4 20 8242 https://digitalprojects.uah.edu/files/original/20/11068/comparadvcoolingtech_071207135801.pdf aed6d60254d832a28574cea4645685fb 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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 comparadvcoolingtech.pdf spc_stnv_000204 Title A name given to the resource "A Comparison of Advanced Cooling Techniques for Rocket Thrust Chambers". Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. 1-65-19 Description An account of the resource The document is a technical paper for Astronautics and Aerospace Engineering Magazine.The copy has handwritten notes that appear to be for revisions. The abstract states "In the early days of rocket propulsion, two primary methods were employed for cooling the walls of thrust chambers. These were uncooled metal chambers where the heat sink capacity of the chamber and nozzle wall materials limited the operating duration, and regeneratively cooled chambers where one of the propellants was circulated in a cooling jacket which constituted the chamber wall. Today, there are at least fourteen different methods with variations for cooling the combustion devices and nozzles of liquid propellant, solid propellant, and/or nuclear rocket propulsion engines. It is the intent of this paper to examine these methods, to describe for each the useful range of operating conditions, as well as present and likely future applications, to define their limitations and associated problems. Emphasis is primarily placed on liquid rocket engines." Creator An entity primarily responsible for making the resource Sutton, George P. Wagner, William R. Seader, J. D. Date A point or period of time associated with an event in the lifecycle of the resource 1965-01-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Rocket engines Cooling Thrust chambers Type The nature or genre of the resource Text Essays Source A related resource from which the described resource is derived Saturn V Collection Box 12, Folder 49 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_000200_000224 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. <a href="http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17066"> View this item in ArchivesSpace </a> https://digitalprojects.uah.edu/files/original/78/1599/spc_horn_000087.pdf f1127dba270f437e1f27b5a6c711071f 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 Helmut Horn Collection Title A name given to the resource Helmut Horn Collection Description An account of the resource Helmut Horn (June 24, 1912 to January 1, 1994) was a member of von Braun's Rocket Team. Helmut Horn earned an MS in engineering from the Institute of Technology, Darmstadt, in 1939. Shortly afterward, he began working at Peenemünde, where he stayed until 1945. He was brought over to Fort Bliss in United States on November 16 of the same year. Horn became a lecturer in Applied Mathematics at UAH in 1952. By 1965, he was employed at the Marshall Space Flight Center, and by 1969, he had become Assistant Director of the Aero-Astrodynamics Laboratory. "Later he served as deputy director of the Aero-Astrodynamics Laboratory" (Lundquist). Sources Lundquist, Charles. "Transplanted Rocket Pioneers," 2015. Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/55">View the Helmut Horn Collection finding aid on ArchivesSpace</a> 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_horn_000087 Title A name given to the resource "A Comparison of an MIT Explicit Guidance Principle with MSFC Iterative Guidance." Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. Aero-Astrodynamics Internal Note 23-64 Description An account of the resource From the summary: "Both [guidance] schemes steer toward a specified end point. The MIT scheme uses thrust to cancel out the effective gravity, a nonlinear term, which may be inefficient in certain cases. The MSFC scheme is more closely connected with calculus of variations and optimization theory in a reasonable degree of approximation." Creator An entity primarily responsible for making the resource Hart, Judson J. Date A point or period of time associated with an event in the lifecycle of the resource 1964-09-30 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource George C. Marshall Space Flight Center Massachusetts Institute of Technology Inertial guidance Spacecraft guidance Space flight Type The nature or genre of the resource Reports Text Source A related resource from which the described resource is derived Helmut Horn Collection Box 1, Folder 2 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_horn_2020_04 https://digitalprojects.uah.edu/files/original/20/11158/compflowcont.pdf.pdf 20bd0806b47e4b5378e9774a6b2f4d14 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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 compflowcont.pdf Title A name given to the resource "A comparison of four control systems proposed for Saturn V launch vehicles." Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. X-53572 Description An account of the resource Presented are the results of a study comparing four proposed control systems for the first stage flight of Saturn V launch vehicles. The primary basis of comparison is the effect on structural loads, using the bending moments at three stations as load indicators. Two of the systems sense only the vehicle attitude and attitude rate, while the other two systems also sense the lateral acceleration. A yaw plane wind response analysis, including rigid body translation, rigid body rotation, four bending modes, five slosh modes, and a non ideal control system, was performed. The winds used in the study were the Marshall synthetic profile and three selected Jimsphere-measured real wind profiles. Load relief obtained from the addition of accelerometer feedback in the control loop amounted to about 10 percent at maximum bending moment station. In view of predicted structural capabilities of the vehicle, this reduction in loads was not considered sufficient to offset the added complexity and the slight reduction in rigid body stability . Creator An entity primarily responsible for making the resource Sumrall, Phil George C. Marshall Space Flight Center. Aero-Astrodynamics Laboratory Date A point or period of time associated with an event in the lifecycle of the resource 1967-02-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Saturn launch vehicles Saturn 5 launch vehicles Testing Spacecraft control Type The nature or genre of the resource Text Essays Source A related resource from which the described resource is derived Saturn V Collection Box 20, Folder 36 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_000200_000224 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. <a href="http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17619"> View this item in ArchivesSpace</a> https://digitalprojects.uah.edu/files/original/20/11153/Decaofspacprog.pdf.pdf e7f7b59fd4603f5127b2a0b6e63a5512 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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 Decaofspacprog.pdf spc_stnv_000226 Title A name given to the resource "A decade of space progress, 1958 to 1968: General Electric Missile and Space Division offers a pictorial tribute to the National Aeronautics and Space Administration." Description An account of the resource Excerpt from G.E. Challenge, Fall (Sept.) 1968, pages 13 to 25. Date A point or period of time associated with an event in the lifecycle of the resource 1960-01-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Manned space flight Space flight United States. National Aeronautics and Space Administration Type The nature or genre of the resource Text Articles Source A related resource from which the described resource is derived Saturn V Collection Box 28, Folder 5 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_000225_000249 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. <a href=" http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17947 "> View this item in ArchivesSpace </a> Creator An entity primarily responsible for making the resource General Electric Company https://digitalprojects.uah.edu/files/original/20/11045/descst124m.pdf.pdf 12f223234438dcb6a4da383a09f1224b 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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 descst124m.pdf NO ADDITIONAL FILE - SAME AS BELOW RECORD spc_stnv_000230 Title A name given to the resource "A Description of the ST 124-M Inertial Stabilized Platform and its Application to the Saturn V Launch Vehicle." Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. 7511-64-R11 Description An account of the resource This report is a description of the ST124-M inertial stabilized platform system and its application to the Saturn V launch vehicle. It is a summary report providing the system concept and not a theoretical presentation. Mathematical equations were included only where necessary to describe the equipment; however, the detail derivations supporting these equations were not presented since this was not the theme of the paper. Creator An entity primarily responsible for making the resource O'Connor, B. J. National Aeronautics and Space Administration. Date A point or period of time associated with an event in the lifecycle of the resource 1964-06-26 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Inertial platform Saturn launch vehicles Inertial guidance Type The nature or genre of the resource Text Reports Source A related resource from which the described resource is derived Saturn V Collection Box 11, 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_000225_000249 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. <a href="http://libarchstor.uah.edu:8081/repositories/2/archival_objects/16992"> View this item in ArchivesSpace </a> https://digitalprojects.uah.edu/files/original/20/11155/descst124minerstab.pdf.pdf 498c9649b1614c1582ca1dff9290294c 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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 descst124minerstab.pdf spc_stnv_000231 Title A name given to the resource "A description of the ST-124M inertial stabilized platform and its application to the Saturn V launch vehicle." Description An account of the resource This report is a description of the ST-124M inertial stabilized platform system and its application to the Saturn V launch vehicle. It is a summary report providing the system concept, and not a theoretical presentation. Mathematical equations were included only where necessary to describe the equipment; however, the detailed derivations supporting these equations were not presented since this was not the theme of the paper. Creator An entity primarily responsible for making the resource O'Connor, B. J. Date A point or period of time associated with an event in the lifecycle of the resource 1964-06-26 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Inertial guidance Inertial platform Saturn launch vehicles Type The nature or genre of the resource Text Reports Source A related resource from which the described resource is derived Saturn V Collection Box 11, 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_000225_000249 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. <a href=" http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17003"> View this item in ArchivesSpace </a> 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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/193/13856/Defense_Billboard_60_001.pdf 8a50c07b8d2e00fc8da3e6c4387ed495 PDF Text Text � 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 Defense Billboard Posters 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 Defense_Billboard_60 Title A name given to the resource "A DWI Conviction Can Bring a Social Life to a Screeching Halt...But It's a Great Way to Save Lives" Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. D2.9:D36/2/No.60 Description An account of the resource Bike parked in parking lot with man visible through window Creator An entity primarily responsible for making the resource Department of Defense Date A point or period of time associated with an event in the lifecycle of the resource 1993-02-23 Temporal Coverage Temporal characteristics of the resource. 1990-1999 Subject The topic of the resource Department of Defense poster United States--Department of Defense Drunk driving Bicycles Type The nature or genre of the resource Posters Still Image Source A related resource from which the described resource is derived The University of Alabama in Huntsville M. Louis Salmon Library Defense Billboards Posters Case 1, Drawer 1 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 Defense Billboards https://digitalprojects.uah.edu/files/original/125/8496/r04c04-03.pdf da84b5bd8342bc6800f62f4311e8e6b6 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 Series 04, Subseries C: Alabama History Title A name given to the resource Series 04, Subseries C: Alabama History Still Image A static visual representation. Examples include paintings, drawings, graphic designs, plans and maps. Recommended best practice is to assign the type Text to images of textual materials. 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 r04c04-03 Source A related resource from which the described resource is derived Series 4, Subseries C, Box 4, Folder 3 Title A name given to the resource "A Future for Virginia's Past" by the Virginia Department of Historical Resources, 1988 Relation A related resource r04c-211007 https://digitalprojects.uah.edu/files/original/20/1138/spc_stnv_000054.pdf 2c71d16aefa23ff5b7d8c14e3e4197de PDF Text Text PRESENTED AT TtiE FOURTII INTERNhTlONAL CONFEREI!CE ON FLU!D SEALING HELD I N CONJUNCTION WITH ~ M ~ . 2 4AS1.E t h AlJNUAL MEETING IN PIIILE.DELPII!A, MAY 5-9.1969: This paper is thc literary prcpcrty of t l ~ eSociety indicated on the first page. Thc press may summarize frecly from this manuscript after presentation, citing source; however, publicstion of material constituting more than 2006 of tile manuscript shall bc construed as a violation of t l ~ cSoricty's rights and subject to appro2riatc I g a l actiori. Manuscripts not to be published by thc Society will bc releascd,in wri!irig for 'publica:lon by otlicr sources. Statcxcnts and opiriions advanced in papcrs arc uridcrstood to be individual expressions of tho author(s) arid not those ' of t3e Scciety. AVAILABLE. FROFA: AMEltiCAN SOCIEl-Y OF LUCRICATION CNCINECRS. 838 DUSSE tIICIl\'~A\', PARK ItIDGE, ILl.li<OlS COOGC �MfALTER J. CIESLII: Pesco Products, Gedford, Ohio Tlzc object o j t1z.c leaorit clisctissccl in this yapcr was to dceelop a rclinblc helitrtn. 60.9 sllnjt scal for rise in an electric motor-driool, licitlid osygeiz pump on a space uellicle. Tllc dcvclo~~mcnt e.orl coocred tests on ttco basically diflerent jnce scal designs, one raith an atfncllecl carbon jacc and ille olllcr tvitll o floating lal,$fted carbon jaca Scocral tclloi~stiibration da~npingcleviccs orlcl unriotrs seal material coinbitzafioru tacre in ticsf iga fcd. . hcliuili seal for use in an eIcctric motor driven liquid oxygcn pump for a n~anncclspacevchicle was tllc objective of tliis investigation. PUfAP DESIGN Elcctric motel--driven, liquid oxygen pumps can be dcsigndd. with a floodccl, canncd, or scalccl motor. Shaft scals arc not required in the first t\vo typcs of units, but oiic or more arc ncccssary with tllc scalcd type motor. Tlic lattcr type of unit is discussed llcrc togctllcr with thc tcst work concluclcd in developing a satisfactory sllah scd. From the clcsign stanclpoint, thc flooded motor unit is t l ~ clnost sinlplc. All motor cotnpo~lcnts opcrate in dircct coritact \\pith the punipccl fluicl and no seals are rcquirccl. But, from a safcty standpoint; this dcsign could bc thc most hazardous. IVhilc all matcrials arc sclcctccl for compatibility \vitll liquicl oxygct~,co~libi.lstionis still possiblc undcr ccrlaiti conclitiol~s.For instance, in a si~nulatcdshort circuit test of a motor stator siibmcrgccl in liquid oxygen, the electrical iiisulalion, part of the colq~crwindings,'and iron stator Inminations were burncd away, as slio\vn in Fig. 1. Coinbustion of thcsc matcrials was tcrniinatccl only wlicn tlic supply of oxygcn was exhaustccl. .: In thc canmcl rtlotor dcsign, usually only thc stator laininations, windings ancl lcads arc hcrmctically scalcd witliin a stainless-stccl slicll, thiis l>rcvcntingdircct contact with tlic liquicl osygcn. 111c rotor, howcvcr, is nor~nallystill submcrgccl clircctly in thc licluicl. In this dcsign tlic safcty aspccts of t l ~ cstator with its elcctrical insulation arc itnprovccl.' I.To\vcvcr, t l ~ cprcscncc of t l ~ c . slainlcss slccl slator sl~cllit1 t l ~ cmotor air gap rccluccs thc molor clricicnr:y and iticrcascs tlic inolor opcraling currcn t. For t l ~ cifnit c;isci~xscdItcrc thc rccluirccl ciirrcnt was incrcasccl 1 y approsiiiintcly 20 pcrccnt \vhcn a canncd stator clcsig~lwas tcslccl. This figurc worilcl 11c ftirtl~cr incrcasccl if llic rolor \\.as also cannccl. ' , INTRODUCTION Liquid ohygcn is one of thc tnorc aclivc cryogenic fluids. Unclcr propcr conditions.it \\.ill react with tllc colnnlon coinbustible matcrials, and undcr ccrtaiu conclitions,, such as aclclccl energy input, it will rcact with mclallic construction materials. l'his is an important consiclcration in tlic dcsign of cquipmc~ltfor usc in liquid oxygen applications. It is cspccially important in the design of rotating macliiucry, for cxainplc eleclric niotor-drivcn pumps. In this type of equiymcnt the rcsultaut encrgy input cluc i0.a possihlc electrical overload or mechanical sllock may bc sufiicicnt to initiate a mild rcaciion or cvcn a violent detonation. Elcctric motor-clrivcn liquicl oxygen pumps havc oieratcd succcssfiilly, undcr norn~alconditions, with all parts complctcly submcrgcd and wcttccl by liqiiicl oxygcii. 13ut in applicatioos which may prescnt a possiblc hazard to human lifc, tllc safcty aspccts can bc enhanced by aclditional clcsign precautions. In tlic elcctric rilotor arc drivcn ptnnp for instance, evcn thougli all ~n;~terials sclcctccl for lnaxi~iiiilncornpal ibili ty with liq~iiilosygii~, thc motor can bc cncloscd in a hcliiun gas incrtccl containcr. A dcsign of this typc, of coursc, will rcqliirc roiatilig shaft scals. Illc sclcction and testing of a stiital>ld . . 9rcscntcd.ul lhc Fourt:i In1crna:ionol ~orafc;enceon Fluid Sco!ing h ~ l in d conjunction with I:ie 1969 ASLE Annuol hlcc!ing irr Pliilodcl;~l~io,Pa. This papcr sponsored by flle An~criconSocicly OF hlccllonicol Engineers. . .. .263 . �flange 10 incllcs in dialnctcr. lirciglit of t l ~ cunit is . splxosimatcly 15 pounds. On [he space v'clliclc the unit is fliinge Inounlccl'in a bottom opening of a liquid osygcn supply lank ar~c1,'cxccpt for the outsidc face of the flange, is totally sub-. rncrgcd in licluicl oxygen at -2'37°F.This cryogcnic cooling pcrlnits a lnotor dcsign of smaller size and \wight and of improvcd cficiency due, to the rctli~ccd coppcr losses in thc stator windings. Normally, the moior cavity is incrted wit11 hclium gas at a prcssrlrc of 11 , I:roximatcly 50 psig, but this prcssurc can go as high as.80 . psig, which is limitcd by the motor cavity rclief valve. , SEAL CONSTRUCTION Fig. I-Elcclric ~ o t o Slator ; Aller Sirnutoted Short Circuit Test in Liquid ' Oxygen. In the sealed motor dcsign all motor parts opcrate within a housing incrted with prcssurized hclium gas. This dcsign prcscllts a minimtun safcty hazarcl. An cxample ,of this clcsign is shown in Fig. 2. This is an clcctric motor drivcn licluid oxygen pump unit for use on a space vehicle. 11ie hclium prcssurizccl motor is separated from tlic pumpcd fluid by a heliuln seal and a liquid oxygen scal opcrating in a back-to-back arrangemcnt with a comnlon ovcrboard vent betwccn them. I l l e pump unit is clrivcn by a one horscpowcr clcctric motor o ~ c r a t i n gat 11,000 rpln from a three-phase A.C., 400 IIz, po\vcr s o ~ u c ca t a supply voltage of approximately 40 17.R.hl.S. lin'c-td-line. Thc unit is approximately 12" long, 4" in clian~ctcrand has an intcgral mounting Because of the cryogcnic opcrating environment, elastomcric sealing clcmcnts are not usable. Thercfore,. an all metal wcldcd bello\vs.seal dcsign is cmploycd as shown in Fig. 3. This is a cartridge type seal which is shrink fittcd directly into the aluminum pump housing. Static scaling is providcd by the seal caltriclgc shrink fit in the pump housing and by tlle metallic bellows. A loose or unattached carbon face picce is usccl with this seal. The back side of the carl~onface piece is lapfittcd to the bellows end platc to provide an cffcctive static seal at this point. The'clynamic or opcrating surface of thc carbon face is of the gas face typc consisting of two concentric lands. l l l e inncr land is continuo~a and performs the pl.cssurc scaling function, wl~ilcthe outcr is a scgmcntcd bcaring land \vI~ichscrvcs to rcduce seal facc pressure. Rotation of the carbon face picce is prcvclltcd by slots, in the O.D. of the carbon face, \vhich engage with radial kcys located in the I.D. of the scal cartridge. Compnrcd to a scal having an integral typc calbon face piece, the loose facc piccc typc seal 11s thc following aclvant agcs: . 1. Seal face distortion due to differential thermal contraction of scal matcrinls is minimized. 2. Vibration damping is achievcd by friction bct\vcen the face picce and keys. l'he carbon facc picce opcratcs against a rot:iing ring clampcd axially on the sllaft and statically scalccl to the shaft by aluminum compression gaskcts. V q WrUd Te brbonN=*\ Fig. 2-Liquid Oxygen Pump Will1 klc,liu~~i lncrfcd Motor. Fig. 3-llcliuni . Bellows Seal \Vil!, I kaI %I1 LD. Loorc Carbon Fate. �Scal materials arc as follo\\,s: lcakagc thcn slo\\;ly dccays to so~iicratc bct\vccn tllc Scal cnrtrirlgc including bcllows-71s Staiulcss Stccl -P5N carbon . Carbon f;~ccpiccc Rotating ring -]lard cliro~nc .. . on 440C Stainless Stccl (Anncalcd) l l i c 400 scrics stainless stccl is l~scclin prefercncc to'a 300 scrics bccause of its higher Lllcrnial conductivity. Thc chrome plate tl~ickncssis 0.0015-0.005" as platccl and 0.001" minimun~aflcr lapping. SEAL CHARACTERISTICS Significant scal cliaracteristics are listcd in Table 1. Tlle scal face prcssure of 10 psi consists of 7.5 psi duc to bellows spring pressure and 2.5 psi resulting from the 5596 scal hydraulic overbalance at 50 psig hclium gas opcrating pressure. l l e ma.\imum a l l o ~ a b l cseal friction torque of 10 oz. in. is governed by thc motor torquc remaining after all othcr pump rcquirenlcnts have bccn satisfied. I t & influenced to a large extent by [lie noto or starting currcnt lililit \vhicIi govclns tlie motor torque capability. The maximum pcr~nissiblcseal leakage ratc is 25 stanclard cd)ic inclies pcr minutc (SCIXI) of hclium gas a t a motor cavity prcssurc of approximately 50 psig. Actual scal lcakngc expericnccd during testing is about 2 SCIhl dynamically and 20 SCIhI statically, i.e., with tlic unit non-operating. It is interesting Lo note that the clynamic leakage is much lo~vcrtlian thc static Icakagc. Tlic transition from the dynamic to thc static lcakagc rate takcs place in apPr~si~natcly 10 to 40 seconds a f c r tlic pump has come to rcst following powcr shut-olf. The seal lcakagc incrcascs to the pcak static valuc at which it remains for a pcriod of 30 seconds to 3 ~ninutes.Thc TA~I.E I-IIELIUhI SEAL CIIARACTElXISTICS 1. Scal Operating Spcccl, RPII 2. ,Surface Spccd, ft/rnin. 3. P-V Factor, PSI' Ft/XIin. 4. Opcratiiig h1cdiu111 5. Prcssurc, PSI11 11,000 5 2300 23.600 .I~cliu~n Gas 50-80 -297 6. l'cmpcraturc, "F 7. Scal 1)cflcction (installed), Inch 8. Axial Load, Lbs. 9. Ikcc Arca, in2: Scaling Land Ilcaring Land 10. IIydraulic Ovcrbalancc, 9L 11. kace I'rcssurc (Total), PSI 12. Frictiori Torquc (Xluxir~ium),oz in. 13. Friction 111' 14. Facc I'Iittl~css,I1cli\111l Light Bands 15. . Run-Out (Ilotating I:acc), l'.I.lt., illcli , .040-.050 2.5 0.19 0.14 55 .Id I0 0.10 1-2 0.0005 ski clyna~nicand ~ n a x i ~ n ustatic ~ n rates. Tl~isclinrncteristic is rcpcat~1,leon sticccssivc pump tcsts. l l i c 1 ~ 1 n iunit p opcrating lifc rcquirc~ncntis 10 1iou1.s wllich is nmde up of duty cyclcs each consisting of 20 minutcs of opcratiun follo~vcclby a soak timc of not lcss than 5 minutcs. \\'car ratcs of scal C O I I I ~ ) O I I C I ~ ~cspcriS enccd during tcst i1.e as follows: P5N Carbon Face Piece Chrome Plate on Rotating Ring 0.00005 in./hr 0.000025 in./lir . ' . Ilicsc \%?carrates wcre detcrniincd from three tcsts with a total run timc of approximately 30 hours. The ratcs indicate that tlic scal \vill easily surpass the rcquired life requirement. Numcrous tcsts were pcrformed to dcvelop a scal combination that would meet the rcquired life, leakage, and torquc requirements. Thc tcsts werc conductcdon scvcral scal dcsign variations and on various con~binationsof seal face and mating ring materials. I'ariations in scal facc unit loading werc accomplisllcd by varying tlic bellows spring load, seal facc \vidtIi, and hydraulic overbalance. For tcst purposes, thc scals werc installed in tlie LO2 pun111 prcviously discussed. The tcsts wcre pcrfor~ncdwith the unit subn~crgcdin liquicl oxygcn and with thc motor cavity incrtccl with helium gas at prcssurcs fro111 5 to 130 psig. Tlic tcsts consisted of rcpeatccl opcrating cycles of 20 millutes cluration. Aftcr each operating cycle, tlic electrical power to tlie unit was shut off and the unit was allowed to soak for a minimum of fivc minutes before restart. Static scal lcakage \!.as measurccl bcforc and aftcr every run, ancl dynamic lcakagc during each run. SEAL CONFIGURATIONS TESTED liyo basically dilferent types of bcllows scals wcre tcstcd wit11 the dcsign variations shown in Fig. 4 and Tablc 2. Initial tcsts were pcrformcd with a scal having an-intcgral carbon facc prcss fittcd in an encl plate weldcd . to tlic scal bcllo\\~s.1,atcr tests wcrc donc with a scal having a scparatc unattached floating carbon nose piccc statically scalccl to thc bello111s end plate by a lappcd fit as previously dcscribcd. A bcllowvs scal will] an intcgral car1)on facc ancl no vibration d:ir~lpcrwas tcsicd first. I~sccssivclcakagc, carbon wcar and chipping of thc carbon filcc at thc O.D. ancl premature bclloti7s failurc were cspcricncccl wit11 this scal. Af(er rcmoval fl'om thc pulnp, tlie scal was sul)jcctccl to vibration tcsts at aml)icnt tcnlpcr;~tt~rc and founcl to have a bronc1 nntural rcsonnut frequency rangc, wliicll inclr~clcclthc unit operating spccd. An attcmpt \vas maclc to shift Ll~isrcsona~itfrcqi~cricyband Ly cllnnging the 1ir1rnl)crof bcllows convoli~tionsto 7 and also to I 1 from tlic original 9 convolutions. Thcsc cllruigcs did not �swsrrn IIICCRU VlORlIlGN I r ' W i R TIE w1h~504ILQ r t c a XAL COIFIGUUIIOY SEU W I ~ HmAnNc cuaon nee A m Fig. 4-Seal Configurations Tesfed. prove cffcctive, so a vibration clamper spring \\:as aclclcd to the scal. l'hc vibration danlper consistcd of a flat steel spring encircling the bcllows O.D.al>prosinnatcly at the ~ n i d point of its axial Icngth. The spring applied a distri- TABLE 2-SEAL VIBRATION DAB~PER butcd forcc acting radially inward at the bello\vs 0.11. This was a fingcr typc spring with lhc fingers cslc~iding o~itiilardmncl rcaqling against the 1.11. of the scnl casc. A vibriition tcst of illis seal at aml)icnt teii1pcl;tture indicatcd that this spring was not vcry cffcctive in clunnping out vibration. Close visual examination of the seal rcvcalcd that thcrc 'was vcry littlc physical interaction bctween tlic spring and tlie bcllo\vs. llnis was confirmed by' the prcscnce of very little hystcrcsis in the load versus dcflcction calibration of this scal pc;fornncd a t room tcmpcrature. The scal design \\.as tlnen furthcr moclilicd to include an adclitional spring acting around the O.D.of the seal nose rctaincr plate w l ~ i c lis~ wclclcd to the bcllows. Vibration tests of this seal indicatcd no natural resonhnce in the operating spccd mnge. IIowevcr, operatiorla1 tests of the scal within the unit still rcsultcd in excessive leakage and chipping of the carl~onnose at the facc 0.13. A load versus deflection calibration df this scal exhibited a very widc liystcrcsis. This iilay have camcd hanging up of the carbon nose rclativc to the mating ring with the consequent poor performance. A round wire damper spring of approximately square ,configuration was installed in the scal acting betwcen tlle scal nose retainer O.D.and the scal case I.D. This spring provcd cffcctive in damping the seal when it was subjcctcd to a vibration tcst at rQoln temperature. An ol>cra: tional test of the seal \ililhin the unit shoivcd the leakage. to be within acceptable limits. But addition of the round VIBR;\TIOX AND LEAKAGE CIIAMCTERISTICS RESOS,\NT FREQUEXCY O F I)ELI.O\VS sE.4~-.' (ROOMTE~IPEIIATURE) , Seal with Integral CnrLo~ifice Piece None 173 to 190 Ilz ~ A ~ A N ; S Excessive lcnkage, premature bcllo\i~sfailurc,.rcsonant fi-cqucncy rangc includcs operating spccd of 183 cps. ' Fingcr Spring at XlidPoint of Dcllows O.D. Finger Spiing at Bcllows Slid-Point & at Carbon Face 0.1). Round IVire at Carbon Face 0.D. Inhcrcnt in Dcsign 120 to 205 112 Nonc bctwcen 20-SO0 IIz 560 1Iz 153 to 205 ITz wit11 ,lo torsional lo:1d. Nonc bciwccn 20SO0 IIz with a t&sionnl load of S oz. in. applicd to thc cnr1)on. Excessive Leakage, Insuficicnt Damping Exccssivc L,cakagc, I righ IIystcrcsis Calibration Curve Low Lcakagc and Adcquatc Damping Low 1-cakagc and Adcq~latc Dariq>i~ig. Prictiori damping ariscs Lctwccn thc slots at thc ca~.l,onface 0.11. and thc keys at the scnl casc I.D. �wirc diunpcr spring incrcasccl tlic scal spriiig r:itc and ~ila'dc Under tliis conclit ion, ass~i~ili~lg a tri:uigular I~ydraulicface inslilliution witliin t l ~ cpurnp fi~irlycritical. For a scal . prcssurc distril~utiot~, 50 percent of tlic scal facc arca is load of 2.5 Ibs. the scal liad to LC installed with an inioutside and 50 ycrccnt is i~~sidc thc bcllo\vs mcan cKectial clctlcclioi~of 0.010 to 0.012 inch. Furtl~crirnprovctive dinmctcr. Such a scal is said to have ail ovcrl)alancc mcnt \\'as, tl~cr~forc, coi~sidcredclcsirable. of 50 pcrccnt. %Ilc ;naul cfTectivc or cquivalcnt piston A basically dilfcrcnt type of bcllo\\s scal was tcstcd ncst. diameter is npprosimalcly equal to the average gcomctThis scal employccl a scparatc u~lattacllcdcarbon fitc6 ric diameter of the. bellows. In a scal with a 70 pcrccnt piccc scaled statically to the bcllowvs end plate l?y' a overbalance, 70 percent of tlic scal facc area is outside lapped fit. NO addccl vibrittion damping devices wcrc rcof tlie incan cffectivc diamctcr. In tliis scal, tlie total facc . quircd with this scal. Leakagc and wcar were rcpcatcdly pressurc consists of tlic pressure due to the spring load within acceptable limits. nccausc of a lower scal spring ancl 70 pcrccnt minus 50 percent or 20 pcrccnt of the rate, installed scal dcflcctio~lis approsi~natcly0.040 to scal operating prcssurc. Theorctically, hydraulic scal over0.050 inch for a.seal loacl of 2.5 Ibs. making installation balance should not be necessary, but practically it comnon-critical. This scal is prcsc~ltlybch~gused in production pcnsatcs for scal facc mccl~a~~ical and thermal distortiorls liquid oxygen pumps. At approximately 50 psig helium and manufacturing impcrfcctions in facc flatness. \lrhcn pressure static Icakagc of this seal is fro1113 to 20 SCIhl the scal must operate ovcr a range of prcssurcs, it must and dynamic Icakagc is about 2 SCIM. be hyclraulically ovcrbalanccd suficicntly to keep the leakage within acceptable liillits at the highest pressure. During the devcloplnent tests, the scal bellows spring SEAL FACE PRESSURE loads were variccl froin approsi~llatelyseven to two pounds, . . scal I~yclraulicovcrbalancc from 70 to 46 per cent, and One of the more important seal pararnetcrs is tllc facc seal face arcas.fr01110.10 to 0.39 squarc inches. This reprcssurc. Statically, it is duc to the bcllo~vsspring load suiltcd in seal facc pressures from 40 to 10 psi. and hydraulic unbalancc. During seal operation, hyclrodyThe highcr values of seal spring load and ovcrbalance namic loads ancl therinal dislortions also affect thc facc producccl higher facc prcssurcs. Thc highcr facc prespressurc. sures resulted in low initial lcakage, but presented conThe spring load must bc adequate to enable the seal siclcrable wear ancl friction torque problems, and cvcntufacc to follow, ancl to maintain contact with, the scal ally Iiigll leakagc duc to seal face scoring. At tlic other rotating ring wit11 its inherent out-of-squarcncss. \Vhcn a scal facc load extreme, wvhile wear and friction torque scal is to be operalee1 at a single pressurc only, the spring were lo\\ very little scaling was achieved. At ovcrbalload alonc could bc uscd, \vitll a liydraulically balanced anccs of 50 pcr ccnt or Icss, scal lcakage was very erratic. scal, to achic've acceptable scal performance. Best over-all results wcrc oblainccl with a seal spring In a ' hydraulically balancccl seal tllc hyclraulic forces load of 2.5 Ibs., an ovcrbalance of 55 per ccnt, and a tcnding to load and unload tllc seal face arc equal and resultant seal face pressurc of 10 psi. Seal Icakagc, frictllc facc prcssurc is due to the bcllo\vs spring load only. tion torque and facc wcar wcrc within acceptable limits. 3-PROPEI~TIES O F SEAL h.lATERIt\IS TAI~LE BTU-IN ~IATERIAI. F0 - El' UECU . , TIIEIL\IAL ESP~~SSION EIARDSESS In./ln./FO @ 70°F Goor 1000 261 (Rc 22) 251 (Sc 20) 2200 to 2.100 ~uriistcn - Carbidc (KSO1) (Nickel Ililldcr) .' ' I ' (Bcrrylco 25) P5N (Purc Carbon Co.) G39. (U. S; Crap!\itc Co.) P2003 (Purc Carl)on Co.) Sclcroscopc 100 220 approx. Sclcroscopc SO �TABLE4-SUMMARY OF SEAL TEST RESULTS Wear Rate Seal face herial Rotating Ring hlaterial Intcgral Carbon Face Typc Scul 1 C39 Carbon Chrome on 30.1 2 Chro~ncon 3 4 " 5 P2003 Carbon S P5S Carbon 9 . ' 1 10 11 12 I. . 13 14 Tungsten Diselenide Silver Tefon ' 5 Over Balance Face 'Area Inch2 ' % Run Time Hr Min Xone 3.2 70 0.18 20 4 1 3 Seal Face In./Hr Rota:ing Ring In./Hr Seal Operating Press. psig Leakage Std In.3/Min. Static Dynamic 0.004 (1) 5 ' 01 (2) (1) . 40 0.00015 (2) 40 5 130 0.000S 0.010 ,130 . 36 130 225 130 Light wear, erratic seal, high leakage P2003 carbon is hygroscopic and not suitable for cryogenic use. High leakage 1.8 70 0.18 18 Round Wire Round IVire 2.6 ' 70 0.18 41 1.3 55 0.18 17 2 27 Chrome i n . 440C P2003 , CnrSon P5S Carbon Round \Yire Round Wire Round Wire 2.6 70 0.18 41 4 00 (2) (2) 3.1 70 0.18 44 4 30 (1) (1) 130 54 36 1.8 46 0.10 13 8 05 (2) . 130 320 220 P5S Carbon' Round Wirc Round Wire Round Wire Round Wire 2.0 55. 0.13 22 1 32 0.0043 0.012 130 87 44 . 1.7. . 50 0.11 16 15 47 0.00008 (1) ,130 81 30 3.2 . 50 0.18 18 2 16 0.0014 (2) 5 130 4.9 50 28 1 55 0.0011 0.000008 130 3 33 590 25 15 33 170 100 130 95 270 ,200" 130 ' , . Rzhr~nxs 44 Xone ' ' (2) . . Heavy transfer film. high torque, wear . and leakage I-Iigh leakage. seal lift off 150 4200 %I 1300 35 22 . High wear 30 Very high rotating ring wear, early seal failure . . . Very high wear pnd high,torque C!:romc on 440C ' Aluminum OsiJc LA-2 C!:romiurn 3 Carbide LC-:c . S!iicon Carbide 2 Flat Spring Chrome on 440C Round Wire Chrome on 440C Round Wire 300 Sort material, low mechanical strength, very high leakage Inherent In Design 20 High seal torque, restart impossible I 3 Floating Carbon Face Type Seal >IYlOii Chrome on 1' I 44OC 4 Spring Load' Lbs. 440C P2003 Carbon P5S Carbon 1:. 7 Damper Spring 5 ~ e Total Face Press. psi P5S Carbon Chrome on RECU Tungsten Carbidc , lnheren t In Design . 3.7 3.6 55 .. . .. . 50 - . 0.18 . 0.16, 0.18 31 ' 21 ' 2 I6 50 40 0.0005 0.0003 (2) '. 0.000003 5 330 . . 260 60 Damper spring ma!$tnctioned Good wear and leakage Selective wear caused conical projcctions and high \wear and high leakage Selective wcnr caused conical projections and high wear and high leakage . ' 300 ' , 10 2 Very high wear, erratic and high leakage (rough surfaces) Low mechanical s:rength, dimensional instability. high leakage and wear High torque a: operating pressure Unit started at lowcr pressure High torque and high leakage 2 Leakage was not significantly better than present design Leakage was 5 sci~nfor first four hours, then increased to 20 scim 2 Low wear, low and repeatable Icakagc �I~~ATERIALS TESTED . ' TO~rlioi~iiizc scal distortion and conscilocnt Icaliagc, it is clesirablc to use ~natcrialsl~nvitlg,as ncarly as possil)lc, similar espinsion charactcristics an6 masirnuin hcat . concluctivity. Listccl in Table 3 arc thcrmal expansion, conclactivity, and Iiarclncss for scvcral scal matcrials. Other properti'es sucll as film laying cl~aractcristics,friction and wcai-ing qualitics, must bc dctcnnincd by actual test. Various combinations of carbon facc and mating ring matcrials wcrc tested as summarized in Tablc 4. Initial tests nrcre performcd ising a seal with an intcgral carbon 'nose wit11 a G39 carbon fact nlatcrial operating versus scveral cliflcrent mating ri~lg~natcrials.Carbon film transfer onto thc mating ring was hcavy and lcakagc, wcar, and torque were gcncrally high ancl not acceptable. A 1'2003 grapliitc matcrial with a clieinical salt imprconation opcrati~igvcrsus scvcral mating ring material~ 9 geilerally rcsultccl in high leakagc. Also, it was clisco\lcred in the coursc of thc program that tliis ~natcrialwas hydroscopic and, tlicrcforc, not suitablc for cryogenic use. Moisture attractecl to it rcsultcd in frcczing - bctwcen tlic seals and matigg rings \vithin the pump. Next, a P5N casbon graphite facc material with a chclnical salt impregnation was operatcd against a P5N mating ring. This resulted in high friction, torquc, wear and Icakagc, ancl confirmccl similar rcsults obtainccl with othcr carbon vcrsus casbon combinations in this pump unit. The 1'5N nose piccc was also tested versus flarnc platcd mating rings of aluminum oxiclc ancl chromium carbide. Carbon nose n7car and scal leakage \\we high. This zppcarccl to bc due to sclcctive wcar of thc flamc platetl materials resulting in sharp conical surface projcctions that abraiclecl thc carbon nosc matcrial. Thc P5N was also opcratcd against a silicon cahidc mating ring. \17ear and lcakagc wcre high and sealing \!?as erratic. In an attempt to rcducc seal friction, two non-casbon scal facc matcrials ~ \ ~ e tcstecl. rc One was a lligli tcrnpcratilrc material consisting largely of tungstcn disclcr~icle solicl lubricant ancl the othcr was silvcr-tcflon composition. Both rcsullecl in higli. wcar ancl leakage. The tungsten disclc~liclematerial had Ihc undcsirablc property of bccoming soft, dimensionally unstablc and wearing excessivcly after bcing cxposcd to liquid osygcn. Thc silverteflon material, duc to the fibrous nature of thc embcdclccl tenon particles, \\?asdiificult to polis11 to. the higli dcgrcc of surface finish ncccnary for good scaling.'i\n 'attempt to run-in thc niatcrial did not improve its scaling characteristics. ' . An h.lYl0K ciubon fucc piccc with an antilnony atldilive \\.as tested \rcrsus I~nrdcnccl(Ilc 55) 440c stainlcss slccl. This material producccl a vcry I~cnvytralisfcr filn~ on tlic mating ring. l'llc carl>on fcicc \\.as polislicd. IZcSulL:~utlediagc.wils low but scal friction torclt~c\ifas exccssivcly high. Tests wcrc also. conducted \\lit11 a I'5N carbon scal face opcrating vcrsus ~natingrings of harcl clirolnc platc on bcryllii~mcoppcr and also versus tungstcn carbide witli a nickcl binclcr. In both cascs thc mating rings ancl carbon faccs werc vcry liglltly scorccl across tllc arcas of contact. A vcry light carbon transfcr film was prcscnt on the mating rings. Lcakagc.and \ircar resl~ltswcrc approsimately thc salnc as obtainccl will1 P5N vcrsus harcl chromc on 440c stainlcss stecl. ?lie bcst and most consistc~ltrcsults wcrc obtainccl with a P5N carbon face opcraling versus a mating ring of hard chrome platc on annealed 440c stainlcss stccl. ljrear, leakagc, and friction torque wcrc within acceptable limits and werc repeatable. This material co~nl>iilation has bccn qualified ancl is presently being med in'a liq~iicloxygen punlp on a space veliicle. CONCLUSIONS From the work clcscril~cdhcrein tlic followi~lgcon clusions nrere reached: 1. The best seal co~nbilialionconsistccl of a P5N ear- bon face opcrating vcrsus a rotating ring of Ilarcl chronic platc 011 annealcc1440c stainless steel with a hydra~ilicoverbalailce of 55%, a face pressure of 10 psi ancl a spring load of 2.5 lbs. 2. The over-all pcrformaucc of the floating carbon facc typc scal was superior to tlie intcgral facc type seal. 3. The floating carbon facc seal \rw..found to have thc following advantagcs: a. Scal facc distortion cluc to the differential contraction bctwecn the carbon face ancl thc stainless stccl Lcllo\\~send platc was eliminated. b. Aclcquatc axial ancl torsional. .vil>ration damping - was achicvcd by friction between the car1)on . facc and the seal stationary keys with no conse. qucnt incrcasc in bcllows spring rate. c. Rcfinisliing and rcplacclncnt of tllc scal ca'rbon facc coulcl be donc without removal of the scal from thc pump housing. . d. Thc Iappccl bcllo~\~s encl plate dicl not rcqriirc rcfinisliing during the life of tllc unit. . ' . � 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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_000054 Title A name given to the resource "A Helium Face Seal Application In a Liquid Oxygen Pump." Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. FICFS Preprint 24 Description An account of the resource Presented at the Fourth International Conference on Fluid Sealing held in conjunction with the 24th annual meeting in Philadelphia, May 5-9, 1969. Creator An entity primarily responsible for making the resource Cieslik, Walter American Society of Lubrication Engineers Date A point or period of time associated with an event in the lifecycle of the resource 1969-05-09 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) Liquid oxygen Pump seals Sealing 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 31, Folder 32 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. FICFS Preprints 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_000051_000074 https://digitalprojects.uah.edu/files/original/20/1139/spc_stnv_000055.pdf a3ffc30c2c9f010d1c077286206b49e3 PDF Text Text A Hybrid Simulation for Dynamic Verif icatio of Saturn Guidance and Control Subsystem: �IBM NO. 68-U6O-0013 A HYBRID SIMULATION FOR DYNAMIC VERIFICATION O F SATURN GUIDANCE AND CONTROL SUBSYSTEMS . Ronald T Patray May 15, 1968 International Business Machines Corporation Federal Systems Division Space Systems Center Huntsville, Alabama �A HYBRID SIMULATION FOR DYNAMIC VERIFICATION O F SATURN GUIDANCE AND CONTROL SUBSYSTEMS Ronald T. Patray International Business Machines Corporation Federal Systems Division Space Systems Center Huntsville , Alabama I. INTRODUCTION This paper presents a discussion of a hybrid simulation used to dynamically verify the Saturn Guidance and Control subsystems. First, the Saturn vehicle is briefly described to provide background information. The Instrument Unit (IU) is considered in more detail to give a proper setting f o r the Guidance and Flight Control (G and FC) discussion that follows. After a brief description of the actual G and FC System operation, simulation models of the G and FC components a r e considered in detail. This is followed by a discussion of the model assignment to a particular computer (digital o r analog) and justification f o r making that assignment. Finally, results of the A S - 2 0 4 / ~ ~ 1 hybrid simulation studies a r e briefly considered with mention of the actual flight data. 1 11. SATURN VEHICLE DESCRIPTION The Saturn IB, which has two propulsive stages (Slide I ) , is serving as a launch vehicle f o r the Apollo spacecraft earth orbital flight tests. These flights simulate certain studies of the lunar landing mission and provide flight 1 Some of the material in this paper is based on notes f r o m an IBM conference presentation entitled, "Digital Computer Program for Support of Hybrid Computer Simulation of Saturn Launch Vehicle, " by E. W. Snyder. �t e s t s for the spacecraft and the S-IVB/IU Stage. Each Saturn IB has a payload consisting of some combination of a Lunar Module (LM), Service Module (SM), Command Module (CM), and Launch Escape System (LES). The Saturn V, which has three stages (Slide I ) , is the launch vehicle f o r the actual lunar landing missions. For these missions the Saturn V will c a r r y a payload consisting of an LM, SM, CM, and LES. 111. INSTRUMENT UNIT The major purpose of the Instrument Unit (IU) shown in Slide 2 is to provide the Saturn vehicle with a centralized astrionics package for guidance, control, sequencing, and telemetry during boost and earth orbit, and through lunar trajectory insertion. The IU subsystems (Slide 3 ) include the Structural Portion, Guidance, Flight Control, Environmental, Instrumentation, and Electrical. A. Guidance and Flight Control Subsvstems Slide 4 lists the major components of the Guidance and Flight Control Subsystems. Included a r e the Launch Vehicle Digital Computer (LVDC), the Flight Control Computer (FCC), the ST-124 Inertial Platform, and the control accelerometer and rate gyro /control signal processor. Slide 5 shows a rough sketch depicting the closed loop operation of the Guidance and Flight Control Subsystems. Sensors on the inertial platform meas u r e the angles ( 8 ) between the inertial and body reference f r a m e s and changes in velocity along each inertial axis. These signals a r e transmitted to the LVDC-LVDA where the velocities a r e used in navigation and in computing the commanded gimbal angles (x). The actual platform gimbal angles ( 8 ) a r e differenced with the x's to give attitude e r r o r signals ($1 in the inertial platform frame. These $ 's a r e transformed to result in attitude e r r o r signals ( A qb ) in the body frame, which a r e fed to the FCC where they a r e filtered and summed with the filtered rate gyro signals to give engine actuator commands (4).The ,f3 signals drive the actuators and thus change the thrust vector orientation which in turn changes the vehicle attitude. (6) IV. DYNAMIC VERIFICATION OF THE GUIDANCE AND CONTROL SYSTEM Filters in the FCC and parameters in the LVDC flight program a r e designed to give satisfactory stability margins while maintaining good vehicle �response to guidance commands. These designs a r e determined by using linearized models and linear stability analysis techniques at a few frozen points in time. While this method of design has proved, thus f a r , to be reliable, it does not consider the effects of nonlinearities in the guidance system, nor does it consider vehicle dynamics continuously throughout boost flight. Thus, a means of dynamically checking the FCC filter design and LVDC flight program in a total system configuration under flight conditions, over all times of vehicle boost flight, was needed to ensure the nonexistence of adverse dynamic effects on the vehicle, the astronauts, and the guidance accuracy. It was decided that a system would be devised in which, except for the LVDC flight program, all components significantly affecting the vehicle dynamics would be simulated. For this task, a six degree-of -f reedom real time hybrid simulation with LVDC/LVDA flight hardware in the loop was chosen that would fully exercise the flight program and check its dynamic effects on the vehicle throughout simulated boost flight, and at the same time check the FCC filter design for vehicle stability and response. V. HYBRID SIMULATION Slide 6 shows a simplified G & FC loop for pitch and yaw. The LVDC and LVDA a r e flight-type hardware, while the Flight Control Computer, Engine Actuator, Vehicle Dynamics, Rate Gyro, Inertial Platform Assembly, and Propellant Utilization System (PU) a r e simulated on the hybrid system. Each component that significantly contributes to vehicle dynamics is described below, followed by a description of the simulation model of each component. A. Launch Vehicle Digital Computer (LVDC) 1. Actual LVDC Slide 7 depicts the Saturn V flight computer (LVDC) tasks by phase: Phase I includes the time of f i r s t stage boost. During this phase the vehicle is moving through the dense portion of the atmosphere where high aerodynamic pressure occurs. To avoid excessive structural loads caused by guidance maneuvers, no guidance constraints a r e applied. An open loop guidance scheme in the form of a time tilt program is used. Phase I1 includes the second stage boost time. The flight program during this phase uses a path adaptive guidance scheme called Iterative �Guidance Mode (IGM) in which guidance is a function of space-fixed position (F ) and velocity (G ) , ~ / m and time. This adaptive guidance scheme seeks to attain predetermined space -fixed position and velocity vectors with the consumption of a minimum amount of propellant. Phase I11 includes the f i r s t burn time of third stage boost and orbital time. IGM guidance is used during the boost portion of this phase. Phase IV includes the second burn time of third stage boost. IGM guidance is also used during this phase. Phase V includes all mission time after $-NB/IU Apollo Spacecraft separation. The LVDC/LVDA has a s inputs inertial platform gimbal angles, measured changes in velocity along each platform axis, and flight sequencing discretes. The LVDC/LVDA outputs a r e attitude-error steering commands and flight sequencing discretes. Since an actual flight type LVDC/LVDA is used in the simulation, no LVDC/LVDA model was devised. B. ST- 124 Inertial Platform Assemblv 1. Actual Platform The Inertial Platform Assembly (Slide 6) is the main sensor for guidance. At guidance reference release, which occurs a few seconds before liftoff, the platform becomes inertial (space-fixed). A resolver attached to each platform surface measures the gimbal angle ( 8 ) between the surface and vehicle axis. These resolver outputs a r e read by the LVDC flight program every 40 milliseconds. Integrating accelerometers, mounted along each axis of the platform, sense changes in measured velocities (AX,, A * ~ , A 2,) in increments of .05 m/sec. Signals representing these velocity changes automatically increment o r decrement velocity counters in the LVDA. These counters a r e read periodically by the LVDC flight program. �2. Platform Simulation Model Platform gimbal angles ( 0 ) a r e simulated by first transforming the simulated body r a t e s (Slide 6) into the inertial coordinate frame, and then integrating the resulting gimbal angle r a t e s (8). Gimbal angles a r e computed and transmitted to the LVDA at a 40-millisecond rate. (4) The platform integrating accelerometers a r e simulated in two ways: During f i r s t stage simulation, vehicle thrust is obtained through a table lookup scheme of thrust versus vehicle altitude. Thrust is then used with remaining vehicle m a s s (m,), which is computed, to obtain total vehicle acceleration . engine angles (F/mV). This acceleration is resolved through the simulated ( P ) to result in body acceleration components gB,yB, ZB). which in turn a r e transformed via the platform gimbal angles (0) into inertial platform acceleration components Wm, Y,, z,). These accelerations a r e then used to compute changes in measured platform velocity components (AX,, A A i m ) which would normally be sensed by the platform integrating accelerometers. The measured velocity changes a r e computed and transmitted through special interface equipment to the LVDA every 40 milliseconds. During the second and third stage simulation, vehicle thrust is obtained through a table lookup scheme of thrust versus Propellant Utilization System (PU) valve position, which is the output of the PU System simulation model. After vehicle thrust has been obtained, changes in the platformmeasured velocities (AX,, A , A z,) a r e derived in the same manner as in the f i r s t stage simulation. . C. Flight Control Computer (FCC) 1. Actual FCC The primary functions of the FCC a r e to provide command signals (PC) to the engine actuators and to ensure adequate vehicle stability by compensating the guidance and control loop with proper attitude e r r o r and r a t e filters. These f i l t e r s a r e implemented with passive elements. The FCC shown in Slide 6 has as inputs attitude-error steering commands ( A4's) from the LVDA and body r a t e s (4's) f r o m the body rate gyros. These inputs, when filtered in the FCC and summed, result in actuator commands (PC's)which move the engine actuator, and thus the thrust vector, to cause changes in vehicle dynamics. �2. FCC Simulation Model Slide 8 shows a simplified block diagram of the pitch control loop, including sloshing and bending models for a single engine stage. The simulated attitude and attitude rate filters a r e implemented with passive elements a s in the actual FCC. The control gains a. and a 1 a r e changed during actual and simulated flight in discrete steps to offset changes in the control moment of inertia. D. Engine Actuators 1. Actual Actuators The Saturn engine actuators, while differing in type from stage-to-stage, a r e all highly nonlinear with rate and position limits. 2 . Actuator Simulation Models Linear approximations of the engine actuators a r e used in the hybrid simulation. The transfer functions for these actuator models a r e of order three o r four, depending on the boost stage. In using these linear approximations, small engine angles (0 to 1 3 degrees) a r e assumed. Simplified nonlinear actuator models a r e presently being developed to handle more severe cases of engine movement. E. Bodv Bending Model The effects of one mode of body bending, caused by forces due to engine position ( p ) and acceleration a r e simulated in the pitch plane (Slide 8) by a second order linear model. The effects of bending (dB and A O B ) a r e sensed by the rate gyros and platform gimbals and therefore affect the guidance and control loop. (B), F. Moment Equation Model Motion of the rigid body is described by simple rotational mechanics: is equal to a moment coefficient C2 times Sin P , The attitude acceleration (4) where C2 is total thrust times the moment a r m (distance from engine gimbal to center of gravity) divided by the moment of inertia. The Hybrid Simulation �computes C2 on line from its component parts. The small angle approximation Sin P = P (radians) is used. G. Propellant Slosh Model Propellant Sloshing (LOX and LH2) effects on the vehicle attitude acceleration in the pitch plane and the Propellant Utilization System Valve Control a r e included in the simulation of the second and third stages. The inputs that cause major sloshing action in the pitch plane a r e the vehicle translational acceleration due to thrust in the pitch plane and vehicle attitude acceleration in the pitch plane. These inputs cause the propellants to move against the tank walls which, in turn, causes attitude acceleration to be induced by two factors: the force of the propellant sloshing m a s s acting on tank walls through a moment a r m about the center of gravity, and the sloshing m a s s being displaced from the center line of the vehicle acting through a radial moment a r m about the center of gravity. The model used to simulate the sloshing effect during second and third stages consists of two linear second-order directly coupled differential equations with m a s s varying coefficients. These differential equations describe the radial motion of the slosh m a s s (LOX and LH2) in the pitch plane. H. S-I1 and S-TVB Propellant Utilization Systems (PU) 1. Actual PU System One function of the PU system is to control the LOX and LH2 flow to the thrust chamber in such a manner that depletion of LH2 and LOX will occur simultaneously. Remaining LOX and LH2 a r e measured by capacitance-type probes in each tank. The signal from each probe is gain adjusted so that when the two signals a r e differenced, a resulting signal will drive the PU valve position servo to give a desired EMR. Sloshing (LH2 and LOX) causes the signals representing remaining propellant to vary, which in turn tends to cause the PU valve position, EMR, and thrust to vary at the sloshing (LOX and L H ~ frequencies. ) Since a varying thrust has ill effects on the guidance system, the PU valve control signal is filtered so that sloshing frequencies a r e highly attenuated in the resulting valve control signal. �2. PU Simulation Models Slide 9 depicts a S-IVB PU system model obtained from a MSFC Guidanct This is basically the model used in the Hybrid Dynamics Design Document. Simulation. The S-I1 model is essentially the same except for a different sloshing filter. In the PU model, remaining LH2 and LOX masses at any point in time a r e determined by integrating the total flow r a t e s and subtracting these f r o m the initial LH2 and LOX masses. Slide 9 also shows how the effects of propellant sloshing on the PU system are implemented. VI. COMPUTING TASK ASSIGNMENTS In assigning computing tasks several factors were considered that seemed to fall into two general categories as shown in Slide 10 and as follows: A. Application Orientation 1. Frequency Content In the Hybrid Simulation, models with high frequency content were simulated on the analog computer, which has a bandwidth of several kH. The f r e quency response of digital computers depends on both the algorithms used to represent a given model and the solution r a t e of the algorithms. In general, f o r good accuracy, the solution rate must be several times the highest significant frequency . 2. Precision Requirements Where high precision was required the digital computer was used, because parameter value can be maintained and expressed in much smaller increments. An analog signal value is usually expressed in no more than four o r five decimal places. 3 . System Composition In the r e a l world the LVDC is digital while the FCC is analog. Precision in a simulation need not be greater than it is in the actual system. This was a consideration in assigning the FCC simulation task. MSFC Memo #R-ASTR-F-66-45, Phase I1 Guidance Dynamics Design Document f o r AS-207, 8 March 1966. �Flight Hardware Interface 4. The output of the hardware (LVDC-LVDA) consists of attitude steering commands ( A 4 ) which a r e analog signals. The inputs to the flight hardware a r e platform velocity counts, which a r e discrete in nature, and platform gimbal angles, which a r e analog signals. 5. Type of System One important consideration in some of the model assignments was the time varying coefficients in the differential equations representing the models. The analog computer readily lends itself to modeling the differential equation while the digital computer easily handles time varying coefficients. The models were therefore simulated on a hybrid system using multiplying DAC's to combine the coefficients with the dependent variable and i t s derivatives. B . Simulation Hardware 1. Memory Size and Speed of Digital Computers While memory size can be important, it was not a consideration in this simulation. The speed of the digital computer was a consideration, in that i t determined how fast the various loops in the program could be processed and, therefore, what the solution r a t e s f o r the various model algorithms would be. 2. Equipment Configuration of the Analog Computer Task assignment is largely dependent on the types and number of elements on the analog computer. In this simulation the analog computer specifications were based on the already determined task assignments listed below; thus the elements were not really a consideration in this case. 3 . Linkage Characteristics The bit configuration (word length), conversion rates, and number of channels @/A, A/D, D/D) were important considerations in assigning c e r tain tasks. �4. Communication Channel Count and Precision Versus Consolidation of Small Computing Task on One Machine When implemented all-analog o r all-digital by the use of special techniques, a model which is best suited to hybrid application will use fewer conversion channels but may lose precision and accuracy. C . Assignments Slide 11 shows a list of the actual computing task assignments. a r e as follows: These Analog - - - Flight Control Computer Control Actuator Moment Equations Propellant Slosh Model Body Bending Model Propellant Utilization Control System Digital - - D. Inertial Platform Time and Mass Varying Function Generation Navigation Model Telemetry Ground Station Control of Automated Setup and Checkout of Analog Computer Propellant Utilization System Valve and Pump Model Data Reduction and Preparation Hybrid Simulation Tie -In Tie-in of the total hybrid simulation is presented by tracing system signal flow in the S-IVB stage pitch plane as follows. The analog computer receives the attitude steering command ( A 4 ) from the LVDC-LVDA. The P control computer model filters this signal and sums it with the filtered body attitude rate ($p) generated by the vehicle dynamics model. The resulting signal (PCP)is fed to the actuator model which generates the simulated engine �(9). angle This is then multiplied by the control moment coefficient (CZp), provided by a digital model, to result in a rigid body pitch attitude acceleration due to engine thrust. This component is summed with the attitude acceleration arising from propellant sloshing to give total attitude acceleration ($p). This $p is integrated once to result in rigid body attitude rate (dp)that is summed with attitude rate due to body bending ) to give a simulated body rate gyro bp output (bgp). The propellant sloshing model has a s inputs, engine angle ( 6 ) P and attitude acceleration (Pp), while the bending model is forced by engine angle (Pp) and engine rotational acceleration (b ). P (6 The propellant utilization (PU) system is forced by remaining LOX and LH2 m a s s which a r e computed on a digital computer. The PU system is perturbed by radial positions of propellant sloshing m a s s e s (LOX and LH2). The output of the PU system is valve position (av). A digital computer receives as inputs from the analog models the attitude rate (dgp), the engine angle (Pp), and the PU valve position (8,). The $gp is resolved into the inertial platform frame to result in a platform gimbal angle rate ( 6 p), which is integrated to give the gimbal angle (0 p). The PU valve position (6 ). is used in a table look scheme of total thrust ( F ) versus 6, to obtain F, which is then divided by remaining vehicle m a s s (mv) to result in total vehicle acceleration (F/mv). Vehicle m a s s is computed by subtracting integrated propellant flow rates from initial vehicle mass. Components of body m ~ the engine gimbal angles. acceleration a r e obtained by resolving ~ / through These components a r e in turn resolved through the inertial platform gimbal angles to result in inertial platform accelerations components, which a r e used to compute changes in measured platform velocities. These changes in velocities and the simulated inertial platform gimbal angles a r e transmitted via special interface equipment to the LVDC -LVDA where the accumulated velocity changes a r e used for navigation and computation of commanded platform gimbal angles (x). These x ' s when differenced with the actual platform gimbal angles result in attitude e r r o r signals (+) which a r e transformed into the body frame to result in attitude steering commands (A$). These A $ 's a r e then transmitted t o the analog computer to close the guidance and control loop. �VII. RESULTS In concluding this presentation, some of the results from the AS-204 L M / ~Hybrid Simulation studies will be discussed. Slides 12 and 13 show s t r i p recordings of some of the simulated vehicle and systems dynamics f o r a nominal case. From left to right on Slide 12 a r e the pitch attitude steering command (A$*), pitch engine angles (Bp (1,2) and ($ (3,4), pitch body r a t e (&p), yaw attitude steering command ( ~y), 4 yaw engine angles (fly (2,3) and (Py (1,4), and yaw body rate (&y). Magnitudes of these parameters and significant flight events a r e indicated. Slide 13 shows Cfrom left to right) the roll attitude command @OR), body roll r a t e (eR), radial displacement of the fuel and LOX sloshing m a s s (Z and ZL), remaining LOX and fuel weight (WL and WF), the change in engine mixture ratio (AEMR), and P U valve position (aV). These simulation results compare favorably with actual flight data. All significant differences a r e attributable to uncertainties in certain initial conditions. While results from the hybrid simulation have been good, certain anomalies in actual Saturn flights have revealed a need f o r studies that were not previously considered. These studies can be handled by making slight modifications to certain simulation models. VIII. SUMMARY A hybrid simulation is used to dynamically verify the guidance and cont r o l subsystems of Uprated Saturn I and Saturn V vehicles. This is done by simulating pertinent vehicle dynamics in a closed guidance and flight control loop with flight-type (LVDC and LVDA) hardware in the loop. In conjunction with equipment constraints, the computational complexity imposed by the requirements for high precision solutions of the guidance and navigation equ: throughout the total boost portion of the mission and f o r accurate solution of nonlinear differential equations with variable coefficients and high frequenc: content led to the choice of a hybrid system for this application. This simr has already proven to be a valuable tool fop preflight prediction of vehicle/ system dynamic performance and i t s effects on guidance accuracy. With further developments, it will also be useful for detailed evaluation of dyna. behavior under extreme combinations of off -nominal situations. �LAUNCH ESCAPE SYSTEM LAUNCH ESCAPE SYSTEM COMMAND MODULE SERVICE MODULE COMMAND MODULE SERVICE MODULE ADAPTER S-IVBSTAGE LUNAR LE q+- - - I 1 J -2 ENGINE INSTRUMENT S-IVB STAGE 5-IVB AFT INTERSTAGE --I I . 1 J-2 ENGINE S -IC STAGE S-IB STAGE 8 H-1 ENGINES APOLLO-SATURN V VEHICLE UPRATED SATURN I VEHICLE Slide 1 �SATURN INSTRUMENT UNIT Slide 2 �Instrument Unit Subsystems e STRUC'TURAL PORTION e GU IDANCE AND CONTROL e ENV I RONMENTAL CONTROL e MEAS UR ING AND TELEMETRY e RAD 10 FREQUENCY e ELECTR ICAL Slide 3 15 �Guidance and Control Subsystem o LAUNCH VEHICLE DIGITAL COMPUTER (LVDC) o LAUNCH VEHICLE DATA ADAPTER (LVDA) o FLIGHT CONTROL COMPUTER (FCC o ST 124 INERTIAL PLATFORM a BODY RATE GYROS Slide 4 16 �Simplified Saturn V Slide 5 17 �Guidance and Control System - .. .. .. Xm ' Ym ' Zm lnertial Platform Assernbl y >P ------------------- B~ - I I I -% JJ I I inertial Velocities (~11,A V , OW) Inertial Platform Gimbal Angles ( 0 ) 1 __c LVDC -1 -1 LVDA n v ~ b Flight Control Computer @CP Engine Actuator Vehicle . -@% Dynamics I A A ' -vT' ' PU System Rate Gyro --------- Slide 6 18 I I I �FLIGHT COMPUTER TASKS B Y PHASE 185 Kilometers (100 Naut. Miles I SATURN V I APOLLO PHASE t Slide 7 19 I TASK I �Control Loop Slide 8 �Propellant Utilization System z~ ,c o s e F SLOSH INITIAL L H 2 ~ t ~LH2~ ~ ~ -- . 8wF a z ~ FROM SLOSH MODEL NOMINAL L H ~ FLOW RATE I LH2 BRIDGE SERVO I 'PU K~ ( d s 2 cs5 t 6s4 - - bS ' - es3 fs2 g s POSlTlONER VALVE AA\P FORWARD SHAPING -1 VALVE : K~ I GEARS & POT REDBACK I LOX BRIDGE SERVO - - 2C~"~ , 1 1\ .s K~~ z~ FROM SLOSH MODEL - ' coseL . IINITIAL aW~ aZL LOX SLOSH WEIGHT Slide 9 LOX WEIGHT I N O M l NAL LOX FLOW RATE Lox TO THRUST MODEL �Factors Related to Computing Task Assignments in Hybrid Simulation 1. APPLICATION a. b. c. d. e. 2. FREQUENCY CONTENT PREC IS ION REQU I REMENTS SYSTEM COMPOS IT1ON FLIGHTEQUIPMENT INTERFACE TYPE OF SYSTEM COMPUTER HARDWARE a. b. c. d. MEMORY S I Z E AND SPEED OF D I G l T A L MEMBER EQU I PMENT CONFIGURATION OF ANALOG MEMBER LINKAGE CHARACTER1 STICS COMMUNICATION CHANNEL COUNT AND PRECISION vS CONSOLIDATION OF SMALL COMPUTING TASK ON ONE MACHINE Slide 10 22 �Computing Task Assignment ANALOG a a a a a a FLIGHT CONTROL COMPUTER CONTROL ACTUATOR MOMENT EQUATIONS PROPELLANT SLOSH MODEL BODYBENDINGMODEL PROPELLANT UTl L l ZATl ON CONTROL SYSTEM DIGITAL a a a a a 0 0 lNERTl AL PLATFORM TIME ANDIOR MASS VARYING FUNCTIONS GENERATION NAVIGATION MODEL TELEMETRY GROUND STATION CONTROL OF AUTOMATED SET-UP AND CHECKOUT OF ANALOG PROPELLANT UTILIZATION SYSTEM VALVE AND PUMP MODELS DATA REDUCTION AND PREPARATION Slide 11 23 �Slide 12 �Slide 13 �4 Federal Systems Division, Space Systems Center, ~untsville,Alabama � 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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_000055 Title A name given to the resource "A Hybrid Simulation for Dynamic Verification of Saturn Guidance and Control Subsystems." Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. IBM No. 68-U60-0013 Description An account of the resource This paper presents a discussion of a hybrid simulation used to dynamically verify the Saturn Guidance and Control subsystems. First, the Saturn vehicle is briefly described to provide background information. The Instrument Unit (IU) is considered in more detail to give a proper setting for the Guidance and Flight Control (G and FC) discussion that follows. After a brief description of the actual G and FC System operation, simulation models of the G and FC components are considered in detail. This is followed by a discussion of the model assignment to a particular computer (digital or analog) and justification for making that assignment. Finally, results of the AS-204/LM1 hybrid simulation studies are briefly considered with mention of the actual flight data. Creator An entity primarily responsible for making the resource Patray, Ronald T. International Business Machines Corporation. Federal Systems Division Date A point or period of time associated with an event in the lifecycle of the resource 1965-07 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) Project Apollo (U.S.) Saturn launch vehicles Apollo spacecraft Spacecraft guidance Spacecraft control Computerized simulation Dynamic tests 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 26, Folder 34 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_000051_000074 https://digitalprojects.uah.edu/files/original/20/1148/spc_stnv_000064.pdf ad809db4108abf8a07cf50bfc0872e0d PDF Text Text With the 1970 lunar touchdown already in its sights, NASA's Office of Manned Space Flight seeks to make the United States pre-eminent in space. A Nation Goes to /r&(/iS ".Note/ is the kime to take longer strides-time for a p e a t new American enterprise-tirrle,fir this nation to take a clearly leading role in space achieuernent a~hichin many zoaj)s may hold the key to our,future on earth. I belieup thal this nation should comrnit itself to achieving the goal, befire lhis decade is out, of landing a man on the moon and returning him safely to earth. . . . It will not be one man going to the moon . . . it will be an entire nation." -President John F. Kennedy ive years ago the United States took its first tiny steps toward the moon when Commander Alan Shepard became the first American to be rocketed into space. And the entire nation-indeed the whole world-witnessed his flight, sharing in the tension and the triumph. Today, at the halfway point in the tenyear program to land a man on the moon and return him to earth safely, the United States manned space program has both lengthened and quickened its stride. And the distance from the earth to the moon doesn't seem quite that far anymore. In developing the elements and capabilities for this decade's manned lunar landing, NASA has marshalled F I I the men and machines that will make it possible to undertake a wide range of space missions beyond the initial moon touchdown. Indeed, as Dr. George Mueller comments, "manned lunar flight serves as the focal-point of a program whose principal goal is to give the United States world leadership in all elements of space activity. The Gemini and Apollo-Saturn programs are equipping this nation with the ability to carry men and instruments into hitherto inaccessible regions of space for hitherto unachievable periods of time." Dr. George E. Mueller Associate Administrator Office of Manned Space Flight ��Dr. Mueller, Associate Administrator for NASA's Office of Manned Space Flight, bases his appraisal on the remarkable progress that has been made in the tri-lateral manned flight program-Projects Mercury, Gemini and Apollo. Together the three constitute the greatest single engineering enterprise in this nation's history. The manned space flight program is carried out by some 300,000 men and women. They work in NASA'sWashington, D.C. office, at three field centers-the John F. Kennedy Space Center in Florida; the Manned Spacecraft Center near Houston, Texas, and the George C. Marshall Space Flight Center at Huntsville, Alabama-and a t some 20,000 industrial plants in every part of the country. Dr. Mueller directs this competent crew by means of a geographically dispersed program office structure which penetrates directly through the functional organizations of the field centers and the prime contractors, to the subcontractors and the vendors. It has been said that Dr. Mueller's techniques of managing so vast a research and development program may, in the long run, prove to be one of the most valuable assets derived from the program. The first phase of the tri-lateral manned space flight program, Project Mercury, set the stage for the sophisticated space maneuvers of today and tomorrow. Using experimental oneman vehicles, Project Mercury put the first Americans into space and laid a solid foundation for the technology of future manned space flights. It demonstrated the effects of space on man, and proved that men could increase the reliability of spacecraft controls. NASA logged its first manned space flight success on May 5,1961, the day Astronaut Shepard rode his Freedom 7 space capsule on a 19-minute suborbital mission, 116 miles high into space. Another Mercury milestone was achieved the following February. Astronaut John Glenn became the first American in orbit, completing three global circuits. The following spring Gordon Cooper completed a 22-orbit mission of 34 and one-half hours, triumphantly ringing down the �curtain on Project Mercury. Dr. Mueller was a witness to, rather than a participant in, NASA's manned flight program at the time of the Mercury space spectaculars, although he was deeply involved in other aspects of aerospace technology. During the five years before he joined NASA in 1963, he was associated with Space Technology Laboratories, Inc., serving successively as director of the electronics labs, program director of the "Able" space program, vice president of space systems management, and finally vice president for research and development. I n this last position, he had overall responsibility for the technical operations of the company. While at STL, Dr. Mueller headed the design, development and testing efforts of the systems and components for Atlas, Titan, Minuteman and Thor ballistic missiles. He also played a major role in the development of Pioneer I, the United States' first successful space probe, and had overall responsibility for several other space projects, including Explorer VI and Pioneer v, and for the establishment of the Air Force satellite track- Gemini Twin Ed White maneuvers 120 miles above the Pacific Ocean, connected to Gemini 4 spacecraft by an umbilical cord. Extravehicular activity, operational term for walking ing network. in space, is a basic technique required for manned space flight capability. Mercury's Dividends Dr. Mueller adds thisfootnote to the story on the path to the moon, and forged Mercury which had j u t con- ahead with the second phase, Project cluded when he became Associate Adminis- Gemini. Named for the twin-star constellatratorfor the Ofice of Manned Space Flight: "Originally, NASA assigned only two broad tion of Castor and Pollux, Project Gemini called for a two-man spacemission objectives to Project Mercury-jrst, to investigate man's ability to survive and craft system to conduct orbital flights perform in the space environment; and sec- around the earth for up to two weeks' ond, to develop the basic space technology duration. Twelve flights were schedand hardware for manned space JEight pro- uled for the Gemini series-ten of prime grams to come. But the dividends Mercuy them manned. One of NASA's paid went beyond those basic goals. Thty objectives was to determine man's include the development of a NASA manage- performance and behavior during ment system to carryforward more advanced prolonged orbital flights, including manned spacejight ventures; exploration of his ability to pilot and control his the fundamentals of spacecra) re-enty; spacecraft. Other mission objectives raising a family of launch vehiclesfrom ex- were orbital rendezvous; docking or isting rockets that led to new booster designs; joining two spacecraft, and maneuverexpansion of the aerospace industry through ing the joined spacecraft as one unit; astronaut activity outside an orbiting NASA contracts; setting up an earthgirdling tracking system, and training a spaceship, and a series of scientific excadre of astronauts for future space explora- periments. Dr. Mueller and his capable tion programs." Small wonder, then, that NASA was manned space flight crew are justifiencouraged by this successful first step ably proud of the stand-out achieve- of Project ments of the Gemini program and the early successes of Apollo-Saturnachievements which can only be described as spectacular in light of the stepped-up pace of the United States manned space flight schedule. In the spring of 1964 the first unmanned test flight of the Gemini-Titan 11 space vehicle was flown. By spring of this year Gemini astronauts had logged more than 1,300 man-hours in space, and traveled some 11 million milesthat's almost fifty times the distance from the earth to the moon. Other mission objectives have been fulfilled. Last year, during the third revolution of an extended earth orbital flight, Gemini 4 Astronauts James McDivitt and Ed White carried out the first extravehicular activity in the manned space flight program. White left the spacecraft to walk in space, becoming a human satellite orbiting the earth at an altitude of 120 miles. Command pilot McDivitt remained �Mueller, is that in every case, the men returned in excellent physical and mental health. From the medical point of view the jights show that well-trained men can live and work in space for extended periods of time, and the condition of weightlessness does not appear to cause any serious afterefects. 7 h e astronauts' state of health is measured continuously, bbefoejight, during j i g h t and after their return. The overall appraisal of NASA'smedical team is that jights lasting a month or more are feasible. I Talented Management Another noteworthy aspect of the Gemini program is the talented management Dr. Mueller gives it. A little more than a year ago, the program was behind sdhedule, and there was.. ... "rave concern about the possibility of cost overruns. "We instituted a new kind of contract administration," Dr. Mueller remarked, "one in which the profit of the Gemini program contractors is ,tied to their total perform- Astronaut David Scott's camera captures orbiting Agena target docking vehicle as Gemini 8 spacecraft hovers about 190 feet away. Michael Collins and John Young maneuvered near this same rocket during the Gemini 10 mission in July. a t the controls with the difficult task of keeping the spacecraft in a stable attitude so that White would have a constant and dependable point of reference to gauge his movements outside the capsule. Orbital rendezvous was another mission objective. Dr. Mueller recalled the events which led to its achievement: "Within hours after Tom Love11 and Ed Borman took off on their twoweek Gemini 7 flight, preparations began for launching their rendezvous ship. Gemini 6 lifted off eleven days later, with Wally Schirra and Tom Stafford aboard. For five hours Schirra a n d Stafford carried out a complicated series of maneuvers. Then, 185 miles above the Pacific, they rendezvoused with Gemini 7. Despite their speeds of 17,000 mile a n hour, Schirra was able to guide his spacecraft to within one foot of the other. I might add that he was aided by some very fine guidance and con- trol equipment." Docking in space was added to the plus side of the mission objective ledger in March of this year after Astronauts Neil Armstrong and David Scott docked their Gemini 8 spacecraft with an unmanned Agena target vehicle. Among the most remarkable Gemini space successes was the Gemini 10 flight in late July. During that record-setting three days, astronauts Michael Collins and John Young chased and linked up with a fuel supply Agena rocket and spent nearly 39 hours linked with the other statellite; fired the rocket engine of the captured Agena for the first manned launching at orbital altitudes; soared to an orbit of nearly 475 miles-deeper into space than man has ever gone; opened the hatch of their capsule to the space environment three times; maneuvered near the orbiting Agena 8 rocket and retrieved a package from it, and accomplished a 25-minute space walk. trol. I think the operation of these contracts has constituted one of the finest examples of the proper working of the free enterprise system." The manned space flight program has a valuable asset in the person of George Mueller (pronounced Miller). The "Show Me" state native received a bachelor's degree in electrical engineering from the Missouri School of Mines, then moved to Indiana to earn a master's in the same discipline at Purdue University. H e came east to the Bell Telephone Laboratories where he conducted television and microwave and measuring experiments, and pioneered in the measurement of radio energy from the sun, in microwave propogation, and in the design - of low field electrons. After a stint of graduate study a t Princeton University, George Mueller joined the faculty of Ohio State University as assistant professor of electrical engineering; later he bacame a full professor. At Ohio State, he conducted research on the study and design of broadcast and dielectric antennas, cathode emission, low field magne- �trons and traveling wave tubes, and was awarded a P H . D in physics. The next stop was Redondo Beach, California and the Space Technology Laboratories where Dr. Mueller spent the next five years before he assumed direction of NASA'smanned space flight program. Dr. Mueller was one of the originaLurs of the concept and design of the Telebit digital telemetry system. He holds seven patents in electrical engineering, and is the author of more than 20 technical papers. With E. R. Spangler, he is co-author of a book, "Communication Satellites." Dr. Mueller is a n active participant in national and international conferences on space communications and space technology. Successful Stepping Stones Uprated Saturn I on Cape Kennedy launch pad just before it successfully boosted unmanned Apollo spacecraft into a 300-mile high suborbital flight. The February 26, 1966 flight marked the first test in space of the Apollo command and service module, the CKIH which will house America's moon explorers. 30 The Mercury and Gemznz space successes are the steppzng stones to the Apollo moon landzng mzssions and to other space operatzons of the future. The Ofice of Manned Space Flzght zs movzng ahead wzth Gemznz and expects to accomplzsh all the remaznzng program obyctzves zn the addztzonalJzghts scheduled over the remaznzng months of thzs year. Szmultaneously, remarkable progress zs also bezng made zn the Apollo program, the largest research and development program the Unzted States has ever undertaken. Project Apollo calls for NASA to develop two major launch vehicles and a three-man spacecraft; to assemble a nation-wide government-industry team; to construct a complex of advanced launch facilities, and to carry on a comprehensive testing program . . . all on a coordinated schedule. Under George Mueller's direction, they're doing just that. America's moon men will make the half-million-mile round trip in the three-man Apollo spacecraft now under development at NASA's Manned Spacecraft Center (MSC) near Houston, Texas, where a cattle range was converted to a modern installation in less than three years. Dr. Robert Rowe Gilruth directs MSC,an organization responsible for the design, development and testing of manned spacecraft and associated systems, for the selection and training of astronauts, �for support.of manned flight operations and for managing the work of the industrial team which shares the work load. The MSC Giant Probably the biggest thing at MSG these days is the Apollo spacecraft. Weighing in at 45 tons and standing 84 feet tall, the spacecraft is divided into three sections-a command module, a service module and a lunar module. T h e command module, something like the crew compartment of a commercial jet airliner, is designed so that the astronauts can eat, sleep and work and relax in a shirt sleeve environment. It is furnished with life support equipment and is chock full of controls and instruments to enable the astronauts to maneuver their craft. Since the command module will return to earth, it is constructed to withstand the tremendous deceleration forces and intense heating caused by re-entry. It's a room with a view. The double-walled pressurized chamber has three windows in front of the astronauts' couch, and two more windows on the side. A tower-like launch escape system perches atop the command module for use in an emergency launch situation. It is jettisoned after the second stage of the launch vehicle ignites. Beneath the command compartment is the service module, a 128foot diameter cylinder weighing about 50,000 pounds. Inside are supplies, fuel and an engine which the astronauts use to maneuver their craft into and out of lunar orbit or alter their course and speed in space. Once the Apollo spacecraft is orbiting around the moon, two of the astronauts crawl through a hatch into the bug-like third section, the lunar module. "The bug" detaches from the combined command-service module and descends to the moon's surface. The lunar module has its own complete guidance, propulsion, computer, communications and environmental control systems. The vehicle has two stages. The bottom stage contains the rocket engine and spidery legs which extend for lunar landing. This unit is detachable and forms the "launch platform" for the upper stage which houses the astronauts. Attached to the upper stage is the rocket engine which America's lunar explorers will ignite when they are ready to rejoin the hovering command-service module. After the astronauts crawl back into the command module, the lunar module is jettisoned and the trio heads back to earth. Just before re-entry, the service module is also detached. Parachutes are deployed to slow down the re-entry forces just before splashdown. The Manned Spacecraft Center is an outstanding example of the advanced facilities, unique in both size and capability, which NASA has constructed to meet Apollo program objectives. MSC is the home of the Mission Control Center-an office/ laboratory combination where engineers, scientists and technicians team up with computers to direct operations of manned space flights. Support functions at the Center include recovery control, recovery communications, meteorology and trajectory data, network support and monitoring devices for life support and vehicle systems. MSC is also the site of the country's largest "man-rated" space environment chamber. Altitudes of about 80 miles can be simulated in this chamber and spacecraft can be subjected to temperatures and solar radiation conditions that will be experienced on a flight to the moon. Muscle for Apollo The muscle for the Apollo program is provided by the Saturn family of heavy launch vehicles. Development of these mammoth boosters is the responsibility of Dr. Werner von Braun, director of NASA'sGeorge C. Marshall Space Flight Center (MSFC) at Huntsville, Alabama. Some 7,000 MSFC employees are engaged in the research and development of the Saturn workhorses-from conception through design, development, fabrication and assembly of the hardware, and testing. Baby of the Saturn family is the 120-foot tall, 2 1.5-foot diameter Saturn I. It has been flight tested with a perfect record of ten successes in ten launches, a record without parallel in the development and operation of large launch vehicles. In unmanned test flights Saturn I has placed test versions of the command and service modules of the Apollo spacecraft into orbit. With its cluster of eight rocket engines burning refined kerosene and liquid oxygen, Saturn I develops 1.5 million pounds of thrust in its first stage. Its second stage has six engines which burn liquid hydrogen and liquid oxygen, producing 90,000 pounds total thrust. Also under development at MSFC is the uprated Saturn I with an improved first stage version of the Saturn I, and a new and more powerful second stage. With 1.6 million pounds booster thrust, and 200,000 pounds second stage thrust, the uprated Saturn I will boost Astronauts Virgil Grissom, Ed White and Roger Chaffee into earth orbit for a long duration mission of up to two weeks. Saturn V Moon Rocket Big Daddy in the Texas-size booster corral is the Saturn v, a vehicle of gigantic size and power. The Saturn v moon rocket tops the 250-foot high Statue of Liberty by 31 feet. Assembled on the launch pad with the three modules of the Apollo spacecraft on top, the moon rocket stands 364 feet tall and weighs about six million pounds. Its first stage has a diameter of 33 feet, and is powered by a cluster of five engines packing a wallop of 7.5 million pounds of thrust. Another million pounds of thrust will be furnished by a cluster of five engines in the second stage. On top of the first two is the third stage which is identical to the uprated Saturn r second stage. The Saturn's first stages are built by NASA's Michoud Assembly Facility in New Orleans, Louisiana, and later are floated by barge into Mississippi for rumbling static tests at NASA's Mississippi Test Facility. The second and third stages of Saturn v are built in California. At Mississippi the gigantic stages are lifted directly from the barges onto the test stands, held captive and run through full strength, full duration "hot" firings. After testing, the rocket stages are replaced on the barges and floated via a complex �canal system to Cape Kennedy. Other flight equipment, manufactured and tested at NASA's nation-wide facilities, are also shipped to the John F. Kennedy Space Center (KSC)in Florida, where an integrated governmenthndustry team takes over assembly, checkout and launch of the moon-bound space ships under the direction of Dr. Kurt Debus. KSC, the major launch organization for manned and unmanned space missions, is the focal point for the development of launch philosophy, procedures, technology and facilities. So huge and so complicated are the Apollo-Saturn launch vehicles that NASA had to devise new approaches to assembling them. Thus a new generation of space facilities was born. Towering over the Kennedy Space Center terrain is the VAB (vehicle assembly building), a 524-foot high plant where four Saturn rockets can be assembled simultaneously and checked out stage by stage. Scheduled for completion this year, the VAB provides for assembly and checkout of the moon rockets in a con- trolled environment which eliminates the hazards weather could wreak on rockets and time schedules. After assembly, the Saturn v rocket, its mobile launch tower and mobile platform leave the VAB through a doorway 456 feet high. A monstrous tractor trundles the works to the launch pad. The Kennedy moonport will have two Saturn v launch pads, with the capability of launching about six vehicles a year after 1968. The pieces in this massive jigsaw puzzle called manned space flight are falling into place. Excellent progress is being made on the development of the Saturn launch vehicle; hardware is being assembled for a 1967 test flight of the Apollo lunar module, astronauts are being trained. At the pivotal halfway point in the program this spring, Dr. George Mueller, the man who manages this engineering enterprise had this to say: "The government/industry team required to carry out the manned flight program is in place and working. The program is on schedule, a schedule set when the program began. And, if progress continues, we will accomplish the manned lunar landing and safe return of America's astronauts in this decade." But Dr. Mueller doesn't want to stop there. He has emphasized many times that the lunar mission is just one of the many possible misszons which can use the capabilities of the Apollo-Saturn program. "The j r s t successful manned lunar landing will just scratch the surface. Its greatest achievement will be a demonstration ofthe ability to travel a quarter of a million miles from earth, land on that heavenly body and return safe& here. Other journeys must follow. W e must use the Saturn rockets, the Apollo spaceship and the launch facilities . . . over and over again to gain the fullest return on our investment. "We can make many jlights in orbit about the earth, about the moon or to the moon's surface. By using our capabilities efectively and imaginatively, we will be able to carry out a wide variety of missions of great scientiJic value and of direct bent$ to mankind." In Mission Operations Control Room at the Manned Spacecraft Center near Houston, Texas, personnel monitor Gemini space flight. Mission Control Center is the focal point of a global network of tracking and communications stations which provide centralized control for orbital flights. 32 � 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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_000064 Title A name given to the resource "A Nation Goes to the Moon." Description An account of the resource Written by NASA Office of Manned Space Flight Associate Administrator George E. Mueller, this is an article from G. E. Challenge, Fall 1966, page 26 to 32. Creator An entity primarily responsible for making the resource Mueller, G. E. (George Edwin), 1918-2015 General Electric Corporation Date A point or period of time associated with an event in the lifecycle of the resource 1966-09-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) Mueller, G. E. (George Edwin), 1918 Project Apollo (U.S.) United States. National Aeronautics and Space Administration--History Manned space flight Type The nature or genre of the resource Clippings Text Source A related resource from which the described resource is derived Saturn V Collection Box 19, Folder 6 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_000051_000074 https://digitalprojects.uah.edu/files/original/20/10389/ssfmanewteltec_031307114348.pdf 4ef1f7ca06204154ca271b8f0509b50c 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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 ssfmanewteltec_031307114348.pdf spc_stnv_000845 Title A name given to the resource "A new telemetry technique." Description An account of the resource A technique new to telemetry is discussed which promises to alleviate an enigma facing the telemetry engineer : How to adequately transmit the avalanche of vibration and other wideband data desired in the development phase of large missiles and launch vehicles. The data channels are stacked in the frequency spectrum as single sideband subcarriers which frequency modulate the RF carrier. The system design utilizes to advantage the statistical properties of vibration data to achieve maximum data transmission efficiency from the available RF carrier deviation. However, in contrast to proposed statistical predigestion techniques, the data is transmitted in raw form. Creator An entity primarily responsible for making the resource Frost, Walter O. Date A point or period of time associated with an event in the lifecycle of the resource 1961-10-16 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Aerospace telemetry Type The nature or genre of the resource Text Reports Source A related resource from which the described resource is derived Saturn V Collection Box 6, Folder 7 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_000825_000849 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/16694 https://digitalprojects.uah.edu/files/original/55/1944/uah_hockey_003.pdf b1e2a4de527a01d2b6067c03a203fb69 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 UAH History Collection Identifier An unambiguous reference to the resource within a given context UAH History Collection 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 uah_hockey_002 Title A name given to the resource "A New Year's Maine Attraction." Description An account of the resource This flier advertises a trip to Maine for UAH hockey fans to see "the Chargers capture the top-ranked Black Bears of the University of Maine." Tours of Maine scenery and sites, a "New England Style Dinner," lodging, and transportation are offered in the package. Creator An entity primarily responsible for making the resource University of Alabama in Huntsville. Division of Continuing Education Date A point or period of time associated with an event in the lifecycle of the resource 1989-01 Temporal Coverage Temporal characteristics of the resource. 1980-1989 Subject The topic of the resource College sports Continuing education--United States Hockey University of Alabama in Huntsville Huntsville (Ala.) Madison County (Ala.) Type The nature or genre of the resource Fliers (Printed matter) Text 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. Source A related resource from which the described resource is derived University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama https://digitalprojects.uah.edu/files/original/20/2337/spc_stnv_000109.pdf 0688c277ff575a7f8a5578951cf23151 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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_000109 Title A name given to the resource "A Practical Approach to the Optimization of the Saturn V Space Vehicle Control System Under Aerodynamic Loads." Description An account of the resource This paper includes the equations for the bending moment of a launch vehicle with the effects of bending and sloshing dynamics. It also includes a comparison between the bending moment response envelope of the measure winds and the bending moment response of the MSFC synthetic wind profile. Creator An entity primarily responsible for making the resource Ryan, Robert S. (Robert Samuel), 1925- Teuber, Dieter Date A point or period of time associated with an event in the lifecycle of the resource 1965-07-21 Subject The topic of the resource Optimization Spacecraft control Saturn launch vehicles Saturn Project (U.S.) Source A related resource from which the described resource is derived Saturn V Collection Box 14, Folder 30 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_000075_000118 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. <a href="%E2%80%9Dhttp%3A//libarchstor.uah.edu:8081/repositories/2/archival_objects/17177%E2%80%9D">View item in ArchivesSpace</a> Temporal Coverage Temporal characteristics of the resource. 1960-1969 Type The nature or genre of the resource Memorandums Still Image Text Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. NASA TM X-53698 https://digitalprojects.uah.edu/files/original/20/2338/spc_stnv_000110.pdf 73fb9d367015e683f202a542837d94c6 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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_000110 Title A name given to the resource "A Prime Contractor's Reliability Program for Components/Parts for the Douglas S-IVB Stage Project." Description An account of the resource This paper, presented at the fifth annual Reliability and Maintainability Conference in New York City, contains a "prime contractor's reliability program for components/parts for the Douglas S-IVB stage project." These parts include special flight critical items and their complementary reliability engineering program plan is outlined in this paper. Creator An entity primarily responsible for making the resource Wilson, R. B. Hug, N.L. Date A point or period of time associated with an event in the lifecycle of the resource 1966-07 Subject The topic of the resource Quality control Reliability engineering Saturn launch vehicles Saturn Project (U.S.) Saturn S-4B stage Source A related resource from which the described resource is derived Saturn V Collection Box 18, Folder 5 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_000075_000118 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. <a href="%E2%80%9Dhttp%3A//libarchstor.uah.edu:8081/repositories/2/archival_objects/17500%E2%80%9D">View this item record in ArchivesSpace</a> Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. Douglas Paper No. 3794. Temporal Coverage Temporal characteristics of the resource. 1960-1969 Type The nature or genre of the resource Reports Still image Text https://digitalprojects.uah.edu/files/original/132/9393/r10_02-06.pdf b2022dcdc7fd73903b40e9d1065b2786 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 Series 10: Books and Pamphlets Title A name given to the resource Series 10: Books and Pamphlets Still Image A static visual representation. Examples include paintings, drawings, graphic designs, plans and maps. Recommended best practice is to assign the type Text to images of textual materials. 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 r10_02-06 Source A related resource from which the described resource is derived Series 10, Box 2, Folder 6 Title A name given to the resource "A Profile of Gabriel Hanby" by Blount County Historical Society, 1962 Relation A related resource r10-211020 https://digitalprojects.uah.edu/files/original/20/10698/Progplaneart_012709164341.pdf bfd2bb526157cf3d96d008ec773907cd 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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 Progplaneart_012709164341.pdf spc_stnv_000621 Title A name given to the resource "A Program plan for earth orbital space astronomy." Description An account of the resource Manned space flight offers the opportunity to couple the astronaut/scientist's ability to select and process data and to calibrate, modify and repair instruments with the vantage point for astronomical observations provided by a platform located above the Earth's atmosphere. This paper briefly examines the role which manned space flight may play in the 1970-1990 time period in meeting astronomy research needs. The instruments and facilities which appear feasible for that period are described.; Paper presented by J. R. Olivier, National Aeronautics and Space Administration, George C. Marshall Space Flight Center and H. L. Wolbers, Ph.D, McDonnell Douglas Astronautics Company - Western Division, Advance Space and Launch Systems. Creator An entity primarily responsible for making the resource Olivier, J. R. Date A point or period of time associated with an event in the lifecycle of the resource 1968-11-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Manned space flight Technology utilization Astronomical observatories Type The nature or genre of the resource Text Program Plans Source A related resource from which the described resource is derived Saturn V Collection Box 29, Folder 11 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_000600_000624 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17997 https://digitalprojects.uah.edu/files/original/193/13828/Defense_Billboard_31_001.pdf 32d541eb570df3a0e7b6b44aed4e1d98 PDF Text Text American Forces Information Service, Department ol Defense 601 N. Fairfax Street, Room 312, Alexandria, VA 22314-2007 � 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 Defense Billboard Posters 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 Defense_Billboard_31 Title A name given to the resource "A Promotion...A Party...A Pity" Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. D2.9:P94 Description An account of the resource Woman's purse and shoe on street outside of a bar as a cab drives away Creator An entity primarily responsible for making the resource Department of Defense Date A point or period of time associated with an event in the lifecycle of the resource 1990-08-17 Temporal Coverage Temporal characteristics of the resource. 1990-1999 Subject The topic of the resource Department of Defense poster United States--Department of Defense Drunk driving Alcoholic beverages Nightlife Type The nature or genre of the resource Posters Still Image Source A related resource from which the described resource is derived The University of Alabama in Huntsville M. Louis Salmon Library Defense Billboards Posters Case 1, Drawer 1 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 Defense Billboards https://digitalprojects.uah.edu/files/original/20/10672/Realtimeopersyst_101507115951.pdf 29c0579a15c0eddd0f4d38fc8ad1481a 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 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 <a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here, </a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here, </a>and <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. 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. 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. 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 Realtimeopersyst_101507115951.pdf spc_stnv_000642 Title A name given to the resource "A real time operating system for the Saturn V launch computer system." Description An account of the resource Presentation aimed to encourage a final check on the Saturn V project before its first launch to ensure safety and success. Creator An entity primarily responsible for making the resource Palm, Frank R. Date A point or period of time associated with an event in the lifecycle of the resource 1966-07-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Saturn launch vehicles Real-time data processing Automatic test equipment Real time operation Operating systems Computer programming Type The nature or genre of the resource Text Presentations Source A related resource from which the described resource is derived Saturn V Collection Box 17, Folder 69 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_000625_000649 Is Referenced By A related resource that references, cites, or otherwise points to the described resource. http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17492