and burn t o a 45-degree yaw command and then s e p a r a t e . A problem w i t h a l l proposals is t o g e t t h e proper t r a c k i n g and t e l e m e t r y f o r t h e S-IVB second burn. d . Lunar Landing Miss i o n Our e f f o r t on t h e l u n a r landing m i s s i o n has been p r i marily t o g e t a trans lunar i n j e c t i o n targeting capability a v a i l a b l e a s soon a s p o s s i b l e . Approximately 60 p e r c e n t of t h e s u b - r o u t i n e s a r e complete and i n our deck. However, we a r e o n l y comparing and no runs have been made. We a r e hoping t o have our in-house c a p a b i l i t y r e a d y f o r checkout by e a r l y August. A s t a t u s on t h e J u l y t a r g e t i n g e x e r c i s e was g i v e n by Boeing on J u l y 19. The purpose of t h i s e x e r c i s e i s t o check o u t and demonstrate t h e c a p a b i l i t y of Boeing t o r e t a r g e t launch v e h i c l e s f o r a l u n a r m i s s i o n i n two weeks. Boeing e s t i m a t e s t h e y a r e t h r e e days t o one week behind s c h e d u l e . One of t h e problems i s i n e s t a b l i s h i n g a proper p1 t e s t f o r t h e six-degrees-of-freedom TLI deck. They can, however, r e a d and w r i t e e a r t h parking o r b i t i n s e r t i o n s t a t e v e c t o r t a p e s , r e a d the t a r g e t i n g t a p e , and card punch a TLI of t h e v e c t o r t o t h e 6D deck. It i s e s t i m a t e d t h a t Boeing i s approximately 35 t o 40 p e r c e n t complete and e f f i c i e n t i n t h i s a r e a . It i s hoped t h a t f o r t h e September e x e r c i s e ( e x e r c i s e period number two) we w i l l demonstrate r a p i d r e t a r g e t i n g ; t h a t i s , one month of t a r g e t i n g i n f i v e working days. �3. O r b i t a l Debris Lockheed, under c o n t r a c t NAS8-20369, has submitted a r e p o r t This document e n t i t l e d "A Study of AS-501 Debris Risk Hazard Analysis." has been reviewed and approved. The p r e s e n t Risk Hazard Program i s being modified t o g e n e r a t e t h e d e b r i s a n a l y s i s f o r t h e AS-502 miss ion. 4. Voyager The nominal t r a j e c t o r y has been generated f o r t h e 45" launch azimuth. The u n r e s t r i c t e d aerodynamic d a t a a r e being p u t i n our 6D deck t o c a l c u l a t e turning r a t e s . 5. AAP A p r e l i m i n a r y range s a f e t y a n a l y s i s has been generated f o r nose-cone and a CSM "2 1/2 s t a g e " con£ i g u r a t i o n . The nose cone coni g u r a t i o n was i n s e r t e d i n t o a 260 n a u t i c a l m i l e c i r c u l a r o r b i t w i t h an i n c l i n a t i o n of 50". The CSM " 2 112 stage" con£ i g u r a t i o n was i n s e r t e d i n t o a n 81 x 120 n a u t i c a l m i l e e l l i p t i c a l o r b i t w i t h a 50' i n c l i n a t i o n . T r a j e c t o r i e s were generated f o r b o t h n o r t h e r l y and s o u t h e r l y launch azimuths . C. Tracking and O r b i t a l Analysis Branch 1. Saturn I B a . A p r e l i m i n a r y copy of AS-204-LM1 a c q u i s i t i o n and l o s s timc was g i v e n t o I-MO-R per r e q u e s t . b. Work w i l l begin t h i s week on t h e AS-205 t r a c k i n g a n a l y s i s wllicl~w i l l b e done in-house. c . An a c t i o n item from I-MO has been r e c e i v e d t o a n a l y z e Bermuda coverage on t h e AS-204/LM1 m i s s i o n f o r v a r i o u s b o o s t phase cont i n g e n c i e s . R-AERO-FM i s p r e p a r i n g t r a j e c t o r y i n f o r m a t i o n n e c e s s a r y t o R e s u l t s should be a v a i l a b l e soon. a n a l y z e t h e coverage problem. 2. Saturn V a . The t r a c k i n g and c o m u n i c a t i o n s a n a l y s i s document on t h e SA-504 m i s s i o n prepared by TBC has been r e c e i v e d , reviewed, and rejected. TBC has been b r i e f e d on t e c h n i c a l d e f i c i e n c i e s , and o f f i c i a l n o t i f i c a t i o n of t h e r e j e c t i o n has been submitted t o R-AERO-P. �ILLS b. 'Che AS-502 t r a c k i n g ancl t e l e m e t r y coverage document bccxn tl i s tr i b u t c d unc1c.r Memorandum R-AERO-FT-45-67 . c . S t u d i e s a r e p r e s e n t l y underway t o a i d i n t h e answer of t h e F l i g h t Mechanics P a n e l a c t i o n i t e m 2 1 . 5 . 4 r e g a r d i n g AS-~O~/S-IVB restart possibilities. S-IVB r e s t a r t t i m e s based on ground p r o f i l e s a r e b e i n g a n a l y z e d , and recommendations w i l l be made t o answer t h e following items: (1) S-IVB r e s t a r t f o r a 10-second b u r n w i t h S/C a t t a c h e d a b o u t 90 m i n u t e s a f t e r i n s e r t i o n . (2) Same a s (1) a b o v e , e x c e p t r e s t a r t w i l l o c c u r a b o u t 180 m i n u t e s a f t e r i n s e r t i o n . ( 3 ) S-IVB r e s t a r t f o r a 30 t o 40-second b u r n , SIC a t t a c h e d , w i t h a 45' yaw a t t i t u d e , a b o u t 90 m i n u t e s a f t e r o r b i t a l i n s c r t i o n and a second r e s t a r t a f t e r LV/SC s e p a r a t i o n . ( 4 ) Perform two S-IVB r e s t a r t s a f t e r LV/SC s e p a r a t i o n , w i t h a f i r s t b u r n of a b o u t 5 0 s e c o n d s . I n f o r m a t i o n on f i r s t r e s t a r t c a s e s a b o u t 90 and a b o u t 180 m i n u t e s a f t e r i n s e r t i o n has been s u p p l i e d t o R-AERO-DA. Informat i o n on second r e s t a r t c a s e s w i l l b e s u p p l i e d a f t e r t r a j e c t o r y informat i o n i s g e n e r a t e d by R-AERO-DA. 3. Apollo Applications a . The second meeting of t h e AAP I & C P a n e l was h e l d a t MSFC on May 24, 1967. The few a c t i o n items t h a t were c o n s i d e r e d were i n d i c a t i v e of t h e c o n t i n u e d l a c k of d e f i n i t i o n of t h e program. b. A p r e s e n t a t i o n given a t F o r c e Meeting h e l d a t MSFC on June 1 and t h e t r a c k i n g and c o m u n i c a t i o n s coverage f o r t h e second c l u s t e r m i s s i o n . O r b i t a l were p r e s e n t e d on b o t h t h e f i r s t c l u s t e r i n c l i n e d o r b i t and on t h e second c l u s t e r inclined orbit. t h e AAP M i s s i o n P l a n n i n g Task 2 i n c l u d e d a b r i e f rundown on on t h e 50-degree i n c l i n e d o r b i t decay and l i f e t i m e s t u d i e s m i s s i o n on t h e 28 112 d e g r e e m i s s i o n on t h e 50-degree c . A p r e s e n t a t i o n on t h e C l u s t e r 1 c o n f i g u r a t i o n o r b i t a l d e c a y and l i f e t i m e was g i v e n t o t h e Guidance, Performance, and Dynamics Subpanel which met a t MSFC on J u n e 1 5 , 1967. The r e s u l t s p r e s e n t e d were based on t h e l a t e s t and b e s t i n f o r m a t i o n a v a i l a b l e . These w i l l be updated a s new i n f o r m a t i o n is o b t a i n e d . �a. A s tutly was co~npleted by NSL Mission Support t o d e t e r n ~ i n c t h e gimbal r a t e s r e q u i r e d t o o r i e n t t h e ATM s t a r t r a c k e r on Canopus over a one-year p e r i o d . These r e s u l t s were given t o M r . Snoddy, I-S/AA, a l o n g w i t h t h e approximate percentage of time t h e ATM s t a r t r a c k e r would be o c c u l t e d by t h e e a r t h . This i n f o r m a t i o n was r e q u e s t e d t o v e r i f y a proposed s t a r t r a c k e r gimbal requirement on t h e ATM mission. b . A meeting was h e l d w i t h I-MO, ASTR, P&VE, and AERO personnel t o a t t e m p t t o e s t a b l i s h a f i r s t c u t a t t h e Voyager m i s s i o n sequence of e v e n t s . This information i s being g a t h e r e d t o g e t h e r by M r . Kurtz of I-MO f o r t h e Mission Operations Working Group. c. P r e l i m i n a r y a n a l y s i s was made concerning communications d u r i n g shroud s e p a r a t i o n and DSN pickup. This i n f o r m a t i o n was i n s u p p o r t of M r . Kurtz, I-MO, a s a panel member of t h e Voyager Mission Operations Working Group. d. M r . Lee Gentry, Martin-Marie tta-Denver, was a t MSFC on June 2 9 , 1967, f o r a n o r i e n t a t i o n meeting on t h e s t u d y "Mars T r a n s f e r T r a j e c t o r y Determination and E r r o r Analysis." The i n i t i a l phase of t h e s t u d y (approximately two months) w i l l be a survey of t h e methods of i n t e r p l a n e t a r y t r a j e c t o r y determination. e . A p r e s e n t a t i o n was g i v e n by M r . Pimm, DISC m i s s i o n s u p p o r t , a t t h e Voyager T r a j e c t o r i e s , Performance, Navigation and Guidance Working Group meeting a t JPL on J u l y 19, 1967, on a Mars O r b i t e r decay and lifetime. 5. O r b i t a l A n a l y s i s and L i f e t i m e a . M r . R. J . H i l l and M r . R. H. Benson each p r e s e n t e d a paper a t t h e Environment Induced O r b i t a l Dynamics Seminar on June 6 , 1967. M r . w ill' s p r e s e n t a t i o n was "Engineering C o n s i d e r a t i o n s i n L i f e time P r e d i c t i o n s ," and M r . enso on' s was "On Obtaining Decay Parameters from O r b i t Determination." Writeups of b o t h p r e s e n t a t i o n s have been completed and copies have been d i s t r i b u t e d t o i n t e r e s t e d personnel. ~~, t h e SA-101 b . O f f i c e Memorandum R - A E R O - F T - ~ ~ -updating Pegasus C l i f e t i m e and decay, has been prepared and d i s t r i b u t e d . c . NSL m i s s i o n s u p p o r t personnel gave a b r i e f i n g on t h e s t a t u s of a t t i t u d e p r e d i c t i o n work being performed. A 3D s i m u l a t i o n program has been w r i t t e n and programmed by R-COMP, and is now being checked o u t . This program w i l l be used t o a n a l y z e t o r q u e magnitudes and t o v e r i f y averaging techniques which a r e t o be developed. D r . Yu, who d i s c u s s e d averaging techniques and o p e r a t i o n s , w i l l soon b e g i n working on t h e s p e c i f i c problem of a t t i t u d e p r e d i c t i o n . �D. F l i g h t E v a l u a t i o n Branch 1. General Computer Programs The use of Marshall Vehicle Engineering System (MARVES) i n t h e Modular 6D t r a j e c t o r y program has shown t h a t t h e advantages o f f e r e d by t h e system could be extended t o computer programs o t h e r t h a n 3 D o r 6D t r a j e c t o r y programs. Other programs, w i t h i n t h e D i v i s i o n , w i l l be converted t o MARVES i n a n e v o l u t i o n a r y manner. To a s s i s t i n t h i s t r a n s i t i o n , t h e following i n f o r m a t i o n has been prepared and w i l l be k e p t c u r r e n t : (1) Index of modules c a t e g o r i z e d by f u n c t i o n . (2) Alphabetized notebook of modules ( i n f o r m a t i o n i n c l u d e s a l l documentation on each module). (3) Alphabetized l i s t of nomenclature (and d e f i n i t i o n s ) used i n t h e modules. (4) Generalized g u i d e l i n e s f o r p r e p a r a t i o n and docum e n t a t i o n of s u b r o u t i n e s o r modules. This m a t e r i a l i s being used t o f a m i l i a r i z e t h e D i v i s i o n w i t h MARVES and t o a i d t h e development of new programs. 2. Saturn I B a. AS-204-LM Wind Limits The AS-204/IX-1 launch v e h i c l e wind l i m i t s document has been r e c e i v e d from CCSD. The l i m i t s a r e based upon t h e s t r u c t u r a l i n t e g r i t y of t h e launch v e h i c l e which i s d e f i n e d a t s e v e r a l Mach numbers a s f u n c t i o n s of a n g l e of a t t a c k ( a ) , c o n t r o l gimbal d e f l e c t i o n (B), and dynamic p r e s s u r e ( q ) . R e s u l t s of t h e s t u d y show t h a t , a t t h e most c r i t i c a l a l t i t u d e (10 km), t h e wind l i m i t s f o r headwind, crosswind, and t a i l w i n d a r e 50, 48, and 70 m/sec, r e s p e c t i v e l y . b. S-IB Cutoff Time and V e l o c i t y Study A memo e n t i t l e d "Analysis of t h e P r e d i c t e d and Actual Cutoff Times and V e l o c i t i e s of S-IB s t a g e s and c u t o f f times on S-IVB s t a g e s of S a t u r n I B v e h i c l e s AS-201, AS-202 and AS-203," w a s approved and r e l e a s e d . �3. Saturn V a. EDS-Abort C r i t e r i a During a meeting on J u l y 19, 1967, between R-AERO, R-P&m, and TBC EDS groups, s e v e r a l proposals were advanced by TBC on how t o proceed w i t h t h e a b o r t t e n s i o n breakup problem. The proposal which r e c e i v e d g r e a t e s t s u p p o r t from R-P&VE was t h a t of s e p a r a t i n g s t a g e s S-IC/S-I1 upon a b o r t i n i t i a t i o n and s i m u l t a n e o u s l y f i r i n g S-IC r e t r o r o c k e t s t o r e l i e v e t h e bending moment a t t h i s i n t e r f a c e . TBC w i l l conc e n t r a t e more h e a v i l y on t h i s approach and determine i f t h e s t o r e d s t r a i n energy r e s u l t s i n a s h i f t of breakup t o h i g h e r v e h i c l e s t a t i o n s . They a r e working t o have a proposed f i x t o t h i s problem by August 1 5 , 1967. b. Abort and A l t e r n a t e Mission Analysis The r e s p o n s i b i l i t y f o r performing a b o r t and a l t e r n a t e m i s s i o n s a n a l y s e s on S a t u r n V launch v e h i c l e s was switched from AERO-mT t o AERO-FFR. R-AERO-FFR w i l l be r e s p o n s i b l e commencing w i t h the AS-503 a n a l y s i s . A new scope of work i.s being n e g o t i a t e d w i t h T ~ C / ~ u n t s v i l l e , 4. Apollo A p p l i c a t i o n s a. F l i g h t E v a l u a t i o n Working Group-Payload A FEWG-Payload and AAP f i l e has been e s t a b l i s h e d f o r AERO-F. This f i l e c o n t a i n s g e n e r a l i n f o r m a t i o n , memorandums, and agenda concerning t h e FEWG-Payload o r g a n i z a t i o n ; a l s o l o c a t e d i n t h i s f i l e a r e MSFC forms No. 422, on each of t h e ATM and OWS experiments. This f i l e i s t o be used w i t h i n t h e D i v i s i o n f o r i n f o r m a t i o n concerning FEWG and AAP. During t h e l a t e r p a r t of May s e v e r a l s m a l l meetings were h e l d among r e s p o n s i b l e persons i n v a r i o u s o f f i c e s and FEWG-Payload s t a f f concerning t h e t a s k requirements f o r t h e OWS. These v a r i o u s meetings provided b e n e f i c i a l r e s u l t s i n t h a t t h e complexity of t h e problem of d e f i n i n g t h e v a r i o u s t a s k requirements was r e a l i z e d . Dr. ing The the There w i l l be a s p e c i a l s t a f f and board meeting w i t h von Braun on August 9 concerning t h e g e n e r a l F l i g h t E v a l u a t i o n WorkGroup (FEWG) o r g a n i z a t i o n w i t h s p e c i a l emphas i s on FEWG-Payload FEWG-Payload s t a f f and s u p p o r t i n g s t a f f (CCSD) a r e now working on v a r i o u s c h a r t s t o be p r e s e n t e d a t t h i s meeting. . �5. Contracts a. S a t u r n I B Sys tems (CCSD) C h r y s l e r Corporation Space D i v i s i o n (CCSD) a t Michoud i s r e s p o n s i b l e f o r e s t a b l i s h i n g t h e i n t e r m e d i a t e (7-day) and f i n a l (14-day) p o s t - f l i g h t t r a j e c t o r i e s on t h e S a t u r n I B v e h i c l e s . The n e x t S a t u r n I B t o be launched (AS-204/LM1) i s t h e f i r s t I B v e h i c l e t o use t h e P r o j e c t Apollo Coordinate System Standards (PACSS). CCSD has r e d e f i n e d and implemented a l l of t h e changes n e c e s s a r y t o use PACSS. These changes have been completely documented. MSFC has f u r n i s h e d CCSD w i t h t h e l a t e s t v e r s i o n of t h e O r b i t a l C o r r e c t i o n Program (OCP) which can handle o r b i t a l v e n t i n g and the l a t e s t v e r s i o n of t h e powered f l i g h t t r a j e c t o r y program (GATE). CCSD w i l l a s s i s t us i n conducting s t u d i e s t o determine t h e c a p a b i l i t i e s and l i m i t a t i o n s of t h e s e programs. It appears t h a t CCSD has made e x c e l l e n t p r o g r e s s and can perform t h i s t a s k w i t h a 1imited amount of s u p e r v i s i o n . b . Miss i o n Support (Nor t h r o p ) Tracking d a t a and telemetered measurements from long d u r a t i o n space f l i g h t comprise a l a r g e volume of i n f o r m a t i o n t h a t r e q u i r e s b o t h p r o c e s s i n g and r e d u c t i o n . Some means of compressing t h e s e d a t a i s needed t o p r e s e r v e a l l t h e s i g n i f i c a n t i n f o r m a t i o n i n t h e d a t a w h i l e reducing t h e volume. D r . Hal P u r c e l l (NSL) has been r e s e a r c h ing v a r i o u s compression techniques t o a r r i v e a t a l o g i c a l method. Emphasis w i l l be on s i m p l i c i t y of technique, minimum computer time, and minimum d e g r a d a t i o n of d a t a . A f t e r a technique has been s e l e c t e d , a computer program w i l l be developed f o r AAP f l i g h t d a t a . An i n f o r m a t i o n a l document compiled f o r t h e ATM and OWS m i s s i o n s c o n t a i n s g e n e r a l in£ ormation, experiment o b j e c t i v e s , and i n s t r u m e n t a t i o n d e s c r i p t i o n . The document w i l l be used f o r background i n f o r m a t i o n and w i l l be updated a s r e q u i r e d . VIII. PROJECTS OFFICE 1. S a t u r n V SE&IS C o n t r a c t As a r e s u l t of s e v e r a l weeks of c o n c e n t r a t e d e f f o r t , R-AERO-P has s u c c e s s f u l l y e s t a b l i s h e d coordinated document d e l i v e r y s c h e d u l e s f o r R-P&VE, R-ASTR, and TBC. This r e s c h e d u l i n g e f f o r t was brought a b o u t by t h e new S a t u r n V launch schedule (Apollo Program D i r e c t i v e 4G). The r e s c h e d u l i n g c y c l e a l s o included a complete rework and r e s c h e d u l i n g of GFD requirements i n s u p p o r t of t h e TBC SE&IS c o n t r a c t . �2. F l i g h t Mechanics Panel Meeting The Twenty-First Meet.ing of t h e FMP was held a t MSFC on J u l y 12 and 13, 1967. A resumc of some of t h e more important items from t h e meeting i s a s f o l l o ~ ? s : ( a ) The L/V and S/C program managers a r e b e i n g r e q u e s t e d t o emphasize t h e f o r m u l a t i o n of checkout procedures, e t c . , t o accommodate a n on-time (or near-on-time) launch which i s r e q u i r e d f o r t h e pol lo/ S a t u r n rendezvous m i s s i o n . (b) The FMP w i l l e x p e d i t e s t u d i e s on t h e f o l l o w i n g AS-503 c a n d i d a t e p r o f i l e s and make a recommendation on which one t o implement f o r t h e miss ion: (1) S-IVB r e s t a r t f o r a 10-second burn w i t h SIC a t t a c h e d a b o u t 90 minutes a f t e r o r b i t a l i n s e r t i o n ( i n t h e e v e n t t h a t SIC checkout r e q u i r e s more than 90 minutes t h e second burn w i l l occur a t a b o u t 180 m i n u t e s ) . (2) S-IVB r e s t a r t f o r a 30 t o 40 second b u r n , SIC a t t a c h e d , w i t h a 45O yaw a t t i t u d e a b o u t 90 minutes a f t e r o r b i t a l i n s e r t i o n and a second r e s t a r t a f t e r LV/ SC s e p a r a t i o n . (3) Perform two S-IVB r e s t a r t s a f t e r LV/SC s e p a r a t i o n w i t h a f i r s t : burn of a b o u t 50 seconds. Due d a t e f o r t h e FMP recommendation i s August 14, 1967. ( c ) The FMP w i l l c o o r d i n a t e a meeting f o r a n o v e r a l l review of A p o l l o I S a t u r n I B and V ( i . e . , L/V and SIC) one-engine-out and EDS problems. This w i l l i n c l u d e Crew S a f e t y P a n e l , Mechanical Panel and o t h e r MSFC & MSC personnel. Date f o r t h e meeting i s Thursday, August 1 0 , 1967, a t MSFC. (d) MSC a g r e e s t h a t t h e SIC has no requirement t o reduce t h e maximum S-IC l o n g i t u d i n a l a c c e l e r a t i o n on AS-502 below a 30 v a l u e of (The s e r v i c e module a f t bulkhead problem i s being "fixed" 4.840 g ' s . by MSC.) ( e ) The LVISC i n t e r f a c e s i g n a l s r e l a t i n g t o f l i g h t mechanics a r e b e i n g reviewed and updated on a l l A p o l l o / S a t u r n I B and V m i s s i o n s . The minutes of t h e meeting have been d i s t r i b u t e d i n Memo R-AERO-P-286-67, dated J u l y 13, 1967. �BIBLIOGRAPHY 1. Weidner, D. K. and C . L. H a s s e l t i n e , " N a t u r a l Environment Design C r i t e r i a G u i d e l i n e s f o r MSFC Voyager S p a c e c r a f t f o r Mars 1973 M i s s i o n , " TM X-53616, June 8 , 1967, U n c l a s s i f i e d . 2. Heybey, W. H . , "On Mixed F.eflection o f S u n l i g h t , J u n e 8 , 1967, U n c l a s s i f i e d . 3. H u f f a k e r , R. M. and M. J . Dash, "A G e n e r a l Program f o r t h e C a l c u l a t i o n o f R a d i a t i o n f o r a n Inhomogeneous, N o n i s o b a r i c , Nonisothermal Rocket Exhaust Plume," TM X-53622, June 1 9 , 1967, U n c l a s s i f i e d . 4. F a l l s , Lee W . , "Peak S u r f a c e Wind Exposure P e r i o d S t a t i s t i c s f o r Cape Kennedy, F l o r i d a , " TM X-53624, J u n e 20, 1967, U n c l a s s i f i e d . 5. H u f f a k e r , R. M . , "Inhomogeneous R a d i a n t Heat T r a n s f e r from S a t u r n Type Rocket Exhaust Plumes," TM X-53630, J u n e 3 0 , 1967, U n c l a s s i f i e d . 6. Wheeler, J o h n T . , " A p p l i c a t i o n o f Higher Order Runge-Kutta I n t e g r a t i o n Techniques Developed by Erwin F e h l b e r g t o Low-Thrust T r a j e c t o r i e s , " TM X-53631, June 30, 1967, U n c l a s s i f i e d . 7. Papadopoulos, J . G . , " A e r o e l a s t i c Load Growth E f f e c t s o n S a t u r n C o n f i g u r a t i o n s , " TM X-53634, J u l y 1 4 , 1967, U n c l a s s i f i e d . 8. Lee, R. F . , J. W. Ownbey and F. T. Q u i n l a n , " ~ h u n d e r s t o r m P e r s i s t e n c e a t Cape Kennedy, F l o r i d a , " TM X-53635, J u l y 1 7 , 1967, U n c l a s s i f i e d . 9. T o e l l e , R. G . , "A Performance Study f o r t h e A p p l i c a t i o n o f t h e S a t u r n V t o High Energy M i s s i o n s , " TM X-53639, J u l y 3 1 , 1967, Unclassified. 10. S c o g g i n s , James R . , "some P r o p e r t i e s o f Low A l t i t u d e Atmospheric T u r b u l e n c e a t Cape Kennedy, F l o r i d a , " TM X-53640, J u l y 31, 1967, Unclassified. 11. B a l l a n c e , James O . , "An A n a l y s i s o f t h e M o l e c u l a r K i n e t i c s o f t h e Thermosphere P r o b e , " TM X-53641, J u l y 3 1 , 1967, U n c l a s s i f i e d . 12. B a l l a n c e , James O . , "Wake and I n t e r r e f l e c t i o n E f f e c t s i n t h e Calcul a t i o n o f F r e e M o l e c u l a r Flow Drag C o e f f i c i e n t s , " TM X-53642, J u l y 3 1 , 1967, U n c l a s s i f i e d . It TM X-53617, �RIBLIOGRAPlFY (Continued) 13. P e r r i n e , B. S., "A Method o f S o f t Tether S t a t i o n k e e p i n g , " TM X-53643, J u l y 31, 1967, U n c l a s s i f i e d . 14. Bauer, E t h e l H . , "Launch Vehicle T a r g e t i n g Using t h e Hypersurface Concept," R-AERO-IN-4-67, June 27, 1967, U n c l a s s i f i e d . 15. Weidner, D. K., "A P r e l i m i n a r y Summary o f t h e MSFC P l a n e t a r y Atmosphere Computer Program," R-AERO-IN-5-67, June 30, 1967, Unclassified. APPROVAL Deputy D i r e c t o r , Aero-Astrodynamics Laboratory E. D. Geiss1e.r D i r e c t o r , Aero-Astrodynamics Laboratory DISTRIBUTION R-AERO-DIR Dr. Geissler M r . Jean I-v-P Harold P r i c e M r . Jennings R-AERO- R M r . B u t l e r (4) Mrs. Hightower R-AERO-P R-AERO-D R-AERO-A R-AERO-G R- AERO-Y R-AERO-F R-AERO-X R-DIR PAO, M r . Kurtz MS-H, Miss J e r r e l l ( 3 ) (8) (16) (20) (6) (5) (8) (2) R- AERO- T Mr. Mr. Mr. Dr. Mr. Dr, Dr. Mr. Mr. Dr. von Puttkamer Murphree Cummings Heybey Jandebeur Liu Krause Few Nathan Sperling � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000045 Title A name given to the resource "Aero-Astrodynamics Laboratory Bimonthly Progress Report: June - July 1967." Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center Date A point or period of time associated with an event in the lifecycle of the resource 1967-08-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) NASA space programs Project management Type The nature or genre of the resource Progress reports Text Source A related resource from which the described resource is derived Saturn V Collection Box 23, Folder 33 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050 https://digitalprojects.uah.edu/files/original/20/993/spc_stnv_000046.pdf b7ae59395c9825efe50a5ed27b15a2ac PDF Text Text AERO-ASTRODYNAMICS LABORATORY BIMONTHLY PROGRESS REPORT October-November 1968 INDEX Page ......................... PROJECTS OFFICE ........................................ SCIENTIFIC AND TECHNICAL STAFF ................................ AEROPHYSICS DIVISION ................................... A . F l u i d Mechanics Research O f f i c e .................... B . Mechanical Design O f f i c e ........................... C . Aerodynamic Design Branch .......................... D . Thermal Environment Branch ......................... E . Experimental Aerophysics Branch .................... F . Unsteady Gas Dynamics Branch ....................... ADVANCED STUDIES OFFICE ......................... ......................... . ..................... ........................... . ASTRODYNAMICS AND GUIDANCE THEORY DIVISION ............. A . Guidance Theory Branch ............................. B . Astrodynamics Branch ............................... C . O p t i m i z a t i o n Theory Branch ......................... DYNAMICS AND FLIGHT MECHANICS DIVISION ................. V I I. A . M u l t i - P r o j e c t s ..................................... B., S a t u r n V ........................................... C . S a t u r n Apollo A p p l i c a t i o n s Program ................. D . General ............................................ V I I I . FLIGHT TEST ANALYSIS DIVISION .......................... A . S p e c i a l P r o j e c t s O f f i c e and S t a f f .................. B . F l i g h t E v a l u a t i o n Branch ........................... C . Tracking and O r b i t a l A n a l y s i s Branch ............... AEROSPACE ENVIRONMENT DIVISION A Atmosphere Dynamics Branch B T e r r e s t r i a l Environment Branch C Space Environment Branch . D . F l i g h t Mechanics Branch ............................ �AERO-ASTRODYNAMICS LABORATORY BIMONTHLY PROGRESS REPORT October-November 1968 SCIENTIFIC AND TECHNICAL STAFF J - 2 s Rendezvous and Guidance Study (Few1 - 1. Guidance Analysis Modified v e r s i o n s of IGM t o more a c c u r a t e l y c a l c u l a t e range a n g l e s a r e being i n v e s t i g a t e d . IGM flown f o r boostc o a s t - b o o s t has shown t h a t range a n g l e c a l c u l a t i o n s a r e inadequate over It has been determined t h a t t h e e x i s t t h e d u r a t i o n of t h e c o a s t p e r i o d . ing IGM f o r m u l a t i o n can be improved by optimizing two miss ion-dependent c o n s t a n t s which b i a s range a n g l e p r e d i c t i o n s f o r t h e s p e c i f i c p r o f i l e . However, t h i s i s n o t des i r a b l e from a n o p e r a t i o n a l p o i n t of view, because t h e s e c o n s t a n t s a r e dependent upon launch window v a r i a t i o n s . Three methods of p r e d i c t i n g time- to-go a r e being i n v e s t i g a t e d f o r a v e h i c l e w i t h t h r o t t l i n g i n t h e f i n a l b o o s t phase. Each of t h e s e methods employ d i f f e r e n t techniques t o s o l v e v e h i c l e range a n g l e and s a t e l l i t e positions. One of t h e s e schemes shows promise f o r the nominal c a s e i n terms of rendezvous e r r o r s and t h r u s t s t a b i l i t y . However, d i s persed cases must s t i l l be e v a l u a t e d . Also, t h r o t t l i n g t h e engine i n s t e p s r a t h e r than c o n t i n u o u s l y i s being reviewed i n terms of guidance s t a b i l i t y and rendezvous e r r o r s . - P r e l i m i n a r y d a t a from t h r o t t l i n g S - I 1 2. Performance Analysis and S-IVB t o c i r c u l a r e a r t h o r b i t (100,262 and 500 N.Mi.) i n d i c a t e t h a t a c o n s i d e r a b l e payload i n c r e a s e i s r e a l i z e d over d i r e c t b o o s t . With t h r o t t l i n g t o 50,000 l b s / e n g i n e (minimum o p e r a t i o n a l l i m i t ) , a p p r o x i mately 55 p e r c e n t of t h e payload l o s s which r e s u l t s when d i r e c t b o o s t i s used i n s t e a d of Hohrnann t r a n s f e r (boos t-coas t-boos t ) may be recovered by u s i n g t h r o t t l i n g . This i s based on o p t i m i z a t i o n of t h e S-IC t i l t p r o f i l e and t h r o t t l i n g i n t h e S-11; t h e g a i n i s o n l y approximately 40 p e r c e n t . 11. PROJECTS OFFICE During October and November, a c o n s i d e r a b l e e f f o r t was d i r e c t e d toward r e s o l u t i o n of RID'S from t h e ATM and LM-A PDR'S d e a l i n g w i t h a 1 t e r n a t e m i s s i o n s , c r i t i c a l time l i n e s , and a t t i t u d e time l i n e s . B r i e f l y , t h e r e s u l t has been t o e l i m i n a t e t h e a l t e r n a t e decoupled m i s s i o n ( a l t e r n a t e being d e f i n e d a s decided upon a f t e r AAP-4 launch a s opposed t o backup which i s s e l e c t e d b e f o r e AAP-4 l a u n c h ) . The �backup m i s s i o n has been c o n s t r a i n e d t o t h e p o i n t t h a t i t w i l l i n p r o f i l e look much 1 i k e t h e primary m i s s i o n ; t h u s , no new d e s i g n requirements s l ~ o u l dbe g c n e r a t c d by t h e decoupled mission. The s t r e a m l i n i n g of t h e M P - 4 m i s s i o n w i l l r e s u l t i n handsome c o s t b e n e f i t s by a l l o w i n g some r e d u c t i o n s , and c e r t a i n l y n e g o t i a t i n g some proposed i n c r e a s e s i n c o s t The f i r s t phase of t h i s e f f o r t is scheduled f o r completion on December 15, 1968. . 111. ADVANCED STUDIES OFFICE A. A s trodynamics and Mission A n a l y s i s Group 1'. Unmanned P l a n e t a r y D e t a i l e d miss i o n d e s i g n S a t u r n passage c o n d i t i o n s ( i n s i d e o r Uranus and Neptune passage d i s t a n c e s performed under c o n t r a c t NAS8-20082, (TM 54130-199). charts f o r earth-depart energies, o u t s i d e t h e r i n g s of S a t u r n ) , and have been completed. The work, i s documented i n LMSC/HREC A791951 Charts a r e b e i n g prepared t o i n d i c a t e t h e performance p e n a l t y ( i n terms of AV) when r e s t r i c t i o n s a r e placed on passage d i s t a n c e s a t J u p i t e r and S a t u r n . P r e l i m i n a r y d a t a have been s e n t t o M r . Guttman, R-ASTR-A, showing t h e v e l o c i t y requirements n e c e s s a r y t o change t h e impact parame t e r a t t h e s p h e r e of i n f l u e n c e f o r J u p i t e r , S a t u r n , and Uranus. The d a t a were based on t y p i c a l approach v e l o c i t i e s f o r t h e t r a n d t o u r miss ions. 2. S a t u r n V OWS/NPS I n t e g r a t i o n Study R-ASTR-AG has r e q u e s t e d (1) p r e l i m i n a r y d a t a d e f i n i n g t h e rendezvous c o r r i d o r s and l o c a t i o n from t h e c e n t e r l i n e of t h e S a t u r n V o r b i t a l workshop/nuclear e l e c t r i c power system (OWSINPS) c l u s t e r v e r s u s time f o r l o g i s t i c s s u p p l y v e h i c l e s and remote modules, (2) d a t a necess a r y t o determine t h e number of times t h e CSM might b e used f o r tugging remote modules t o and from experiment l o c a t i o n s and t h e concomitant t r a j e c t o r i e s , and (3) d a t a which d e f i n e t h e p r o p u l s i o n requirements and c r i t e r i a f o r mode s e l e c t i o n f o r r e a c t o r d i s p o s a l ( d e o r b i t f o r ocean d i s p o s a l w i t h impact d i s p e r s i o n r e s u l t i n g from p e r t u r b a t i o n s i n t h r u s t v e c t o r magnitude and alignment v e r s u s i n j e c t i o n i n t o a l o n g - l i v e d o r b i t ) . �A l l d a t a excluding t h e impact d i s p e r s i o n have been computed and a copy d e l i v e r e d t o M r . L. W. B r a n t l e y . The impact d i s p e r s i o n d a t a a r e being computed, and m o d i f i c a t i o n s of t h e remote module t r a j e c t o r i e s which r e s u l t i n t h e i n c u r r e n c e of a s m a l l e r r a d i a t i o n dose a r e being investigated. 3. Computer Program Development a. S p a c e c r a f t Communications and O r i e n t a t i o n Angles Program A computer program has been developed t o a n a l y z e spacec r a f t p l a n e t o c e n t r i c passage c o n d i t i o n s f o r t h e Grand Tour m i s s i o n s . The program c a l c u l a t e s s p a c e c r a f t communication d i s t a n c e s and a n g l e s , o r i e n t a t i o n a n g l e s , and o c c u l t a t i o n s w i t h r e s p e c t t o t h e Sun, E a r t h , and Canopus. A r i n g model f o r S a t u r n has been i n c o r p o r a t e d t o d e t e r mine t h e r i n g passage c o n d i t i o n s ( i n s i d e o r o u t s i d e of S a t u r n ' s r i n g s ) . b. Fly-By O c c u l t a t i o n Program A computer program i s being developed t o a s s e s s the These occul t a o c c u l t a t i o n regions f o r planetary fly-by t r a j e c t o r i e s t i o n r e g i o n s can be viewed i n t h e R-T plane by p a r a m e t e r i z i n g t h e impact parameter B. A t p r e s e n t , t h e program c o n s i d e r s o c c u l t a t i o n s w i t h r e s p e c t t o Sun, E a r t h , and Canopus . . B. F l i g h t Mechanics and Performance Analysis Group 1. Space S t a t i o n The j o i n t s t a t e m e n t of work f o r t h e space s t a t i o n has been prepared. Headquarters has d r a f t e d a combined s t a t e m e n t of work drawing i n p u t s from MSFC and MSC. For t h e most p a r t , i t was a n MSFC s t a t e m e n t of work which was submitted t h e previous week. A team of Headquarters, MSC, LaRC, and MSFC met a l l week t o complete t h i s t a s k ; they reviewed i t w i t h M r . Mathews on November 22. I n g e n e r a l , t h e s t u d y w i l l be conducted a l o n g t h e l i n e s d e s i r e d by ASO. One prime concession Headquarters made, which b o t h MSC and MSFC wanted, was t h a t each c e n t e r w i l l n e g o t i a t e i t s own c o n t r a c t . S e v e r a l p o i n t s were decided which may be of i n t e r e s t a s follows: (a) b a s e l i n e w i l l b e a 9-man s t a t i o n , (b) LV f o r s t a t i o n w i l l b e S-IC S-11, S-IC S-IVB, S-IVB, o r 1.56" s o l i d + S-IVB, 260" s o l i d + + + �2. (c) LV f o r l o g i s t i c s w i l l be S a t u r n I B , T-IIIM, 260" s o l i d + S-IVB, o r 156" s o l i d + S-IVB, (d) l o g i s t i c s S / C w i l l be e i t h e r e x i s t i n g SIC, mods e x i s t i n g SIC, o r new SIC (MSC d i d not want t o cons i d e r e x i s t i n g S I C , and (e) experiments f o r s t a t i o n w i l l r e c e i v e major emphasis (MSC d i d n o t want t o denote much e f f o r t i n t h i s a r e a ) . E a r t h O r b i t a l Experiments A m i s s i o n a n a l y s i s has been performed i n s u p p o r t of the hydrogen maser c l o c k experiment t h a t w i l l t e s t t h e t h e o r y of r e l a t i v i t y . M r . Gregory of A s t r i o n i c s has been our p o i n t of c o n t a c t on t h e s t u d y . The experiment w i l l be i n s e r t e d i n t o a n i n c l i n e d synchronous o r b i t over H a w a i i by a T i t a n I I I C launched from ETR. We have g e n e r a t e d t h e performance, and d e f i n e d t h e f l i g h t environment ( a c c e l e r a t i o n s , dynamic p r e s s u r e , e t c . ) c o a s t i n b o t h parking and Hohmann t r a n s f e r o r b i t , and burn times. 3. The Launch Vehicle T r a j e c t o r y Optimization Computer Program (RFQ No. DCN-1-7-2100027) A c o n t r a c t has been awarded t o Northrop. Some meetings have been h e l d w i t h t h e c o n t r a c t o r s , and work has been s t a r t e d . Prel i m i n a r y i n d i c a t i o n s a r e that we can expect a good s t u d y . 4. Tip Tank We a r e s u p p o r t i n g t h e ILRV s t u d y and a l s o a t t e m p t i n g t o f i n d t h e impact on t h e v e h i c l e d e s i g n of r e l a t i v e c o s t d i f f e r e n c e s between v a r i o u s subsystems; i . e . , "What i s t h e e f f e c t on t h e optimum v e h i c l e d e s i g n i f t h e c o r e c o s t s twice a s much per pound a s does t h e t i p tanks"? I n t h i s c a s e t h e minimum l i f t o f f weight i s n o t t h e o p t i mum d e s i g n . C. Sys tem A n a l y s i s Group A $250,000 c o n t r a c t e n t i t l e d "Study of S a t u r n V D e r i v a t i v e (s-IC/S-IVB) Launch Vehicle System" NAS8-30506 was awarded t o t h e Boeing Company on a s o l e s o u r c e b a s i s on November 4 . Members of t h i s o f f i c e p a r t i c i p a t e d i n t h e t e c h n i c a l e v a l u a t i o n of t h e proposal and a r e members of t h e t e c h n i c a l panel t h a t w i l l d i r e c t t h e s t u d y . McDonnel Douglas A s t r o n a u t i c s Company and I n t e r n a t i o n a l Bus i n e s s Machines were subcont r a c t e d by TBC f o r s u p p o r t i n t h e a r e a s of S-IVB s t a g e d e s i g n and �a s t r i o n i c s system d e s i g n , r e s p e c t i v e l y . The o b j e c t of t h e 10-month (8 t e c h n i c a l , 2 r e p o r t i n g ) s t u d y i s t o provide a d e t a i l e d p r e l i m i n a r y d e s i g n of t h e S-Ic/S-IVB/IU launch v e h i c l e system. The 8-month t e c h n i c a l p o r t i o n of t h e c o n t r a c t w i l l c o n s i s t of a t r a d e s t u d y (Phase I ) , a prel i m i n a r y d e s i g n s t u d y (Phase 1 1 ) , and d e f i n i t i o n of a d e s i g n , development, t e s t , and e v a l u a t i o n p l a n (Phase 111). This s t u d y w i l l r e c e i v e i n p u t s from a launch f a c i l i t i e s s t u d y being done f o r KSC by Boeing and from t h e J - 2 s i n t e g r a t i o n s t u d y . �IV. AEROPHYSICS DIVISION A. F l u i d Mechanics Research Off i c e - - (1) The helium h e a t e r was b e i n g checked o u t . (2) From t h e a n a l y s i s of t h e r e s u l t s of p a s t crossed-beam t e s t s , i t was decided t h a t a thorough c a l i b r a t i o n of t h e crossed-beam s y s tem was n e c e s s a r y . Crossed-Beam S t u d i e s Crossed-beam t e s t s were suspended TAJF on October 1 i n t h e MSFC Thermo-Acoustic J e t F a c i l i t y f o r two main reasons : On November 26, t h e crossed-beam system frame i n t h e TAJF was found t o be i n o p e r a b l e and had t o b e modified. These m o d i f i c a t i o n s a r e i n p r o g r e s s . Three t e s t s i n t h e TAJF a r e planned f o r t h e n e a r f u t u r e . B. Mechanical Des i g n Off i c e 1. Cryo-Panels f o r t h e 1 8 - f o o t Diameter IBFF Vacuum Tank P r e l i m i n a r y d e s i g n s t u d i e s have begun on cryo-panels f o r t h e 1 8 - f o o t diameter IBFF vacuum tank. The panels w i l l cover a l l i n t e r i o r s u r f a c e s and w i l l have removable, non-active s e c t i o n s over t h e windows and manways. A t e s t panel f o r h e a t t r a n s f e r t e s t s i n t h e Low D e n s i t y Chamber i s b e i n g f a b r i c a t e d by ME Laboratory. The panel c o n s i s t s of a n aluminum honeycomb bonded t o a 118" t h i c k aluminum p l a t e w i t h m e t a l - f i l l e d epoxy. I f t h e s e t e s t s prove t h e e f f e c t i v e n e s s of t h e d e s i g n , t h e cryo-panel system w i l l be designed and s e n t t o ME Laboratory f o r in-house f a b r i c a t i o n . 2. Model Cover f o r t h e 18-foot Diameter IBFF Vacuum Chamber Design has been i n i t i a t e d on a model cover f o r t h e 18-foot diameter IBFF vacuum chamber. This cover w i l l be mounted i n s i d e t h e vacuum chamber and remotely c o n t r o l l e d t o cover and uncover IBFF models w i t h a vacuum- t i g h t e n c l o s u r e . This w i l l a l l o w i n s t a l l a t i o n and removal of models w i t h o u t l o s s of vacuum, thus i n c r e a s i n g t h e number of runs per day and d e c r e a s i n g pumping c o s t . 3. The f o l l o w i n g i s a p a r t i a l l i s t of p r o j e c t s and t h e i r current status. Sonic Nozzle, C. F.D. (AF) M o d i f i c a t i o n of Model No. 397, C.F.D (AF) Design Des i g n �P o s i t i o n i n g Equipment L a s e r , 7" WT (AF) Helium Vent T e s t Equipment, 14" WT (AD) X-Y-Z P o s i t i o n i n g Devices, L a s e r s , Rm. 215 (AF) P r e s s u r e Model, IBFF (AE) M o d i f i c a t i o n of Model No. 422, 14" WT (AE) E l e c t r o n Beam Gun, L.D.C. (AE) E l e c t r o n Beam C o l l e c t o r , L.D.C. (AE) E l e c t r o n Beam O p t i c a l System, L.D.C (AE) E l e c t r o n Beam P o s i t i o n i n g Device, L.D.C. (AE) Heated Plenum Chamber, L.D.C. (AE) F l a t P l a t e Heat T r a n s f e r Model, L.R.C. 4' WT (AT) 5-Component Micro-Force Balance, L.D.C. (AE) (AE) P r e s s u r e Model, 2.7" d i a . H.R.N. (AE) C a l i b r a t i o n Equipment, H.R.N. Redesigned Survey Probe, 14" WT (AE) Model No. 425, Curved C e n t e r l i n e Force Model 14" WT (AD) Camera Support Equipment, 14" WT (AD) Laser Beam Support Hardware (AF) Low Volume Diaphragm C u t t e r , IBFF (AE) T r a c e r M a t e r i a l System, X-Beam, S.T.S. 14" WT (AF) C. Des i g n Des i g n Des i g n Design Des i g n Des i g n Des i g n Design Des i g n Design Des i g n Des i g n Des i g n Fabrication Fabrication Fabrication Delivered Delivered Delivered Delivered Aerodynamic Design Branch 1. Saturn V a. Hydrogen Venting Study P o s s i b l e changes i n t h e S-IVB hydrogen tank v e n t v a l v e sequencing have g e n e r a t e d a need f o r some i n f o r m a t i o n a b o u t t h e concent r a t i o n l e v e l s of hydrogen surrounding t h e launch v e h i c l e d u r i n g f l i g h t . T e s t s w i l l b e conducted i n t h e MSFC 14-inch t r i s o n i c wind t u n n e l t o determine v e l o c i t y and c o n c e n t r a t i o n decay of a helium j e t e x i t i n g normally from a c i r c u l a r p o r t i n t h e s i d e w a l l . Helium i s used a s a s i m u l a n t f o r hydrogen s i n c e t h e two a r e c l o s e i n molecular weight. Combinations of t h e following t e s t parameters w i l l be i n v e s t i 0.9, 1.2, 1.96; r a t i o of j e t mass flow t o g a t e d : frustum Mach number 0.1, 1.0 and 10.0; j e t Mach number frustum mass flow ( p e r u n i t a r e a ) 0.3, 0.7 and 1.0; measurement l o c a t i o n s x / d = 15, 45, 100, y / d = 0 t o 20. - - - - Hardware i s b e i n g designed and t e s t s w i l l b e g i n a s soon a s t h e equipment i s a v a i l a b l e . A p r e t e s t r e p o r t which has more d e t a i l s of t h e t e s t approach i s n e a r l y completed. �b. I n t e r s t a g e Optimization Study A t e s t has been conducted i n t h e MSFC 14-inch TWT t o determine t h e e f f e c t s t h a t t h e removal of t h e i n t e r s t a g e e x t e r n a l coveri n g s (forward and a f t ) would have on t h e aerodynamic c h a r a c t e r i s t i c s of t h e S a t u r n V c o n f i g u r a t i o n . A 0.33-percent s c a l e model (No. 383) of t h e c o n f i g u r a t i o n , b u i l t i n a b u i l d i n g - b l o c k format, was t e s t e d w i t h s e v e r a l v a r i a t i o n s of t h e i n t e r s t a g e s . Mach number ranges from 0.50 t o 4.96 and a n g l e of a t t a c k ranges from -2 t o +12 degrees. Five-component f o r c e and base p r e s s u r e d a t a were o b t a i n e d f o r each c o n f i g u r a t i o n . A n a l y s i s of t h e t e s t d a t a i n d i c a t e s t h a t t h e z e r o a n g l e of a t t a c k s t a b i l i t y d e r i v a t i v e s f o r t h e S a t u r n V launch v e h i c l e were not a f f e c t e d ; however, t h e s t a b i l i t y d e g r a d a t i o n w i t h a l p h a f o r t h e S a t u r n V was reduced. A d d i t i o n a l t e s t s a r e planned f o r t h e MSFC 14-inch TWT on r e f i n e d o p e n - i n t e r s t a g e c o n f i g u r a t i o n s f o r t h e S a t u r n V. A r e p o r t documenting t h e s e r e s u l t s w i l l be prepared. c. S-IVB O r b i t a l R e s t a r t 5-2 Engine Plume Impingement Effects Plans f o r Mission D , p r e s e n t l y scheduled f o r AS-504, i n c l u d e demonstration of S-IVB r e s t a r t i n o r b i t . This o p e r a t i o n i s t o b e performed w i t h t h e Command Module s e p a r a t e d and l o c a t e d somewhere a f t of t h e S-IVB s t a g e . Consequently, t h e Command Module w i l l e x p e r i e n c e some degree of J - 2 engine plume impingement. The 5-2 engine plume and c e r t a i n a s p e c t s of i t s impingement a r e d e s c r i b e d i n o f f i c e memorandum R-AERO-A-68-32, d a t e d October 29, 1968. 2. AAP a. O r b i t a l Aerodynamics O f f i c e Memorandum, R-AERO-AD-68-64, " O r b i t a l Aerodynamic Data f o r S i x AAP O r b i t a l C o n f i g u r a t i o n s , " November 25, 1968, c o n t a i n s o r b i t a l aerodynamic d a t a f o r t h e following s i x con£ i g u r a t ions : (1) OWS w i t h t h e CSM a t p o r t f i v e and OWS s o l a r a r r a y s extended p e r p e n d i c u l a r t o t h e OWS l o n g i t u d i n a l a x i s . (2) OWS w i t h s o l a r a r r a y s n o t extended. (3) OWS w i t h s o l a r a r r a y s extended p e r p e n d i c u l a r t o t h e OWS a x i s . (4) OWS w i t h s o l a r a r r a y s extended p a r a l l e l t o t h e OWS longitudinal axis. �(5) OWS with docked CSM and LM/ATM (CSM docked a t p o r t f i v e , OWS s o l a r a r r a y s extended p a r a l l e l t o the OWS l o n g i t u d i n a l a x i s ) . (6) Same a s (5) b u t w i t h the CSM docked a t p o r t f o u r . A scope of work has been prepared f o r a proposed c o n t r a c t t o develop methods t o c a l c u l a t e o r b i t a l aerodynamics. The tasks t o be performed under t h i s c o n t r a c t would be a s follows: (1) Incorporate the Nocilla molecule r e f l e c t i o n model i n t o the e x i s t i n g computer program that i s p r e s e n t l y used t o c a l c u l a t e f r e e molecule aerodynamic c o e f f i c i e n t s . This model has advantages i n terms of g e n e r a l i t y , accuracy, and t r a c t a b i l i t y . It would provide a parametric expression f o r the complete v e l o c i t y function of re-emitted molecules which f o r t u i t o u s l y matches t o a considerable degree such observed d i s t r i b u t i o n s that a r e now a v a i l a b l e . (2) Provide w i t h i n the e x i s t i n g computer program the c a p a b i l i t y t o vary momentum and energy accommodation c o e f f i c i e n t s a s a f u n c t i o n of s u r f a c e o r i e n t a t i o n , s u r f a c e temperature, and any other p e r t i n e n t parameters. (3) Through a l i t e r a t u r e search, summarize a v a i l a b l e experimental and t h e o r e t i c a l s t u d i e s that have been performed t o d e t e r mine momentum and energy accommodation c o e f f i c i e n t s . Based on t h i s search, recommend values of t h e momentum and energy accommodation coeff i c i e n t s t h a t would be a p p r o p r i a t e f o r use i n the c a l c u l a t i o n of aerodynamic c o e f f i c i e n t s f o r v e h i c l e s i n e a r t h o r b i t and d e f i n e a r e a s i n which experimental s t u d i e s a r e needed t o provide a b e t t e r d e f i n i t i o n of t h e s e c o e f f i c i e n t s f o r conditions t h a t e x i s t on v e h i c l e s i n e a r t h o r b i t . This c o n t r a c t would be funded by OMSF work u n i t 908-10-10-08-62; the estimated c o s t is $40,000. b. Saturn IB/AAP I1 - Solar Panel Shroud Pressure Tests t o determine load d i s t r i b u t i o n over the s o l a r panel shroud of the Saturn IB/AAP I1 with the new payload configuration w i l l be conducted i n the MSFC 14-inch t r i s o n i c wind tunnel f o r Mach numbers from 0.8 t o 1.96 and r o l l angles of 0 and 90 degrees. Tests w i l l commence during the week of December 9 , 1968. c. AAP Plume Impingement I n v e s t i g a t i o n Phase I t e s t s a r e continuing i n t h e MSFC base flow f a c i l i t y i n support of AAP plume impingement s t u d i e s . The Phase I e f f o r t i s concerned w i t h a p i t o t pressure survey of an H2/02 5-2 engine �plume. The experimental d a t a w i l l be compared with t h e o r e t i c a l 5-2 motor plumes derived f o r the proposed t e s t conditions. These comparisons w i l l d e f i n e the degree of consistency between experimental and a n a l y t i c a l plume c r i t e r i a . A Phase I1 study, t o begin December 16, 1968, w i l l determine pressures and h e a t t r a n s f e r r a t e s on a f l a t p l a t e immersed i n t h e 5-2 plume. The p l a t e angle of a t t a c k , a x i a l and r a d i a l l o c a t i o n i n the plume w i l l be v a r i e d . The d a t a f o r small d e f l e c t i o n angles w i l l be used t o confirm empirical modifications t o Newtonian Impact Theory f o r small d e f l e c t i o n angles. Progress during Phase I has been very slow due t o limited manpower and our lack of experience i n conducting t e s t s of t h i s type. A memorandum documenting the o v e r a l l experimental and a n a l y t i c a l e f f o r t i n support of AAP plume impingement i s being prepared, including a n t i c i p a t e d completion d a t e s based on c u r r e n t manpower and funding l e v e l s . d. Saturn I B AAP Local pressure d i s t r i b u t i o n s f o r the Saturn I B O r b i t a l Workshop payload shroud were defined a t Mach numbers from 0.8 t o 2.99. Maximum and minimum pressure c o e f f i c i e n t s were defined a s a function of l o n g i t u d i n a l s t a t i o n a t each Mach number. The maximum pressure coeff i c i e n t a t angle of a t t a c k occurs on the windward s i d e of the v e h i c l e , and the minimum pressure c o e f f i c i e n t occurs on the leeward s i d e of the v e h i c l e . Maximum and minimum pressures do n o t n e c e s s a r i l y occur on the c e n t e r l i n e of the v e h i c l e . Maximum pressures a r e usually c l o s e t o the c e n t e r l i n e , while minimum pressures u s u a l l y occur zero t o 30' from the c e n t e r l i n e on t h e leeward s i d e of the v e h i c l e . These d a t a , based on wind tunnel t e s t of a small s c a l e model conducted i n the MSFC 14-inch t r i s o n i c wind tunnel, a r e published i n o f f i c e memorandum R-AERO-AD-68-58. 3. General a. Saturn Venting Contract NAS8-20200 w i t h Nortronics-Huntsville has been concluded. A f i n a l r e p o r t containing an a n a l y s i s of the Ames o r i f i c e flow c o e f f i c i e n t d a t a i s being published. Future work i n support of r e f i n i n g Saturn venting design c r i t e r i a w i l l include t h e determination of v e n t c h a r a c t e r i s t i c s located i n adverse flow f i e l d s . Undesirable flow f i e l d s may be caused by various protuberances and frustum-cylinder junctions which could have a b e n e f i c i a l o r unfavorable e f f e c t on v e n t performance. �It i s p r e s e n t l y planned t o do a d d i t i o n a l experimental work which w i l l supplement t h a t of Ames, a s w e l l a s ' t h e a d v e r s e flow f i e l d s t u d i e s . The m a j o r i t y of t h e s e programs w i l l be c a r r i e d o u t i n t h e MSFC 14-inch TWT. b. Nonlinear L i f t of Bodies of Revolution The c o n t r a c t o r , CCSD, has n e a r l y completed t h e Phase I f i n a l r e p o r t . Phase I c o n s i s t e d of o b t a i n i n g a complete p r e s s u r e d i s t r i b u t i o n on o g i v e - c y l i n d e r and o g i v e - c y l i n d e r - f r u s tum-cylinder b o d i e s i n t h e MSFC 14-inch TWT. Phase 11 i n c l u d e s a p r e s s u r e r a k e s u r v e y of t h e v o r t e x flow f i e l d behind a n o g i v e - c y l i n d e r - f r u s tum-cyl i n d e r t e s t model c o n f i g u r a t i o n a t a n g l e of a t t a c k . Because of t h e d e l a y s encountered d u r i n g t h e Phase I t e s t i n g due t o t u n n e l s c h e d u l e s l i p p a g e and a low r u n r a t e , Phase I1 . of t h e c o n t r a c t scope of work cannot be completed w i t h i n t h e o r i g i n a l p e r i o d of performance and funding. The p e r i o d of performance i s being extended t o J a n u a r y 15, 1969, t o accomplish a s much work a s p o s s i b l e w i t h t h e s m a l l amount of funds remaining. A new scope of work i s being developed which w i l l extend t h e Phase I1 s t u d y t o a s u b s o n i c Mach number; i t w i l l i n c l u d e a n o g i v e - c y l i n d e r c o n f i g u r a t i o n . Phase I1 i s t e n t a t i v e l y scheduled i n t h e MSFC 14-inch TWT f o r A p r i l 1969. c. Body of Revolution Viscous Cross-Flow I n v e s t i g a t i o n The p r e t e s t conference a t LTV on t h e 4.0-inch diameter p r e s s u r e model has been postponed due t o a d d i t i o n a l d e l a y s of model d e s i g n and f a b r i c a t i o n . A scope of work i s being prepared s o l i c i t i n g b i d s f o r d e s i g n and f a b r i c a t i o n of t h i s model. The flow v i s u a l i z a t i o n phase of t h e MSFC t e s t s has been r e s c h e d u l e d f o r December 1968 J a n u a r y 1969, and w i l l be conducted by MSFC p e r s o n n e l r a t h e r t h a n CCSD. - d. Cone-Cylinder Local Normal Force G r a d i e n t s During t h i s r e p o r t i n g p e r i o d , a 25-degree cone-cylinder p r e s s u r e model was t e s t e d i n t h e 14-inch t r i s o n i c wind t u n n e l a t Mach numbers of 2.99 and 4.00 f o r a n g l e s of a t t a c k from -2 t o -6 d e g r e e s . These t e s t s were performed t o p r o v i d e d e t a i l e d experimental l o c a l normal f o r c e g r a d i e n t d i s t r i b u t i o n s f o r comparison w i t h a method-of - c h a r a c t e r Initial i s t i c s s o l u t i o n b e i n g developed by M r . J o e L. Sims, R-AERO-AF. e v a l u a t i o n of t h e d a t a has i n d i c a t e d some good r e s u l t s . �e. C a l i b r a t i o n of High Reynolds Number Equipment A c a l i b r a t i o n rake is being designed t o survey the flow f i e Ld of the High Reynolds Number Equipment. The rake i s of cruciform c o n f i g u r a t i o n and contains i n each arm s e v e r a l f i v e - p o r t conical pressure probes, which w i l l measure both the l o c a l Mach number and flow d i r e c t i o n i n one operation. This method w i l l reduce t h e number of runs necessary during the c a l i b r a t i o n procedure. The survey probe t o be used i n t h e rake w i l l be c a l i b r a t e d and checked f o r dynamic c h a r a c t e r i s t i c s i n the MSFC 14-inch TWT i n e a r l y 1969. f. Saturn S-IVB F l i g h t Evaluation The aerodynamic evaluation of AS-205 was limited s i n c e only t h r e e aerodynamic pressures were measured and the v e h i c l e angle of a t t a c k was too small t o allow normal f o r c e and center-of-pressure d e t e r minations. The pressures measured were compared w i t h previous f l i g h t d a t a and found t o be a s expected. The aerodynamic evaluation f o r AS-205 i s cons idered complete. D. Thermal Environment Branch 1. High Angle of Attack Heating Test The e v a l u a t i o n of the r e s u l t s of Mach 2.5 and 3.7 phases of t h e t e s t continues. The Langley time-integrated constant-heat input method of obtaining h e a t r a t e s from the thermocouple temperature h i s t o r i e s has been compared w i t h a more e x a c t procedure which assumes a time-varying h e a t input. The r e s u l t s show good agreement a t the e a r l y t e s t times and then diverge, with the varying-heat input method being lower. The f i n a l t e s t phase a t Mach 6 has been completed, and the d a t a were r e c e n t l y received from Langley Research Center. 2. LRC Protuberance Test Drafting of the f i n a l drawings of the t e s t p l a t e has begun. A sample of the t e s t p l a t e has been made t o e v a l u a t e s e v e r a l p o s s i b l e i n s t a l l a t i o n s of t h e thermocouples. A t e n t a t i v e t e s t d a t e of the f i r s t two weeks i n May 1969 has been e s t a b l i s h e d w i t h LRC. 3. E l e c t r o n Density The c a l c u l a t i o n of t h e e l e c t r o n d e n s i t y d i s t r i b u t i o n i n the i n v i s c i d plume and the shear l a y e r of the F-1 engine exhaust plume a t 10,000 f e e t a l t i t u d e has been completed. The Aero-Chem I n v i s c i d Streamline �Program has been modified t o f a c i l i t a t e i t s use by malcing communication 01 d a t a from the flow f i e l d programs d i r e c t and a u t o m a t i c . The c a p a b i l i t y t o r e s t a r t t h e c a l c u l a t i o n a l o n g a s t r e a m l i n e has been added t o prov i d e an a c c u r a t e method t o compute e n t i r e nozzle l e n g t h s w i t h o u t r e q u i r i n g e x c e s s i v e blocks of computer r u n times. 4. Vacuum Expans i o n Study The purpose of t h i s i n v e s t i g a t i o n i s t o develop a mathem a t i c a l technique f o r t h e d e s c r i p t i o n of t h e high a l t i t u d e and space environment expansion of a n axisymrnetric gaseous j e t . An experimental program w i l l be conducted t o provide experimental d a t a f o r comparison with a n a l y t i c a l predictions. A s e t of p a r t i a l d i f f e r e n t i a l e q u a t i o n s which d e f i n e t h e v e l o c i t y , d e n s i t y , and s t r e s s t e n s i o n i n the flow f i e l d have been d e r i v e d . This d e r i v a t i o n was made f o r a s i n g l e component, monatomic g a s , using t h e B-G-K approximation f o r t h e c o l l i s i o n i n t e g r a l . M e t h o d - o f - c h a r a c t e r i s t i c s s o l u t i o n s t o t h i s s e t of e q u a t i o n s have been developed f o r t h e c a s e s of n e g l i g i b l e and n o n - n e g l i g i b l e s h e a r s t r e s s . These s o l u t i o n s a r e c u r r e n t l y being programmed. 5. O p t i c a l Measurement of Plumes A cold flow t e s t was conducted a t AEDC w i t h a l a s e r doppler v e l o c i t y i n s t r u m e n t ( v e l o c i m e t e r ) t o determine t h e v e l o c i t y f i e l d i n t h e base and exhaust r e g i o n s of a f o u r n o z z l e model of t h e S a t u r n I1 type. The t e s t was a f i r s t e f f o r t t o use t h e v e l o c i m e t e r i n a low d e n s i t y s u p e r s o n i c flow. An e q u a l l y important purpose of t h e t e s t was t o e v a l u a t e t h e v e l o c i m e t e r and v e l o c i m e t e r s u p p o r t systems ( e l e c t r o n i c and contaminant systems) a s a n i n t e g r a t e d system. While t h e week of t e s t i n g did n o t produce t h e v e l o c i t y f i e l d , the s y s tem "shakedown" has provided a n important bas is f o r instrument changes t h a t should extend t h e i n s t r u m e n t range t o i n c l u d e flow f i e l d s of t h e type encountered i n t h e t e s t . 6. Miss i o n Support a. Shear Layers A s t u d y of t h e flow f i e l d c o n d i t i o n s t h a t r e s u l t when low temperature hydrogen i s vented i n t o a p a r a l l e l high temperature a i r s t r e a m was completed f o r those c o n d i t i o n s p r e s e n t a t 10 km of a S a t u r n V f l i g h t . The p h y s i c a l p r o p e r t i e s and chemical c o n s t i t u e n t s were evaluated u s i n g chemistry models of f r o z e n , f i n i t e r a t e and e q u i l i b r i u m . To d e t e r mine a s t a n d a r d s t a r t i n g l i n e f o r F-1 plume c a l c u l a t i o n s , a mixing �a n a l y s i s of t h e flow through the combustion chamber has been s t a r t e d . A new e q u i l i b r i u m ducted mixing program i s being a p p l i e d t o d e s c r i b e t h i s p o r t i o n of t h e nozzle flow. b. Nozzle and J e t Wake A d e t a i l e d s t u d y of t h e flow f i e l d i n t h e R ~ motor D i s i n progress f o r two f u e l / o x i d i z e r combinations. The study includes p r e d i c t i o n of continuum flow f i e l d c h a r a c t e r i s t i c s i n t h e combus t i o n chamber and nozzle i n a d d i t i o n t o continuum and free-molecular flow f i e l d c h a r a c t e r i s t i c s i n , t h e plume. The a n a l y s i s of t h e flow f i e l d f o r t h e Aerozine-50/Nitrogen-tetroxide system has been completed i n t h e continuum regime including t h e e f f e c t s of O/F g r a d i e n t s and frozen chemistry. The flow f i e l d i n t h e f r e e molecular regime i s being predicted . P r e d i c t i o n of t h e flow f i e l d f o r t h e Monomethyldrazine/ N i t r o g e n - t e t r o x i d e system is i n progress. E f f o r t s a r e c u r r e n t l y being concentrated on p r e d i c t i n g t h e continuum flow f i e l d c h a r a c t e r i s t i c s i n t h e combus t i o n chamber and nozzle. A usable condensation model f o r multi-component vapor expans i o n i s being e s t a b l i s h e d . The g r e a t e s t amount of experimental and t h e o r e t i c a l work done on condensation of expanding gases has been concerned w i t h pure vapors. For r e a l i s t i c a p p l i c a t i o n s , a n engineer must determine t h e e f f e c t s of condensation i n a m u l t i - s p e c i e s vapor. Modifications of e x i s t i n g pure vapor t h e o r i e s a r e being i n v e s t i g a t e d and used t o p r e d i c t t h e e f f e c t s of condensation i n a multi-component expand ing flow. 7. Laser Velocimeter S t u d i e s A l a s e r doppler velocimeter t h a t w i l l measure t h r e e veloci t y components i n a p a r t i c u l a r seeded flow has been developed and made o p e r a t i o n a l . I t i s c u r r e n t l y being used f o r flow v e l o c i t y and turbulence measurements i n t h e plume of a subsonic j e t . Future a p p l i c a t i o n s include s t u d i e s of t h e mixing r e g i o n of a s u p e r s o n i c j e t , flows around high angle of a t t a c k aerodynamic p r o f i l e s , and base flow i n t e r a c t i o n s . The f e a s i b i l i t y of using a C 0 2 l a s e r doppler velocimeter t o measure t h e v e l o c i t y of atmospheric motions has been demonstrated b o t h a n a l y t i c a l l y and experimentally. The design of a p r a c t i c a l prototype s y s tem t o measure ground wind v e l o c i t i e s i s complete and t h e s y s tem i s being f a b r i c a t e d . P o t e n t i a l a p p l i c a t i o n s t o long range wind v e l o c i t y measurement and c l e a r air turbulence d e t e c t i o n a r e being considered. �8. Plume Impingement Heating Heating r a t e s t o v a r i o u s components on t h e S a t u r n / ~ Pconf i g u r a t i o n due t o plume impingement a r e being c a l c u l a t e d . P r e l i m i n a r y v a l u e s have a l r e a d y been determined and d e l i v e r e d t o R-P&VE. These v a l u e s a r e now being r e f i n e d u s i n g more a c c u r a t e plume flow f i e l d chemistry and h e a t i n g r a t e c a l c u l a t i o n t e c h n i q u e s . S p e c i f i c a r e a s b e i n g cons i d e r e d a r e : 9. (1) Impingement of LM/RCS engine on MDA r a d i a t i o n . (2) Impingement of LN/RcS engines on f o l d e d ATM s o l a r panels (3) Impingement of CSM/RCSengines on unfolded ATM s o l a r panels. (4) Impingement of CSM/RCS engines on MDA forward cone. . Transonic S o l u t i o n A new technique t o s o l v e simultaneous p a r t i a l d i f f e r e n t i a l e q u a t i o n s , d e s i g n a t e d a s a f r e e - e r r o r minimization technique, has been a p p l i e d t o t h e r e l a t i v e l y simple c a s e of i s e n t r o p i c i n v i s c i d flow of a n i d e a l gas through a n o z z l e . The minimization technique s o l v e s t h e e n t i r e flow f i e l d ( s u b s o n i c , t r a n s o n i c , and s u p e r s o n i c ) a s a boundary v a l u e problem. To d a t e , t h e t r a n s o n i c and s u p e r s o n i c p o r t i o n s of t h e n o z z l e flow f i e l d a r e v e r y encouraging, a l t h o u g h t h e s u b s o n i c p o r t i o n i s n o t r e l a x i n g a s expected. The problems of s c a l i n g and i n t e r n a l and e x t e r n a l communication b e tween t h e t h r o a t r e g i o n and t h e en t r a n c e p l a n e a r e being explored. The i d e a l gas t r a n s o n i c r e s u l t s would i n d i c a t e t h a t t h i s method can b e used t o s o l v e much more complex f l u i d mechanics problems. 10. Continuum Heating and Miss i o n Support Work has begun on t h e modeling of t h e S a t u r n AS-501 v e h i c l e f o r t h e purpose of c a l c u l a t i n g clean-body h e a t i n g r a t e s u s i n g t h e Lockheed SHORE-CATCH computer program. Heating r a t e s w i l l be compared t o f l i g h t d a t a . I n a r e a s of p r o t u b e r a n c e s , t e s t d a t a w i l l be used t o a d j u s t t h e clean-body h e a t i n g r a t e s . Recommendations w i l l be made a s t o which a n a l y t i c a l techniques should b e used t o p r e d i c t aerodynamic h e a t i n g r a t e s on f u t u r e S a t u r n f l i g h t s . S i m i l a r o r b i t a l h e a t i n g r a t e s w i l l b e c a l c u l a t e d on t h e AS-203 v e h i c l e , and t h e r e s u l t s compared t o f l i g h t d a t a t o v e r i f y accuracy of t h e Heat Rate Program. �The SHORE-CATCH i s being modified t o add f l e x i b i l i t y i n i n p u t t i n g p r e s s u r e d a t a , and t o add t h e c a p a b i l i t y of c a l c u l a t i n g h e a t r a t e s i n t h e s l i p flow regime. E. Experimental Aerophysics Branch 1. Low Density Chamber Examination of t h e experimental j e t plume (C02) d a t a i n d i c a t e s t h a t t h e n o z z l e w a l l temperature f l u c t u a t i o n s a r e of such magnit u d e a s t o a d v e r s e l y a f f e c t t h e impact p r e s s u r e . Because of t h e long r u n times p o s s i b l e , a l a r g e amount of h e a t i s b e i n g t r a n s f e r r e d t o t h e n o z z l e w a l l ; t h e r e f o r e , a n a t t e m p t i s being made t o cool t h e n o z z l e w a l l ( o r a t l e a s t m a i n t a i n t h e w a l l a t a c o n s t a n t known temperature). The n o z z l e w a l l temperature i n v e s t i g a t i o n precedes f u r t h e r work w i t h a l a r g e r nozzle. A c l o s e r look w i t h t h e S a f e t y O f f i c e i n t o t h e p o s s i b i l i t y of u s i n g l i q u i d hydrogen i n t h e cryo-panels t o i n c r e a s e t h e c a p a b i l i t y of t h e Low Density Chamber r e v e a l s no insurmountable problem. An in-house s t u d y i s b e i n g done w i t h t h e end r e s u l t t o be a g u i d e l i n e d e s c r i b i n g why, where, and how we a r e going t o u s e t h e LH2 f o r p r e s e n t a t i o n t o t h e S a f e t y Off i c e . The e l e c t r o n beam work being c a r r i e d on by D r . B e y l i c h has progressed t o t h e p o i n t of r e c e i v i n g most of t h e ordered equipment and having t h e e l e c t r o n gun and a s s o c i a t e d hardware i n t h e f i n a l d e s i g n s t a g e s . This i n s t r u m e n t a t i o n i s t o be used i n t h e gas d e n s i t y d e t e r m i n a t i o n s of t h e p r e s e n t j e t plume work. I f t h e r e e x i s t s t h e p o s s i b i l i t y t o add N2 o r u s e N2 e n t i r e l y i n t h e j e t plume s t u d i e s , t h e n t h e e l e c t r o n beam measurements w i l l b e extended t o i n c l u d e r o t a t i o n a l temperature. 2. Impulse Base Flow F a c i l i t y The experimental program i n s u p p o r t of t h e S-IVB workshop plume impingement problems was continued. The e n t i r e analog d a t a r e c o r d ing system of o s c i l l o s c o p e s and cameras has been r e p l a c e d by t h e t h i r t y two-channel d i g i t a l d a t a s y s tem o r i g i n a l l y used f o r t h e shock t u n n e l . The s y s tem i s now o n - l i n e and working s a t i s f a c t o r i l y . A program f o r reducing t h e d i g i t a l d a t a a u t o m a t i c a l l y has been w r i t t e n and i s b e i n g used. This g r e a t l y reduces time and e f f o r t expended i n hand d a t a reduction a t the f a c i l i t y . As a segment of t h e c o n t i n u i n g e f f o r t t o i n c r e a s e t h e f a c i l i t y o u t p u t , a system t o i s o l a t e t h e engine model from t h e vacuum �t a n k a f t e r a r u n i s being designed. This s y s tem w i l l c o n s i s t of a l a r g e v a l v e t o b e c l o s e d a s t h e model p r e p a r a t i o n i s being done, t h e r e b y removi n g t h e n e c e s s i t y of v e n t i n g t h e e n t i r e tank a f t e r each r u n . The pacing i t e m w i l l then become t e c h n i c i a n e f f i c i e n c y r a t h e r than vacuum pumping c a p a c i t y . This i s expected t o more than double t h e f a c i l i t y o u t p u t . As a means of extending t h e c a p a b i l i t y of t h i s f a c i l i t y , a cryo-panel w i l l be i n s t a l l e d . It i s hoped t h a t t h i s panel w i l l a b s o r b t h e n o z z l e - s t a r t i n g shock system, a s w e l l a s t h e engine flow, and e f f e c t i v e l y extend t h e r u n time. Furthermore, a d d i t i o n a l a l t i t u d e s i m u l a t i o n c a p a b i l i t y w i l l be a v a i l a b l e . S t u d i e s a r e now a l m o s t complete f o r a l l phases. Two m a t e r i a l s have been s e l e c t e d f o r p o s s i b l e use i n f a b r i c a t i n g t h e cryo-panel: a bonded aluminum honeycomb and a n extruded f i n n e d aluminum. The honeycomb m a t e r i a l seems t o have aerodynamic advantages b u t thermal drawbacks; t h r e e t e s t specimens a r e being prepared by ME Laboratory f o r e v a l u a t i o n i n t h e Low Density Chamber. Scheduled d e l i v e r y f o r t h e s e specimens i s December 2, 1968. A t t h e c o n c l u s i o n of t h e s e e v a l u a t i o n t e s t s , t h e b e t t e r con£ i g u r a t i o n w i l l be s e l e c t e d , and d e t a i l d e s i g n and procurement on n e c e s s a r y items i n i t i a t e d . A s u r p l u s l i q u i d n i t r o g e n t a n k has been o b t a i n e d from R-TEST f o r cryogenic s t o r a g e . 3. High Reynolds Number Equipment The f i r s t low p r e s s u r e t e s t of t h e High Reynolds Number T e s t Equipment i s expected around t h e f i r s t of January. A l l t e s t hardware and a s s o c i a t e d equipment i s on hand e x c e p t t h e s u p e r s o n i c t e s t s e c t i o n which w i l l be shipped November 29, 1968. Welding and c l e a n i n g of t h e supply tube may s l i p t h e above t e s t d a t e . However, i f work c o n t i n u e s w i t h o u t d e l a y , t h e f i r s t of t h e y e a r seems r e a s onable. 4. Thermal A c o u s t i c J e t F a c i l i t y Two major problems remain i n t h e helium h e a t e r checkout by t h e c o n t r a c t o r (Fuel Engineering). The f i r s t , a temperature i n s t a b i l i t y i n t h e flow, i s being s t u d i e d by t h e c o n t r a c t o r and h i s c o n s u l t a n t , who a r e now of t h e o p i n i o n t h a t a redesigned s e t t l i n g chamber w i l l cure t h e i n s t a b i l i t y . The second problem i s that t h e temperature of t h e o u t p u t flow i s c o n s i d e r a b l y lower t h a n t h e s t o r a g e mass temperature, s u c h a s o n l y 900 OF f o r a s t o r a g e temperature of 1200 OF. This problem i s s t i l l unsolved . The cold flow d u c t was i n a c t i v e d u r i n g t h i s period b u t i s b e i n g r e a d i e d f o r f u r t h e r crossed-beam t e s t i n g . �5. 14 x 14-Inch T r i s o n i c Tunnel a. An i n v e s t i g a t i o n t o f u r n i s h d a t a f o r quasi-steady a n a l y s i s i n t h e production of aerodynamic damping of various launch The t e s t d a t a a r e v e h i c l e s was conducted by LMSC f o r R-AERO-AUA. r e q u i r e d f o r c o r r e l a t i o n w i t h t h e a n a l y t i c a l method and f o r e v a l u a t i n g t h e communication time o r l a g e f f e c t s on t h e flow f i e l d . The t e s t cons i s t e d of both forced and f r e e o s c i l l a t i o n dynamic t e s t i n g . Total runs: 68. b. An i n v e s t i g a t i o n t o f u r n i s h information on cross-beam survey of axisymmetric base flows i n t h e s p e c i a l t e s t s e c t i o n of t h e TWT was conducted by NSL f o r R-AERO-AE. This t e s t had four o b j e c t i v e s : (1) To determine t h e c h a r a c t e r i s t i c of a l a s e r crossbeam system when a p p l i e d t o base flow i n the modified s p e c i a l t e s t section. (2) To determine t h e adequacy of n a t u r a l t r a c e r s t o produce s u f f i c i e n t beam modulation o r t h e a r t i f i c i a l t r a c e r concentrat i o n r e q u i r e d f o r t h e s t u d y of t u r b u l e n t f r e e shear l a y e r s . (3) To determine a p p l i c a b i l i t y of p l e x i g l a s s o u t e r w a l l e x t e n s i o n f o r suppressing t h e l a r g e c o n t r i b u t i o n s t o t h e cross-beam s i g n a l s caused by t h e f r e e s h e a r l a y e r s of t h e o u t e r wall. (4) To determine t h e e f f e c t s of extraneous n o i s e sources. S i x t y - e i g h t runs were made. c. An i n v e s t i g a t i o n was conducted, f o r R-AERO-AD, t o prov i d e experimental l o c a l normal f o r c e d a t a , f o r comparison w i t h a computer program which c a l c u l a t e d l o c a l normal f o r c e g r a d i e n t on cone-cylinder bodies i n s u p e r s o n i c f l o w . . T o t a l runs: 3 4 . d . An i n v e s t i g a t i o n was conducted, f o r R-AERO-AU, t o d e t e r mine t h e boundary l a y e r c h a r a c t e r i s t i c behind a roughened s e c t i o n of an otherwise smooth w a l l . This i n v e s t i g a t i o n was performed t o analyze a proposed method by McDonnell-Douglas Corporation p r e p a r a t o r y t o the upcoming panel f l u t t e r t e s t s i n t h e Ames 2-foot supersonic wind tunnel. T o t a l runs: 49. e. An i n v e s t i g a t i o n was conducted f o r R-AERO-AD t o e v a l u a t e t h e e f f e c t s of varying sting-to-model diameters f o r a i d i n analyzing viscous c r o s s flow d a t a . Some d i f f e r e n c e is apparent i n t h e s t a t i c s t a b i l i t y d a t a . This d i f f e r e n c e can be a t t r i b u t e d t o s e v e r a l a r e a s , such a s Reynolds number s t i n g v a r i a t i o n blockage, e t c . The t e s t i s s t i l l i n progress. �6. 7 x 7-1nch B i s o n i c Wind Tunnel As a r e s u l t of i n f o r m a t i o n obtained from the cross-beam t e s t i n t h e s p e c i a l t e s t s e c t i o n of t h e TWT, a n i n v e s t i g a t i o n has been i n i t i a t e d i n t h e BWT t o develop cross-beam technology a p p l i c a b l e t o wind t u n n e l flows. The c u r r e n t i n v e s t i g a t i o n i s being conducted by R-AERO-AF on a n i n d e f i n i t e s c h e d u l e . 7. Data Reduction Besides t h e r o u t i n e f a c i l i t y d a t a r e d u c t i o n , t h e f o l l o w i n g work w a s performed: ( a ) C o n t i n u a t i o n of t h e program f o r D r . Beylich r e g a r d i n g t h e o r e t i c a l gas dynamics. Problems which were encountered u s i n g t h e high o r d e r numerical i n t e g r a t i o n procedures of t h e R-COMP MARVESS language have now been r e s o l v e d . (b) The Low D e n s i t y Chamber program was f i n i s h e d , i n c l u d i n g t h e p l o t t i n g r o u t i n e s . S e v e r a l dozen r u n s have been reduced using o n - l i n e plotting. ( c ) A program t o reduce t h e d i g i t a l d a t a from t h e IBFF was w r i t t e n and checked. This program a v e r a g e s the many d a t a p o i n t s taken d u r i n g t h e quas i-s teady c o n d i t i o n s of 5-10 m i l l i s e c o n d s , computes t h e s t a t i s t i c a l a n a l y s i s of t h e s t e a d i n e s s , and p r i n t s o u t t h e d a t a i n e n g i n e e r i n g u n i t s . The program a p p e a r s t o work s a t i s f a c t o r i l y f o r t e s t cases. 8. I n s trumenta t i o n a. High Response Balance One phase of t h e jet-plume s t u d i e s i n t h e Impulse Base Flow F a c i l i t y c o n s i s t s of f o r c e measurements on a f l a t p l a t e . The f a c i l i t y run-time of 5-10 m i l l i s e c o n d s r e q u i r e s h i g h r e s p o n s e b a l a n c e s f o r such measurements. A b a l a n c e l e f t from t h e shock t u n n e l e f f o r t s which appears t o be s u i t a b l e f o r i n i t i a l work, i s being r e a d i e d f o r t h i s t e s t . The magnitude of t h e l o a d s , t y p i c a l l y l e s s t h a n one pound, p r e s e n t s unusual problems. New b a l a n c e s a r e b e i n g designed and f a b r i c a t e d f o r t h i s work. b . Cross ed-Beam Support The van which was o r i g i n a l l y equipped f o r t h e Colorado f i e l d t e s t s has been r e t u r n e d t o MSFC. A f t e r r e t u r n , i t was r e f u r b i s h e d f o r t h e m u l t i - d e t e c t o r f i e l d t e s t s to' be conducted a t MSFC. The d e t e c t o r s f u r n i s h e d by IITRI have been i n s t a l l e d and a r e b e i n g checked o u t . The �parking l o t i s being used a s t h e t e s t s i t e f o r the checkout work, w i t h cons i d e r a t i o n b e i n g g i v e n t o f i e l d t e s t i n g a t t h e R-AERO-Y Atmospheric Research F a c i l i t y . F. Unsteady Gas Dynamics Branch 1. Ground Winds Load p r e d i c t i o n s published on August 29, 1968, f o r t h e AS-503 manned v e h i c l e corresponding t o miss i o n D dynamic c h a r a c t e r is t i c s have been checked f o r t h e C' m i s s i o n dynamic c h a r a c t e r i s t i c s and a r e cons i d e r e d a p p l i c a b l e . Based upon a v a i l a b l e d a t a , load p r e d i c t i o n s f o r t h e AS-504 manned v e h i c l e were published on November 27, 1968. For t h e a v a i l a b l e d a t a , t h e s e p r e d i c t i o n s were made f o r a l l b a s i c on-pad weight c o n f i g u r a t i o n s w i t h and w i t h o u t t h e MSS and w i t h and w i t h o u t t h e damper a t t a c h e d (where a p p l i c a b l e ) . A s t u d y f o r determining t h e second mode e f f e c t s on ground wind l o a d i n g s f o r t h e S a t u r n V v e h i c l e i s s t i l l i n p r o g r e s s . Also, a s t u d y i s i n p r o g r e s s t o determine t h e v a r i a t i o n i n bending moment pred i c t i o n s f o r v a r i o u s wind p r o f i l e s . E f f o r t s a r e underway t o f u l l y reduce a l l a v a i l a b l e S a t u r n V wind t u n n e l t e s t d a t a us ing t h e Lockheed s t a t i s t i c a l a n a l y s i s program and a Boeing d a t a a n a l y s i s program f o r r e f i n i n g load p r e d i c t i o n s f o r a l l wind d i r e c t ions and complex con£ i g u r a t i o n s . 2. I n f 1i g h t A c o u s t i c s a. Data r e d u c t i o n a n a l y s i s has begun on t h e AEDC 4 p e r c e n t model s u p e r s o n i c d a t a . O v e r a l l l e v e l s s c a l e d t o f u l l s c a l e c o n d i t i o n s a r e b e i n g computed and p l o t t e d . Cross spectrum a n a l y s i s w i l l begin upon completion of t h e o v e r a l l a n a l y s i s . b. Model f a b r i c a t i o n and i n s t r u m e n t a t i o n i n s t a l l a t i o n i s b e i n g completed f o r t h e shock-turbulence i n t e r a c t i o n experimental s t u d i e s b e i n g conducted i n t h e 7-inch MSFC s u p e r s o n i c wind t u n n e l by Wyle Labs. This experiment should r u n a b o u t one week. c. A d d i t i o n a l c o n t r a c t work f o r t h e "Development of F u l l I n f l i g h t A c o u s t i c Design C r i t e r i a S c a l i n g E f f e c t s " has been i n i t i a t e d . Data from Ames, f o u r - p e r c e n t S a t u r n V, PSTL-1 and PSTL-2 wind t u n n e l t e s t c o n d i t i o n s , and f l i g h t w i l l b e used, a l o n g w i t h o t h e r d a t a a v a i l a b l e i n t h e 1i t e r a t u r e . P r e l i m i n a r y d a t a r e d u c t i o n i s being continued . �d. A program has been conducted i n t h e AEDC 16-foot t r a n s o n i c tunnel t o provide experimental information t o h e l p d e r i v e methods by wllicll f l u c t u a t i n g a i r l o a d s i n t h e r e g i o n of protuberances can a c c u r a t e l y be p r e d i c t e d on launch v e h i c l e s , i n s u p p o r t of a c o n t r a c t with Wyle L a b o r a t o r i e s , H u n t s v i l l e , A l a b a m a , e n t i t l e d " ~ n v i r o r n n e n tAround Protuberances Submerged i n a Boundary Layer." The s t a t i c p r e s s u r e d a t a a r e b e i n g a n a l y z e d , and t h e f l u c t u a t i n g p r e s s u r e d a t a a r e b e i n g reduced. ~ wind t u n n e l t e s t program which e. A j o i n t M S F C / A ~ Force c o n s i s t e d of s e v e r a l b i c o n i c nose c o n f i g u r a t i o n s has been conducted. These con£ i g u r a t i o n s p r o v i d e a bas i s f o r a n a l y z i n g t h e c r o s s c o r r e l a t i o n c h a r a c t e r i s t i c s ( n e c e s s a r y f o r d e s i g n c r i t e r i a ) of t h e i n £ l i g h t f l u c t u a t i n g p r e s s u r e environment f o r v a r i o u s AAP miss i o n s . C a r e f u l planning i s r e q u i r e d t o a c h i e v e t h e optimum s e l e c t i o n of d e s i g n i n f o r m a t i o n from t h e tremendous amount of p o s s i b l e d a t a t o be reduced. The A i r Force, v i a Lockheed, paid f o r t h e i n i t i a l d a t a r e d u c t i o n c o n s i s t i n g of a few o v e r a l l l e v e l s s p e c t r a . The p r e l i m i n a r y d a t a a r e being analyzed. f . A t e s t t o a c o u s t i c a l l y c a l i b r a t e t h e MSFC 14-inch wind t u n n e l was completed September 17 by p e r s o n n e l of t h e C h r y s l e r Corporation. The primary o b j e c t i v e of t h i s t e s t was t o measure background p r e s s u r e f l u c t u a t i o n s g e n e r a t e d by t h e t u r b u l e n t boundary l a y e r on t h e t u n n e l w a l l s and by v a r i o u s o t h e r components of t h e wind t u n n e l . The Mach number r a n g e s f o r which t h i s t e s t was conducted was 0.4 t o 4.0; o t h e r v a r i a b l e s were w a l l p o r o s i t y , Reynolds number, and t u n n e l c o n f i g u r a t i o n . The c a l i b r a t i o n d e v i c e ( o r model) used was a 10-degree-included-angle cone w i t h two f l a t s u r f a c e s 180 degrees a p a r t f o r flush-mounting dynamic p r e s s u r e t r a n s d u c e r s . The f l u c t u a t i n g p r e s s u r e d a t a were recorded on magnetic t a p e . P r e l i m i n a r y d a t a r e d u c t i o n and a n a l y s i s a r e i n p r o g r e s s . 3. Launch S i t e A c o u s t i c s a. Papers were p r e s e n t e d by Messrs. Guest and Jones a t t h e r e c e n t Langley Conference (8-10 October) on t h e "Progress of NASA Research The proR e l a t i n g t o Noise A l l e v i a t i o n s of Large Subsonic J e t A i r c r a f t . " ceedings of t h e conference have been published a s a NASA SP-189. b. A c t i v i t y a t t h e A c o u s t i c Model T e s t F a c i l i t y (AMTF) a t T e s t Laboratory has slowed down d u r i n g t h e p a s t month. P l a n s a r e now being i n i t i a t e d t o conduct t h e 20-percent S a t u r n V model r o c k e t n o i s e experiment, which has been designed t o o b t a i n amplitude and phase i n £ o r mation f o r b o t h t h e l a u n c h and s t a t i c f i r i n g c o n d i t i o n of t h e S a t u r n V v e h i c l e . S p e c t r a l and s p a t i a l c o r r e l a t i o n c h a r a c t e r i s t i c s w i l l be obtained f o r t h e v e h i c l e a s w e l l a s t h e immediate launch complex a r e a . This t e s t i s scheduled t o b e g i n i n January. �c. The s t u d y of ground a t t e n u a t i o n e f f e c t s on a c o u s t i c wave p r o p a g a t i o n is b e i n g continued w i t h t h e m e t e o r o l o g i c a l parameters being analyzed i n more d e t a i l . A model more a p p l i c a b l e i n terms of t h e p h y s i c a l phenomena i s b e i n g sought f o r p r e d i c t i o n accuracy a p p l i c a t i o n s . 4. Panel F l u t t e r a . A p r e - t e s t conference concerning t h e upcoming h i g h amplitude S a t u r n V/S-IVB panel f l u t t e r t e s t (NASA-21250) was held a t Arnes Research Center on November 1 3 , 1968, w i t h r e p r e s e n t a t i v e s from MSFC, ARC, and McDonnell-Douglas C o r p o r a t i o n a t t e n d i n g . The following agenda were discussed: (1) Review of Wind Tunnel T e s t Program O b j e c t i v e s . (2) I n s t r u m e n t a t i o n and Data A c q u i s i t i o n . (3) GFE Requirements (4) V i s i t t o Tunnel F a c i l i t y wind t u n n e l . (5) Hardware d e s c r i p t i o n . (6) D e t a i l e d t e s t procedure. - ARC 2 x 2-foot t r a n s o n i c It was concluded t h a t a l l hardware and equipment should be a t ARC a t l e a s t one week b e f o r e t h e t u n n e l e n t r y , which has been t e n t a t i v e l y s e t f o r February 3 , 1969. b. S t a t u s of t h e government f u r n i s h e d equipment f o r t h e high-amplitude S-IVB panel f l u t t e r t e s t s is as follows: The RFQ f o r t h e n o n c o n t a c t i n g displacement meters has been r e l e a s e d . No p r o p o s a l s have y e t been r e c e i v e d . The boundary l a y e r r a k e d e s i g n , which has been r e c e i v e d from t h e McDonnell-Douglas C o r p o r a t i o n , i s being f a b r i c a t e d by the wind t u n n e l (MSFC) machine shop. I n a d d i t i o n , MSFC w i l l s u p p l y seven s t r a i n gage b r i d g e b a l a n c e u n i t s ; seven h i g h g a i n , low n o i s e "broad band a m p l i f i e r s " ; and two root-mean-square v o l t m e t e r s . Ames w i l l s u p p l y one f o u r t e e n - c h a n n e l magnetic t a p e r e c o r d e r , one d i r e c t - w i r i n g o s c i l l o g r a p h r e c o r d e r , two o s c i l l o s c o p e s , one D.C. v o l t m e t e r , one 16 mm h i g h speed camera, f i v e p r e s s u r e t r a n s d u c e r s , and a p r e s s u r e c o n t r o l v a l v e f o r r e g u l a t i n g t h e c a v i t y p r e s s u r e . A l l items a r e a v a i l a b l e w i t h t h e e x c e p t i o n of t h e noncontacting displacement m e t e r s . This may cause a s l i g h t slippage i n t h e tunnel e n t r y date. �c. The roughened s o l i d s i d e w a l l boundary l a y e r p r o f i l e i n v e s t i g a t i o n conducted i n t h e MSFC 14 x 14-Inch T r i s o n i c Wind Tunnel was completed November 1 5 , 1968. Made i n s u p p o r t of the upcoming panel f l u t t e r t e s t mentioned i n ( a ) above, t h i s t e s t was t o determine t h e boundary l a y e r c h a r a c t e r i s t i c s r e s u l t i n g from roughening a s e c t i o n of a n o t h e r w i s e smooth w a l l t o i n c r e a s e t h e boundary l a y e r t h i c k n e s s . To accomplish t h i s , .3125-inch diameter r o l l p i n s were d i s t r i b u t e d over t h e l e a d i n g 8 inches of t h e smooth w a l l , and t h r e e p i n h e i g h t s ( h e i g h t above wall: 0, .118 and.250 i n c h e s ) were t e s t e d . Boundary l a y e r p r o f i l e s were measured a t t h r e e l o c a t i o n s , f o r t h r e e Mach numbers, and f o r two Reynolds numbers. The d a t a o b t a i n e d looks good, and i s now being analyzed. 5. Quas i-S teady Analys i s a. The Shock-Induced S e p a r a t i o n Study program was conducted i n t h e MSFC 14-inch t u n n e l from September 19 through October 7 , 1968. The f a c i l i t i e s a t t h e MSFC's 14-inch t u n n e l a r e b e i n g used f o r data reduction. . Under c o n t r a c t NAS8- 21459, t h e quas i-s teady techniques b a r e b e i n g extended by Lockheed t o provide t h e c a p a b i l i t y t o compute g u s t p e n e t r a t i o n l o a d s on t h e S a t u r n v e h i c l e s , i n c l u d i n g t h e e f f e c t s of s e p a r a t e d flow. These techniques a r e b e i n g developed t o determine t h e aerodynamic damping f o r v a r i o u s s t r u c t u r a l modes by assuming t h a t t h e v e h i c l e w i l l f l y through a s i n u s o i d a l g u s t of c o n s t a n t amplitude and wavelength. This c o n t r a c t i s b e i n g extended t o r e f i n e t h e q u a s i - s t e a d y techniques developed f o r t h e computation of t h e dynamic e f f e c t s of s e p a r a t e d flow i n c l u d i n g t h e e f f e c t s of g u s t loadings on t h e a e r o e l a s t i c s t a b i l i t y c h a r a c t e r i s t i c s of t h e S a t u r n launch v e h i c l e s . These a n a l y t i c a l techniques w i l l b e expanded ( i f f e a s i b l e ) t o i n c l u d e more r e a l i s t i c i n f l i g h t g u s t environments. This c o n t r a c t i s a l s o being expanded t o p r e d i c t t h e a e r o e l a s t i c c h a r a c t e r i s t i c s , by u s e of t h e quas i-s teady techniques The i n c r e a s e developed, of t h e S a t u r n V v e h i c l e s AS-505 through AS-508. i n t h e scope of work w i l l become e f f e c t i v e on February 1, 1969, and t h e c o n t r a c t ending d a t e extended t o March 31, 1970. V. AEROSPACE ENVIRONMENT DIVISION A. Atmosphere Dynamics Branch 1. S u r f a c e Wind Data S u r f a c e wind speed and d i r e c t i o n d a t a a t t h e KSC Launch Pads a n d / o r NASA's 150-meter M e t e o r o l o g i c a l Tower F a c i l i t y were provided a s follows: �(.I) Memorandum R-AERO-YE-171-68 p r e s e n t e d d a t a recorded d u r i n g launch o p e r a t i o n s of AS-205 on October 11, 1968, from Launch Complex 34. (2) Memorandum R-AERO-YE-173-68 concerned d a t a obtained a t Launch Complex 39 d u r i n g h u r r i c a n e "Gladys" on October 17-19, 1968, f o r R-P&VE-SL t o determine maximum v e h i c l e response and s t r a i n guage d r i f t on a S a t u r n V v e h i c l e . (3) C u r r e n t d a t a recorded a t t h e m e t e o r o l o g i c a l tower were s e n t t o t h e Manned S p a c e c r a f t Center f o r Apollo command module l a n d i n g impact t e s t s s i m u l a t i n g a n off-the-pad a b o r t under v a r i o u s launch wind c o n d i t i o n s . ( 4 ) Two y e a r s of reduced m e t e o r o l o g i c a l tower d a t a were provided t h e Boeing Company, S e a t t l e , t o s t u d y g u s t f a c t o r s , s t a b i l i t y c o n d i t i o n s , e t c . , f o r t h e s u p e r s o n i c t r a n s p o r t program. 2. Jimsphere Wind Data f o r S p e c i a l S t u d i e s C o o r d i n a t i o n and p l a n s f o r t h e s u p p o r t of v a r i o u s turbul e n c e programs u s i n g Jimsphere wind p r o f i l e d a t a have been accomplished by p e r s o n n e l of R-AERO-YE. Support i s intended f o r t h e f o l l o w i n g programs : (1) R-AERO-Y/SRI LIDAR (Light D e t e c t i o n and Ranging) probing program t o d e t e c t t u r b u l e n c e a l o f t a t Half Moon Bay, C a l i f o r n i a , i n January 1969 under c o n t r a c t NAS8-21117. (2) LRC/ESSA/AFCRL t u r b u l e n c e a l o f t (CAT) program t o b e conducted d u r i n g t h e p e r i o d January-March 1969 a t Wallops I s l a n d , V i r g i n i a . (3) I n s u p p o r t t o LRC/ESSA mountain l e e wave s t u d y a t Edwards AFB, C a l i f o r n i a d u r i n g t h e period of February-March 1969. A l l i n f o r m a t i o n a c q u i r e d on t u r b u l e n c e a l o f t , whether s e v e r e , m o d e r a t e , , o r l i g h t , w i l l become a v a i l a b l e from t h e s e s t u d i e s f o r updating environmental c r i t e r i a t o d e s i g n and launch l a r g e space v e h i c l e s . 3. Atmospheric Turbulence Boundary Layer P r o j e c t a. Pennsylvania S t a t e U n i v e r s i t y (NASA C o n t r a c t NAS8-21140) Penn S t a t e has completed a n a l y s e s of t h e v e r t i c a l coherence f u n c t i o n s of t h e l o n g i t u d i n a l and l a t e r a l components of These t u r b u l e n c e , and has t r a n s m i t t e d them t o NASA (R-AERO-YE) coherence f u n c t i o n s d e s c r i b e t h e c o r r e l a t i o n between t h e F o u r i e r . �coin?.jl.t n t s of t h e l o n g i t u d i n a l and l a t e r a l components of t u r b u l e n c e a s s o c i a t e d w i t h frequency w between two l e v e l s i n t h e v e r t i c a l a t h e i g h t s zl and z2 ( z l and z2 150 m). These coherence f u n c t i o n s a r e i n dimensionless form and a r e s c a l e d i n terms of zl, z2, and t h e q u a s i - , s t e a d y wind speeds a t l e v e l s zl and z2. - b. C o r n e l l A e r o n a u t i c a l L a b o r a t o r i e s (NASA C o n t r a c t NAS8-21178) The C o r n e l l A e r o n a u t i c a l L a b o r a t o r i e s have completed t h e i r a n a l y s e s of t h e l a t e r a l spectrum of t u r b u l e n c e and have t r a n s m i t t e d t h e r e s u l t s t o R-AERO-YE. The l a t e r a l component of t u r b u l e n c e i s p e r p e n d i c u l a r t o q u a s i - s t e a d y wind speed v e c t o r . This spectrum i s s c a l e d i n terms of t h e t a n g e n t i a l eddy s t r e s s a t t h e s u r f a c e of t h e e a r t h , t h e h e i g h t z above t h e s u r f a c e of t h e e a r t h , and t h e q u a s i - s t e a d y wind speed a t h e i g h t z . Thus, t h e l a t e r a l spectrum is g i v e n i n terms of a dimensionl e s s function. c . In-Hous e Inves t i g a t i o n s The a n a l y s i s of t h e l o n g i t u d i n a l spectrum of t u r b u l e n c e has been completed. The l o n g i t u d i n a l component of t u r b u l e n c e i s p a r a l l e l t o t h e q u a s i - s t e a d y wind v e c t o r . Here a g a i n , t h e l o n g i t u d i n a l spectrum i s g i v e n by a dimensionless f u n c t i o n i n which t h e eddy s t r e s s a t t h e s u r f a c e of t h e e a r t h , t h e h e i g h t z , t h e q u a s i - s teady wind speed a t h e i g h t z. appear a s s c a l i n g parameters. ' d. Turbulence Model The Penn S t a t e , C o r n e l l Lab., and our in-house a n a l y s e s a r e b e i n g combined i n t o a complete and t h e o r e t i c a l l y cons i s t e n t s p e c t r a l t u r b u l e n c e model. The e n g i n e e r needs o n l y t o pres c r i b e t h e q u a s i - s t e a d y wind p r o f i l e t o o b t a i n t h e l o n g i t u d i n a l and l a t e r a l s p e c t r a and t h e a s s o c i a t e d coherence f u n c t i o n s (and co- and q u a d r a t u r e - s p e c t r a ) a s known f u n c t i o n s of h e i g h t z , completely d e f i n e d f o r t h e f i r s t 150 m e t e r s of t h e atmosphere. The model can be used i n v e h i c l e development work (low c o s t a s w e l l as r e c o v e r a b l e launch v e h i c l e s ) and i s i n a form s u i t a b l e f o r performing p a r a m e t r i c a n a l y s e s of v e h i c l e c a p a b i l i t i e s . These r e s u l t s w i l l appear i n a forthcoming r e v i s e d C l i m a t i c G u i d e l i n e s Document, NASA TN's, and NASA CR's. �B. T e r r e s t r i a l Environment Branch 1. In-House a. AS-503 Wind C o n s t r a i n t s Considerable e f f o r t has been devoted t o determining t h e p r o b a b i l i t y of occurrence of wind c o n s t r a i n t s s p e c i f i c a l l y f o r AS-203 f o r o p e r a t i o n a l planning and m i s s i o n r u l e s . D i s t r i b u t i o n s of ground winds and wind p r o f i l e i n t e r p r e t a t i o n s have been f u r n i s h e d t o MSC f o r t h e s p a c e c r a f t l a n d i n g c o n s t r a i n t s . b. T e r r e s t r i a l Environment G u i d e l i n e s Document A r e v i s e d e d i t i o n of t h e T e r r e s t r i a l Environment ( C l i m a t i c ) C r i t e r i a G u i d e l i n e s Document has been completed, e x c e p t f o r t h e c h a p t e r on wind. Two more months w i l l b e r e q u i r e d t o complete t h e e x t e n s i v e r e v i s ions t o t h i s important s e c t i o n . c. World-Wide Cloud Model The Monte C a r l o procedures f o r s i m u l a t i n g photographic coverage of t h e clouded e a r t h from s p a c e were completed. One procedure p e r m i t s t h e incremental a r e a photographed on each pass t o be determined by one minus t h e cloud cover encountered on t h a t pass. I n the other procedure, t h e a r e a under cons i d e r a t i o n i s d i v i d e d i n t o 100 s q u a r e s , w i t h each s q u a r e a s s i g n e d a number. The incremental photographic coverage i s then determined by s e l e c t i n g t h e number of random numbers corresponding t o t h e p e r c e n t of c l e a r sky on t h a t p a s s . Some r e s w l t s w i l l b e published a f t e r t h e two procedures a r e evaluated. d. F a r - F i e l d Sound Propagation M r . 0. E. Smith p r e s e n t e d a paper, " E f f e c t s of Atmosp h e r i c R e f r a c t i o n on F a r - F i e l d Sound Propagation," a t t h e NASA Acoustic Conference which was l a t e r published by Langley Research Center i n NASA SP-189. I n view of t h e i n t e r e s t generated by t h i s p a p e r , we a r e p r e p a r i n g our Kaman Nuclear c o n t r a c t r e p o r t on sound p r o p a g a t i o n and a t m o s p h e r i c v a r i a b i l i t y f o r i s s u e a s a h i g h l e v e l NASA C o n t r a c t o r Report �2. Contracts a. u n i v e r s i t y of Georgia C o n t r a c t (NAS8-11175) The agenda items f o r a s e r i e s of seminars a t t e n d e d by Messrs. Smith, Brown, and F a l l s a t t h e U n i v e r s i t y of Georgia on November 21, 1968, a r e l i s t e d below. MORNING 9: 30 - 10: 00 A Modified Negative Binomial is t r i b 6 t i o n by W. 0. W i l l i f o r d , Univers i t y of Georgia. 10:OO - 10:30 Some Numerical I n v e s t i g a t i o n s of t h e Parameters of Weibull D i s t r i b u t i o n s by B . J. Williams and F. R. Helm, U n i v e r s i t y of Georgia. 10:30 - 11:OO S t r u c t u r e s of Programs and F i l e s i n Computers by Rolf E. Bargmann, U n i v e r s i t y of Georgia. 11: 00 - 11: 30 The Use of Markov Chains i n Atmospheric S t a t i s t i c s by A. C. Cohen, U n i v e r s i t y of Georgia. AFTERNOON 1:30 - 2:OO Pearson Curves by Lee F a l l s , MSFC. 2: 00 - 2: 30 M e t e o r o l o g i c a l S t a t i s t i c s by S. C l a r k Brown, MSFC. 2:30 - 3: 00 Extreme Value S t a t i s t i c s by 0. E. Smith, MSFC. 3:OO - 3:30 Summary and E v a l u a t i o n by C a r l F. Kossack, U n i v e r s i t y of Ge o r g ia . b. Lockheed Support C o n t r a c t (Schedule Order 1, Appendix A-1) AS-503 launch p r o b a b i l i t y v a l u e s d e r i v e d from a n a n a l y s i s of t h e n a t u r a l environment were published i n O f f i c e Memorandum R-AERO-YT68-68, dated November 1 8 , 1968. The atmospheric parameters considered were c e i l i n g and v i s i b i l i t y , ground winds, and unfavorable weather conditions. . �Space Environment Branch C. 1. Study of E l e c t r o n Cooling i n t h e ~ a r t h ' sUpper Atmosphere The c o o l i n g of i o n o s p h e r i c e l e c t r o n s through t h e e x c i t a t i o n of t h e s p i n m u l t i p l e t s of t h e ground s t a t e of atomic oxygen have been s tudied This mechanism !seems t o c o n t r i b u t e s i g n i f i c a n t l y t o t h e energy l o s s t o e l e c t r o n s i n t h e e a r t h ' s upper atmosphere. R e s u l t s have shown t h a t a n e x p o n e n t i a l c r o s s s e c t i o n f o r t h e r e a c t i o n s seems t o f i t t h e d a t a b e s t , w h i l e y i e l d i n g a s u b s t a n t i a l energy l o s s i n t h e e l e c t r o n c o o l i n g . A p r e l i m i n a r y a n a l y s i s of t h i s work i s a v a i l a b l e i n a p r o g r e s s r e p o r t by t h e Northrop s u p p o r t c o n t r a c t o r . . 2. I o n o s p h e r i c Disturbances Caused by t h e I n t e r a c t i o n of t h e Space Plasma w i t h t h e ~ a r t h ' sMagnetosphere and Upper Atmosphere M i s s i s s i p p i S t a t e U n i v e r s i t y w i l l s t u d y t h e i n t e r a c t i o n of t h e s o l a r plasma w i t h t h e e a r t h ' s magnetosphere and upper atmosphere t o d e l i n e a t e t h e t y p e s of i o n o s p h e r i c d i s t u r b a n c e s caused . This information w i l l then be i n c o r p o r a t e d i n t o t h e i o n o s p h e r i c programs now i n p r o g r e s s t o f u r t h e r d e f i n e t h e t r a t e l i n g i o n o s p h e r i c d i s t u r b a n c e s and t h e i r c h a r a c t e r is t i c parameters. Of p a r t i c u l a r i n t e r e s t t o t h e U n i v e r s i t y a r e t h e Alfven waves and H a l l c u r r e n t s produced i n a magnetohydrodynamic field . 3. A c o u s t i c G r a v i t y Wave Study The f i n a l r e p o r t on t h e f i r s t y e a r ' s work on t h e coupling of a c o u s t i c energy from t h e troposphere t o t h e thermosphere is due by December 1 5 , 1968. The follow-on c o n t r a c t f o r t h e c o n t i n u a t i o n of t h i s work i s being n e g o t i a t e d . During t h e second y e a r , we w i l l a s c e r t a i n t h e predominant coupling mechanisms, examine t h e e f f e c t s of a v a r y i n g p r o p a g a t i o n medium, and o b t a i n f u r t h e r experimental d a t a on t h e e f f e c t s on t h e ionosphere of s t a t i c t e s t f i r i n g s and l o c a l thunderstorms. 4. I o n o s p h e r i c Plasma I n v e s t i g a t i o n s from a n E a r t h O r b i t a l Space S t a t i o n R e s p o n s i b i l i t y f o r t h e d e f i n i t i o n of t h e I o n o s p h e r i c Plasma I n v e s t i g a t i o n s t o be included i n t h e Experiment Program f o r a n E a r t h O r b i t a l Space S t a t i o n has been a s s i g n e d t o t h i s D i v i s i o n . The e x p e r i ments t o be included i n t h i s package a r e a plasma wake experiment ( t o s t u d y t h e i o n o s p h e r i c wake a s s o c i a t e d w i t h l a r g e s p a c e c r a f t ) and a plasma wave p r o p a g a t i o n experiment which w i l l examine t h e harmonic resonance a s s o c i a t e d w i t h antennas t r a n s m i t t i n g i n t o t h e magnetoplasma. Even though t h e s e experiments have NASA Headquarters backing, much more work needs t o be done on t h e e n g i n e e r i n g d e f i n i t i o n of t h i s program than i s now b e i n g done. �5. Atmospheric Model S t u d i e s The d e t a i l e d s t u d y program f o r t h e development of an improved upper atmospheric model i s c o n t i n u i n g . I n s u p p o r t of t h i s program, dragdetermined d e n s i t i e s from 64 s a t e l l i t e s have been compared w i t h d e n s i t i e s t h a t were c a l c u l a t e d u s i n g t h e MSFC Modified J a c c h i a Model Atmosphere, 1967. The model d e n s i t i e s and drag d e n s i t i e s a r e i n good agreement above 350 km a l t i t u d e ( w i t h i n 15 p e r c e n t ) , b u t d i f f e r e r r a t i c a l l y , by a s much a s 50 p e r c e n t , below t h i s a 1 t i t u d e . P r e l i m i n a r y i n v e s t i g a t i o n s have i n d i c a t e d t h a t t h e model may be improved by c u r v e - f i t t i n g t h e model e x o s p h e r i c temp e r a t u r e t o t h e drag-determined d e n s i t y a t d i s c r e t e a l t i t u d e s and u s i n g the r e s u l t i n g expressions t o define the a l t i t u d e density r e l a t i o n s h i p s . This w i l l provide a n improved mass d e n s i t y model, b u t t h e atmospheric composition and temperature t h a t a r e a s s o c i a t e d w i t h t h e mass d e n s i t y must be o b t a i n e d b y some e m p i r i c a l technique. One such technique t h a t is c u r r e n t l y being i n v e s t i g a t e d e n t a i l s t h e m o d i f i c a t i o n of ~ a c c h i a ' s e x o s p h e r i c temperature e q u a t i o n s t o f o r c e them t o f i t t h e e x o s p h e r i c temperatures t h a t have been d e r i v e d from e i g h t MSFC and twelve GSFC thermosphere probe o b s e r v a t i o n s . S i x of t h e MSFC probes a r e p a r t i c u l a r l y u s e f u l , s i n c e t h e y were launched a s a s e r i e s on one day and thus provided v a l u a b l e i n f o r m a t i o n on t h e d i u r n a l v a r i a t i o n i n e x o s p h e r i c temperature. Once t h e s e m o d i f i c a t i o n s a r e made, t h e boundary c o n d i t i o n s a t 120 km (N2, 02, and 0) w i l l be r e - e s t a b l i s h e d s o t h a t the newly modified J a c c h i a model w i l l be i n c l o s e agreement w i t h t h e s a t e l l i t e d e n s i t i e s . These r e s u l t s w i l l p r o v i d e a n improved r e p r e s e n t a t i o n of t h e atmospheric compos i t i o n and temperature and t h e i r v a r i a t i o n s . 6. Environment C r i t e r i a NASA TM X-53798, "Space Environment G u i d e l i n e s f o r Use i n Space Vehicle Development, 1968 R e v i s i o n , " has been d i s t r i b u t e d . This (Copies may be obtained document i s a r e v i s e d v e r s i o n of NASA TM X-53521. from R-AERO-YS. ) S p e c i a l i z e d environment c r i t e r i a i n p u t s , n o t g i v e n i n t h i s document,have been f u r n i s h e d by R-AERO-YS f o r s e v e r a l e n g i n e e r i n g and s c i e n t i f i c s t u d i e s i n s u p p o r t of t h e OWS/ATM and Future Space S t a t i o n (FSS) Programs. As MSFC becomes more involved i n long l i f e t i m e o r b i t a l m i s s i o n s , such a s OWSIATM and FSS, t h e r e q u e s t s f o r s p e c i f i c o r b i t a l environmental c r i t e r i a w i l l become more numerous. A l a r g e percentage of t h e s e r e q u e s t s , however, w i l l be s a t i s f i e d by a n O r b i t a l Environment C r i t e r i a Document t h a t i s being developed a s a supplement t o NASA TM X-53798. 7. Thermosphere Probe Program A d e t a i l e d a n a l y s i s of s i x MSFC thermosphere probes launched on January 24, 1967, has r e s u l t e d i n a s c i e n t i f i c paper t h a t w i l l b e subm i t t e d t o one of t h e p r o f e s s i o n a l j o u r n a l s f o r p u b l i c a t i o n . This paper �shot\rs t h e MSFC thermosphere probe measurements of N2 number d e n s i t y and c a l c u l a t e d temperatures t o be i n e x c e l l e n t agreement w i t h o t h e r s i m i l a r measurements. Atmospheric mass d e n s i t i e s t h a t a r e implied by t h e N2 measurements a r e i n good agreement w i t h t h e MSFC Modified J a ~ c h i aModel Atmosphere, 1967 above 300 km a l t i t u d e and t h e i n f e r r e d 0 and O2 number d e n s i t i e s a r e i n d i c a t e d t o be i n good agreement w i t h s e v e r a l mass spectrome t e r measurements of t h e s e q u a n t i t i e s . The paper t e n t a t i v e l y i l l u s t r a t e s t h a t t h e ornegatron mass s p e c t r o m e t e r , which was flown on a l l of t h e MSFC thermosphere probes, may be used t o o b t a i n atmospheric i n f o r m a t i o n i n as much d e t a i l as can be o b t a i n e d from o t h e r mass s p e c t r o m e t e r s t h a t a l s o measure 0 and O2 c o n c e n t r a t i o n s . Data r e d u c t i o n problems i n t h e O2 and 0 measurements, s u c h a s recombination and accommodation i n s i d e t h e gauge, however, a r e n o t a p p l i c a b l e t o t h e O2 and 0 c o n c e n t r a t i o n s t h a t a r e c a l c u l a t e d from t h e N2 measurements. Study e f f o r t - i n t h i s program i s c u r r e n t l y being d i r e c t e d t o t h e e x t e n s i o n of t h e 20 thermosphere o b s e r v a t i o n s from 140 km down t o 90 km a l t i t u d e . This t a s k , which i s being accomplished u s i n g t h e o r e t i c a l molecular d i s s o c i a t i o n and eddy d i f f u s i o n c o n s t r a i n t s , w i l l p r o v i d e i n f o r m a t i o n concerning t h e v a r i a b i l i t y of t h e temperature and atmospheric c o n s t i t u e n t s n e a r 90 km a l t i t u d e . This i n f o r m a t i o n w i l l be used t o e s t a b l i s h v a r i a b l e boundary c o n d i t i o n s a t 90 km f o r a dynamic model atmosphere t h a t is being developed from s a t e l l i t e drag-determined d e n s i t y d a t a . A second s c i e n t i f i c paper, which is i n d r a f t form, w i l l p r e s e n t t h e a n a l y s i s of t h e two MSFC thermosphere probes launched i n A p r i l 1967. Two a d d i t i o n a l probes a r e planned f o r e a r l y 1969, and t h e RFP f o r f o u r more has been s e n t o u t . The a n a l y s i ~ ~ oa fl l of t h e MSFC and GSFC thermosphere probes, i n c o n j u n c t i o n w i t h t h e a n a l y s i s of a l l a v a i l a b l e s a t e l l i t e d r a g - d e t e r mined d e n s i t y d a t a , w i l l provide i n f o r m a t i o n needed f o r t h e development of a n improved upper atmosphere model t h a t w i l l n o t be l i m i t e d by t h e c o n s t a n t boundary assumptions i n h e r e n t i n e x i s t i n g model atmospheres. 8. Solar A c t i v i t y Studies Lockheed M i s s i l e s and Space Company has computed t h e v a r i o u s parameters which a r e d e s c r i p t i v e of t h e i n t e r a c t i o n of t h e p l a n e t s w i t h t h e sun. These parameters a r e : (1) P o s i t i o n of t h e s u n r e l a t i v e t o t h e c e n t e r of mass of t h e s o l a r system. (2) V e l o c i t y of t h e s u n r e l a t i v e t o t h e c e n t e r of mass. �(3) A c c e l e r a t i o n of t h e sun. (4) Angular momentum of t h e sun about t h e c e n t e r of mass. (5) Radius of c u r v a t u r e of t h e sun's path. (6) Rate of change of angular momentum. (7) Rate of change of a c c e l e r a t i o n ( j e r k ) . These d a t a have been s e n t t o ~ o c k h e e d ' s Palo A l t o Research F a c i l i t y f o r d e t a i l e d n o n l i n e a r c o r r e l a t i o n study t o determine t h e b e s t sunspot p r e d i c t o r . R e s u l t s from t h i s c o n t r a c t work should be forthcoming i n l a t e February. MIT Experimental Astronomy Laboratory i s conducting a n a n a l y t i c a l s t u d y t o d i s c i v e r which p l a n e t a r y i n f l u e n c e s a r e most import a n t i n determining s o l a r weather (sunspots and f l a r e s ) . Time g r a d i e n t components of t h e t e n s o r r e p r e s e n t i n g t h e t o t a l g r a v i t y g r a d i e n t a t t h e sun due t o t h e p l a n e t s should g i v e an i n s i g h t i n t o t h e underlying s o l a r physics which cause sunspots and f l a r e s . P r o g r a m i n g t o o b t a i n t h e necessary data i s nearly finished. Denver Research I n s t i t u t e i s conducting r e s e a r c h t o improve long-range s o l a r a c t i v i t y p r e d i c t i o n s . The square of t h e v e r t i c a l t i d a l f o r c e on t h e sun due t o t h e p l a n e t s i s being compared w i t h s o l a r proton events t o determine whether o r not any c o r r e l a t i o n e x i s t s between t h e s e parameters. Another e f f o r t under t h e c o n t r a c t i s t h e development of techniques t o p r e d i c t sunspot numbers f o r periods of one t o two s o l a r cycles. The U n i v e r s i t y of Arkansas is a t t e m p t i n g t o develop mathem a t i c a l f u n c t i o n s t o f i t s o l a r cycles. Data from many sources t h a t e s t i m a t e t h e c y c l e s back s e v e r a l hundred y e a r s have been t a b u l a t e d , and w i l l be searched f o r hidden p e r i o d i c i t i e s . A c o n t r a c t i s being negotiated w i t h t h e Solar A c t i v i t y Group of the ESSA Space Disturbance Laboratory t o s e a r c h f o r p o s s i b l e means of p r e d i c t i n g sunspot numbers throughout t h e s o l a r c y c l e , t o v e r i f y a l t e r n a t i v e f o r e c a s t s a g a i n s t independent o b s e r v a t i o n s , and t o s e a r c h f o r poss i b l e improved means of r e l a t i n g t h e s o l a r r a d i o f l u x t o t h e sunspot number o r of p r e d i c t i n g t h e s o l a r r a d i o f l u x d i r e c t l y . In-house e f f o r t s a r e aimed a t improving s o l a r cycle predict i o n s through t h e a p p l i c a t i o n of Fourier a n a l y s e s , power spectrum techniques, and band pass f i l t e r analyses. �We p l a n t o sponsor a seminar on S o l a r A c t i v i t y P r e d i c t i o n i n the s p r i n g of 1969. I n a d d i t i o n t o r e s e a r c h e r s working under MSFC cont r a c t , we hope t o have p a r t i c i p a t i o n by o t h e r l e a d i n g a u t h o r i t i e s i n t h i s field. VI. ASTRODYNAMICS AND GUIDANCE THEORY DIVISION A. Guidance Theory Branch 1. Support Contract S t u d i e s a. Lunar Targeting Analysis Using QUOTA Terminal conditions f o r the t a r g e t i n g problem have been s e l e c t e d a s r a d i u s of c l o s e s t approach, s p e c i f i c energy, and azimuth a t periselenum. The a s s o c i a t e d t r a n s v e r s a l i t y conditions have been developed and incorporated i n t o t h e QUOTA program. Several t e s t s have been run, and a s expected, t h e r e s u l t s i n d i c a t e d two problem a r e a s : t h e s e n s i t i v i t y a s s o c i a t e d w i t h t h e i s o l a t i o n of a n optimum s o l u t i o n , and t h e accuracy of t h e two-body s o l u t i o n over t h e c o a s t a r c s . The problem a r e a s a r e being i n v e s t i g a t e d . b. ~ u a s i - o p t i m a lGuidance Study Rendezvous s t u d i e s a r e now being conducted w i t h QUOTA. Two d i f f e r e n t problems a r e being s t u d i e d : (1) rendezvous w i t h a n S-IVB, i n i t i a l time 151 seconds ( f i r s t burn s u b - o r b i t a l ) , and a t a r g e t v e h i c l e i n a 225 n.m. o r b i t , and (2) rendezvous w i t h i n t e r c e p t o r and t a r g e t i n c i r c u l a r o r b i t w i t h varying r e l a t i v e i n c l i n a t i o n s . c. O r b i t Trim Systems E r r o r Analysis D i f f i c u l t i e s a r e s till being encountered i n transforming t h e n a v i g a t i o n accuracy d a t a , generated by the Bissett-Berman program a s a covariance m a t r i x i n l o c a l C a r t e s i a n coordinates, i n t o a covariance m a t r i x i n o r b i t a l elements. An a n a l y t i c a l method of transforming t h e l o c a l C a r t e s i a n coordinate covariance m a t r i x d i r e c t l y i n t o a n o r b i t a l element covariance m a t r i x has been p a r t i a l l y developed. This a n a l y t i c a l method , a f i r s t - o r d e r p e r t u r b a t i o n a n a l ys i s , assumes zero means. d. Optimal Guidance Study Some progress has been made i n understanding t h e behavior of t h e switching f u n c t i o n and how t h i s a f f e c t s t h e formulation of m u l t i p l e l u n a r a r c o p t i m i z a t i o n t r a j e c t o r i e s . Also, a g e n e r a l t h r e e dimensional computer program f o r m u l t i p l e burn a r c t r a j e c t o r i e s w i t h v a r i o u s terminal s u r f a c e s i s being assembled. �2. Contracts a. - IBM A p p l i c a t i o n of Numerical Methods t o Extend C a p a b i l i t i e s f o r Optimal Rocket Guidance During t h i s r e p o r t i n g p e r i o d , improvements t o t h e comp u t a t i o n of p a r t i a l d e r i v a t i v e t r a n s i t i o n m a t r i c e s have been i n c o r p o r a t e d i n t o t h e computer program f o r determining optimal t h r u s t - c o a s t - t h r u s t t r a j e c t o r i e s . The computer program i s s t i l l being checked o u t . A l s o , a n IBM t e c h n i c a l n o t e c o n t a i n i n g t h e d e r i v a t i o n of t h e improvements t o t h e computation of t h e c o a s t a r c t r a n s i t i o n m a t r i c e s was published. b. Lockheed - Rendezvous Guidance The method of f i r s t - o r d e r p e r t u r b a t i o n s i s being a p p l i e d t o t h e powered f l i g h t phases of t h e rendezvous m i s s i o n which has now been r e g u l a r i z e d a c c o r d i n g t o Levi-Civita. D i g i t a l programming of t h e r e s u l t i n g c o n t r o l l a w s i s underway. 3. In-House S t u d i e s Work i s i n p r o g r e s s t o f i n d a COV s o l u t i o n t o an AAP type of rendezvous miss i o n . An optimal burn-coas t - b u r n , w i t h a s h o r t c o a s t ( l e s s than 90 m i n u t e s ) , s o l u t i o n t o t h e problem has been o b t a i n e d . However, s i n c e t h e s h o r t c o a s t time v i o l a t e s the r e s t a r t c a p a b i l i t i e s of t h e S-IVB, a s e a r c h f o r a l o n g e r c o a s t s o l u t i o n i s b e i n g made. It i s planned t o develop optimal rendezvous t r a j e c t o r i e s f o r t h e e n t i r e launch window. The r e s u l t s of t h i s s t u d y w i l l be compared, i n terms of payload and launch window d u r a t i o n , w i t h t h e p r e s e n t l y d e f i n e d AAP mission p r o f i l e s . , A patched c o n i c s o l u t i o n of ~ a m b e r t ' s problem has been numerically o b t a i n e d w i t h a technique i n v o l v i n g t h e use of p a r t i a l d e r i v a t i v e t r a n s i t i o n m a t r i c e s . The motion of t h e probe i s approximated by two c l a s s i c a l two-body segments which a r e pieced t o g e t h e r . This r e s u l t s i n a patched c o n i c s o l u t i o n f o r t h e l u n a r problem. Such a s o l u t i o n makes p o s s i b l e a new approach t o t h e l u n a r t a r g e t i n g problem A paper concerning optimal c o - a l t i t u d e rendezvous has been prepared and i s b e i n g submitted f o r c o n s i d e r a t i o n a s a t e c h n i c a l n o t e i n t h e ALClA j o u r n a l . The c a p a b i l i t y t o t r a n s f e r o r rendezvous between a r b i t r a r i l y o r i e n t e d e l l i p t i c o r b i t s has been added t o t h e CDC-3200 COV program. The r e f e r e n c e c o o r d i n a t e s y s tem i s t h e same a s used by North American A v i a t i o n . One t e s t case has been solved and a number of o t h e r s w i l l be attempted t o compare w i t h some of NAA' s r e s u l t s using quas i-1i n e a r i z a t ion. ' �B. As trodynamics Branch 1. Broken-Plane T r a j e c t o r i e s (Lockheed) The f i r s t d r a f t of t h e u s e r ' s manual f o r t h e Lockheed Broken-Plane Computer Program has been completed and i s now being e d i t e d f o r p u b l i c a t i o n . Work was begun on t h e development of a comp l e t e l y g e n e r a l broken- lane program that w i l l e l i m i n a t e t h e r e s t r i c t i o n s on t h e e x i s t i n g program w i t h r e g a r d t o h e l i o c e n t r i c t r a n s f e r a n g l e . 2. Miss i o n Design C h a r t s A paper i s being prepared i l l u s t r a t i n g a n e f f e c t i v e means of communicating a s t r o d y n a m i c a l l y based miss i o n a n a l y s i s m a t e r i a l between t h e a s trodynamicis t and t h e s y s tems e n g i n e e r . The r e p o r t w i l l emphasize b o t h t h e type of m a t e r i a l t o b e p r e s e n t e d and t h e method of i t s p r e s e n t a t ion. 3. I n t e r p l a n e t a r y N-Body Programs a. Program Development (Lockheed) Work was begun on t h e checkout of t h e N-Body I n t e r p l a n e t a r y T r a j e c t o r y Program o b t a i n e d from ~ o c k h e e d / ~ u n n y v a l e .The program i s coded i n F o r t r a n I1 and FAP and t h e r e f o r e must be converted t o F o r t r a n I V f o r u s e on t h e IBM 7094 corYlputer system. The program, which i s extremely v e r s a t i l e , has e l e v e n d i f f e r e n t o p t i o n s . b . I s o l a t i o n Routines (Nor t h r o p ) The f i n a l d r a f t of a summary r e p o r t on t h e i s o l a t i o n s t u d i e s was completed. Work continued w i t h checkout of t h e computer program which t e s t s i s o l a t i o n schemes. c. T a r g e t i n g S t u d i e s (Northrop) S t u d i e s were made t o determine a n e x p o n e n t i a l v a l u e t o c o r r e c t l y v a r y t h e displacement of a probe. A method that worked w e l l t o c o r r e c t t h e e r r o r was t o change t h e a c c e l e r a t i o n a t a d e c r e a s i n g r a t e . The r e s u l t a n t displacement showed a n improvement over two-body t h e o r y , a s w e l l a s i n t h e c o n s t a n t s t e p method, i n a l l t r a j e c t o r i e s considered f o r p e r i o d s of l e s s than one hundred days of f l i g h t . The "Average A c c e l e r a t i o n Vector" method was a l s o i n v e s t i g a t e d . This method a l t e r s t h e two-body t r a j e c t o r y by t h e average a c c e l e r a t i o n v e c t o r s of each p l a n e t . Each v e c t o r was used t o c a l c u l a t e t h e displacement of t h e probe due t o t h e p a r t i c u l a r p l a n e t , and t h e s e �displacements were added t o t h e Kepler s o l u t i o n t o o b t a i n more accuracy. Tlle method i s very a c c u r a t e f o r reasonable periods of c o a s t . 4. O r b i t a l Transfer (Lockheed) Work was continued t o extend t h e c a p a b i l i t i e s of Lockheed's Medium Accuracy O r b i t a l Transfer Program (MOAT) t o compute t h e h e l i o c e n t r i c p o s i t i o n and v e l o c i t y h i s t o r y of a n i n t e r p l a n e t a r y s p a c e c r a f t a t equal time increments along t h e h e l i o c e n t r i c t r a j e c t o r y . The program i s a l s o being modified t o c a l c u l a t e the communications angles and d i s tances a t equal time increments along t h e t r a j e c t o r y . Automatic p l o t r o u t i n e s a r e being added t o t h e program t o g r a p h i c a l l y d i s p l a y t h e d a t a a s a f u n c t i o n of time along t h e t r a j e c t o r y . Swingby Miss i o n Analysis (Lockheed) 5. F i n a l e d i t i n g of t h e "Mars Capture Miss ions v i a Venus Swingby" r e p o r t has been completed, and copies of the f i n a l r e p o r t w i l l be d e l i v e r e d t o R-AERO-GA w i t h i n t h e next week. 6. O r b i t s i n Non-Central F i e l d s Work continues i n a n e f f o r t t o f i n d a simple c h a r a c t e r i z a t i o n of those transforms which g i v e no cross products i n momenta when t h e Hamiltonian of a given mechamical system i s r e w r i t t e n i n t h e new coordinates . 7. Abort and A l t e r n a t e Missions (Boeing) Phase I and Phase I1 of t h e study of f i r s t - s t a g e engineo u t problems, which began September 3 , have been completed. An i n t e r i m r e p o r t covering t h e s e two phases was received November 11, 1968. The purpose of Phase I was t o show t h e e f f e c t s of v e h i c l e and t r a j e c t o r y changes on c r i t i c a l t r a j e c t o r y parameters f o r t h e AS-502 v e h i c l e . The r e s u l t s were t h a t t h e c e n t e r engine c u t o f f (CECO) on a f i x e d time r a t h e r than on p r o p e l l a n t d e p l e t i o n i s d e t r i m e n t a l t o engine o u t s t a g i n g cond i t i o n s , and t h e AS-502 v e h i c l e w i t h t h e updated c o n f i g u r a t i o n of modif i e d t i l t a r r e s t , outboard engine c a n t , and CECO a t 125 seconds would s t i l l have a n engine-out s t a g i n g problem. Phase I1 c o n s i s t e d of a d e t a i l e d e v a l u a t i o n of AS-504 s i n g l e engine-out c a p a b i l i t y . The b a s e l i n e v e h i c l e and t r a j e c t o r y included t h e r e v i s e d t i l t a r r e s t , c a n t , and e a r l y CECO a t 135 seconds. The r e s u l t s show t h a t i n i t s p r e s e n t c o n f i g u r a t i o n the AS-504 v e h i c l e has an engine-out s t a g i n g problem using t h e AS-503 c h i - f r e e z e schedule. This problem w i l l be examined more c l o s e l y and p o s s i b l y a r e v i s e d chif r e e z e schedule recommended through a p p r o p r i a t e channels. �Phase I11 i s now almost complete and a s a r e s u l t w i l l recomm mend (1) a s p e c i f i c f i x f o r t h e AS-504 v e h i c l e , and ( 2 ) a g e n e r a l engineo u t guidance method a p p l i c a b l e t o a l l v e h i c l e s . A f i n a l r e p o r t on t h i s should be o u t around December 1, 1968. 8. O c c u l t a t i o n S t u d i e s (Lockheed) A r e p o r t p r e s e n t i n g t h e r e s u l t s of a p a r a m e t r i c a n a l y s i s of t h e e f f e c t s of v a r i o u s s a t e l l i t e o r b i t parameters on t h e o c c u l t a t i o n c h a r a c t e r i s t i c s of Mars o r b i t e r was d e l i v e r e d t o R-AERO-GA, "Mars O r b i t e r O c c u l t a t i o n A n a l y s i s w i t h P a r a m e t r i c Data f o r t h e 1973 through 1979 Type I Mars Capture M i s s i o n s , " by T. C. Davis, LMSC/HREC A791860, October 1968, C. O p t i m i z a t i o n Theory Branch 1. Parameter O p t i m i z a t i o n Study f o r ATM Schedule Order E-64 - Lockheed - The s o u r c e of t h e problem w i t h s t a b i l i t y of t h e l i n e a r i z e d analog s i m u l a t i o n used i n t h e hybrid o p t i m i z a t i o n technique has been i s o l a t e d ; i t i s due s o l e l y t o n o i s e and s c a l i n g problems a t a c r i t i c a l p o i n t i n analog s i m u l a t i o n s . S e v e r a l d i f f e r e n t analog r e p r e s e n t a t i o n s show cons i s t e n t r e s u l t s , w h i l e d i g i t a l s i m u l a t i o n s do n o t show any s t a b i l i t y problems. This problem has been d i s c u s s e d w i t h A s t r i o n i c s . A l o g i c change t h a t A s t r i o n i c s has introduced i n t o t h e CMG command s i g n a l t o smooth t h e s i g n a l appears l i k e l y t o c o r r e c t t h e s i m u l a t i o n problem a l s o . This i s c u r r e n t l y being checked o u t . The d i g i t a l l o g i c has been checked o u t , and o p e r a t i o n a l hybrid runs a r e expected when t h e analog problem i s corrected. 2. Launch Vehicle F l i g h t Control a. S a t u r n V/Apollo Load R e l i e f S t u d i e s Schedule Order E-60 - Northrop The b a s i c r i g i d a n a l y s i s has been completed. The load r e l i e f c o n t r o l l e r developed through r i g i d body s t u d i e s i s being analyzed on a high-speed analog s i m u l a t i o n which i n c l u d e s f l e x i b l e body e f f e c t s . A s e t of 500 measured winds w i l l provide t h e d i s t u r b a n c e t o t h e system. Supplemental i n v e s t i g a t i o n s continue on t h e u t i l i t y of parameter s e n s i t i v i t y technique t o d e s i g n a load r e l i e f cqnTomovicl s t r o l l e r f o r the Saturn ~ I A p o l l o . �b. . S t a t i s t i c a l Wind Model - Hayes (NAS8-21444) Objective: C o n s t r u c t i o n of a wind model f o r u s e i n s t a t i s t i c a l a n a l y s i s of launch v e h i c l e performance. A meeting w a s h e l d w i t h t h e c o n t r a c t o r on November 22 t o d i s c u s s t h e s t a t u s and f u t u r e d i r e c t i o n of t h e s t u d y . Data r e d u c t i o n has r e q u i r e d more e f f o r t and expense t h a n was expected, and t h e c o n t r a c t o r has s t a t e d t h a t t h e scope of work cannot be completed w i t h i n t h e fund a l l o c a t i o n u n l e s s some r e l i e f on t h e computation e f f o r t i s provided. No a d d i t i o n a l funds a r e c u r r e n t l y a v a i l a b l e . Attempts a r e being made t o reduce a l a r g e segment of t h e d a t a on MSFC computers. I f s a t i s f a c t o r y arrangements cannot be made, i t w i l l be n e c e s s a r y t o reduce t h e scope of work. It does appear p o s s i b l e t o reduce t h e scope of work i n such a manner a s t o r e t a i n s i g n i f i c a n c e of t h e reduced f i n a l ( p a r t i a l ) r e s u l t s ; t h e a d d i t i o n a l work n e c e s s a r y t o complete t h e o r i g i n a l scope of work could be completed inhouse u s i n g t h e programs and techniques developed by t h e c o n t r a c t o r . 3. Trajectory Optimization - Northrop (Schedule Order E-59) F i n a l copies of t h e r e p o r t on n e c e s s a r y c o n d i t i o n s f o r optimal c o n t r o l w i t h i n e q u a l i t y c o n s t r a i n t s on t h e time r a t e of change of t h e c o n t r o l v a r i a b l e s have been r e c e i v e d and d i s t r i b u t e d . The d r a f t copy of t h e r e p o r t on Runge-Kutta formulas f o r reducing t h e amount of computation needed i n t h e s o l u t i o n of optimal t r a j e c t o r i e s has been s t u d i e d and approved; f i n a l copies w i l l soon b e d e l i v e r e d . The cont r a c t o r i s i n v e s t i g a t i n g methods f o r o b t a i n i n g expans i o n s of Lagrange m u l t i p l i e r s i n terms of a n impulsive s o l u t i o n and methods f o r "updating" d e r i v a t i v e s of Lagrange m u l t i p l i e r s a t a g i v e n time w i t h r e s p e c t t o t h e s t a t e v a r i a b l e s a t t h e same time. 4. Minimax Control - General ~ y n a m i c s / ~ o n v a i(NAS8-21454) r Objective: (1) t o extend t h e C-minimax t h e o r y t o determine C-minimax performance i n t h e presence of incompletely s p e c i f i e d d i s t u r b a n c e s ; (2) t o determine i f a n a n a l y t i c s o l u t i o n e x i s t s f o r C-minimax performance f o r l i n e a r dynamical s y s tems w i t h bounded c o n t r o l ; and (3) t o i n v e s t i g a t e t h e computational problems d i s c o v e r e d t o e x i s t w i t h t h e c u r r e n t computational a l g o r i t h m . �The c o n t r a c t o r has continued t o s e a r c h f o r computationally a t t r a c t i v e methods of computing C-minimax c o n t r o l s f o r h i g h o r d e r systems. Methods a d d i t i o n a l t o t h o s e c i t e d p r e v i o u s l y have been o b t a i n e d , b u t each seems t o have i t s own computational d i s a d v a n t a g e . I n e s s e n c e , a p l e t h o r a of methods have been o b t a i n e d which y i e l d s t h e optimal c o n t r o l f o r g i v e n i n i t i a l c o n d i t i o n s , a l b e i t a t some computational expense. None of t h e methods y i e l d i n s i g h t i n t o t h e g e n e r a l p r o p e r t i e s of t h e s o l u t i o n , however, a s t h e c u r r e n t computational a l g o r i t h m does f o r second o r d e r systems. S t u d i e s of l i n e a r systems w i l l c o n t i n u e , and some cons i d e r a t i o n w i l l be g i v e n t o approximating problems y i e l d i n g general solutions. 5. Lunar Roving Vehicle I n v e s t i g a t i o n s have been i n i t i a t e d t o determine i f t h e r e e x i s t any s e r i o u s m o b i l i t y or n a v i g a t i o n problems f o r t h e c u r r e n t l y planned l u n a r r o v i n g v e h i c l e , which i s t o b e c o n t r o l l e d from e a r t h i n t h e unmanned mode of o p e r a t i o n . E f f o r t s t o d a t e have c o n s i s t e d of o b t a i n i n g and s tudying background m a t e r i a l on t h e l u n a r s u r f a c e environment and on t h e c o n t r o l and n a v i g a t i o n s t u d i e s made f o r p r e v i o u s l y proposed l u n a r r a v i n g v e h i c l e s . Progress has been impeded by t h e long time n e c e s s a r y t o o b t a i n some of t h e r e l e v a n t documents. �V I I . DYNAMICS AND FLIGHT MECHANICS DIVISION A. Multi-Projects Dynamics and Control 1. Vehicle Response t o D e t a i l e d Winds (Ref. ~ e c / ~ a n1968 . P* 49) The S a t u r n V v e h i c l e has been s i m u l a t e d b o t h a s a r i g i d and a s a n e l a s t i c v e h i c l e f o r f l i g h t through 975 d e t a i l e d Jimsphere winds, b o t h s c a l a r and d i r e c t i o n a l . R e s u l t s i n d i c a t e d t h a t f l y i n g a r i g i d v e h i c l e through t h e f i l e t e r e d winds (Rawinsonde e q u i v a l e n t ) and adding t h e r e s p o n s e obtained from a g e n e r a l i z e d harmonic a n a l y s i s approach, u s i n g a spectrum f o r t h e t u r b u l e n c e , c l o s e l y d u p l i c a t e s t h e r e s u l t s o b t a i n e d using t h e d e t a i l e d p r o f i l e s . I f t h e s e t e n t a t i v e conc l u s i o n s h o l d , a b e t t e r a n a l y s i s approach could b e developed s i n c e t h e r i g i d v e h i c l e s i m u l a t i o n w i t h f i l t e r e d winds can b e e f f i c i e n t l y s o l v e d on computers. R-AERO-DD 2. Six-Dimens i o n a l E l a s t i c Body Hybrid S i m u l a t i o n (New) A s ix-dimensional e l a s t i c body s i m u l a t i o n has been g i v e n t o t h e Computation Laboratory f o r p r o g r a m i n g on t h e hybrid computer. The approach i s t o a p p l y t h e same technique as used on t h e h i g h speed a n a l o g , u s i n g many winds, t o a 6-D s i m u l a t i o n . The h i g h speed simulaComputation Laboratory people b e l i e v e t h e y can run a t o t a l t i o n i s 2-D. t r a j e c t o r y w i t h a r e a l wind i n 1/100 of r e a l time. S i n c e a l l s t a t i s t i c s can be handled i n t h e d i g i t a l p o s i t i o n of t h e computer, o n l y one pass w i l l be needed through t h e wind ensemble t o o b t a i n a l l v e h i c l e responses i n a s t a t i s t i c a l manner. R-AERO-DD 3. Prelaunch Wind Monitoring (Ref. F e b . / ~ a r c h 1968, p. 3 7 ) The a t t e m p t t o develop an approach t o p r e d i c t , T hours b e f o r e launch, t h e v e h i c l e response t o expected winds a t launch is prog r e s s i n g . The wind s t a t i s t i c s have been obtained from R-AERO-Y, and b a s i c computer programs w i t h which t o u s e t h e wind s t a t i s t i c s have been w r i t t e n . The s t a t i c a e r o e l a s t i c p o r t i o n has been checked o u t , a l o n g w i t h t h e b a s i c v e h i c l e dynamics and c o n t r o l , i n c l u d i n g t r a j e c t o r y . The e v a l u a t i o n of t h e s e n s i t i v i t y of t h e v e h i c l e response t o t h e changing wind c h a r a c t e r i s t i c s has begun. D D D / M ~t i~ n �I). SaturnV 1. Dynamics and Control ~ o n g i t u d i n a l l ~ a t e r aCoupling l (Ref. Aug./Sept. 1968, p. 35): The l a t e r a l / l o n g i t u d i n a l coupling i n v e s t i g a t i o n of t h e 503 v e h i c l e has been completed w i t h no evfdence of a problem. AS-504 i s being analyzed by Boeing under a new t a s k f o r b o t h s t a b i l i t y and response. A paper on t h e AS-502 r e s u l t s , t o be p r e s e n t e d a t t h e AIAA meeting i n J a n u a r y , w i l l b e completed w i t h i n 2 weeks. A f i n a l r e p o r t of a l l inhouse work should be completed i n December. R-AERO-DD 2. P r o j e c t Information A p p l i c a b l e t o Many Vehicles D i r e c t Ascent Lunar Launch Window Study (Ref. March 1966, p. 35): Performed a t a low l e v e l of e f f o r t , a n a n a l y s i s of t h e d i r e c t a s c e n t l u n a r launch window has been completed. This a n a l y s i s d e f i n e d t h e payload and azimuth v a r i a t i o n s a s s o c i a t e d w i t h a d i r e c t - a s c e n t launch p r o f i l e t o e n e r g i e s corresponding t o f l i g h t times of 62, 6 7 , and 7 2 hours. A c o n s t r a i n t imposed on t h e f l i g h t p r o f i l e w a s t h a t the minimum d i p a l t i tude d u r i n g S-IVB burn be g r e a t e r than o r e q u a l t o 80 km. Coast times between t h e S - I 1 and t h e S-IVB s t a g e s were i n v e s t i g a t e d a s a method of i n c r e a s i n g t h e launch window d u r a t i o n . For e a r l y launches t h i s i s a p p r o p r i a t e , b u t i s n o t a p p l i c a b l e t o l a t e launches. (R-AERO-DAP/NSL) 3. P r o j e c t Information A p p l i c a b l e t o I n d i v i d u a l Vehicles a. Dynamics Data f o r AS-503 Third F l i g h t S t a g e (Mission C") ~ p r i l / ~ a1968, y p. 38 and August/September 1968, p. 37 A v i b r a t i o n a n a l y s i s which r e f l e c t s t h e payload change has been made of t h e t h i r d f l i g h t s t a g e S a t u r n V/AS-503 (Mission C' w i t h LES a t t a c h e d ) . A document which c o n t a i n s t h e dynamic d a t a f o r AS-503 S-IVB f l i g h t s t a g e (Mission c ' ) has been prepared f o r b o t h t h e manned t r a n s l u n a r miss i o n and t h e e a r t h o r b i t CSM o p e r a t i o n s w i t h command r e s t a r t m i s s i o n . This document was d i s t r i b u t e d under cover memorandum R-AERODD-138-68. R-AERO-DDS/BO~~~~ b. On-Pad Dynamics C h a r a c t e r i s t i c s f o r AS-504 (New) An on-pad v i b r a t i o n a n a l y s i s has been made of AS-504 f o r s e v e r a l d i f f e r e n t f u e l i n g c o n d i t i o n s . A payload of 100,000 l b s was assumed f o r t h e a n a l y s i s . These d a t a a r e soon t o be d i s t r i b u t e d a s e n c l o s u r e s t o memorandum R-AERO-DD-141-68. R-AERO-DDS �C. S a t u r n Apollo A p p l i c a t i o n s Program 1. Cluster a. Mission P r o f i l e (1) AAP-1, 2, 3A, 3, and 4 F l i g h t P r o f i l e and Launch Window A n a l y s i s (Ref. Aug./Sept. 1968, p. 38 and 41) The documentation of t h e p r e l i m i n a r y f l i g h t p r o f i l e and launch window a n a l y s i s f o r t h e AAP C l u s t e r missions t o a n AAP-2 b r b i t a l a l t i t u d e of 220 NM has been completed. The AAP c l u s t e r m i s s i o n p r e l i m i n a r y £1 i g h t p r o f i l e and launch window a n a l y s i s i s being r e p e a t e d t o r e f l e c t r e c e n t a n d / o r a n t i c i p a t e d b a s e l i n e changes. Under t h e new p l a n , t h e OWS ( U P - 2 ) w i l l i n s e r t , a f t e r p a s s i v a t i o n , near p e r i g e e of a 185 x 210 NM o r b i t . The o r b i t a l i n c l i n a t i o n of t h e OWS w i l l be approximately 35 d e g r e e s , chosen s u c h that t h e AAP-2 launch w i l l be optimum (maximum payload) and a n AAP-1 optimum in-phase s o u t h e r l y launch o p p o r t u n i t y w i l l be a v a i l a b l e approxim a t e l y 2 112 s t a g e s t o o r b i t . On AAP-1, t h e CSM w i l l i n s e r t i n t o a n 8 1 x 120 NM o r b i t and c i r c u l a r i z e a t apogee. The c o e l l i p t i c rendezvous method w i l l t h e n be followed, w i t h t h e h e i g h t ad j u s t maneuver being performed s o a s t o r a i s e apogee t o 10 NM below t h e p e r i g e e of t h e workshop o r b i t . This p r o f i l e w i l l provide t h e maximum amount of phasing v a r i a t i o n . Af t e r rendezvous i s complete, t h e CSM w i l l c i r c u l a r i z e t h e OWS/CSM c l u s t e r i n t o a 210 x 210 NM o r b i t . Then AAP-3A and AAP-3 w i l l be launched s o u t h e r l y approximately 90 and 180 days a f t e r t h e AAP-1 launch, r e s p e c t i v e l y . AAP-4 i s t o be launched s e v e r a l days a f t e r AAP-3 and w i l l perform a n unmanned rendezvous w i t h t h e c l u s t e r . The s i m u l a t i o n of t h e AAP c l u s t e r m i s s i o n has proceeded t o t h e c i r c u l a r i z a t i o n of t h e OWS/CSM (AAP-2/AAP-1) c l u s t e r . The OWS o r b i t a l i n c l i n a t i o n s a t i s f y i n g t h e U P - 1 and 2 optimum launch r e q u i r e ments i s 35.747 d e g r e e s . The OWS w i l l be launched a t 17:OO @lT on day z e r o and AAP-1 w i l l be launched a t 21:24 GMT on day 2. R-AERO-DAO/DAP/ Nor t h r o p (2) Mechanization of t h e C l u s t e r Mission P r o f i l e and Launch Window Analysis (Ref. Aug./Sept. 1968, p. 40) The l o g i c flow f o r t h e d r i v e r o r e x e c u t i v e program n e c e s s a r y f o r t h i s mechanization has been developed. The O r b i t a l P r e d i c t i o n Program, used f o r c o a s t s and launch o p p o r t u n i t y c a l c u l a t i o n s , and t h e Quick-Look Program, used f o r p r e l iminary m i s s i o n s imulat i o n s , have been converted and l i n k e d on t h e UNIVAC 1108 computer. P r e s e n t l y , t h e CDC 3200 v e r s i o n s o f t h e s e programs a r e being used t o develop and check �o u t t h e m o d i f i c a t i o n s n e c e s s a r y f o r t h e s e programs t o perform t h e operat i o n s which have p r e v i o u s l y been done by hand. Also, they a r e being used t o develop some of t h e l o g i c which w i l l l a t e r be placed i n t h e d r i v e r . R-AERO-DAO/NO~~~~O~ (3) LM/ATM Unmanned Rendezvous (Ref. J u n e / ~ u l y1968, P. 41) The p r a c t i c a l i t y of using t h e workshop a t t i t u d e c o n t r o l system (WACS) a s a k i c k s t a g e t o do a p o r t i o n of t h e maneuvers i n t h e AAP-4 rendezvous p r o f i l e i s now under i n v e s t i g a t i o n . It i s assumed t h a t t h e S-IVB s t a g e i n s e r t s i n t o a n o r b i t w i t h a p e r i g e e somewhat below t h e f i n a l d e s i r e d o r b i t and apogee above i t . The ,WACS (modif i e d w i t h a f t f i r i n g t h r u s t e r s ) performs a c i r c u l a r i z a t i o n maneuver a f t e r p a s s i n g through apogee t h e second time. By v a r y i n g t h e r a d i u s of apogee (and p e r i o d ) a launch window can be o b t a i n e d , and i t i s p o s s i b l e t o comp e n s a t e f o r t h e down-range, i n s e r t i o n d i s p e r s i o n s . Trade-offs a r e being determined between i n s e r t i o n a l t i t u d e , payload, WACS p r o p e l l a n t r e q u i r e d , LM RCS p r o p e l l a n t r e q u i r e d , launch window widths and number of phasing o r b i t s . R-AERO-DAO ( 4 ) Design Reference Miss i o n Document (DRMD) AAP-112 (Ref. April/May 1968, p. 42) Volume V of t h e DRMD i s being r e v i s e d . Revision A i s f o r t h e purpose of i n c o r p o r a t i n g changes t o t h e m i s s i o n r e s u l t i n g from change 1 t o Program D i r e c t i v e 3C, F l i g h t Mission D i r e c t i v e f o r AAP-112, dated May 1 4 , 1968, and t h e F i n a l Report of t h e AAO C l u s t e r AD Hoc A t t i tude Control Working Group, dated May 24, 1968. Revision B i s issued a s Appendix A t o i n c o r p o r a t e p r e l i m i n a r y r e s o u r c e usage d a t a . Revision A has been i s s u e d under cover memorandum R-AERO-DAM-36-68 and Revis i o n B under cover memorandum R-AERO-DAM-40- 68. R-AERO-DAM/M~~t i n (5) AAP Experiments Data Bank (Ref. April/May 1968, P. 42) ( a ) Two more i s s u e s of t h e d a t a bank have been p u b l i s h e d . These i s s u e s (October 1968, and November 1968) i n c o r p o r a t e changes t o v a r i o u s experiments which have a d i r e c t e f f e c t on t h e payload f o r t h e AAP. (b) The AAP experiment d a t a bank i s being r e v i s e d t o i n c o r p o r a t e v a r i o u s s u g g e s t i o n s and comments t o make i t more meaningf u l . C o o r d i n a t i o n between -DAM, I-S/AA, and M a r t i d M a r i e t t a C o r p o r a t i o n i s b e i n g maintained t o i n s u r e that t h e r e v i s e d d a t a bank i s u s e f u l f o r a l l purposes. R-AERO- artin in �(6) Experiment C o m p a t i b i l i t y (New) R-AERO-DAM, i n c o n j u n c t i o n w i t h R-AERO-P, I-S/AA, and ~ a r t i n / M a r i tet a C o r p o r a t i o n , i s answering a n a c t i o n item s e n t from Luskin r e l a t i v e t o Experiment/Mission C o m p a t i b i l i t y A n a l y s i s . The scope of t h e endeavor is f o r a more comprehensive assessment t o i n c l u d e e v a l u a t i o n of s e v e r a l a l t e r n a t i v e experiment combinations. R-AERO-DAM (7) AAP Hardware U t i l i z a t i o n (New) E f f o r t s a r e being made t o complete a flow c h a r t showing hardware u t i l i z a t i o n i n t h e AAP f o r contingency and backup miss i o n planning. I n a d d i t i o n , a second phase ( t h a t of p r o b a b i l i t y d e t e r mination) is b e i n g worked, a l t h o u g h t h i s phase i s p r o g r e s s i n g s l o w l y because some of t h e i n f o r m a t i o n i s n o t a v a i l a b l e . (8) . AAP LM/ATM Unmanned Rendezvous (Ref. Aug /Sep t . 1968, p. 44) The t a s k of e s t a b l i s h i n g f e a s i b i l i t y of a n S-IVB/ LM-ATM rendezvous w i t h t h e o r b i t a l assembly u s i n g t h e S-IVB mainstage p r o p u l s i o n s y s tem i n a r e i g n i t i o n mode and t h e a u x i l i a r y p r o p u l s i o n s y s tem l o n g i t u d i n a l type t h r u s t e r c o n t i n u e s . The a r e a s under s tudy a r e (1) second S-IVB 5-2 t h r u s t i n g i n t o a n i n t e r m e d i a t e w a i t i n g o r b i t , (2) h e i g h t a d j u s t m e n t maneuver f o r proper phase r e l a t i o n s h i p w i t h t h e t a r g e t , (3) p l a n e change maneuver a t t h e l i n e of nodes between t h e S-IVB/LM-ATM and t h e workshop o r b i t , ( 4 ) t k r m i n a l rendezvous t r a n s f e r maneuvers, (5) midcours e c o r r e c t i o n maneuver, and (6) t h e f i n a l v e l o c i t y matching maneuver a t t h e s t a t i o n k e e p i n g pos i t i o n . The a n a l y s i s i n d i c a t e d that a l l maneuvers can be performed w i t h t h e low a c c e l e r a t i o n p r o f i l e provided c a r e i s t a k e n t o e s t a b l i s h compatible geometry s o t h a t d e l t a v e l o c i t y requirements a r e cons is t e n t w i t h t h e a v a i l a b l e t h r u s t l e v e l . R-AERO-DGG/ Nor t h r o p b. Guidance T r a j e c t o r y Shaping Payload Improvements (Ref. Aug./Sept. 1968, p. 42): The payload t r a d e - o f f s w i t h S-IB v e h i c l e l o a d s u s i n g t h e S-IBIS-IVB/LM-ATM c o n f i g u r a t i o n has been e s t a b l i s h e d f o r two d i f f e r e n t o r b i t s u s i n g S-IB t r a j e c t o r y shaping t e c h n i q u e s . Approximately 450 pounds of payload can b e gained w i t h a n i n c r e a s e i n v e h i c l e l o a d s of 3 p e r c e n t and 580 pounds f o r 5 p e r c e n t f o r a n o r b i t of 80 x 260 n a u t i c a l m i l e s . Approximately 450 pounds payload i n c r e a s e f o r 3 p e r c e n t l o a d s i n c r e a s e and 560 pounds payload i n c r e a s e f o r 5 p e r c e n t i n c r e a s e i n v e h i c l e loads can be achieved f o r a d i r e c t i n s e r t i o n i n t o a 220 n a u t i c a l m i l e c i r c u l a r R-AERO-DGG orbi t . �c. Dynamics and Control (1) ATM S t a b i l i t y and P o i n t i n g S t u d i e s (Ref. Aug./Sept. 1968, p. 43) Work being conducted f o r t h e ATM m i s s i o n , C l u s t e r I , i s divided i n t o f i v e b a s i c areas: (1) s t a b i l i t y of e l a s t i c body c l u s t e r and bending f i l t e r d e t e r m i n a t i o n , (2) p o i n t i n g a c c u r a c i e s of t h e ATM t o d i s t u r b a n c e s such a s man motion, (3) momentum management, (4) s t e e r i n g laws, and (5) program development. This work i s being done in-house, w i t h t h e m i s s i o n s u p p o r t c o n t r a c t o r s , and i n t e g r a t i o n c o n t r a c t o r and i s p r o g r e s s i n g a s follows: - A n a l y s i s has been made (a) S t a b i l i t y Analysis of t h e g e n e r a l s t a b i l i t y c h a r a c t e r i s t i c s of t h e c l u s t e r u s i n g CMG'S by 1i n e a r i z i n g t h e d e s c r i b i n g d i f f e r e n t i a l e q u a t i o n s . I f t h e s y s tem were i d e a l (no l a g s ) , no bending f i l t e r s would be needed s i n c e c o n t r o l s e n s o r s and t o r q u e s a r e l o c a t e d a t t h e same v e h i c l e s t a t i o n ; however, t h e i n h e r e n t l a g s i n t h e s y s tem r e q u i r e networks. These networks a r e f a i r l y s i m p l e , u s u a l l y a f o u r t h o r d e r . S t u d i e s thus f a r i n d i c a t e a n a c c e p t a b l e s t a b i l i t y margin u s i n g t h e s e networks, w i t h v e r y l i t t l e d e t e r i o r a t i o n of t h e pointing accuracy. R - A E R O - D D D I M ~ ~ ~ ~ ~ To b e t t e r a s s e s s coupling and n o n l i n e a r i t i e s e l i m i n a t e d through t h e l i n e a r i z a t i o n assumed i n t h e above s t u d i e s , t h e t o t a l 3-D system of e q u a t i o n s has been formulated, expanded a b o u t t h e s i n g u l a r p o i n t s (CMG gimbal a n g l e s ) , and t h e n l i n e a r i z e d a b o u t t h e s e p o i n t s f o r s t a b i l i t y . This e f f o r t i s i n f i n a l check-out on t h e computer; r e s u l t s a r e expected soon. ~ - A E R 0 - ~ ~ ~ / N o r t h r o p - (b) P o i n t i n g Accuracy The p o i n t i n g a c c u r a c y f o r t h e ATM has been approached i n two ways: o b t a i n i n g t h e response of the t e l e s c o p e and v e r n i e r c o n t r o l system by d r i v i n g t h e t e l e s c o p e base a t t h e maximum expected bending mode amplitude f o r each bending mode frequency; and o b t a i n i n g t h e response of t h e t o t a l e l a s t i c system t o v a r i o u s man motions and d i s t u r b a n c e i n p u t s . R e s u l t s of t h e s e a n a l y s e s i n d i c a t e t h a t t h e p o i n t i n g a c c u r a c y of t h e s y s tem can be met f o r a l l c a s e s s t u d i e d which included i n i t i a l a t t i t u d e e r r o r s of 0.02" on each a x i s . Some 25 d i f f e r e n t gimbal a n g l e o r i e n t a t i o n s were i n v e s t i g a t e d on t h e hybrid computer. R - ~ ~ ~ ~ - D ~ / ~ a r t i n / N o r t h r o p - ( c ) Momentum Management S t u d i e s have been made comparing v a r i o u s s t e e r ing laws and d i s t r i b u t i o n laws t o determine cont r o l l a b i l i t y of t h e c l u s t e r . This was done by observing t h e system r e s p o n s e t o a sequence of 50 n-m torque commands, u s i n g CMG1s and Che 4-vector c o n t r o l w i t h no gimbal c o n t r o l , ~ e n n e l ' s r o t a t i o n and d i s t r i b u t i o n , l i n e a r gimbal a n g l e feedback, and q u a d r a t i c feedback. The H-vector �was changed t o H-vector c o n t r o l and t h e s t u d y r e p e a t e d f o r lLnear gimbal feedback. I n i t i a l i n d i c a t i o n s show t h e l i n e a r o r q u a d r a t i c feedback s u p e r i o r t o t h e i s o g o n a l d i s t r i b u t i o n l a w i n t h e c a p a b i l i t y of each s y s tem f o r p r e v e n t i n g a n t i p a r a l 1 , e li s m . R-AERO-DD/Nor t h r o p - The work done u s i n g a CMG con(d) S t e e r i n g Laws t r o l l a w based on t h e concept t h a t t h e momentum v e c t o r s always form a maximum volume i s being documented. Although t h e law i s c o n c e p t u a l l y v e r y s i m p l e , t h e a c t u a l p h y s i c a l implementation of t h e law a p p e a r s t o b e more complex t h a n t h e c o n t r o l laws c u r r e n t l y i n o p e r a t i o n . R-AERO-DDD - Development of a s e t of ( e ) Program Development d i g i t a l computer modules f o r t h e v a r i o u s phases of C l u s t e r I m i s s i o n i s c o n t i n u i n g . Modules have been programmed f o r a l l c o n t r o l systems (LNG, v e r n i e r , r e a c t i o n j e t ) , r i g i d body dynamics, o r b i t dynamics, and g r a v i t y g r a d i e n t . Four of t h e modules, r i g i d body dynamics, o r b i t dynamics CMG'S, and g r a v i t y g r a d i e n t have been r u n t o g e t h e r on t h e 1108 computer and good r e s u l t s o b t a i n e d . The major d i f f i c u l t y thus f a r i s computer r u n time. Unless a major breakthrough is obtained i n speed on d i g i t a l comp u t e r s , most o r b i t a l dynamic s t u d i e s w i l l have t o be made on h y b r i d o r a n a l o g computer. ~ ~ / ~ o r t h r o p . (2) P a s s i v e A t t i t u d e C o n t r o l (Ref. Aug./Sept. P. 4 5 ) 1968, The f l e x i b i l i t y of t h e g e n e r a l purpose a t t i t u d e c o n t r o l program (ACP) f o r l a r g e e a r t h o r b i t i n g s p a c e c r a f t has been subs t a n t i a l l y enhanced by adding a s e l f - c o n t a i n e d s u b r o u t i n e f o r d e n s i t y computation based on ~ a c c h i a ' s d e n s i t y model. The program has been s u c c e s s f u l l y checked o u t . A computer program e s p e c i a l l y e f f i c i e n t f o r s imul a t i n g p a s s i v e s a t e l l i t e motion over long time p e r i o d s s u c h a s 10 o r more o r b i t s has a l s o been s u c c e s s f u l l y checked o u t . The i n t e g r a t i o n r o u t i n e s a r e b e i n g r e f i n e d f o r f u r t h e r r e d u c t i o n s i n t h e computing time. The program i s b e i n g documented. E x c e l l e n t r e s u l t s have been o b t a i n e d i n f i r s t comp u t e r s i m u l a t i o n s where t h e s o l a r panels of a p a s s i v e s a t e l l i t e a r e used a s aerodynamic dampers. T o r s i o n a l s p r i n g s and dampers provide t h e necess a r y phasing between s p a c e c r a f t and panel o s c i l l a t i o n s f o r maximum dampi n g . An e f f o r t i s underway t o reduce t h e computing time of t h e d i g i t a l s imula t i o n program. R-AERO-DCA �d. P r o j e c t Information Applicable t o I n d i v i d u a l Vehicles AAP-2 Rigid Body Control Responses *(Ref. Aug./sept. 1968, p. 43) Rigid body c o n t r o l responses f o r t h e AAP-2 v e h i c l e have been completed f o r two time p o i n t s (max q a , max q ) and published i n R-AERO-DCC-11-68. Because of t h e l a r g e responses and near l o s s of cont r o l f o r t h e RSS c a s e when e x c i t e d by a 95 p e r c e n t i l e n o n d i r e c t i o n a l d e s i g n wind, time responses f o r t h e 90 p e r c e n t i l e n o n d i r e c t i o n a l s y n t h e t i c wind were a l s o included. Responses f o r t h e Mach 1 time p o i n t and j u s t b e f o r e inboard engine c u t o f f w i l l be published l a t e r . The l a r g e responses o b t a i n e d f o r t h i s v e h i c l e r e s u l t from a forward s h i f t i n t h e c e n t e r of p r e s s u r e and a n i n c r e a s e i n t h e normal f o r c e c o e f f i c i e n t i n t h e c r i t i c a l h i g h dynamic p r e s s u r e r e g i o n caused by t h e con£ i g u r a t i o n (AS-203 nose cone w i t h c y l i n d r i c a l e x t e n s i o n , and s o l a r panel c o n d u i t s ) . R-AERO-DC 2. OWS a. OWS Control Impulse S t u d i e s (Aug./Sept. 1968, p. 4 4 , 45) The p r e s e n t m i s s i o n t i m e l i n e f o r AAP-1-2, 3A, 3 - 4 r e q u i r e s t h e OWS c o n t r o l system t o handle t h e c l u s t e r c o n t r o l f o r s e v e r a l types of o r b i t s , v e h i c l e o r i e n t a t i o n , and maneuvers. S t u d i e s i n each of t h e s e a r e a s a r e being conducted a s w e l l a s s e n s i t i v i t y of impulse requirement These s t u d y a r e a s a r e "tugboat" t o v a r i o u s s y s tem parameter v a r i a t i o n s s t a b i l i t y c h a r a c t e r i s t i c s , s e n s i t i v i t y t o mass parameters, s e n s i t i v i t y t o c o n t r o l systems deadbands, and e f f e c t of o r b i t i n c l i n a t i o n . A t t h e p r e s e n t time, t h e OWS impulse c a p a b i l i t y meets t h e r e q u i r e m e n t s . R-AERO-DDD . - - "Tugboat" c o n f i g u r a t i o n Computer runs have (1) OWS i n d i c a t e d t h a t t h e second bending- mode of t h e " tugboat" configuration i s unstable. S i n c e t h i s was unexpected, a c l o s e r checkout of t h e e q u a t i o n s and program was i n i t i a t e d . I t has been decided t h a t a TR-48 analog s i m u l a t i o n might be more f l e x i b l e than a l i n e a r i z e d s t a b i l i t y a n a l y s i s f o r parameter s t u d i e s . This analog s i m u l a t i o n i s now being implemented. R-AERO-DDD - ( 2 ) OWS Mass Parameter S e n s i t i v i t y - R-P&VE has r e q u e s t e d t h a t a l i s t i n g be made of mass parameters which a f f e c t WACS p r o p e l l a n t b u d g e t s . Computer runs a r e now being made t o show t h e e f f e c t of i n e r t i a l and c . g . v a r i a t i o n s upon t h e WACS impulse per o r b i t . These r e s u l t s w i l l be published by memo w i t h i n t h e n e x t r e p o r t i n g p e r i o d . This i n f o r m a t i o n i s needed by P&VE t o h e l p them p l a n a b e t t e r c o n t r o l of important mass c h a r a c t e r i s t i c s . R-AERO-DDD �(3) OWS Control Impulse S e n s i t i v i t y t o Control System An OWS c o n t r o l a t t i t u d e parameter s t u d y has been made (R-AERODeadband DDD-137-68 ) The o p e r a t i o n a l mode of the OWS i s X-POP (x-axis perpendicu l a r t o o r b i t a l p l a n e ) . From g r a p h s , we can determine t h e impulse per o r b i t f o r v a r i o u s combinations of deadband, average d e n s i t i e s , and deviat i o n s from X-POP. R-AERO-DDD - ( 4 ) E f f e c t of 35" O r b i t I n c l i n a t i o n on Impulse RequireA c l u s t e r contingency s t u d y f o r t h e OWS u s i n g a 35-degree ments (New) i n c l i n a t i o n w i l l be completed b e f o r e t h e end of t h e month. I n t h e e v e n t of a m i s s i o n a b o r t , t h e OWS w i l l decay i n o r b i t , and a t t h e s t a r t of a n o t h e r m i s s i o n t h e CSM w i l l b o o s t t h e OWS i n t o a h i g h e r o r b i t . Circul a r and e l l i p t i c a l o r b i t s a r e considered. The impulse per o r b i t f o r the c i r c u l a r o r b i t s can be obtained from graphs i n R-AERO-DDD-137-68. R-AERO-DDD - b. A c t i v e Control (Ref. Aug./Sept. 1968, p. 44) X-POP-type missions a r e being simulated f o r t h e OWS/ATM c l u s t e r , where t h e e f f e c t s of time l a g s on f u e l consumption of t h e React i o n C o n t r o l Sys tem a r e under s t u d y . The o r b i t considered i s a 230 n.mi. c i r c u l a r o r b i t . The s t u d y of t h e e f f e c t s of i n t e g r a t i o n s t e p s i z e on t h e a c c u r a c y of t h e computed f u e l e x p e n d i t u r e s r e q u i r e s some a d d i t i o n a l work. A program t o s i m u l a t e g r a v i t y - g r a d i e n t momentum dumping and a program f o r a c c u r a t e e v a l u a t i o n and comparison of v a r i o u s CMG momentum d i s t r i b u t i o n techniques a r e being checked o u t . R-AERO-DC 3. ATM - Mission Profile Vis i b i l i t y of t h e Earth-Moon L i b r a t i o n P o i n t s from ATM (Ref. A u g . / ~ e p t . 1968, p. 46 and .June/.July 1968, p. 46) A l l p r e s e n t l y planned development work on t h i s problem has been completed and i s being documented. F u t u r e p r o d u c t i o n runs w i l l probably occur a t i r r e g u l a r i n t e r v a l s a s more d e t a i l s on t h e ATM m i s s i o n become a v a i l a b l e . During t h e course of t h i s work, a n e r r o r was discovered i n a n e x i s t i n g program a t t h e Computation Laboratory. The program was one used t o c o n v e r t t h e ephemeris from a "mean e q u a t o r and equinox of 1950.0" c o o r d i n a t e system t o a "mean e q u a t o r and equinox of date" c o o r d i n a t e system. This program had a time e r r o r of 110.8 minutes which produced a n e r r o r i n t h e a n g u l a r p o s i t i o n of t h e sun of a b o u t one t e n t h of one d e g r e e , and a n e r r o r i n t h e a n g u l a r p o s i t i o n of t h e moon of about one degree. (An e r r o r i n t h e a n g u l a r p o s i t i o n of t h e moon of one degree i s e q u a l t o two l u n a r d i a m e t e r s . ) The s e a r c h f o r t h i s e r r o r consumed more than one week and, what i s more s e r i o u s , someone i n t h e p a s t may have used t h i s program w i t h t h e e r r o r unknowingly. �D. General 1. Response of F l e x i b l e Space Vehicles t o Docking fmpact The e f f o r t thus f a r has been d i r e c t e d a t completion of t h e phase wherein t h e chase and t a r g e t v e h i c l e s a r e assumed t o be r i g i d b o d i e s . The programming and f o r m u l a t i o n corresponding t o t h i s phase of t h e t a s k i s complete. The d i g i t a l program i s being e x e r c i s e d w i t h a s e t of nominal parameters t h a t c h a r a c t e r i z e a t y p i c a l AAP con£ i g u r a t i o n , i n c l u d ing t h e docking mechanism parameters . The c a l c u l a t i o n s f o r response based on r i g i d chase and t a r g e t v e h i c l e s w i l l , i n a l l p r o b a b i l i t y , i n f l u e n c e t h e modeling and f o r m u l a t i o n corresponding t o t h e e l a s t i c chase and t a r g e t v e h i c l e s phase of t h e s t u d y . It i s expected t h a t c e r t a i n s i m p l i f y i n g assumptions can be made based on t h e r e s u l t s of t h e i n i t i a l phase of t h e s t u d y . R - A E R O - D D I M ~ ~ ~ ~ ~ 2. S t r u c t u r a l Damping P r e d i c t i o n s (Aug. / S e p t . 1968, p. 47) The m a t e r i a l damping program w a s completed and p a r t i a l l y checked o u t d u r i n g October. This program n u m e r i c a l l y i n t e g r a t e s elemental m a t e r i a l damping over t h e volume of each s t r u c t u r a l element. I t then sums t h e energy d i s s i p a t e d and t h e s t r a i n energy f o r each element over the e n t i r e s t r u c t u r e . The s o l a r a r r a y s of t h e Apollo Telescope Mount a r e being used f o r checkout. R-AERO- lockheed heed 3. Study of Use of S c a l e Models t o Determine t h e S t r u c t u r a l Dynamics C h a r a c t e r is t i c s of Space Vehicles (New) The f o l l o w i n g p r o g r e s s has been made i n t h i s study: (a) V i b r a t i o n a n a l y s i s of t h e f u l l - s c a l e a n t e n n a c o n f i g u r a t i o n was completed, t o p r o v i d e bas i s f o r comparison w i t h v a r i o u s models. (b) A s i m p l i f i e d e q u i v a l e n t beam-type model c o n f i g u r a t i o n was a n a l y z e d . V i b r a t i o n a n a l y s i s was completed and the method of cons t r u c t i o n was found u n s a t i s f a c t o r y . A s t u d y of b e t t e r beam-type r e p r e s e n t a t i o n of t h e s t r u c t u r e i s underway. ( c ) A g e n e r a l approach f o r s t i f f n e s s s i m u l a t i o n f o r v a r i o u s methods of antenna model c o n s t r u c t i o n was o u t l i n e d . Design c a l c u l a t i o n s f o r t h e model s h e l l s of t h e S a t u r n V second s t a g e t a n k , s k i r t , and a d a p t e r have been made f o r two types of models. (d) evaluated. V i b r a t i o n modes f o r t h e AAP c l u s t e r were r e c e i v e d and �( e ) A s t u d y of a l t e r n a t e approaches t o the c o n s t r u c t i o n of each of t h e main s e c t i o n s of t h e c l u s t e r was continued. Study of l i q u i d mass s i m u l a t i o n was begun. R-AERO- artin in 4. System P r o b a b i l i t y Module (Ref. ~ u n e / J u l y 1968, p. 4 8 ) During t h i s performance p e r i o d , t h e methods devised f o r u s i n g t h e Markov Chain Theory f o r c a l c u l a t i n g p r o b a b i l i t i e s a r e i n t h e f i r s t s t a g e s of programming. The programming should be completed d u r i n g t h e n e x t one o r two r e p o r t i n g p e r i o d s . ~ - A ~ ~ o - ~ A ~ / L o c k h e e d VIII . A. FLIGHT TEST ANALYSIS DIVISION S p e c i a l P r o j e c t s O f f i c e and S t a f f 1. F l i g h t ~ v a l u a t i b nPanel (FEP) a. Meeting The s i x t e e n t h meeting of t h e F l i g h t E v a l u a t i o n Panel was h e l d a t MSC on October 8 , 1968. M r . Don D. Arabian, Chief of t h e T e s t D i v i s i o n i n t h e Apollo S p a c e c r a f t Program O f f i c e , i s t h e new MSC co- chairman. Major agenda d i s c u s s i o n s concerned i n t e r - c e n t e r anomaly i n v e s t i g a t i o n procedures, subpanels r e p o r t s , and manned f l i g h t i n t e r center i t e r f a c e plans. It was a l s o agreed t h a t t h e FEP w i l l g e n e r a t e a proposed r e w r i t e of Apollo Program D i r e c t i v e 19 f o r submission t o Headquarters. A f t e r t h e FEP meeting on October 8 , 1968 a t MSC, M r . Arabian s t a t e d t h a t t h e l a t e s t f i n d i n g s of t h e AS-502 133-seconds anomaly a b s o l v e t h e launch v e h i c l e f o r t h e s p a c e c r a f t f a i l u r e . These f i n d i n g s d e r i v e d from microdens i t o m e t e r (photogrammetric) a n a l y s e s of s e l e c t e d frames of t h e ALOTS f i l m n e a r 133-seconds combined w i t h t e s t s on honeycomb s t r u c t u r e l e a d them t o t h e c o n c l u s i o n t h a t honeycomb debonding p e r m i t t e d i n t e r f a c e s h e e t f a i l u r e followed by t h e o u t e r f a c e s h e e t f a i l u r e . M r . Arabian was t o b r i e f M r . Low on t h e s t a t u s t h a t a f t e r n o o n and w a s recommending t h a t t h e Apollo 6 anomaly r e p o r t be i s s u e d d e l e t i n g t h e a n a l y s i s on t h e S-IVB and I U . M r . E r n e s t Nathan a g r e e d , i f a c r e d i t remark f o r MSFC s u p p o r t i n t h e i n v e s t i g a t i o n i s included. MSFC w i l l b e a b l e t o review t h e anomaly d r a f t of t h e r e p o r t b e f o r e p u b l i c a t i o n . M r . Arabian was most complimentary t o MSFC f o r i t s support during the i n v e s t i g a t i o n . �b. Activities (1) An MSFC t e c h n i c a l c o n t i n g e n t a t t e n d e d the Apollo 7 (128-205) F l i g h t Crew Systems Debriefing ( C o n f i d e n t i a l ) a t MSC on October 31 and November 1, 1968. The group headed by M r . E r n e s t B. Nathan, MSFC Co-Chairman of t h e Apollo F l i g h t E v a l u a t i o n Panel (FEP) , cons i s ted o f : James S i s s o n (I-IB-E) - S a t u r n I B Program F l i g h t Dynamics and Mechanics Robert Jackson (R-AERO-P) As t r i o n i c s Sys tems Glen R i t t e r (R-ASTR-S) Robert Hunt (R-P&VE-S) Propuls i o n and S t r u c t u r e s D r . James Dozier (R-SSL-P) - A s t r o p h y s i c s . - - - Attendance was p r i m a r i l y f o r t h e launch v e h i c l e p o r t i o n of t h e d e b r i e f i n g , e x c e p t f o r M r . Nathan, who was t h e r e b o t h days, and M r . Dozier, who a l s o a t t e n d e d t h e Crew Observations p o r t i o n . The FEP a l s o arranged f o r i n t e r m i t t e n t a t t e n d a n c e of M r . J e f f e r y H a m i l t o n , t h e MSFC AAP l i a i s o n r e p r e s e n t a t i v e a t MSC. (2) Air-to-ground v o i c e t r a n s c r i p t s through T f 30 (cSM-S-IVBIIUISLA rendezvous) were condensed t o a launch v e h i c l e hours o r i e n t e d c o n t e n t and d i s t r i b u t e d t o MSFC management, s e l e c t e d FEP and FEWG members, AAP, and o t h e r i n t e r e s t e d t e c h n i c a l elements. (3) Two c l a s s i f i e d volumes of the F l i g h t Crew Technical D e b r i e f i n g t r a n s c r i p t s were d i s t r i b u t e d t o MSFC personnel on a need-toknow bas i s . (4) MSFC i n p u t s t o t h e Apollo 8 ( A S - ~ O ~ / C S M - ~FOl i~g)h t Crew D e b r i e f i n g Guide were compiled f o r t r a n s m i t t a l t o MSC. 2. Apollo A p p l i c a t i o n s - FEWG - Payload The group membership i s being r e c o n s t r u c t e d because of t h e cons i d e r a b l e changes that. have been made i n t h e MSFC r e s p o n s i b i l i t i e s d u r i n g t h e p a s t y e a r . New e v a l u a t i o n r e s p o n s i b i l i t i e s have been added, and concepts have been r e v i s e d , a s the many new a s p e c t s of manned payloads have been a n a l y z e d . The d a t a flow i n t e r f a c e has been under study and i s now b e i n g worked w i t h t h e newly formed i n t e r - c e n t e r panel. A p r e l i m i n a r y d r a f t of t h e updated programmatic p l a n f o r AAP Payload E v a l u a t i o n has been d i s t r i b u t e d t o t h e membership f o r review and comment. A g e n e r a l p r e s e n t a t i o n and review meeting of t h e group i s planned f o r e a r l y n e x t y e a r t o up-date t h e developments f o r t h o s e prev i o u s l y involved and t o o r i e n t t h e new elements, i n c l u d i n g t h e new module contractors. �Very meager a s s i s t a n c e has been a v a i l a b l e from t h e i n t e g r a t i o n c o n t r a c t o r , who i s t o supply s t a f f s u p p o r t t o t h e group. It i s expected t h a t t h i s s u p p o r t w i l l be s u f f i c i e n t t o be,meaningful e a r l y n e x t y e a r . The e a r l y d r a f t s of t h e m i s s i o n p l a n s a r e being delayed a s a r e s u l t . 3. Mission E v a l u a t i o n Panel The f i r s t meeting of t h e AAP Mission E v a l u a t i o n Panel was h e l d a t MSFC on November 7 t h . R e p r e s e n t a t i v e s fromMSFC, MSC, KSC, GSFC, and Headquarters a t t e n d e d . H i g h l i g h t s of t h e p r i m a r i l y o r g a n i z a t i o n a l meeting were membership review, s t a t e m e n t of MEP p o l i c i e s , proposed c h a r t e r review and AAP d a t a p l a n s t a t u s . One of t h e f i r s t a r e a s of a c t i v i t y of t h e panel w i l l be i n p o s t - f l i g h t d a t a flow handling. B. F l i g h t E v a l u a t i o n Branch 1. Saturn I B a. AS-205 P o s t f l i g h t T r a j e c t o r y The a c t u a l f l i g h t t r a j e c t o r y of t h e AS-205 v e h i c l e launched on October 11, was v e r y c l o s e t o nominal. The t o t a l spacef i x e d v e l o c i t y a t S-IVB c u t o f f was 0.4 m/s lower than nominal. A t S-IVB c u t o f f , t h e a l t i t u d e and s u r f a c e range were 0.2 km h i g h e r than nominal and 1.1 km g r e a t e r than nominal, r e s p e c t i v e l y . The powered-flight t r a j e c t o r y , based e n t i r e l y on C-band r a d a r t r a c k i n g d a t a , was determined by CCSD a t Michoud. The MSFCdeveloped GATE program w a s t h e method used, and f o r t h e f i r s t time, a f i n a l t r a j e c t o r y was e s t a b l i s h e d w i t h o u t using any h i g h p r e c i s i o n t r a c k ing d a t a . The o r b i t a l t r a j e c t o r y was obtained w i t h t h e OCP program u s i n g C-band r a d a r d a t a from s e v e r a l s t a t i o n s . An e s t i m a t e of t h e v e n t i n g f o r c e s was obtained from t h e telemetered guidance d a t a . The o r b i t a l and powered f l i g h t t r a j e c t o r i e s were c o n s i s t e n t , and were merged t o form a smooth continuous t r a j e c t o r y from guidance r e f e r e n c e r e l e a s e t o S-IVBISC separation. The n a v i g a t i o n update was accomplished w i t h a c c e p t a b l e a c c u r a c y , and t h e LOX s a f i n g experiment was a b o u t a s expected. One a r e a of i n t e r e s t i s t h e more-rapid-than-predicted decay of t h e S-IVB o r b i t . MSC i s i n t e r e s t e d because t h e s p a c e c r a f t had t o make a n unplanned 5 f t / s e c maneuver t o accomplish rendezvous. A t t h i s time, no c o n c r e t e evidence has been found p o i n t i n g t o a cause, b u t t h e i n v e s t i g a t i o n i s c o n t i n u i n g . MSC agreed t o a c c e p t our r e s u l t s on t h e o r b i t a l recons t r u c t i o n and w i l l use t h e MSFC g e n e r a t e d ephemeris up t o S-IVB/SC separation. �b. AS-205 P o s t f l i g h t Guidance Analysis The AS-205 guidance a n a l y s i s was e s s e n t i a l l y completed and g i v e n t o t h e F l i g h t E v a l u a t i o n Working Group (FEWG) as a p a r t of t h e i r r e p o r t . The a n a l y s i s i n d i c a t e s t h a t t h e hardware e r r o r s were v e r y s m a l l and t h a t t h e pos t f 1i g h t e s t a b 1 ished t r a j e c t o r y was good. The n a v i g a t i o n update of t h e s t a t e v e c t o r on AS-205 was s u c c e s s f u l i n t h e s e n s e t h a t t h e update was accepted by t h e system. 2. Saturn V a. AS-503 Abort and A 1 t e r n a t e Miss i o n Ana1ys.i~. The d e l i v e r y s c h e d u l e f o r t h e AS-503C' Abort and A 1 t e r n a t e Mission Document is as follows: Item - Due Date I I1 111 Final Status Received Received Received Expected on on on on time time time time Item I i s t h e m a l f u n c t i o n a n a l y s i s from l i f t o f f t o e a r t h parking o r b i t . Item I1 is t h e m a l f u n c t i o n a n a l y s i s from parking o r b i t t o TLI w i t h t h e s p a c e c r a f t (primary m i s s i o n ) . Item I11 i s t h e a n a l y s i s from parking o r b i t t o TLI w i t h o u t t h e s p a c e c r a f t ( a l t e r n a t e m i s s i o n ) . The f i n a l item w i l l be a summation of t h e t h r e e d e l i v e r i e s i n c o r p o r a t i n g c o r r e c tions - . I n a d d i t i o n t o t h i s AAM document, MSC has been f u r n i s h e d p r e l i m i n a r y i n f o r m a t i o n concerning l i m i t l i n e s f o r v e l o c i t y (V) and p a t h a n g l e (y) p l o t s i n d i c a t i n g c o n d i t i o n s from which e a r l y s t a g i n g t o t h e S-IVB can be accomplished. This r e s u l t s i n burning t h e S-IVB t o d e p l e t i o n t o a c h i e v e a 75 nm minimum o r b i t . An a n a l y s i s has a l s o been performed t o determine when i t i s n e c e s s a r y t o s t a g e t o t h e S-IVB (assuming a previous m a l f u n c t i o n ) t o avoid extended S - I 1 burn such t h a t t h e c h i f r e e z e would p r e v e n t t h e S-IVB from o b t a i n i n g proper end c o n d i t i o n s due t o h i g h a l t i t u d e s . b. been i n i t i a t e d . AS-504 Abort and A l t e r n a t e Mission Analys5s The AS-504 D Abort and A l t e r n a t e Miss i o n Analysis has A l l of t h e GFD requirements have been s a t i s f i e d , and �the p r c l iminary f l i g h t program p r e - s e t t i n g s have been d e r i v e d . Since t h e PLJ s y s t c r n w i l l bc "closcd loop" on t h e S - I 1 s t a g e , a f a i l u r c a n a l y s i s w i l l I>c pcrformcd . c. AS-503 Dynamic A n a l y s i s and Wind Limits The AS-503 D Mission Dynamics Analysis was published t o s e r v e a s a p r e l i m i n a r y AS-504 Dynamics A n a l y s i s . This document i s b e i n g updated f o r t h e C' m i s s i o n . S t a b i l i t y margins w i l l be contained i n a n appendix of t h e updated document i n t h e form of r o o t l o c i of t h e l e a s t s t a b l e v e h i c l e c h a r a c t e r i s t i c r o o t s . R-P&VE-S has i n d i c a t e d t h a t t h e f i n a l AS-503 A-B s t r u c t u r a l l i m i t s a r e n o t expected t o change s i g n i f ic a n t l y . T h e r e f o r e , the e x i s t i n g i n f l i g h t wind l i m i t s a r e not expected t o be updated. d. AS-504 Dynamics Analysis and Wind L i m i t s TBC p l a n s t o b e g i n work on t h e AS-504 Dynamics Analysis Document soon i n o r d e r t o meet t h e i r scheduled d e l i v e r y d a t e of January 20, 1969. However, t h e l i f t o f f and tower c l e a r a n c e s e c t i o n s t u d i e s w i l l be delayed u n t i l t h e s o f t r e l e a s e c o n f i g u r a t i o n , t h e S-IC engine alignment d a t a , and t h e ground winds a r e d e f i n e d . e. AS-503 Emergency D e t e c t i o n System Analysis Documentation of t h e EDS a n a l y s i s f o r t h e C' m i s s i o n i s now a v a i l a b l e . The t h r e e r e p o r t s which c o n s t i t u t e t h i s e f f o r t a r e t h e AS-503 D M i s s i o n Document and t h e two l e t t e r r e p o r t s updating t h e a n a l y s i s t o t h e C' m i s s i o n . As-503 Emergency D e t e c t i o n System and F l i g h t L i m i t s Report should be d i s t r i b u t e d soon. 3. General a. Unified S-Band Tracking Data U t i l i z a t i o n The c a p a b i l i t y t o c o n v e r t Unified S-Band from i t s r e c e i v e d format t o one compatible w i t h o t h e r program requirements has been completed. The AS-502 USB d a t a have been converted and w i l l be used t o check o u t o t h e r decks p r e p a r a t o r y t o t h e AS-503 e v a l u a t i o n . b. Two Body S e p a r a t i o n S i m u l a t i o n Program Nortronics-Northrop has prepared a r e p o r t TR-796-8-395, under Schedule Order 43 documenting a six-degrees-of-freedom s i m u l a t i o n of t h e s e p a r a t i o n of two v e h i c l e s . The program i s w r i t t e n i n D S L / ~ O ,and IBM 7090194 s y s tem language f o r t h e s i m u l a t i o n of continuous sys tem dynamics. The document d i s c u s s e s t h e e q u a t i o n s which a r e programmed, c o n t a i n s a u s e r ' s manual, and i n c l u d e s a program l i s t i n g and flow c h a r t �and a sample problem w i t h the r e s u l t s . This program was w r i t t e n t o s t u d y r e l a t i v e motion between s t a g e s f o r a malfunctioned v e h i c l e such a s a retro-rocket failure. C. Tracking and O r b i t a l A n a l y s i s Branch 1. Saturn I B - AS-205 Real-time s u p p o r t provided t o t h e Mission Operations O f f i c e d u r i n g t h e AS-205 f 1i g h t included making t r a n s f o r m a t i o n s of the MSC v e c t o r s and e s t i m a t i n g t h e S-IVB s t a g e o r b i t a l l i f e t i m e . Based on t h e Antigua v e c t o r a t 18:35 U.T. (end of t h e second r e v o l u t i o n ) , t h e o r b i t a l l i f e t i m e of t h e S-IVB s t a g e was e s t i m a t e d a t 8 . 9 days (nominal p r e d i c t i o n ) and 5.6 t o 12.9 days f o r t h e i20 p r e d i c t i o n s . This compares w i t h 9 , 6.8, and 12.3 days f o r t h e p r e f l i g h t nominal and i 20 p r e d i c t i o n s . The a c t u a l l i f e t i m e was 6 . 8 days. Since t h e p r e d i c t i o n s were n o t a s a c c u r a t e a s p a s t p r e d i c t i o n s , we a r e examining t h e p o s s i b i l i t y of some r e t r o v e l o c i t y being a t t a i n e d a f t e r t h e second r e v o l u t i o n due t o v e n t i n g . We have r e c e i v e d t r a c k i n g d a t a up t o t h e 2 1 s t r e v o l u t i o n and w i l l s o l v e f o r a n o r b i t a l v e c t o r a f t e r a l l v e n t i n g was completed, and t h e s t a g e was i n a random tumble. 2. Saturn V - AS-503 C' V i r t u a l l y a l l of t h e t r a c k i n g and communications coverage a n a l y s i s has been completed on t h e AS-503 C' m i s s i o n f o r b o t h t h e December and January launch o p p o r t u n i t i e s . R e s u l t s have been published i n t h e f o l l o w i n g memoranda: (1) AS-503 C' Mission Launch Vehicle Tracking and Communicat i o n s a n a l y s i s f o r TLI Phase f o r December 21, 1968, R-AERO-FT-40-68, October 1, 1968. (2) AS-503 C' Option 1 Mission Launch Vehicle Tracking and Communications A n a l y s i s f o r December Launch Opportunity, R-AERO-FT-42-68, October 1 5 , 1968. (3) AS-503 C' Option 1 Mission Launch Vehicle Tracking and Communications Analysis f o r December 20-27, 1968, and January 18-24, 1969, Launch Opportunity, R-AERO-FT-44-68, November 8 , 1968. (4) AS-503 C' Launch Vehicle A c q u i s i t i o n and Loss Data f o r Extended E a r t h O r b i t (No S-IVB TLI Burn), R-AERO-FT-45-68, November 12, 1968. �(5) Tracking and Communications Analysis on t h e AS-503 C ' Launch Vehicle O p e r a t i o n a l T r a j e c t o r y B a s i c Mission, R-AERO-FT-46-68, November 20, 1968. - AS-503 C' s h i p a n a l y s i s d a t a and t r a c k i n g and communications d a t a on t h e AS-503 a b o r t and a l t e r n a t e missions were p r e s e n t e d a t the G&P Subpanel meeting a t MSC. 3. AAP a . Look-angle i n f o r m a t i o n on t h e LN/ATM f o r f i v e o r b i t s a t 210 n.mi. a l t i t u d e f o r 28.9" i n c l i n a t i o n r e q u e s t e d by R-ASTR was delivered. b. P r e s e n t a t i o n s on t h e f e a s i b i l i t y of c o n t r o l l e d r e e n t r y of t h e S-IVB s t a g e on AAP-4 and t h e OWS were g i v e n t o t h e Mission Requirements Panel meetings on October 2 4 t h a t MSFC and on November 2 1 s t a t MSC. The p r e s e n t a t i o n on October 2 4 t h was a s t a t u s r e p o r t , and t h e November 2 1 s t p r e s e n t a t i o n was t h e f i n a l r e s u l t s of o u r s t u d i e s . c. A contingency mode of o p e r a t i o n f o r t h e C l u s t e r m i s s i o n was analyzed w i t h r e s p e c t t o o r b i t a l decay and l i f e t i m e . R e s u l t s of t h i s a n a l y s i s a r e documented i n O f f i c e Memorandum R-AERO-FT-47-68, November 20, 1968. d. R e s u l t s of a launch phase t r a c k i n g and communications a n a l y s i s f o r some t y p i c a l AAP S a t u r n I B low a l t i t u d e t r a j e c t o r i e s on v a r i o u s launch azimuths a r e p r e s e n t e d i n O f f i c e Memorandum R-AERO-FT41-68, October 3, 1968. 4. General Arrangements have been made t o comply w i t h a r e q u e s t by t h e C I A i n Washington (made through NASA Headquarters) f o r a copy of our E a r t h O r b i t a l L i f e t i m e Program. D. F l i g h t Mechanics Branch Saturn V a. ., AS-503 C' Mission A l l m i l e s t o n e s were a t t a i n e d f o r the January launch window as p r e v i o u s l y r e p o r t e d f o r t h e December window. S i n c e t h i s w i l l be t h e f i r s t manned f l i g h t of a S a t u r n V launch v e h i c l e and w i l l a l s o e n t a i l a v a r i a b l e launch azimuth w i t h l u n a r t a r g e t i n g , c o n s i d e r a b l e e f f o r t has been expended i n s i m u l a t i o n and v e r i f i c a t i o n procedures. �Guidance p r e s e t t i n g s , d i s p e r s i o n a n a l y s e s , and range s a f e t y d a t a , which have included numerous launch azimuths and engine-out simul a t i o n s , have been f u r n i s h e d a s r e q u i r e d . The f i n a l o p e r a t i o n a l t r a j e c t o r y document combining t h e December and January launch windows w i l l be d i s t r i b u t e d i n e a r l y December. b. AS-504 (D Miss i o n ) A s h i f t from Launch Pad B t o Launch Pad A on t h i s f l i g h t , subsequent t o t h e AS-503 launch, w i l l n o t r e q u i r e a rework of o p e r a t i o n a l t r a j e c t o r y , e t c . , a s long a s t h e i n i t i a l i z a t i o n parameters can be updated i n t h e LVDC. ( A s t r i o n i c s Laboratory i n d i c a t e s t h i s w i l l n o t b e d i f f i c u l t t o accomplish. ) The p r e l i m i n a r y b o o s t t o parking o r b i t o p e r a t i o n a l t r a j e c t o r y and guidance p r e s e t t i n g s have been r e c e i v e d from Boeing. A thorough a n a l y s i s and checking of t h e p r e s e t t i n g s w i l l be made t o avoid format d e f i n i t i o n problems, a s encountered p r e v i o u s l y f o r a v a r i a b l e launch azimuth. The complete o p e r a t i o n a l t r a j e c t o r y document w i l l be d e l i v e r e d i n e a r l y December. A new S - I 1 s t a g e p r o p u l s i o n p r e d i c t i o n w i l l soon be a v a i l a b l e . This new p r e d i c t i o n has a d i f f e r e n t l o a d i n g v a l u e and a n approximate 3-second d i f f e r e n c e i n PU s h i f t time t h a n t h a t p r e s e n t l y being simulated. c. Quick Response T a r g e t i n g Program (QRTP) Conversion of t h e QRTP from t h e Boeing computer system t o t h e UNIVAC 1108 computer system i s now e n t e r i n g t h e d e t a i l e d checkout phase. Data, compiled i n g e n e r a t i o n of t h e l a s t day of January 1969 t a r g e t i n g f o r t h e AS-503 C' m i s s i o n , has been s u p p l i e d f o r use a s a b a s e l i n e f o r comparison. Miles tones of deck c o m p i l a t i o n , e x e c u t i o n , and ephemeris t a p e i n t e r r o g a t i o n have been a t t a i n e d . Once t h i s program becomes o p e r a t i o n a l , i t may permit us (in-house) t o reduce t h e impact of s u p p o r t i n g t h e numerous launch days c u r r e n t l y r e q u i r e d f o r C' and F type miss i o n s . d. I n f l i g h t T r a j e c t o r y Support The c a p a b i l i t y t o a s s e s s the S a t u r n S-IVB 2nd burn performance margin i n r e a l time i s n e a r i n g completion. The computer program i s b a s i c a l l y t h e Marves-SPED 6D o p e r a t i o n a l t r a j e c t o r y program. Modificat i o n s t o permit i n p u t of I U and t r a c k i n g s t a t e v e c t o r s , a s w e l l a s t h e r e f o r m a t t e d t a r g e t i n g and r e i g n i t i o n e q u a t i o n s , have been implemented. The program, however, h a s , n o t y e t been converted from t h e IBM 7094 t o t h e UNIVAC 1108 computer system. While t h i s conversion i s n o t mandatory f o r t h e AS-503 C' m i s s i o n , removal of t h e 7094 computers j u s t a f t e r t h e m i s s i o n i s flown w i l l n e c e s s i t a t e t h e s e conversions i f any in-house o p e r a t i o n a l t r a j e c t o r y c a p a b i l i t y i s t o be maintained. �I n t e r n a l s i m u l a t i o n s of t h e r e a l - t i m e s u p p o r t a c t i v i t i e s were perEormed i n c o n j u n c t i o n w i t h HOSC/MCCHo p e r a t i o n s on 22 November and 3 December i n o r d e r t o confirm t i m e l i n e s . The f i r s t s u c c e s s f u l runs were made on t h e 3 December s i m u l a t i o n . This program i s now being completely checked o u t . It i s f e l t t h a t v i r t u a l d u p l i c a t i o n of previous o p e r a t i o n a l t r a j e c t o r y d a t a i s r e q u i r e d b e f o r e confidence i n a go/no-go d e c i s i o n can be e s t a b l i s h e d . Although t h i s r e q u i r e s c o n s i d e r a b l e e f f o r t , no s i g n i f i c a n t problems a r e a n t i c i p a t e d . This has been a coordinated e f f o r t between members of R-AERO-FF, R-AERO-FM, Computer Sciences Corporation, and Northrop Space Laboratories . e. Document Schedules A meeting was h e l d on October 29 w i t h R-P&VE-PPE t o e s t a b l i s h p r o p u l s i o n requirements f o r AS-505 and AS-506. It was agreed t h a t t h e p r e d i c t i o n s would b e f i n a l . The f o l l o w i n g s c h e d u l e was o u t l i n e d : AS-505 nominal p r e d i c t i o n on Nov. 25, 1968 mass d a t a 2-3 days l a t e r . - AS-505 d i s p e r s i o n p r e d i c t i o n on Dec. 2, 1968 mass d a t a 5 days l a t e r . AS-505 engine o u t p r e d i c t i o n on Dec. 9 , 1968 mass d a t a 5 days l a t e r . AS-506 nominal p r e d i c t i o n on Dec. 23, 1968 mass d a t a 2-3 days l a t e r . - - AS-506 d i s p e r s i o n p r e d i c t i o n on J a n . 23, 1969 mass d a t a 5 days l a t e r . - AS-506 engine o u t p r e d i c t i o n on Jan. 30, 1969 mass d a t a 5 days l a t e r . - It was agreed t o r e - s c h e d u l e t h e p r e l i m i n a r y p r o p u l s i o n d a t a f o r AS-507 f o r February 26, 1969 ( i . e . , nominal and d i s p e r s i o n ) and engine-out d a t a f o r March 1 2 , 1969. Based upon t h e above d a t a d e l i v e r y , t h e following document d e l i v e r y s c h e d u l e was d e r i v e d : �D e l i v e r y Date Document AS-505 AS-506 I n i t i a l Operational Trajectory 2-4-69 3-27-69 EPO and Guidance P r e s e t t i n g s 1-2-69 2-7-69 Dispersion Analysis 2-26-69 4-22-69 The F i n a l O p e r a t i o n a l T r a j e c t o r y documents have been d e l e t e d . BIBLIOGRAPHY 1. "Research Achievements Review, Vol. 111, Report No. 2," NASA TM X-53777, October 1968. 2. Smith, R. E. and D. K. Weidner, e d . , "Space Environment C r i t e r i a G u i d e l i n e s f o r Use i n Space Vehicle Development (1968 ~ e v i s i o n ) , " NASA TM X-53798, October 31, 1968. 3. S p e r l i n g , Hans J . , "On t h e Real S i n g u l a r i t i e s of t h e N-Body Problem IN-AERO-68-6, October 1 5 , 1968. " �APPROVAL rodynamics Laboratory E. D. G e i s s l e r D i r e c t o r , Aero-Astrodynamics Laboratory DISTRIBUTION .R-AERO-DIR Dr. G e i s s l e r M r . Jean Mr. B u t l e r R-DIR, M r . W e i d n e r MS-H, M i s s J e r r e l l (3) I-V-P, R-AERO-R Mr. B e a n ( 4 ) Mrs. Hightower R- AERO- T Mr. M u r p h r e e Mr. Cummings Dr. Heybey Mr. J a n d e b e u r Dr. K r a u s e Mr. N a t h a n Mr. Few M r . von P u t t k a m e r R-AERO-P R-AERO-D R-AERO-A R-AERO-G R-AERO-Y R-AERO-F R-AERO-X (8) (16) (16 ) (6) (8) (8) (4) PAO, M r . K u r t z Mr. P r i c e � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000046 Title A name given to the resource "Aero-Astrodynamics Laboratory Bimonthly Progress Report: October - November 1968." Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center Date A point or period of time associated with an event in the lifecycle of the resource 1968-12-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) NASA space programs Project management Type The nature or genre of the resource Progress reports Text Source A related resource from which the described resource is derived Saturn V Collection Box 29, Folder 27 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050 https://digitalprojects.uah.edu/files/original/20/994/spc_stnv_000047.pdf fb2797b8681dcb2476235d9b3b076a6c PDF Text Text AERO-AS TRODYNAMICS LABORATORY MONTHLY PROGRESS REPORT October 11. 1966 INDEX Page ......................... ENGINEERING STAFF ...................................... PROJECTS OFFICE ........................................ AERODYNAMICS DIVISION .................................. A. Mechanical Design O f f i c e ........................... B . F a c i l i t i e s Branch .................................. C . V e h i c l e D e s i g n Branch .............................. D . Thermal Environment Branch ......................... E . Unsteady Aerodynamics Branch ....................... AEROSPACE ENVIRONMENT DIVISION ......................... ASTRODYNAMICS AND GUIDANCE TmORY DIVISION ............. A . O f f i c e o f t h e C h i e f ................................ B. Astrodynamics Branch ............................... C . Guidance Theory Branch ............................. D . O p t i m i z a t i o n Theory Branch ......................... V I I . DYNAMICS AND FLIGHT MECHANICS DIVISION ................. A . M u l t i - P r o j e c t s ..................................... B . S a t u r n V ........................................... C . S a t u r n IB .......................................... D . U P ................................................ E . G e n e r a l ............................................ V I I I . FLIGHT TEST ANALYSIS DIVISION .......................... A . S p e c i a l P r o j e c t s O f f i c e ............................ B . F l i g h t E v a l u a t i o n Branch ........................... C . F l i g h t Mechanics Branch ............................ D . T r a c k i n g and O r b i t a l A n a l y s i s Branch ............... ADVANCED STUDIES OFFICE ................................ A. F l i g h t Nechanics and Performance Anal y s i s Group .... B . Systems A n a l y s i s Group ............................. C . As modynamics and M i s s i o n A n a l y s i s Group ........... TECHNICAL AND SCIENTIFIC STAFF �AERO-ASTRODYNAMICS LABORATORY MONTHLY PROGRESS REPORT October. 11, 1966 I. TECHNICAL AND SCIENTIFIC STAFF 1. Advanced Launch Vehicle T r a j e c t o r y Research (Northrop C o n t r a c t S.O. 1 5 ) a. HTO A i r b r e a t h e r Model Work i s p r o g r e s s i n g on t h e computer model of a i r b r e a t h i n g ( l i f t i n g ) launch v e h i c l e s . The ground r u n , l i f t o f f and minimum-fuelp u l l - u p phases of t h e f l i g h t have been programmed. T r i a l runs of t h i s p o r t i o n of t h e program showed t h e d e s i r a b i l i t y of two a d d i t i o n a l cont r o l modes d u r i n g t h e p u l l - u p . These modes, which a l l o w a quick l i f t o f f and a n e a r l y l e v e l f l i g h t d u r i n g sound b a r r i e r p e n e t r a t i o n , have been i n c o r p o r a t e d i n t o t h e program. I n a d d i t i o n , a n i t e r a t i v e loop t o cont r o l t h e v a l u e of t h e d e r i v a t i v e of v e l o c i t y w i t h r e s p e c t t o a l t i t u d e a t t h e end of t h e p u l l - u p phase has been programmed and checked o u t . b. HTO/VTO Rocket Models Both the HTO-only and t h e VTO-only decks were checked o u t and found o p e r a t i o n a l . Northrop i s modifying t h e VTO-only deck f o r s i m u l a t i o n of a 4 - s t a g e a s c e n t i n t h e Mars atmosphere, i n s u p p o r t of a n o t h e r Schedule Order. (von Puttkamer) 2. Advanced Systems and Mission S t u d i e s a. S3 L a r - E l e c t r i c P r o p u l s i o n Miss ions Aero-As trodynamics Laboratory i s s u p p o r t i n g Research P r o j e c t s Laboratory i n s t u d i e s concerned w i t h miss ions i n v o l v i n g s o l a r e l e c t r i c propulsion. I n an i n i t i a l "kick-off" meeting between M r . von Pdttkamer f o r AERO and D r . S t u h l i n g e r , D r . S h e l t o n , D r . Hale, M r . Wood and M r . D a i l e y f o r RP, t h e g o a l s and t h e modus o p e r a n d i of t h e mutual e f f o r t s were e s t a b l i s h e d . It was decided t o undertake t h e i n v e s t i g a t i o n of a photographic Mars m i s s i o n w i t h s o l a r - e l e c t r i c p r o p u l s i o n , involving a n unmanned P e g a s u s - l i k e s p a c e c r a f t and sun-synchronous o r b i t s around Mars w i t h s h i f t i n g a l t i t u d e s . Subsequent meetings between RP and AERO personnel on September 1 5 t h and 23rd served t o e s t a b l i s h t h e program p l a n . AERO's c o n t r i b u t i o n w i l l be i n t r a j e c t o r y computation, m i s s i o n o p t i m i z a t i o n , �c o n t r o l and g u i d a n c e , o r b i t a l mechanics, and r i g i d body dynamics, t o b e performed by AERO-G and AERO-X, w i t h t h e l a t t e r b e i n g s u p p o r t e d by Nor t h r o p . Two-dimensional a n a l y s e s and p r e p a r a t i o n s f o r more s o p h i s t i c a t e d t h r e e - d i m e n s i o n a l t r a j e c t o r y s t u d i e s a r e underway. A f i r s t r e p o r t o f p r e l i m i n a r y r e s u l t s i s s c h e d u l e d f o r e a r l y November. P a r t i c i p a t i n g AERO p e r s o n n e l i n c l u d e A. Schwaniger, Causey, R. Duncan, B. L i s l e , AERO c o n t a c t Galloway, H. Ingram of AERO-G and A r c h i e Young o f AERO-X. i s J. v. Puttkamer . b. J u p i t e r Flyby Missions C o n t a c t h a s b e e n e s t a b l i s h e d w i t h p e r s o n n e l of GDIForth Worth i n c o n n e c t i o n w i t h i n t e r p l a n e t a r y p r o b e s t u d i e s . A GD/FW team u n d e r D r . L. E. Hove h a s conducted a n e x t e n s i v e s t u d y o f J u p i t e r f l y b y m i s s i o n s i n v o l v i n g S a t u r n l a u n c h v e h i c l e s f o r JPL. A p r e s e n t a t i o n t o AERO p e r s o n n e l on October 11 of p e r t i n e n t r e s u l t s and r e l a t e d e f f o r t s i n t h e Advanced P l a n e t a r y Probe s e c t o r i s being prepared. c. L i f t i n g Body AAP Experiment N o r t h r o p has s u b m i t t e d a p r o p o s a l o f a l i f t i n g body r e e n t r y e x p e r i m e n t as a p o s s i b l e advanced S a t u r n I AAP m i s s i o n t o M a r s h a l l . 10's S a t u r n / A p o l l o A p p l i c a t i o n s O f f i c e i s e v a l u a t i n g t h e p r o p o s a l and h a s a s k e d AERO f o r i n p u t s . The p r o p o s a l h a s b e e n e v a l u a t e d and M r . J a c k Waite of t h e S/AAP O f f i c e was informed o f AERO'S p o s i t i o n on October 4. In general, as a l a r g e - s c a l e t e s t o f aerodynamics of LID = 1 . 0 b o d i e s i n s u p p o r t o f Langley/Ames a e r o n a u t i c a l work, t h e LBV e x p e r i m e n t a p p e a r s d e f i n i t e l y d e s i r a b l e , i t b e i n g a l s o backed by r e c e n t r e s u l t s o f MSFC's RAPT s t u d y . On t h e o t h e r hand, t e c h n i c a l 1 y and f i n a n c i a l l y , t h e e x p e r i m e n t would have some s h o r t c o m i n g s , and t h a t , p o l i t i c a l l y , t h e r e would b e n o t h i n g i n i t f o r AERO ( b e s i d e s p a s s i v e w a t c h i n g ) and l i t t l e f o r MSFC. d. T e c h n i c a l Review o f H y p e r s o n i c A i r c r a f t Technology Aero-As trodynamics L a b o r a t o r y was r e p r e s e n t e d a t t h e 1966 t e c h n i c a l r e v i e w m e e t i n g of t h e NASAIUSAF Ad Hoc Working Group f o r H y p e r s o n i c A i r c r a f t Technology, o r g a n i z e d by NASA a t t h e Langley R e s e a r c h C e n t e r on September 21 and 22. �The o b j e c t i v e of t h e conference was t o d i s c u s s t h e key problems, t h e r e c e n t accomplishments and t h e f u t u r e plans i n t h e a r e a of h y p e r s o n i c f l i g h t r e s e a r c h . S p e c i f i c a l l y , progress made i n t h e f i e l d s i n c e t h e 1964165 r e p o r t of t h e USAF Ad Hoc Task Force on SCRAMJET was t o be p r e s e n t e d . I n 28 t e c h n i c a l p a p e r s , r e p r e s e n t a t i v e s of A i r Force and NASA a t t e m p t e d t o p r e s e n t a d e t a i l e d survey of t h e c u r r e n t s t a t e - o f - t h e a r t of p r o p u l s i o n , aerodynamics, s t r u c t u r e s , and a p p l i c a t i o n s t u d i e s of h y p e r s o n i c a i r c r a f t . It i s f e l t t h a t t h e meeting, under t h e chairmans h i p of John V. Becker (Langley) and Robert E . Supp (AF-APL, USAF) was h i g h l y s u c c e s s f u l i n i t s b a s i c o b j e c t i v e of e s t a b l i s h i n g a new m i l e s t o n e i n h y p e r s o n i c technology development. A detailed t r i p r e p o r t ( c l a s s i f i e d Confidential) i s a v a i l a b l e from J. v . Puttkamer on r e q u e s t . e. AIAA Aerodynamic D e c e l e r a t i o n Sys tems Conference, September 7-9, Houston, Texas Besides some papers p e r t a i n i n g t o b o o s t e r r e c o v e r y , a p r e s e n t a t i o n on e a r t h - b a s e d t e s t i n g of Voyager/Mars parachutes was of interest. I n t h i s paper, J. C. McFall and H. N. Murrow of NASA-Langley r e p o r t e d on t h e NASA P l a n e t a r y Entry Parachute (PEP) Program which uses r o c k e t s and b a l l o o n s t o conduct r e c o v e r y of Voyager-like payloads under deployment c o n d i t i o n s envisioned f o r Mars e n t r y , i. e . , h i g h Mach numbers (M r 1 . 2 ) and low d e n s i t i e s ( e a r t h a l t i t u d e s between 30 and 90 km). "Quick look" d a t a of the f i r s t t e s t (of s i x planned), s u c c e s s f u l l y conducted on August 30 a t Walker AFB, were p r e s e n t e d . The 1600 l b Voyager c a p s u l e was launched i n a n upward d i r e c t i o n by 12 s o l i d r o c k e t s from a ( r e c o r d - s i z e ) 2 6 - m i l l i o n - c u - f t b a l l o o n f l o a t i n g a t 39 km a l t i t u d e . A t M a c h l . 2 , a n 8 4 - f o o t r i n g s a i l parachute was deployed and t h e c o n i c a l aero-shell jettisoned. The recovered payload of 200 l b s (plus 325 l b s b a l l a s t ) included s u c c e s s f u l l y o p e r a t i n g onboard cameras. (von Puttkamer) 3. Five magnetic t a p e s c o n t a i n i n g analog d a t a from 90 experimental r u n s made by D r . F i s c h e r , I I T , have been r e c e i v e d . D e t a i l e d computer i n p u t parameters and o p e r a t i n g i n s t r u c t i o n s , t o g e t h e r w i t h t h e analogt o - d i g i t a l c o n v e r s i o n requirements have been agreed upon and provided t o R-COMP by our Northrop Mission Support personnel w i t h a r e q u e s t t o process through t h e new piecewise c o r r e l a t i o n program P a r t I. Very l i t t l e p r o g r e s s has been made on t h e r e q u i r e d computational d a t a process i n g of t h e s e 90 runs because of a change i n personnel and because of i n t e r f e r e n c e of o t h e r heavy workload demands on R-COME'. The e v e n t u a l e f f e c t of t h e s e d e l a y s on D r . F i s c h e r ' s c o n t r a c t has n o t been determined as yet. �The t e s t c a s e s which were m u t u a l l y agreed upon by I I T , Northrop, R-COMP-PRV, R-AERO-AM, and R-AERO-T a s n e c e s s a r y and s u f f i c i e n t t o e x p e r i m e n t a l l y determine t h e accuracy, e f f i c i e n c y , and l i m i t a t i o n s of a p p l i c a b i l i t y of t h e c o n c e p t s , approximations and assumptions contained i n t h e computer program p r e v i o u s l y prepared by R-COMP-PRV and R-AERO-AM f o r p i e c e w i s e e s t i m a t i o n of c o r r e l a t i o n f u n c t i o n s , P a r t I, have been o n l y p a r t i a l l y completed. R e s u l t s of t h e remaining r e q u e s t e d runs a r e being awaited s i n c e t h e y a r e needed t o f i n i s h t h e e v a l u a t i o n and t o document t h e s e new techniques and t h e i r r e l a t i v e performance a s compared t o more c o n v e n t i o n a l t e c h n i q u e s . Considerable p r o g r e s s was made t h i s month i n a t t e m p t s t o unders t a n d t h e a p p a r e n t b u t s u r p r i s i n g l y inadequate performance of t h e numerical i a t e g r a t i o n technique t h a t had o r i g i n a l l y been a p p l ied t o t h e computation of t h e band-averaged s p e c t r a l d e n s i t y of t h e random processes a s s o c i a t e d w i t h t h e crossed-beam experiments. I n a n e f f o r t t o p r e v e n t scrapping more of t h e s i g n i f i c a n t o r i g i n a l c o n t r i b u t i o n s t o t h i s sens i t i v e and c o m p u t a t i o n a l l y d i f f i c u l t problem, some f u r t h e r e f f o r t w i l l be expended in this pursuit. The g e o m e t r i c c o n s i d e r a t i o n s a s r e p o r t e d l a s t month a r e cont i n u i n g b u t w i t h a lower p r i o r i t y t h a n t h e above work. (Cumings) 11. ENGINEERING STAFF ODYSSEY I (Multisphere S a t e l l i t e Experiment): The f i r s t p r o j e c t d e f i n i t i o n s t u d y meeting was h e l d on September 8 , 1966. A l l p a r t i c i p a t i n g l a b o r a t o r i e s have submitted a Phase "B" s t u d y p l a n except R-P&VE. Their p l a n i s expected by October 14, 1966. The requirement f o r a u x i l i a r y prop u l s i o n i s e s s e n t i a l l y a c e r t a i n t y t o modify e x i s t i n g f l i g h t o r b i t s t o an a c c e p t a b l e experiment o r b i t . R-AERO-F i s w e l l underway i n d e f i n i n g a c c e p t a b l e ensemble o r b i t s w i t h r e s p e c t t o s p h e r e s e p a r a t i o n and l i f e t i m e , which a r e t h e parameters t h a t p r i m a r i l y c o n t r o l t h e experimental d a t a . 111. PROJECTS OFFICE 1. Incentive Contract - TBC S%IS Formal n e g o t i a t i o n s on Task 8.0, " F l i g h t Systems Analysis ," were begun September 15, 1966. An agreement was reached between MSFC and TBC t o a c c e p t t h e &DO i n c e n t i v e document l i s t i n g and i n c e n t i v e p o i n t d i s t r i b u t i o n . Most of t h e c o n t r a c t wording r e l a t i n g t o t h e implementation of Task 8.0 has been agreed upon. However, a t t h e p r e s e n t time, n e g o t i a t i o n s a r e deadlocked on t h e schedule i n c e n t i v e f o r t h e R&DO i n c e n t i v e document l i s t i n g . Every e f f o r t i s being made t o develop a n e g o t i a b l e plan. �2. S a t u r n I B L o g i s t i c s Vehicle Study This s t u d y has e s s e n t i a l l y been d i s c o n t i n u e d because (1) the a c t u a l hardware c o s t r e p r e s e n t s o n l y a s m a l l p o r t i o n of t h e t o t a l program c o s t , (2) e l i m i n a t i o n of t h e p r e s e n t I U hardware and u s i n g a n a u t o p i l o t system would reduce t h e c a p a b i l i t y of t h e S a t u r n I B t o a l e v e l n o t comp e t i t i v e w i t h o t h e r launch v e h i c l e systems, and (3) a l i m i t e d c o s t r e d u c t i o n was p o s s i b l e , a l t h o u g h t h i s r e d u c t i o n would i n t h e long run p e n a l i z e t h e S a t u r n I B launch v e h i c l e program. 3. CCSD Performance I n c e n t i v e f o r SA-203 The a c t u a l end cond i t i o n s of f l i g h t (s-IB/ S-IVB s e p a r a t i o n s i g n a l ) achieved d u r i n g t h e S-IB-3 f l i g h t d e v i a t e d from t h e published nominal v a l u e s a s f o l l o w s : V e l o c i t y (m/sec) Actual D e v i a t i o n 23.5 Allowed D e v i a t i o n t32.1 F l i g h t P a t h Angle (deg) Range (km) A l t i t u d e (km) Cross Range (km) A l l parameters e x c e p t t h e a l t i t u d e were w i t h i n t h e t o l e r a n c e s agreed t o b e f o r e f l i g h t . There were two primary causes of t h e d e v i a t i o n s of t h e S-IB-3 f l i g h t . The f i r s t was a n a l t i t u d e e f f e c t on t h e i n d i v i d u a l engine performance which was n o t obtained from t h e engine o r s t a g e a c c e p t a n c e f i r i n g t e s t s . The second cause, which was a l s o a d d i t i v e t o t h e f i r s t , was a n a d d i t i o n a l i n c r e a s e i n performance caused by a n a p p a r e n t i n f l u e n c e of t h e s t a g e on t h e c l u s t e r e d engine t h r u s t . The performance i n c e n t i v e of t h e S-IB s t a g e c o n t r a c t s t i p u l a t e s that t h e government and the c o n t r a c t o r w i l l a g r e e b e f o r e f l i g h t on t h e a c c e p t a b l e t o l e r a n c e s a b o u t t h e nominal t r a j e c t o r y . I f any of t h e s e parameters a r e o u t of t o l e r a n c e , t h e c o n t r a c t o r cannot a c h i e v e f u l l i n c e n t i v e bonus. However, a f t e r i n v e s t i g a t i n g t h e problem, i t t u r n s o u t t h a t t h e i n p u t d a t a s p e c i f i e d by MSFC were i n e r r o r . Based on t h e i n p u t d a t a f u r n i s h e d t o CCSD, i t appears t h a t t h e t r a j e c t o r y d a t a s u p p l i e d by CCSD were c o r r e c t . T h e r e f o r e , i t was recommended t h a t CCSD n o t be p e n a l i z e d , i n t h i s p a r t i c u l a r c a s e , f o r being o u t of t o l e r a n c e i n a l t i tude. �IV. AERODYNAMICS DIVISION A. Mechanical Design Off i c e 1. R-ME f a b r i c a t i o n s u p p o r t has been d r a s t i c a l l y reduced during t h i s r e p o r t i n g period. I n s u f f i c i e n t funds has f o r a l l p r a c t i c a l purposes e l i m i n a t e d t h e u s e of R-ME'S s i n g l e s u p p o r t c o n t r a c t o r , Hayes I n t e r n a t i o n a l (and s u b s e q u e n t l y M i c r o c r a f t , A s t r o Space, e t c . ) , except f o r t h e f a b r i c a t i o n of approved S a t u r n I B and S a t u r n V mainstream programs. This l e a v e s R-ME'S in-house shops and t h e A.E.C. shops a t Oak Ridge, Tennessee, a s our o n l y r e 1 i a b l e f a b r i c a t i o n s o u r c e s . A 1 though n e g o t i a t i o n s a r e underway i n a n a t t e m p t t o o b t a i n a d d i t i o n a l funds f o r R-ME'S s i n g l e s u p p o r t c o n t r a c t o r , t h e s h o r t a g e of f a b r i c a t i o n c a p a b i l i t y should be considered i n t h e planning of f u t u r e p r o j e c t s . 2. F a b r i c a t i o n of a l l items f o r t h e base flow t e s t c e l l , model and s u r v e y assembly f o r Tunnel "E", V.K.F. AEDC, i s complete and t h e s u r v e y assembly i s being checked o u t . Shipment t o AEDC w i l l be made d u r i n g t h e f i r s t week i n October. 3 . The probe c a r t assembly and survey r a k e s f o r t h e cold flow d u c t have been d e l i v e r e d . These a r e t h e f i n a l mechanical components r e q u i r e d f o r cold flow cross-beam c o r r e l a t i o n t e s t i n g . 4. The f l a t p l a t e model assembly i s undergoing f u n c t i o n a l checkout a t t h e f a b r i c a t i o n s i t e a t A.E.C. (Oak Ridge, Tenn.) b e f o r e shipment t o Ames f o r t e s t i n g . 5 . The f o l l o w i n g i s a l i s t of a d d i t i o n a l p r o j e c t s and t h e i r current status : Status Description Viscous Cross Flow Force Model and Balance - 14" W.T. Fabrication Updated S a t u r n V Force Model- 14" W.T. F i n and Asymmetric Body and Balances - 14" W.T. Sidewall-Mounted I n n e r s t a g e Ring Model and 14" W.T. Balance Updated S a t u r n TB Tank Balance - 14" W.T. Drafting Loads Force Model and Design Design Design Balance Cal i b r a t i o n Stand Design 8' O.D. Drafting Vacuum Exhaust Plenum M o d i f i c a t i o n of Nozzle f o r S.T.S. - 14" W.T. Fabrication �5. (Continued) Description Status P e r f o r a t e d F l o o r and C e i l i n g Assembly, T.T.S. 14" W. T. P l e x i g l a s s Models f o r Cross Bean i n S.T.S. 14" W.T. - P r e s s u r e Models f o r Cross Beam i n S.T.S. S a t u r n I B Thin Skin Heat T r a n s f e r Model - - Fabrication - Fabrication 14" W.T. Fabrication JPL Design Base Heating Model f o r IBFF Drafting High Reynolds No. F a c i l i t y Development Design B. F a c i l i t i e s Branch 1. Impulse Base Flow F a c i l i t y A l l systems a s s o c i a t e d w i t h t h e m o d i f i c a t i o n t o extend t h e p r e s s u r e and vacuum c a p a b i l i t i e s of t h e f a c i l i t y have been checked o u t . The North American A v i a t i o n , Dual Plane S e p a r a t i o n T e s t f o r R-AERO-AT has begun w i t h some f i f t y runs being completed. R e s u l t s from t h e cold flow phase (using N 2 g a s ) of t h e above t e s t a r e i n r e a s o n a b l e agreement w i t h d a t a obtained a t t h e Langley Research C e n t e r . The l i m i t e d d a t a obtained thus f a r from t h e *how flow phase, u s i n g HZ and O2 combustion, a r e i n good agreement w i t h cold flow d a t a when t h e i n t e r s t a g e i s 120 inches o r more a f t of t h e s e p a r a t i o n p o i n t ; however, d a t a obtained t h u s f a r w i t h t h e i n t e r s t a g e between t h e s e p a r a t i o n p o i n t and 120 inches a f t i n d i c a t e a s i g n i f i c a n t i n c r e a s e i n l o a d s . S i n c e o n l y a v e r y few runs have been made, no conclusions can be drawn u n t i l f u r t h e r d a t a a r e a v a i l a b l e . P r e s e n t plans c a l l f o r a t e s t program t o i n v e s t i g a t e p o s s i b l e dimensional s c a l i n g e f f e c t s on t h e s t a r t i n g time of a h i g h Reynolds Number f a c i l i t y a t t h e c o n c l u s i o n of t h e c u r r e n t t e s t . 2. Hot and Cold Flow T e s t F a c i l i t i e s T e s t s a r e pending f o r b o t h t h e Cold Flow F a c i l i t y and t h e Hot Flow T e s t F a c i l i t y . Based on t h e r e l a t i v e p r i o r i t i e s , t h e a v a i l a b l e manpower has been s h i f t e d t o o t h e r t e s t a r e a s . The shadowgraph s t u d i e s of Mach wave r a d i a t i o n a s a n o i s e s o u r c e i n j e t exhausts should be �resumed d u r i n g October. The nozzle plume s t u d y i s dependent on i n s t r u m e n t a t i o n c u r r e n t l y being used on o t h e r t e s t s . It i s expected t h a t equipment and manpower demands w i l l s l a c k e n during October, and t h e s e t e s t s can be completed. 3. 7 x 7-Inch Bis o n i c Wind Tunnel The i n v e s t i g a t i o n by R-AERO-AT i n t o t h e use of l a s e r s i n measuring gas v e l o c i t i e s i s c o n t i n u i n g . 4. Thermal-Acoustic J e t F a c i l i t y The cold flow d u c t i s undergoing c a l i b r a t i o n t e s t s i n p r e p a r a t i o n f o r t h e cross-beam c o r r e l a t o r s t u d i e s t o be r u n i n October. The i n s t r u m e n t a t i o n c a r t was d e l i v e r e d d u r i n g September and i s ready f o r use. The s c h l i e r e n assembly i s being s t r u c t u r a l l y modified b e f o r e a n October i n s t a l l a t i o n . Because of t h e extremely h i g h n o i s e l e v e l s (150 db and l e s s ) a s s o c i a t e d w i t h t h e f a c i l i t y , sound l e v e l surveys have been t a k e n and p r e c a u t i o n s taken t o avoid a c c i d e n t a l exposure. The helium h e a t e r d e l i v e r y was p r e v i o u s l y scheduled f o r d i d - 0 c t o b e r b u t a n unexpected mechanical f a i l u r e d u r i n g assembly has delayed d e l i v e r y f o r a n a d d i t i o n a l 30 days. 5. 1 4 x 14-Inch T r i s o n i c Wind Tunnel The f o l l o w i n g t e s t s were conducted during September 1966: ( a ) An i n v e s t i g a t i o n t o determine t h e aerodynamics of s trap-on b o o s t e r u n i t s and t h e i r i n f l u e n c e on t h e c h a r a c t e r i s t i c s of t h e 70-inch diameter b o o s t e r tanks of t h e proposed uprated S a t u r n I B configurations. T o t a l runs: 190. (b) An i n v e s t i g a t i o n t o determine s t a t i c s t a b i l i t y charact e r i s t i c s of t h e proposed u p r a t e d S a t u r n I B c o n f i g u r a t i o n s based on t h e u t i l i z a t i o n of s o l i d p r o p e l l a n t s t r a p - o n s . T o t a l runs: 244. The t u n n e l i s h e a v i l y scheduled f o r t h e remainder of t h e c a l e n d a r y e a r . 6. Low Density Chamber Experiments have continued i n c a l i b r a t i n g t h e Mach 4 low d e n s i t y nozzle, Impact p r e s s u r e measurements a c r o s s t h e nozzle e x i t have shown a n i s e n t r o p i c c o r e diameter i n t h e range of 2 inches t o 15 i n c h e s w i t h s t a g n a t i o n p r e s s u r e of 30 microns of mercury t o 400 microns of mercury, r e s p e c t i v e l y . A Mach number of 3.865 has been c a l c u l a t e d from t h e impact t o s t a t i c p r e s s u r e r a t i o s . �Thc molecular beam equipment has been checked o u t , and t h e f i r s t s e r i e s of experiments f o r determining t h e c a p t u r e c o e f f i c i e n t of C02 on l i q u i d n i t r o g e n cooled s u r f a c e s has begun. Work has continued on t h e t i t a n i u m pumping experiment f o l l o w i n g a b r i e f pause f o r s e t t i n g up and c a l i b r a t i n g t h e c r y s t a l microb a l a n c e d e t e c t o r system. This s t u d y i s t o determine t h e c a p t u r e coeff i c i e n t s of hydrogen on titanium-coated c r y o s u r f a c e s . R e s u l t s from t h i s i n v e s t i g a t i o n w i l l be used t o determine i f s u c h a technique would b e p r a c t i c a l i n extending t h e r u n time of t h e IBFF by flow a b s o r p t i o n . 7. Heat T r a n s f e r Measurements I n checking t h e c a l i b r a t i o n of t h e 1000°F h e a t t r a n s f e r gages, i t was found t h a t t h e r e i s a s h i f t i n i n i t i a l r e s i s t a n c e and dR/dT of t h e gage a f t e r each h e a t c y c l e . A f i x has been made t o t h e gage d e s i g n , and a d d i t i d n a l gages a r e being f a b r i c a t e d . 1 I The perforrpance of newer type gages, such a s t h e t h i n - d i s c , t y p e , i s b e i n g e v a l u a t e d i n t h e IBFF using t h e NAA Dual Plane Separat i o n model. 8. Data Reduction Three f o r c e b a l a n c e s (14 c h a n n e l s ) and a s many a s s i x b a s e p r e s s u r e s were used i n t h e t e s t i n g of t h e uprated S a t u r n I B i n t h e t r i s o n i c t u n n e l . Two d a t a s y s tems were used, r e q u i r i n g e x t e n s i v e modif ic a t i o n s t o t h e d a t a r e d u c t i o n program t o accommodate t h e s e channels. The program t o reduce t h e low d e n s i t y chamber n o z z l e c a l i b r a t i o n d a t a has been checked o u t and i s o p e r a t i o n a l . Four f l u c t u a t i n g p r e s s u r e t r a n s d u c e r s were l o c a t e d on t h e u p r a t e d S a t u r n I B mode1 t o g i v e "quick-look" e s t i m a t e s of t h e e f f e c t s Limited analog r e d u c t i o n of t h e d a t a was done by of t h e s t r a p - o n s . Chrys l e r and R-AERO-AF personnel us ing our equipment. The program t o reduce t h e c a l i b r a t i o n d a t a from t h e cold flow d u c t was w r i t t e n and p a r t i a l l y debugged i n September. 9. P r e s s u r e Measurements The ~ y t r e x ' ~ r e s s u rt rea n s d u c e r s which a r e o f t e n used f o r unsteady and f l u c t u a t i n g p r e s s u r e measurements a r e expensive ($400 e a . ) 100 p e r c e n t l o s s i s i n c u r r e d i n any t e s t . and f r a g i l e . U s u a l l y a 50 S i m i l a r items from o t h e r s o u r c e s a r e being e v a l u a t e d a s a cheaper and more rugged replacement. - �10. I S a t u r n V 4 P e r c e n t A c o u s t i c Model The 4 p e r c e n t S a t u r n model and i n s t r u m e n t a t i o n a r e being checked o u t f o r t h e second phase of t e s t i n g a t AEDC i n December. A l l 180 e l e c t r i c a l connectors have been r e i n s t a l l e d on t h e model's w i r i n g , and i n s t r u m e n t a t i o n equipment r e p r e s e n t a t i v e s have r e p a i r e d equipment t h a t f a i l e d d u r i n g Phase I. A p r e l i m i n a r y s e t of c a l i b r a t i o n c o n s t a n t s f o r t h e recorded d a t a has b e e n computed and submitted along w i t h s e v e r a l r e e l s of recorded F i n a l t a b u l a t i o n s of c a l i b r a t i o n d a t a and d a t a t o R-AERO-AU and R-COMP. t a p e c o n s t a n t s w i l l be a v a i l a b l e i n e a r l y October. C. Vehicle Design Branch 1. Saturn V a . NASA TM X-53517, " S t a t i c Aerodynamic C h a r a c t e r i s t i c s of t h e Apollo-Saturn V Vehicle" has been published. This r e p o r t i n c l u d e s s t a b i l i t y , a x i a l f o r c e , and l o a d d i s t r i b u t i o n d a t a . b. The a b o r t aerodynamics f o r t h e S a t u r n V v e h i c l e i s being r e v i s e d . The new d a t a w i l l r e f l e c t t h e r e s u l t s of t h e AEDC 4 p e r c e n t load d i s t r i b u t i o n t e s t , The r e s u l t s of t h i s s t u d y , which i s being performed under t h e Northrop s u p p o r t c o n t r a c t , w i l l be a v a i l a b l e i n l a t e October 1966. c. Range s a f e t y aerodynamics f o r t h e S a t u r n v e h i c l e w i l l be r e v i s e d i n t h e a n g l e of a t t a c k range of 0 t o 30 d e g r e e s f b e c a u s e of changes i n t h e s t a b i l i t y d a t a based on r e c e n t l a r g e s c a l e wind t u n n e l t e s t s . R e s u l t s should b e a v a i l a b l e a b o u t November 1 5 , 1966. d. Second s t a g e a x i a l f o r c e c h a r a c t e r i s t i c s f o r t h e Apollo S a t u r n V v e h i c l e have been d e f i n e d and published i n o f f i c e memo R-AERO-AD66-41. The forebody a x i a l f o r c e c o e f f i c i e n t s were o b t a i n e d from wind t u n n e l t e s t s , w h i l e t h e b a s e a x i a l f o r c e was e s t i m a t e d from d a t a o b t a i n e d i n high a l t i t u d e simulation t e s t s . e. The flow f i e l d parameters f o r t h e S a t u r n V I ~ o y a g e rw i t h a 5 4 - f o o t payload e x t e n s i o n have been published i n O f f i c e Memorandum R-AERO-AD-66-43. The d a t a p r e s e n t e d i n c l u d e t h e l o c a l p r e s s u r e coeff i c i e n t , . C p l , l o c a l Mach number Mo, and l o c a l temperature r a t i o , T~/T,. The d a t a a r e p r e s e n t e d f o r a Mach number range of 1.75 t o 8.00 a t z e r o a n g l e of a t t a c k . �f . An experimental i n v e s t i g a t i o n w i l l be conducted i n t h e MSFC 14" t r i s o n i c wind t u n n e l t o determine s t a t i c s t a b i l i t y and a x i a l f o r c e c h a r a c t e r i s t i c s of up-rated S a t u r n V c o n f i g u r a t i o n s . I n i t i a l t e s t s w i l l be conducted w i t h two b a s i c S a t u r n V con£ i g u r a t i o n s : a twos t a g e v e h i c l e w i t h a payload and f i n a l s t a g e diameter of 396 inches f u l l s c a l e , and a t h r e e - s t a g e v e h i c l e w i t h a payload f i n a l s t a g e diameter of 260 i n c h e s f u l l s c a l e . Each of t h e s e c o n f i g u r a t i o n s use f o u r 120-inch (seven segment) s o l i d r o c k e t s a t t a c h e d t o t h e S-IC s t a g e . These t e s t s , scheduled f o r November 1966, w i l l be conducted a t Mach numbers from 0.50 t o 5.0. g. A f o r c e t e s t , conducted i n t h e MSFC 14" wind t u n n e l has been completed on t h e 0.33 p e r c e n t s c a l e model A p o l l o / S a t u r n V LOR i n which r o l l a n g l e e f f e c t s on s t a t i c s t a b i l i t y were i n v e s t i g a t e d . The model was r o l l e d from 0 t o 180 degrees a t 22.5-degree i n t e r v a l s and t e s t e d a t t r a n s o n i c Mach numbers. A n a l y s i s of t h e s e d a t a i s i n p r o g r e s s and should be published w i t h i n t h e n e x t month. h. The Lockheed H u n t s v i l l e Research and Engineering Center have c a l c u l a t e d s t a t i c aerodynamic load d i s t r i b u t i o n s on t h e 4 p e r c e n t s c a l e S a t u r n V a c o u s t i c s environment model t h a t was t e s t e d i n t h e AEDC 1 6 - f o o t t r a n s o n i c t u n n e l . They have a l s o p l o t t e d l o n g i t u d i n a l s t a t i c p r e s s u r e d i s t r i b u t i o n s . The d a t a have been used t o r e f i n e e x i s t i n g aerodynamic load and p r e s s u r e d i s t r i b u t i o n s on t h e A p o l l o / S a t u r n launch v e h i c l e f o r Mach numbers from 0.6 t o 1.45 and a n g l e s of a t t a c k up t o 1 0 d e g r e e s . Lockheed i s p r e p a r i n g a d a t a r e p o r t which w i l l be completed i n November 1966. The experimental i n v e s t i g a t i o n t o determine t h e a e r o dynamic c h a r a c t e r i s t i c s of t h e S-Ic/ S - I 1 i n t e r s t a g e i s scheduled f o r t h e l a t t e r p a r t of November i n t h e MSFC 14" t r i s o n i c wind t u n n e l . The d a t a w i l l be used t o p r e d i c t t h e t r a j e c t o r y of t h e i n t e r s t a g e a f t e r s e p a r a t i o n from t h e S - I 1 s t a g e f o r range s a f e t y purposes. i. The t u n n e l sidewall-mounted t e s t model has been designed. D e t a i l e d d e s i g n drawing and f a b r i c a t i o n remains t o b e done. The model w i l l be f a b r i c a t e d in-house and should be completed by November 1 5 , 1966. 2. Saturn I B a. S t a t i c s t a b i l i t y t e s t s a r e t o b e conducted f o r t h e S a t u r n IB/AS-206 and A p o l l o / S a t u r n V models i n t h e AEDC/VKF f a c i l i t y e a r l y i n October 1966. A 0.55 p e r c e n t s c a l e model S a t u r n IB/AS-206 and 0.33 p e r c e n t s c a l e model A p o l l o / S a t u r n V a r e t o be t e s t e d a t Mach numbers 5, 6 , 7 and 8. T h e s e d a t a w i l l supplement t h o s e o b t a i n e d i n a t e s t which was conducted i n August 1966 a t t h e AEDc/VKF t u n n e l "A". �b. T e s t s have been conducted i n t h e MSFC 14" t r i s o n i c wind t u n n e l t o determine s t a t i c s t a b i l i t y , a x i a l f o r c e , tank loads and a c o u s t i c c h a r a c t e r i s t i c s f o r s e v e r a l proposed S a t u r n I B c o n f i g u r a t i o n s u p r a t e d w i t h UTC-120 s o l i d p r o p e l l a n t r o c k e t motor s t r a p - o n u n i t s . Data were o b t a i n e d f o r Mach numbers ranging from 0.5 t o 4.0 and a n g l e s of a t t a c k up t o 18 d e g r e e s . P r e l i m i n a r y r e s u l t s i n d i c a t e t h a t s t r a p - o n u n i t s cause a n i n c r e a s e i n l o a d s on t h e 70-inch diameter b o o s t e r tanks by a f a c t o r of two o r t h r e e d e g r e e s . However, t o t a l s t a t i c f o r c e s and moments appear t o be a s expected, 3. General a. Viscous Cross-Flow S t u d i e s Large model h i g h Reynolds number f o r c e t e s t s have been conducted a t LTV and a r e being checked f o r accuracy. It w i l l be necess a r y t o r e p e a t s e v e r a l runs b e f o r e t h e s e t e s t s a r e complete. In addit i o n t o t h e LTV r e p o r t , d a t a c o e f f i c i e n t s w i l l be s e n t from LTV t o MSFC by t a p e and t r a n s f e r r e d t o IBM c a r d s f o r machine p l o t t i n g used i n f i n a l evaluation. A f t e r s e v e r a l d e l a y s , small s c a l e f o r c e d a t a obtained a t MSFC a r e being p l o t t e d f o r e v a l u a t i o n . These d a t a w i l l be compared w i t h t h e l a r g e model h i g h Reynolds number from LTV when they become available. Hardware f o r a d d i t i o n a l small s c a l e model t e s t s (ogivec y l i n d e r f r u s t u m - c y l i n d e r ) i s expected t o be completed by mid-October 1966. These t e s t s a r e p r e s e n t l y scheduled f o r November 1966. b. O r i f i c e Flow C o e f f i c i e n t Study The i n v e s t i g a t i o n t o determine o r i f i c e flow c o e f f i c i e n t s f o r s i m u l a t e d f l i g h t boundary l a y e r c o n d i t i o n s and v a r i o u s v e n t g e o m e t r i e s , i n s u p p o r t of t h e S a t u r n v e n t i n g program, i s scheduled f o r f o u r weeks beginning October 31, 1966 i n t h e Ames 6 x 6 f o o t s u p e r s o n i c wind t u n n e l . The f a b r i c a t i o n and assembly of the f l a t p l a t e t e s t model have been comp l e t e d by AEC, Oak Ridge, Tennessee. A t r i p t o AEC i s planned f o r October 4 through 6, 1966, by MSFC and c o n t r a c t o r (NSL) personnel t o make a f u n c t i o n a l checkout of t h e t e s t model and a s s o c i a t e d equipment. Because of d e l a y s i n s c h e d u l i n g t h e wind tunnel f a c i l i t y and l o n g e r - t h a n - a n t i c i p a t e d model d e s i g n and f a b r i c a t i o n time, the cont r a c t t o Northrop Space L a b o r a t o r i e s was extended from September 1966 t o May 1967 w i t h a s l i g h t i n c r e a s e i n c o s t . �c. O r b i t a l Aerodynamics I n t h e p a s t few weeks, R. Wimberly, R-AERO-ADE, i n c o o r d i n a t i o n w i t h L. Donehoo, J. Bal l a n c e and miss i o n s u p p o r t from Lockheed, has worked on v a r i o u s problems i n o r b i t a l aerodynamics i n c l u d i n g p r o v i d i n g t h e Lab w i t h t h e in-house c a p a b i l i t y of p r e d i c t i n g t h e aerodynamics of v a r i o u s o r b i t a l c o n f i g u r a t i o n s . This c a p a b i l i t y was o b t a i n e d by c o n v e r t i n g an a l r e a d y running computer program, prev i o u s l y w r i t t e n f o r t h e IBM 7094 t o o p e r a t e on t h e CDC 3200. The program i s l i m i t e d t o convex bodies i n f r e e molecule flow. An a d d i t i o n a l e f f o r t was made t o expand t h e e x i s t i n g program t o i n c l u d e t h e e f f e c t s of concave b o d i e s . The n e c e s s a r y e q u a t i o n s f o r t h e drag and l i f t c o e f f i c i e n t s f o r t y p i c a l concave c o n f i g u r a t i o n s have been d e r i v e d and a r e b e i n g programmed f o r t h e CDC 3200. A t t h e r e q u e s t of J. B a l l a n c e , t h e contamination problem of t h e ATM o r b i t a l c o n f i g u r a t i o n was s t u d i e d . The a n a l y s i s included t h e i n v e s t i g a t i o n of t h e e f f e c t s of g i v e n leakages from t h e v e h i c l e o r b i t i n g a t a b o u t 260 m i l e s a l t i t u d e on t h e viewing c a p a b i l i t y of a t e l e s c o p e l o c a t e d 100 f e e t from t h e v e h i c l e . "Worst" c a s e s were considered i n d e t e r m i n i n g t h e r a d i a l molecular d e n s i t y from t h e v e h i c l e ; i t was cone t c . ) of 24 l b s / d a y cluded t h a t a g i v e n gaseous leakage (02, C02, N,, from t h e v e h i c l e w i l l produce a n a d d i t i o n a l d e n s i t y of molecules a t 100 f e e t from t h e v e h i c l e i n t h e o r d e r of magnitude of a normal atmosphere t h a t would appear a t a b o u t 200 m i l e s a l t i t u d e . The Martin Company, i n a meeting a t MSFC pointed o u t a n o t h e r p o s s i b l e c o n t r i b u t i o n , confirmed ,by t h o s e i n a t t e n d a n c e , of i c e c r y s t a l s of 1-10 microns i n d i a m e t e r . The i c e c r y s t a l s should be few i n r e l a t i o n t o the gas p a r t i c l e s , depending, however, on t h e dumping r a t e s , and w i l l v a r y i n d e n s i t y i n t h e r a d i a l d i r e c t i o n a s w e l l a s w i t h time, assuming t h a t t h e dumping i s n o t continuous. During t h e dumping p r o c e s s , each of t h e non-ionized p a r t i c l e s d e p a r t t h e v e h i c l e a t a f i n i t e v e l o c i t y and l e a v e t h e v i c i n i t y of t h e t e l e s c o p e i n a m a t t e r of seconds. For those i c e p a r t i c l e s w i t h t h e p o s s i b l e s u f f i c i e n t amount of i o n i z a t i o n t o r e t a i n a p o s i t i o n c l o s e t o t h e t e l e s c o p e w i l l be swept away by t h e a i r molecules and vaporized It was determined t h a t the v a p o r i z a t i o n time f o r an by s o l a r r a d i a t i o n . i c e c r y s t a l 1 0 microns i n diameter a t 260 m i l e s a l t i t u d e should be a b o u t 30 seconds. The combined r e s u l t s of t h e s e a n a l y s e s i n d i c a t e an i n s i g n i f i c a n t e f f e c t of leakages oh t h e ATM viewing c a p a b i l i t y . �D. Thermal Environment Branch 1. Saturn I B a. Thermal Analysis of t h e S-IVB Workshop An a n a l y s i s of t h e s o l a r , a l b e d o , and e a r t h r a d i a t i o n i n c i d e n t on t h e S-IVB workshop f o r a g r a v i t y g r a d i e n t o r b i t i s a b o u t 80 p e r c e n t completed. S i n c e t h e o r i e n t a t i o n of t h e v e h i c l e i n o r b i t i s n o t f i r m , t h e a n a l y s i s i s i n t h e form of a parameter s t u d y . Five o r i e n t a t i o n s were s e l e c t e d and t h e o r b i t a l h e a t i n g c a l c u l a t e d f o r o r b i t a l a l t i t u d e s of 175 and 259 n a u t i c a l m i l e s . Two launch d a t e s June 2 2 and December 22 - were considered which w i l l g i v e minimum and maximum shadow times - . b. S-IB High Angle-of-Attack Aerodynamic Heating Work i s c o n t i n u i n g on t h e d e s i g n of t h e S-IB higha n g l e - o f - a t t a c k h e a t i n g model. Analyses a r e being performed t o ' d e t e r m i n e t h e b e s t m a t e r i a l , s k i n t h i c k n e s s , and thermocouple l o c a t i o n s . M r . H i l l of R-AERO-AEM and M r . Wilson v i s t e d JPL personnel on September 20 t o d i s c u s s w i t h them o u r p r e l i m i n a r y p l a n s . c. Aerothermodynamics The computation of t h e maximum aerodynamic h e a t i n g environment f o r t h e SA-206 v e h i c l e has been completed. The environment f o r t h e SA-206 was found t o be approximately e i g h t p e r c e n t more s e v e r e than f o r t h e SA-201, and 18 p e r c e n t g r e a t e r t h a n t h e SA-202 v a l u e s . A n a l y s i s of t h e SA-204 launch v e h i c l e environment has been completed. The SA-204 launch environment was found t o be s l i g h t l y l e s s s e v e r e t h a n t h e SA-201 launch environment. Thus, no thermal problems are anticipated. P u b l i c a t i o n of t h e SA-204 launch environment i s scheduled f o r t h e middle of October. C o r r e l a t i o n of model d a t a , f l i g h t d a t a and a n a l y t i c a l c a l c u l a t i o n s f o r t h e f i r s t t h r e e S a t u r n I B v e h i c l e s i s c o n t i n u i n g . Prel i m i n a r y r e s u l t s i n d i c a t e good agreement between a n a l y t i c a l model r e s u l t s and f l i g h t d a t a . A v a i l a b l e wind t u n n e l d a t a f o r protuberances g e n e r a l l y r e s u l t i n more s e v e r e environments than t h o s e i n d i c a t e d by t h e f l i g h t d a t a . This d i s c r e p a n c y i s under i n v e s t i g a t i o n . The SA-203 d a t a c o r r e l a t i o n r e p o r t is scheduled f o r p u b l i c a t i o n i n November 1966. C o r r e l a t i o n of t h e SA-201 and SA-202 f l i g h t d a t a w i t h model d a t a and a n a l y t i c a l pred i c t i o n s is scheduled f o r p u b l i c a t i o n i n December 1966 a s a j o i n t r e p o r t . �d. Base Heating Maximum base and exhaust plume h e a t i n g environments f o r t h e SA-205 v e h i c l e were published i n September a s CCSD TN-AP-66-67. Analyses t o determine maximum b a s e and exhaust plume h e a t i n g environments f o r t h e SA-206 launch v e h i c l e a r e proceeding on s c h e d u l e . These w i l l i n c l u d e a n o p t i m i z a t i o n s t u d y of t h e plume r a d i a t i o n computer program (C00050). + e. Thermodynamic F l i g h t E v a l u a t i o n Thermal e v a l u a t i o n of t h e SA-202 f l i g h t d a t a has been completed. The MSFC-FEWG review meetings were a t t e n d e d and f i n a l r e s u l t s r e p o r t e d t o b o t h t h e MSFC-FEWG and t o t h e CCSD-FEG. SA-202 thermal d a t a were found t o be g e n e r a l l y a s expected, c o r r e l a t i n g w e l l w i t h corresponding d a t a recorded on previous S a t u r n I B v e h i c l e s . A n a l y s i s of t h e SA-203 i n f r a r e d spectrometer d a t a i s c o n t i n u i n g . A s a t i s f a c t o r y s e n s o r c a l i b r a t i o n f o r one of t h e two channels has been o b t a i n e d . P u b l i c a t i o n of t h e spectrometer d a t a r e p o r t a w a i t s f i n a l s e l e c t i o n of t h e c a l i b r a t i o n d a t a f o r t h e o t h e r channel by MSFC . 2. Saturn V a. General (1) S a t u r n VIVoyager Launch Vehicle T r a j e c t o r i e s and flow f i e l d s have been obtained f o r t h e S a t u r n VIVoyager launch v e h i c l e . As c e n t thermal environments w i l l b e r u n soon. Data f o r t h e shroud have been r e q u e s t e d by October 20, and i t seems t h a t t h i s d a t e can be met. (2) s a t u r n Improvement S t u d i e s P r e l i m i n a r y plans a r e being made f o r a base h e a t ing t e s t f o r S a t u r n v e h i c l e s w i t h s t r a p - o n s . C o n f i g u r a t i o n drawings and t r a j e c t o r i e s have been passed on t o CAL. A r e p r e s e n t a t i v e from CAI, w i l l p r e s e n t h i s i d e a s on a t e s t program e a r l y n e x t month. The S a t u r n V conf i g u r a t i o n i s b e i n g g i v e n more c o n s i d e r a t i o n than t h e S a t u r n I B . �(1) Short-Duration Model T e s t Volume I of Document D5-15615, "Saturn V Model Base Heating T e s t A n a l y s i s (S-IC S t a g e ) ," has been r e l e a s e d . Volume I1 w i l l be r e l e a s e d soon. (2) Des i g n Assurance A n a l y s i s of t h e h e a t i n g environment f o r t h e S-IC con£ ined d e t o n a t i n g f u s e has been published i n Coordination Sheet ATT-H-015. The a d d i t i o n of a f a i r i n g on t h e forward s i d e of t h e IU r e t r o - r e f l e c t o r r e q u i r e d a r e - e v a l u a t i o n of i t s protuberance f a c t o r s and t h e a f f e c t e d a r e a s . A c o o r d i n a t i o n s h e e t w i l l be i s s u e d a s soon a s t h e c u r r e n t environment document d r a f t i s f i n i s h e d . The d e f i n i t i o n of energy t r a n s f e r from s o l i d motor p a r t i c l e s t o s u r f a c e s from experimental t e s t programs i s i n rough draft. F i n a l r e l e a s e depends on v e r i f i c a t i o n of the r e s u l t s of one t e s t u s i n g t h e thermal a n a l y z e r . (3) O p e r a t i o n a l Thermal Environment - SA-501 The atmospheric d e n s i t y v a r i a t i o n was r e c e i v e d from MSFC Aerospace Environment D i v i s i o n on September 6, 1966. F l i g h t Mechanics produced o u r r e q u i r e d + l o h e a t i n g t r a j e c t o r i e s using t h e o p e r a t i o n a l t r a j e c t o r y a s t h e b a s e l i n e . The a e r o - h e a t i n g environment f o r t h e s e t r a j e c t o r i e s has been determined. A rough d r a f t of t h e t r a j e c t o r y and a e r o - h e a t i n g s e c t i o n s has been completed. S-IC b a s e h e a t i n g and S-IC/ S-11s t a g i n g environments a r e b e i n g e v a l u a t e d . Staging p r e d i c t i o n s f o r t h e LOX dome and i n t e r s t a g e p r e s s u r e s have been completed. The a s y m p t o t i c c a l o r i m e t e r w a l l temperature and c o n v e c t i v e h e a t i n g r a t e s have been determined. T o t a l and d i f f e r e n t i a l p r e s s u r e e s t i m a t e s a r e being e v a l u a t e d . (4) F l i g h t Evaluation Thermal a n a l y z e r models f o r t h e instrument l o c a t i o n s on t h e f i n s and engine f a i r i n g s have been c o n s t r u c t e d . The models w i l l be checked o u t when t h e o p e r a t i o n a l environment becomes a v a i l a b l e . A r e q u e s t t o revamp t h e t h i n s k i n computer program f o r u s e i n f l i g h t e v a l u a t i o n was made i n Coordination Sheet ATT-H-014. The changes w i l l reduce i n p u t time and e r r o r s . �c. S - I 1 Stage The many protuberances on t h e S - I 1 a f t i n t e r s t a g e l i e s o c l o s e t o g e t h e r t h a t t h e i r e f f e c t s o v e r l a p . NAA has requested t h a t l a r g e a r e a s of t h e a f t i n t e r s t a g e be i n s u l a t e d because of t h e i n t e r f e r e n c e . R-AERO-ATA reviewed t h e i r thermal environments t o determine whether t h e r e q u e s t should be approved. R-AERO-AT. recommended t h a t l e s s a r e a b e i n s u l a t e d than NAA r e q u e s t e d , b u t I 0 approved t h e r e q u e s t i n t o t a l s i n c e l i t t l e o r no c o s t was involved and payload i s n o t critical. 3. General a. J u p i t e r Probe The J u p i t e r probe s t u d y has n o t been a c t i v e l y c a r r i e d o u t t h i s month because of t h e slowness of a c q u i r i n g a computer program n e c e s s a r y f o r i t s p r o g r e s s . A p r e s e n t a t i o n was made by H. Hoshizaki, K. Wilson, and A. Wood of Lockheed, Palo A l t o a b o u t t h e i r ' e n t r y h e a t t r a n s f e r work. During t h e i r p r e s e n t a t i o n , t h e y s t a t e d t h e i r o p i n i o n t h a t shock l a y e r temperatures f o r a J u p i t e r probe might range from 20,000°K t o 50,000°K. Heating r a t e s would be h i g h enough t o cause II massive" a b l a t i o n , d e s t r o y i n g t h e boundary l a y e r a s i t i s u s u a l l y thought o f . The a b s o r p t i o n c o e f f i c i e n t s f o r t h e Jovian atmospheric g a s e s and t h e a b l a t e d m a t e r i a l seem t o be t h e d a t a which must be g e n e r a t e d t o complete t h e i n p u t f o r t h e problem. b. M a r t i a n Entry Probe Study AS0 is c o o r d i n a t i n g a s t u d y t o determine t h e of and problems a s s o c i a t e d w i t h combining a r e t r i e v a b l e probe w i t h t h e Mars Manned Flyby Mission. R-AERO-ATA i s s u p p o r t i n g s t u d y w i t h h e a t i n g d a t a and h e a t s h i e l d a n a l y s e s . Input data being gathered. c. feasibility experiment t h e AS0 a r e now Research i n t o t h e Problem of I n t e r a c t i o n of Coaxial Axisymme t r i c J e t s The i n c l u s i o n of a s u b r o u t i n e t o c a l c u l a t e and use t h e e q u i l i b r i u m c o n s t a n t s from NASA TN D-1454, October 1962, has been The new s u b r o u t i n e would r e q u i r e o n l y a deferred f o r the present. moderate expansion of t h e program; however, i t has been decided t h a t t h i s a d d i t i o n w i l l n o t be included u n t i l t h e e n t i r e procedure u s i n g t h e p r e s e n t e q u i l i b r i u m c o n s t a n t s u b r o u t i n e has been checked o u t . P r o d u c t i o n ' r u n s aye being made u s i n g t h e e q u i l i b r i u m c o n s t a n t s of "JANAF Thermochemi.ca1 Tables," by Dow Chemical Co., August 1965. These runs a r e f o r a n o z z l e exhaust which i n c l u d e s t h e f o l l o w i n g chemical �s p e c i e s w i t h t h e i r corresponding mass f u n c t i o n s : hydrogen, 0.00406; w a t e r , 0.02054; carbon, 0.00006; carbon monoxide, 0.00141; carbon d i o x i d e , 0.62051; and methane, 0.23253. The atmosphere i s t r e a t e d a s a m i x t u r e of oxygen (0.23300) and n i t r o g e n (0.76700). P r e s e n t l y t h e i n i t i a l cases of n o z z l e exhaust and t u r b i n e e x h a u s t mixing and t h o s e of t h e t u r b i n e exhaust and e x t e r n a l a i r mixing a r e being t r e a t e d s e p a r a t e l y a s two-stream mixing problems. The r e s u l t s of t h e s e c a s e s w i l l b e p l o t t e d and normalized f o r use a s i n p u t t o t h e combined t h r e e - s t r e a m mixing of t h e nozzle e x h a u s t , t u r b i n e e x h a u s t and e x t e r n a l a i r . d. Base P r e s s u r e and Environment The p o r t i o n s of t h i s s t u d y c u r r e n t l y under inves t i g a t i o n i n v o l v e t h e t u r b u l e n t boundary l a y e r growth on nozzle w a l l s w i t h mass i n j e c t i o n and t h e r e a c t i n g s h e a r l a y e r a t t h e plume boundary. The f i n i t e - r a t e s h e a r l a y e r program i s being used on The r e s u l t i n g s h e a r l a y e r d e s c r i p t i o n w i l l coma s e a l e v e l F-1 plume. p l e t e t h e a n a l y s i s of t h e e n t i r e plume f o r t h i s engine using the b e s t a v a i l a b l e a n a l y t i c a l tools. F i n i t e - r a t e shear layer calculations a r e a l s o planned f o r t h e CAL 1120-scale F-1 burning L O ~ I E t h y l e n e , t h e 5 - 2 w i t h water-cooled d i f f u s e r r i n g , and a Rocketdyne LOXIRP-1 t e s t engine. A v a i l a b l e experimental d a t a f o r t h e s e plumes range from simple photographs t o t e m p e r a t u r e and composition probes through t h e plume a t s e v e r a l a x i a l stations. I n a d d i t i o n , t h e GAL 1120-scale F-1 engine i s being instrumented t o measure l o c a l s k i n f r i c t i o n on t h e nozzle w a l l which w i l l be compared w i t h t h e p r e d i c t i o n s of LMSC'St u r b u l e n t boundary l a y e r program. e. O r b i t a l Heating Program The thermal a n a l y s i s of t h e LFV engine compartment h a s been p u b l i s h e d i n a Technical Data Release. The r e s u l t s of t h e s t u d y i n d i c a t e t h a t (1) t h e s t e a d y - s t a t e temperatures i n t h e nozzle t h r o a t and chamber r e g i o n s w i l l a l l o w s e v e r a l hours of continuous operat i o n , and (2) t h a t t h e engine compartment w a l l s should be completely i n s u l a t e d from t h e f u e l and o x i d i z e r tanks f o r s teady-s t a t e c o n d i t i o n s . f. Nozzle and J e t Wake Study Two s e p a r a t e t a s k s were completed a s a r e s u l t of cont i n u i n g e f f o r t on t h e n o z z l e and j e t wake s t u d y . These two t a s k s , documented a s Technical Data R e l e a s e s , a r e d e s c r i b e d b r i e f l y below: �(1) Analysis of a 3 - 2 Engine Exhaust Flow w i t h a Mach D i s c Type of Shock S t r u c t u r e : Flow f i e l d d a t a were generated f o r a 5 - 2 engine e x h a u s t plume, u s i n g ~ o c k h e e d ' sm e t h o d - o f - c h a r a c t e r i s t i c s program. The c a l c u l a t e d shock s t r u c t u r e w i t h i n t h e flow f i e l d was compared w i t h t h a t observed i n photographs of a l i v e s e a l e v e l f i r i n g . Good agreement was obtained a f t e r a d j u s t i n g t h e chamber p r e s s u r e t o a l l o w f o r momentum l o s s e s . A f t e r t h e l o c a t i o n of t h e shock s t r u c t u r e was s e t , t h e s u b s o n i c r e g i o n behind t h e observed Mach d i s c w a s approximated w i t h a one-dimensional s o l u t i o n . ( 2 ) Flow F i e l d Analysis of a Cold Flow J e t : D e n s i t y v a r i a t i o n s , i n t e r p r e t e d a s sound waves, were observed i n shadowgraphs of a s u p e r s o n i c j e t . These waves appear t o o r i g i n a t e a t p o i n t s of i n t e r a c t i o n between shock waves and t h e j e t boundary. To d e f i n e more thoroughly t h e flow p r o p e r t i e s a t those i n t e r a c t i o n p o i n t s , a n a n a l y s i s of t h e flow f i e l d was conducted w i t h ~ o c k h e e d ' sm e t h o d - o f - c h a r a c t e r i s t i c s program. Data f o r t h e f i r s t two shock/boundary i n t e r a c t i o n p o i n t s were generated. g. S t a g e S e p a r a t i o n Thermodynamics Work i s c o n t i n u i n g on t h e p r e d i c t i o n of impingement p r e s s u r e s caused by r o c k e t exhaust plumes a d j a c e n t t o s o l i d boundaries. U n t i l r e c e n t l y , hand c a l c u l a t i o n s were r e q u i r e d t o p r e d i c t impingement p r e s s u r e i n t h e s t r o n g shock r e g i o n where t h e flow must become s u b s o n i c t o t u r n p a r a l l e l t o t h e s o l i d boundary. This a n a l y s i s has been combined i n t o a n a d d i t i o n a l computer program which uses v a l u e s from t h e methodo f - c h a r a c t e r i s t i c s (MOC) plume r u n a s i n p u t . The r e s u l t s a r e being checked a g a i n s t experimental d a t a . An improved c a p a b i l i t y has been added t o t h e impingement flow f i e l d a n a l y s i s . It i s now p o s s i b l e t o i n p u t a s t a r t l i n e t o t h e MOC program which has two p a r t s : a l e f t running charact e r i s t i c p o r t i o n and t h e remainder a s t r a i g h t s t a r t l i n e . This removes some of t h e d i f f i c u l t i e s w i t h s t a r t i n g t h e impingement flow f i e l d experienced i n t h e p a s t . I n connection w i t h impingement h e a t i n g r a t e s , a n e f f o r t i s underway t o use t h e LMSC/HREC t r a n s p o r t p r o p e r t y program a l o n g w i t h t h e MOC impingement flow f i e l d t o o b t a i n v e r y a c c u r a t e t r a n s p o r t prop e r t i e s a t each p o i n t a l o n g t h e s o l i d boundary where t h e impingement h e a t t r a n s f e r r a t e i s d e s i r e d . Using t h e s e p r o p e r t i e s i n t h e boundary l a y e r program, t h e o b j e c t i v e i s t o compare t h e r e s u l t i n g h e a t t r a n s f e r r a t e s t o experimental d a t a and t o determine i f t h i s a f f o r d s a marked improvement i n t h e acCuracy of t h e p r e d i c t i o n method. �E. Uns tead y Aerodynamics Branch 1. I n f l i g h t F l u c t u a t i n g P r e s s u r e and A c o u s t i c Environment a . Environmental p r e d i c t i o n s of t h e f l u c t u a t i n g p r e s s u r e environment i n t h e v i c i n i t y of t h e Snap-29, a r a d i o - i s o t o p e thermoe l e c t r i c g e n e r a t o r , have been completed. b. Environmental p r e d i c t i o n s of t h e f l u c t u a t i n g p r e s s u r e l e v e l s i n t h e v i c i n i t y of the S-IC and S - I 1 s e p a r a t i o n plane have been completed. c. "Quick look" r e d u c t i o n of t h e f l u c t u a t i n g p r e s s u r e d a t a a c q u i r e d a t AEDC on t h e 4 p e r c e n t model t e s t have been implemented. A t t h i s time t h e r e a r e no d a t a a v a i l a b l e f o r a n a l y s i s and e x t r a p o l a t i o n t o f u l l s c a l e f l i g h t condition. d. A "quick look" method f o r a s s e s s i n g t h e response of t h e S a t u r n V s t r u c t u r e t o f l u c t u a t i n g p r e s s u r e f o r c e s i s being published. It i s planned t o u s e t h e d a t a from t h e 4 p e r c e n t model t e s t a t AEDC i n t h e s e s t r u c t u r a l r e s p o n s e e s t i m a t i o n s which w i l l be made by R-P&VE-S. 2. Launch S i t e Acous t i c Environment a . A l l planned t e s t s under c o n t r a c t NAS8-20223 e n t i t l e d , "Acoustic S c a l e Model T e s t s of High-Speed Flows , ' I have been completed. The d a t a r e d u c t i o n of a l l a c o u s t i c measurements has a l s o been completed, and t h e f i n a l r e p o r t covering b o t h phases of t h i s e f f o r t i s being prepared. b. An e n c l o s u r e f o r t h e " J e t Flow Shadowgraph" experiments i s r e q u i r e d t o keep extraneous l i g h t s i g n a l s from over-exposing t h e shadowgraph f i l m d u r i n g t h e experiments. The d e s i g n of t h e e n c l o s u r e i s expected t o be completed by t h e end of n e x t month. c. An experiment t o determine t h e e f f e c t s on t h e a c o u s t i c environment of a j e t exhaust impingement on water i s i n p r o g r e s s . F a c i l i t y checkout t e s t s were conducted l a s t week, and e x p e r i m e n t a l program t e s t s a r e expected t o b e g i n soon. d. The e n g i n e e r i n g a n a l y s i s of t h e i n f l i g h t f l u c t u a t i n g p r e s s u r e d a t a from AS-203 has been completed. e . A n a l y s i s of t h e f l u c t u a t i n g p r e s s u r e d a t a from AS-202 Other d a t a on a common t e l e m e t r y l i n k w i t h c e r t a i n i s s t i l l i n progress. f l u c t u a t i n g p r e s s u r e d a t a a r e being reviewed t o determine t h e cause of extraneous s i g n a l s during the f l i g h t . �. f Task Order #7, f o r Baganof f A s s o c i a t e s ' d a t a r e d u c t i o n on t h e MSFC/AMES s e p a r a t e d flow experiment has been w r i t t e n t o provide d a t a f o r a p i l o t s t u d y t o f u r t h e r e v a l u a t e t h e flow c o n d i t i o n s and environments. Cross PSD'S, narrow band time c o r r e l a t i o n s , and s e v e r a l r e c o r d e r h e a d - s c a t t e r e r r o r s were r e q u e s t e d f o r v a r i o u s channel p a i r s . g . A r e p o r t on "The Ground Plane A c o u s t i c Environments Due t o a S a t u r n V Launch from Complex 39 a t Cape Kennedy," i s completed. h. A m o d i f i c a t i o n t o t h e 1120th s c a l e S a t u r n V launch conf i g u r a t i o n , soon t o be t e s t e d t o measure t h e a c o u s t i c s c a l i n g f a c t o r s and t o o b t a i n c e r t a i n o t h e r d e t a i l e d information on the sound s o u r c e mechanisms, has been made f o r T e s t ~ a b o r a t o r y ' s f a b r i c a t i o n group. This m o d i f i c a t i o n saved c o n s i d e r a b l e time and m a t e r i a l s i n t h e t e s t program w i t h o u t s i g n i f i c a n t p e n a l t y t o t h e a c o u s t i c d a t a a c q u i s i t i o n program. i. A c o m p i l a t i o n of t h e dynamic response t e l e m e t r y channels onboard AS-2041s-IVB and subsequent f l i g h t s has been made. The purpose of determining t h e d a t a measuring c a p a b i l i t y is t o p l a n f o r a m o d i f i c a t i o n i n t h e program t o o b t a i n a p o s s i b l e f l u t t e r measurement program. 3. Aeroelasticity The wavy-wall panel f l u t t e r t e s t s conducted i n t h e ARC 2 x 2-foot t r a n s o n i c wind t u n n e l have been completed. The d a t a a r e b e i n g prepared f o r shipment t o MSFC. The p r e s s u r e phase of t h e panel f l u t t e r t e s t s f o r t h e S a t u r n IV-B forward s k i r t has been completed. The p r e s s u r e d i s t r i b u t i o n and boundary l a y e r p r o f i l e d a t a have been reduced; however, t h e f l u c t u a t i n g p r e s s u r e environment d a t a remain t o be analyzed. Although t h e d a t a o b t a i n e d were good, i t w a s n o t p o s s i b l e t o a c h i e v e i n f l i g h t condit i o n s i n a l l c a s e s because of wind t u n n e l l i m i t a t i o n s . The AEDC 16-foot t r a n s o n i c wind t u n n e l was used f o r t h e s e t e s t s and w i l l b e used d u r i n g t h e f i r s t week of October t o t e s t t h e a c t u a l f l u t t e r model. V. AEROSPACE ENVIRONMENT DIVISION 1. An e x p l o r a t o r y r e s e a r c h e f f o r t has been i n i t i a t e d t o compare FPS-16 r a d a r f ~ i m s p h e r ewind p r o f i l e d a t a w i t h t h e upper atmospheric This w i l l be phenomena t h a t a r e d e t e c t a b l e by LIDAR techniques. accomplished w i t h t h e a s s i s t a n c e of S t a n f o r d Research I n s t i t u t e p r i n c i p a l i n v e s t i g a t o r ) . SRI w i l l a r r a n g e t o (Mr. Ronald C o l l i s probe t h e upper atmosphere a t t h e same time t h a t wind d a t a a r e being - �measured w i t h a Jimsphere. This work w i l l be completed a t t h e Western T e s t Range, P o i n t Mugu, C a l i f o r n i a where Jimsphere wind p r o f i l e d a t a a r e r o u t i n e l y a c q u i r e d . This i s being c l o s e l y coordinated between t h e r e s p o n s i b l e R-AERO-Y, SRI and P o i n t Mugu personnel b e f o r e t h e LIDAR t a~ measurements a r e made. Once a l i m i t e d number of ~ i m s p h e r e / L ~d~aA samples a r e obtained, a "quick-look" a p p r a i s a l w i l l be made. Any cont i n u a t i o n of t h i s e f f o r t w i l l depend upon the r e s u l t s of t h i s i n i t i a l e f f o r t . The LIDAR has been used s u c c e s s f u l l y t o measure such atmospheric phenomena a s (1) cloud h e i g h t s and i n t e n s i t y , (2) p r e c i p i t a t i o n , (3) induced and n a t u r a l p a r t i c u l a t e m a t e r i a l s of t h e atmosphere (4) v i s i b i l i t y , and (5) l a y e r s of extreme wind s h e a r . 2. The m e t e o r o l o g i c a l a s p e c t s of t h e S t r a t o s c o p e I1 P r o j e c t was i n v e s t i g a t e d d u r i n g a v i s i t by M r . Turner and M r . H i l l t o t h e h i g h a l t i Cude b a l l o o n r e s e a r c h launch s i t e a t P a l e s t i n e , Texas. Recommendations have been made t o t h e MSFC committee reviewing t h i s p r o j e c t . 3 . A n a l y s i s of ground wind p r o f i l e d a t a t h a t were measured i n s u p p o r t of t h e Ground Wind Loads T e s t (GWLT) of S a t u r n V 500F.at Cape Kennedy (LP-39A) i s c o n t i n u i n g . Information on wind v e l o c i t y cond i t i o n s , i n c l u d i n g g u s t d a t a , i s being formalized and t r a n s m i t t e d t o M r . K r o l l (R-P&W-S) a s r e q u i r e d . - 4. A meeting was h e l d w i t h personnel of GCA Corporation a t MSFC on August 31, 1966, t o review t h e s t a t u s of a temperature s e n s o r developThe temperature s e n s o r i s ment program under C o n t r a c t No. NAS8-20588. t o be used on t h e Jimsphere b a l l o o n t o o b t a i n d e t a i l e d upper atmospheric t e m p e r a t u r e p r o f i l e d a t a a s s o c i a t e d w i t h t h e d e t a i l e d wind d a t a being Loutinely acquired. This c o n t r a c t i s proceeding s a t i s f a c t o r i l y and on s c h e d u l e . No major problems have evolved. The temperature s e n s o r has been s e l e c t e d (a 5 m i l bead t h e r m i s t o r ) , and breadboarding of t h e temperat u r e s e n s i n g system has begun. 5. Work i s c o n t i n u i n g on a s o l a r c y c l e p r e d i c t i o n technique u s i n g random numbers. P r e l i m i n a r y r e s u l t s s u g g e s t t h a t c y c l e twenty has a The s o l a r a c t i v i t y should r i s e r a p i d l y i n t h e months long p e r i o d . ahead t o a peak n e a r a monthly average of 170 during t h e l a t t e r p a r t of 1968 followed by a few y e a r s of continued h i g h a c t i v i t y . 6. Work i s p r o g r e s s i n g s a t i s f a c t o r i l y on t h e MSFC Upper Atmosphere Measurement Program (MUMP). Two probes w i t h omegatrons, which had been g o l d - p l a t e d s o they t h e o r e t i c a l l y would n o t a b s o r b atomic oxygen, were launched by GSFC i n August; however, they b o t h f a i l e d t o measure t h e Two modified instruments which i n c l u d e a proposed a t o m i c oxygen p r e s e n t . s , o l u t i o n t o t h i s problem w i l l be launched by MSFC t h e l a t t e r p a r t of October w i t h t h e remaining s i x probes now scheduled f o r launch during January 1967. 22 r; �7 . The i n t e r i m r e p o r t on t h e m e t e o r o l o g i c a l p o r t i o n of t h e space s t a t i o n s t u d y was completed d u r i n g t h e l a s t week of September. A f t e r t h e p r e s e n t a t i o n t o NASA H e a d q u a r t e r s , t h e s t u d y was extended a n a d d i t i o n a l s i x weeks. 8. The 1966 r e v i s i o n t o t h e Space Environment C r i t e r i a Guidelines f o r Use i n Space Vehicle Development document w i l l b e completed d u r i n g t h e f i r s t week i n October. 9. Nine p r o p o s a l s f o r t h e d e f i n i t i o n of a n i n - f l i g h t experiment t o inves t i g a t e the phys i c s of g a s - s u r f a c e molecule i n t e r a c t i o n s i n t h e ambient s p a c e environment were r e c e i v e d and a r e b e i n g e v a l u a t e d . The e v a l u a t i o n w i l l be completed i n October. 10. Work i s p r o g r e s s i n g on updating t h e models of t h e Mars, Venus, and J u p i t e r atmospheres f o r use i n advanced m i s s i o n s t u d i e s being conducted under t h e a u s p i c e s of t h e Advanced Systems O f f i c e . 11. We a r e c o n t i n u i n g t o provide atmospheric d e n s i t y d a t a t o s u p p o r t t h e a t t i t u d e and guidance and c o n t r o l system s t u d i e s being conducted by A s t r i o n i c s Laboratory. 12. We have i n i t i a t e d a p r e l i m i n a r y a n a l y s i s of t h e e f f e c t s of s t a t i c f i r i n g s on t h e ionosphere. We e x p e c t t o g e t some c o n t r a c t u a l e f f o r t underway on t h i s program d u r i n g October. 13. Work has begun on i d e n t i f y i n g s o l a r c y c l e v a r i a t i o n s i n t h e Mars atmosphere. Knowledge of t h e amplitude of t h e s e v a r i a t i o n s i s n e c e s s a r y i n t h e advanced p l a n e t a r y probe s t u d i e s . A t t h e same time, some e f f o r t i s b e i n g devoted t o e s t a b l i s h i n g models of t h e Mars s u r f a c e environment and i t s v a r i a t i o n s . VI, AS TRODYNAMICS AND GUIDANCE THEORY DIVISION A. O f f i c e of t h e Ch5ef A NASA g r a n t h o l d e r s p r e s e n t a t i o n on Control Theory was h e l d on September 21, 1966 a t MSFC. P a r t i c i p a t i n g were P r o f e s s o r s Kinnen, L i n d o r f f , B r i d g l a n d , FlKgge-Lotz, Polak, Meirovich, Roy, F r a n k l i n , Hunt, d i s cuss i n g t h e i r NASA g r a n t s . The second NASA I n t e r c e n t e r meeting on Control Theory was held on September 22-23, 1966 a t MSFC. The meeting covered c u r r e n t t o p i c s of NASA r e s e a r c h i n t e r e s t i n t h e c o n t r o l t h e o r y a r e a . A b s t r a c t s of t h e papers a r e a v a i l a b l e from R-AERO-G. �Work was done on t h e p o s s i b i l i t y of v e r i f y i n g t h a t t h e u s u a l 1i n e a r i z a t i o n s t a b i l i t y technique (Aizerman' s c o n j e c t u r e ) l e a d s t o bounded s o l u t i o n s . Only p a r t i a l r e s u l t s a r e o b t a i n e d on t h i s problem. 'Methods f o r i n v e s t i g a t i n g p e r i o d i c behavior i n autonomous s y s terns were s o u g h t , i n p a r t i c u l a r , t h o s e a p p l i c a b l e t o Hamil t o n i a n systems, s u c h a s t h e n-body problem. The method of Krylov-Bogoliubov i s a l i k e l y candidate . E x i s t e n c e and uniqueness theorems of t h e Okamura type (necessary and s u f f i c i e n t c o n d i t i o n s ) were considered f o r p o s s i b l e a p p l i c a t i o n s i n (J. George). t r a j e c t o r y c a l c u l a t i o n s and p e r i o d i c o r b i t p r o p e r t i e s . B. A s trodynamics Branch 1. I n t e r p l a n e t a r y Trans i t S t u d i e s (In-House) a . Work i s c o n t i n u i n g on t h e f r e e f l i g h t multi-body power s e r i e s i n t e g r a t i o n deck. The n e c e s s a r y programming changes have been made, and t h e deck i s being checked o u t . b. Formulation of t h e e q u a t i o n s f o r a new deck designed p r i m a r i l y f o r parameter type s t u d i e s of low t h r u s t t r a j e c t o r i e s i s n e a r i n g completion. The deck w i l l i n c l u d e t h e second, t h i r d , and f o u r t h harmonics of t h e e a r t h ' s p o t e n t i a l f u n c t i o n and has a f i x e d a n g l e t h r u s t ; t h e g r a v i t a t i o n a l f i e l d s of t h e e a r t h , t h e sun, and a s e l e c t e d t h i r d body a r e i n t e r d e p e n d e n t . The e q u a t i o n s of motion of t h e sun, probe and t h e t h i r d body w i l l be i n t e g r a t e d u s i n g power s e r i e s , and t h e deck w i l l compute i t s own i n t e g r a t i o n time s t e p f o r maximum speed c o n s i s t e n t w i t h t h e s p e c i f i e d accuracy. Furthermore, a l l computations w i l l be c a r r i e d o u t i n double p r e c i s i o n . 2. S t u d i e s of R a d i a t i o n P r e s s u r e on a R e f l e c t i n g S a t e l l i t e Work i s c o n t i n u i n g on t h e s t u d y t o determine t h e e f f e c t s of t h e new c o n t r o l laws, r e c e n t l y i n s e r t e d i n t o t h e two-dimensional o r b i t a l parameter deck, on t h e o r b i t a l p e r t u r b a t i o n s caused by r a d i a t i o n p r e s sure. 3. Support C o n t r a c t a. Cislunar Orbit Studies The deck designed t o a i d i n minimizing t h e t o t a l v e l o c i t y increment r e q u i r e d t o p r o v i d e o r b i t a l s t a b i l i t y i n c i s l u n a r space has been programmed and t h e check c a s e s a r e being analyzed. �b. I n t e r p l a n e t a r y Trans i t S t u d i e s The c a p a b i l i t y of i n v e s t i g a t i n g a l l c l a s s e s and types on t h e second l e g of a fly-by m i s s i o n t o determine t h e b e s t a v a i l a b l e o r b i t has been added t o t h e Modified Marshall I n t e r p l a n e t a r y Conic T r a j e c t o r y Program; work has now begun on t h e f o r m u l a t i o n of the programming changes n e c e s s a r y t o add powered f l i g h t c a p a b i l i t y t o t h e deck. C. Guidance Theory Branch 1. Support C o n t r a c t S t u d i e s a. Low T h r u s t Guidance The a l t e r e d IGM e q u a t i o n s mentioned l a s t month have been checked f o r a h i g h - t h r u s t (2-D) t r a j e c t o r y w i t h a burn time of 340 seconds. The t h r u s t w i l l be lowered, and t h e r e s u l t i n g t r a j e c t o r i e s w i l l be checked f o r a c c u r a c y of t e r m i n a l c o n d i t i o n s . The a l t e r e d IGM e q u a t i o n s have been extended t o i n c l u d e yaw maneuvers. They have n o t y e t been programmed and checked o u t . b. Power S e r i e s S o l u t i o n f o r I n i t i a l Lagrange M u l t i p l i e r s The a n a l y s i s of a s e r i e s s o l u t i o n f o r t h e i n i t i a l m u l t i p l i e r s f o r t h e c a s e of t r a n s f e r from a f i x e d p o i n t t o a n e l l i p s e w i t h o n l y i t s energy and momentum s p e c i f i e d has continued. As t h e t e r m i n a l c o n d i t i o n e q u a t i o n s a r e expanded i n t o Taylor s e r i e s , i t is n e c e s s a r y t o determine t h e i r a c c u r a c y by observing t h e magnitude of t h e s u c c e s s i v e remainder terms. A program has been w r i t t e n t o e v a l u a t e t h e remainder terms us ing d a t a from a numer i c a l l y i n t e g r a t e d c a l culus-ofv a r i a t i o n s t r a j e c t o r y ; a l s o , p r o v i s i o n has been made t o r e v e r t t h e s e r i e s f o r t i m e - t o - c u t o f f v a l u e s . The energy e q u a t i o n has been expanded and i s now b e i n g t e s t e d . 2. In-house S t u d i e s a . The computer program t o compute optimal continuous t h r u s t o r b i t a l t r a n s f e r s has been coded and checked o u t , and i s now operational. The m o d i f i c a t i o n needed t o compute optimal t h r u s t-coas tt h r u s t o r b i t a l t r a n s f e r s w i l l now be added t o t h e program. b. A b r i e f summary of t h e s t u d i e s performed by MSFC on t h e f l i g h t mechanics and guidance of r e e n t r y v e h i c l e s has been prepared f o r p r e s e n t a t i o n a t t h e NASA Ad Hoc Groups meeting on Reentry Guidance and C o n t r o l . �c. A low t h r u s t o r b i t a l parameter computer program has been formulated and s e n t t o t h e Computation Laboratory f o r coding. This program i s t o be used i n a parameter s t u d y of d e s c e n t i n t o t h e J o v i a n atmosphere. Programming d i f f i c u l t i e s have been encountered, which have delayed t h i s p r o j e c t . d. Work has been i n i t i a t e d , i n s u p p o r t of RPL, on c a l c u l a t ing low t h r u s t t r a n s f e r from E a r t h t o Mars. This s t u d y w i l l r e q u i r e some m o d i f i c a t i o n s of e x i s t i n g computer programs. 3. Contracts a. Boeing - Rendezvous Guidance E v a l u a t i o n of t h e r e l a t i v e c o o r d i n a t e scheme f o r t h e t e r m i n a l burn has continued. Using o n l y t h e p o s i t i o n e q u a t i o n s t o s o l v e a ( t h e c o n s t a n t a n g l e i n t h e X e q u a t i o n ) , we o b t a i n a v a l u e f o r t f and . of t f which i s d i f f e r e n t from t h e tf o b t a i n e d from s o l v i n g t h e f u l l s e t of guidance e q u a t i o n s . As t h e f i n a l burn phase p r o g r e s s e s , i t seems t h a t t h e d i f f e r e n c e s i n t h e t f ' s converge t o some non-zero r e a l number, N, and remain a t N u n t i l t h e f i n a l phase i s over. Close examination of such t r a j e c t o r i e s i n d i c a t e s t h a t the closer N i s t o zero, the smaller the f i n a l end e r r o r i n p o s i t i o n . I n order t o d r i v e N t o zero, a correction scheme was added t o t h e s t e e r i n g e q u a t i o n . This c o r r e c t i o n was K(tmf t f ) , where K i s a predetermined c o n s t a n t . Using t h i s scheme, range a n g l e t o 5 x 1 0 ' ~d e g r e e s . e r r o r s were reduced from 4 x - b. Lockheed - Rendezvous Guidance A phase plane a n a l y s i s of t h e rendezvous guidance problem i s continuing. The r e s u l t i n g guidance law i s being programmed s o t h a t s i m u l a t i o n runs can be made. Work has a l s o begun on a guidance scheme f o r t h e f i r s t - b u r n phase of t h e rendezvous problem. This phase w i l l be used t o p l a c e t h e i n t e r c e p t o r i n a p o s i t i o n f a v o r a b l e f o r rendezvous and s u i t a b l e f o r t h e t e r m i n a l scheme. The energy, a n g u l a r momentum, and o r i e n t a t i o n of t h e t r a n s f e r e l l i p s e w i l l be d e f i n e d i n terms of t h e s t a t e v a r i a b l e of t h e i n t e r c e p t o r and t h e s e p a r a t i o n a n g l e between t h e t a r g e t and t h e i n t e r c e p t o r . This scheme w i l l assume some p r i o r i n f o r m a t i o n conc e r n i n g t h e t e r m i n a l burn. c. Vanderbil t U n i v e r s i t y Because of v a c a t i o n s , l i t t l e p r o g r e s s was made d u r i n g t h e month. M r . L i n n s t a e d t e r continued s t u d y of t h e extended m u l t i s t a g e Bolza problem. D r . Bowman developed a proof of t h e m u l t i p l i e r r u l e and t r a n s v e r s a l i t y c o n d i t i o n s based on t e n s o r and e x t e n s o r theory. �D. O p t i m i z a t i o n Theory Branch 1. Design Concept Comparison Study A s t u d y has been i n i t i a t e d t o compare s e v e r a l promising c o n t r o l systems and t h e i r r e l a t e d s y n t h e s i s t e c h n i q u e s , and t o examine t h e p o s s i b i l i t y of t h e i r a p p l i c a t i o n t o t h e development of a s e t of t o l e r a n t c o n t r o l l e r s f o r the Saturn vehicles. S i x c o n t r o l systems w i l l be s t u d i e d : two load r e l i e f s y s tems, two " t o l e r a n t " systems, and two bending s i g n a l s u p p r e s s i o n systems. The s t u d y w i l l proceed i n two phases. The f i r s t phase w i l l be a d e t a i l e d examination of t h e r e l a t i v e m e r i t s of t h e systems. I n the second phase, t h e r e s u l t s of t h i s work w i l l be a p p l i e d t o t h e p r e s s i n g need f o r f l e x i b i l i t y i n t h e S a t u r n c o n t r o l systems. 2. A p p l i c a t i o n of Optimal Control Theory f o r Design of Load Re1 i e f C o n t r o l The s o u r c e of p r e v i o u s l y r e p o r t e d d i f f i c u l t i e s encountered w i t h t h e computer program developed f o r f i n d i n g optimal f i x e d feedback g a i n s f o r s y s tems w i t h d i s t u r b a n c e i n p u t s has been found and c o r r e c t e d . Some r e s u l t s o b t a i n e d by t h i s method a r e now being e v a l u a t e d . New a t t e m p t s t o use t h e Newton-Raphson technique show t h a t i t i s extremely d i f f i c u l t t o a p p l y t h e method f o r s o l u t i o n of t h i s p a r t i c u l a r problem. The above mentioned program i s s i m p l e r c o m p u t a t i o n a l l y and p r e s e n t s fewer d i f f i c u l t i e s i n a p p l i c a t i o n . F u t u r e e f f o r t s w i l l c e n t e r on use of t h i s method only. 3 . A paper on advanced f l i g h t c o n t r o l techniques f o r launch v e h i c l e s was p r e s e n t e d t o t h e NASA I n t e r c e n t e r Meeting on Control Theory It w i l l a l s o be p r e s e n t e d a t t h e DOD/ h e l d a t MSFC on September 22-23. NASA/FAA Conference on Navigation, Guidance, and Control a t WrightP a t t e r s o n A i r Force Base on October 1 1 - 1 2 . 4. Northrop Schedule Order #26 a. Voyager Load R e l i e f Objective: Saturn V/~oyager. To i n v e s t i g a t e l o a d r e l i e f systems f o r t h e A s y s tem p r e v i o u s l y s t u d i e d by Nor t h r o p f o r a p p l i c a t i o n t o t h e S a t u r n V/LOR i s b e i n g i n v e s t i g a t e d f o r t h e Voyager t o determine i t s l o a d r e l i e f c a p a b i l i t i e s f o r t h i s c o n f i g u r a t i o n . This system i s a d r i f t - m i n i m i z i n g s y s tem which employs feedback of t h e v e l o c i t y normal t o t h e r e f e r e n c e plane. A s t u d y is a l s o being i n i t i a t e d t o determine how i n f o r m a t i o n from t h e guidance p l a t f o r m can most e f f e c t i v e l y be used t o p r o v i d e load r e l i e f . �b. Learning Systems Objective: To determine t h e a p p l i c a b i l i t y of l e a r n i n g s y s tems t o b o o s t e r c o n t r o l and of f - l i n e problem s o l v i n g . A r e p o r t on t h e s t u d y i s being w r i t t e n . It i s concluded t h a t , w i t h one p o s s i b l e e x c e p t i o n , l e a r n i n g s y s tems a r e n o t c u r r e n t l y a p p l i c a b l e t o b o o s t e r c o n t r o l . The one p o s s i b l e p r e s e n t a p p l i c a t i o n i s t h e use of a p e r i o d i c sampling, t o g e t h e r w i t h high-gain n o n l i n e a r t r a c k ing systems s u c h a s some of t h e l e a r n i n g d e v i c e s . This might be s u i t a b l e f o r g a i n s t a b i l i z a t i o n of t h e bending modes. A b r i e f e x c u r s i o n i n t o i n f o r m a t i o n t h e o r y i s being made t o determine i f a p e r i o d i c sampling of t h e type e n v i s i o n e d w i l l s u i t a b l y d e s t r o y t h e bending information t o p r o v i d e a c c e p t a b l e i n p u t i n t o t h e " l e a r n i n g element." c. A n a l y t i c Design Objective: f o r l i n e a r s ys tems . To i n v e s t i g a t e a n a l y t i c d e s i g n techniques A r e p o r t on t h e e v a l u a t i o n of t h e a n a l y t i c d e s i g n technique proposed by Bass and Webber of Hughes A i r c r a f t i s being prepared. Some r e l a t i v e l y minor i n v e s t i g a t i o n s remain t o be conducted. A summary of t h e s t u d y t o d a t e was p r e s e n t e d a t t h e Control Theory Symposium on September 19-21. 5. Honeywell (NAS8-11206) a. Development of T o l e r a n t Control Systems O b j e c t i v e : To develop c o n t r o l l e r s which maximize t h e t o l e r a n c e t o v e h i c l e and environmental parameter v a r i a t i o n s . Candidate c o n t r o l l e r s have been t e s t e d by use of t h e s y n t h e s i s programs i n t h e h i g h dynamic p r e s s u r e r e g i o n of t h e f i r s t s t a g e t r a j e c t o r y . Many c a n d i d a t e s had d i f f i c u l t y i n r e a c h i n g t h e g i v e n load l i m i t i n t h i s r e g i o n f o r Model Vehicle 2. The g o a l s were reviewed, and Future e f f o r t s w i l l more r e a l i s t i c v a l u e s were g i v e n t o t h e c o n t r a c t o r . i d e n t i f y t h e range of c o n d i t i o n s ( t r a j e c t o r y s u b r e g i o n s ) over which a g i v e n c o n t r o l l e r i s adequate. b. Voyager Load R e l i e f O b j e c t i v e : To develop a n e f f e c t i v e load r e l i e f c o n t r o l s y s tern f o r t h e S a t u r n voyager. A meeting was held a t t h e c o n t r a c t o r ' s f a c i l i t y on D i s c u s s i o n c e n t e r e d around t h e e q u a t i o n s of motion and September 6-7. d e t a i l e d s i m u l a t i o n s , and on determining a "worst" wind f o r t h e c l a s s of Implementation of t h e s i m u l a t i o n s i s s l i g h t l y s y s tems being i n v e s t i g a t e d . behind s c h e d u l e . 28 �A c l a s s of s y n t h e t i c winds producing l a r g e r bending moments f o r t h e s y s tems cons i d e r e d t h a n t h e c o n v e n t i o n a l l y employed s y n t h e t i c p r o f i l e has been i s o l a t e d . Whereas t h e conventional p r o f i l e has s h e a r s always i n c r e a s i n g t h e wind from a s m a l l v a l u e t o a l a r g e v a l u e , t h e new c l a s s demonstrates s h e a r r e v e r s a l ; that i s , t h e s h e a r s d e c r e a s e t h e wind magnitude f o r a p e r i o d of time and then s h e a r s a r e i n t r o d u c e d which i n c r e a s e t h e wind magnitude a g a i n . R-AERO-Y personnel were r e q u e s t e d t o determine t h e l i k e l i h o o d of t h i s phenomenon o c c u r r i n g . R-AERO-Y could n o t r e a c h any c o n c l u s i o n s based on t h e i r l i m i t e d s t u d y . However, based on t h e i r d a t a , p e r s o n n e l of t h i s branch decided t h a t t h e p r o b a b i l i t y of occurrence of s u c h a c l a s s of winds e x h i b i t i n g l a r g e s h e a r r e v e r s a l over a l t i t u d e i n t e r v a l s of s e v e r a l hundred meters was s u f f i c i e n t l y low t h a t i t would n o t be used a s a b a s i c d e s i g n wind f o r t h i s study. A more d e f i n i t i v e s t u d y of t h e p r o b a b i l i t y of occurrence of winds w i t h s h e a r r e v e r s a l and of t h e a s s o c i a t e d s h e a r s would probably be u s e f u l f o r f u t u r e load r e l i e f system s t u d i e s . No a c t i o n has y e t been taken t o request such a study. 6. Sys tems Technology, I n c . (NAS8-11419) O b j e c t i v e : To determine t h e 1i m i t a t i o n s of convent konal c o n t r o l systems f o r v e h i c l e s e x h i b i t i n g a l a r g e amount of intermodal coup1 ing . Design of a c o n t r o l system f o r Model v e h i c l e 2 u s i n g conv e n t i o n a l components i s c o n t i n u i n g . Use of a t t i t u d e and a t t i t u d e r a t e s i g n a l s t o s t a b i l i z e bending has been shown t o r e q u i r e some r e l a t i v e l y complex f i l t e r i n g between second and t h i r d modes, whereas b o t h modes can be s t a b i l i z e d w i t h r e l a t i v e l y simple f i l t e r i n g when a high-passed a c c e l e r o m e t e r s i g n a l i s used t o s t a b i l i z e them. The e f f e c t of s u c h a u s e of t h e a c c e l e r o m e t e r on t h e load r e l i e v i n g c a p a b i l i t y of t h e system i s being e v a l u a t e d . VII. DYNAMICS AND FLIGHT MECHANICS DIVISION A. Multi-Projects 1. - Guidance Minimization of Turn Around Time f o r t h e Guidance System f o r Changes i n Vehicles and Missions The bas i c h y p e r s u r f a c e f o r determining t a r g e t i n g v a l u e s f o r t h e t r a n s l u n a r i n j e c t i o n c o n i c i s used t o a r r i v e a t a g e n e r a l i z e d hypersurface f o r the following missions: �(1) Lunar o r deep s p a c e probes. (2) Space-fixed near e a r t h o r b i t s . (3) Earth- fixed o r b i t s (4) Orbits with o r i e n t a t i o n free. (5) D i r e c t a s c e n t rendezvous m i s s i o n s . . The s i g n i f i c a n t d i g i t s of t h e n a v i g a t i o n a l information used i n t h e IGM s t e e r i n g e q u a t i o n s a s w e l l a s t h e f u n c t i o n s i n t e r n a l l y used by IGM have been p a r a m e t r i c a l l y t r u n c a t e d u n t i l t h e system becomes i n d e t e r m i n a t e o r performance and a c c u r a c e a r e s i g n i f i c a n t l y p e n a l i z e d . This s t u d y g i v e s some i n s i g h t i n t o t h e number of s i g n i f i c a n t d i g i t s r e q u i r e d f o r IGM t o perform i n a s a t i s f a c t o r y manner and a l s o i n d i c a t e s how much t h e m i s s i o n can be changed w i t h o u t needing t o r e s c a l e t h e f i x e d p o i n t launch v e h i c l e d i g i t a l computer. The t r u n c a t i o n s a r e being a p p l i e d t o t h e f o l l o w i n g miss i o n s : (1) Near-earth o r b i t s . (2) High energy e a r t h o r b i t s , i n c l u d i n g e a r t h synchronous o r b i t s . (3) Lunar miss i o n s . (4) Typical i n t e r p l a n e t a r y miss i o n s . The n e x t s t e p i n t h e s t u d y w i l l be t o a c t u a l l y program a n I G M s u b r o u t i n e i n f i x e d p o i n t , s c a l e d t o a p a r t i c u l a r m i s s i o n , and determine how much (DAG/Northrop) t h e m i s s i o n can be changed w i t h o u t a s e r i o u s p e n a l t y . 2. Dynamics and Control a. Three-Dimens i o n a l Analysis of Large Launch Vehicles I n c l u d i n g 6 h e l l Degrees of Freedom The e q u a t i o n s of motion have been d e r i v e d s e p a r a t e l y f o r t h e component of t h e s t i f f e n e d s h e l l and i n t e g r a t e d i n t h e X d i r e c tion. These s o l u t i o n s have been combined u s i n g t h e c o n d i t i o n s of cont i n u i t y and e q u i l i b r i u m a t t h e i n t e r s e c t i o n s of t h e s h e l l segment and beams. The r e s u l t i s a s e t of d i f f e r e n t e q u a t i o n s i n terms of t h e d e f l e c t i o n s and r o t a t i o n s of t h e s t i f f e n e r c e n t r o i d a l a x i s . The p e r t i n e n t s o l u t i o n s t o t h i s s e t of e q u a t i o n s y i e l d f o u r a l g e b r a i c e q u a t i o n s (DDS/NO t h~ c o n t a i n i n g t h e frequency of v i b r a t i o n a s a parameter Carolina S t a t e University) . �b. A t e c h n i c a l r e p o r t e n t i t l e d "A Comparison of F l e x i b l e and Rigid Ring B a f f l e s f o r S l o s h Suppression" has been published. The included t e s t r e s u l t s i n d i c a t e that f l e x i b l e b a f f l e s g e n e r a l l y p r o v i d e damping e q u a l t o o r b e t t e r than s i m i l a r r i g i d b a f f l e s , The r a t i o of f l e x i b l e b a f f l e damping t o r i g i d b a f f l e damping i s shown t o v a r y from approximately 2 t o s l i g h t l y g r e a t e r than 1 a s a f u n c t i o n of s l o s h amplitude. The r a t i o i s l a r g e s t f o r low amplitudes. These r e s u l t s a g r e e v e r y w e l l w i t h d a t a p r e v i o u s l y published by Langley. southwest Research I n s t i t u t e ) c. Nonlinear F i l t e r f o r High Frequency Cutoff The f i n a l r e p o r t , "The Nonlinear Cutoff F i l t e r i n t h e S a t u r n V Vehicle w i t h Time Varying C o e f f i c i e n t s ," August 1966, LMSC/ HREC A783123, has been d i s t r i b u t e d . This r e p o r t summarizes t h e r e s u l t s of a n a n a l o g s i m u l a t i o n of t h e S a t u r n V w i t h time v a r y i n g c o e f f i c i e n t s , f l e x i b l e dynamics and t h e n o n l i n e a r f i l t e r over t h e b o o s t e r p o r t i o n of f l i g h t . The system was s u b j e c t e d t o programmed s t e p s i n a t t i t u d e , v a r i a b l e wind d i s t u r b a n c e s , and a d v e r s e bending mode c o n d i t i o n s . I n a l l c a s e s , v e r y s a t i s f a c t o r y performance was achieved, and t h e n o n l i n e a r f i l t e r provided system s t a b i l i t y w i t h extreme changes i n t h e bending c h a r a c t e r i s t i c s , f o r example, s i g n r e v e r s a l i n bending mode s l o p e s . For comparison purposes, s i m u l a t i o n s were a l s o conducted w i t h t h e AS tr i o n i c " des igned 1i n e a r f il t e r i n t h e loop. (~~A/~ockheed) B. Saturn V 1. Mission P r o f i l e - AS-504 I g n i t i o n Time E r r o r s f o r Fixed f3 A s t u d y i s i n p r o g r e s s t o determine i f t h e t a r g e t i n g parameter p ( a n g l e from i g n i t i o n t o t h e nodal c r o s s i n g of i g n i t i o n p l a n e and t r a n s l u n a r p l a n e ) i s a c o n s t a n t mission-dependent i n p u t . A launch azimuth s p r e a d of 7 2 108 degrees i s considered w i t h i n j e c t i o n s f o r t h e f i r s t and second o p p o r t u n i t i e s . P r e l i m i n a r y i n d i c a t i o n s a r e t h a t t h e a n g l e f3 h o l d s c o n s t a n t throughout t h e range o f azimuths, b u t a s l i g h t e r r o r is induced when u s i n g t h e same f3, d e r i v e d from a f i r s t o p p o r t u n i t y l a u n c h , f o r a second o p p o r t u n i t y i n j e c t i o n . Second o p p o r t u n i t y i n j e c t i o n time v a r i a t i o n s due t o t h e c o n s t a n t p average 20 seconds which r e s u l t i n 18 km m i s s - d i s t a n c e a t t h e moon. Midcourse c o r r e c t i o n AV requirements a r e b e i n g determined f o r t h e s e e r r o r s . I n d i c a t i o n s a r e t h a t a c o n s t a n t may be added t o t h e f i r s t o p p o r t u n i t y f3 t o update the a n g l e f o r u s e i n (DA~/~oeing) second o p p o r t u n i t y s i t u a t i o n s - . �2. P r o j e c t I n f o r m a t i o n A p p l i c a b l e t o Many V e h i c l e s S a t u r n V C u r r e n t Performance S a t u r n V performance b a s e d upon August 1966 c u r r e n t v e h i c l e w e i g h t and performance d a t a was computed and t r a n s m i t t e d t o I n d u s t r i a l O p e r a t i o n s . Payload i n c r e a s e s of a p p r o x i m a t e l y 600 pounds o v e r t h e p r e v i o u s month o c c u r f o r v e h i c l e s SA-501 and SA-501 and SA-502. T h i s i n c r e a s e i n performance i s t h e r e s u l t o f u p r a t e d S - I 1 and S-IVB p r o p u l s i o n p e r f o r m a n c e . The S - I 1 and S-IVB p r o p u l s i o n d a t a f o r t h e SA-501 and SA-502 v e h i c l e s a r e based on a c c e p t a n c e d a t a . Payload d e c r e a s e s o f a p p r o x i m a t e l y 1000 pounds i n t h e SA-503 and 600 pounds i n SA-504 and s u b s e q u e n t v e h i c l e s a r e i n d i c a t e d . These payload changes a r e p r i m a r i l y due t o t h e u p d a t e d upper s t a g e p r o p u l s i o n systems and increases i n the vehicles stage i n e r t weights. (DAPIBoeing) C. Saturn I B 1. Mission P r o f i l e AS-208 Guidance R e f e r e n c e R e l e a s e C o r r e c t i o n F u n c t i o n The method proposed f o r t h e AS-2071 208 rendezvous m i s s i o n r e q u i r e s t h e 208 v e h i c l e t o b e launched a t s u c h a t i m e t h a t , when o r b i t a l i n s e r t i o n o c c u r s , i t w i l l b e a g i v e n c e n t r a l r a n g e a n g l e a h e a d of t h e AS-207 v e h i c l e ( w i t h i n t h e i n f l i g h t d i s p e r s i o n s ) . To maintain t h i s range a n g l e , the guidance r e f e r e n c e r e l e a s e time, and, t h e r e f o r e , t h e l i f t o f f time must b e changed t o compensate f o r f l i g h t t i m e v a r i a t i o n s and a s s o c i a t e d downrange d i s p e r s i o n s caused by changes i n t h e t a r g e t p a r a m e t e r s from t h e planned o r nominal v a l u e s . The problem o f d e t e r m i n i n g t h e new g u i d a n c e r e f e r e n c e r e l e a s e time on s h o r t n o t i c e h a s b e e n s o l v e d and g i v e s a n a c c u r a c y w i t h 0.1 s e c o n d s . The d e t a i l s o f how t h i s s o l u t i o n was r e a c h e d h a v e b e e n documented i n O f f i c e Memorandum R-AERO-DAG-33-66. 2. U p r a t e d S a t u r n I C u r r e n t Performance Uprated S a t u r n I performance c a p a b i l i t y based upon September 1966 c u r r e n t v e h i c l e w e i g h t and performance d a t a was computed and t r a n s m i t t e d t o I n d u s t r i a l O p e r a t i o n s . Because o f w e i g h t c h a n g e s , t h e p a y l o a d c a p a b i l i t i e s o f v e h i c l e s SA-205 t h r o u g h SA-208 changed 1-35, -102, -18, and -10 pounds, r e s p e c t i v e l y . A l l v e h i c l e s i n c u r r e d a 16-pound i n c r e a s e i n payload due t o a r e v i s i o n i n b a s e d r a g p r e d i c t i o n . AS-207 p a y l o a d d e c r e a s e d 7 0 pounds a s a r e s u l t o f a m i s s i o n r e d e f i n i t i o n (change i n i n j e c t i o n a l t i t u d e from 1 0 0 n.m. c i r c u l a r o r b i t ) . ( D ~ P / C h r y s l e r ) �3. P r o j e c t Information Applicable t o I n d i v i d u a l Vehicles AS-208: A l l a n a l y s e s have been completed t o provide anL/V Reference T r a j e c t o r y r e f l e c t i n g t h e f i r s t o p p o r t u n i t y f o r AS-208 launch t o rendezvous w i t h AS-207. The r e p o r t documenting t h i s s t u d y should be submitted t o Chrysler r e p r o d u c t i o n on September 30, 1966. The L/V T a r g e t i n g O b j e c t i v e s Proposal document has been r e v i s e d and r e i s s u e d . Based on t h e L/V Reference T r a j e c t o r y , work has been i n i t i a t e d on " P r e l i m i n a r y Abort and Engine-Out S t u d i e s ," and "Launch (DAPIChrysler) V e h i c l e Performance Analysis." D. AAP 1. Mission P r o f i l e a. Electromagnetic Radiation S a t e l l i t e Data showing t h e v i s i b i l i t y times of c e r t a i n s t a r s t o a v e h i c l e i n o r b i t a b o u t t h e e a r t h have been determined. A s t u d y has a l s o been conducted t o determine what s t a r s would be v i s i b l e t o t h e X-ray and photographic equipment w h i l e c e r t a i n s t a r s a r e being observed w i t h t h e gamma-ray equipment. Analysis of t h e d a t a and documentation a r e i n p r o g r e s s . (DAP) b. Solar Pressure Perturbations A computer r o u t i n e has been w r i t t e n and implemented t o c o n t r o l t h e o r i e n t a t i o n of a s a t e l l i t e i n a twelve-hour e q u a t o r i a l o r b i t i n s u c h a way a s t o e l i m i n a t e i n c l i n a t i o n changes. This i s done by c a n c e l l i n g o u t t h e accumulated change every o t h e r o r b i t . During t h e c a n c e l l i n g o r b i t s , t h e component of t h e s o l a r p r e s s u r e f o r c e normal t o t h e o r b i t p l a n e i s made e q u a l b u t o p p o s i t e t o t h a t which i s experienced w i t h t h e nominal o r i e n t a t i o n . (DAP) c. ATM S o l a r E c l i p s e Observation A b r i e f s t u d y i s being made t o determine a n o r b i t which w i l l g i v e simultaneous o b s e r v a t i o n w i t h a ground s t a t i o n of t h e 1970 t o t a l e c l i p s e of t h e sun. The d u r a t i o n of t h e e c l i p s e vs apogee r a d i u s has been c a l c u l a t e d . Other o r b i t a l parameters a r e now being (DAP) cons i d e r e d . �2. Dynamics and Control a. Low g S l o s h S t u d i e s A r e p o r t proposing t o perform low g s l o s h s t u d i e s i n a r o t a t i n g cable-connected S-IVB, SLA combination has been submitted. The s l o s h experiment packages a r e l o c a t e d i n t h e SLAY and a c c e l e r a t i o n l e v e l s a r e v a r i e d by v a r y i n g t h e l e n g t h of t h e c a b l e . Some t y p i c a l parameters of t h e proposed experiment a r e l i s t e d below: Acceleration 0.00036 t o 0.0068 g ' s TankDiameter 6and 12in. Bond Number .67 t o 55. A primary advantage of t h e proposed r o t a t i n g s t a t i o n over n o n r o t a t i n g s t a t i o n s i s t h e a b i l i t y t o measure any d e s i r e d number of c y c l e s of o s c i l l a t i o n w i t h o u t p r o p e l l a n t consumption. Measurement t o t h e dynamic p r o p e r t i e s of t h e r o t a t i n g , cable-connected c o n f i g u r a t i o n i s a l s o proposed. (DDS) b. F e a s i b i l i t y of Providing A r i t i f i c i a l G r a v i t y f o r Crew i n ATM/Orb i t a l Workshop The f e a s i b i l i t y of g e n e r a t i n g a r t i f i c i a l g r a v i t y f o r t h e A T ~ / O r b i t a lWorkshop by s p i n n i n g t h e c o n f i g u r a t i o n a b o u t i t s t e t h e r rod was i n v e s t i g a t e d . Without s p i n n i n g , t h e t e t h e r rod i s a1 igned a l o n g the l o c a l v e r t i c a l , but i f a s p i n r a t e i s applied about the t e t h e r a x i s t h e c o n f i g u r a t i o n becomes u n s t a b l e . T h e r e f o r e , i t i s n e c e s s a r y t o r e o r i e n t the configuration such t h a t the s p i n a x i s i s perpendicular t o the o r b i t a l plane. Such a c o n f i g u r a t i o n was i n v e s t i g a t e d w i t h a s p i n r a t e a p p l i e d t o produce a b o u t 116 g i n t h e crew compartment. It was concluded t h a t a r t i f i c i a l g r a v i t y i s f e a s i b l e i f (1) r e o r i e n t a t i o n of t h e c o n f i g u r a t i o n i s p o s s i b l e w i t h regard t o gimbal and v i s i b i l i t y requirements f o r s o l a r d a t a r e c o v e r y , ( 2 ) f l e x u r a l s t a b i l i t y q u e s t i o n s of t h e boom a r i s i n g from misalignment and s h i f t s of c e n t e r of mass l o c a t i o n s can be r e s o l v e d , and ( 3 ) p h y s i o l o g i c a l e f f e c t s on a s t r o n a u t s due t o a d v e r s e C o r i o l i s f o r c e s a r e a c c e p t e d . c. O r b i t i n g M i r r o r Sumulation The i s r e f l e c t i n g a beam s t u d i e d . .The m i r r o r t h e d i s t a n c e between problem of c o n t r o l l i n g a l a r g e o r b i t i n g m i r r o r t h a t of l i g h t t o a f i x e d p o i n t on t h e e a r t h i s s t i l l being i s c o n t r o l l e d by v a r y i n g i t s c e n t e r of mass t o a l t e r t h e c e n t e r of p r e s s u r e and mass such t h a t r a d i a t i o n �p r e s s u r e and g r a v i t y t o r q u e s a r e used t o c o n t r o l t h e system's a t t i t u d e and r a t e . A l i n e a r combination of s t a t e v a r i a b l e s i s used a s a c o n t r o l law, w i t h a c o s i n e f u n c t i o n modifying t h e c e n t e r of mass displacement command s i g n a l . L i m i t i n g v a l u e s were placed on t h e mass displacement and r a t e of change s o t h a t a more r e a l i s t i c model was obtained f o r s i m u l a t i o n . S e v e r a l o t h e r minor m o d i f i c a t i o n s were made t o t h e d i g i t a l program t o c o r r e c t f o r moment of i n e r t i a v a r i a t i o n s , c e n t e r of l i g h t p r e s s u r e change, and e c c e n t r i c i t y of o r b i t . A systematic search f o r control l a w gains t h a t give s m a l l displacements and a c c e l e r a t i o n s i s b e i n g pursued. I n i t i a l runs i n d i c a t e t h a t s u i t a b l e s t a b i l i t y and c o n t r o l can be o b t a i n e d w i t h a p p r o p r i a t e choice of c o n t r o l g a i n s . A t p r e s e n t t h e p o i n t i n g a c c u r a c y o b t a i n e d g i v e s a maximum d e v i a t i o n of 100 k i l o m e t e r s a b o u t a f i x e d p o i n t on e a r t h . Maximum v a l u e s a r e o b t a i n e d i n morning and evening. F u r t h e r s i m u l a t i o n is expected t o c o r r e c t t h i s e r r o r t o perhaps 1 0 p e r c e n t of t h e above v a l u e . The p r e s e n t p o i n t i n g a c c u r a c y is l i m i t e d by t h e maximum c e n t e r of mass r a t e of change (about one meter per minute) that i s being a 1 lowed. (DCA) d. C y l i n d r i c a l Payload Module S e p a r a t i o n A memorandum p r e s e n t i n g t h e r e s u l t s of t h e RAcK/CPM s e p a r a t i o n s t u d y h a s been d i s t r i b u t e d . R-P&VE-VAW has announced t h a t t h e moments of i n e r t i a they s u p p l i e d f o r t h e s t u d y were i n e r r o r by a f a c t o r of a p p r o x i m a t e l y two. S i n c e t h e moments of i n e r t i a a r e a c t u a l l y l a r g e r t h a n t h o s e used i n t h e s t u d y , 'the d r i f t problem w i l l be a l l e v i a t e d t o t h e e x t e n t t h a t a n a t t i t u d e maneuver d u r i n g t h e e x t r a c t i o n of t h e CPM from t h e RACK probably w i l l n o t be r e q u i r e d . The s t u d y w i l l be redone us i n g t h e c o r r e c t d a t a (DC) . E. General 1. 6-D Response Program The 6-D d i g i t a l response program has been modified t o i n c l u d e m a l f u n c t i o n s s u c h as engine o u t . Problems have occurred i n s i m u l a t i n g t h e p r e s e n t 5-D c o n t r o l system because of h i g h frequency components i n t h e f i l t e r s . The problem has been by-passed w i t h s l i g h t m o d i f i c a t i o n i n t h e t r a n s f e r f u n c t i o n s of t h e f i l t e r s . (DDD) 2. NASA I n t e r c e n t e r Meeting on Control Theory A d i s c u s s i o n on "Research i n C o n t r o l ~ e s i g n "was presented a t t h e I n t e r c e n t e r C o n t r o l Conference. The p r e s e n t a t i o n c e n t e r e d a b o u t t h e a u t o m a t i c g a i n and f i l t e r s y n t h e s i s program. A d e s c r i p t i o n of t h e d e s i g n procedure a l o n g w i t h some of t h e d a t a o b t a i n e d from s e v e r a l checko u t c a s e s was p r e s e n t e d . A s y e t no d e f i n i t e d e c i s i o n can be made 35 �concerning t h e u t i l i t y of t h e procedure a s a p r a c t i c a l s y n t h e s i s t o o l . S i n c e a c e r t a i n amount of e n g i n e e r i n g judgement and i n t u i t i o n i s necessary t o p r o p e r l y s e l e c t f i l t e r p o l e s , t h e procedure i s n o t f u l l y a u t o m a t i c i n i t s p r e s e n t form. (DCA) 3. Reduction of Bending Moment v i a Modern Control Techniques A s t u d y has been completed i n which modern c o n t r o l techniques were a p p l i e d i n t h e d e s i g n of a load r e l i e f c o n t r o l l e r f o r t h e S a t u r n type v e h i c l e . The s t u d y r e s u l t s a r e summarized i n t h e following reports : (1) "The A p p l i c a t i o n of a n Algorithm f o r Optimization of Nonlinear Control Problems t o a Minimax Bending A782451, March 1966, by Moment Study," LMSC/HREC J. F. S o h l e r . (2) "Synthesis of a n Optimal Load R e l i e f Control System," LMSC~HRECA782527, March 1966, by J . N. Dashiell. (3) "Optimal C o n t r o l System t o Minimize t h e I n t e g r a l of Bending Moment Squared w i t h a Terminal S t a t e Weighting Condition," LMSC/HREC A783130, J u l y 1966, by J. N. D a s h i e l l . I n each r e p o r t a c o s t f u n c t i o n i s d e f i n e d which e x p r e s s e s v e h i c l e s t r u c t u r a l l o a d i n g and t e r m i n a l d r i f t , and t h e system e q u a t i o n s a r e f o r m u l a t e d i n t h e s t a t e space n o t a t i o n w i t h t h e n t h o r d e r systems b e i n g d e s c r i b e d by "n" f i r s t o r d e r d i f f e r e n t i a l e q u a t i o n s . Then t h e minimizing c o n t r o l l e r i s s y n t h e s i z e d by d i g i t a l l y s o l v i n g e i t h e r a twop o i n t boundary v a l u e problem o r t h e M a t r i x R i c c a t i d i f f e r e n t i a l e q u a t i o n . I n t h e f i r s t r e p o r t t h e d e r i v e d c o n t r o l was n o n l i n e a r i n t h e s t a t e v a r i a b l e s and minimized t h e maximum d r i f t r a t e f o r the r i g i d body system. I n t h e second r e p o r t a l o a d r e l i e f c o n t r o l l e r f o r t h e v e h i c l e w i t h f l e x i b l e dynamics was s y n t h e s i z e d , b u t no a t t e m p t was made t o minimize t e r m i n a l d r i f t . However, i n t h e t h i r d r e p o r t a c o n t r o l l e r was s y n t h e s i z e d t o minimize b o t h i n - f l i g h t s t r u c t u r a l l o a d i n g and t h e t e r m i n a l d r i f t . Reports 2 and 3 formed t h e b a s i s f o r a p r e s e n t a t i o n a t t h e MSFC C o n t r o l Theory Symposium, September 19-21, 1966. The p l a n t f o r t h e s t u d i e s , Model Vehicle I1 w i t h time .varying c o e f f i c i e n t s over t h e b o o s t phase of f l i g h t , was d i s t u r b e d by t h e MSFC d e s i g n wind p r o f i l e . These s t u d i e s i n d i c a t e t h a t modern c o n t r o l techniques can be used a s a c o n t r o l l e r d e s i g n procedure which can produce a system w i t h d e s i r a b l e c h a r a c t e r i s t i c s i n b o t h load r e l i e f and t e r m i n a l d r i f t . However, t h e more d e s i r a b l e r e s u l t s could o n l y be obtained w i t h a knowledge of t h e e x a c t wind p r o f i l e . �These s t u d i e s i n d i c a t e d that, i f t h e wind d i s t u r b a n c e could b e known b e f o r e l a u n c h , then a b i a s s i g n a l could be added t o t h e feedback s i g n a l t o g r e a t l y reduce v e h i c l e s t r u c t u r a l l o a d s and m a i n t a i n However, any s i g n i f i c a n t d e v i a t i o n from terminal d r i f t specifications t h e d e s i g n wind from which t h e c o n t r o l law was based y i e l d s n e g a t i v e r e s u l t s i n v e h i c l e performance. S i n c e wind s t a t i s t i c s a r e of random n a t u r e , t h e f u t u r e of t h i s type approach w i t h o u t any method of d i s t u r b a n c e p r e d i c t i o n appears limited. (~CA/Lockheed) . VIII. FLIGHT TEST ANALYSIS DIVISION A. Special Projects Office The AS-202 f l i g h t e v a l u a t i o n has been l a r g e l y completed. I n d i c a t i o n s a r e t h a t a v e r y s a t i s f a c t o r y f l i g h t t e s t was o b t a i n e d and t h a t t h e e i g h t f l i g h t anomalies and performance d e v i a t i o n s r e v e a l e d had no e f f e c t on t h e accomplishment of m i s s i o n o b j e c t i v e s . These anomalies and d e v i a t i o n s can b e sunnnarized a s f o l l o w s : 1. Timing f a i l u r e s were experineced by 24 p e r c e n t of t h e e n g i n e e r i n g s e q u e n t i a l cameras r e s u l t i n g i n s e r i o u s impairment of f i l m q u a l i t y . 2. One of two redundant onboard cameras viewing S-IBIS-IVB s e p a r a t i o n was n o t recovered. A camera mounted i n t h e same v e h i c l e p o s i t i o n was l o s t on t h e two previous S a t u r n I B f l i g h t s . The p o s s i b i l i t y of boos t e r l c a m e r a f r e e - f l i g h t t r a j e c t o r y i n t e r s e c t i o n i s being i n v e s t i g a t e d . 3. One of f o u r r e t r o - r o c k e t motors on t h e S-IBIS-IVB i n t e r s t a g e e x h i b i t e d abnormal burning c h a r a c t e r i s t i c s , which i s considered t o b e a random performance d e v i a t i o n . 4. The S-IVB LH2 r e c i r c u l a t i o n s h u t o f f c o n t r o l v a l v e f a i l e d t o c l o s e a s p r o g r a m e d . This m a l f u n c t i o n a l s o occurred on AS-203. 5. A 1.4 m / s c r o s s range e r r o r b i a s was accumulated by t h e guidance s y s tem s h o r t l y a f t e r l i f t o £ f. This d e v i a t i o n was probably due t o s a t u r a t i o n of s e r v o e r r o r s i g n a l s caused by i n i t i a l v e h i c l e v i b r a t i o n e f f e c t on t h e ST-124M p l a t f o r m a c c e l e r o m e t e r s . 6. A t s p a c e c r a f t / b o o s t e r s e p a r a t i o n , t h e s e p a r a t e d S-IV%/IU experienced SPS plume impingement caused by t h e i g n i t i o n sequence o c c u r r i n g t o o soon a f t e r LV/SC s e p a r a t i o n . �B. 7. A probable s h o r t c i r c u i t on t h e o u t p u t s i d e of t h e Q-ball s e r i e s trans i s t o r regulator c i r c u i t resulted i n Q-ball f a i l u r e a f t e r 93.6 seconds of f l i g h t . 8. The S-IVB LOX chilldown pump motor c o n t a i n e r experienced a l o s s of p r e s s u r e d u r i n g countdown which was probably caused by a s e a l leakage. F l i g h t E v a l u a t i o n Branch 1. S a t u r n I.B a. AS-202 Guidance Analysis GLOTRAC d a t a have been r e c e i v e d f o r t h e AS-202 f l i g h t . Comparisons w i t h guidance d a t a i n d i c a t e t h a t t h e p o s t f l i g h t t r a j e c t o r y and GLOTRAC a r e i n good agreement u n t i l a b o u t 420 seconds where GLOTRAC i s l o s t f o r a b o u t 50 seconds. The v e l o c i t y d i f f e r e n c e s between b o t h GLOTMC and t h e r e f e r e n c e t r a j e c t o r y i n d i c a t e t h a t the t o t a l guidance e r r o r s a r e w e l l w i t h i n t h e 3-0 t o l e r a n c e . The problem i n reducing t h e guidance a c c e l e r o m e t e r d a t a has n o t been c o r r e c t e d . Hopefully, a programmer w i l l be o b t a i n e d i n t h e n e a r f u t u r e t o look i n t o t h e d a t a r e d u c t i o n program t o e l i m i n a t e t h e t r o u b l e . The guidance v e l o c i t i e s f o r AS-203 and AS-202 were Lagrange i n t e r p o l a t i o n s of t h e guidance computer o u t p u t s . (1 ) Separation A s p e c i a l meeting of t h e l e v e l I1 c o n f i g u r a t i o n c o n t r o l board was h e l d on September 19. The purpose of t h e meeting was t o determine t h e a d v i s a b i l i t y of extending t h e time from outboard engine c u t o f f (OECO) t o s e p a r a t i o n s i g n a l by .5 second i n o r d e r t o i n c r e a s e t h e p r o b a b i l i t y of s u c c e s s f u l s e p a r a t i o n i n t h e e v e n t t h a t a r e t r o r o c k e t f a i l e d t o i g n i t e . A n a n a l y s i s performed by CCSD on t h e AS-204 con£ i g u r a t i o n i n d i c a t e s t h a t t h e change w i l l i n c r e a s e t h e p r o b a b i l i t y of s u c c e s s f u l s e p a r a t i o n ( r e t r o - o u t ) from approximately 17 t o 95 p e r c e n t . The meeting r e s u l t e d i n a d e c i s i o n t o implement t h i s sequence change on AS-204 and subs. (2) Wind Limits I n f l i g h t wind l i m i t s f o r t h e AS-204 launch v e h i c l e have been e s t a b l i s h e d f o r t h e 5 t o 15 km a l t i t u d e range, based on t h e s t r u c t u r a l c a p a b i l i t i e s of t h e launch v e h i c l e p r e s e n t e d i n Memorandum R-P&VE-SJ-66-183, " S t r u c t u r a l Limits f o r Uprated S a t u r n I, AS-204," �August 23, 1966. These l i m i t s a r e p r e s e n t e d i n terms of a n g l e of a t t a c k , gimbal a n g l e , Mach number and dynamic p r e s s u r e . The e f f e c t s of 99 perc e n t s h e a r s and g u s t and 3-0, C, and C2 v a r i a t i o n s were used t o e s t a b l i s h t h e s e wind l i m i t s . These d i s t u r b a n c e s were a l l combined i n t h e "worst" way t o e s t a b l i s h t h e peak wind l i m i t a s measured by t h e FPS-16I~imsphere system. A t t h e most c r i t i c a l a l t i t u d e (12 km), t h e v e h i c l e i s windl i m i t e d t o 62, 96, and 66 m/sec f o r a head, t a i l , and c r o s s wind, r e s p e c t i v e l y . These r e s u l t s , a s w e l l a s s u r f a c e wind r e s t r i c t i o n s , a r e i n c l u d e d i n Memorandum R-AERO-FF-42-66, "Wind Launch C r i t e r i a f o r AS- 204," September 7 , 1966. (3) Emergency D e t e c t i o n A document, 66-FMP-16, "Emergency D e t e c t i o n System (EDS) and F l i g h t Dynamics Limits," August 15, 1966, c o n t a i n i n g t h e recommended l i m i t s e t t i n g s and a d i s c u s s i o n of t h e f a i l u r e modes f o r v a r i o u s f 1i g h t p e r i o d s has been pub1 ished. 2. Contracts a. S a t u r n I B Sys tems C o n t r a c t (CCSD, New Orleans) CCSD w i l l assume r e s p o n s i b i l i t y f o r e s t a b l i s h i n g t h e i n t e r m e d i a t e (7-day) and f i n a l (14-day) t r a j e c t o r i e s on S a t u r n IB v e h i c l e beginning w i t h AS-204. To s e e i f CCSD had t h e c a p a b i l i t y , i t was decided f o r them t o perform t h i s t a s k on AS-202 a s i f i t were t h e i r r e s p o n s i b i l i t y . CCSD s a t i s f a c t o r i l y e s t a b l i s h e d t h e s e t r a j e c t o r i e s on AS-202 i n a t i m e l y manner. To e s t a b l i s h t h e t r a j e c t o r y r a d a r d a t a from 7 d i f f e r e n t s t a t i o n s , ODOP and GLOTUC S t a t i o n I d a t a were a v a i l a b l e . The f i n a l GLOTUC PVA d a t a were n o t r e c e i v e d i n time t o b e used i n e s t a b l i s h i n g t h e f i n a l t r a j e c t o r y , b u t i t d i d v e r i f y t h e a c c u r a c y of t h e t r a j e c t o r y . I n summary, CCSD proved themselves f u l l y capable and prepared t o assume t h i s r e s p o n s i b i l i t y on t h e remaining S a t u r n IB v e h i c l e s . c. S a t u r n V Sys tems C o n t r a c t (TBC) The Boeing Company was scheduled t o assume a l l t h e p o s t f l i g h t t r a j e c t o r y r e s p o n s i b i l i t i e s on t h e S a t u r n V v e h i c l e beginning It has now been decided t h a t , because of u n c e r t a i n d a t a w i t h AS-504. d e l i v e r y s c h e d u l e s and o t h e r c o n s i d e r a t i o n s , t h e r e s p o n s i b i l i t y f o r t h e p r e l i m i n a r y (48-hour) t r a j e c t o r y w i l l remain inhouse. TBC i s p r e p a r i n g t o assume t h e r e s p o n s i b i l i t y f o r t h e e s t a b l i s h m e n t of t h e i n t e r m e d i a t e (7-day) and f i n a l (14-day) t r a j e c t o r y . Copies of some of t h e computer programs now used by MSFC have been d e l i v e r e d t o TBC, who is developing t h e remainder of t h e programs r e q u i r e d . I n some a r e a s , such a s d a t a e d i t i n g and f i l t e r i n g , TBC has s u f f i c i e n t c a p a b i l i t y , w h i l e i n most of t h e remaining a r e a s , t h e y have no proven c a p a b i l i t y . For TBC t o do a p a r a l l e l e f f o r t beginning on AS-501, c o n s i d e r a b l e work i n most a r e a s is necessary. �C. F l i g h t Mechanics Branch 1. Saturn I B The o p e r a t i o n a l t r a j e c t o r y r e p o r t was d i s t r i b u t e d on September 30 w i t h a n addendum r e f l e c t i n g t h e change i n t h e S-IBIS-IVB s e p a r a t i o n sequence. P a r t s of t h e d i s p e r s i o n a n a l y s i s have been r e c e i v e d from CCSD. The f i n a l d a t a a r e a v a i l a b l e t o t r a j e c t o r y . The S-IB t i l t program and S-IVB IGM have been completed. The S a t u r n I B "block-type" (based on 205 d a t a ) has been documented i n Range 5-66, d a t e d August 26, 1966. generate the operational guidance p r e s e t t i n g s range s a f e t y r e p o r t S a f e t y Data Report No. The p r e l i m i n a r y range s a f e t y a n a l y s i s has been documented i n Range S a f e t y Data Report No. 6-66, d a t e d August 26, 1966. A t t h e August 30, 1966 " t a s k team" meeting, t h e symbols and u n i t s f o r t h e t a r g e t i n g parameters were agreed on. The minutes of t h e meeting a r e documented i n a memo "Minutes of 20718 J o i n t T a r g e t i n g Meeting h e l d on August 30, 1966," dated September 2, 1966. 2. Saturn V (1) An e r r a t a s h e e t prepared by R-AERO-FMT on t h e AS-501 o p e r a t i o n a l t r a j e c t o r y r e p o r t has been g i v e n t o TBC, who i s supposedto s u p p l y R-AERO-FMT w i t h a n o f f i c i a l e r r a t a s h e e t from t h e i r shop t o d i s t r i b u t e w i t h t h e i r o p e r a t i o n a l t r a j e c t o r y r e p o r t . (2) The f i n a l AS-501 range s a f e t y document has been n e g o t i a t e d w i t h TBC, R-AERO-FMT, and t h e P r o j e c t O f f i c e . It was r e s o l v e d t h a t TBC would c o r r e c t t h e i r AS-501 range s a f e t y document t o i n c o r p o r a t e r e v i s e d 3-0 maximum and minimum cases. This document i s now due on October 14, 1966. It was a l s o agreed t h a t t h e AS-503 p r e l i m i n a r y range s a f e t y document would r e f l e c t t h e 3-0 maximum and minimum c a s e s . The due d a t e f o r t h i s r e p o r t was changed t o November 10, 1966. �(3) R-AERO-FMT i s s t i l l a w a i t i n g t h e AS-501 guidance presettings. The f i n a l c o p i e s a r e expected by September 30, 1966. These w i l l b e forwarded t o R-ASTR-NG a s soon a s we g e t them. 3. General The in-house open loop MARVES i s almost complete except A d e t a i l e d check w i t h t h e f o r a problem w i t h p r o p u l s i o n t a p e look-up. open loop B-2 i s b e i n g made t o a s s u r e a complete MARVES s i m u l a t i o n , which h a s been slowed because of l a r g e r e v i s i o n s of t h e IBM flow diagrams. The l o g i c , however, has been programmed and should be checked o u t soon. D. Tracking and O r b i t a l Analysis Branch 1. The aerodynamic f o r c e s a c t i n g on t h e o r b i t i n g AS-204 payload were f u r n i s h e d t o M r . Marcus Meadows of CCSD, who provides s u p p o r t t o R-PSrVE-PT. 2. Aerodynamic f o r c e s and a c c e l e r a t i o n s on t h e S-IVB/LM/CSM con£ i g u r a t i o n f o r P r o j e c t Thermo were f u r n i s h e d t o M r . Nathan, R-AERO-T, f o r o r b i t a l a l t i t u d e s of 125, 150, 175, and 200 n.m. Aerodynamic drag c o e f f i c i e n t s were r e c e i v e d from R-AERO-A f o r t h i s con£ i g u r a t i o n . 3. A memorandum, R-AERO-FT-33-66, e s t a b 1 i s h i n g optimal o r b i t a l azimuths f o r t h e proposed Multiband Camera Experiment, assuming Weslaco, Texas, a s a t a r g e t s i t e , has been d i s t r i b u t e d . 4 . The p r e d i c t e d l i f e t i m e of t h e o r b i t i n g AS-204 S-IVB has been d i s t r i b u t e d i n Memorandum R-AERO-FT-35-66. 5. V a r i a t i o n s i n t h e o r b i t a l plane of SA-lO/Pegasus C and t h e p r e d i c t e d l i f e t i m e of SA-10 have been f u r n i s h e d t o D r . G. Anderson of Bellcam. This i n f o r m a t i o n , r e q u e s t e d t o f u r t h e r p l a n t h e Pegasus C rendezvous m i s s i o n , was t r a n s m i t t e d by l e t t e r t o D r . Anderson on August 30, 1966. 6. A viewgraph has been s u p p l i e d t o M r . G i l l i s of R-AERO-DA f o r a p r e s e n t a t i o n t o M r . Weidner concerning t h e 209/210/211/212/213 m i s s i o n i n t h e unmanned mode. The viewgraph p r e s e n t e d t h e l i f e t i m e of t h e S-IVB f o r v a r i o u s c i r c u l a r a l t i t u d e s assuming t h a t t h e v e h i c l e s t a b i l i z e s due t o t h e g r a v i t y g r a d i e n t b r o a d s i d e t o t h e d i r e c t i o n of mot ion. 7. A j o i n t R-AERO-FT and R-ASTR-IR memorandum p r e s e n t i n g t h e S a t u r n V/Voyager t r a c k i n g and communications c h a r a c t e r i s t i c s f o r v a r i o u s proposed launch azimuths was d i s t r i b u t e d (R-AERO-FT-39-66). �8. M r . R. Benson a t t e n d e d a p r e s e n t a t i o n on the rendezvous w i t h Pegasus C and t h e coupon r e t r i e v a l from t h e meteoroid p a n e l s . This p r e s e n t a t i o n was g i v e n t o NASA Headquarters personnel t o b e t t e r a c q u a i n t them w i t h t h i s proposed experiment b e f o r e s u b m i t t i n g t h e Form 1138 f o r a p p r o v a l of t h i s experiment. R-RP-P p r e s e n t e d t h e o r b i t a l a t t i t u d e of Pegasus C and s t a t e d t h e a t t i t u d e would remain r e l a t i v e l y t h e same w i t h t h e e x c e p t i o n that t h e f l a t s p i n would damp t o a n o s c i l l a t i o n . M r . T e l f e r , R-AERO-DA, p r e s e n t e d performance d a t a on AS-210, t h e proposed rendezvous v e h i c l e . M r . R. Benson p r e s e n t e d t h e o r b i t a l l i f e t i m e of Pegasus C based on t h e l a t e s t o r b i t a l a t t i t u d e . This r e c e n t l y a t t a i n e d a t t i t u d e p r o f i l e i n c r e a s e d t h e p r e d i c t e d o r b i t a l l i f e t i m e by approximately 1100 days. This i n d i c a t e s t h e h i g h degree of dependence of o r b i t a l l i f e t i m e on t h e Pegasus C o r b i t a l a t t i t u d e . Prev i o u s l i f e t i m e p r e d i c t i o n s were based on a randomly tumbling v e h i c l e . 9. An e f f o r t i s underway t o complete t h e Phase "B" s t u d y of p r o j e c t d e f i n i t i o n f o r t h e proposed M u l t i s p h e r e S a t e l l i t e Experiment (Odyssey I ) . 10. The a n g u l a r s e p a r a t i o n a s viewed by Bermuda and S-IVB s t a g e s of AS-501 a f t e r S-111s-IVB s e p a r a t i o n was documented i n Memorandum R-AERO-FT-44-66. This i n f o r m a t i o n was p r e v i o u s l y g i v e n t o I-MO-R. 11. The Sequencing Optimization Automatic Program (SOAP) was s u p p l i e d t o Emerson E l e c t r o n i c s of S t . Louis on September 27, 1966. This program w i l l be used on a n Emerson c o n t r a c t t o Marshall on EVA experiment sequencing. IX. ADVANCED STUDIES OFFICE A. F l i g h t Mechanics and Performance Analysis Group 1. A memorandum summarizing t h e performance c a p a b i l i t i e s of s e l e c t e d c o n f i g u r a t i o n s of t h e S a t u r n V and S a t u r n I B f o r s p a c e s t a t i o n s u p p o r t has been assembled. 2. New c o n t r o l l o g i c f o r t h e mode deck i s b e i n g developed t o p r o v i d e g r e a t e r f l e x i b i l i t y and more r a p i d convergence i n t h e optimizat i o n of p r o p e l l a n t l o a d i n g s f o r two s t a g e v e h i c l e s . 3 . The e x i s t i n g two-dimensional r i g i d body c o n t r o l deck i s being r e v i s e d t o meet t h e requirements imposed by t h e improved S a t u r n The r e v i s e d program w i l l a l l o w b o t h l i q u i d and s o l i d con£ i g u r a t i o n s . motors t o be used i n f l i g h t s i m u l a t i o n . �4. M r . W. D. Goldsby and M r . Ron T o e l l e v i s i t e d t h e Space and I n f orma t i o n Sys terns D i v i s i o n of Ray theon Company t o review work performed under c o n t r a c t NAS8-1107. Raytheon w i l l be a t MSFC on October 26 t o g i v e a p r e s e n t a t i o n on t h e i r p r o g r e s s and proposed f u t u r e work. 5. M r . Don Perkinson a t t e n d e d t h e C o n t r a c t o r (GD/C) O r i e n t a t i o n f o r a Study of Large Space S t r u c t u r e s Experiment f o r U P . R-AERO-XF has been r e q u e s t e d by R-ASTR-A t o s u p p o r t t h e m o n i t o r s h i p and assessment of t h e r e s u l t s of c o n t r a c t NASW-1438 ( F e a s i b i l i t y Study of Space E r e c t a b l e Antennas f o r S/AAP Experiments). 6. A p r e l i m i n a r y m i s s i o n a n a l y s i s f o r a package of exper iments proposed f o r a synchronous o r b i t m i s s i o n (510) has been i n i t i a t e d . R-AERO-XF is working c l o s e l y w i t h R-AERO-DA and R-AERO-FT i n performing t h e t i m e l i n e a n a l y s i s f o r which R-AERO has been g i v e n t h e l e a d . B. Systems Analysis Group S a t u r n Improvement S t u d i e s The f i n a l p r e s e n t a t i o n s of the S a t u r n Improvement S t u d i e s of FY-65 were p r e s e n t e d by t h e c o n t r a c t o r s t o MSFC on October 3 , 4 , and 5 . The c o n t r a c t e d e f f o r t c o n s i s t e d of two phases: Phase I was a t r a d e s t u d y p e r i o d l a s t i n g approximately 6-8 weeks, and Phase I1 c o n s i s t e d of d e t a i l e d d e s i g n s t u d i e s on s e l e c t e d base1 i n e c o n f i g u r a t i o n s t h a t evolved d u r i n g t h e t r a d e s t u d y phase. The s t u d i e s covered b o t h t h e S a t u r n I B and S a t u r n V growth v e r s i o n s . A S a t u r n I n t e r m e d i a t e Range of Vehicle con£ i g u r a t i o n s evolved which cons is t e d of S a t u r n V upper s tages used i n v a r i o u s "ground launchq1 modes. I n g e n e r a l , t h e aerodynamic c h a r a c t e r i s t i c s p r e s e n t e d by Chrys l e r , t h e Boeing Company, and North American were " b e s t e s t i m a t e s " based on T i t a n I11 experimental d a t a and v a r i o u s a n a l y t i c a l approximat i o n s . Advanced Systems O f f i c e and t h e s u b j e c t c o n t r a c t o r s a l l agreed t h a t i f any of t h e s e v e h i c l e s a r e s t u d i e d i n more d e p t h i n t h e f u t u r e , wind t u n n e l t e s t i n g w i l l be necessary. R-AERO-AD concurred. The unknowns r e l a t i v e t o base h e a t i n g of uprated v e h i c l e s u s i n g s o l i d motor s t r a p - o n s have r e v e a l e d t h e need f o r base h e a t i n g R-AERO-AT i s i n v e s t i g a t i n g t h e requirements and r e s o u r c e s tests a v a i l a b l e f o r such a base heating t e s t . . �R e p r e s e n t a t i v e s of R-AERO-AU expressed a need f o r t e s t d a t a i n any f u t u r e in-depth s t u d i e s on c o n f i g u r a t i o n s w i t h s o l i d s t r a p - o n motors. P a r t i c u l a r problem a r e a s a r e where shock waves from s o l i d motor nose cones impinge upon t h e c o r e v e h i c l e . D e t a i l e d f i n a l r e p o r t s of t h e s t u d y e f f o r t can be made a v a i l a b l e t o interested parties. C. As trodynamics and Miss i o n Analysis Group 1. Manned P l a n e t a r y Flyby Missions Based on S a t u r n / ~ p o l l o Sys terns The f i r s t q u a r t e r l y review of t h i s s t u d y i s scheduled t o t a k e p l a c e i n approximately t h r e e weeks. North American A v i a t i o n , t h e m i s s i o n s t u d y c o n t r a c t o r , has j u s t n e g o t i a t e d c o n t r a c t s w i t h AVCO and AiResearch f o r s u b c o n t r a c t s covering s c i e n t i f i c a s p e c t s and l i f e s u p p o r t s y s t e m s , r e s p e c t i v e l y . On October 14, NAA i s having a meeting w i t h t h e i r s i x s c i e n t i f i c c o n s u l t a n t s t o s e l e c t s c i e n t i f i c experiments f o r t h e manned f 1yby miss ions. 2. R-AERO-XA i s c o o r d i n a t i n g and conducting a two t o t h r e e month s t u d y on t h e Mars S u r f a c e Sample Return Probe (MSSR). The probe would be launched from a manned f l y b y s p a c e c r a f t a t some time b e f o r e a r r i v a l a t m r s . The probe a r r i v a l time would be sequenced t o a r r i v e a t Mars ahead of t h e manned s p a c e c r a f t , descend t o t h e Martian s u r f a c e , o b t a i n a s u r f a c e sample, then ascend t o rendezvous w i t h t h e passing s p a c e c r a f t . There a r e s e v e r a l major problem a r e a s a s s o c i a t e d w i t h t h i s problem t h a t r e q u i r e i n v e s t i g a t i o n b e f o r e determining miss i o n f e a s i b i l i t y . R e p r e s e n t a t i v e s from s e v e r a l Aero Laboratory d i s c i p l i n e s a r e p a r t i c i p a t i n g i n t h e s t u d y i n a d d i t i o n t o personnel from R-P&VE, R-ASTR, R-RP, and Northrop Space L a b o r a t o r i e s . �PUBLICATIONS 1. Dalton, Charles C., " E f f e c t s of Recent NASA-ARC Hypervelocity Impact R e s u l t s on Meteoroid Flux and Puncture Models," NASA TM X-53512, September 7 , 1966, U n c l a s s i f i e d . 2. " S t a t i c Aerodynamic C h a r a c t e r i s t i c s of t h e Apollo-Saturn V Vehicles," TM X-53517, September 16, 1966, Vehicle Aerodynamics S e c t i o n , R-AERO-AD, Unclass i f i e d . 3. Smith, Robert E. and 0. N. Vaughan, J r . , "Space Environment C r i t e r i a G u i d e l i n e s f o r Use i n Space Vehicle Development,'%SA TM X-53521, September 22, 1966, U n c l a s s i f i e d . 4. Mull i n s , L a r r y D., "Optimization of Impulsive Hohmann T r a n s f e r s between Non-Coplanar C i r c u l a r O r b i t s , " Aero-Astrodynamics I n t e r n a l Note 15-16, September 20, 1966, U n c l a s s i f i e d . 5. O f f i c e Memorandum R-AERO-Y-114-66, "Cape Kennedy, F l o r i d a , January and J u l y R e l a t i v e D e v i a t i o n s of D e n s i t i e s from t h e P a t r i c k Reference Atmosphere, 1963 f o r S e l e c t e d P e r c e n t i l e Values from t h e S u r f a c e t o 30 km," September 7 , 1966. 6. O f f i c e Memorandum R-AERO-Y-108-66, "Comments on Atmospheric S t a t i s t i c s f o r Voyager," September 8 , 1966. 7. O f f i c e Memorandum R-AERO-Y-119-66, " P r o b a b i l i t i e s of Thunderstorm Occurrences and Associated Ground Winds a t Cape Kennedy," dated September 26, 1966. 8. Young, J. C . , " C r i t i c a l V e l o c i t i e s v s Wind D i r e c t i o n , " R-AERO-AU-66-81, dated September 19, 1966. 9. Wilhold, G. A., " F e a s i b i l i t y of Monitoring S-IVB Forward and A f t S k i r t Panel Areas f o r Evidence of Panel F l u t t e r Phenomena," ~-AERo-Au-66-84, September 22, 1966. 10. Walker, R. W., "uprated Wind Tunnel Data," R-AERO-AU-66-85, September 26, 1966. 11. Beranek, R. G., " P r e t e s t Conference Panel F l u t t e r T e s t y v 1R-AERO-AU-66-89, 12. Walker, R. W . , " P r e d i c t e d F u l l - S c a l e Bending Moment f o r S a t u r n V Empty-On-Pad C o n f i g u r a t i o n w i t h 4 112 p e r c e n t of Damping,'' R-AEROAU-66-92, September 30, 1966. - dated S a t u r n S-IVB Forward S k i r t dated September 2 1 , 1966. �PUBLICATIONS (Continued) 13. R-AERO-DD-57-66, " O f f i c i a l Data f o r AS-503 C o n t r o l System Design." 14. R-AERO-DD-62-66, " S l o s h Damping Device Requirement f o r AS-5011 S-IVB LOX Tank.'' 15. R - A E R O - D D - ~ ~ -"~C~o,r r e c t i o n of AS-502 Dynamic Data.'' 16. R - A E R ~ - D D - ~ ~ - "~S~l o, s h T e s t Requirements i n Low g Environments ." 1r I 17. "The Use o f Wind S h e a r s i n t h e Design of Aerospace V e h i c l e s , " R o b e r t S. Ryan and James R. Scoggins. P r e p a r e d f o r p r e s e n t a t i o n a t t h e 23rd Meeting o f t h e S t r u c t u r e s and M a t e r i a l s P a n e l , AGARD, October 4, P a r i s , Franch. 18. R-AERO-IN-DD-14-66, "Damping P r o p e r t i e s o f Some Polymer Films f o r Spacecraft Structures." 19. R-AERO-DCC-14-66, 20. R-AERO-DC-007-66, " F e a s i b i l i t y of P r o v i d i n g A r t i f i c i a l G r a v i t y f o r Crew i n ATMIOrbital Workshop." "RACKICPMS e p a r a t i o n Study," August 23, 1966. R-AERO-DA-32-66, "Guidance E q u a t i o n f o r S-IVB S t a g e Second Burn f o r SA-501 and Subsequent," September 1 2 , 1966. R-AERO-DA-33-66, " P r e l i m i n a r y Guidance R e f e r e n c e R e l e a s e C o r r e c t i o n F u n c t i o n f o r t h e AS-208 V e h i c l e Based on AS-207 O r b i t a l P a r a m e t e r s , " September 1 5 , 1966. R-AERO-DA-34-66, "Guidance A n a l y s i s f o r t h e S-V AS-502 M i s s i o n , " September 1 6 , 1966. R-AERO-DA-35-66, "Data Format of t h e S-IB E r r o r A n a l y s i s Beginning w i t h t h e AS-2071208 M i s s i o n , " September 1 6 , 1966. R-AERO-DAM-15-66, "Launch Window Study R e p o r t s f o r t h e 20718 Rendezvous Miss i o n . " R-AERO-DAM-16-66, "Data Requested by t h e Payload I n t e g r a t i o n C o n t r a c t o r s i n S p l i n t e r Meetings." R-AERO-DAM-19-66, " S a t u r n V Synchronous O r b i t . " i R-AERO-DAP-76-66, "September C u r r e n t Weights ." �PUBLICATIONS (Continued) 29. R-AERO-DAP-77-66, "Saturn IB September 1966 Current Performance." 30. R-AERO-DAP-78-66, "Saturn V September 1966 Performance ~eport." 31. R-AERO-DAP-79-66, "Saturn I~/ServiceModule Performance to a 200 Nautical Mile Circular Orbit. 32. R-AERO-DAP-80-66, "Launch Vehicle Reference Trajectory Saturn V AS-503 Mission." 33. R-AERO-DAP-81-66, "Verification of Data for AS-503 Performance Analysis." 34. R-AERO-DAP-82-66, "Saturn IB and V Inertial Guidance Platform Realignment Study .. R-AERO-DAP-83-66, "Saturn V Project Able." 35. ." �AERO-ASTRODYNAMICS LABORATORY MONTHLY PROGRESS REPORT O c t o b e r 11, 1966 APPROVAL Aero-As t r o d y n a m i c s L a b o r a t o r y E . D. G e i s s l e r D i r e c t o r , Aero-As t r o d y n a m i c s L a b o r a t o r y DISTRIBUTION R-AERO-D I R Dr. G e i s s l e r M r . Jean R-AERO-P (8) R-AERO-D (16 ) R-AERO-R M r . B u t l e r (4) Mrs. Hightower R-AERO-A (20) R-AERO-G (5) R-AERO- T Mr. M u r p h r e e Mr. Cummings Mr. D i c k e y Dr. Heybey Mr. L a v e n d e r Mr. J a n d e b e u r Dr. Liu Dr. K r a u s e M r . von P u t t k a m e r R-AERO-Y (5) R-AERO-F (8) R-AERO-X (2) R-DIR, Dr. M c C a l l PAO, M r . K u r t z I-V-P, Harold P r i c e � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000047 Title A name given to the resource "Aero-Astrodynamics Laboratory Bimonthly Progress Report: October 11, 1966." Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center Date A point or period of time associated with an event in the lifecycle of the resource 1966-10-11 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) NASA space programs Project management Type The nature or genre of the resource Progress reports Text Source A related resource from which the described resource is derived Saturn V Collection Box 19, Folder 19 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050 https://digitalprojects.uah.edu/files/original/20/995/spc_stnv_000048.pdf 6c86756dd61d4b98b584d3f3d947da52 PDF Text Text Tho Aorojot propoonl for a 1,000,000 pound tilruoe hydrogon oxygen engIno is for e cooiglctely new mgLnr.. l71oy claim that t h e i r d e s i ~ n utilizes to t h e f u l l e o t extent p o o s i b l e praneilt otcate-of-the-art and currently w e d techniques. Tiley have already s tnrtetl design arudiee and 61i)all 0ca1e d~weI-opcwneo f sob= ol tba crnpvnellts mine company Punde - . They e a t i n a c e that 24 munttie acter rlic c o n t r a c t ie let the c n ~ i n ewill be r ~ u ~ lfor y PCRT. D e l i v e r y o f the f i r o t ground tent engine i o estirxited 18 alonthn a f t e r the contract l o ~ i m n l c d . T i ~ i ais a m w i ~ a t optinis . i n cmlpnrioon to our rilanntd lunnr lntldioa otucly results wi~orefnwe e s t i m a t e d 36 rnontho to PFXT t e o t n aid 30 n o n t h o to delivery6& t h e firtat ground t e a t @n,7ineo. S m oi' this 12 wont113 d I f L e r e n c ~m y & be explnjned by t h e pre-cootmct work currently under way a t Acrofet. \ . The F - l engine a o ouch cannot Go adapted t o hydro-en o;cy;en p r e pcflnats. To adapt the F-1 engine to h y d r o ~ c no q g e n would require o mjor redcsian oB e c s c n t i a l l y a l l oE tlis engine crn?oncnts which i n easence reaulte in a now e . ~ g i n s . � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000048 Title A name given to the resource Memo from William A. Fleming to Robert Seamans concerning an "Aerojet proposal for 1,000,000 pound thrust hydrogen oxygen engine." Creator An entity primarily responsible for making the resource Fleming, William A. Seamans, Robert C. United States. National Aeronautics and Space Administration Date A point or period of time associated with an event in the lifecycle of the resource 1961-07-27 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Liquid propellant rockets Saturn Project (U.S.) Hydrogen oxygen engines Saturn 5 launch vehicles Type The nature or genre of the resource Correspondence Text Source A related resource from which the described resource is derived Saturn V Collection University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Is Part Of A related resource in which the described resource is physically or logically included. NASA HQ Miscellaneous Correspondence August 1968 Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050 https://digitalprojects.uah.edu/files/original/20/996/spc_stnv_000049.pdf cf77a09b2dab3ca549ff01ac46eeba9a PDF Text Text AERO-ASTRODYNAMICS LABORATORY BIMONTHLY PROGRESS REPORT December 1968 .January 1969 INDEX Page ............................ I1. PROJECTS OFFICE ........................................... I11. ADVANCED STUDIES OFFICE ................................... A . A s t r o d y n a m i c s a n d M i s s i o n A n a l y s i s G r o u p .............. B . Systems A n a l y s i s Group ................................ C . F l i g h t Mechanics and Performance A n a l y s i s Group ....... I V. AEROSPACE ENVIRONMENT DIVISION ............................ A . Space Environment Branch .............................. B . Atmospheric Dynamics Branch ........................... C . T e r r e s t r i a l Environment ............................... V. AEROPHYSICS DIVISION ...................................... A . Mechanical Design O f f i c e .............................. B . Aerodynamic Design Branch ............................ C . Experimental Aerophysics Branch ....................... D . Thermal Environment Branch ............................ E . Unsteady Gas Dynamics Branch .......................... V I. ASTRODYNAMICS AND GUIDANCE THEORY DIVISION ................ A . O p t i m i z a t i o n Theory Branch ............................ B . Astrodynamics Branch ................................ C . Guidance Theory Branch ................................ DYNAMICS AND FLIGHT MECHANICS DIVISION .................... VII. A . S a t u r n V ............................................... B . S a t u r n Apollo A p p l i c a t i o n s Program .................... C . General ................................................ V I I I . FLIGHT TEST ANALYSIS DIVISION ............................. A . S p e c i a l P r o j e c t s O f f i c e and S t a f f ..................... B . F l i g h t E v a l u a t i o n Branch .............................. C . Tracking and O r b i t a l Analysis Branch .................. D . F l i g h t Mechanics Branch ............................... TECHNICAL AND SCIENTIFIC STAFF 3 4 4 5 6 8 8 11 14 15 15 16 22 26 29 32 32 34 37 39 39 42 50 52 52 53 58 61 �AERO-ASTRODYNAMICS LABORATORY BIMONTHLY PROGRESS REPORT December 1968 I. - January 1969 TECHNICAL AND SCIENTIFIC STAFF J - 2 s Program 1. a. Mission Performance Analysis Two-stage p o l a r o r b i t m i s s i o n d a t a w i t h c h i - f r e e z e mode s i m u l a t i o n a r e being p r o c e s s e d . R e s u l t s a r e expected i n t h e near f u t u r e . Design t r a j e c t o r y w i t h o u t c h i - f r e e z e mode was completed and d i s t r i b u t e d t o t h e a p p r o p r i a t e c o n t r a c t o r s . P o l a r o r b i t m i s s i o n d a t a have been g e n e r a t e d u s i n g d i r e c t i n j e c t i o n and Hohmann t r a n s f e r p r o f i l e s f o r o r b i t a l t i t u d e s of 100, 200, and 300 n a u t i c a l m i l e s . Synchronous o r b i t miss i o n d a t a f o r t h e i n - l i n e J - 2 s v e h i c l e (max. t h r u s t J - 2 s ) have been g e n e r a t e d f o r o r b i t i n c l i n a t i o n s of 28.5" and 55" assuming f i v e r e v o l u t i o n s i n t h e 100 n a u t i c a l m i l e parking o r b i t . An e q u a t o r i a l synchronous o r b i t m i s s i o n , one of t h e b a s e l i n e p r o f i l e s , has been r e l e a s e d . The t r a j e c t o r y f o r t h e l u n a r m i s s i o n w i t h d i r e c t i n j e c t i o n i s complete w i t h a payload of 119,000 pounds a s compared t o 110,000 pounds f o r t h e LOR profile (Few) . b . Rendezvous / IGM Guidance Study Some of t h e more s a l i e n t p o i n t s of t h e s t u d y t h u s f a r a r e a s f o l l o w s . T h r o t t l i n g t o 50,000 pounds t h r u s t can improve weight t o o r b i t above d i r e c t b o o s t . S h o r t range rendezvous ( w i t h i n 180" range from launch s i t e ) provides v e r y s m a l l launch windows ( 1 t o 3 min) w i t h IGM c u r r e n t l y formulated can r e l a t i v e l y l a r g e performance p e n a l t i e s . handle moderate c o a s t (300 seconds) w i t h r e v i s e d mission-dependent cons t a n t s , and can a l s o handle t h r o t t l i n g b o o s t p r o f i l e s w i t h moderate range a n g l e s (burn a r c s ) . Three forms of time-to-go e q u a t i o n s i n IGM have been i n v e s t i g a t e d f o r rendezvous w i t h t h r o t t l i n g . The most promising form, which uses launch v e h i c l e and s a t e l l i t e p o s i t i o n and a c c e l e r a t i o n s , has n o t been t e s t e d w i t h lower s t a g e d i s p e r s i o n s . 2. A manuscript e n t i t l e d , "Determination of Meteoroid N a t u r a l Environments from Photographic Meteor Data," has been completed. This i s a r e s u l t of a n o p e r a t i o n s - r e s e a r c h type of e v a l u a t i o n of a l t e r n a t i v e t h e o r e t i c a l and e m p i r i c a l r e s u l t s f o r the physics of meteor f l i g h t i n t h e atmosphere. A p r e l i m i n a r y n e c e s s i t y was t o c o n s t r u c t a mathematical model f o r s e t h e t h e o r e t i c a l r e s u l t s which were published i n 1958 by D r . E r n s t J . Opik from t h e Armagh Observatory i n Northern I r e l a n d . Meteor �luminous e f f i c i e n c y i s t h e r a t i o of the a i r - e n t r y k i n e t i c energy of t h e meteoroid and t h e i n t e g r a t e d luminous i n t e n s i t y of t h e consequent meteor. The c e n t r a l problem was t o determine whether t h e mode-result f o r t h e velocity-and-mass dependence of meteor luminous e f f i c i e n c y was more o r l e s s p l a u s i b l e than any model p r a p o r t i o n a l t o t h a t which is presupposed i n t h e mass s c a l e , which has been used by t h e Harvard Meteor P r o j e c t s i n c e 1438. The a n a l y s i s , c o n t r a r y t o r e c e n t s t u d i e s by D r . Franco V e r n i a n i a t t h e Smithsonian A s t r o p h y s i c a l ObservaLory, shows t h a t , w i t h a c t u a l meteor s t a t i s t i c s , t h e 1958 newer work by Opik is more p l a u s i b l e t h a n t h e 1938 Harvard model, which was bgsed on t h e 1931 o l d e r r e s u l t s , a l s o by g p i k . The consequence is t o i n c r e a s e t h e c a l c u l a t e d v a l u e s of t h e k i n e t i c energy and t h e mass of a f a s t meteor. (Dalton) 3. Experimentation is planned a t MSFC t e s t s i t e s t o measure nearground winds b o t h by tower-mounted anemometers and by a crossed-beam system combining a s i n g l e beam w i t h a multiple-beam d e t e c t o r . A TM X was prepared i n which t h e p e r t a i n i n g beam geometry is s t u d i e d , i t s range of p h y s i c a l a p p l i c a b i l i t y i s examined, and a f i n a l proposal is made f o r a n optimum d e t e c t o r arrangement d e s t i n e d t o observe h o r i z o n t a l winds a t s e v e r a l h e i g h t s s i m u l t a n e o u s l y . . Also, work has been i n p r o g r e s s on a s u i t a b l e single-beam (Heybey) d e t e c t o r l a y o u t f o r measuring non-horizontal winds. 4. Transformations Between D i f f e r e n t Fundamental P l a n e s For many a s t r o n a u t i c a l i n v e s t i g a t i o n s , i t i s n e c e s s a r y t o r e f e r t h e o r b i t of a s p a c e c r a f t , o r a n a t u r a l o r a r t i f i c i a l s a t e l l i t e n o t o n l y t o t h e e q u a t o r i a l p l a n e of i t s ~ g n t r a lp l a n e t b u t a l s o t o t h e o r b i t a l plane of t h e p l a n e t , o r t h e e c l i p t i c , or t h e c e l e s t i a l e q u a t o r , o r even t h e f i x e d , p r o p e r , L a p l a c i a n p l a n e of t h e s a t e l l i t e . When a l l t h e s e fundamental p l a n e s a r e p r o j e c t e d on the c e l e s t i a l s p h e r e , t h e r e a r e 19 s p h e r i c a l t r i a n g l e s . To h e l p t h e a s t r o n a u t i c a l m i s s i o n p l a n n e r , a s y s t e m a t i c c a t a l o g u e has been s e t up which g i v e s 30 independent r e l a t i o n s f o r each of t h e 19 s p h e r i c a l t h i a n g l e s , o r a t o t a l of 570 e q u a t i o n s . Addit i o n a l l y , 5 r e l a t i o n s between d i f f e r e n t i a l s a r e g i v e n f o r each s p h e r i c a l t r i a n g l e , o r a t o t a l of 95 r e l a t i o n s . A t f i r s t , i t was n e c e s s a r y t o f i n d a l s o a s y s t e m a t i c way t o d e s i g n a t e (symbols) t h e q u a n t i t i e s appearing i n t h e many s p h e r i c a l t r i a n g l e s . A t p r e s e n t , i n c l i n a t i o n s and l o n g i t u d e s of nodes, a s w e l l a s t h e i r time r a t e s , a r e compiled f o r t h e d i f f e r e n t p l a n e t a r y and n a t u r a l s a t e l l i t e systems i n our s o l a r system. It is planned t o c a l c u l a t e t h e s e q u a n t i t i e s , r e f e r r e d t o the other reference planes. (Krause) �11. PROJECTS OFFICE 1. The f i f t e e n t h meeting of the Saturn/Apollo F l i g h t Limits subP a n e l (of t h e F l i g h t Mechanics P a n e l ) was h e l d a t MSFC on January 17, 1969. During t h e meeting, two changes f o r AS-504's manual a b o r t l o g i c were recommended. F i r s t change: Use 5 " p i t c h o r yaw a t t i t u d e e r r o r as a f i r s t cue d u r i n g t h e S-IC f l i g h t phase. This provides a n e a r l y cue f o r t h e l o s s of a t t i t u d e e r r o r s i g n a l malfunction. The second a b o r t cue w i l l be t h e d e l t a P i n d i c a t o r . A 5 " r o l l e r r o r w a s a l r e a d y planned a s a f i r s t cue mainly f o r an a c t u a t o r hardover f a i l u r e . Second change: F o r a n S - I C c o n t r o l engine o u t b e f o r e 50 seconds, i g n o r e d e l t a P a s an a b o r t cue. Recent a n a l y s e s i n d i c a t e d t h a t w i t h an S-IC c o n t r o l engine o u t b e f o r e 50 seconds, it i s p o s s i b l e t o exceed t h e d e l t a P l i m i t s (3.2 p s i ) and n o t l o s e c o n t r o l o r exceed t h e s t r u c t u r a l limit. T h e r e f o r e , w i t h o u t t h i s change, i t was p o s s i b l e t o g e t f a l s e a b o r t i n d i c a t i o n s . There a r e no a d d i t i o n a l r i s k s a s s o c i a t e d w i t h t h i s change, s i n c e , a f t e r tower c l e a r a n c e , an engine o u t b e f o r e 50 seconds does n o t r e s u l t i n an a b o r t requirement d u r i n g the max q r e g i o n . The Crew S a f e t y Panel has o f f i c i a l l y approved t h e s e recommendations. D e t a i l e d minutes of t h e meeting a r e documented i n memorandum R-AEROP-S- 2-69. 2. A l t e r n a t e and backup missions f o r t h e AAP CORE program have been i d e n t i f i e d and r e s u l t s p r e s e n t e d t o t h e Mission Requirements Panel. Plans i n c l u d e r e t a i n i n g t h e c a p a b i l i t y f o r f l y i n g a backup CSM/LM/ATM decoupled m i s s i o n i n t h e e v e n t of workshop f a i l u r e and d e l a y i n launching t h e backup workshop. I n a l l c a s e s , however, t h e AAP hardware is used t o o b t a i n , e v e n t u a l l y , t h e c l u s t e r m i s s i o n whereby t h e workshop i s used i n s u p p o r t of t h e astronomy m i s s i o n . The r e s u l t s of t h i s a n a l y s i s a r e t o be p r e s e n t e d a t t h e n e x t b a s e l i n e meeting. 3 . A s t u d y of c o n t r o l l e d r e e n t r y f o r t h e AAP c l u s t e r hardware h a s been completed and r e s u l t s forwarded t o h e a d q u a r t e r s . The s t u d y was performed t o determine t h e f e a s i b i l i t y of c o n t r o l l i n g t h e impact t o a s s u r e p r e v e n t i n g land impact f o r t h e AAP hardware a f t e r t h e AAP-314 m i s s i o n i s completed. R e s u l t s showed t h a t e i t h e r ( a ) a r e t r o - s y s t e m weighing about 4000 pounds o r ( b ) a l i g h t e r system designed f o r operat i o n up t o 600 days a f t e r launch w i t h t h e a t t i t u d e c o n t r o l system and o t h e r onboard systems' l i f e t i m e s i m i l a r l y extended would be n e c e s s a r y . It was concluded t h a t c o n t r o l l e d r e e n t r y f o r t h e AAP c l u s t e r hardware i s impractical . �4. Headquarters has approved t h e p l a n s f o r SPS i n s e r t i o n f o r t h e manned AAP 1, 3A, and 3 v e h i c l e s . his technique improves t h e payload c a p a b i l i t y f o r t h e s e v e h i c l e s by a b o u t 2500 pounds. his improvement s o l v e s t h e b a s i c payload problem b u t does n o t e l i m i n a t e t h e t o t a l problem because o i t h e l i m i e a t i o h s impdsed on t h e CM by t h e paracljutehung ,weight. During a b o r t , t h e CM i s a t t h e parachute l i m i t of 13,000 he weight Bnd volume l i m i t a t i o n s of t h e CM a r e producing pounds. s e r i o u s s t o r a g e brobleins e s p e c i a l l y f o r t h e 56-day AAP 3A and 3 v e h i c l e s . A. A s trodynamics and M i s s i o n Analysis Group , Miss i o h d e s i g n c h a r t s f o r e a r t h - d e p a r t enkrgiqd ~ u h i t e r passage d a t e s and d i s t d d c e s , ~ a t d r r ipadsdge coriditions, an8 ~ l u t o a r r i v a l d a t e s have been com$leted, Theiie e h a r t s and t r ~ j e c t a r yd a t a a r e being prepdred f o r documentation. + 2. Saturn V FSSI~PS~ n t e g r a t i o nStudy A mid- term review of t h e "Saturn V Future Space S t a t i o n / Nuclear-Thermal E l e c t r i c Power Systetn h t e g r a t i o n sttidyti Qas p r e s e n t e d on December 11, 1968; A model f o r t h e rekctor-induced r a d i a t i o n e d i r o n m e n t about t h e s p a c e s t a t i o n , which has been .teceived from Atoinics I h t e t n a t i o n a l C o r p o r d t i o n , i s b e i n g uhed t o ifikbki-8ke t h e t o & I r a d i a t i o n dbde i n c u r r e d along t h e v a r i o u s &emote experimeht module placement and r e t t i e v a l t r a j e c t o r i e s . The p o s s i b i l i t y 04 u s i n g t r a j e c t o r i e s f o r o b t - o f - o r b i t - p l a n e remote experiment module pldkemeht i s being i n v e s t i g a t e d . A p a r a m e t r i c a n a l y s i s f o r v a r i o u s types of t r a j e c t o r i e s v i t h r e s p e c t t o AV budget; t r i n k f e r time, and r a d i a t i o n dose is a l s o being conducted. A f i n a l review of t h e s t u d y ks scheduled f o r mid-March 1969. 3. ITCC Meeting The s e v e n t h mekting of t h e NASA I n t e r p l a n e t a r y T r a j e c t o r y Coordinating Committee was h e l d December 4 and 5 , 1968, a t ~ a n ~ l e ~ Research C e n t e r . The minutes of t h i s meeting a r e a v a i l a b l e . �4. Computer Program Development A matched conic computer program has been developed which matches t h e p l a n e t o c e n t r i c h y p e r b o l i c t r a j e c t o r i e s w i t h t h e h e l i o c e n t r i c t r a j e c t o r y a t t h e s p h e r e of i n f l u e n c e . The program provides p r e l i m i n a r y d a t a f o r communication d i s t a n c e s and o r i e n t a t i o n a n g l e s f o r i n t e r p l a n e t a r y m i s s i o n s , and good i n i t i a l c o n d i t i o n s f o r t h e JPL "Space Tra j e c t o r i e s Program." B. Systems Analysis Group 1. I n t e g r a l Launch and Reentry Systems I n t e g r a l Launch and Reentry Systems (ILRS) s t u d y c o n t r a c t s have been f i n a l i z e d . MSFC has two c o n t r a c t s under i t s d i r e c t i o n : (1) Lockheed M i s s i l e s and Space Company of Sunnyvale, C a l i f o r n i a , and (2) General Dynamics Convair of San Diego, C a l i f o r n i a . MSC has North American Rockwell Corporation of Downey, C a l i f o r n i a , under c o n t r a c t and Langley Research Center has M c ~ o n n e l l / ~ o u g l aCs o r p o r a t i o n of S t . Lous, M i s s o u r i . O r i e n t a t i o n f o r t h e MSFC c o n t r a c t o r s b e g i n s February 18, 1969. The s t u d y p e r i o d has been compressed from e i g h t t o s i x months. Data from t h e ILRS s t u d y a r e t o be f e d i n t o t h e Phase B s t u d y of t h e 1975 Space S t a t i o n . A follow-on s t u d y is t o be l e t immediately a f t e r t h e c u r r e n t ILRS s t u d y is completed. A meeting w i l l be s e t up between t h e c o n t r a c t o r s and MSFC r e p r e s e n t a t i v e s a t t h e February 1 8 c o n t r a c t o r o r i e n t a t i o n . 2. Launch Vehicles The f i r s t review of t h e "Saturn V D e r i v a t i v e (S-1C/S-IVB) Launch Vehicle Systems Study" (NAS8-30506)was h e l d a t MSFC on J a n u a r y 16, 1969. The r e s u l t s r e p r e s e n t e d t h e Phase I t r a d e s t u d y p o r t i o n c o n s t i t u t ing approximately 15 p e r c e n t of t h e t o t a l e f f o r t . The o b j e c t i v e of t h i s phase of t h e s t u d y was t o provide t r a d e d a t a f o r t h e s e l e c t i o n of a basel i n e INT-20 launch v e h i c l e c o n f i g u r a t i o n f o r t h e Phase I1 p r e l i m i n a r y d e s i g n . The t r a d e s included t h e number of engines i n t h e f i r s t s t a g e , s e r i e s of S-IVB s t a g e , s e r i e s of I U , payload envelope, and t h e a x i a l a c c e l e r a t i o n l i m i t . The t e c h n i c a l panel managing t h e c o n t r a c t s e l e c t e d (1) f o u r a v e h i c l e f o r t h e d e s i g n phase w i t h t h e s e c h a r a c t e r i s t i c s : F-1 engines i n t h e S-IC s t a g e , (2) 500 s e r i e s of S-IVB s t a g e and IT, (3) a c a p a b i l i t y of 4 - 6 8 g ' s w i t h a 1 . 4 f a c t o r of s a f e t y , and ( 4 ) t h e payload envelope c o n s i s t i n g of a double a n g l e MLV nose cone and a 43-foot c y l i n d r i c a l s e c t i o n . The s e l e c t e d c o n f i g u r a t i o n w i l l p l a c e 132,000 pounds i n t o a 1 0 0 - n a u t i c a l - m i l e c i r c u l a r o r b i t (payload d e n s i t y of 16.3 l b s / f t 3 ) and is designed t o f l y through March winds. The �b a s e l i n e v e h i c l e i s a l s o capable of c a r r y i n g a 68-foot c y l i n d r i c a l s e c t i o n (payload d e n s i t y of 7.8 l b s / f t 3 ) f l y i n g through t h e August synthetic profile. C. F l i g h t Mechanics and Performance Analysis Group I. Launch Vehicle The f o l l o w i n g memoranda on performance were published during t h i s period: (a) R-AERO-X-68-43, "Performance and T r a j e c t o r y Data f o r t h e T i t a n I I I D Vehicle," December 1 2 , 1968. (b) R-AERO-X~68-44, "Performance and T r a j e c t o r y Data f o r t h e T i t a n I I I C Vehicle," December 20, 1968. (c) R-AERO-X-69-1, "Performance gnd T r a j e c t o r y Data f o r t h e T i t a n IIIM Vehicle," J a n u a r y 1, 1969. Performance d a t a now being g e n e r a t e d f o r t h e T i t a n I I I D Agena and t h e T i t a n IIID-Centaur w i l l be documented l a t e r . 2. S a t u r n V Workshop The Bo concept ( t h e u s e of t h e wet workshop backup a s a d r y workshop launched on a S a t u r n V), which was p r e s e n t e d t o D r . von Braun on December 13, 1968, i s being documented. From t h i s meeting evolved the concept of t h e S a t u r n V c l u s t e r m i s s i o n , a g r o u n d - f i t t e d S-IVB workshop launch on a S a t u r n V and l a g i s t i c a l l y supported w i t h S a t u r n I B f l i g h t s . This was conceived a s a replacement f o r t h e core program. It was p r e s e n t e d go D r . Lucas pn January 29, 1969, and i s t o b e completed and p r e s e n t e d t o D r . von Brgun on February 26, 1969. Four p o s s i b l e m i s s i o n p r o f i l e s were g e n e r a t e d . F i r s t considered was t h e p o s s i b i l i t y of u s i n g a BL I1 CSM t o t a k e t h e crew up and then r e t u r n t h e f o l l o w i n g day w i t h t h e p r e v i o u s crew, I n t h i s method of o p e r a t i o n , t h e f i r s t BL I1 CSM is thrown away, and t h e l a s t crew d e o r b i t s i n a r e t u r n module t h a t was brought up w i t h t h e workshop on t h e S a t u r n V. There a r e two major d i s a d v a n t a g e s t o t h i s method of o p e r a t i o n : F i r s t , s h o r t pad turn-around time i s r e q u i r e d , and second, i f a crew must r e t u r n e a r l y , they have t o use t h e r e t u r n module intended f o r t h e t h i r d crew and t h e e n t i r e m i s s i o n i s the'reby a b o r t e d . This problem is a l l e v i a t e d i f , i n s t e a d of a BL I1 CSM, a modified CSM i s useg, t h e major m o d i f i c a t i o n being t h e i n s e r t i o n of q s o l i d r e t r o - p a c k between t h e command and s e r v i c e module. This gllows t h e s e r v i c e module w i t h i t s l i m i t e d l i f e t i m e t o be d i s c a r d e d a f t e r docking w i t h t h e workshop. S i n c e t h e crews r e t u r n i n t h e command module that took them t o o r b i t , t h e ~ ei s no requirement f o r crew o v e r l a p , and t h e crews may be spaced as d e s i r e d . �I n each of t h e s e m i s s i o n p r o f i l e s , t h e LM/ATM i s brought up by a S a t u r n I B launched a f t e r t h e t h i r d crew, and an unmanned rendezvous and dock a r e done w i t h t h e LM. The o t h e r two m i s s i o n s ' p r o f i l e s e l i m i n a t e t h e need f o r t h i s e x t r a f l i g h t and the LM by launching t h e ATM a s p a r t of t h e workshop on the S a t u r n V. There is a p o s s i b i l i t y of a d e c i s i o n soon concerning t h i s configuration. 3. Nuclear This o f f i c e has been r e q u e s t e d by R-AS-MP t o a s s i s t i n a S a t u r n nuclear launch v e h i c l e f l i g h t s a f e t y s t u d y f o r SNPO. The c a p a b i l i t y , i n c a s e of an a b o r t a f t e r d e p a r t u r e from c i r c u l a r o r b i t , of t h e n u c l e a r s t a g e t o i n j e c t onto a n i n t e r m e d i a t e e l l i p s e f o r a twoyear minimum l i f e t i m e i s being analyzed. 4. Unmanned P l a n e t a r y Performance d a t a f o r s e v e r a l p o s s i b l e Grand Tour m i s s i o n launch v e h i c l e c o n f i g u r a t i o n s have been g e n e r a t e d . The S a t u r n V p e r formance was based on t h e SA-502 launch v e h i c l e which i n c o r p o r a t e s J - 2 s engines i n t h e upper s t a g e . The c o n f i g u r a t i o n s s t u d i e d included t h e b a s i c S a t u r n V, S a t u r n VINuclear, S a t u r n V/Service Module, S a t u r n V/ Centaur, and t h e S a t u r n V w i t h an assumed s p a c e c r a f t p r o p u l s i o n system used f o r i n j e c t i o n . The INT-20/Service Module and I N T - 2 0 / ~ e n t a u r c o n f i g u r a t i o n s were a l s o s t u d i e d , w i t h t h e e f f e c t s of i n c l u d i n g t h e 3 - 2 s engine i n t h e S-IVB being determined f o r b o t h c o n f i g u r a t i o n s . 5. Launch Vehicle T r a j e c t o r y Optimization Computer Program With o n e - t h i r d of t h e c o n t r a c t p e r i o d f i n i s h e d , work b e i n g done by Northrop on t h e Launch Vehicle T r a j e c t o r y O p t i m i z a t i o n Computer Program (Phase IV) i s p r o g r e s s i n g v e r y w e l l ; i t looks now a s i f we w i l l g e t a l l t h a t was expected from t h e c o n t r a c t . 6. ROBOT The ROBOT t r a j e c t o r y o p t i m i z a t i o n program has been modified t o g r e a t l y reduce t h e p r i n t o u t . This r e s u l t s i n s u b s t a n t i a l s a v i n g s i n computer paper and time r e q u i r e d f o r p r i n t i n g t r a j e c t o r i e s r u n f o r t h i s o f f i c e by t h e Computation Laboratory, �IV. AEROSPACE ENVIRONMENT DIVISION A, Space Environment Branch 1. Atmospheric Model S t u d i e s The d e t a i l e d s t u d y program f o r t h e development of an improved upper atmospheric model is c o n t i n u i n g , C u r r e n t s t u d i e s i n s u p p o r t of t h i s program a r e b o t h s t a t i s t i c a l and t h e o r e t i c a l . I n t h e s t a t i s t i c a l s t u d i e s , drag-determined d e n s i t i e s from 64 s a t e l l i t e s a r e being used t o develop r e g r e s s i o n e q u a t i o n s t h a t d e f i n e t h e atmospheric d e n s i t y i n terms of e x o s p h e r i c temperature ( c a l c u l a t e d from ~ a c c h i a ' se q u a t i o n s ) a t d i s c r e t e a l t i t u d e l e v e l s from 140 t o 350 km. S i m i l a r equatiohd w i l l a l s o be e s t a b l i s h e d f o r a l t i t u d e l e v e l s below 140 km u s i n g c l a s s i f i e d , l o w - a l t i t u d e , A i r Force s a t e l l i t e drag d e n s i t y d a t a and i n f o r m a t i o n t h a t might be i n f e r r e d from t h e a l t i t u d e dependency of t h e r e g r e s s i o n c o e f f i c i e n t s obtained i n t h e above 140 km s t u d i e s . These e q u a t i o n s w i l l be used t o develop a aiodel of t h e atmospheric mass d e n s i t y from 90 t o 1000 km a l t i t u d e , The new model w i l l provide p r e d i c t i o n s of atmospheric d e n s i t y t h a t a r e i n b e t t e r agreement w i t h s a t e l l i t e drag d e n s i t i e s than t h e p r e d i c t i o n s obtained from c u r r e n t atmosp h e r i c models. These s t u d i e s a r e being conducted j o i n t l y w i t h in-house NASA e f f o r t and under Lockheed M i s s i l e s and Space Company c o n t r a c t NAS8-30513. The s t a t i s t i c a l s t u d i e s d i s c u s s e d i n t h e above paragraph w i l l r e s u l t i n an improved atmoepheric d e n s i t y model, b u t t h e y w i l l not provide i n f o r m a t i o n r e l a t F v e t o atmospheric temperature and chemical composition. To o b t a i n t h i s i n f o r m a t i d n , v a r i o u s t h e o r e t i c a l s t u d i e s a r e being conducted t o e s t a b l i s h a model atmosphere t h a t w i l l be cons i s t e n t w i t h t h e mass d e n s i t i e s of the model d i s c u s s e d above and t h a t w i l l a l s o be i n agreement w i t h e x i s t i n g temperature and chemical comp o s i t i o n measurements. I n one s u c h s t u d y , a new technique f o r c a l c u l a t i n g t h e temperature and O2 and 0 number d e n s i t i e s t h a t should be a s s o c i a t e d w i t h measured N 2 d e n s i t y p r o f i l e s has been e s t a b l i s h e d . The technique has been a p p l i e d t o M2 p r o f i l e s obtained from s i x M a r s h a l l / u n i v e r s i t y of Mighican Probes (MUMP) t h a t were launched i n s e r i e s from Cape Kennedy on January 24, 1967. The c a l c u l a t e d O2 and 0 number d e n s i t i e s a r e i n e x c e l l e n t agreement w i t h o t h e r e x i s t i n g mass s p e c t r o m e t e r and a b s o r p t i o n s p e c t r o m e t e r measurements. The newly developed technique and t h e r e s u l t ing atmospheric i n f o r m a t i o n a r e d i s c u s s e d i n a paper e n t i t l e d , "Diurnal y V a r i a t i o n i n t h e Thermosphere from a S e r i e s of ~ a r s h a l l / ~ n i v e r s i tof Michigan Probes." The paper has been s e n t t o t h e J o u r n a l of Geophyeical Research f o r p u b l i c a t i o n . �~ a c c h i a ' sexospheric temperature equations a r e being mod i f i e d t o make them more c o n s i s t e n t w i t h e x o s p h e r i c t e m p e r a t u r e s t h a t have b e e n o b t a i n e d from t h e MUMP program. When e s t a b l i s h e d , t h e s e e q u a t i o n s w i l l be used i n c o n j u n c t i o n w i t h t h e improved d e n s i t y model t o c a l c u l a t e atmospheric chemical composition. R e s u l t s from a l l o f t h e s e w i l l b e used t o e s t a b l i s h a n improved dynamic upper a t m o s p h e r i c model. The f i n a l v e r s i o n of t h i s model w i l l d e f i n e t h e a t m o s p h e r e from 90 t o 1000 km a l t i t u d e and w i l l n o t b e l i m i t e d b y c o n s t a n t 1 2 0 km boundary c o n d i t i o n s o r s t a t i c d i f f u s i o n a s s u m p t i o n s which a r e i n h e r e n t i n t h e c u r r e n t models. 2. Environment C r i t e r i a The monograph e n t i t l e d , " E a r t h O r b i t a l Atmospheric Model," w i l l be p u b l i s h e d by t h e O f f i c e of Advanced R e s e a r c h and Technology a s a NASA S p e c i a l P u b l i c a t i o n . S p e c i a l i z e d environment c r i t e r i a i n p u t s , n o t g i v e n i n NASA TM X-53798, "Space Environment C r i t e r i a G u i d e l i n e s f o r Use i n Space V e h i c l e Development, 1968 R e v i s i o n , " have b e e n f u r n i s h e d t o s e v e r a l e n g i n e e r i n g and s c i e n t i f i c s t u d i e s i n s u p p o r t of t h e OWS/ATM and F u t u r e Space S t a t i o n (FSS) programs. To f u r n i s h t h e s e s p e c i a l i z e d e n v i r o n m e n t c r i t e r i a i n a more s y s t e m a t i c manner, a document e n t i t l e d , " V a r i a t i o n i n Atmospheric D e n s i t y f o r MSFC 1971-1976 O r b i t a l Space S t a t i o n Programs," h a s b e e n w r i t t e n . The document, w h i c h w i l l b e p u b l i s h e d a s a NASA TM X i n F e b r u a r y 1969, w i l l a s s i s t t h e u s e r i n d e t e r m i n i n g t h e environment c r i t e r i a r e q u i r e m e n t s f o r a p a r t i c u l a r e n g i n e e r i n g o r s c i e n t i f i c s t u d y . It w i l l a l s o p r o v i d e p r e d i c t i o n s of t h e mean o r b i t a l a t m o s p h e r i c d e n s i t y , p r e s s u r e , and m o l e c u l a r w e i g h t t o which a s p a c e c r a f t w i l l b e exposed on p a r t i c u l a r days a t i n t e r v a l s of t h r e e months from J a n u a r y 1, 1971 t h r o u g h J a n u a r y 1, 1977. 3. Solar Activity Studies Lockheed M i s s i l e s and Space Company h a s computed c r o s s c o r r e l a t i o n f u n c t i o n s f o r s u n s p o t s and e a c h of t e n s e l e c t e d p r e d i c t o r s , which a r e d e s c r i p t i v e of t h e i n t e r a c t i o n of t h e p l a n e t s w i t h t h e s u n . P r e d i c t o r s t a k e n a t t h e time of s u n s p o t numbers p l u s a time z have b e e n used t o o b t a i n t h e v a l u e of T t h a t g i v e s t h e maximum and minimum c r o s s c o r r e l a t i o n f u n c t i o n s f o r .c # 0. T h i s i n f o r m a t i o n w a s t h e n used t o c a l c u l a t e c o r r e l a t i o n c o e f f i c i e n t s . The b e s t c o r r e l a t i o n s were o b t a i n e d by t r e a t i n g t h e s u n s p o t s a s a c y c l e of 22 y e a r s r a t h e r t h a n 11 y e a r s . The 22-year c y c l e c o n s i d e r s t h e f i r s t h a l f o f t h e c y c l e p o s i t i v e and t h e l a s t h a l f n e g a t i v e . These p r e d i c t o r s a r e b e i n g s u b j e c t e d t o a nonl i n e a r c o r r e l a t i o n t e c h n i q u e t o g i v e a s u n s p o t p r e d i c t i o n method. �MIT Experimental Astronomy Laboratory is c o n t i n u i n g r e s e a r c h f o r p o s s i b l e p l a n e t a r y e f f e c t s on t h e sun. ~ a b c o c k ' s h y p o t h e s i s of a p h y s i c a l model of t h e sun which would permit t h e formation of s u n s p o t s by p l a n e t a r y i n f l u e n c e s i s being s t u d i e d . Some of t h e s e hypotheses a r e being v e r i f i e d ; i t i s hoped t h a t t h e p l a n e t a r y t i d a l f o r c e caq be shown t o be a t l e a s t p a r t of t h e s u n s p o t t r i g g e r i n g mechanism. The proposed c o n t r a c t w i t h t h e S o l a r A c t i v i t y Group of t h e ESSA Space D i s t u r b a n c e Labotatory f o r D r . S l u t z t o s t u d y s o l a r a c t i v i t y i s s t i l l being n e g o t i a t e d . 4. A L i n e a r Regression S o l a r Cycle Study An in-house s t u d y u s i n g a l i n e a r r e g r e s s i o n technique w i t h monthly d a t a i n d i c a t e s a second peak of s o l a r c y c l e 20 o c c u r r i n g about September 1969. During t h i s expected i n c r e a s e i n s o l a r a c t i v i t y , t h e r e w i l l be an i n c r e a s e d p r o b a b i l i t y of major s o l a r f l a r e s o c c u r r i n g near September 1969. 5. Space S t a t i o n I o n o s p h e r i c Experiment Package The Phase A in-house s t u d y of i o n o s p h e r i c experiments which can be performed from a manned s p a c e s t a t i o n has been completed. A b r i e f i n g of t h e r e s u l t s , t o be g i v e n a t NASA Headquarters on January 30, 1969, w i l l i n c l u d e i n t e r e s t e d groups from MSFC, MSC, Langley and NASA Headquarters. The groups from Headquarters w i l l i n c l u d e r e p r e s e n t a t i v e s of OMSF, OART, and OSSA. A meeting was held w i t h D r . S t u h l i n g e r on January 28, 1969, i n which he was a p p r i s e d of t h e i o n o s p h e r i c experiment s t a t u s . A meeting w i l l be h e l d w i t h D r . E . R. Schmerling, C h i e f , I o n o s p h e r i c P h y s i c s , on January 29, 1969, t o review t h e s t a t u s of t h e experiment package. 6. A c o u s t i c G r a v i t y Wave Study The review of AVCO's f i n a l r e p o r t on Phase I of t h i s s t u d y should be held w i t h i n t h e n e x t two weeks. The Phase I1 c o n t r a c t n e g o t i a t i o n s a r e now i n p r o g r e s s . The Phase I1 emphasis w i l l be placed on o b t a i n i n g l i m i t e d d a t a on times of s t a t i c t e s t f i r i n g s and m e t e o r o l o g i c a l e v e n t s , The a n a l y s is and a s s o c i a t e d s t u d i e s w i l l emphasize t h e coupling of n e u t r a l motions t o i o n o s p h e r i c e l e c t r o n motions and an in-depth s t u d y of t h e a t t e n u a t i o n of a n a c o u s t i c g r a v i t y wave a s i t propagates from t h e t r o p o s p h e r e t o t h e thermosphere. I n a d d i t i o n t o t h e i o n o s p h e r i c sounder d a t a , we w i l l r e q u i r e p e r i o d i c o v e r n i g h t monitoring and p i c t u r e s from t h e weather r a d a r a t t h e Atmospheric Research F a c i l i t y . These w i l l be r e q u i r e d when n i g h t t i m e storm c e l l s a r e f o r e c a s t f o r t h e immediate a r e a . This i s a n OSSA sponsored and funded e f f o r t . �7. I o n o s p h e r i c Monitoring Equipment I n a d d i t i o n t o the MSFC ionosonde, a Phase P a t h Sounder i s being a c q u i r e d f o r use i n subsequent i o n o s p h e r i c experiment programs. This item w i l l r e q u i r e c o n s i d e r a b l e a t t e n t i o n t o o p e r a t i o n and maintenance, s i n c e i t i s a s t a t e - o f - t h e - a r t development. These two p i e c e s of i o n o s p h e r i c monitoring equipment provide a unique o p p o r t u n i t y f o r s t u d y i n g i o n o s p h e r i c dynamics i n c o n s i d e r a b l e d e t a i l . The b u i l d e r s of t h e Phase P a t h Sounder (IT&T) have been c o n t r a c t e d t o come t o MSFC t o t r a i n our e n g i n e e r i n g personnel i n t h e r o u t i n e o p e r a t i o n and maintenance of t h i s p i e c e of equipment. The i o n o s p h e r i c experiments subs e q u e n t l y r u n w i l l then depend d i r e c t l y on t h e a v a i l a b i l i t y and c a p a b i l i t y of t h e s e t r a i n e d people. B . Atmospheric Dynamics Branch 1. Technical Meeting Concerning Wind Loads on B u i l d i n g s and S t r u c t u r e s M r . George H. F i c h t l and M r . John W. Kaufman, R-AERO-YE, gave a p r e s e n t a t i o n a t t h e t e c h n i c a l meeting on wind l o a d s on b u i l d i n g s and s t r u c t u r e s , sponsored by t h e Building Research D i v i s i o n , N a t i o n a l Bureau of S t a n d a r d s , and t h e Environmental Data S e r v i c e , ESSA. The purpose of t h e meeting was t o g a t h e r t o g e t h e r a u t h o r i t i e s i n s t r u c t u r a l d e s i g n and atmospheric s c i e n c e t o d i s c u s s t h e wind load problem and perhaps make some s p e c i f i c recommendations t o improve t h e U. S. S t r u c t u r a l B u i l d i n g Code. The meeting covered f o u r a r e a s : (1) e n g i n e e r i n g problems i n t h e d e s i g n of s t r u c t u r e s t o r e s i s t wind l o a d s , ( 2 ) atmosp h e r i c c o n s i d e r a t i o n s , ( 3 ) experimental and t h e o r e t i c a l d e t e r m i n a t i o n of aerodynamic f o r c e s , and (4) r e c e n t advances i n d e s i g n procedures and c u r r e n t d i f f i c u l t i e s . The NASA ground wind d e s i g n wind model f o r KSC and t h e NASA 150 m M e t e o r o l o g i c a l Tower were d e s c r i b e d i n a pres e n t a t i o n by M r . F i c h t l and M r . Kaufman. The approach taken by NASA t o s p e c i f y t h e ground wind environment from a d e s i g n p o i n t of view was w e l l r e c e i v e d . P r o f e s s o r G i l l of t h e Michigan S t a t e U n i v e r s i t y , a well-known a u t h o r i t y on i n s t r u m e n t a t i o n , pointed o u t t h a t t h e NASA 150 m M e t e o r o l o g i c a l Tower is one of t h e f i n e s t towers of i t s kind i n t h e U. S. and i s an example of what can be done. Furthermore, he pointed o u t t h a t t h e d a t a from t h i s tower should be used i n t h e new U . S. Building Code t o s p e c i f y wind flow c o n d i t i o n s over "Type C" t e r r a i n . It appears t h a t t h e NASA Tower F a c i l i t y and a n ESSA F a c i l i t y a r e t h e only towers i n t h e U . S. t h a t a r e being used t o o b t a i n atmospheric wind d a t a on a r o u t i n e 24-hour b a s i s f o r t h e e x p r e s s purpose of determining wind load f o r c i n g f u n c t i o n s . �The o v e r a l l approach t o t h e wind problem by NASA w a s h a i l e d a s being a p o s i t i v e s t e p forward t o o b t a i n i n g a s o l u t i o n t o t h e wind load problem. The work performed by Marshall personnel i n ground wind environment s p e c i f i c a t i o n i s a b e n e e i c i a l by-product of t h e aerospace indus t r y . 2. F i n a l Report under C o n t r a c t NAS8-21148 The f i n a l r e p @ r t has been r e c e i y e d and accepted under C o n t r a c t NAS8-21548, e n t i t l e d , "Studies of V e r t i c a l Wind V e l o c i t y a t Cape Kennedy, F l o r i d a . " The r e p o r t , being published a s a NASA CR, w i l l be a v a i l a b l e soon. VariouB d e t a i l s of wind phenomena a s measured by t h e FPS-16 r a d a r l f i m s p h e r e system, i n c l u d i n g s p e c t r a l energy of t h e mesoand m l c r o - s c a l e v e l o c i t y v a r i a t i o n s , a r e d i s c u s s e d . 3, Study of V e h i ~ l eExhaust Cloud Phenomena A s t u d y e n t i t l e d , "Rise Rate and Growth of S t a t i c T e s t Vehicle Engine Exhaust Clouds ," i s included i n t h e r e c e n t l y published TM X-53782. AEC, A i r Force, a s w e l l a s o t h e r concerns, a r e i n t e r e s t e d i n such d a t a t o s t u d y atmospheric d e b r i s f a l l b a c k , f a l l o u t , i n d u s t r i a l pollution, etc. 4. Revised Ground Wjnd C r i t e r i a Memorppdum R-AERO-YEd176-69, dated January 1 0 , 1469, d i s c u s s e s t h e d i s t r i b u t i o n of peak gxound wipd p r o f i l e shapes Eor m i s s i o n planning and o p e r a t i o n s , Any camments o r q u e s t i o n s r e g a ~ d i n gt h e s e new c r i t e r i a should be d i r e c t e d t o M.P. George F i c h t l of R-AERO-YE, o r Mr. W. W. Vaughan, R-AERO-Y. These c r i t e r i a have been ahd w i l l be used i n t h e f u t u r e i n m o n i t o r i n g wind p r o f i l e c o n d i t i o n s d u r i n g p r e - f l i g h t o p e r a t i o n s of A p o l l o / S a t u r n v e h i c l e s . This work is accomplished by t h e HOSC/MSFC wind monitoriqg team of which MSBCIMSC personnel a r e members. 5 . Jimsphere Ascent Rate Data R e c e n t l y , t h e l o c a l inhouse Boeing c o n t r a c t o r personnel submhtred a d r a f t r e p o r t oh a scheme t o p r o p e r l y f i l t e r the S i m p h e r e a s c e n t r a t e d a t a . The technique d i s c u s s e d i n t h e r e p o r t w i l l be s e r i o u s l y considered a s a d a t a r e d u c t i o n s u b r o u t i n e t o provide r e l i a b l e a s c e n t r a t e d a t a f o r r e s e a r c h of v e r t i c a l wind motion s t u d i e s of t h e upper atmosphere t o a h e i g h t of about 18 km. 6. Atmospheric Turbulence (Ground Winds) a . I n v e s t i g a t i o n @£ t h e t u r b u l e n t wind f i e l d below 500 f t a l t i t u d e a t t h e E a s t e r n T e s t Range, F l o r i d a (Contract NAS8-21140 w i t h t h e Pennsylvania S t a t e U n i v e r s i t y ) . �The f i r s t year of e f f o r t i n t h i s a r e a has been comp l e t e d , and the c o n t r a c t o r has submitted a p r e l i m i n a r y d r a f t of h i s f i n a l r e p o r t f o r review. This r e p o r t covers (1) a n a l y s e s of s p e c t r a of t h e h o r i z o n t a l wind components; ( 2 ) t h e r e l a t i o n between t h e t u r b u l e n t wind components a t d i f f e r e n t h e i g h t s a s manifested by t h e cospectrum o r q u a d r a t u r e spectrum, o r r a t h e r the s p e c t r a l coherence and t h e s p e c t r a l eddy s l o p e ; (3) a p r e l i m i n a r y s t u d y of t h e p r o b a b i l i s t i c s t r u c t u r e of t u r b u l e n t f o r c i n g of launch v e h i c l e s ; and (4) t h e q u a s i - s t e a d y wind p r o f i l e . Although much i n f o r m a t i o n about atmospheric t u r b u l e n c e has been gained d u r i n g t h i s f i r s t year of e f f o r t , t h e r e i s much t o l e a r n ; t h e r e f o r e , t h i s c o n t r a c t w i l l be continued f o r a n o t h e r y e a r . The cont r a c t o r w i l l g i v e a b r i e f i n g on h i s work i n l a t e February. b. Ground wind f i e l d a n a l y s i s f o r d e s i g n and o p e r a t i o n f o r s p a c e v e h i c l e s (NAS8-21178 C o r n e l l A e r o n a u t i c a l L a b o r a t o r i e s , I n c . ) . This e f f o r t w i l l be completed i n mid-February. The c o n t r a c t o r has completed h i s d a t a a n a l y s e s , and a f i n a l r e p o r t i s now b e i n g d r a f t e d . We should r e c e i v e t h i s r e p o r t i n e a r l y February f o r review and comments. The r e p o r t w i l l be concerned w i t h q u a s i s t e a d y wind p r o f i l e s , g u s t f a c t o r s , g u s t a c c e l e r a t i o n s , s p e c t r a , e t c . The c o n t r a c t o r w i l l g i v e a b r i e f i n g on h i s work i n l a t e February. c . Ground Wind Turbulence Analys i s (In-House E f f o r t ) A d e s i g n s p e c t r a l model was completed d u r i n g t h i s The r e s u l t s of t h i s e f f o r t and o t h e r a s p e c t s of t h e ground wind period. problem were p r e s e n t e d i n a paper by M r . F i c h t l and M r . Kaufman a t t h e NBS-ESSA meeting on wind l o a d s on b u i l d i n g s and t a l l s t r u c t u r e s i n Washington, D. C . on January 27 and 28. The paper was w e l l r e c e i v e d . M r . F i c h t l and D r . John Dutton of t h e Pennsylvania S t a t e U n i v e r s i t y submitted a paper e n t i t l e d "Approximate Equations of Motion f o r Gases and L i q u i d s , " t o t h e J o u r n a l f o r Atmospheric Sciences. The p a p e r , which w i l l appear i n t h e March e d i t i o n , i s concerned w i t h developing a cons i s t e n t s e t of Boussinesq approximated e q u a t i o n s f o r f l u i d flotqs i n g r a v i t a t i o n a l l y s t r a t i f i e d f l u i d s . These e q u a t i o n s a r e being used i n some of t h e a n a l y s e s of low l e v e l atmospheric t u r b u l e n c e and wind p r o f i l e s . 7. A n a l y s i s of Atmospheric Turbulence from FPS-16 ~ a d a r / Jimsphere Data (NAS8-21331 w i t h t h e Meteorology Research, Incorporated) The c o n t r a c t o r has completed most of t h e work on t h i s f i r s t year of e f f o r t . The r e s u l t s seem t o show t h a t t h e FPS-16 ~ a d a r l ~ i m s p h e r e system might be capable of d e t e c t i n g c l e a r a i r t u r b u l e n c e . A f i n a l r e p o r t �w i l l be prepared i n February. Although e x t e n s i v e work has been done d u r i n g t h e f i r s t y e a r , t h e r e is much l e f t t o be done. Accordingly, t h i s e f f o r t sill be renewed f o r an a d d i t i o n a l y e a r . 8. Operation Procedures f o r Determining Space Vehicle Response t o Wind Turbulence (NAS8-21325 w i t h t h e Martin-Marietta Corporation) M r . F i c h t l , R-AERWYE, t r a n s m i t t e d quas i-s teady wind and t u r b u l e n c e s p e c t r a s t a t i s t i c s of i n - f l i g h t winds t o Mrs. ~ l b e r t aKing, R-AERO-DD, t h e c d n t r a c t monitor. These s t a t i s t i c s w i l l be used t o develop a p r e l a u n c h m o n i t a r s h i p l o a d s f o k e c a s t i n g procedure and t o s t u d y load s e n s i t i v i t y t o i n f l i g h t winds Bnd t u r b u l e n c e . C. T e r r e s t r i a l Environmeht 1. The N a t i o n a l Weather Records Center (GovernmeBt Order 76789) The 1966 Cape Kennedy s e r i a l l y complete winds a l o f t wete r e c e i v e d from t h e H a r i o n a l Weather Records Center. A f t e r accuracy checks, t h e o b s e r v a t i o n s , when &dded t o t h e p r e s e n t d a t a , w i l l i n c r e a s e t h e sample s i z e t o 11 y e a r s . The p e r i o d of r e c o r d of two of t h e primary s t a t i s t i c a l d a t a samples was a l s o i n c r e a s e d by 6 months w i t h t h e a d d i t i o n of January-June 1968, Cape Kennedy h o u r l y peak ground winds, and J u l y December 1967, Cape ~ e n n e d yh o u r l y s u r f a c e o b s e r v a t i o n s . A r e p o r t e n t i t l e d 'iidarkov C h a i ~Techn-Lques f o r P r e d i c t i n g t h e Maximum Wind i n t h e I4aximuitl Dynamic P r e s s u r e Regi0t.t f a 2 Launching Space V e h i c l e s , " by H. L. CrutkHer and N, B. Guttman, prepared under Government Order 76789 w i t h t h e NWRC was r e c e i v e d and submitted f o r p u b l i c a t i o n a s a c o n t r a c t a r r e p o r t . Other NWRC p u b l i c a t i o n s being p r e pared f o r i s s u a n c e a s conPractor r e p o r t s a r e : 2. (a) " P r e d i c t i o n of t h e Maximum Wind Speed i n t h e 10-15 km Layer Above Cape Kennedy," (b ). "Thunders t o r h Pers E s t e n c e a t Cape Kennedy, F l o r i d a (c) "An Empirical Analysis of the 10-15 km Maximum Winds t o Determine Apollo and AAP Launch O p p o r t u n i t i e s Cape Kennedy, F l o r i d a . " ." - Kaman Nuclear (NAS8-11348) Kaman Nuclear p u b l i c a t i o n s being i s s u e d a s c o n t r a c t o r r e p o r t s a r e "The E f f e c t s of Atmospheric F l u c t u a t i o n s and R e p r e s e n t a t i o n Upen Propagated Sound," aRd " V g r l a b i l i t y 6f Sound Propagation red i c t i o n Due t o Atmospheric V a r i a b f l i t y . " �3. Eockheed A Lockheed C o n t r a c t o r Report d e t a i l i n g t h e AS-504 launch p r o b a b i l i t i e s by hour, a s determined by atmospheric c o n s t r a i n t s , was i s s u e d under o f f i c e memorandum R-AERO-YT-10-69, January 29, 1969. V. AEROPHYSICS DIVISION A. Mechanical Design O f f i c e 1. BalanceIModel System f o r Plume Study i n IBFF Design i s n e a r completion on a balance/model system f o r measuring normal f o r c e s on an e i g h t - i n c h s q u a r e f l a t p l a t e d u r i n g a plume impingement t e s t i n t h e IBFF. The system u t i l i z e s t h r e e q u a r t z load washers and can be p i t c h e d t o 30° a n g l e of a t t a c k . (-AD) 2. 5-Component, Micro-Force Balance f o r t h e Low D e n s i t y Chamber Design, d r a f t i n g and drawing check-out has been completed on Balance No. 224 and i t s r e l a t e d c a l i b r a t i o n and i n s t a l l a t i o n equipment. F a b r i c a t i o n w i l l be i n i t i a t e d upon r e q u e s t of t h e o r i g i n a t i n g organization. (-AE) 3. E l e c t r o n Beam Equipment f o r t h e Low Density Chamber F i n a l drawings have been completed on t h e E l e c t r o n Beam Gun designed by D r . B e y l l c h f o r R-AERO-AE. Fabrication w i l l be i n i t i a t e d by d i r e c t c o n t r a c t through P&C, r a t h e r t h a n our u s u a l procedure through ME Laboratory. It i s e s t i m a t e d t h a t 1600 hours w i l l be r e q u i r e d t o f a b r i c a t e t h i s item. The s t a t u s of o t h e r items i n t h i s d e s i g n package a r e (1) E l e c t r o n Beam C o l l e c t o r ( D r a f t i n g ) , (2) E l e c t r o n Beam O p t i c a l Equipment ( ~ ei sg n ) , and (3) E l e c t r o n Beam P o s i t i o n i n g Device (Design) (-AE) . 4. The following i s a p a r t i a l l i s t of p r o j e c t s and t h e i r current status: Cryo-panels, 18' diameter IBFF Vacuum Tank, -AE Design Model Cover, 18' diameter IBFF Vacuum Tank, -AE Des i g n Heated Plenum Chamber, LDC, -AE Design F l a t P l a t e Heat T r a n s f e r Model, LRC 4' WT, -AT Design �P r e s s u r e Model, 2.7'' d i a m e t e r , HRE, -AD Des i g n P r e s s Model, Cone, w i t h Transducers, AEDC WT, -AU Des i g n C a l i b r a t i o n C r o s s , HRE, -qE Dee i g n X-Y-Z P o s i t i o n i n g Devices, L a s e r s , -AF Design M o d i f i c a t i o n Model, No, 397, CFD, -AF $abr i c a t i o n Helium Vent Equipment, 14" WT, -AD Fabrication P r e s s u r e Model, 1 / 4 C y l i n d e r , IBFF, -AE Fabrication Supersonic T e s t Spool, HRE, -AE Fabrication Sonic Nozzle, CFD, -AF Delivered Pos i t i o n i n g Equipment, L a s e r , 7" WT,' -AF Delivered M o d i f i c a t i o n of Plodel No. 422, 14" WT, -AE Delivered C a l i b r a t i o n Equipment, HRE, -AE Delivered Redesigned Survey Probe, 14" WT, -AE Delivered Model 425, Curved C e n t e r l i n e Force Model, 14" WT, -AD Del i y e r e d M o d i f i c a t i o n of Model 392, 14" WT, -AD Delivered Gas H e a t e r , LDC, -AE Delivered O p t i c a l Equipment Support, CFD, -AF Delivered B. Aerodynamic Design Branch 1. Saturn V a. AS-503 Aerodynamic F l i g h t E v a l u a t i o n The f l i g h t compartment p r e s s u r e s compared w e l l w i t h t h e p r e d i c t e d band f o r each compartment on t h e v e h i c l e e x c e p t t h e S-IC b a s e compartment. The p r e s s u r e i n t h i s compartment was lower t h a n pred i c t e d due t o a n i n c r e a s e i n leakage a r e a because t h e f u e l l i n e boots were n o t i n s t a l l e d , �The AS-503 v e h i c l e , a s w i t h p r i o r S a t u r n f l i g h t s , f l e w a t v e r y low a n g l e s of a t t a c k t h a t d i d n o t exceed 2.5 d e g r e e s d u r i n g t h e p e r i o d of i n t e r e s t . Because of t h i s , a r e l i a b l e s t a b i l i t y and f i n l o a d a n a l y s i s could n o t be made, The AS-503 b a s e p r e s s u r e f e l l w i t h i n a p r e d i c t e d band based on AS-502 d a t a even though AS-503 had a 2-degree o u t b o a r d e n g i n e c a n t and o n l y s i x v a l i d b a s e p r e s s u r e measurements,whereas AS-502 had e i g h t measurements. The r e v i s e d b a s e a x i a l f o r c e o b t a i n e d from AS-503 f l i g h t d a t a f o r t h e A p o l l o j S a t u r n V v e h i c l e h a s b e e n p u b l i s h e d i n o f f i c e memo R-AERO-ADV-69-6. The d a t a a r e t o be used i n performance and c o n t r o l studies . b. S a t u r n V S t a t i c Ground Wind Loads R e s u l t s of LTV t e s t LSWT-253 (August 1967) have b e e n compiled f o r b r a n c h r e c o r d i n o f f i c e memorandum R-AERO-AD-68-72, " S t a t i c Ground Wind Loads f o r t h e A p o l l o / ~ a t u r nV Launch V e h i c l e , " by K . L. B l a c k w e l l . These d a t a a r e a v a i l a b l e upon r e q u e s t . 2. S a t u r n V and AAP a. Venting Northrop-Huntsville has published a f i n a l r e p o r t (TR-794-434) c o v e r i n g a n a n a l y s i s of t h e o r i f i c e flow c o e f f i c i e n t d a t a o b t a i n e d i n t h e Ames R e s e a r c h C e n t e r ' s 6 - f o o t S u p e r s o n i c Wind Tunnel. P l a n s a r e made t o do a d d i t i o n a l e x p e r i m e n t a l work which w i l l supplement t h a t of Ames a s w e l l as a d d i t i o n a l work on o r i f i c e s l o c a t e d i n a d v e r s e f l o w f i e l d s . The m a j o r i t y of t h i s work p r o b a b l y w i l l be c a r r i e d o u t i n t h e MSFC 1 4 - i n c h TWT. b. Hydrogen Vent Study (S-IVB Hydrogen Tank) O f f i c e memorandum R-AERO-AD-68-70, " P r e t e s t I n f o r m a t i o n f o r a n I n v e s t i g a t i o n t o Determine t h e Downstream D i s s i p a t i o n of Helium I n j e c t e d from a C i r c u l a r P o r t P e r p e n d i c u l a r t o t h e 1 4 - i n c h TWT Wind Tunnel w a l l , " December 30, 1968, h a s been i s s u e d . Hardware d e s i g n h a s b e e n comp l e ted e x c e p t f o r minor mod i f i c a t i o n s t o t h e o r i g i n a l d e s i g n , and f a b r i c a t i o n i s underway. A c o n f e r e n c e was h e l d w i t h R-AERO-AE and R-AERO-AM t o c o o r d i n a t e hardware and t e s t p r e p a r a t i o n s . T e s t i s s c h e d u l e d f o r March 1960. �3. AAP a. AAP-2 Nose Shroud Venting To reduce t h e a c o u s t i c n o i s e l e v e l on t h e AAP-2 MDA, i t was decided t o s u b s t i t u t e helium i n p l a c e of n i t r o g e n a s t h e gas used t o purge t h e nose shroud compartment. Simultaneously, means of reducing t h e weight of t h e nose shroud (AS-203 t y p e ) by some 400 pounds a r e being investigated. One means of a c h i e v i n g a weight r e d u c t i o n i s t o r a i s e t h e i n t e r n a l p r e s s u r e l e v e l abave t h a t p r e s e n t l y p r e d i c t e d u s i n g a v e n t a r e a of 150 i n 2 w i t h a gaseous n i t r o g e n purge. It t h e r e f o r e becdhles necess a r y t o be a b l e t o a c c u r a t e l y p r e d i c t i n t e r n a l p r e s s u r e l e v e l s when v e n t i n g w i t h helilrm. S i n c e helium i s an extremely l i g h t g a s , i t s p r o p e r t i e s and v e n t i n g c h a r a c t e r i s t i c s a r e s i g n i f i c a n t l y d i f f e r e n t from n i t r o g e n . . T e s t s have r e c e n t l y been conducted a t MSFC t o compare t h e c h d r a c t e r i s t i c s of n i t r o g e n and helium v e n t i n g t o q u i e s c e n t a i r . Tn March f u r t h e r t e s t s i n t h e MSFC 1 4 - i n c h T r i a o n f c blind Tunnel w i l l s i m i l a r l y compare t h e two g a s e s when v e n t i n g i n t o an e x t e r o a l stream. b. AAP-2 S o l a r Array F a i r i n g S e v e r a l ppoblerns have been encountered w i t h t h e pres e n t l y proposed means of v e n t i n g t h e U P - 2 s o l a r a r r a y f a i r i n g d u r i n g f l i g h t (Ref. R-AERO-AD-68-45). The primary problem i s t h a t of keeping the b u r s t load on t h e f a i r i n g t o a minimum s i n c e the f a i r i n g can o n l y be a t t a c h e d on each end t o t h e S-IVB s t a g e forward and a f t s k i r t s . The v e n t l o c a t i o n p r e v i o u s l y s e l e c t e d t o produce a low i n t e r n a l p r e s s u r e i s u n s u i t a b l e f o r p r e - f l i g h t purging, and thus t h e i n - f l i g h t v e n t s must be c l o s e d f o r purging and opened j u s t b e f o r e l i f t - o f f . Clearance problems, however, i n h i b i t t h e use off v a l v e s t o a c h i e v e t h i s , and a c c e s s t o t h e f a i r i n g o p p o s i t e t h e tower p r e v e n t s removing v e n t covers w i t h l a n y a r d s . A 1 t e r n a t e means of v e n t i n g t h e f a i r i n g a r e p r e s e n t l y being i n v e s t i g a t e d . The most a t t r a c t i v e i s t o v e n t o u t t h e b a s e of t h e f a i r i n g where an o r i f i c e w i l l e x i s t f o r t h e purpose of dumping t h e p r e - f l i g h t purge g a s . This v e n t i n g scheme would appear t o be a c c e p t a b l e provided t h e e x t e r n a l p r e s s u r e a t t h e base of t h e f a i r i n g can be a c c u r a t e l y d e f i n e d . c. AAP Plume Impingement (1) A n a l y t i c a l work by LMSC (under m i s s i o n s u p p o r t ) d e f i n i n g WACS plume impingement l o a d s on t h e Workshop s o l a r panels and protuberances has been completed. These d a t a have been developed f o r two-size s o l a r a r r a y s and p a r a m e t r i c a l l y a s a f u n c t i o n of s o l a r panel o r i e n t a t i o n a n g l e . The d a t a a r e being prepared f o r p u b l i c a t i o n . �(2) A s c o p e of work h a s b e e n p r e p a r e d f o r a proposed c o n t r a c t t o d e t e r m i n e s c a l i n g p a r a m e t e r s n e c e s s a r y f o r performing e x p e r i m e n t a l low d e n s i t y plume impingement f o r c e t e s t s . The work t o be performed under t h i s c o n t r a c t is i n s u p p o r t of e x p e r i m e n t a l plume impingement f o r c e t e s t s t o be conducted f o r A p o l l o A p p l i c a t i o n s m i s s i o n s . D e t a i l s of t h e s c o p e of work a r e p r e s e n t e d i n o f f i c e memorandum R-AERO-AD-68-66. ( 3 ) Phase I t e s t s (Ref. R-AERO-AD-68-52) i n t h e MSFC Base Flow F a c i l i t y were completed on F e b r u a r y 3 , 1969. These t e s t s t o determine p i t o t pressure d i s t r i b u t i o n s w i t h i n scaled 5-2 e n g i n e plumes r e q u i r e d l o n g e r t h a n a n t i c i p a t e d . P a r a m e t r i c v a r i a t i o n s i n t h e e x p e r i m e n t a l hardware were n e c e s s a r y t o p r o v i d e s u f f i c i e n t i n f o r m a t i o n f o r a n a l y s i s . A r e p o r t documenting t h e s e d a t a w i t h comparisons between e x p e r i m e n t a l and a n a l y t i c a l plume c a l c u l a t i o n s is i n p r o g r e s s . A Phase I1 s t u d y , t o b e g i n F e b r u a r y 1 9 , 1969, w i l l d e t e r m i n e p r e s s u r e s and h e a t t r a n s f e r r a t e s on a f l a t p l a t e immersed i n t h e s c a l e d 5-2 plume. A memorandum documenting t h e o v e r a l l e x p e r i m e n t a l and a n a l y t i c a l e f f o r t i n s u p p o r t of AAP plume impingement h a s b e e n p u b l i s h e d (R-AERO-A- 69-3). d. Helium Venting (AAP-2 Payload Shroud) R e c e n t l y t h e purge g a s f o r t h e AAP-2 payload s h r o u d compartment was changed from n i t r o g e n t o helium. C u r r e n t compartment v e n t a n a l y s e s a r e based on v e n t d i s c h a r g e c o e f f i c i e n t s which were d e t e r mined e x p e r i m e n t a l l y u s i n g a i r a s t h e d i s c h a r g e g a s . Since i t is not known how t h e u s e of h e l i u m a f f e c t s d i s c h a r g e c o e f f i c i e n t s , t e s t s w i l l be conducted t o d e t e r m i n e h e l i u m d i s c h a r g e c o e f f i c i e n t s i n t h e MSFC 1 4 - i n c h T r i s o n i c Wind Tunnel. T e s t s w i l l be r u n c o n c u r r e n t l y w i t h t h e S-IVB hydrogen t a n k v e n t t e s t s s i n c e t h e equipment i s t h e same e x c e p t f o r v e n t c o n f i g u r a t i o n . A r e q u e s t f o r a new v e n t p l a t e h a s been s u b m i t t e d t o R-AERO-AM f o r u s e d u r i n g t h e March 1, 1969 t e s t s . e. UP-2: S o l a r P a n e l Shroud/APS P r e s s u r e T e s t s T e s t s were conducted i n t h e MSFC 1 4 - i n c h T r i s o n i c Wind Tunnel t o d e t e r m i n e p r e s s u r e d i s t r i b u t i o n s o v e r t h e s o l a r p a n e l shroud and APS u n i t s t o examine t h e i n f l u e n c e of t h e new AAP-2 payload s h r o u d c o n f i g u r a t i o n ( g e n e r a l payload s h a p e ) . Data were o b t a i n e d a t Mach numbers of 0.8, 0 . 9 , 1 . 0 , 1.1, 1 . 2 , 1 . 4 6 and 1.96 f o r a n g l e s of a t t a c k up t o 8 d e g r e e s . A r e p o r t documenting t h e t e s t r e s u l t s i s b e i n g prepared. �f. AAP-2 ( P r e s s u r e T e s t & ) The f o l l o w i n g o f f i c e memoranda have been completed over the p d g t r e p o r t i n g p e r i o d and a r e a v a i l a b l e upon r e q u e s t : (1) Lanel D. G , , 6. 6 . D i l l , "Results from ah I n v e s t i g a t i o n t o DeterMing t h e Local P r e s s u r e s and Load ~ i s t r i b u t i o n sW e r a Proposed Forebddy ~ o n f F g u r & t l o r fi o r t h e AAP-2 Launch Vehicles," R-AEROAD-68-69 (Resul td bf MSFC-TWT-463, August 1968). . (2) ~ l a e k w e l l ,K. L , , "Ah I n v e s t i g a t i o n tct Obtain Local P r e s s u r e ~ i s t t i b u t i o f i sover t h e APS Uhit and S o l a r Panel Shroud ( R e s u l t s of MSFC-TWTof t h e S a t u r n fB/MP-2 Vehicle ," R-AERO-AD-~~-'/~ 397, A p r i l 1968). g. B r b i t a l Aaradya&mFcs AAP O f f i c e tnemdranduh R-AERO-AD-69-1, "Orbithl kerodynaaiic Data f o r t h e U P 1 3 and U P 4 4 ~ i d s i ~ r i sJBnhary ~ " 10, 1969, was! published during t h i s r e p o r t i n g period. It c o n t a i n s o r b i t a l aepodynahic d a t a f o r t h e following two con£ igurkitiona s (1) OV3 w i t h docked CShf and LM/AW - LbrZI~l$f gal&r % f r & y sextended. (1) OMS w i k k ddaked Z=&T and L H ~ A ~ - LMJATM s o l a r a r r a y s n o t extended. h. Cantamination - MP isc charge of waste l i q u i d s d u r i n g s p a c e f l i g h t has a l r e a d y c r e a t e d some contafhinatioh problerlns d u r i n g t h e Apolfo m i s s i o n s . For l o n g e r f l i g h t s of l a r g e o r b l t i n g s p a e e s t a t i o n s , t h e s e problems could become s e r i o u s . There a r e p r i m a r i l y two a r e a s of concern: (1) Cont a m l n a t i o n of t h e atmosphete s u r t o u n d i n g t h e a p a c e s t a t i o n and (2) cont a m i n a t i o n of e x t e r n a l s u r f g c e s of t h e s p a t e s t a t i o n . To o b t a i n some i n p d t f n f o r m a t i o n t h a t i s r e q u i r e d i n the s t u d y of t h i s problem, Lotiisiana S t h t e U n i v e r s i t y has been a s s i g h e d a t a s k to i n v e s t i g a t e t h e c h a r a c t e r is t i c s of f l u i d 9 t h a t a r e i n j e c t e d i n t o a vacuum. This t a s k w i l l be one of S e v e r a l t h a t w i l l be included i n a g r a n t t o LSU. The work t o be performed by LSU i s as follows: Gondvct an experimental i n v e s t i g a t i o n of f l u i d 9 when they a r e i n j e c t e d i n t o d Rear-vacuum through s m a l l o r i f i c e s . Determine Che e i z e , s h a p e , v e l o c i t y , d e n s l t y , and d i r e c t i o n of p a r t i c l e s t h a t form kWe6 ehe f l u i d e a t e r s t h e v%cuurh. Water a t s p a c e c r a f t temperature and p r e s s u r e w i l l be used a s t h e f l u i d d u r i n g t h i s i r m e s t i g a t i o n . O r i f i c e �geometries should s i m u l a t e geometries of v e n t s t h a t w i l l be used f o r waste c o n t r o l d u r i n g Apollo A p p l i c a t i o n s m i s s i o n s . D r . F. M. Donovan, J r . and D r . D. Maples, both members of t h e LSU f a c u l t y , w i l l be t h e i n v e s t i g a t o r s f o r t h i s t a s k . Experimental work w i l l be performed i n vacuum chamber f a c i l i t i e s a t t h e NASA M i s s i s s i p p i T e s t F a c i l i t y . The budget f o r t h i s t a s k is $22,000. M r . ~ u i n t r e l la t NASA Headquarters, who i s t h e c o n t r a c t o f f i c e r f o r t h i s g r a n t , has i n d i c a t e d t h a t paper work should be s u f f i c i e n t l y completed s o t h a t work can b e g i n a t LSU d u r i n g February 1969. 4. General a. Body of Revolution Viscous Cross-Flow I n v e s t i g a t i o n ( P r e s s u r e , Force and Flow V i s u a l i z a t i o n ) Design of t h e 2.70-inch diameter o g i v e - c y l i n d e r model t o be t e s t e d i n t h e High Reynolds Number Equipment has been completed and i s b e i n g d r a f t e d . F a b r i c a t i o n of t h e model is t e n t a t i v e l y scheduled t o be completed i n J u l y w i t h t e s t i n g t o begin i n August 1969. A S a t u r n V model of the same diameter w i l l be f a b r i c a t e d and ready f o r t e s t i n g upon completion of t h e o g i v e - c y l i n d e r t e s t s . S e v e r a l a t t e m p t s have been made t o f a b r i c a t e flow v i s u a l i z a t i o n models u s i n g b l a c k epoxy over a s t e e l s h a f t . R e s u l t s t o d a t e have been unacceptable due t o a i r pockets forming d u r i n g t h e pouring of t h e epoxy. We have been a s s u r e d t h a t t h i s problem can be remedied, and a d d i t i o n a l c a s t i n g s a r e being made by ME Laboratory. Contract negotiations a r e progressing f o r the f a b r i c a t i o n of t h e 4.0-inch diameter model t o be t e s t e d i n t h e LTV 4 - f o o t HSWT. Work on t h e f o r c e d a t a t e s t r e s u l t s has slowed c o n s i d e r a b l y because of t h e l o s s of NSL t e c h n i c a l a i d s u p p o r t . b. Nonlinear L i f t of Bodies of Revolution (Wake Flow Survey) A new scope of work, which covers t h e remaining Phase I1 work and t h e e x t e n s i o n of t h e i n v e s t i g a t i o n t o a s u b s o n i c Mach number, has been completed and forwarded t o t h e Purchasing O f f i c e . Phase I1 c o n s i s t s of a p r e s s u r e r a k e survey of t h e v o r t e x flow f i e l d behind a n ogive-cylinder/frustum-cylinder t e s t model c o n f i g u r a t i o n f o r Mach numbers of 0.8 and 1.96 i n t h e MSFC 14-inch TWT. The program w i l l be f i r m l y scheduled when a c o n t r a c t i s f i n a l i z e d , b u t is now t e n t a t i v e l y s e t f o r May 1969. �r a t i o n of Nigh R e y n ~ l d sNumber Equipment f a b r icaged i n c 1i n a t i o n i cal ibrpted i n urvey probe has been designed and i s now being b e , which w i l l determine Mach number and flow ch @nd yaw planes sirnqltaneously, w i l l b e 14pinch TWT d u r i n g February. which w i l l us when complete Tunnel i n Dal available for i g h Reynolds Number Equipment c a l i b g a t i o n r a k e vey probe is p r e s e n t l y i n d e s i g n . The r a k e , c a l i b r a t e d i n t h e LTV 4 - f o o t High #peed WFnd d u r i n g mid-May 1969. The r a k e would then be calibration topl. . C. Aerophys Ccs Branch Experiment be procured and d s l i v e p e d t q P451;"e i n i c h was f i n a l i z e d Cn Dec@pber 1968. a i l a b l e a t low c o s t and egn now be t h e cryopumping s y s tem i g t h e Lpw Che e f f o r t of a d a p t i n g l i q u i d hydrogen 11 m l p i a t u r e n o a % l e s , instrumented with s t a t i c t u r g gkerwcoupPes, a r e now i n t h e d e e i g n s t a p e a . n f i $ u y a t f o n s p e a i f h d by 8-AEBO-AD, $ r e r e q u i r e d j e t - p l u m impingement program. p o r t s and wal These n o z z l e s i n continuati t i o p s and Brgwhnge b v e been completed on t h e and s e n t t o R-L$EPO-RM f o r c o n t r a c t i n t t i a t i o n . eliura c r y o p w p i n g t o the low d e n s t t y wind t u n n e l , i l i t y ts flow n i t r o g e n gas from whish one can e r ~ t u r eby use of a h i g h r e s o l u t i o n s p e c t r o m e t e r . t i ~ ns p e c t r o m e t e r has been ordered f o r use i n CS, Alga, a Q-5000 mass spectrqmete;c has t plume s t u d i e e With t h e addf there e x i s t s measure r o t a t A two-me t e r . i S p e c i f i p a g i o ~ shave been completed on a l i q u i d n i t r o g e n shroud wiCh b l a c k i t e r i o r s u r f a c e s f ~ t rh e low d e n s i t y wind t u n n e l and s e n t t o R-AERO-& for i n i t i ~ t i o n . Fb An e x p e t i m e n t a l cryopanel c o n s i s t + n g of expended honeycomb w a s t e s t e d for t h e IBFP i n t h e Low Density Chamber. Thermocouples were a t t a c h e d , a n d t h e panel was connecged t o t h e l i q u i d n i t r o g e n (LN2) s u p p l y l i n e s i n the Low W p s i t y Chamber. The panel w a s then t e s t e d under vacuum c o n d i t i o n @ t o determine t f a w i e n t cool-down times and t o observe s t e a d y - s t a t e temperature g r a d i e n t s from t h e LN2 s u p p l y l i n e s �t o t h e edge of t h e honeycomb " f i n s . " An a d d i t i o n a l purpose of t h e t e s t s was t o determine what e f f e c t r a p i d temperature c y c l i n g might have on t h e s t r u c t u r a l i n t e g r i t y of t h e aluminum-filled epoxy bond. The expanded honeycomb c e l l s were bonded t o a 0.125-inch machined aluminum p l a t e t o form t h e cryopanel. The t e s t s were cons i d e r e d s u c c e s s f u l from t h e s t a n d p o i n t of t r a n s i e n t cool-down time and s t r u c t u r a l i n t e g r i t y of t h e epoxy bond. Except f o r some poor thermocouple c o n n e c t i o n s , t h e observed temperature g r a d i e n t s from t h e LN2 s u p p l y l i n e s (welded t o t h e cryopanel b a c k s i d e s ) t o t h e f a r t h e s t edge of t h e honeycomb " f i n s " were s t i l l w i t h i n a c c e p t a b l e l i m i t s f o r use i n t h e Impulse Base Flow F a c i l i t y (IBFF). 2. Impulse Base Flow F a c i l i t y A s i z e a b l e q u a n t i t y of d a t a has been c o l l e c t e d from t h e impact p r e s s u r e probe survey of t h e s c a l e d 5-2 engine plume. Impact p r e s s u r e v e r s u s s t a g n a t i o n p r e s s u r e d a t a were c o l l e c t e d a t v a r i o u s s t a t i o n s i n b o t h t h e a x i a l and r a d i a l p l a n e s . Data were c o l l e c t e d t o e v a l u a t e any d i f f e r e n c e s caused by s c a l i n g , combustion chamber O/F g r a d i e n t s , and O / F v a r i a t i o n s due t o v a r y i n g mass flows, and t h e d a t a a r e p r e s e n t l y being compared t o t h e t h e o r e t i c a l plume c o n f i g u r a t i o n . The experimental i n v e s t i g a t i o n i s c o n t i n u i n g w i t h t h e f l a t p l a t e p r e s s u r e impingement s u r v e y scheduled t o b e g i n February 3, 1969. Design of t h e cryopanel s y s tem i s p r o g r e s s i n g s a t i s f a c t o r i l y . S p e c i f i c a t i o n s f o r a l l a s s o c i a t e d hardware a r e 90 p e r c e n t comp l e t e . R-ME i s i n v e s t i g a t i n g some new bonding techniques f o r a t t a c h i n g t h e honeycomb m a t e r i a l t o t h e cryogenic f l u i d l i n e s . 3. High Reynolds Number Equipment F i n a l assembly of t h e High Reynolds Number Equipment has been delayed due t o t e s t s e c t i o n d e l i v e r y s l i p p a g e of 2 months. The f i r s t s h o t i s now scheduled f o r A p r i l 1, 1969. A l l welding has been completed e x c e p t one seam a t t h e d i f f u s e r elbow. This seam r e q u i r e s f i n a l alignment of t h e t u n n e l which is pending d e l i v e r y of t h e s u p e r s o n i c t e s t s e c t i o c o r s p o o l p i e c e t o r e p l a c e t h e t e s t s e c t i o n . D e l i v e r y of t h e s p o o l p i e c e i s expected February 1 0 , 1969. The s u p p l y tube c l e a n i n g , which i s approximately 50 p e r c e n t complete, should be completed by February 1 9 , 1969. C a l i b r a t i o n s c h e d u l e s a r e being made w i t h t h e f i r s t t e s t s i n t h e t u n n e l t o use a 33--static-probe r a k e . The f i r s t c a l i b r a t i o n w i l l be t h e s u b s o n i c Mach number d i s t r i b u t i o n w i t h i n the t e s t s e c t i o n . �T r a n s o n i c c a l i b r a t i o p w i l l probably f o l l o w t h e s u b s o n i c c a l i b r a t i o n provided t h e p r e s e n t d e l i v e r y s c h e d u l e of t h e t r a n s o n i c t e s t s e c t i o n i s maintained, 4. Thermal Acouetic J e t F a c i l i t y The checkout pf t h e helium h e a t e r is a t a s t a n d s t i l l . Fuel e n g i n e e r i n g p p r s a n n e l a r e c u r r e n t l y a t t h e home p l a n t r e p a i r i n g a v a r i a b l e t r a n s f o r m e r t h a t burned because of a broken carbon brush. New, h a r d e r m a t e r i a l w i l l b e used t o ~ e p l a c et h e brushes. FFCO w i l l t r u c k t h e t r a n s former t o HuntavilZe aboug February 1, 1969, and t h e checkout should c o n t i n u e then. The c o n t r a c t o r has ino t a l l e d a redesigned s t i l l i n g chamber which he f e e l s w j l l a l l e v e a t e t h e temperature f l u c t u a t i o n s i n t h e flaw. Nonuniform heatiQg of t h e storbag9 nlatrix d u r i n g t h e h e a t i n g c y c l e i s b e l i e v e d t o be capeing t h e p r ~ b i @ m ~f t h e o u t p u t a i r temperature being s o much l w e r t h a n t h e s t o r a g e pehperature. Only one p s r t f s n a£ t h e m a t r i x is a t t h e h i g h temperature and t h e surroundfng m a t e r l a l a t a much lower temperature. During c a l i b r a t i o n r u n s , t h e incoming a i r i s heated o n l y t o t h e lower tempergture. It is b e l i e v e d t h a t b e t t e r c i r c u l a t i o n o r a g i t a t i o n of phe a i r d u r i n g t h e h e a t i n g c y c l e w i l l s o l v e t h i s problem. A new c r o s s - h e m framework bas been i n s t a l l e d i n t h e Cold Flow Duct f o r t h e fnrthcowingig TITRT EeqEs. 5. 7 x 7 - i n c h B i - s o n i c Wind Tunnel A t e s t was conducted by Wyle L a b p r a t o r i e s f o r R-AERO-AU a s a p a r t of t h e experimental program f o r i n v e s t i g a t i o n of shock t u r bulence i n t e r a c t i o n phenomena. The experiment was performed t o examine t h e p r o d u c t i o n of a c o u s t i e waves i n t h e i n t e r a c t i o n of a shock wave and a t u r b u l e n c e environment. The remaining t u n n e l time was absorbed by the c o n t i n u i n g cross-beam i n v e s t i g a t i o n being performed by R-AERO-AF. 6. 1 4 x 14-inch T r i s o n i c Wind Tunnel The f o l l o w i n g i n v e s t i g a t i o n s were conducted d u r i n g December 1968 and January 1969: (1) A con tinued i n v e s t i g a t i o n by R-AERO-AD t o supplement d a t a from a n e a r l i e r Cest which wqs a n i n v e s t i g a t i o n t o determine l o c a l normal f o r c e g r a d i e p t s on cone-cylinder b o d i e s i n s u p e r s o n i c flow a t low a n g l e s of a t t w k . T o t a l runs: SO. �( 2 ) A c o n t i n u a t i o n by R-AERO-AD of a t e s t t o determine t h e cause of c e r t a i n d a t a i n c o n s i s t e n c i e s i n t h e previous phase. The o r i g i n a l i n v e s t i g a t i o n was t o determine what e f f e c t s t h e removal of t h e i n t e r s t a g e e x t e r n a l coverings could have on the aerodynamic c h a r a c t e r i s t i c s The d a t a d i s c r e p a n c y was due t o a model of a S a t u r n V c o n f i g u r a t i o n . r o l l misalignment caused by e x t e r n a l model p r o t u b e r a n c e s . The problem was c o r r e c t e d and a l l d a t a correlate'd. T o t a l runs: 143. ( 3 ) An i n v e s t i g a t i o n by R-AERO-AD t o determine t h e load d i s t r i b u t i o n a l o n g t h e s o l a r panel shroud and APS u n i t on t h e u p r a t e d AAP/Saturn I B payload c o n f i g u r a t i o n . T o t a l runs: 16. ( 4 ) A continued i n v e s t i g a t i o n by R-AERO-AD i n t o t h e a e r o dynamic p r o p e r t i e s of i n t e r s t a g e r i n g s . The t e s t was conducted t o v e r i f y previous t e s t d a t a and o b t a i n a d d i t i o n a l information. T o t a l runs: 82. (5) An i n v e s t i g a t i o n by R-AERO-AD t o determine t h e flow a n g u l a r i t y i n t h e t u n n e l a t s e l e c t e d s t a t i o n s . This i n v e s t i g a t i o n , which is p r e p a r a t o r y t o a wake s u r v e y t e s t , w i l l a i d i n a c c u r a t e c o r r e l a t i o n of d a t a . 7. Data Reduction Besides the r o u t i n e f a c i l i t y d a t a r e d u c t i o n , t h e programs f o r t h e IBFF were f i n i s h e d , checked o u t , and documented i n a Branch memo. Problems i n t h e program f o r D r . B e y l i c h , r e g a r d i n g t h e o r e t i c a l gas dynamics, were f i n a l l y c l e a r e d up and t h e MARVESS numerical i n t e g r a t i o n techniques worked w e l l . 8. Instrumentation a. High Response Balance The shock t u n n e l b a l a n c e , which was t o be used f o r f o r c e measurements on a f l a t p l a t e a s p a r t of t h e j e t plume s t u d i e s , was reworked and checked o u t . The low range of f o r c e s , t y p i c a l l y l e s s It was f i n a l l y than one pound, p r e s e n t e d c a l i b r a t i o n d i f f i c u l t i e s . resolved t h a t the l i n e a r i t y w a s s u f f i c i e n t t o c a l i b r a t e a t higher l e v e l s and i n c r e a s e t h e g a i n a f t e r t h e c a l i b r a t i o n . b. Crossed-Beam Support The f i e l d t e s t i n g of t h e m u l t i - d e t e c t o r f a n f o r t h e atmospheric crossed-beam program has been moved t o t h e v i c i n i t y of t h e R-AERO-Y f a c i l i t i e s . An i n s t r u m e n t a t i o n van, h e a t e d , a i r c o n d i t i o n e d , and c o n t a i n i n g power r e g u l a t i o n equipment and equipment r a c k s , has been borrowed from R-TEST. Three e x c e l l e n t t a p e r e c o r d e r s were a l s o i n c l u d e d . �D. Thermal Environment 1. ranch Continuum Heating and Mission Support Modeling of t h e S a t u r n AS-501 v e h i c l e f o r t h e purpoBe of c a l c u l a t i n g deafi-body h e a t i n g rates? and s k i n temperatures w i n g t h e ~ o c k h e e dSNORE-CATCH computbr prd$r&m was completed. Temperatures o b t a i n e d were cdmparcd t o t h o s e meadured 6& t h e i n n e r s k i n of t l i k I n s t r u m e n t U n i t . The c a l c b l a t e d teniperattires were approxiniately 15' lower t h a n thoge measured. Thk ef f e k t s a f a n g l e of a t t d c k a t e being added t o t h e model. $hese e f f e k t s w i l l i n c r e d s e the c a l c u l a t e d t e h p e r a t u r e s . Heatihg r a t e s and temperatbres recorded dn t h e f o r d a r d s # i k t , LH2 tank and i n t e k g t a g e of tHe 9-11 s t a g e w i l l a l s o be conipared t b r e s u l t s o b t a i n e d w i t h t h e SHORE-CA$CH p+agrefm. wdkk has begun 6i-1 thk? niotlelitig of t h e AS-203 v e h i b l e f o r the pdrpoge ti£ c $ l c u l a t i n g o t b i t a l h e a t i n g r a k e s tising ti-ie ~ B h k h e e dHe&t Rdhe c m p h t b r program. ~ & t u l t w b i l l be cdhpared t o f l i g h k d a t a t o v e r i f y t h e akWraey of t h e Heat Rate prograta. he s&OF&-CATCH computer Ptdgram mod i f i c a t i6ns a r e being checked o u t . THese fnodifibati6hS included added f l e x i b i l i t y i n i h p u t t i n g p r e s s u r e d a t a and t h e c a p d b i l i t y t U c a l c u l a t e h e a t r a t e s i t i t h e s l i p flow regime. P r e l i m i n a r y & f f d P t s have beeti made t o o b t a i n ebmputer g e n e r a t e d p l o t s fr6m t h e S ~ ~ R E - C B prograin, TC~ Attempts were d d e t o coBvert t h e Beat Rate p+ogram t o t h e 1108 EXEC V I I I dystem. ~ f d c U s & i & i s& r e b@ing h e l d t o e d r r e c t t h e e r r o r s caused by i r i c a r r e c t cdnipilatioa bf the prdgkam. 2. Mission Supputt a. Shear Laybrs The r e a l i s t i c p r e d i c t i o n of cofiditions p r e s e n t a t tHe i n j e c t o r f a c e has been s t u d i e d . These p r o p e r t i e s a r e n e c e s s a r y f o r i n p u t i n t o t h e mixing progkams used t o a n a l y z e t h e combuStion chamber. For s m a l l l i q u i d - p r o p e l l a t i ? e n g i n e s , t h e e f f k c t of d r o p l e t s i n t r o d u c e s a n a d d i t i o r f a l l o s s i n t h e combustion prdkeks. D r o p l e t v a p o r i z a t i o n models a r e b e i n g c o l l e c t e d . ~ a l c d l a t i d r iof mixing e f f e c t s i n t h e R ~ D cofibustion chamber, excluding d r o p l e t s , has been s t a r t e d . b. Nozzle and J e t Wake A f t e r t h e s t u d y of t h e R4D r o c k e t motor flow f i e l d was completed, i t wag discovered t h a t t h e m i x t u r e r a t i o d i s t r i b u t i o n Currently, e f f d r ts a r e underway t o o b t a i n documentation f o t the c o r r e c t d is t r i b u tFdh and then t o r e - r u n tHb c a l c u l a t i d h using t h e c o r r e c t e d O/F g r a d f e n t . The c a l c u l a t i o n S w i l l t h e n be compared w i t h t h e r e c e n t t e s t d a t a obtait-iod from MSC. was s u b s t a n t i a l l y d i f f e r g n t from t h e d i s t r i b u t i o n analyzed. �Work i s being conducted t o e s t a b l i s h a u s a b l e condensat i o n model f o r multi-component vapor expansion. The g r e a t e s t amount of experimental t h e o r e t i c a l work done on condensation of expanding g a s e s has been concerned w i t h pure v a p o r s . For r e a l i s t i c a p p l i c a t i o n s , an e n g i n e e r must determine the e f f e c t s of condensation i n a m u l t i - s p e c i e s vapor. M o d i f i c a t i o n s of e x i s t i n g pure vapor t h e o r i e s a r e being i n v e s t i g a t e d and used t o p r e d i c t t h e e f f e c t s of condensation i n a multi-component expanding flow. 3. Laser Velocimeter S t u d i e s A l a s e r doppler v e l o c i m e t e r has been developed which is capable of making v e l o c i t y and t u r b u l e n c e measurements on a gaseous flow. Data o b t a i n e d from measurements on a s u b s o n i c j e t have shown good promise. Comparisons between t u r b u l e n c e i n t e n s i t y and t u r b u l e n c e s p e c t r a l power d e n s i t y measurements from b o t h t h e v e l o c i m e t e r technique and the h o t w i r e anemometer method gave s a t i s f a c t o r y agreement. F u r t h e r experiments on a s u b s o n i c j e t a r e planned i n t h e l i g h t of t h e e x p e r i e n c e gained w i t h t h e f i r s t s e t of measurements. Subsequent a p p l i c a t i o n s w i l l b e t o measurements of t h e mixing r e g i o n of a s u b s o n i c j e t and flows around h i g h a n g l e - o f - a t t a c k aerodynamic p r o f i l e s . A C 0 2 l a s e r doppler v e l o c i m e t e r is being developed f o r atmospheric a p p l i c a t i o n s . A system i s being b u i l t capable of a twometer s p a t i a l r e s o l u t i o n a t 150 meters which w i l l be used t o s t u d y t h e v e r t i c a l wind v e l o c i t y p r o f i l e near t h e e a r t h ' s s u r f a c e . Subsequent a p p l i c a t i o n s a r e t h e s t u d y of t r a i l i n g v o r t i c e s g e n e r a t e d by a i r c r a f t and t h e long range d e t e c t i o n of c l e a r a i r t u r b u l e n c e . 4. O p t i c a l Measurements of Plumes A cold flow t e s t was conducted a t AEDC w i t h a l a s e r d o p p l e r v e l o c i t y i n s t r u m e n t ( v e l o c i m e t e r ) t o determine t h e v e l o c i t y f i e l d i n t h e b a s e and e x h a u s t r e g i o n s of a four-nozzle model of t h e S a t u r n I1 type. The t e s t was t h e f i r s t e f f o r t t o use t h e v e l o c i m e t e r i n a low d e n s i t y s u p e r s o n i c flow. An e q u a l l y important purpose of t h e t e s t was t o e v a l u a t e t h e v e l o c i m e t e r and v e l o c i m e t e r s u p p o r t systems ( e l e c t r o n i c and contaminant systems) a s an i n t e g r a t e d system. While t h e week of t e s t i n g d i d n o t produce t h e v e l o c i t y f i e l d , t h e s y s tem "shakedown" has provided an important b a s i s f o r i n s t r u m e n t changes t h a t should extend t h e instrument range t o i n c l u d e flow f i e l d s o f t h e type encountered i n t h e t e s t . Those changes a r e c u r r e n t l y being e v a l u a t e d i n response t o a r e - e n t r y of t h e cold flow t e s t t e n t a t i v e l y scheduled f o r September 1970. I n a d d i t i o n , r e f i n e ments a r e b e i n g considered t o upgrade the r e l i a b i l i t y of the v e l o c i meter s u p p o r t system. A l l of t h e instrument and instrument s u p p o r t system d e f i c i e n c i e s a r e being e v a l u a t e d i n p r e p a r a t i o n f o r t h e 1970 t e s t entry. �5. Plume fmpingement Heating & e a t i n g ratee t o v a r i o u s components on the ~ a t u r n l A Acon~ f i g u r a t i o n due t o plume impingement a r e b e i n 8 c a l c u l a t e d . S p e c i f i c a r e a s b e i n g Cohsidered are (1) h p i n g e ~ e n ts f W/RCS engine on MDA r b d i a t i o ~ , q (2) i i - i n g e i n e n t of WJRCQ kngiIIed 6a Solded ATM s o l a r p a n e l s , (3) impingeinent of ESMJRCB engfiies ori MDr$ forwbrd cone, and (4) impingement of cSM/ RCS engines on unfolded Am s o l a r p a n e l s . The a n a l y s i s of ebe f i r s t t h r e e a r e a s i s ebmplete and is being d o c w n t e d . The fourth. a r e a has been analyzed Bed pre1j;mlmry r e s u l t s have been o b t a i n e d . !Phis p r e l iminary arlalyO is $8 p r e s e n t l y being *ef i n e d , The Egret: I3yfFrirplizaLig-n ~ e & t p i u ; l ~a ~aumeficsal m t h a d t o o b t a i h t h e 5hI@@otao 8BlQtioit Q& & iskt a5 p a r t i a l dLEEer@ntfal equatioHs, has sa@ee$8ful hy salved t h e Pdoai pa$ t r a n s o h l g f l~ problem. The method has d-ngtrdted i t &$ b i l i t y t e fiad smooth and ~e.11-behaved flow f i e l d solyk%oi%$ Pn hoaile @siBtltguus~ 5 t ha v a r y sm.zill ithpoat raddus of c u r v a t u r e . Th%sW r k has bee& d 6 c m e a t e d i n Lockheed dDkswment TM 541 20-213, ~ s G / & U ~ C B~a46622~ '"A $ & ~ f i s o n i cN ~ i a l eS o l u t i o n the E r r o r MTQimFzation ~ e e h n i q u e , 'bp ~ R, J, B~D$FABJ .dind D. E. Ko.ok@t, J&naasy 1969. F u t u r e plans ckll fi6r Bncok@or.ihk$LqkAs ief Eects -sf equi'i$be&umJf rozen r e a c t i n g g a s m t z t u r c $ and f u e l ~ t & $ & t ~ i e (OJF n S g ~ a d i e n a )i n t o t h e praeenk t r a n g d n i c nbsele siolkitbh. The c a l c u l a t i p n of %he e 1 e c t r - e ~ d e n s i t y d i s t r i b u t i o n i n t h e 5 n v I s c i d plume and the S h a r layer QZ tb6 Z"I e e h e exha@t plume a t 10,'04)0 f e e t a l t i t d e has been ,eMpl.eted, The Aero-Cbem ~ ~ y k e c iStreamd lcme 'P'rograni bad bee^ mod h g b d to faei.1 & a t e bts u s e by witking ~ m u n $ c a eion of d a t a from the f l o e f i e l d grograms d i r e c t and automatkc. The c a p a b i l i t y t o restarc t h e &alcukbrtLon a16Dg .a s t r e a m l i n e has been added to p r o v i d e a n a c c u r a t e me-t:b'od t o compu.te entire nozzle l e n g t h w i t h o u t r e g u i r ing excess i v e b l o c k s @f Icorgputer r u n tidies . he BASAI Lewii$, k h e m . ~ c h e m j m lanalys i s i.n bas f c f o m u l a t i o n Is s h i t e d !to p r e d i c t Dhe d e g r e e of ioni.uation and hence s h e e l e c t r o n mole d e h ~ S k yWE a gaseous tays tern a t e q u i l Zbriumn, U n f o r t u n a t e l y , S T E ~ E ~ ~ ?of ~IS i o n $ ~ e dS p e c i e s and Eree,e;lecCrons a r e s o s m a l l , from a the~moChem5ca.l :p.Oint of v . W , chat tL&, A $ A / ~ e w i sprogram i s n u m e r i c a l l y aneaiired ,t,o p e r F ~ r mt h e cailcul&~tian. A supplemental t e c b n t q u e has been pr&gramed t.o p e r f o r m "this ~ a l c u ; L : ~ t i Th5s ~ n ~ !program, which is b e i n g che*ed ouZ, r e q - u b e s ou%ptit fr a n t h e ~ U A l ~ e w ic sa l c u l a t i ~ nas .input. �8, Vacuum ~ G ~ ai o n ns Study The purpose of t h i s i n v e s t i g a t i o n i s t o develop a mathem a t i c a l technique f o r t h e d e s c r i p t i o n of t h e h i g h a l t i t u d e and s p a c e An experimental environment expansion of an axisymme t r i c gaseous j e t . program w i l l be conducted t o provide experimental d a t a f o r comparison with a n a l y t i c a l predictions. A s e t of p a r t i a l d i f f e r e n t i a l e q u a t i o n s which d e f i n e t h e v e l o c i t y , d e n s i t y and s t r e s s t e n s i o n i n t h e flow f i e l d has been d e r i v e d . This d e r i v a t i o n was made f o r a s i n g l e component, monatomic g a s , u s i n g t h e B-G-K approximation f o r t h e c o l l i s i o n i n t e g r a l . M e t h o d - o f - c h a r a c t e r i s t i c s s o l u t i o n s t o t h i s s e t of equat i o n s have been developed f o r t h e c a s e s of n e g l i g i b l e and non-neglig i b l e s h e a r s t r e s s . These s o l u t i o n s a r e c u r r e n t l y being programmed. Using t h e m e t h o d - o f - c h a r a c t e r i s t i c s e q u a t i o n s , r e p o r t e d i n t h e previous p r o g r e s s r e p o r t , a s e t of e q u a t i o n s was obtained f o r d e s c r i b i n g t h e flow around a c o r n e r expansion, s u c h a s a n o z z l e l i p . A computer program has been developed f o r a m e t h o d - o f - c h a r a c t e r i s t i c s nozzle plume flow f i e l d , i n c l u d i n g t h e corner expansion. This program i s being checked o u t . 9. Study of Dual Channel Spectroradiometer An i n t e r i m r e p o r t (Rocketdyne Report R-7733) d e s c r i b i n g t h e d a t a o b t a i n e d under Phase I1 of t h e c o n t r a c t has been r e c e i v e d . S p e c t r a l d a t a and zone r a d i o m e t r y d a t a were obtained a t t h e e x i t p l a n e of a b e l l n o z z l e f o r f i v e d i f f e r e n t p r o p e l l e n t combinations. These d a t a , however, were n o t s u f f i c i e n t t o determine temperature and s p e c i e p a r t i a l pressure p r o f i l e s . The s p e c t r o r a d i o m e t e r i s now being modified t o a l l o w f a s t e r s c a n r a t e s and w i l l be used t o o b t a i n a d d i t i o n a l d a t a on f i r i n g s t o be conducted i n March. E. Unsteady Gas Dynamics Branch 1. I n f l i g h t Acoustic a . Data r e d u c t i o n a n a l y s i s has begun on t h e AEDC 4 p e r c e n t model s u p e r s o n i c d a t a . C u r r e n t l y , o v e r a l l l e v e l s s c a l e d t o f u l l s c a l e c o n d i t i o n s a r e being computed and p l o t t e d . Cross spectrum a n a l y s i s has begun. b. The experimental p o r t i o n of t h e shock t u r b u l e n c e i n t e r a c t i o n s t u d i e s has been completed. The d a t a a r e being reduced. - �c. A d d i t i o n a l c o n t r a c t work f o r t h e "Development of F u l l P n f l i g h t A c o u s t i c Design C r i t e r i a S c a l i n g E f f e c t s " has been i n i t i a t e d . Data from AMES' f o u r p e r c e n t S a t u r n V, PSTL-1 and PSTL-2 wind t u n n e l t e s t c o n d i t i o n s and f l i g h t w i l l be used. A l l o t h e r d a t a a v a i l a b l e i n t h e l i t e t a t u r e w i l l be included. p r e l i m i n a r y d a t a r e d u c t i o n is continuing. d. A wind tclnnel prograth has been conducted i n t h e AEDC 1 6 - f o o t t r a n s o n i c t u n n e l t o provide experimental i n f o r m a t i o n t o h e l p d e r i v e methods by which f l u c t u a t i n g a i r l o a d s i n t h e r e g i o n a£ prohis wind tuberances can be a c c u r a t e l y p r e d i c t e d on launch v e h i c l e s . t u n n e l t e s t program is i n s u p p o r t of a c d d k r a c t w i t h Wyle L a b o r a t o r i e s , H u n t s v i l l e , Alabama e n t i t l e d "En%irbnment Around ProtubBtances SubS t a t i c p r e s s u r e d a t a have been analyzed merged i n a Boclndairjir Layer.'' afid t h e pkelimihqk$ & e d u c t i o n bf the f l u c t h a t i n g p r e s s u r e d a t a iS i n pragres8, e. A j o i n t MSFc/Air Fotce wirld t u n n e l t e s t plPogram has been conducted. his t e s t program c o n ~ i s t e dof s e v e r a l becofiic hose c o n f i g u r a t i o n s which w i l l provide a b a s i s f o r a n a l y s e s of t h e c r o s s c o r r e l a t i o n c h a r a c t e r i s t i c s ( a e e e s s a r y f o r d e s i g n c r i t e r i a ) of t h e i n f l i g h t f l u c t u a t i n g p r e s s u r e e n v i r o m e n t f o r v a r i o u s AAP mibsions. U P d e s i g n s p e c i f i e r t t i o n s a r e e t t r r e n t l y being d e r i v e d frbm t h e s e d a t a . The i n i t i a l s p e c i f i c a t i o n s f o r U P - 2 and 4 w i l l i n c l u d e o v a f a l l l e v e l s v e r s u s body s t a t i o n , 2. ~ a u n c hS i t e Acd.ustics a. A c t i v i t y a t t h e Acoustic Model T e s t F a c i l i t y (AMTF) a t T e s t L a b o r a t o r y has slowed d u r i a g t h e p$st mbnth. Plans a r e now being i n i t i a t e d t o conduct a 20 percetlt S a t u r n V model r o c k e t n o i e e e x p e r i ment. This experiment has been desighed t o o b t a i n amplitude and phase ifiform8tion f o r b o t h t h e launch and s t a t i c f i r i n g c o n d i t i o n of t h e S a t u r n V v e h i c l e . S p e c t r d l and s p a t i a l c o r r e l a t i o n c h a r a c t e r i s t i c s w i l l be o b t a i n e d f o r a v e h i c l e a s w e l l as t h e immediate launch cunplex , area . b. The s t u d y of ground a t t e n u a t i o n e f f e c t s on a c o u s t i c wav6 p r o p a g a t i o n i s c o n t i n u i n g w i t h more d e t a i l e d a n a l y s i s being g i v e n t o t h e m e t e o r o l o g i c a l parameters. A & r e a p p l i c a b l e model i n terms of t h e p h y s i c a l phenomena i s being sought f o r p r e d i c t i o n a c c u r a c y a p p l i c a t i a n of t h e r e s u l t s . ' �3. Panel F l u t t e r a . The upcoming h i g h a l t i t u d e S a t u r n V S-IVB p a n e l f l u t t e r t e s t , o r i g i n a l l y s c h e d u l e d t o e n t e r t h e ARC 2 x 2 - f o o t t r a n s o n i c wind t u n n e l i n F e b r u a r y 1969, has been d e l a y e d b e c a u s e t h e n o n c o n t a c t i n g d i s p l a c e m e n t m e t e r s were n o t o b t a i n e d on s c h e d u l e . To d a t e , t h e o n l y company t o respond t o a n RFQ f o r t h e s e m e t e r s i s t h e Wayne-Kerr Corporat i o n of G r e a t B r i t a i n . T h i s , of c o u r s e , has caused problems due t o t h e "Buy American Act" c o n t a i n e d i n t h e C o n t r a c t (NAS8-21250). These m e t e r s a r e r e q u i r e d f o r v i b r a t i o n t e s t s b e f o r e t h e wind t u n n e l t e s t , as w e l l as f o r t h e wind t u n n e l t e s t i t s e l f . T h e r e f o r e , t h i s d e l a y h a s postponed t h e t u n n e l e n t r y d a t e u n t i l a t l e a s t May 1969. No problems have been e n c o u n t e r e d f o r t h e r e s t of t h e g o v e r n m e n t - f u r n i s h e d equipment r e q u i r e d f o r t h i s c o n t r a c t . The boundary l a y e r r a k e r e q u i r e d h a s been f a b r i c a t e d and w i l l be s h i p p e d t o McDonnell w i t h i n t h e n e x t few d a y s , b . The roughened s o l i d s i d e w a l l boundary l a y e r p r o f i l e i n v e s t i g a t i o n , conducted i n t h e MSFC 1 4 x 1 4 - i n c h t r i s o n i c wind t u n n e l i n s u p p o r t o f t h e above mentioned p a n e l f l u t t e r t e s t , h a s y i e l d e d good r e s u l t s . A memorandum i s b e i n g p r e p a r e d t o d e s c r i b e t h e t e s t and present the data. c . S t u d i e s t o d e t e r m i n e t h e l i m i t c y c l e b e h a v i o r of f l u t t e r i n g clamped p l a t e s , t a k i n g i n t o a c c o u n t t h e e f f e c t s of i n - p l a n e compress i v e l o a d s , d i f f e r e n t i a l p r e s s u r e l o a d i n g s and c a v i t y , a r e b e i n g continued. The computer program, developed by P r o f e s s o r E a r l H. Dowell and P r o f e s s o r Voss a t P r i n c e t o n U n i v e r s i t y , was m o d i f i e d t o c a l c u l a t e (1) f u l l l i n e a r i z e d aerodynamic f o r c e s , ( 2 ) f l u t t e r r e s p o n s e u s i n g t h e computed aerodynamic f o r c e , and ( 3 ) s t r e s s e s i n p a n e l due t o i t s f l u t t e r deformation. 4. Ground Winds A d d i t i o n a l S a t u r n V wind t u n n e l t e s t d a t a have b e e n f u l l y reduced u s i n g t h e Lockheed and Boeing d a t a a n a l y s i s programs. E f f o r t s a r e underway t o u s e t h i s newly reduced d a t a i n b e t t e r d e f i n i n g S a t u r n V f u l l - s c a l e l o a d p r e d i c t i o n s f o r a l l b a s i c on-pad w e i g h t c o n f i g u r a t i o n s w i t h and w i t h o u t t h e MSS, and w i t h and w i t h o u t t h e damper a t t a c h e d (where a p p l i c a b l e ) . A p r e l i m i n a r y i n v e s t i g a t i o n h a s b e e n conducted i n r e d u c i n g ground winds w i n d - t u n n e l t e s t d a t a by means of a n a n a l o g s y s tem. The method a p p e a r s f e a s i b l e and t h e b a s i c a n a l o g c i r c u i t h a s b e e n �o u t l i n e d f o r t h e d a t a r e d u c t i o n system. Design and c o n s t r u c t i o n of t h e analog system w i l l be completed when funds a r e approved. Load p r e d i c t i o n s were made f o r the most c r i t i c a l wind a z i muths of t h e S a t u r n V AS-503 v e h i c l e c o n f i g u r a t i o n s d u r i n g launch coyntdown f o r s e v e r a l wind p r o f i l e s f o r m o n i t o r s h i p of AS-503 CDDT and launch countdown. This type of wind load p r e d i c t i o n s i s being extended f o r more c r i t i c a l wind azimuths and weight c o n f i g u r a t i o n s f o r AS-504 and subsequent v e h i c l e s , A s t u d y t o determine second mode e f f e c t s on ground wind l o a d i n g s f o r t h e S a t u r n V v e h i c l e i s s t i l l i n p r o g r e s s . Also, a prel i m i n a r y s t u d y has been conducted t o determine t h e e f f e c t s on graund wind load p r e d i c t i o n s r e s u l t i n g from measuring wind v e l o c i t i e s a t t h e 445-foot EUT l e v e l r a t h e r t h a n t h e 60-foot l e v e l . VI. ASTRODYNAMfCS AUD GUIDAEJCE THEDRY DIVISION A. O p t i m i z a t i o n Theory Branch 1. Lunar Roving Vehicle S t u d i e s P r o p o s a l s submitted i n response t o t h e c e n t e r ' s RFQ f o r phase B s t u d i e s of a d u a l mods l u n a r roving v e h i c l e (DLRV) were e v a l u a t e d and recommendations were submitted cansernipg t h e e f f o r t s proposed by each c o n t r a c t o r i n the a r e a s of n a v i g a t i o n , remote c o n t r o l o p e r a t i o n , and hazard avoidance. I n a d d i t i o n , r e q u e s t s f o r s u p p o r t i n g r e s e a r c h funds were made i n t h e a r e a s of (1) pre-programmed c o n t r o l s t r a t e g i e s f o r reducing t h e work load on t h e earth-based o p e r a t o r of unmanned LRV'S, ( 2 ) improvement of LRV n a v i g a t i o n a l accuracy through updating and c o r r e l a t i o n , ( 3 ) computer s i m u l a t i o n of s u r f a c e movement of unmanned LRV's f o r t h e development of ecanornical and r a p i d means of a s s e s s i n g t h e dynamic performance of unmanned LRV'S under d i f f e r e n t modes of o p e r a t i o n , and (4) u s e of non-imaging s e n s o r s t o avoid t e r r a i n hazards t o continued m o b i l i t y which were not d e t e c t e d by v i s u a l or o t h e r s e n s o r s a t t h e l a s t d e c l s i o n p o i n t i n s t o p - g o o p e r a t i o n of a n unmanned LRV. In-house s t u d i e s i n s u p p o r t of t h e program a r e p r o g r e s s i n g . 2. Lunar T a r g e t i n g S t u d i e s - Northrop (Schedule Order 60) During t h e r e p o r t i n g i n t e r v a l , t h e c o n t r a c t o r was d i r e c t e d t o suspend h i s p r i o r invee t i g a t i o n s ( s e e item 63 and t e m p o r a r i l y r e d i r e c t h i s e f f o r t s t o s u p p o r t l u n a r t a r g e t i n g i n v e s t i g a t i o n s being conducted i n t h e d i v i s i o n . I n s u p p o r t of t h e s e Fnves t i g a t i o n s , t h e c o n t r a c t o r w i l l modify t h e 6-D in-house computer program used f o r t a r g e t i n g v e r i f i c a t i o n t o a n approximate 3-D program and a s c e r t a i n whether o r n o t t h e r e s u l t i n g �accuracy is operational t h a t i t has t o r y and w i tation. s u f f i c i e n t t o use t h e 3-D program i n c e r t a i n phases of t h e verification. E f f o r t s have been hampered by t h e time (5 weeks) taken t o g e t a copy o f 4 t h e program from t h e Computation Laboral l be f u r t h e r hampered'by the complEte l a c k of program documen- In-house e f f o F t s to. convert7,a t a r g e t i n g v e r i f i c a t i o n computer program t o t h e 1108 have b e e n suspended because of t h e u s e r ' s r e c e n t i n t e r e s t i n a n o t h e r program u n d e ~development. 3. Parameter op;im?zat?on (Schedule Order 64) Studies f o r ARI - Lockheed 1 The hybrid computer program employed i n t h i s s t u d y i s operat i o n a l . During t h i s r e p o r t i n g p e r i o d , a n i n i t i a l s e r i e s of p r o d u c t i o n runs was made t o d e f i n e t h e form of performance index t h a t w i l l b e s t f i t the design objectives. 4. T r a j e c t o r y Optimization - Northrop (Schedule Order 59) F i n a l c o p i e s of t h e r e p o r t on Runge-Kutta formulas f o r second-order d i f f e r e n t i a l e q u a t i o n s have been d i s t r i b u t e d . On January 1 4 , t h e c o n t r a c t o r gave a n o r a l p r e s e n t a t i o n t o a l l i n t e r e s t e d persons i n t h e d i v i s i o n . The t a l k covered work done over t h e p a s t year and concluded w i t h a summary of c u r r e n t p r o j e c t s and aims, C u r r e n t l y , the c o n t r a c t o r i s c o n t i n u i n g t h e i n v e s t i g a t i o n i n t o o b t a i n i n g expansions of Lagrange m u l t i p l i e r s i n terms of a n impulsive s o l u t i o n . S e v e r a l n e c e s s a r y b a s i c e q u a t i o n s have been s u c c e s s f u l l y d e r i v e d t o date. 5. C-Minimax Control a . The p o s s i b i l i t y of c o n v e r t i n g a c o n t r o l problem of t h e C-minimax type i n t o a n e q u i v a l e n t Mayer problem and s o l v i n g t h e l a t t e r problem v i a t h e techniques of t h e c a l c u l u s of v a r i a t i o n s i s being s t u d i e d ; problems a r i s e due t o t h e d i s c o n t i n u i t i e s i n t h e d e r i v a t i v e s of t h e s t a t e v a r i a b l e s i n t h e proposed f o r m u l a t i o n . A review of t e x t s and papers i n the f i e l d i s i n progress. b. General DynamicslConvair (NAS8-21456) Objectives: (1) To extend t h e C-Minimax t h e o r y t o determine C-Minimax performance i n t h e presence of inconipletely s p e c i f i e d d i s t u r b a n c e s ; ( 2 ) t o determine i f a n a n a l y t i c s o l u t i o n e x i s t s f o r C-Minimax performance f o r l i n e a r dynamical systems w i t h bounded c o n t r o l ; and (3) t o i n v e s t i g a t e t h e computational problems discovered t o e x i s t w i t h t h e c u r r e n t computational a l g o r i t h m s . . �S u f f i c i e n t c o n d i t i o n s fo? c o n t r o l of l i n e a r systems i n t h e presence of d i s t u r b a n c e s of known form s o as t o a t t a i n t h e s p e c i f i e d t e r m i n a l c o n d i t i o n s have been developed d u r i n g t h e r e p o r t i n g period and a r e being, i n v e s t i g a t e d t o determine t h e i r u t i l i t y . S m e theorems r e g a r d ing t h e r e d u c i b i l i t y of high-order Systems to e f f e c t i v e low-order s y s teme f o r c e r t a i n r e s t r i c t e d C-minfmax performance i n d i c e s have a l s o been developed. 6. Launch Vehicle Control a. S t a t i s t i c a l Wind Model - Hayes (NAS8-21444) Objectives C o n s t r u c t i o n of a wind model f o r use i n s t a t i s t i c a l a n a l y s i s of launch v e h i c l e performance. Data r e d u c t i o n on MSFC computers has been s t i c c e o s f u l l y completed. The reduced d a t a have been d e l i v e r e d , and t h e c o n t r a c t o r is c o n f i d e n t of completing t h e g o a l s of t h e s t u d y . Because of t h e time l o s t i n d a t a r e d u c t i o n , they have r e q u e s t e d and r e c e i v e d a one-month no-cost e x t e n s i o n f o r t h e c o n t r a c t . The f i n a l r e p o r t i s now expected a t t h e end of February. b. S a t u r n V/Apollo Load R e l i e f (Schedule Order 60) - Northrap The c o n t r a c t o r ' s e f f o r t s 'have been t e m p o r a r i l y r e d i r e c t e d from t h i s a r e a ( s e e item 2 above). P r i o r t o t h e r e d i r e c t i o n , t h e cont r a c t o r had completed p r e l i m i n a r y s t a t i s t i c a l response s t u d i e s of t h e proposed load r e l i e f c o n t r o l law f o r t h e S a t u r n po pol lo on RAAERO-D'S high-speed analog f a c i l i t y . I n i t i a l e v a l u a t i o n of t h e r e s u l t s w a s favorable. B. As trodynamics Branch 1. Broken-Plane T r a j e c t o r i e s (Lockheed) Work continued on t h e development and checkout of new subr o u t i n e s f o r t h e General Broken-Plane Computer Program. Equations were w r i t t e n and p r o g r a m e d t o t e l a r e t h e i n c l i n a t i o n of t h e d e p a r t u r e and a r r i v a l p l a n e t o t h e t r a n s f e r a n g l e and t h e p o s i t i o n of t h e d e p a r t u r e and a r r i v a l planes w i t h r e s p e c t t o t h e l i n e of nodes. A u s e r ' s manual f o r t h e LMSC Broken-Plane I n t e r p l a n e t a r y T r a j e c t o r y Program by J. D. P a r r o t t , LMSC/HREC ~ 1 4 8 5 0 0 ,December 1968, was completed and d e l i v e r e d Do R-AERO-GA, �2. Mission Design C h a r t s a . Work was completed on t h e paper e n t i t l e d , "The A s t r o dynamicis t 's Role V i s -A-Vis t h e Sys terns Engineer. " The paper was p r e s e n t e d a t t h e AIAA 7 t h Aerospace Sciences Meeting i n New York. b. Work i s c o n t i n u i n g on t h e g e n e r a t i o n and r e p r e s e n t a - t i o n of a s trodynamical parameters used i n m i s s i o n a n a l y s i s s t u d i e s . The d a t a r e p r e s e n t i n g Earth-Mars t r a n s f e r s w i l l be p r e s e n t e d over a 15-year c y c l e of 7 s y n o d i c p e r i o d s . The method of p r e s e n t a t i o n of t h e d a t a w i l l f o l l o w t h e procedure o u t l i n e d i n t h e paper mentioned i n (a) above. 3. I n t e r p l a n e t a r y N-Body Programs a. Program Development (Lockheed) Work continued on t h e checkout of t h e N-Body I n t e r p l a n e t a r y T r a j e c t o r y Program. It w a s converted t o F o r t r a n I V language, and checkout of t h e 11 d i f f e r e n t o p t i o n s is underway. Also, a n i n v e s t i g a t i o n of methods of g r a p h i c a l l y p r e s e n t i n g i n t e r p l a n e t a r y d a t a i s underway. b. I s o l a t i o n Routine and T a r g e t i n g S t u d i e s (Northrop) The summary r e p o r t is i n f i n a l p r e p a r a t i o n and w i l l be d e l i v e r e d t o c o g n i z a n t MSFC p e r s o n n e l when completed. 4. O r b i t a l T r a n s f e r (Lockheed) Work continued on t h e i n v e s t i g a t i o n of methods of g r a p h i c a l l y p r e s e n t i n g i n t e r p l a n e t a r y t r a j e c t o r y d a t a , s u c h t h a t t h e m e r i t s of d i r e c t s i n g l e - p l a n e , broken-plane and p l a n e t a r y swingby t r a n s i t s can be r a p i d l y a s s e s s e d f o r a g i v e n m i s s i o n o p p o r t u n i t y . Computer r o u t i n e s were developed t o p l o t t h e h e l i o c e n t r i c r a d i u s , l o n g i t u d e and d i f f e r e n c e i n l o n g i t u d e s between two g i v e n p l a n e t s . These w i l l be used i n p r e d i c t i n g p l a n e t a r y encounter d a t e s t h a t r e s u l t i n f a v o r a b l e i n t e r p l a n e t a r y transfers . 5. O r b i t s i n Non-Central F i e l d s E f f o r t s a r e s t i l l b e i n g made t o c h a r a c t e r i z e c o n v e n i e n t l y t h o s e t r a n s f o r m a t i o n s of Euclidean 3-space which w i l l g i v e r i s e t o no c r o s s - p r o d u c t s i n transformed momenta. �6. Abort and A 1 t e r n a t e Migsions (Boeing) A f i n a l r e p o r t from Boeing f a r SSR-222 w a s r e c e i v e d t h e f i r s t of December. he‘ ma@ ab j p c r i u e of t b i s s t u d y was t o d e s i g n a g i n g l e e q g i n e - o u ~ gu jdance pethod $ h a t ~ o n f s r m st o a l l known r e s fr i c t i o n s g e n g i t i v e t q chqgges i q m$ssion, environment, o r v e h i c l e . and i s ~ i m p l i c i t yand rnfnirnum i m p g ~ tgn the f l i g h t program were considered major d e s i g n g o a l s . q e gyidance metbads m on side red were t o s a t i s f y t h e r e q u i r e ments of succesgf y l f l i g h t throuqh t h e maximym dynamic prgssHre r e g i o n , and c o n d i t i o n s g t 8-Ie burnout which a r e a c c e p t a b l e f o r S - I I s t a g e f l i g h t . The p r e s e n t e q g i p e s o q t c h i q f r e e z e metbgd dpes n o t meet tFe l g t t e y r e g u i r e ment f o r a l l c a s e s of engiqe o u t . D a t a f o r t h e AS-504 v e h i c l e were used f o r t h i s phase of t h e gtydy. * nq The f ~ l l o w i q gengfpe-out guidaqce methods weFe s x d t e d and eyaluated: (2) B r o p e l l a n t d e p l e t i o q f q y c e n t e r engipe c u t o f f . (3) T i l t arrest a t c e p t e r engine c u t o f f , ( 4 ) Mpdified p i t c h ~ ~ l y n w j . qcfo e f f i c i e n t s . (5) $Eeeying m$qglfg?mgpt ~ @ ? c r e $ t i afqo l l a w i ~ gengine o p t . (6) S e p a r a t e c h i - f r e e z e s c h e d u l e f o r upper and l ~ w e renggne failures, The r e s u l t s were t h a t the s e g a r a t e c h i - f r e e z e s c k e d u l e f q r upper and lo we^ e n g j n e f a i l u r e s b e s t met phe engine-out guidqnce r e q q i r e ments w i t h o u t e x t e n s i v e f l i g h t prograni changes. There would n o t , however, be enough time t o implement2t h e ~ eclzangps on t h e 504 f l i g h t , and a new c h i f r e e z e s c h e d u l e was o f f e r e d a s a n a l t e r n a t i y e t o t h e e x i s t i n g one f o r t h e AS-504 f l i g h t . A copy of t h e r e p o r t ~ a n t a l n i n gt h e s e r e s u l t s wqs g i v e n t o R-AEROIF. The a l t e r n a t e c b i - f r e e z e s c h e d u l e f o r AS-504 w a s implemented and c o q s i d e r a t i o n of t h e q s e of a c h i - f r e e z e s c h e d u l e based on knowledge a£ an upper o r lower engine f a i l y r e f ~ f ru t u r e f l i g h t s was recommended. 7. O c c q l t a t i o n S t u d i e s (Lockheed) The Blqne t g ~ yO r b i t Des i g a and Occut t a t i o n Computer Program i s being mod j f i e d t o q q l ~ g l a t et h e occultation c h a r a c t e r i s t i c s qf a prgbe qn a h y p e r b o l i c sp$ngky of t h e t a r g e t p l q n e t . C h a r a c t e r i s t i c s w i l l be c a l c u l a t e d from t h e time t h e probe e n t e r s t h e p l a n e t ' s s p h e r e a f i n f l u ence t o t h e time it l e a v e s . �Guidance Theory Branch C. 1. Support C o n t r a c t S t u d i e s a. Lunar T a r g e t i n g Analysis Using QUOTA The l u n a r t a r g e t i n g a n a l y s i s using QUOTA is s t i l l plagued w i t h s e n s i t i v i t y problems. E f f o r t s a r e c o n t i n u i n g toward improving t h e s e c a n t i s o l a t i o n scheme. A s i n g l e - p r e c i s i o n v e r s i o n of t h e l u n a r t a r g e t ing program was g e n e r a t e d on t h e 1108 computer. E f f o r t s a r e b e i n g made t o c o n v e r t t h i s program t o double p r e c i s ion. b. Quasi-Optimal Guidance Study Documentation of t h e QUOTA guidance scheme has been i n i t i a t e d . The document w i l l b a s i c a l l y summarize t h e complete QUOTA scheme w i t h t h e main emphasis on t h e minimum time problem, o r b i t a l t r a n s f e r and rendezvous. A p p l i c a t i o n of QUOTA t o AAP type rendezvous m i s s i o n s i s s t i l l under s t u d y . c. O r b i t Trim Systems E r r o r Analysis An a n a l y t i c technique i n d i c a t e s t h a t e f f e c t s of a n o r b i t t r i m maneuver upon t h e n a v i g a t i o n u n c e r t a i n t i e s w i l l be q u i t e s m a l l . Three Monte C a r l o s i m u l a t i o n t e s t c a s e s t o v e r i f y t h i s r e s u l t a r e being run. V e r i f i c a t i o n of t h i s r e s u l t i s i m p o r t a n t , s i n c e i t provides a b a s i s f o r decoupling n a v i g a t i o n u n c e r t a i n t y e f f e c t s and e x e c u t i o n u n c e r t a i n t y effects . d. Optimal Guidance Study Work is c o n t i n u i n g on the checkout of t h e g e n e r a l t h r e e dimensional optimal o r b i t a l t r a n s f e r computer program. Also, e f f o r t s t o o b t a i n good i n i t i a l g u e s s e s f o r t h i s computer program u t i l i z i n g impulsive conic s o l u t i o n s i s continuing. 2. Contracts a. - IBM A p p l i c a t i o n of Numerical Methods t o Extend C a p a b i l i t i e s f o r Optimal Rocket Guidance During t h i s r e p o r t i n g p e r i o d , t h e improvements t o t h e f i n i t e t h r u s t optimal o r b i t a l t r a n s g e r deck which were i n c o r p o r a t e d d u r i n g t h e l a s t r e p o r t i n g p e r i o d have been completely checked o u t . The program w i l l converge v e r y r a p i d l y f o r a v a r i e t y of i n i t i a l c o n d i t i o n s (about 3 seconds per c a s e ) . E v a l u a t i o n of the d e c k ' s c a p a b i l i t i e s f o r low t h r u s t o r b i t t r a n s f e r s i s now underway. - �b. Lockheed - Rerldedtous ~uidance The d i g i t a l programming of the r e g u l a r i z e d e q u a t i o n s i s s t i l l under-going checkout. The kdugh d r a f t of t h e f i n a l r e p o r t is being started. c. North American The computer pkogtam fop corhputing oprimai f i a i t e t h r u s t o r b i t a l t r a n ~ f k r sby q u a s i - l i n e a r i z d t i d n is e s s e n t i a l l y cotK@lete a l t h o u g h i t s t i l l hGs dif f i c t i l t y cbhverging same i s o i a r e t l c a s e s . A14d, a d d i k i d n s t o t h e program f o r i n p u t and s u t p b t i n a $ B r i e t y bf syse&ms of u n i t s were conipleted d u r i h b t h i h t e p b r t i n g p e r i o d . Eahvefsicin af t h e &beihg Q R ~ $t o the 1108 is p r d g r w s i n g d t a f a s t e t r a t e kh&h $ h t i c i p a t e d ; s e v e r a l e r r d f e i n €He pwgkarn (Boeing c o r r e c t e d theSe errbrs a f t e r we r e c e i v e d the program) k e r e discovered and t h e s e have been c o r r e c t e d . ~ o k ht h e t a r g e t i n g o p t i o n Bad midcourse c a r r e c t i o n o p t i o n have been checketl Out w i t h card i n p u t . These o p t i o n s w i t h i n p u t from t a p e have n o t Been rllecked o u t . It iS hopgd t h a t t h i s program w i l l be completely k o m k r t e d and ready f o r R-AERO-F w i t h t n a few weeks. An i n v k s t i g a t i o n was inad& t o determine wHat chdnges t o t h e QRTP would b e r e q t i i l c d iri ofdef tei t a r g c k high p e r i l u n e t r ~ j e c t o r i e s . ~t a p p e a r s t h a t the progrdm h&3 the c d p a b i l i t y t o Handle t h i s type of missiari w i t h o u t modifying it. It isi planded t o t a r g e t a t e s t cage t o verify this. The patched c o n i c s o l u t i o n a£ ~ a m b e r t ' s prdblem i n v o l v i n g t h e use of p a + t i a l d c r i v d t i v e t r a n s i t i o n m a t r i c e s is now s p e k a t i o n a l . This program makes t h e i p a t c h a t t h e eiract "sphere of inflixence," n o t a t t h e u s u a l approximate "spEiere crf i n ~ l u e h c e . " A t p r e s e n t , t h e program has o n l y one s e t of bobndary+cbndittons which i t can S a t i s f y . This s e t i s a s p e c i f i c a t i o n of to and Ro p l u s tf and t h e a s s o c i a t e d s e l e n o c e n t r i c p o s i t i o n v e c t o r . A d d i t i o n a l boundary c o n d i t i d n s f o t more g e n e r a l erid condit f o h s a r e b e i n g added. Making use of t h e f a c t t h a t , i n t h e absence of atmosphere t h e right-hand s i d e s (RHS) of t h e COV d i f f e r e n t i a l e q u a t i o n s a r e independent of f i r s t d e r i v a t i v e s , s p e c i a l i z e d r o u r t h - o r d e r Runge-Kutta formulas r e q u i r i n g o n l y t h r e e e v a l u a t i o n s of t h e RHS can be used. The R i t h a r d s o n e x t r a p o l a t i o n t h e n becomes a t t r a c t i v e a s a s t e p - s i z e c o n t r o l . TH&e f e a t u r e 8 haQe been used i n Peprogrdmming t h e three-dimensional COV deek t o o b t a i n a f a s t - r u h n i n g d&ck f o r t h e SDS-930 u s i n g a t r l r i a b l e s t e p 31te. Td i l l t i s t r a t e t h e efEectiveries8 ijf t h e repr6gratrmiing, 7000 second �coast-burn-coast-burn t r a n s f e r s between two e l l i p t i c o r b i t s can b e accomplished i n l e s s than 3 seconds of computer time f o r 6 - d i g i t accuracy. The burn phases which l a s t l e s s than 300 seconds a r e i n t e g r a t e d i n one s t e p , a n d t h e c o a s t phases a r e i n t e g r a t e d i n 1000-second time s t e p s . This new program makes more p r a c t i c a l t h e s o l u t i o n of l e n g t h y t r a j e c t o r y problems s u c h a s t r a n s f e r s between e l l i p t i c o r b i t s and t r a n s f e r s between t h e e a r t h and moon on machines l i k e t h e SDS-930, which a r e s m a l l and slow compared t o c u r r e n t t h i r d g e n e r a t i o n computers. VII. DYNAMICS AND FLIGHT MECHANICS DIVISION A. Saturn V 1. Guidance a. T a r g e t i n g f o r S-IVB P r o p e l l a n t D e f i c i e n c y (New) I f f o r some contingency, t h e S-IVB a r r i v e s a t r e i g n i t i o n i n t h e e a r t h parking o r b i t w i t h i n s u f f i c i e n t f u e l t o complete t h e nominal t r a n s l u n a r i n j e c t i o n , t h e nominal m i s s i o n o r an a l t e r n a t e l u n a r m i s s i o n can be accomplished by u s e of t h e s p a c e c r a f t p r o p u l s i o n system (SPS). The type of a l t e r n a t e l u n a r m i s s i o n depends upon t h e SPS AV requirement. The AV r e q u i r e d i s n o t o n l y a f u n c t i o n of t h e p r o p e l l a n t d e f i c i e n c y of t h e S-IVB s t a g e , b u t a l s o a f u n c t i o n of how e f f i c i e n t t h e a v a i l a b l e S-IVB p r o p e l l a n t s a r e used. This c o n d i t i o n i s t h e primary r e a s o n t h a t MSC wants " t a r g e t update." Two s t u d i e s have been made t o determine how t o make t h e most e f f i c i e n t u s e of t h e a v a i l a b l e p r o p e l l a n t s . The Boeing Company d i d a s t u d y (SSR-230, "Real Time T a r g e t Update") where t h e traj e c t o r y was completely optimized based on t h e a v a i l a b l e p r o p e l l a n t s . The in-house s t u d y (R-AERO-DGA-13-68, "Target v e c t o r s y n c h r o n i z a t i o n f o r t h e l u n a r l a n d i n g m i s s i o n due t o S-IVB p r o p e l l a n t d e f i c i e n c y " ) was made t o move t h e t a r g e t v e c t o r i n o r d e r t o o b t a i n from a d i f f e r e n t approach: a more optimum burn. The two s t u d i e s gave e s s e n t i a l l y t h e same r e s u l t s . Both s t u d i e s showed t h a t t h e amount o f SPS f u e l r e q u i r e d t o complete some type of l u n a r m i s s i o n can be s i g n i f i c a n t l y reduced (30 p e r c e n t ) . The t a r g e t v e c t o r s y n c h r o n i z a t i o n approach can be accomplished w i t h i n LVDC. The e q u a t i o n s a r e simple and a r e t r i g g e r e d by B , p r o p e l l a n t d e f i c i e n c y , which can b e c a l c u l a t e d f a i r l y a c c u r a t e l y onboard. A s t u d y i s now underway t o determine t h e i n f l u e n c e of m i s s predicting the D. ( ~ ~ A / ~ o e i n g ) . �b. S t a t u s of Recommended Guidance Changes (New) R-AERO-DGA-12-68, " s a t u r n V Continuous Guidance U n t i l 3-11: C u t o f f , " November 6 , 1968, recomended c o n t i n u i n g guidance u n t i l S - I 1 c u t o f f e f f e c t i v e w i t h AS-404. T ~ F Sd i d n o t g e t i n t o t h e f l i g h t R-ASTR d i d i n c l u d e t h i s recommendation i n a program f o r AS-504. memorandum t o Mr. Duerr, I - V - I U , s p e l l i n g o u t i n f o r m a t i o n f o r use i n e s t a b l i s h i n g t h e LVDC f l i g h t program f o r t h e AS-505 mission. The recumnlendation t o r e d e f i n e t h e p r e d i c t e d burn time i n t h e S - I 1 s t a g e f o r t h e guidance e q u a t i o n s w i l l n o t be implemented However, b e f o r e AS-504. R-ASTR has s t a t e d t h a t t h i s w i l l be i n AS-506. no docunientation has been r e c e i v e d . (DOA) 2. ~ynaimiss and Control a. S-XI S t a g e POGO (New) O s c i l l a t i o n s i d e n t i f i e d on t h e AS-503 f l i g h t j u s t b e f o r e S-11 c u t o f f have n o t been i d e n t i f i e d as POGO. The 18 Hz l o n g i t u d i n a l mode amplitude w a s a p p a r e n t l y h i g h e r than u s u a l due t~ abnormal engine operat i o n , The v e h i c l e responge was v e r y complex w i t h l a r g e subharmonic c o n t e n t i n d i c a t i n g s i g n i f i c a n t n b n l i n e a r i t i e b . A l l paratneter changes between AS-504 and AS-503 which could make t h i s v i b r a t i o n worse w i l l be i n v e s t i g a t e d . (DDS b. Pl&tform Backup Using S p a c e c r a f t A t t i t u d e Reference (New) Because of t h e h i g h c r i t i c a l i t y a s s o c i a t e d w i t h a f a i l u r e of t h e S a t u r n V ST-124M p l a t f o r m , a backup a t t i t u d e r e f e r e n c e f o r v e h i c l e c o n t r o l is b e i n g considered t o enhanice crew s a f e t y . Prel i m i n a r y s t u d i e s have i n d i c a t e d f e a s i b i l i t y , and follow-on s t u d i e s a r e b e i n g planned, A p r e l i m i n a r y scope f o r t h e s t u d i e s and p r e l i m i n a r y he a r e a s needing ground r u l e s f o r implementation have been d i s c u s s e d . more d e t a i l e d s t u d i e s and i n f o r m a t i o n concerning t h e s p a c e c r a f t systems needed from MSC t o perform t h e s e s t u d i e s have been i d e n t i f i e d , E a r l i e s t (~C/~~/Astrionics) e f f e c t i v i t y f o r t h i s backup i s now s e t f o r AS-506. 3. P r o j e c t I n f o r m a t i o n A p p l i c a b l e t o Many Vehicles S a t u r n y.. Rigid, Body Respons-e Anal ys is (New) : The r i g i d body response t o winds of t h e S a t u r n V launch v e h i c l e i n f l i g h t condiindividual t i o i s near c e n t e r engine c u t o f f i s betng examined c l o s e l y . per t u r b a t i o n c a s e s a r e being i n v e s t i g a t e d t o determine t h e RSS condit i o n s f o r t h i s maximum l o f l g i t u d i n a l a c c e l e r a t i o n case. The s t r u c t u r a l s a f e t y margin i n t h i s f l i g h t r e g i o n i s r a t h e r s e n s i t i v e t o a s l i g h t �b u i l d u p i n bending moment due t o c o n t r o l d e f l e c t i o n a n g l e s brought a b o u t by d i s t u r b a n c e o r misalignment. (DC) 4. P r o j e c t Information A p p l i c a b l e t o I n d i v i d u a l Vehicles a. AS-504 S t a b i l i t y Analyses (New) Recent i n v e s t i g a t i o n of t h e s t a b i l i t y of t h e AS-504 v e h i c l e has r e v e a l e d t h a t coupling between t h e bending and s l o s h i n g modes of t h e v e h i c l e has a s i g n i f i c a n t e f f e c t upon r e l a t i v e s t a b i l i t y . Some p r e v i o u s work on e a r l y c o n t r o l c o n f i g u r a t i o n s and v e h i c l e d a t a had l e d t o t h e c o n c l u s i o n t h a t , even w i t h t h e r e d u c t i o n i n s t a b i l i t y margins due t o i n c l u d i n g t h e coupling e f f e c t s i n t h e a n a l y s i s , v e r y adequate margins were s t i l l m a i n t a i n e d , and t h e r e f o r e t h e i n c r e a s e d complexity of t h e coupling s i m u l a t i o n could be dispensed w i t h t o reduce t h e volume of d a t a t o be handled. A f t e r many i t e r a t i o n s , however, t h e adequate margins have d i s a p p e a r e d , and t h e now s i g n i f i c a n t e f f e c t s of coupling must be included i n t h e s i m u l a t i o n s . With t h e i n c l u s i o n of s l o s h / b e n d i n g c o u p l i n g , the s l o s h modes of t h e AS-504 couple t o produce a s l i g h t l y u n s t a b l e s l o s h mode f o r t h e damping p r e d i c t e d f o r a n 0.05-meter s l o s h wave h e i g h t u s i n g nominal v e h i c l e parameter v a l u e s (AS-503 shows t h e same ind i c a t i a n s w i t h s i m i l a r a n a l y s e s ) . Allowance f o r parameter v a r i a n c e s produces a n u n d e s i r a b l y l a r g e i n s t a b i l i t y f o r t h e f ixed-time, 1i n e a r a n a l y s i s used. However, s l o s h damping i n c r e a s e s as wave h e i g h t i n c r e a s e s , and a l i m i t c y c l e w i l l be reached i n t h e s t e a d y s t a t e i f t h e degree of i n s t a b i l i t y i s n o t t o o g r e a t . Response s t u d i e s f o r one - ( r a t h e r a r b i t r a r y ) method of r e p r e s e n t i n g t h e 30 parameter v a r i a t i o n s , u s i n g measured Jimsphere winds t o f o r c e t h e s y s tem, have shown t h a t t h e i n c r e a s e i n damping due t o t h e i n c r e a s e d wave h e i g h t is s u f f i c i e n t t o (~~/Astrionics/ p r e v e n t dangerous b u i l d u p s of s l o s h i n g p r o p e l l a n t s . Boe ing) b. AS-504 Third S t a g e Bending A n a l y s i s (Ref. F e b r u a r y l ~ a r c h1968, p. 38) A v i b r a t i o n a n a l y s i s has been made of t h e t h i r d f l i g h t s t a g e S a t u r n V/AS-504 ( w i t h LES a t t a c h e d ) . This c o n f i g u r a t i o n would occur i f c e r t a i n m a l f u n c t i o n s e x i s t e d i n e a r l i e r s t a g e s . Consequently, t h e dynamic c h a r a c t e r i s t i c s a r e n e c e s s a r y f o r c o n t r o l system v e r i f i c a t i o n . The r e s u l t s of t h i s a n a l y s i s a r e being p u b l i s h e d . (DDS) c. Dynamic Data f o r AS-504 M i s s i o n D, S-IVB S t a g e h A f t e r Payload S e p a r a t i o n (Ref. ~ e b r u a r y l ~ a r c1968, P* 38) Bending and t o r s i o n d a t a f o r AS-504 Mission D, S-IVB s t a g e a f t e r payload s e p a r a t i o n , have been p u b l i s h e d i n memorandum ~ - A E ~ 0 - ~ ~ - 1 4 8 - 6 Included 8. w i t h t h e d a t a a r e t h e t o l e r a n c e s and damping t o be used f o r c o n t r o l system v e r i f i c a t i o n . (DDS) �B. S a t u r n Apollo A p p l i c a t i o n s Program 1, Cluster a. Missiorl P r o f i l e (1) AAP Experiments Data Bank (Ref. ~ c t o b e r / ~ o v e m b e r 1968, p. 42) The AAP experiments d a t a bank has been r e v i s e d t o i n c o r p o r a t e v a r i o b s s u g g e s t i o n s and camtrierits t o make i t more meaningful. The r e v i s i o t l is now b e i n g e v a l u a t e d by R-AERO-DAM. This e v a l u a t i o n w i l l be forwarded t o ~ a r t i n / M a r i e t t aC o r p o r a t i o n f o r implementatibn s o t h a t t h e f i n a l v e r s i o n w i l l be a c c u r a t e and up t o d a t e . This v e r s i o n w i l l have wide d i s t r i b u t i o n and w i l l represent t h e l a s t i t e r a t i o n and docu(DAM/Martin) m e n t a t i o n of t h e d a t a bank. (2) nes i&n Reference Miss i o n Document (DRMD) AAP-l/AAP-2 (Ref. April/May 1968, p. 42) Change 1 t o r e v i s i o n B of t h e DIWD was made t o add t h e a n a l y s i s of t h e A i r l o c k Module ~ i e c t r i c a lPower System Consuma b l e s and t o r e v i d e f u e l c e l l cryogenic requirements. Copies w i l l be s e h t t o a l l who r e c e i v e d t h e o r i e i n a l i s s u e . (~A~fMartFn) (3) Exper imant C o n i p a t i b i l i t y (Ref. October/November 1968, p , 43) . The r e s u l t $ of t h e experiment/mission c o m p a t i b i l i t y a a a l y s i s were p r e s e n t e d t o t h e Manned Spaee F l i g h t Experiment Board (MSFEB). The MSFEB, a c t i n g upan r e e a m e n $ % t f o n s made i n the s t u d y , chose one of t h e o p t i o n s t o be included i n t h e new Mission D i r e c t i v e 3D; t h e o p t i o n chosen d e f i n e d a new b a s e l i n e of experiments f o r t h e m i s s i o n AAP-1/AAP- 2 and AAP-3A. (hAM) (4) Missfon AAP-3/AAP-4 Timeline Analysis (New) The l a g i c f o r a new a u t o m a t i c experiment s c h e d u l e r w a s developed f o r the ATM-type m f s s i o n . This prbgram w i l l i r i t e r r o g a t e an e v e n t i n p u t , such a s s o l a r f l a r e s , and w i l l s c h e d u l e t h e experiment. A l ~ h o u g ht h e program has been developed p r i m a r i l y f o r t h e ATM package, i t can a l s o be used i n connection w i t h any event--oriented program ( i . e . , e a r t h resources). The program 2s being developed by M a r t i n / ~ a r i e t t a C o r p o r a t i o n (MMC), Denver, i n s u p p o r t of t h e i n t e g r a t i o n c o n t r a c t . (Drn/rnC ) �(5) The Markov Chain S a t u r n V Apollo Mission Success P r o b a b i l i t y Model (New) The s k e l e t o n computer program c o n t a i n i n g t h e b a s i c i n g r e d i e n t s of t h e f i n a l program has been completely checked o u t . The countdown model has been coded, and t h e r e s u l t i n g computer program is b e i n g checked o u t . The i n p u t scheme i n t r o d u c e s f a i l u r e r a t e d a t a f o r each subsys tem v i a c a r d s o r tape. These f a i l u r e r a t e d a t a and a n a r b i t r a r y time i n t e r v a l a r e then used t o compute t h e countdown t r a n s i t i o n p r o b a b i l i t i e s , which a r e t h e n s t o r e d on t a p e f o r l a t e r use. Tape updating s u b r o u t i n e s a r e being p r o g r a m e d . The s t u d y i s expected t o be complete i n about a month ( c o n t r a c t t e r m i n a t e s March 10, 1969). (DAM/ ~ o c k h e e d) (6) AAP Hardware U t i l i z a t i o n (Ref. OctoberlNovember 1968, p. 4 3 ) The o v e r a l l flow showing hardware u t i l i z a t i o n i n t h e Apollo A p p l i c a t i o n s Program f o r contingency and backup m i s s i o n planning has been completed. The o b j e c t i v e of t h i s m i c r o l o g i c i s t o determine t h e p r o b a b i l i t y of s u c c e s s of 2 b a s e l i n e AAP m i s s i o n a s a f u n c t i o n of t h e hardware a v a i l a b l e . The more d e t a i l e d m i c r o l o g i c which i n t e g r a t e s t h e hardware s u c c e s s and f a i l u r e s i n t o t h e program is n e a r completion. Pro(DAM) g r a m i n g of t h e problem f o r t h e IBM 1108 has begun. (7) Lockheed FORRCAST Computer Program (New) The f i r s t t h r e e f i l e s of t h e FORRCAST Computer Program a r e now o p e r a t i n g on t h e IBM 1108. These f i l e s c o n s i s t of (1) t h e ephemeris g e n e r a t o r , (2) t h e t i m e l i n e of t a r g e t l s t a t i o n t a b l e s g e n e r a t o r , and (3) t h e a s t r o n a u t s c h e d u l e r program. A f a m i l y of check a s t r o n a u t t i m e l i n e c a s e s a r e b e i n g r u n u s i n g b a s e l i n e experiment d a t a from t h e AAP 1 / 2 mission. A simple check c a s e has been r u n s u c c e s s f u l l y , and t h e (DAM/ s c h e d u l e s should now be a b l e t o handle p r e s e n t t i m e l i n e problems. Lockheed) (8) AAP-2 Launch Vehicle Performance A n a l y s i s (New) The launch v e h i c l e performance a n a l y s i s f o r AAP-2 ( O r b i t a l Workshop) has been completed and d i s t r i b u t e d i n R-AERO-DAP-1-69. Maximum l o n g i t u d i n a l a c c e l e r a t i o n , dynamic p r e s s u r e (with and w i t h o u t w i n d s ) , and aerodynamic h e a t i n g i n d i c a t o r d e s i g n t r a j e c t o r i e s a l o n g w i t h t h e f l i g h t performance r e s e r v e s were determined. F l i g h t performance r e s e r v e s a r e computed f o r b o t h open- and closed-loop PU o p e r a t i o n . The launch v e h i c l e i n s e r t s i n t o a 185 x 193 n a u t i c a l m i l e a l t i t u d e o r b i t w i t h S t u d i e s a r e being i n i t i a t e d f o r t h e manned AAP a n i n c l i n a t i o n of 35'. launches t o d e f i n e d e s i g n c r i t e r i a and FPR requirements. (~AP/~hrysler) �(9) AAP-1, 2 , 3A, 3 apd 4 F l i g h t P r o f i l e and Launch Window Analysis (Ref. October/November 1968, P . 41) The AAP c i u s t e r q & s i o n p r e l i n l i q a r y f l i g h t p r o f i l e and launch window a n a l ys is i s c o n t i n u i n g The OWS o r b i t a l i n c l i q a t i o n has p r e v i p u s l y been d e f i n e d t o s a t i s f y t h e AAP-1 and 2 optimum launch requirements. The AAP-3A @-phase lqunch o p p o r t u n i t y f o r t h e nominal rendezvous p r o f t l e o c c u r r i q g a p p r o x b a t e l y 9Q days a f t e r t h e U P - 1 launch and r e q u i r i n g t h e s m a l l e s t amouqt QE nodg change occurs a t 22:51 GMT on day 94. This launch o p p o r t ~ n i t yoccurs approximately 9 minutes b e f o r e t h e optipum launch t i p e and causes q paylbad l o s s of approximately l O O Q pounds f o r AAP-?A. The e f f e c t s f adding a c i r c u l a r i z a t i o n paneyver a t gpogee of t h e i n s e r p i p n qrblf ($1 x $20 NM) of t h e nominal repdezvqus p r o f i l e and c o a s t l p ~i n t h i p qrbgt i s being i n v e s t i g a t e d . By c o a s t i n g i n t h i s o r k i p , the pn-phaqa l a q p ~ h~ p p o r f u n i t yw i l l pccur n e a r e r t h e optimum launch o p p p ~ P v n i t y , tbua g a i q i o g U P - 3 A payloqd, b u t r e q u i r i n g (F)A0/~A~/Nprfhr~p) more rendezvous twe. . (1Qf Mechanizat$an of t h e C l u s t e r pliasion P r o f i l e and "bapnch Window Anqlysis (Ref. Ocrober/ Vavember 1968, p. 41-42] The l o g i e Flpw prgv$gusly developed £or t h e d r i v e r o r e x e c u t i v e proFram n e c e s s a r y goy Eh$q mechanj.aation bas been p r o g r a m e d . The purpose of t h e d r i v e r i s $a tfgnqfga: data between t h e O r b i t a l Bredict i o n , QgSck Look, and ROBOT @FQ$FWS. T h i ~daga t r a g a f e r is now being performed by hand. The development of t h e d r i v e r has made i g n e c e s s a r y t o develqp c o w o n b l o c k s f o r each program and Che d r i v e r i n o r d e r t o make t h e d a r a t r a n s f e r bqtween prQgFams p o s s i b l e . Also, n a m e - l i s t i n p u t c a p a b i l i t y has been added t o t h e p r b g r w s t o f a c i l i p a t e t h e d a t a t r a n s f e r Cgpputey rpns a r e being made t o check phis o u t . between prOgraRS. (DAQLNO~ throp) (11) LM Repdozvous A t t i t u d e P r o f i l e (New) Work is underway t o determine t h e a t t i t u d e of t h e This i n p u t is t o be used as Jnput ts a thermal a n a l y s i s of t h e LM d u r i n g rendezvous. I n t h i s a n g l y s j s , two d i f f e r e n t methods of readezvous a r e being considered (Hybrid S t a b l e O r b i t and M = 3), and t h e maximum d e v i a t i o n s from t h e nominal w i l l b e analyzed i n each case t o provide l i m i t s on t h e sun (DAO) angle, Di w i t h r e p p e c t t o t h e s u n d u r i n g rendeavpus. �(12) SO27 (New) An a n a l y s i s has been made t o f i n d t h e s e p a r a t i o n between t h e LM and S-IVB as a f u n c t i o n of time a f t e r p r o p u l s i v e dumping from t h e s p e n t S-IVB. The impulse from t h e dump w a s g i v e n i n b o t h t h e p o s i g r a d e and r e t r o g r a d e d i r e c t i o n s , and t h e growth of t h e s e p a r a t i o n a s a f u n c t i o n of time i s symmetrical i n t h e two c a s e s e x c e p t i n one case t h e S-IVB l a g s t h e LM (posigrade impulse) and i n the o t h e r c a s e t h e S-IVB l e a d s t h e LM. For nominal performance of t h e launch v e h i c l e t o o r b i t , enough p r o p e l l a n t is l e f t i n t h e S-IVB t o g i v e a n impulse of 19.4 m / s . For a -30 performance of t h e launch v e h i c l e , a n impulse of 12 m/s is o b t a i n e d and f o r a +3a performance of t h e launch v e h i c l e , an impulse of 26 m / s i s o b t a i n e d . The growth i n s e p a r a t i o n as a f u n c t i o n of time r a n g e s from approximately 113 minute p e r o r b i t f o r -30 performance t o approximately 1 minute p e r o r b i t f o r +30 performance. The times j u s t mentioned a r e t h e approximate d i f f e r e n c e s i n time when t h e two o b j e c t s pass a g i v e n p o i n t (say, a t r a c k i n g s t a t i o n ) . (DAO) (13) S o l a r Observation Times and Out-of-Plane Angles (New) To supplement t h e AAP f l i g h t p r o f i l e and launch window a n a l y s e s , d a t a have been g e n e r a t e d f o r a n o r b i t a l i n c l i n a t i o n of 35O, y i e l d i n g s e t s of curves such t h a t : Given any launch d a t e and launch time, d u r i n g t h e y e a r 1972, one may determine t h e p e r c e n t a g e of time a v e h i c l e spends i n t h e s u n l i g h t f o r any day d u r i n g t h e m i s s i o n and t h e out-of-plane a n g l e , @ (which is d e f i n e d a s t h e a n g l e between t h e o r b i t a l plane and t h e s o l a r v e c t o r ) , f o r any day d u r i n g t h e mission. Given any launch d a t e i n 1972, one may determine t h e t o t a l time s p e n t i n t h e s u n l i g h t f o r a 56-day m i s s i o n (minimum and maximum) corresponding t o two launch times d u r i n g t h e day. A memorandum d i s p l a y i n g t h e s e curves is now being prepared. The program used f o r g e n e r a t i n g t h e s e curves c o n t a i n s a subr o u t i n e which can c a l c u l a t e t h e r i g h t a s c e n s i o n and d e c l i n a t i o n of t h e sun f o r a g i v e n J u l i a n d a t e . (DAO) b. Guidance (1) S-IVB/CSM Guidance C o m p a t i b i l i t y Study (New) The e q u a t i o n s and computer programs d e s c r i b i n g Hohmann/cross-product s t e e r i n g guidance used i n our s t u d y of t h e S-IVB/ CSM guidance c o m p a t i b i l i t y s t u d y f o r AAP-3 have been documented. The memorandum has been g i v e n t o t h e C h r y s l e r Corporation Space D i v i s i o n f o r (DGA) u s e i n AAP s t u d i e s u n t i l more i n f o r m a t i o n is r e c e i v e d from MSC. �(2) A d d i t i o n t o and V a r i a t i o n of t h e Lambert Problbm (New) Th& ~titnlj6rtptoblem d e a l s w i t h d e f i n i n g a Conic betweefi h a p d g i f i o n v e c t d f d wh&n: kh& time i s s p e c i f i e d . Th& &s$hmptions a r e t h e ihvCrS'e squake law1 3rd thd<t i h e a f a r r i v a l is t h e " f i r s t time" of a r r i v a l . w i t h t h i s a s e d i p t i o n , t h e cbnid i s unique. HoweverI i f t h e d t h i t i h e bf i r f i v a l oh t h e dgeond (or time of a r r i v g l i g ~ @ & e i f i gas more) pass ( m h l b i d f b l t ) , LHen tH@ cBiiFc id hrit lihique an*al.$. I n thbst c a s e s , t h e r e afk kw6 6 o l i t t F ~ n s . A komputer progrim, which It$$ beeh developed t o deEtirni%ric ill1 d b l c l t i b n ~iS ~ eixpeeted t o b e used i n sonie AAP s t u d i e s ; The kh&bert pPobl&ih nkgledkb thk o b l d t e n e s s e f f b c t of t h e edetH and bklie? ~ e k t b f b i h g&!Ef$cfs. W h ~ p u k e rpro@lil& has beeti d e i e l o p e d t o p r c d F t t t h e dbi&t6fi$!4b @ff&ck# by h i n & ~i.ick8'itikthbd of r & c t i f i c i r t i c j l i . 'I%$@ tkehtlique i b b e i h g ii!3kd With thk ~ a n i b & %~boblem t i n Idiite &I? g t c i d i ~ ~ :~ h $ d$pt-~j;&khcgh bi! dsed i n kibsk f k @ t i - f l i g k t . t r a j e c t d r y ehl&til&fi 6 i i g ; (B@A!#bkthro#) 1 ~38 kuidaake d a v i g h t i b n Hdrdw&i-e f3) ~ p - 3, ~ d n p itt i5 it i ty Akalgs is (New) The s o f t w a f e (kqddtiorid) c m p c i t i b k l ~ t j fbf t h e CSM c r o s s - p r o d u c t s te@?irig w i t H f@l B teekitig hi39 d l r e a d y be&i ei3 t g b l i s h e d , b u t t h e p l a t f o r m a i i g f h e n t etFdEB of thk e$h '&fU p l & r e s a reijuireniknt on t h e d21m s t a g @ kb eiigbrc$ tH(3 &!liked ~ ~ ~ ~pldne i k dl tl d - f a dtbge dubd r b i k a l ctitdff. THk fMU tHd.3 k6HPiikE8 &he i h s t a i i k 6 W b ~ #plhne and st@k?B i n t h i d p l a n e t o a c h i e v e o r b i t P 1 i n i e r t i ~ i i , To e s t a b l i s h t h e accuracy of the riatripational S t a t e a t s ' I ~ ~ B c u t o f f , h diiai n a v i g a t i o i i system s i m t i i a t i d n is r e q u i r e d w i t h t W i h U i h i3 mmdnit6r mode d u r i n g 3-IB dnd t d t h e l'bll.7 a t c ~ H ignition s - ~ ~ T I S s t a g e b o o s t efivlronmeht: R &v?lEcB~V&r and subsequent cohput&tion bf t h e reniaining t r a j e c t o r y t o o t b f t a l ih3ertibfi Q r e r 6 q h i r e d i n dkdei- t o e v a l h d t e t h e a c c u r a t y 6f t h e i n s e r tibn orbit. (~GG/Na?throp) c. Dyhamids dhd Codtrol (1) Mcknefikurn M&nagSiiIektt ( R k f . ~ c t o b e r / ~ o v e t h b e1968, r p. 44245) ~ t u d i ' l 3 sa r e continuing on t h e l i n e a r giffibal arid rrds3-feedback laws, which a r e dekigned t o e l i m i n a t e t h e problems of a n t i - 2 j a r a l l e l i s m and h i t t i n g ginibal stop^. LOSS o f c o n t r o l may i - e s u l t i n e i t h e r ease. The advankage O£ tii&Se laws over t h e ones c u r r e n t l y i n use id t h e i r s i i h ' p l i e i t y w i t h no h&@tni"ri$ d6gkddation i n o v e r a l l sydtem reswhse. �Comparison r e s u l t s obtained thus f a r have been w i t h o u t bending f i l t e r s i n t h e forward loop. Bending f i l t e r s a r e b e i n g included and cross-checks w i t h A s t r i o n i c s Laboratory w i l l be made. (DDD/Northrop) (2) S t r u c t u r a l Damping P r e d i c t i o n s (Ref. October/ November 1968, p. 48) The m a t e r i a l damping program has been checked o u t . The i n p u t d a t a f o r computing t h e m a t e r i a l damping of the s o l a r p a n e l s f o r the ATM were g e n e r a t e d u s i n g t h e frame s t r u c t u r a l a n a l y s i s program. Design of t h e j o i n t t e s t f i x t u r e s was completed. (DDS/~ockheed) F a b r i c a t i o n of t e s t f i x t u r e s is a b o u t 40 p e r c e n t complete. (3) Impulse Requirements (New) The impulse r e q u i r e d t o hold t h e c l u s t e r w i t h t h e ATM docked t o P o r t I is being determined. The c u r r e n t t h i n k i n g i s t o s p i n up t h e CMG's w i t h t h e c l u s t e r i n a s o l a r i n e r t i a l hold as opposed t o X-POP. Since t h e a n g l e between t h e sun l i n e and t h e o r b i t a l p l a n e i s not known, t h e impulse r e q u i r e d f o r CMG spin-up must be o b t a i n e d f o r a range of @ a n g l e s from 0 t o 60 d e g r e e s . (DDD) d. P r o j e c t Information Applicable t o I n d i v i d u a l Vehicles (1) U P - 2 Response Analyses (October/November 1968, P* 46) The AAP-2 launch v e h i c l e f i r s t f l i g h t s t a g e is b e i n g i n v e s t i g a t e d i n terms of v e h i c l e responses t o measured wind p r o f i l e s on t h e h i g h speed analog computer. Gain changes i n c o n j u n c t i o n w i t h a l r e a d y e s t a b 1 i s h e d c o n t r o l networks w i l l be i n v e s t i g a t e d i n a n a t t e m p t t o p r e v e n t c o n t r o l l a b i l i t y problems i n t h e maximum dynamic p r e s s u r e r e g i o n of f l i g h t . Rigid body responses t o a 50 p e r c e n t i l e wind p r o f i l e a r e being checked a g a i n s t those obtained from a d i g i t a l s i m u l a t i o n . The c o m p i l a t i o n of f l e x i b l e body d a t a f o r u s e i n t h e a n a l y s i s i s a l s o i n progress. (DC) (2) AAP-2 Shroud J e t t i s o n (Augus t/September , p . 43) S i n c e t h e l a s t s t u d y of t h e AAP-2 shroud j e t t i s o n (published i n R-AERO-10-68, October 9, 1968), more r e c e n t i n f o r m a t i o n has r e v e a l e d t h a t t h e r e w i l l be an u m b i l i c a l d i s c o n n e c t f o r c e of approxim a t e l y 500 pounds a c t i n g a t t h e mouldline near v e h i c l e p o s i t i o n 11. This has n o t been considered i n any of t h e previous s t u d i e s . The e f f e c t of t h i s d i s c o n n e c t f o r c e on t h e s h r o u d - j e t t i s o n o p e r a t i o n i s b e i n g s t u d i e d . A preload d e v i c e t o a l l e v i a t e t h i s . f o r c e w i l l be considered i f t h e pre(DC) s e n t s t u d y i n d i c a t e d i t s need. �(3) AAP-4 LPIIATM S e p a r a t i o n From Launch Vehicle (New) E j e c p i a n Q£ t h e LM/A@ from t h e 3-IVB s t a g e w i t h t h e A p s l l o s p r i n g s y s tam i e beiqg s t u d i e d f o r adequacy. This a e p a c a t i ~ n s i m u l a t i o n i n v o l v p s ti imu@pion pf e i e c t r i c a l and pneumatic y m b i l t c a l d i s connectq which r e s i s t s e p g f q t i a n w i t h a t o t a l f o r c e a s l a r g e a6 r h a t of one of t h e f o u r maip s e p a r a t i o n ' ap$ings. 4 preload d e v i c e t o c o u n t e r a c t t h e u m b i l i c a l d$sconnect fgjrce i p being designed. Tbis s t u d y is t o e s t a b l i s h d e s i g n c r i t e r i a f o r t h e p y e l ~ a dd e v i ~ eand t o v e r i $ y t h e f e a s i b i l i t y o f A q e j e c t i o nw i t h t h e ~ h b l l as p r i n g system. (DC) 2. OWS 3-XKB Workshop 4lnsFFnp ppring Powered P l i g h t (&pf. Auguntbf3eptember '19682 p. 45) a. The a x p e r i w n f $ l $nve%t$g&fionof $he podel8 of t h e f o o d , waste management, aqd wsrk areas i s ppw complete. Tho d a t a f o r t h e work a r e a cornpagefneet heve been reduged, apd peqhapicgtl model has ~ b i si q t h e lgpges t and' b a s t i g t r i c a ~ e l yqhaped t a n k been i d e n t i f i e d compartment. Three @lash frequppcies f q i z l y c l o s e t o g e t h e r have been i d e n t i f i e d , and these poded g r e a e n s i t i y e FD t h e d l r e c t i o g q f e x c i t a t i o ~ . The mechanical model f o r t h i s p g g t i o n of the tank is comgqoed of t h r e e spring-mass-damper eyg terns an4 pwo r$g+d Isasses. The over311 s l o s h model f a r t h e e n t i r e p a r t i t i a n @ @g e p F h p @ likely t o be q q i t e ' complgx. ( ~ ~ 8 / 6 0 u t h w-te sResearch In@ t l g y g p ) . b. Wo~kfhopC o n t r o l S i m u l a t i o p (New) A ~ c u d yhqs hepp ~ ~ n d q s ~ pu sgi nl g~ a d i g i t a l Gomputer program, t o s i m u l a t e t h e S-IVB c o f l t r o l s y s k s ~ ,t h e aeradynag$.c t b r q u e s a c t i n g an t h e v e h i c l e , and thg d e n s i t y p r b f i l e , The r e s u l t s pf phis s t u d y , npmely, t h e hapulse r e q u i r e d f a r c o n t r o l and i-qaneuvgre, have been compared w i t h t h e 5(92/S-IV'@ f l i g h t d a t a , A memorandum g i v i n g t h e s e r e s u l t s w i l l be p u b l i s h e d gpoa. (DDD) c. vass Parameter S e n s i t i v L t y- (Ref. , Qctober/Noyember 1968, P. 4 6 ) The WACS impulse was found t o be v e r y s e n s i t i v e t o m o p n t s of i n e r t i a , I2 and 13. v a r i a t i o n s i n t h e two l a r g e s t The d i s t u r b a n c e t o r q u e is' a Sunctign af s e v e r a l q u a n t i t i e s , one ef which is ,the d i f f e r e n c e between these promenf;s of i n e r t i a (I2 Ig), A 15 p e r c e n t i n o r e a s e i n (I2 T3$ c a u s e s a la $crease i n t h e r e q u t r e d impulse p e r orbst. The increase qf 15 p e r e g n t can be r e a l i z e d i f t h e l 8 r g e r of the z@owqts is iincyeered by 112 percenp, These comments have been r e g a r t e d 6n plernorc~nx9umR-&E~~o-DQ-1434.3 , "Cs f - t i c a l I n e r tfa Proper t i e s - - �During AAP C l u s t e r Mission," November 27, 1968. A more d e t a i l e d a n a l y s i s i s i n p r o g r e s s and t h e r e s u l t s w i l l be r e p o r t e d l a t e r . (DDD) d. A c t i v e Control (Reference ~ c t o b e r / ~ o v e m b e1968, r p. 45) Checkout of a program t o e v a l u a t e OWS/ATMmomentum dumping schemes u s i n g g r a v i t y g r a d i e n t torques i s n e a r i n g completion. Momentum management over more than 12 o r b i t s has been simulated s u c c e s s f u l l y . The a n g u l a r momentum of the CMG's which accumulates d u r i n g t h e l i g h t p o r t i o n of a n o r b i t i s reduced s u b s t a n t i a l l y d u r i n g t h e d a r k p o r t i o n of an o r b i t . Minor i n c o n s i s t e n c i e s i n t h e r e s u l t s a r e b e i n g c o r r e c t e d . A d e t a i l e d r e p o r t p r e s e n t i n g t h e t h e o r y of t h e b a s i c g r a v i t y g r a d i e n t momentum dumping method i s being published. The program t o e v a l u a t e v a r i o u s CMG momentum d i s t r i b u t i o n laws has been extended t o i n c l u d e t h e computation of power consumption and subsequent p l o t t i n g . A r e p o r t is being w r i t t e n on t h i s program. (DCA) a. Bending F i l t e r s (Ref. oct$~r/~ovemb& 1968, p. 44) A s e t of second o r d e r f i l t e r s has. been designed f o r t h e ATM based on a l i n e a r uncoupled s i m u l a t i o n . These f i l t e r s p r o v i d e f o r a 50 p e r c e n t v a r i a t i o n i n bending mode natuPa1 frequency and a 20 p e r c e n t v a r i a t i o n i n bending mode s l o p e , The r e s u l t s of t h i s s t u d y w i l l be published i n a memorandum. F u t u r e s t u d i e s w i l l i n c l u d e t h e e f f e c t s of (DDD) c r o s s - a x i s coupling and a l s o CMG backlash. b. P a s s i v e A t t i t u d e Control (Ref. October/November 1968, P a 45) A f e a s i b i l i t y s t u d y concerning t h e aerodynamic damping of an O r b i t a l Workshop type of s p a c e v e h i c l e u s i n g t h e s o l a r panels i s almost complete. A t o r s i o n a l s p r i n g and a v i s c o u s damper i n each of t h e s o l a r panel hinges r e s u l t i n e x c e l l e n t damping of t h e tumbling motion of t h e s p a c e c r a f t , a s i n d i c a t e d by a n a n a l y t i c a l o p t i m i z a t i o n s t u d y and by r e c e n t computer s i m u l a t i o n s . R o t a t i o n a l motion a b o u t a l l three-body axes i s s i m u l t a n e o u s l y damped by t h i s a t t r a c t i v e concept, which r e q u i r e s o n l y minor d e s i g n e f f o r t s and i s subs t a n t i a l l y l i g h t e r than o t h e r known concepts. A r e p o r t on t h e o p t i m i z a t i o n of c r i t i c a l d e s i g n parameters and s i m u l a t i o n r e s u l t s has been published. Minor m o d i f i c a t i o n s were made i n a computer program which i s e s p e c i a l l y e f f i c i e n t f o r s i m u l a t i n g t h e P a s s i v e Motion of O r b i t i n g S a t e l l i t e s (PAMOS) over long time p e r i o d s of 10 o r more o r b i t s . The m o d i f i c a t i o n s were aimed a t f u r t h e r reducing t h e computing time and a t maximum convenience i n t h e d a t a i n p u t s . �A b a s i c program f ~ t rh e s i m u l a t i o n of hinged s a t e l l i t e s is n e a r i n g completion. S i m p l i f i e d c a s e s have been r u n s u c c e s s f u l l y u s i n g b o t h Runge-Kutqa and Adams i n t e g r a t i o n packages. The i n p u t and o u t p u t r o u t i n e s have been modified and s e v e r a l o p t i o n s added t o (QCA) f a c i l i t a t e program use. c. AAP Uf/ATM Unmanned Rendezvous (Ref. ~ u n e / J u l y1968, p. 47, August/September 1968, p . 44, and October/ November 1968, p , 4 3 ) The f e a s t b i l i t y a n a l y s i s i s e s s e n t i a l l y completed s i n c e c a p a b i l i t y has been e s t a b 1 $shed Co perform 811 maneuvers r e q u i r e d of t h e S-IVB/LM-ATM t o rendeevqug w i t h t h e s r b i t a l gssembly. F u r t h e r s t u d y of t h e f o r m u l a t i o n of S g n i t i o n eguagCspq f q r q11 maneuver? i s r e q u i r e d b e f o r e the r e s u l g s $re docytpenterl. Navigation update of t h e B-IVI$, IU s t a t e u a r 4 a b l e s sitill p r e s e n t s a p r ~ b l e q ,s i n c e t h e r a d a r is mounted on t h e LM s t r u c t u r e and c o n s i d e r a b l e r a d a r a n g y l a r e r r o r s would e x i s t i f t h e s e d a t q were t r a n s f e r r e d acroBs t h e fMU (LM n a v i g a t i o n ) t o t h e IU (Saturn n a v i g a t i o n ) . It may be d e s i r a b l e t o t r a n s f e r t h e I U e s t i m a t e d s t a t e t o t h e INU and a l l o w t h e DfU t o update t h e s t a t e v a r i a b l e s i n t h e W computer and t h e n t r a n s f e r t-he updated n a v i g a t i o n a l s t a t e t o t h e I U s i n c e t h i s c a p a b i l i t y a l r e q d y e x i s t s i n t h e L,M IMU, (~~~/~orthrop) d. AAP &bf/ATM N a v i f a t i q n a l s t a t e a t O r b i t a l I n s e r t i o n (New) The working Level meeting w i t h Grumman emplayees e s t a b 1iohed c o n t a c t s f o r guidance and miss i o n a n a l y s i s . Grumman i d e n t i f i e d a need foy a LM-ATM n a v i g a t i o n a l s t a t e a t o r b i t a l i n s e r t i o n s o t h a t r a d a r a c q u i s i t i o n s t u d i e s cpuld be s t a r t e d . The LMtqTM n a v i g a t i o n a l accuracy w i l l be a s s e s s e d through t h e S - I 3 and 3-IVB b o o s t environment by s i m u l a t ing t h e IMU (M n a v i g a t i o n hardware) i n a monitor mode of o p e r a t i o n . The d u a l p l a t f o r m - a c c e l e r o m e t e r system a n a l y s i s computer program w i l l be used f o r t h i s s t u d y ? (DGG/Nor t h r o p ) C. General 1. Dynamic S t a b i l i t y of P r o p e l l a n t Tank Under Steady Load and Oscillating E x c i t a t i o n Force (New) A t h e o r e t i c a l a n a l y s i s has been conducted t o p r e d i c t t h e dynamic response of a s i m p l i f i e d model c o n s i s t i n g of a p a r t i a l l y l i q u i d f i l l e d c y l i n d e r w i t h a r i g i d f l a t bottom, a n i n t e r n a l u l l a g e p r e s s u r e , and a r i g i d mass on top. Wumerical, 3s w e l l a s e x p e r l m e n t a l , r e s u l t s have v e r i f i e d a s t r o n g coupling between t h e s h e l l , l i q u i d , and top mass. The r e s u l t s of t h i s s t u d y y i f l b e r e p o r t e d a t t h e A N S t r u c t u r a l Dynamics and A e r o e l a s t i c i t y Meeting i n A p r i l . @DS/Southwest Res. I n s t . ) �2. E v a l u a t i o n of Lumped S h e l l Analysis Methods (New) A two-task s t u d y has been conducted t o determine t h e a c c u r a c y of c e r t a i n lumped s h e l l a n a l y s i s methods. Task I was (1) t o use v a r i o u s f i n i t e element r e p r e s e n t a t i o n s t o perform a number of v i b r a t i o n a l a n a l y s e s on a c y l i n d r i c a l i s o t r o p i c s h e l l and (2) t o compare t h e r e s u l t s thus obtained w i t h known s o l u t i o n s . The a n a l y s e s were performed f o r v a r i o u s g r i d s i z e s , v a r i o u s element t y p e s , and v a r i o u s mass m a t r i c e s . The f i n a l g o a l was t o d e f i n e an optimum a n a l y s i s (one u s i n g t h e fewest degrees of freedom and t h e l e a s t computer time) t h a t would reproduce, w i t h r e a s o n a b l e a c c u r a c y , a number of t h e lowest frequency s h e l l modes. I n Task 11, f i n i t e elements were used t o perform a s e t of v i b r a t i o n a l a n a l y s e s on a g i v e n p r a c t i c a l s t r u c t u r e t o demonstrate t h e v a l i d i t y of t h e conclusions implied from Task I. The s t r u c t u r e t h a t was analyzed approximates t h e m u l t i p l e docking a d a p t e r . The b a s i c MDA s t r u c t u r e , a c y l i n d e r having a t r u n c a t e d cone a t t a c h e d t o one end, was approximated by a n e q u i v a l e n t i s o t r o p i c , homogeneous s h e l l . Two d i f f e r e n t elements and two mass m a t r i c e s were used i n t h e a n a l y s i s . The r e s u l t s of t h i s a n a l y s i s were t h e n compared w i t h r e s u l t s from a computer program known t o produce a c c u r a t e r e s u l t s f o r symmetric homogeneous s h e l l s of r e v o l u t i o n . S e l e c t i n g t h e element s t i f f n e s s and m a t r i c e s p l a y s a n important r o l e i n determining the (DDS/Martin) accuracy of t h e r e s u l t s . 3. Study of Use of Scale Models t o Determine t h e S t r u c t u r a l Dynamic C h a r a c t e r i s t i c s of Space Vehicles (Ref. October/ November 1968, p. 48) The a n a l y t i c a l development of t h e e q u i v a l e n t t r u s s r e p r e s e n t a t i o n of t h e 100-meter r e f l e c t i n g space antenna was completed. This a n a l y s i s i n d i c a t e s t h e d e f i n i t e f e a s i b i l i t y of c o n s t r u c t i n g t h e dynamic model from t h i n - w a l l tubing o r rod s t o c k i n a t r u s s con£ i g u r a t i o n s i m i l a r t o t h e p r o t o t y p e . Diagonal c r o s s - b r a c i n g of i n d i v i d u a l model bays ( r a t h e r t h a n a s i m u l a t e d r e f l e c t i n g s u r f a c e ) i s assumed i n o r d e r t o reduce t h e e f f e c t of aerodynamic damping should i t be d e s i r a b l e t o t e s t t h e model i n an ambient environment. A d e s i g n s t u d y t o e s t a b l i s h t h e optimum model s c a l e f a c t o r was i n i t i a t e d . P r e l i m i n a r y r e s u l t s of t h i s a n a l y s i s i n d i c a t e t h e f e a s i b i l i t y of c o n s t r u c t i n g t h e model from e i t h e r s t e e l o r aluminum rod s t o c k ( d i a , = 0.06 i n ) a t model s c a l e f a c t o r s a s low a s 1 / 6 0 , A l i m i t e d e f f o r t t o e s t a b l i s h c r i t e r i a f o r the model s u s pension system was conducted. No d e f i n i t e conclusions a r e y e t a v a i l a b l e . �D e f i n i t i o n of t h e r e p l i c a AAP c l u s t e r model i s c o n t i n u i n g w i t h o u t d i f f i c u l t y . The s t u d y i n d i c a t e s tfiat it w i l l b e f e a s i b l e t o c o n s t r u c t t h e MDA c y l i n d r i k a l s e c t i o n frdm one p i e c e of 6061-T6 p i p e . ~aehfning chkn+miliing processes w i i l bk used t o a c h i e v e the f i n a l thin-v&ili/weld l a n d a r e a dgpeafance. (D~s/Mdrtin) FLIGHT VIII. A. %WL!T ~ A L Y S I E DIVISXON ~ p e c i Q 1P r o j e c t s & £ i c e and S t a f f 1. F~wd-Pay1oad A hek Pligtik k v a l i i 9 t t o n w.d$khii;t ~ r o u ~ - J e a ~ l d[FEWG-P) ad prelimiiidiry U P Fd$iaiid etr&luail'dri p l k b ha3 Been d i s t r i b d k d d arid regfionkes hgve b ~ tec.eFv&. @ ~ h 3 i new d h f t 3hdi1ld GijdH b& ke&dy f o r review. THe C ~ ~ Y iI n~ EtHe FblS of h 9 ~ tfar payload3 niade the r e v i s i o d hekesdary; t h e cfiilirtnan of tHe FEWG-P m e t w i t h t h e integrkttion cont r a c t o r i n DehveF' t b d i s c l i ~ ss t & £ Guppbrt t o t h e FEWG-P, t h e p l a n comment review, and the &gent33 f o r t h e 6th. FEWG-P ineeklng scheduled fo4 February 11-12. On ~ & c & m ~21-ih5 er 1966, hk, &than inohitdl@d t h e Apollo 8 m F s d i o n from pre-18uiich through L u h a ~OrbFt I n s e r t i o n (LOIf a t t h e M i s s i o n Cdntrol Center (MCC) and Also t h e real/neaP-real-ti'me o p e r a t i o n of kH@ MSC Migsion E v a l u a t i o n Te6m ( c o u n t @ ~ p & kt to t h e MSFC &WG) i n s u p p o r t of t h e MCC and p o s t - a i s ~ i o he v a l d a t i o n , Be a l s o handled i n t e r - c e n t e r (launch v e h i c l e ) CvAluation FntePfhceb. M r ; Natfian a160 atcended two Apollo 8 f l i g h t crew d e b r i e f ings a t MCS: (a) Program &nd p r o j e c t d e b r i e f i n g on Jaduary 2, 1969. (b) Sys tems ( m i s s i o n e v a l u a t i o n ) d e b r i e f i n g on January 9-10, 1969. . ~ o n s o l i d a t e dApoll'o 8 f l i g h t crew d e b r i e f i n g n o t e s ( o u t p u t frdki t h e Technical Pr'dgram and Pro j e e t , and Sys tems D e b r i e f i n g s ) were d i 4 t r i b u t e d t o FEP meinbe?$. �B. F l i g h t E v a l u a t i o n Branch 1. Saturn I B The AS-205 p o s t f l i g h t t r a j e c t o r y r e p o r t r e c e i v e d from CCSD has been reviewed and i s b a s i c a l l y c o r r e c t . D i s t r i b u t i o n w i l l be made i n e a r l y February. 2. Saturn V a. AS-503 C' (1) (Apollo 8 ) Postflight Trajectory The p o s t f l i g h t t r a j e c t o r i e s have been d i s t r i b u t e d t o t h e v a r i o u s u s e r s . A t S-IVB f i r s t c u t o f f , t h e s p a c e - f i x e d v e l o c i t y was 0.44 m/s g r e a t e r than nominal, and t h e a l t i t u d e was 0.02 km lower t h a n nominal. This r e s u l t e d i n an o r b i t which had a n apogee 0.03 krn l e s s t h a n nominal and a p e r i g e e 0.16 km l e s s than nominal. The t r a n s l u n a r i n j e c t i o n t a r g e t i n g parameters were a l s o v e r y c l o s e t o nominal. The e c c e n t r i c i t y w a s 0.00083 l e s s than nominal, t h e i n c l i n a t i o n w a s 0.025 deg. g r e a t e r t h a n n o m i n a l , ' t h e node was 0.043 deg. g r e a t e r than nominal, and C3 was 49,631 m 2 / s 2 l e s s than nominal. A t t r a n s l u n a r i n j e c t i o n , t h e s p a c e - f i x e d v e l o c i t y was 5.23 m/s l e s s t h a n nominal, and t h e a l t i t u d e was 3.62 km h i g h e r than nominal. The s l i n g s h o t maneuver was s u c c e s s f u l l y accomplished, was placed i n a s o l a r o r b i t . and t h e S-IVB/IU (2) P o s t f l i g h t Control Analyses E v a l u a t i o n of the c o n t r o l s y s tem a c t i v i t y is e s s e n t i a l l y completed w i t h t h e e x c e p t i o n of APS p r o p e l l a n t consumption and o r b i t a l maneuvers. MDC e x p e c t s t o i n p u t t h e s e d a t a by February 3. CSM s e p a r a t i o n a n a l y s i s has n o t been completed, b u t r e c e n t i n f o r m a t i o n obtained from MSC has r e s o l v e d a l l d i s c r e p a n c i e s . To d a t e , no anomalies i n c o n t r o l system performance have been d e t e c t e d . NAR/SD has confirmed t h a t t h e 1 8 Hz o s c i l l a t i o n s e e n i n t h e c o n t r o l r a t e gyros d u r i n g t h e S - I 1 performance s h i f t w a s p r o p e r l y a t t e n u a t e d by t h e c o n t r o l £ l i t e r networks and w a s a b s e n t from t h e a c t u a t o r c u r r e n t and p o s i t i o n measurement d a t a . The magnitude sensed by t h e gyros were 10.0, .06 and 2.5 d e g / s e c peak-to-peak f o r t h e p i t c h , yaw and r o l l a x e s , r e s p e c t i v e l y . These magnitudes a r e c o n s i d e r a b l y lower t h a n sensed d u r i n g b o o s t when r a t e s of 3.2, 1.2 and 10.7 d e g / s e c were s e e n f o r f r e q u e n c i e s on t h e o r d e r of 15-35 Hz. �(3) P o s t f l i g h t Guidance Analysis The guidance aqd n a v i g a t i o n s ys tern performed v e r y s a t i s f a p f o r i l y d u r i n g a l l p e r i o d s of f l i g h t f o r which d a t a a r e a v a i l a b l e , The b o e s t n a v i g a t i o n and guidance schemes were p r o p e r l y execyted and t e r m i n a l parameters f ~ bro t 4 parking o r b i t and TLI were v e r y good. A l l t a r g e t parameters were s a t i s f a c t o r i l y achieved and o r b i t a l o p e r a t i o n s were nominal. The v e h i c l e f l e w p s l i g h t l y f l a t t e r p r o f i l e than p r e d i c t e d . A t 6-IC OECO, the v e h i c l e a l t i t u d e was l e s s than p r e d i c t e d and t h e t o t a l v e l o c i t y g r e a t e r . The r e s u l c i q g optimum f u e l usage t r a j e c t o r y determined by t h e t!@G f l i g h t pyogray wets p r e d i c t a b l e and r e s u l t e d i n s a t i s f a c t o r y end c o n d i t i o n s . The ggidaqee h@rdvataze c ~ m p ~ n e n tosp e r a t e d as deeigned. ~ r b i t a ft e l e m e t r y i n d i c a t e d gypo d r i f t s were w e l l w i t h i n s p e c i f i c a t i o n s . Telemetry from the LVaC i n d i c a t e d t h a t i n e r t i a l r e f e r ence was s t i l l being n a i n t a i n e d a f t e r 7 haurs of f l i g h t . V e l o c i t y c ~ m p a r i s ~ nwsi t h t h e f i n a l p a s t f l i g h t t r a j e c t o r y i n d i c a t e v e r y gqod cpapar$sone f o r t h e b o o s t t a p a r k i ~ go r b i t t r a j e c t o r y . The comparisons a r e ~ e l a t i v e l ygosd f o r t h e a e ~ o n dS-IVB burn. The d i f f e r e n ~ eprobably r e s u l t s more from t r a j e c t o r y d a t a than t h e LVnCi Rowewer, campanent d i f f e $ a n c e a do 9esulF from a prpgrwmed v e p t i n g p r o f i l e used d u r i n g p a r k i n g o q b l t , The tatal v e l o c i t y change d u r i n g second S-IVB burn as computed by t h e LVQG was 2.2 mdsec g r e a t e r t h a n s h o r n by t h e p o s t f l i g h t t r a j e c t o r y . The v e l a c i t y change as measured by t h e ST-124-M-3 p l a t f o r m system w4s w i t h t n 0.05 m/sec of t h e o p e r a t i o n a l t r a j e c t o r y v a l u e f o r t h e second S-TVB hu'rq mode. ( 4 ) P o s t f l i g h t C l u s t e r e d Engine P r o p u l s i o n Analysis The S-IC c l u s t e r e d engine p r o p u l s i o n a n a l y s i s was made by Boeing H u n t s v i l l e (TBC) u s i n g t h e i r r e c e n t l y developed g r a p h i c s d i s p l a y c g p a b i l i t y . The g r a p h i c d i s p l a y has proved t o be a v e r y u s e f u l t o o l t o speed t h e p r o p u l s i o n a n a l y s i s . It has enabled TBC t o meet t h e i r d e l i v e r y schedule although the f i r s t propulsion reconstruction d a t a tape from R-P&VE had erroneous d a t a . A p r e l i m i n a r y d r a f t of t h e f i n a l r e s u l t s of t h e i r a n a l y s i s has been r e c e i v e d ; t h e f i n a l r e p o r t w i l l be p u b l i s h e d by 35 days a f t e r launch. �(1) Emergency D e t e c t i o n System Analysis The TBC Document No. ~5-15555-4B, "Saturn V Launch Vehicle Emergency D e t e c t i o n Sys tem A n a l y s i s , SA-504," r e c e i v e d January 13, 1969, has been reviewed. Comments were s e n t t o TBC, and t h e r e v i s e d document should be d i s t r i b u t e d i n e a r l y February. The F l i g h t Mechanics Panel Document No. 69-FMP-1, "AS-504 Mission D , Apollo 9, Emergency D e t e c t i o n System (EDS) and F l i g h t Dynamics L i m i t s , ' ' i s b e i n g reviewed. D i s t r i b u t i o n i s planned f o r e a r l y February. (2) Dynamics Analysis and Wind Limits The dynamics a n a l y s i s document was d e l i v e r e d by TBC on January 30, 1969. The i n f l i g h t wind l i m i t s a r e p r e l i m i n a r y ; updated ones based on t h e l a t e s t t r a j e c t o r y and s t r u c t u r a l d a t a should be d i s t r i b u t e d i n e a r l y February. (3) Abort and A l t e r n a t e Mission Analysis The S a t u r n AS-504 Launch Vehicle O p e r a t i o n a l Abort and A l t e r n a t e Mission T r a j e c t o r y document was d e l i v e r e d January 30, 1969, on s c h e d u l e . The document, now being reviewed, should be ready f o r d i s t r i b u t i o n i n February. No S-IVB s t a g e PU f a i l u r e a n a l y s i s was performed d u r i n g f i r s t burn s i n c e e a r t h parking o r b i t (EPO) can b e a t t a i n e d w i t h a PU f a i l u r e t o any p o s i t i o n . This b e i n g a "D" m i s s i o n , i t was f e l t t h a t a n o u t - o f - o r b i t S-IVB PU f a i l u r e a n a l y s i s w a s n o t n e c e s s a r y . Also, EPO can b e a t t a i n e d f o r S - I 1 s t a g e mT f a i l u r e t o any p o s i t i o n . On AS-203, w i t h a 30 low performing v e h i c l e and a Z-accelerometer f a i l u r e b e f o r e 280 seconds, t h e S-IVB s t a g e f a i l e d t o a c h i e v e a 75 n.m. p e r i g e e . For AS-504, t h e S-IVB s t a g e can a c h i e v e a 75 n.m. p e r i g e e f o r a Z-accelerometer f a i l u r e a t any time. On AS-503, w i t h a 30 h i g h performing v e h i c l e and a n X-accelerometer f a i l u r e b e f o r e 80 seconds, t h e S-IVB s t a g e f a i l e d t o a c h i e v e a 75 n.m. p e r i g e e . For AS-504, w i t h a 30 low performing v e h i c l e and a n X-accelerometer f a i l u r e b e f o r e 60 seconds, t h e S-IVB s t a g e f a i l s t o a c h i e v e a 75 n.m. parking o r b i t . J Abort and a l t e r n a t e m i s s i o n p r e s e t t i n g s f o r t h e LVDC f l i g h t program were checked and s u p p l i e d t o R-ASTR a s scheduled. �c. General (1) 6?D p a j e c t q r y C a p a b i l i t y Development S i n c e t h e dgcfsj.on w a s made t o g o t o a s i n g l e 6-D t r a j s c c p ~ ys i p u l a t i o n p r o g y p on t h i Upivac 1108 f o r u s e w i t h i n t h e d i v i s i ~ p ,puch p l a l ~ n i n gand o r g a n i z a t $ o n have been accpmplished. The gchedule goy t h e n y j o r m i l e s t p n e ~is shown Date - Capab il i f y . -. '1°C " o p e r a f i o n a l t r a j e g f ~ f@9-505) ~ Reg$- tra j e c t ~ p ySuPPoyt: (48-505) PSM p i e d t o OT degk February 15 March 15 April 1 The a t p t u ~pg t h e a p e r a t i o n a l t r a j e c t o r y is a s follows: (a) A l t h ~ u g hR-FOMP p e r s q n n e l have worked v e r y hard t o c o n v e r t t h e p r e s e n t ~ A A Mdeck fit h e Upivac 1108, v e r y l i t t l e p r o g r e s s ha9 been made thus f a r . The d i f f i c u l t i g s a r e w i t h t h e systetp and a r e somewhat random. Thg encqprag$n& a s g e F t of t h i s is t h e e x c e l l e n t t u r n around pn t h e Urliva5: 1108. ( Chepko~kpf t h e IGM mqdule f o r S _ I ~ b u is~ ~ ~ n f i n u j npr, g t h e IBg 7994 slM c q p l e t e thrqygh $-IVB r e i g p i t i a n . To p s q i s t ip t p i s chqpkqyFI rgry@!4 as f o r fqcpyd prqbiems, ~ ~ ' I c $ I r a u t i s e whiph can r)m indepegdeptly of php 6-0 t r a j e c t o r y ' brogram i s being prepared. (c) Berssnnel have been a s s i g n e d t o e s t a b l i s h she c a p a b i l i t y t o a c c e p t a P&VE p r o p u l s i o n t a p e and t o o u t p u t a B7 t a p e , and t h e work w i l l ' q o o n begin. The d e t a i l e d t a s k s r e q u i r e d f o r t h e o t h e r m i l e s t o p e s have been d e f i n e d , and p e r s o n n e l have been a s s i g n e d . Considera b l e planning must be done i n t h e do~um-entationand d a t a c o o r d i n a t i o n prqcpdures. (2) S-IC Engine-Out Chi-Breeze Schedule The AS-504 c h i - f r e e z e s c h e d u l e f o r a n S-I€ s t a g e engine f a i l ~ r ewas n o t p r o p e r l y implemented i n t h e Launch Vehicle D i p j F a l Computer (LVDC), I f a n engine were t o f a i l b e f o r e T1 14 secs., t h e LVDC would compute t h e l e n g t h of c h i - f r e e z e based on a T1 14-secpnd englpe f a i l u r e . This could r e s u l t i n t h e c h i - f r e e z e d u r a t i o n being ~ e a y by ~ das much as 9.6 geconda. A s t q d y was made t o d e t e r q i n e t h e e f f e c t of t h e s h o r t e r c h i - f r e e z e on e a r l y F-1 engine f a i l u r e s . For ~ p g $ p a lwinds, b o t h t h e A S ; ~ O ~and AS7505 v e h i c l e s would l o s e c o n t r o l 4ufCng S-IC pqwered f l i g G t f o r a lower c o n t r o l engine f a i l u r e b e f o r e + + �approximately T1 + 6 seconds. The most obvious s o l u t i o n t o t h e c o n t r o l problem would be t o change t h e LVDC l o g i c and corresponding hardware t o p r o p e r l y implement t h e p r e s e n t c h i - f r e e z e schedule. However, because of l a c k of time, t h i s change could n o t be made on t h e AS-504 and AS-505 v e h i c l e s w i t h o u t a d e l a y i n t h e launch s c h e d u l e s . An a l t e r n a t e s o l u t i o n , a l t h o u g h i t i s n o t as d e s i r a b l e , would be t o change t h e c h i - f r e e z e schedule. It has been v e r i f i e d t h a t a'60-second c h i - f r e e z e d u r a t i o n , f o r a n F-1 engine f a i l u r e b e f o r e TI 14 seconds, would s o l v e t h e cont r o l problem. This s o l u t i o n has been implemented on t h e AS-505, and is now scheduled f o r t h e AS-504. A memorandum recommending that: t h e LVDC l o g i c and a s s o c i a t e d hardware be modified on t h e AS-506 and subsequent v e h i c l e s t o permit t h e use of t h e d e s i r e d c h i - f r e e z e s c h e d u l e , has been s e n t t o R-ASTR-NG. + (3) Navigation Update A n a l y s i s The Boeing document No. 5-9600-H-160, "SSR-216, Navigation Update C a p a b i l i t y Checkout," December 16, 1968, w a s r e c e i v e d . S i n c e t h i s document is v e r y l e n g t h y , a summary (Memo No. R-AERO-FF-1-69) i s being d i s t r i b u t e d . The n a v i g a t i o n update a n a l y s i s i n d i c a t e s t h a t l u n a r l a n d i n g m i s s i o n f a i l u r e s a r e reduced by performing a n update i n e a r t h p a r k i n g o r b i t . Assuming t h e "present" (45 m/s) midcourse AV budget, 3200 f a i l u r e s (per m i l l i o n f l i g h t s ) a r e reduced t o 2500. I f t h e "proposed" (18 m / ~ )budget i s used, 15400 f a i l u r e s a r e reduced t o 3360 failures. S e v e r a l items concerning n a v i g a t i o n update s t i l l need t o be i n v e s t i g a t e d . One i s t h e e f f e c t of manual c u t o f f s t o p r e v e n t e x c e s s i v e overspeeds. Another is t o determine t h e AV budget r e q u i r e d t o reduce f a i l u r e s t o a more d e s i r a b l e l e v e l . (4) P r o p u l s i o n S i m u l a t i o n Module (Operations Research, I n c o r p o r a t e d (ORI) ) S e v e r a l m o d i f i c a t i o n s have been made t o t h e SPED- PSM computer program t o enhance i t s u t i l i t y . ( a ) The i n f l u e n c e c o e f f i c i e n t model was a l t e r e d s o t h a t Rocketdyne i n f l u e n c e c o e f f i c i e n t s f o r PU v a l v e a n g l e , m i x t u r e r a t i o , and c h a r a c t e r i s t i c v e l o c i t y c o r r e c t i o n could b e used d i r e c t l y . (b) The i n f l u e n c e c o e f f i c i e n t model was provided w i t h a n independent v a r i a b l e f o r use i n performing p e r t u r b a t i o n a n d / o r dispersion analyses. �(c) The engine model was provided w i t h a b i a s and s c a l e f a c t o r a r r a y t o a i d i n compensating f o r n o n l i n e a r i t i e s and d a t a incompatibil i t i e s . A l l of t h e s e modifications have been programmed, checked o u t , and documented. (5) S t u d i e s i n the Theory and A p p l i c a t i o n of Kalman F i l t e r i n g Two r e p o r t s have r e s u l t e d from a c o n t r a c t w i t h t h e Univac Federal Systems D i v i s i o n of Sperry Rand. The f i r s t r e p o r t , " I n t r o d u c t i o n t o Kalman F i l t e r i n g , " is a survey of the t h e o r e t i c a l developments l e a d i n g t o Gauss's l e a s t s q u a r e s , Markov's minimum v a r i a n c e s t a t i s t i c a l e s t i m a t i o n theory, t h e Wiener f i l t e r , and t o t h e u n i f i e d e x t e n s i o n t o t h s Kalman f i l t e r , A step-by-step computational procedure f o r the Kalman f i l t e r is developed w i t h s e v e r a l s p e c i f i c a p p l i c a t i o n s given. The r e p o r t includes an exten'sive l i s t of r e f e r e n c e s . The second r e p o r t , "Survey of E r r o r Sources f o r Estimates i n Kalman ~ i l t e r i n g , " i d e n t i f i e s t h e causes and e f f e c t 8 t h a t lead t o v a r i o u s e s t i m a t e e r r o r s and d i s c u s s e s t h e v a r i o u s methods t h a t have been proposed f o r t h e i r treatment. These methods a r e derived i n d e t a i l using a n o t a t i o n comp a t i b l e w i t h t h e former r e p o r t . The problem of d a t a s a t u r a t i o n is explored, and s e v e r a l approaches f o r salutian are developed. C. Tracking and O r b i t a l Analysis Branch 1. Saturn V AS-503 C t Mission a. (1) A s h i p - t r a c k i n g and communications a n a l y s i s was i t e r a t e d s e v e r a l times b e f o r e a f i n a l s e t of coordinates f o r t h e s h i p s The f i n a l a n a l y s i s was documented i n memorandum was e s t a b l i s h e d R-A.ERO-FT-50-68. . (2) The S-IVB s t a g e was s u c c e s s f u l l y perturbed by l u n a r g r a v i t y t o a c h i e v e a h e l i o c e n t r i c o r b i t . This l u n a r g r a v i t y pert u r b a t i o n caused a s l i n g s h o t e f f e c t by adding s u f f i c i e n t v e l o c i t y t o the S-IVB s t a g e t o achieve a n e a r t h escape v e l o c i t y (C3 w i t h r e s p e c t t o the e a r t h > 0). O r b i t parameters of t h e s t a g e a t p e r i c y n t h i o n (lunar c l o s e approach) a r e a s follows: �D i s t a n c e t o c e n t e r of moon Distance t o lunar s u r f a c e O r b i t i n c l i n a t i o n t o l u n a r equator D e c l i n a t i o n o r l a t i t u d e of c l o s e approach subpoint* Longitude of c l o s e approach s u b p o i n t (pos e a s t ) * Approximate time of c l o s e approach Dec, 24, 1968 3000 km 1262 km 44-56" 0.4" 79.6" 10: 50 U.T. These parameters a r e based on a Goddard Space F l i g h t Center v e c t o r f o r t h e S-IVB s t a g e on ~ e c e m b e r22 a t 0100 U.T. This v e c t o r was determined u s i n g t h e b e s t t r a c k i n g i n f o r m a t i o n a v a i l a b l e (Unified S-Band t r a c k i n g of t h e S-IVB s t a g e from s t a g e p a s s i v a t i o n u n t i l l o s s of CCS s i g n a l due t o b a t t e r y l i f e t i m e t e r m i n a t i o n ) . The h e l i o c e n t r i c o r b i t of t h e S-IVB s t a g e is a s follows : Semimajor a x i s Aphel i o n Perihelion Eccentricity I n c l i n a t i o n t o e q u a t o r i a l plane Period V e l o c i t y a t aphelion** V e l o c i t y a t peri2Elion** Average v e l o c i t y " " b. AS-504 "D" 1.428 x l o 8 km 1.4774 x lo8 km 1.3795 x lo8 km 0.03427 23.47" 340.8 days 29.45 kmlsec 31.54 km/sec 30.5 km/sec Mission ( I ) The t r a c k i n g and communications a n a l y s i s has been completed and d i s t r i b u t e d . +\ (2) Magnetic t a p e s of l o o k a n g l e and o t h e r s u r v e i l l a n c e d a t a have been t r a n s m i t t e d t o TBC, MSC, IBM, MDC, NAA, and John Hopkins U n i v e r s i t y . These u s e r s a r e s u p p o r t i n g R-ASTR i n t h e i r a n a l y s e s . *Referenced t o a moon-centered c o o r d i n a t e system d e f i n e d a s : X-axis p o i n t s from moon c e n t e r t o e a r t h c e n t e r (moons z e r o l o n g i tude l i n e ) . z - a x i s p a r a l l e l t o e a r t h a x i s of r o t a t i o n (through North P o l e ) . Y-axis forms right-handed system. **These v e l o c i t i e s a r e w i t h r e s p e c t t o t h e s u n and a r e v e r y s i m i l a r t o t h e v e l o c i t i e s of t h e e a r t h about t h e sun s i n c e t h e S-IVB'S o r b i t and the earth's o r b i t a r e very similar. �( 3 ) A memorandum on t r a c k i n g and cotmnu~ications a c q u i s it i o n and l o s s d a t a f o r a l t e r n a t e m i s s i o n s of t h e launch v e h i c l e has been prepared. ' ( 4 ) ~ n a t y s i shhd been performed t o i n s u r e nb S-IVB impzict, of t h e mdon, A 1 1 d2itei, laurfch times, and azimukh windows i n d i c a t e t h a t the S-IVB W i l l n o t impact t h e inobn on a ndminal m i s s i o n , For t h e contingency mi9sion With afily bne burn, the S-IVB does pass i n t h e v i c i n i t y of t h e &on, b u t a g a i n no impaktii werk i d e n t i f i & d , t h e c l o s e s t approach t o t h & boon bking approximately 5b,00O k i l o m e t e r s . (1) an g'sR hds t h e n sFg6bd w i t h TBC Fd p r b t i d e p r o p & r a t t i t u d e s and tbh &V r e q h i i e d fur t h e &t$g& t o s l i & e l i t l t , t h e htbon. $i-&linikridky ?e&bik8 Wgre $ i \ f k h t b k-Am# &fid R-P&& t d hfibblb thzSit a n a l y s e s t o coritihiie. ?hes& prkiihifiai-jr fjardihgterg inf&e' d = l l b O akid nv = 40 rntl!!ec. A f 8 a k i b i l i t y dtudy vaB &rforrned dri t h e p 6 d s i b i l i t y of k o n t t o l l i n g t h e g a r t h r e e n t r y of t h e s - W ~s t a g e fkom a 100 n.thi. o r b i t . The s t u d y d & ~ u m e dt h e d& on a l d a r m i s s i o n s e p a r a t e d f r m t h e , S - ~ i T f f i n e a r t h b r l i i t ; and thS drage e ~ d i dBe r e e n t e r e d b$ & i t h e r f e i g n i t i n g t h e S-IVB o r By a cold dd&p 8f tHe p f ~ h 8 1 . f a n t s d ~ r e l f h i n a ri n~ v e s t i gatioris show k h d t e i t h e r dead3 k b b i d be ddkd t o r e b h t e k khe S-IVB i n t b an ocean a r e a t o minimize t h e hdsayds of o r b i t a l d e b r i s . However, t h e irripact f o o t p r i n t could be g r e a t l y reduced by r e i g f i i t f n g t h e s t a g e and a p p l y i n g a much l a r g e r e q u i v a i e n t retro-AV. Orbftirl decay and l i f e t i t t r e s f o r v a r i o u s f l i g h t a b o r t s and e a r l y f l i g h t t e r m i n a t i o n s on t h e AAP m i s s i o n a r e being i n v e s t i g a t e d . These s t u d i e s , t o b e used t a dete*mine madimum d e l a y s which could occur ahd s t i l l complete t h e b a s i c c o r e missitjn, i n c l u d e u s i n g only a nominal decay w i t h b o o s t c a p a b i l i t i e s of t h e fdllow-on CSM~s. R e s u l t s of t h e s e deeay and l i f e t i m e a n a l y s e s w i l l be documented by memorandum. �D. F l i g h t Mechanics Branch 1. Saturn V a. AS-503 C' Mission (1) Operational T r a j e c t o r y : The f i n a l p u b l i c a t i o n of t h e Boeing Company's Operational T r a j e c t o r y f o r ~ e c e m b e r l ~ a n u a rwas y received and d i s t r i b u t e d approximately 10 days before launch. Although t o o l a t e t o s e r v e a s a g e n e r a l r e f e r e n c e f o r t h e Apollo 8 mission, i t w i l l be t h e b a s e l i n e a n a l y s i s f o r subsequent lunar mission o p e r a t i o n a l trajectories. (2) Targeting: The a c t u a l r e s u l t s of t h e Apollo 8 t r a n s l u n a r i n j e c t i o n (TLI) powered f l i g h t , with t h e p r o j e c t e d required midcourse of approximately 6 f e e t per second computed i n r e a l time by MSFN (Manned S p a c e f l i g h t Network), has proven t h e Saturn V launch v e h i c l e s y s tem c a p a b i l i t y t o perform t h e l u n a r mission. I n p a r t i c u l a r , t h e hypers u r f a c e concept, t h e mode of t a r g e t i n g ( i . e . , g e n e r a t i o n of t h e numerical c u t o f f c r i t e r i a and t h e IGM s t e e r i n g concept and implementation) and t h e innumerable s i m u l a t i o n models a r e no longer s u b j e c t t o t h e q u e s t i o n of whether a b a s i c flaw e x i s t s . However, t h e p o t e n t i a l of unknown cons t r a i n t s , e s p e c i a l l y i n t h e t a r g e t i n g a r e a , s t i l l e x i s t s . The r e a l l e s s o n from t h i s mission a n a l y s i s i s t h e establishment of "for r e a l " procedures of g e n e r a t i o n and v e r i f i c a t i o n . Basic flaws d i d e x i s t here i n t h e c o n t r a c t o r check procedures, a s exampled by t h e 17-second e r r o r i n e s t a b l i s h i n g t h e Apollo 8 launch window. Steps a r e being taken t o expose t h e p o t e n t i a l t a r g e t i n g t r o u b l e a r e a s (i.e., l u n a r d e c l i n a t i o n s g r e a t e r than t h e launch l a t i t u d e and h i g h l u n a r c l o s e approach d i s t a n c e s ) and t o produca procedures which w i l l p o s i t i v e l y check t h e t a r g e t i n g a c t i v i t i e s . On t h i s mission, 15 d a i l y windows were t a r g e t e d . (3) The E a s t e r n T e s t Range placed t h e a d d i t i o n a l requirement of many contingency t r a j e c t o r y s i m u l a t i o n s b e f o r e a f l i g h t waiver was g r a n t e d . Again, being t h e f i r s t Apollo v a r i a b l e azimuth launch, and a l s o p o t e n t i a l l y t h e most s o u t h e r l y f l i g h t azimuth, t h e range s a f e t y a n a l y s e s f o r t h i s mission should s e r v e a s b a s e l i n e a n a l y s i s f o r a l l Saturn V launches i n t h e 72 t o 108 degree f l i g h t azimuth s e c t o r . ( 4 ) The low payload requirement f o r t h i s mission reduced t h e s i g n i f i c a n c e of t h e f l i g h t performance r e s e r v e requirement g e n e r a t i o n , except as a b a s e l i n e f o r f u t u r e l u n a r missions. The midcourse requirement envelopewas of more concern and i n t e r e s t and w i l l probably s e r v e a s t h e b a s e l i n e f o r f u t u r e Apollo lunar missions. �(5) Real Time T r a j e c t g r y Support: While the m i s s i o n experienced no contingency'sl't'uatcon which might h u l y e x e r c i s e t h e assessment c a p a b i l i t y of f h e 1n-f l $ h t T r a j e c t o r y Teay, t h e time l i n e of a c t i v i t y was extremely smooth. --y--* (6) Slj. g h a t . The concept and implementatioq of t h e s l i n g s h o t methpd Q£ S - I n i s p b s a l was s u c ~ e s s f u l l ydemonstrated. Reasonably r g l i a b l e gigpoqal of t h e S-SVE s t a g e should npxq g x i s t f o r f u t u r e l u n a r mieqionq. ( 7 ) F l i p h g E e r f o r q n c e f n ~ e n t i v e : F l i g h t performance i n c e n t i v e c r i t e r i a were'es'r'blY$bed $or t h ' k X $ - 1 C (Boeing) , S-IVB (McDonnell Douglas], an4 IU [ I n t e r n g f $ o n a l Business Machines). C o ~ t ~ a c t u na el g p t i a Cipns between TO qpd Boaiqq did n a t culmipate i n a f l i g h t p e y f a r w n c e agreement f o r migsioq, It wap n e c e s s a r y , dqe t o t h e v a y t q b l p a z i q u t h f e a t u r e , Po e~t a k l i g h q '!pop t ~ l a u n c ho p e r g t i o n a l t r a j e c ~ o y y l ' i n o r d e r t o have a b a s a l i q e f o r compariqqn. . A O ~ 5 0 4"D" Misgion ( 1 ) C&eggti~qg$ T r a j e p t q ~ y : The docupeqped a n a l y s i s r ~f +aunch pad from was r e l e a s e d on 16 ~ ~ c e m 6 ; r19q"d". ~ u b ~ e q b e n tcharlge " R J I go "A" pn Coqplex 39, p i u s an p p d g ~ gpf p ~ ~ p u l s i ogata n has resglted i a a t r a j e c t o r y y p d ~ f e . Th&g ~ 5- 1 1ka rplaased a p p r ~ q & ~ t e ! y 3 0 J3;jnuqry, a i t h o p g h t h e b a s i c a n a l y s i s i n Ehe e a s / b e g docwnegt w L ) l s t i l l be vaf i d . i( (2) Digpgrsioq Anqlysipr This docqment i s n e a r l y ready f o r d is t r i b u t t o p m c = 6 $ r g i p problem e x i s t g f o r e i t h e r c ~ m p l e t i o nof t h e t h r e e primary S - I D s t a g p burns t o egcape o r t h e two contiqgency 9-IVB s t a g e burns t o escape, (3) S e Safety: The range s a f e t y analys'es f ~ t rh i s v e h i c l e have been publ%sKe,d ( k i d - ~ a n u a ~ y )a,l o p g w i t h s e v e r a l a d d i t i o n a l cages r e q y e ~ t e dby t h e E a s f e r n T e s t Raqge. No a d d i t i p n a l e f f o r t i s a n r t c i p a t e d r e s u l t i n g f r w t h e chang,e i n launch pads. (4) Guj-dance P r e s e t r i n g s : The guidance p r e s e t t i n g s were t r a n s m i t t e d t o ~ s t f i b n i c b oh 2 f GbvGmber 1968. A s is t y p i c a l w i t h t h i ~d e l i v e r y , i p s u f f i c i e n t time was a v a $ l a b l e t o v e r i f y them inhouse prior t o transmittal. S e v e r a l follow-up meetings were held t o c l a r i f y d e f i n i t i o n s and, i n some c a s e s , t o modify some numbers. �c. AS-505 "F" Mission (1) O p e r a t i o n a l T r a j e c t o r y : An i n t e r i m r e l e a s e of t h e o p e r a t i o n a l t r a j e c t o r y document is due on February 11, 1969. This w i l l c o n t a i n d a t a o n l y f o r t h e f i r s t 4 d a i l y windows i n May. The f i n a l r e l e a s e , due March 15, 1969, w i l l be comprehensive f o r t h e 6-day windows of b o t h May and June. The J u l y o p p o r t u n i t y , n o t y e t d e f i n e d , w i l l b e worked on a two-month turnaround b a s i s o n l y i f a May launch does n o t occur. (2) T a r g e t i n g : T a r g e t i n g i s complete and d a t a t r a n s m i t t e d f o r t h e 17 May window, o n l y , w i t h t h r e e a d d i t i o n a l days of May t o be d e l i v e r e d on 27 January. The remainder of May and June a r e due February 14. The nominal midcourse c o r r e c t i o n r e q u i r e d i s i n s i g n i f i c a n t . Note t h a t S p a c e c r a f t Reaction Control System (RCS) margin f o r t h i s m i s s i o n i s much more c o n s t r a i n e d r e l a t i v e t o Apollo 8 a s a r e s u l t of t h e presence of t h e LM. (3) Guidance P r e s e t t i n g s : Guidance p r e s e t t i n g s were t r a n s m i t t e d ( l a u n c h d a t e independent) t o A s t r i o n i c s on January 23, 1969, i n accordance w i t h s c h e d u l e requirements. 2. AAP CCSD has been a u t h o r i z e d t o proceed on range s a f e t y a n a l y s e s i n s u p p o r t of m i s s i o n a n a l y s e s f o r AAP-1, -2, and - 4 . The b a s i c g o a l is t o a c h i e v e p r e l i m i n a r y range s a f e t y approval f o r t h e s e m i s s i o n s by mid-summer . 3. Quick Response T a r g e t i n g Program (QRTP) Conversion t o t h e Univac 1108 computer system h a s been achieved f o r t h e midcourse c o r r e c t i o n r o u t i n e of t h i s program. The t a r g e t i n g r o u t i n e w i l l be checked n e x t . If t h i s program i s o p e r a t i o n a l i n time, t h e "F" m i s s i o n t a r g e t i n g f o r t h e J u l y o p p o r t u n i t y w i l l be attempted a s b o t h a checkout and a l s o a s o p e r a t i o n a l s u p p o r t i n t h e e v e n t of a launch s l i p . �BIBLLOGRAPHY 1. NASA TN D-4963, "The I n f l u e n t i a l Aspects Of Atmospheric D i s t u r b a n c e s on Space Vehicle Des i g n Us i n g S t a t i s t i c a l Approaches f o r A n a l y s i s , I t January 1969. 2. A U A Paper No. 69-58, "A Study of S a t u r n AS-502 Coupling L o n g i t u d i n a l S t r u c t u r a l V i b r a t i o n and L a t e r a l Bending Response D~rlttlgBoost," p r e s e n t e d a t A W 7 t h A@rospaice S c i e n c e s Meeting, New York, New York, J a n u a r y 20-22, 1969. 3. TR-795-8-420, "Dynamic A n a l y s i s of ~ k n g e dF l e x i b l e Space V e h i c l e s , " C o n t r a c t MdS8-20082, M o r t r o n i c l l R u h t s v i l l e . 4. TR-795-8-498, "An I n v e s t i g a t i o n of S a t u r n VIS-IC S t a g e Coupled Long Feud i n a l i3 t r u c t u r d l V i b r a t i o n whd L a t e r a l Bending Response During Boost Ff i g h t , " Mortlronfcs/Humltaville, 5. A E R 0 - ~ ~ - 1 4 4 - 6 8 ,"Saturn V O f f i c i a l Dynamics Data," December 23, 1968. 6. R-AERo-DD-~~~-& ttljynopsis &, of POGO A c t i v i t i e s 7. R-AERO-DD-148, " ~ f f i c i a lDynamic Data f o r AS-504, Mission "D", A f t e r Payload S e p a r a t i o n , " J a n u a r y 7, 1969. 8. R-AERO-DD-1, " U P S t r u e t u l a l DynarrllLci~Data," J a n u a r y 24, 1969. 9, 8-AERO-DD-2, "Technical E v a l u a t i o n of Propo6als Received i n Response Advanced Subs t r u e t u r ing ~ e c h n i ~ u .eI f k t o RFQ DCN 1-9-75-10045 10. R-AERO-DCC-12-68, " P r e l i m i n a r y Rigid Body C o n t r o l Responses f o r t h e S a t u r n IB, AAP-2 M i s s i o n , f o r M r c h 1 and Near-IECO," Dec. 1 8 , 1968, 11. R-AERO-DCC-~~-~S, "Wind Tapes f o r GPS High Speed Analog Computer," December 1 0 , 1968. 12. R-AERO-DCC-14-68, 1968. ,It December 11, 1968. S-IVB - "Ag-503 C ' M i s s i o n , Vehicle S t a b i l i t y , " December 1 8 , I 13. IN-AERO-68-7, "Discuss i o n of Manual C o n t r o l Problems , I t DecesnbG 27, 1968, James H. Colmon. 14. IN-AERO-69-1, "Aerodynamic Design and C a l i b r a t i o n of t h e MSFC Thermal Cobd Flow Duct," J a n u a r y 9, 1969, K , D, Acoustic J e t F a c i l i t y Johns t o n , W-AERO-A, and W. C. Tidmore , Nor throp-Nor t r o n i c s H u n t s v i l l e 15. - TM X-53813, "The Use of a Ground-Baged MultPple-Beam D e t e c t o r i n Crossed-Beam Atmospheric Experimentation," J a n u a r y 30, 1969, W. H. Heybey. . �APPROVAL L: /&<./>,+.A, E . D. G e i s s l e r D i r e c t o r , Aero-Astrodynamics Laboratory DISTRIBUTION R-AERO-DIR Dr. G e i s s l e r M r . Jean Mr. B u t l e r R-AERO-R Mr. B e a n ( 4 ) Mrs. H i g h t o w e r Mrs. P e t t u s R-AERO-T Mr. M u r p h r e e Mr. C u m m i n g s Dr. Heybey Mr. J a n d e b e u r Dr. K r a u s e Mr. N a t h a n Mr. Few M r . von P u t t k a m e r R-AERO-P R-AERO-D R-AERO-A R-AERO-G R-AERO-Y R-AERO- F R-AERO-X PAO, M r . K u r t z R-DIR, MS-H, I-V-P, Mr. W e i d n e r M i s s J e r r e l l (3) Mr. P r i c e � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000049 Title A name given to the resource "Aero-Astrodynamics Laboratory Bimonthly Progress Report: December 1968 - January 1969." Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center Date A point or period of time associated with an event in the lifecycle of the resource 1969-02-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) NASA space programs Project management Type The nature or genre of the resource Progress reports Text Source A related resource from which the described resource is derived Saturn V Collection Box 30, Folder 20 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050