1 20 970 https://digitalprojects.uah.edu/files/original/20/976/spc_stnv_000029.pdf ca468b145201e0165b47451724301481 PDF Text Text NASA TECHNICAL MEMORANDUM January 13, 1966 1965 P U B L I C A T I O N S BY M a t e r i a l s Division NASA George C. Mdrshdll S'dce Flight Center, �NASA-GEORGE C. MARSHALL SPACE FLIGHT CENTER January 13, 1966 NASA TM.X-53378 1965 PUBLICATIONS Materials Division ABSTRACT "1965 Publications" is a compilation of abstracts of NASA Technical Memorandums and MSFC Internal Notes, written by personnel of the Materials Division and released during 1965. These reports may be requested from the MSFC Library at the following address: National Aeronautics and Space Administration George C. Marshall Space Flight Center Huntsville, Alabama 35812 Attention: MS-IPL �NASA-GEORGE C. MARSHALL SPACE F L I G H T CENTER TECHNICAL MEMORANDUM X-53378 1965 PUBLICATIONS by Materials Division MATERIALS D I V I S I O N PROPULSION AND VEHICLE ENGINEERING LABORATORY �TABLE OF CONTENTS ........................:.... INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . SUMMARY Page 1 1 NASA TECHNICAL MEMORANDUMS . ... . . .. . . . . . ... . .. Spectrographic Solution Analysis of Aluminum Alloys . . Nonmonotonicity in Sensitivity Test Data . . . . . . . . Studies in Silazane Chemistry . . . . . . . . . . . . . 1964 Publications .. .. .. . . 2 2 2 3 Vacuum Compatibility of Engineering Materials (Liquid and . . . . . . . . . . . Semi-Solids) 3 Effect of LiquPd Nitrogen Dilution of LOX Impact Sensitivity 3- Acoustic Techniques for the Nondestructive Evaluation of . . Adhesively Bonded Composite Materials . . . . . . 4 H-1 Engine LOX Dome Failure 4 . . .. . ... . .. .. . . . ..... ...... . ... . Comparison of Two Instruments for Determining Hardness . . . . ... .. . . . . of Elastomers 5 Effects of Nuclear Radiation, Cryogenic Temperature, and Vacuum on the Electrical Properties of Dielectric Materials 5 Accelerated Compression Set Properties of Fourteen . . . . . . . . . . Elastomers . . 6 . .... . . . . ... ... ... ..... Preliminary Investigation of Blast Hazards of R P - 1 1 ~ 0 ~ and LH2/LOX Propellant Combinations . . . . . . . . . . .. Further Development and Evaluation of M-31 Insulation for . .. . .... Radiant Heating Environments . . . . . . . . ........... Tracuum Compatibility of Engineering Materials (Solids) I1 . Automatic Extensometer for Elastomers . . Size and Duration of Fireballs from Propellant Explosions . Stress Corrosion Studies of AM-355 Stainless Steel . . . . . Low Temperature Mechanical Properties of HP 9-4-25 Alloy 6 7 7 7 8 8 8 �Page Experimental X-ray Stress Analysis for PrecipitatTon Hardened Alloys . . . . . . .. . . . . . 9 Investigation of the Coefficient of Friction of Various Greases and Dry Film Lubricants at Ultra High Loads for the Saturn Hold Down Arms . . . . . . . . . . .. . 9 Low Temperature Mechanical Properties of Aluminum Alloy 2219T87, 0.040-Inch Thick Sheet Through 5.000-Inch Thick Plate . . 9 Distribution of Failure Times in Stress Corrosion Tests . . . 10 Effects of Various Additives on Physical Properties and . . . . . . . . Performance of Monomethylhydrazine ... 10 Simulation Study of the Amount of Sensitivity Test Data Required to Reject the Hypothesis of Normality When the Sample Population is Nonnormal . . . .. . .... .... 11 Status Report on Chemical Synthesis of Monomeric SelfSealant Type Esters . . . . . .. . . 11 A Compilation of Radiant and 12 . ... ... ... ... .. . ... . . ... . . . .. .. . . ..... Convective Heating Test Results . MSFC INTERNAL NOTES Flexure Fatigue Properties of Typical S-IV Common Bulkhead Composite Sandwich structure at Liquid Nitrogen.Temperature . 12 Low Temperature Mechanical Properties of "Tensilized" Waspaloy Bolts . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 Preliminary Investigation of Explosive Hazards of Solvents . . . .. . .. . in Contact with Liquid Oxygen .. 13 S-13 Thermal.Contro1 Coating for SA-91Pegasus A Spacecraft .. 13 . .. 14 . '. . . . Examination of Electropolished Foils of Aluminum Alloys by Transmission Electron Microscopy . .. . .. . . . . Absorption Correction Tables for the Philips A M R / ~Electron .. Probe at Electron Energies of 30 and 20 KV . . ... 14 Low Temperature Mechanical Properties Evaluation of TD Nickel 14 ... �GEORGE C. MARSHALL SPACE FLIGHT CENTER ---- -- - TECHNICAL MEMORANDUM X-53378 1965 PUBLICATIONS by Materials Division SUMMARY This report lists and abstracts NASA Technical Memorandums'and MSFC Internal Notes written by personnel of the Materials Division, Propulsion and Vehicle Engineering Laboratory, George C. Marshall Space Flight Center, National Aeronautics and Space Administration, during 1965. INTRODUCTION The mission of the Materials Division is to conduct research and development in materials science and engineering as related to the programs of the George C. Marshall Space Flight Center. This report lists and abstracts the technical reports written by personnel of the Materials Division during 1965. Requests for copies of these reports should be addressed to: National Aeronautics and Space Administration George C. Marshall Space Flight Center Huntsville, Alabama 35812 Attention: MS-IPL �NASA TECHNICAL MEMORANDUMS J a n u a r y 30, 1965 1964 PUBLICATIONS NASA TM X-53191 by M a t e r i a l s D i v i s i o n U n c l a s s i f i e d , 1 8 pages "1964 P u b l i c a t i o n s " i s a c o m p i l a t i o n of a b s t r a c t s o f a NASA T e c h n i c a l Note, NASA T e c h n i c a l Memorandums, and MSFC I n t e r n a l N o t e s , w r i t t e n by p e r s o n n e l of t h e M a t e r i a l s D i v i s i o n and r e l e a s e d d u r i n g 1964. J a n u a r y 20, 1965 SPECTROGRAPHIC SOLUTION ANALYSIS OF ALUMINUM ALLOYS NASA TM X-53192 by D. Hamilton and S. C o r b i t t U n c l a s s i f i e d , 1 8 pages, 5 t a b l e s , 6 f i g u r e s , 1 p l a t e To o b t a i n a c c u r a t e a n a l y s e s of m e t a l s and a l l o y s w i t h t h e most w i d e l y used t e c h n i q u e of s p e c t r o g r a p h i c a n a l y s i s , i . e . , t h e p o i n t - t o p l a n e s p a r k t e c h n i q u e , t h e s t a n d a r d s and t h e unknown m a t e r i a l must be q u i t e s i m i l a r i n s i z e , s h a p e , chemical c o m p o s i t i o n , and m e t a l l u r g i c a l s t a t e . By d i s s o l v i n g t h e sample and u s i n g t h e vacuum cup s p a r k t e c h n i q u e t o a n a l y z e t h e s o l u t i o n , t h e s e l i m i t a t i o n s c a n be circumvented. Standards c a n be s y n t h e s i z e d e a s i l y by mixing a l i q u o t s of m a s t e r r e f e r e n c e s o l u tions. The s o l u t i o n t e c h n i q u e a l s o o f f e r s t h e p o s s i b i l i t y of a d d i n g a n i n t e r n a l s t a n d a r d and, t h e r e b y , o b t a i n i n g a w i d e r s e l e c t i o n o f r e f e r e n c e l i n e s t o use i n the analysis. The s o l u t i o n s p e c t r o g r a p h i c method h a s been i n v e s t i g a t e d and a p p l i e d t o a wide v a r i e t y of a n a l y t i c a l problems a t t h i s C e n t e r . A s a n example, t h e p r o c e d u r e f o r t h e d e t e r m i n a t i o n of manganese, z i r c o n i u m , magnesium, vanadium, t i t a n i u m , and i r o n i n t y p e s 2219 and 2319 aluminum a l l o y i s presented. The r e s u l t s a g r e e w i t h t h e r e s u l t s o f c l a s s i c a l wet methods and a r e p r e c i s e t o f0.005 p e r c e n t i n t h e c o n c e n t r a t i o n r a n g e s i n v o l v e d . J a n u a r y 22, 1965 NONMONOTONICITY I N SENSITIVITY TEST DATA NASA TM X-53194 by J . B. GAYLE U n c l a s s i f i e d , 9 pages, 2 f i g u r e s I n g e n e r a l , t h e f r e q u e n c y of r e a c t i o n s f o r s e n s i t i v i t y t e s t d a t a of t h e ''go-no-go" t y p e i n c r e a s e s m o n o t o n i c a l l y w i t h i n c r e a s i n g l e v e l s of s t i m u l u s . However, o c c a s i o n a l i n s t a n c e s o f nonmonotonic b e h a v i o r have been n o t e d . �One such instance has been investigated by carrying out a sufficient number of replicate tests to permit a statistical analysis of the data. The results indicated that over a considerable range of stimulus levels the frequency of response decreased. significantly with increasing stimulus levels. The significance of this finding to sensitivity testing in general is discussed. February 1, 1965 STUDIES IN SILAZANE CHEMISTRY NASA TM X-53197 by James D. Byrd and James E. Curry Unclassified, 31 pages, 6 tables, 7 figures The chemistry of a number of silazane compounds has been studied in an effort to prepare polymers containing Si-N linkages. This effort has resulted in the discovery or development of some new and interesting polymeric materials. Polysilazanes having good thermal stability, elastomeric properties, and good film-forming properties have been prepared. A method has been developed for the preparation of an elastomeric silazane from dimethyldichlorosilane and ethylenediamine. This material has good thermal stability and remains rubbery after extended exposure to elevated temperatures (300-400°C). Polymers having a number of useful properties were prepared by the polymerization of equimolar amounts of h e x a p h e n y l c y c l o t r i s i l a z a n e and a number of different aromatic diols such as p, p'-biphenol. February 5, 1965 VACUUM COMPATIBILITY OF ENGINEER- NASA TM X-53207 ING MATERIALS (LIQUIDS AND SEMI-SOLIDS) by J. G. Austin and J. B. Gayle Unclassified, 34 pages, 25 figures The rates of evaporation of 20 liquid and semi-solid materials in a vacuum environment and the effects of temperature on the rates of evaporation of 11 of the 20 materials were determined experimentally. Test conditions were from room temperature to 154'C at pressures of lom5 torr or less. February 15, 1965 EFFECT OF LIQUID NITROGEN DILUTION ON LOX IMPACT SENSITIVITY by C. F. Key and J. B. Gay,le NASA TM X-53208 �Unclassified, 26 pages, 18 figures An experimental investigation was carried out to study the decrease in reactivity of materials with liquid oxygen (LOX) that is caused by A wide range of materials dilution of the LOX with liquid nitrogen (LN2). was selected for testing, each of which previously had been shown to be sensitive to impact in LOX. Tests were made with the ABMA LOX Impact Tester using LOX/LN2 mixtures ranging in concentration from 20 percent LOX in LN2 to pure LOX. The results showed that relatively large proportions of LN2 were required to effect an appreciable decrease in reactivity; however, all materials tested were insensitive to impact at 10 kg-m in liquid air. March 17, 1965 ACOUSTIC TECHNIQUES FOR THE NASA TM X-53219 NONDESTRUCTIVE EVALUATION OF ADHESIVELY BONDED COMPOSITE MATERIALS by W. N. Clotfelter Unclassified, 43 pages, 27 figures The extensive usage of composite materials in the Saturn vehicle has required considerable effort in the development of nondestructive inspection methods to evaluate the mechanical integrity of these materials. This report describes through-transmission and single-side acoustic methods applicable to the quality verification of composite panels. Some of the techniques discussed are "off the shelf.'' Others are believed to be unique. All of these inspection methods are discussed and illustrated to show their applicability to the quality verification of certain types of composite structure used in the Saturn. An attempt has been made to relate selected techniques to the acoustic characteristics of the materials used. March 18, 1965 H-1 ENGINE LOX DOME FAILURE NASA TM X-53220 by C. E. Cataldo Unclassified, 22 pages, 6 tables, 9 figures A 7079-T6 aluminum forging, which is the forward closure of the H-1 rocket engine combustion chamber, failed after the engine was installed on the Saturn S-1-7 vehicle. It was concluded that the failure, occurringseveral weeks before launch at the Kennedy Space Center, was caused by stress corrosion. This report describes the metallurgical analysis of the failure and discusses previous failures experienced on this same part and the corrective actions that were taken. �March 26, 1965 COMPARISON OF TWO INSTRUMENTS NASA TM X-53226 FOR DETERMINING HARDNESS OF ELASTOMERS by J. T. Schell and C. D. Hooper Unclassified, 31 pages, 5 tables, 18 figures To reach a higher degree of accuracy in control evaluations of rubber compounds, a comparison was made of two commercially available instruments for measuring hardness of elastomeric compounds. These instruments, the Shore durometer and ASTM (Tinius Olsen), were compared over a wide hardness range on 13 types of rubber formulations. Studies indicated that, although the ASTM (Tinius Olsen) instrument requires a more refined test specimen and is somewhat more difficult to operate, it is a more precise instrument and should be used where very close tolerances are involved or as a "referee" in case of doubt with other instruments. The Shore durometer provides a rapid means for measuring hardness of elastomers; the specimen size is not critical; and the Shore durometer accuracy is sufficient for control evaluations as well as for the majority of end items. With the graphs and tables in this report, it is possible to convert units of measure from one instrument to the other for a particular compound of interest; however, to prepare a single table (or graph) illustrating a "typical" correlation for all elastomers is not practical because of the variation in creep with different formulations. EFFECTS OF NUCLEAR RADIATION, NASA TM X-53230 CRYOGENIC TEMPERATURE, AND VACUUM ON THE ELECTRICAL PROPERTIES OF DIELECTRIC MATERIALS March 30, 1965 by R. L. Gause and E. C. McKannan Unclassified, 29 pages, 6 tables, 11 figures The dielectric properties of polymeric materials probably are among the most sensitive to the effects of radiation from the space environment, from nuclear power sources, or from nuclear rockets. These properties also are affected in various ways by other parameters of the space environment such as vacuum and temperature. Therefore, a combined environmental evaluation of four commonly used dielectrics was made. Some preliminary results indicate that the effect on the dielectric constant and dissipation factor of the polymers was minor for vacuum alone but of major significance for radiation alone. The cryogenic tempemperatures had �a minor effect on the dielectric properties of silicone rubber and polytetrafluoroethylene but a direct and signifikant effect on the epoxy and polyurethane materials. It appeared that the effect.of cryogenic temperatures may have counteracted the radiation effects in spme cases. Obtaining dielectric measurements within the combined environmental simulator posed some special problems and required some novel techniques which are described. April 2, 1965 ACCELERATED COMPRESSION SET PROPERTIES OF FOURTEEN ELASTOMERS NASA TM X-53232 by C. D. Hooper and J. T. Schell Unclassified, 44 pages, 35 figures Fourteen types of synthetic elastomers, from which O-rings and other gaskets might be fabricated, were investigated for their compression set properties. Each compound was tested at a minimum of three temperatures (ranging from 70°C (158OF) to 250°C (482OF)) during various periods of time up to 32 days. Results showed that most elastomers have reasonably good compression set properties at room temperature (25OC) but that many of these might have critical limitations when subjected to the same compression at an elevated temperature. These tests, like other accelerated tests, were not expected to indicate the small differences that might be encountered in actual service; however, they do provide a practical evaluation of the properties that are useful where a high degree of precision is not expected. A summary of the data obtained from this study is presented in graphical form, illustrating the characteristics and limitations of each compound tested. April 9, 1965 PRELIMINARY INVESTIGATION OF BLAST HAZARDS OF RP-1/LOX AND LH~/LOXPROPELLANT COMBINATIONS NASA TM X-53240 by John B. Gayle, Charles H. Blakewood, James W. Bransford, William H. Swindell, and Richard W. High Unclassified, 31 pages, 20 figures This report discusses the current status of information regarding the blast hazards of liquid propellants and presents results obtained from one part of a comprehensive analytical and experimental investigation of this problem. The data generally were consistent with siting �criteria now used for RP-11LOX. However, explosive yields determined for LH2/LOX were markedly lower than values reported by previous investigators and suggest that current siting criteria for this propellant combination may be overly conservative. May 25, 1965 FURTHER DEVELOPMENT AND EVALUATION OF M-31 INSULATION FOR RADIANT HEATING ENVIRONMENTS NASA TM X-53267 by Vaughn F. Seitzinger Unclassified, 25 pages, 4 tables, 6 figures The results of a program for additional development and evaluation of M-31 insulation, a composite material developed specificaliy to protect the base of the Saturn launch vehicle, are presented. This insulation is comprised of fibrous potassium titanate ,and asbestos fibers, bonded with colloidal silica. Processing techniques by the manufacturer of potassium titanate resulted in an increase in the bulk density, thermal conductivity, mechanical strength, and drying shrinkage of the insulation. June 21, 1965 AUTOMATIC EXTENSOMETER FOR ELASTOMERS NASA TM X-53231 by C. D. Hooper Unclassified, 19 pages, 1 table 11 figures An extensometer has been designed to measure accurately the elongation of any elastomer or similar material and to record electronically this data on the chart of the testing instrument. This instrument, which may be used by operators with a minimum of experience, results in reproducibility of data from laboratory to labdratory since the extension is measured by a semi-automatic.process. Although it was designed for accuracy (from 0 to 1000 percent using a one-inch original gauge), the instrument is rugged enough to require no special handling. It is relatively simple to fabricate in a standard machine shop and can be adapted to almost any tension testing instrument (conforming to ASTM or Military Specifications for testing elastomers) at a very low cost when compared to other commercial laboratory equipment. June 24, 1965 VACUUM COMPATIBILITY OF ENGINEERING NASA TM X-53286 MATERIALS (SOLIDS) I1 by J. G. Austin and J. B. Gayle �Unclassified, 156 pages, 2 tables, 130 figures .The rate and extent of weight loss of 62 solid materials in a vacuum environment were determined experimentally by continuous and intermittent weighing techniques. Test conditions ranged from 41°C to 200°C at presto 10-5 torr. The results are presented in 2 tables and sures of 130 figures. July 23, 1965 LOW TEMPERATURE MECHANICAL PROPERTIES NASA TM X-53302 OF HP 9-4-25 ALLOY by W. R. Morgan Unclassified, 13 pages, 3 tables, 4 figures The mechanical properties of HP 9-4-25 alloy sheet (0.062-inch thick) The were determined at temperatures from 27OC (80°F) to -253OC (-423OF). ultimate tensile and yield strengths were considerably greatet at -253OC (-423OF) than at 27OC (80°F),' and the notched/unnotched tensile ratios were greater than 0.81 at temperatures from 27OC (80°F) to -196OC (-320°F). This alloy is not recommended for critical applications below -196OC (-320°F) since the elongation and notched/unnotched tensile ratio decreased raptdly below this temperature. August 4 , 1965 SIZE AND DURATION OF FIREBALLS FROM PROPELLANT EXPLOSIONS NASA TM X-53314 by J. B. Gayle and J. W. Bransford Unclassified, 19 pages, 7 figures Data from tests and vehicle incidents have been compiled and analyzed with respect to fireball diameters and durations. Both variables were found to be dependent on the cube root of the weight of the combined propellants and independent of the particular propellant combination. Fireball diameters also appear to be roughly dependent on the cube root of the ambient pressures. August 9, 1965 STRESS CORROSION STUDIES OF AM-355 STAINLESS STEEL NASA TM X-53317 by J. G. Williamson Unclassified, 18 pages, 3 tables, 6 figures The stress corrpsion cracking susceptibility of AM-355 stainless steel alloy was studied. This alloy is used extensively for sleeves in flared �tube fittings in the S-I and S-IC stages of the Saturn I and Saturn V vehicles, respectively. Various heat treated conditions were investigated and relative stress corrosion cracking susceptibility determined. Of the generally used heat treatments, the fully hardened SCT 1000 treatment was found to be superior in stress corrosion resistance. September 13, 1965 EXPERIMENTAL X-RAY STRESS ANALYSIS FOR PRECIPITATION HARDENED ALUMINUM ALLOYS NASA TM X-53329 by J. H. Wharton and W. L. Prince Unclassified, 26 pages, 12 figures X-ray diffraction techniques for dekrmining stress in precipitation hardened aluminum alloys have been developed and evaluated. The materials investigated included 2014-T6, 2219-T37, and 7075-T6 aluminum alloys. A precision corresponding to +5 percent of the alloy yield strengths was obtained under laboratory conditions. Further studies are needed to evaluate this method for field measurements of stress in vehicle components. September 14, 1965 INVESTIGATION OF THE NASA TM X-53331 COEFFICIENT OF FRICTION OF VARIOUS GREASES AND DRY FILM LUBRICANTS AT ULTRA HIGH LOADS FOR THE SATURN HOLD DOWN ARMS by K. E. Demorest and A. F. Whitaker Unclassified, 29 pages, 2 tables, 12 figures A series of high load, l6w speed sliding friction tests was made on 8 fluid lubricants and 18 dry lubricants at normal unit loads from 10,000 psi to 150,000 psi. Four different substrate materials having a range of hardnesses from Rockwell C 18 to Rockwell C 55 were used. The ultimate load capability of both fluids and dry films is a function of substrate hardness with the best ultimate load capability being provided by inorganically bonded molybdenum disulfide films with small amounts of graphite added. The coefficient of friction of the fluid lubricants appears to be an inverse function of substrate hardness and a direct function of the normal load. The coefficient of friction of the dry lubricants is an inverse function of the normal load, but it does not appear to be related to the substrate hardness. September 14, 1965 LOW TEMPERATURE MECHANICAL PROPERTIES OF ALUMINUM ALLOY 2219-T87, 0.040-INCH THICK SHEET THROUGH 5.000-INCH THICK PLATE by C. R. Denaburg NASA TM X-53332 �Unclassified, 33 pages, 12 tables, 11 figures The mechanical properties of aluminum alloy 2219-T87 sheet and plate of various thicknesses were determined over the temperature range from ambient through -253OC (-423OF). The ultimate tensile and yield strengths in the longitudinal and transverse direction increased as the temperature decreased. The ultimate tensile strength ranged from 66.4 to 69.4 ksi at ambient temperature and 95.8 to 107.3 ksi at -253°C (-G23OF). The yield strength at ambient temperature was between 54.1 and 57.1 ksi; however, at -253OC (-423OF), it ranged between 68.8 and 79.5 ksi. The elongation, in general, increased as the temperature decreased. Elongation in the longitudinal and transverse directions for all the thicknesses investigated averaged 9.0 percent at ambient temperature and 11 percent at -253OC (-423OF). The tensile strength in the short transverse direction for the twoinch thick plate was 64.0 ksi at ambient temperature and 78.9 ksi at -253OC (-423OF). The elongation was 4.6 percent at ambient temperature and decreased to 1.3 percent at -253OC (-423OF). The tensile strength in the short transverse direction of the fiveinch thick plate was 54.6 ksi at ambient temperature and 65.1 ksi at -253°C (-423OF). Elongation was 0.6, 0.2, and 1.6 percent in two inches for ambient temperature, -196OC (-320°F), and -253OC (-423OF), respectively. Previous evaluations of aluminum alloy 2219 by this division are referenced. November 1, 1965 DISTRIBUTION OF FAILURE TIMES IN STRESS CORROSION TESTS NASA TM X-53355 by J. B. Gayle Unclassified, 12 pages, 3 figures The results of stress corrosion tests on aluminum alloys have been analyzed with respect to the statistical nature of the distribution of failure times. The analyses indicated that the data were represented adequately by a three-parameter Weibull distribution in which the induction period amounted to 85 percent of the time of the first observed failure and 55 percent of the time required for failure of half the specimens. November 3, 1965 EFFECTS OF VARIOUS ADDITIVES ON NASA TM X-53356 PHYSICAL PROPERTIES AND PERFORMANCE OF MONOMETHYLHYDRAZINE by Harold Perkins �Unclassified, 15 pages, 2 tables, 7 figures The freezing and boiling points of 0 -40 percent mixtures of various nitrogen compounds and water in monomethylhydrazine (MMH) were determined experimentally. The additives for these mixtures were selected on the basis of chemical similarity to MMH, mixture thermal stability, probability of contamination occurrence, cryoscopic and ebullioscopic effects, and anticipated effects on propellant performance. Theoretical specific impulses were calculated as a function of additive concentration using nominal values of the Saturn S-IVB Vehicle Auxiliary Propulsion System as a basis. November 4, 1965 SIMULATION STUDY OF THE AMOUNT OF NASA TM X-53357 SENSITIVITY TEST DATA REQUIRED TO REJECT THE EIYPOTHESIS OF NORMALITY WHBN THE SAMPLE POPULATION IS NONNORMAL by J. B. Gayle and C. L. Hopkins Unclassified,l3 pages, 3 tables, 3 figures Computer simulation techniques were used to study the number of sensitivity tests which are required to reject the hypothesis of a normally distributed sample population when the population actually was nonnormal. The results indicated that, even under the most favorable conditions, the number of tests required far exceed the number usually run in sensitivity type testing. This suggests that any assumption concerning the statistical nature of the distribution ordinarily will not be verified experimentally. November,4 , 1965 STATUS REPORT ON CHEMICAL SYNTHESIS NASA TM X-53358 OF MONOMERIC SELF-SEALANT TYPE ESTERS by Lawrence R. Moffett, Jr. Unclassified, Zlpages, 8 figures The purpose of this program was to develop an efficient synthetic chemical route or the preparation of alkyl esters of a -cyanosorbic acid (1-cyano-hexadienoic acid) as intermediates in self sealant polymerization studies. The in-house investigation of the direct and indirect esterification of a-cyanosorbic acid, employing standard and non-conventional techniques, has resulted in the development of a satisfactory procedure for the preparation of n-butyl-a-cyanosorbate and n-amyl-acyanosorbate in yields approaching 90 percent. Parallel stuzies which were initiated by the Research and Technology Division of the Air Force Systems Command, Wright-Patterson Air Force Base, Ohio, (ASD) under Government Work Order H-71461, have resulted in the preparation of �n-butyl-a-cyanosorbate in - somewhat lower yields with concomitant longer reaction periods. The synthetic procedures developed in both investigations are discussed in detail in this report, and chemical and spectral data are presented to verify the identities of the esters formed in the various reactions. This program established that the direct esterification of a-cyanosorbic acid is quite feasible and is a much preferred route to the indirect esterification through preparation of such intermediates as the corresponding acid chlorides and sodium salts. December 15, 1965 A COMPILATION OF RADIANT AND CONVECTIVE HEATING TEST RESULTS NASA TM X-53369 by F. Uptagrafft, L. A. Soileau, and T, Barkley Unclassified, 164 pages, 12 tables, 5 figures The report is a compilation of data which characterize the response of approximately 1,500 insulation materials when they are exposed to a variety of temperature and pressure environments. To establish the capability of these materials to satisfy the many conditions to which they could be exposed in the Saturn launch vehicles, a multitude of different heat pulses was included in the material evaluation. The purpose of the program was to define the characteristics of these materials in peculiar environments (e.g., radiant heating, heating at reduced pressure, etc.) which are experienced in the Saturn stages and for which no data were available. The preponderance of the materials evaluated are available commercially. INTERNAL NOTES January 4, 1965 FLEXURE FATIGUE PROPERTIES OF IN-P&VE-M-65-1 TYPICAL S-IV COMMON BULKHEAD COMPOSITE SANDWICH STRUCTURE AT LIQUID NITROGEN TEMPERATURE by 0. Y. Reece and R. S. Harvey Unclassified, 12 pages, 1 table, 4 figures A series of fatigue tests was completed at -196OC (-320°F) 0 to 5 million cycles range for the purpose of establishing an for a honeycomb structure typical of that used for Saturn S-IV bulkhead construction. The data and projections show that the fatigue strength of the panels exceeded the proportional limit in the S-N curve common average in the �range of 0 to 10 million cycles, and the 95 percent confidence limit of the fatigue strength exceeded the proportional limit in the range of 0 to 400;OOO cycles. January 28, 1965 LOW TEMPERATURE MECHANICAL PROPERTIES OF f l ~ ~ WASPALOY BOLTS IN-P&VE-M-65-2 ~ ~ ~ ~ ~ ~ ~ by J. W. Montano Unclassified, 22 pages, 7 tables, 6 figures This report presents the mechanical properties of "Tensilized" Waspaloy bolts and reduced shank bolt specimens which were tested at temperatures from ambient to -423OF (-253OC). The mechanical properties of the bolt specimens were compared with those of high strength A-286 alloy. It was concluded from the low temperature tests that the "Tensilized" Waspaloy bolts of 5116-inch diameter, 24 threads per inch should be satisfactory for structural applications in space vehicles at temperatures from ambient to -423OF (-253OC). April 9, 1965 PRELIMINARY INVESTIGATION OF EXPLOSIVE HAZARDS OF SOLVENTS IN CONTACT WITH LIQUID OXYGEN IN-P&VE-M-65-3 by C. F. Key and J. B. Gayle Unclassified, 9 pages, 1 table, 1 figure Small scale tests were carried out to study the explosive hazards of selected solvents in contact with liquid oxygen. The results indicated that many solvents react'explosively with liquid oxygen when suitably initiated. These findings are similar to results of previous studies using nitrogen tetroxide. June 22, 1965 S-13 THERMAL CONTROL COATING FOR SA-9IPEGASUS A SPACECRAFT IN-P&VE-M-65-4 by L. K. Zoller Unclassified, 15 pages, 5 tables Optical property data from various tests of the S-13 thermal control coating used on the SA-9 launch vehicle are tabulated. Specimens of the S-13 coating were prepared when the SA-9 vehicle components were painted. These specimens were located in the Launch Complex 37 Service ~ l l �Tower and, thus, were exposed to the same environmental history as the SA-9 launch vehicle. The specimens were periodically evaluated for ultraviolet radiation stability. The data indicate that the S-13 paint on the SA-9 vehicle was within design requirements and that the paint should not deteriorate beyond prescribed limits due to ultraviolet radiation degradation. July 22, 1965 EXAMINATION OF ELECTROPOLISHED FOILS OF ALUMINUM ALLOYS BY TRANSMISSION ELECTRON MICROSCOPY IN-P&VE-M-65-5 by J. H. Wharton, G. R. Marsh, and W. L. Prince Unclassified, 22 pages. 12 figures This report describes the techniques which are involved in electropolishing foils of 7075 aluminum alloy for transmission electron microscopy investigations. The success of these electropolishing techniques is demonstrated by the transmission micrographs that are included. Brief comments concerning the microstructure observed in 7075 aluminum alloy are given. July 26, 1965 ABSORPTION CORRECTION TABLES FOR THE PHILIPS A M R / ~ ELECTRON PROBE AT ELECTRON ENERGIES OF 30 AND 20 KV IN-P&VE-M-65-6 by J. H. Wharton, W. L. Prince, and G. R. Marsh Unclassified, 186 pages, 2 tables Mass absorption corrections have been tabulated as a function of mass absorption coefficients and atomic number. The corrections are based upon Philibert's simplified expression for F(X) and the use of an emergence angle of 15 degrees. Calculations at two accelerating voltages, 30 KV (Table I) and 20 KV (Table 11), are included. A typical application of these data is demonstrated. December 15, 1965 LOW TEMPERATURE MECHANICAL PROPERTIES EVALUATION OF TD-NICKEL IN-P&VE-M-65-7 by C. R. Denaburg Unclassified, 10 pages, 2 tables, 3 figures The mechanical properties of annealed TD-Nickel, 0.030-inch thick sheet, furnished by E. I. duPont de Nemours and Company, Incorporated, were determined from ambient temperature through -253OC (-423OF). In �general, the tensile properties increased with a decrease in temperature, and the properties in the longitudinal direction increased slightly more than in the transverse direction at -253OC (-423OF). The notched tensile strength and notched/unnotched tensile ratio in the transverse direction were slightly higher than in the longitudinal direction at all test temperatures. �January 13, 1966 APPROVAL NASA TM X-53378 1965 PUBLICATIONS by Materials Division The information in this report has been reviewed for securtiy classification. Review of any information concerning Department of Defense or Atomic Energy Commission programs has been made by the MSFC Security Classification Officer. This report, in its entirety, has been determined to be unclassified. This document has also been reviewed and approved for technical accuracy. n wQ a d W. R. Lucas, Chief, Materials Division F. B. Cline Director, Propulsion and Vehicle Engineering Laboratory �DISTRIBUTION DIR DEP-T DEP-T R-DIR R-DIR I-DIR I-DIR I-V-MGR R-A S R-SA R-RM R-AERO-DIR R-ASTR-DIR R-COMP-DIR R-ME-DIR R-RP-DIR R-P&VE-DIR R-P&VE-A R-P&VE - P R-P&VE-R R-P&VE-RT R-P&VE- S R-P&VE -V R-P&VE-M R-P&VE-MC R-P&VE-ME R-P&VE-MM R-P&VE-MN R-QUAL-DIR R-TEST-DIR v MS-H MS-I MS- IPL MS-T CC-P R-ME-m Dr. von Braun Dr. Rees Mr. Neubert Mr. Weidner Dr. McCall Col. OIConnor Dr. Mrazek Dr. Rudolph Mr. Williams Mr. Dannenberg Mr. McCartney Dr. Geissler Dr. Haeussermann Dr. Hoelzer Mr. Kuers Dr. Stuhlinger Mr. Cline Mr. Goerner Mr. Paul Mr. Rieger Mr. Hofues Mr. Kroll Mr. Aberg Dr. Lucas Mr. Riehl Mr. Kingsbury Mr. Cataldo Mr. Curry Mr. Grau Mr. Heimburg Dr. Gruene Mr. Akens Mr. Remer Miss Robertson 'Mr. Wiggins Mr. Wof ford Mr. Hasemeyer Scientific and Technical Information Facility P. 0. Box 33 Colle,ge Park, Maryland 20740 � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000029 Title A name given to the resource "1965 Publications," Materials Division, George C. Marshall Space Flight Center. Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. NASA TM X-53378 Description An account of the resource This document is a compilation of abstracts of NASA Technical Memorandums and MSFC Internal Notes, written by personnel of the Materials Division and released during 1965. Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center United States. National Aeronautics and Space Administration Date A point or period of time associated with an event in the lifecycle of the resource 1966-01-13 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) Materials science Spacecraft construction materials Propellants Type The nature or genre of the resource Annotated bibliographies Text Source A related resource from which the described resource is derived Saturn V Collection Box 16, Folder 3 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050 https://digitalprojects.uah.edu/files/original/20/10244/zerostage_082707085507.pdf 3798949d9a5d3372c1c7b9185e9fcaaf Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context zerostage_082707085507.pdf spc_stnv_000942 Title A name given to the resource "A 'Zero Stage' for the Saturn IB Launch Vehicle." Description An account of the resource To meet the demands of increasing payload size and weight, and to fill the large payload gap between the Saturn IB and Saturn V, a number of methods of uprating the Saturn IB have been studied by NASA and Chrysler Corp. of providing increased payload capability is discussed in this paper. Four 120 in. United Technology Center UA-1205 solid propellant motors, originally developed for the Air Force Titan III program, are clustered around the S-IB first stage of the Saturn IB launch vehicle. These four solid propellant motors provide the total thrust for liftoff of the vehicle, with S-IB stage ignition occurring just prior to burn-out and separation of the solid propellant motors. The term "Zero Stage" is applied to this added stage. Creator An entity primarily responsible for making the resource Vehko, Vaino J. Ruhland, William E. Date A point or period of time associated with an event in the lifecycle of the resource 3/1/1966 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn project Saturn launch vehicles Solid propellant rockets Saturn 1B launch vehicles Spacecraft propulsion 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 16, Folder 23 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_000925_000942 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/17414 https://digitalprojects.uah.edu/files/original/20/977/spc_stnv_000030.pdf 907a19de79b9e4a1422476b62c823081 PDF Text Text rb $3 -! ,/- t c; --J 'A &"r- A=!-. iw A BIBLIOGRAPHY OF WERNHER VON BRAUN ,+ 1965 - -: .'g . ,, '=3, \ X -* U 7 q-3 ; ! -I e b , - - !;I: - a ) , Lc-z . cc;s ,,,,-- .- 3;c. "About Comets and Meteors, " Popular Science, 184, No. 4 (April 1964) , 95. 3 = ' 2 !;7 , a - - -- 9 i+3. ,t . 3 -- -- -- ! "The Acid Test, National Strategy in an Age of Revolutions, ed. G. B. de Huszer. New York: Frederick A. Praeger Publishers, 1959, 64. ilp'"i d4 ??qF 1 , Chemical and Engineering News, 36, No .9 (March 3, 1958) , 52. , Signal (Journal of the Armed Forces Communications and Electronics Association) , 12, do. 7 (March 1958) , 5. , Space Journal, , Vital , V. 1, No. 3 (Summer 1958), 31. Speeches, 24, No. 14 (May I,1958), 433. F. W. Magazine, 46, No. 7 (March 1959), 12. Across the Space Frontier (with J. Kaplan, H. Haber, W. Ley, and 0. Schachtek, F. L. Whipple) , ed. C. Ryan. New York: Viking P r e s s , 1952. "The Age of the Flying Grandmothers ,I' As We Are, ed. H. Brandon. New York: Doubleday and Co. , Inc. , 1961, 235. "All Aboard for Outer Space, " Current Science and Aviation, 43, No. 18 (February 3-7, 1958), 1. "The Allure of Space, I ' Hartwick Review, 1 , No. 1 (October 1965) , 16. 1 "A Long Look into Space, " St. Petersburg (Fla. ) Times, Sect. D. July 11, 1965, 1. I I 1 "A Minimum Satellite Vehicle Based Upon Components Available from Missile Development of the Army Ordnance Corps, " Guided Missile Development Division, Ordnance Missile Laboratories, Redstrone Arsenal, Alabama, September 15, 1954. "An Interview with Dr. Wernher von Braun, " Sun Magazine, 1, No. 2, n. d. 10. , �"Anwendungen d e r Rakete Saturn," Weltraumfahrt, 11, No. 2 (June 1960), 47. "A Plea for a Coordinated Space Program, ' I The Complete Book of Satellites and Outer Space, 2nd ed. New York: Maco Magazine Corp. , 1957, 17. "A Rendezvous in Space, I f Popular Science, 187, No. 1 (July 1965) , 58. "Astronautical Fallout, " (with F. I. Ordway , 111) , Bulletin of the Atomic Scientists, 18, No. 11 (November 1962), 13. "Astronauts Will Land Standing Up," Popular Science, 184, No. 5 (May 1964), 82. "Atomic Power for Rockets, Popular Science, 185, No. I (July 1964) , 68. "Aufgabe und Ziel amerikanischer Raumfahrtprojekte, Raumfahrt wohin? ed. E. Sznger. Miinchen: Bechtle Verlag, 1962, 65. "Automatic Checkout Gives Rockets the Green Light, " Popular ~ c i g n c e ,184, No. 1 (January 1964), 58. "The Baby Space Station, (with Cornelius Ryan) , Collier's, 131, No. 26 (June 27, 1953), 33. "Because It Is There, I' Space Journal, 1 , No. I (Summer 1957) , 39. "Beginn d e r Raumfahrt, " Der Weltenraum in Menschenhand, H. V. H. Bolewski and H. Grb'ttrup. Stuttgart : Kruez -Verlag, 1959, 72. "Blast-off From the Moon, " This Week Magazine, April 12, 1959, 16 (Conclusion of F i r s t Men on the Moon). "Braun Calls for New Missile Space Alloys, " American Metal Market, 66, No. 102 (May 28, 1959) , 7. "Can an Astronaut Bail Out and Live?" Popular Science, 183, No. 3 (September 1963), 14. "Can We Get to Mars?" (with Cornelius Ryan), Collier's, 133, No. 13 (April 30, 1954) , 22. "Can We Ever Go to the Stars?" Popular Science, 183, No. 1 (July 1963), 63. �. C a r e e r s in Astronautics and Rocketry, (with C C. Adams and F. I. Ordway , 111) New York: McGraw -Hill Book Co. , Inc. , 1962. . "Ceramics for Critical Areas," Ceramic Industry, 83, No. 4 (October 1964), 29. "C lest Certain Maintenant: En 1970 Trois Hommes Partiront Pour La Lune ," P a r i s Match, No. 775 (February 15, 1964) , 46. "The Challenge to Instrument Makers, " ISA Journal, 5 , No. I 1 (November 1958), 52. "Challenge of Space, " Ordnance, 43, No. 234 ( May -June 1959) , 90 1. Chandranil Ettal. Chandra-Vijaya. Bombay: Pearl Publications, 1960. Bombay : Pearl Publications, 1960. ~ h & gFu Hsing K'ung. "Coming Kao Hsiung: Shih-Sui, 1962. . .. F e r r i e s in Space?" (Conquest of the Moon) (Conquest of Moon) (Conquest of the Moon) Popular Science, 87, No. 3 (September 1965) , 68. "Coming Mail by Satellite?" (Interview) , U. S. News and World Report, 44, No. 7 (February 14, 1958), 34. "Computer State-of-the-art on Spacef1 Electronic News, Vol. 10, 518, Sec. 2 (November 29, 1965) , 42. "Conference on Lunar Exploration, Part B, Proceedings, August 12-17, 1962, " (with J. V. Evans, T. B. A. Senior, E. Shoemaker, and Jack Green) Virginia Polytechnic Institute Bulletin, Engineering Experiment Station Series, No. 152, Vol. 56, No. 7 (May 1963). Conquest of the Moon (with F. L. Whipple and W. Ley) , ed. C. Ryan. New York: Viking P r e s s , 1953. "Contemporary Challenge, (Winter 1960), 19. The American Journal of Catholic Youth Work, 1, "Cosmic Wonders, " New York Times Magazine, December 8 , 1957, 13. flCrossingthe Last Frontier, ' l Collier's, 129, No. 121 (March 22, 1952) , 24. �, Great Adventures in Science, ed. H. Wright and S. Rappaport. New York: Harper and Bros. , 1956, 320. , A Calvacade of Collier's, ed. Kenneth McArdle. York: A. S. Barnes, 1959, 474. New Das Marsprojekt ; Studie einer interplanetarischen Expedition. Sonderheft der Zeitschrift Weltraumfahrt , Frankfurt: Umschau Verlag, 1952. "Das Programm der Weltraumfahrt, " Griff nach den Sternen, Gunther Lehner. Munich: Ehrenwirth Verlag, 1962, 7. ' B a s ~rggerraketen-programmd e r USA, " Weltraumfahrt , I 1, No. 4 (December 4, 1960) , 99. ?'The Day He Stopped Dreaming," Guidepost (October i960), 1. "Derflug zum Mars, f f Frankfurter Illustrierte, No. 7 (February 1957) , 6. "Destination Space, " History of Rockets, J. L. Russell, Jr. New York: Popular Mechanics P r e s s , 1959, 4. "The Deteriorating Effects of the Space Environment, " PDC Newsletter (National Academy of Sciences) 4, No. 3 (April 1961), I. . c De Verovering van Het Wereldruim (with Willy Ley) ~ t r eht/~ntwerpen: Prisma-Boeken, 1960. (Dutch translation of Across the Space Frontier). Die Erforschung des Mars. Frankfurt/Main: (Exploration of Mars) Fischer Biicherei, 1957. Die Eroberung des Mondes. Frankfurt/Main: S. Fischer , 1954. translation of Man on the Moon). (German Die Eroberung des Weltraums (with Willy Ley) . Frankfurt/Main, Hamburg: Fischer Biicherei , 1958. (Based on Across the Space Frontier and Conquest of the Moon). Die Eroberung des Weltraums, deutsches Lesbuch (with Willy Ley). New York: Ronald P r e s s , 1963. ?Do We Want a Space Industry?" Vital Speeches, 25, No. 4 (November 15, 1958) , 77. �"Do the Moon Photos Change Our Plans?" Popular Science, 185, No. 5 (November 1964) , 110. "Dr. Wernher von Braun Answers Your Questions About Nuclear Rockets, " Popular Science, 182, No. 3 (March 1963) , 62. "Dr. Wernher von Braun Answers Your Questions on Inertial Guidance, I ' Popular Science, 182, No. 4 (April 1963) , 18. "The Early Steps in the Realization of the Space Station, " Journal of the British Interplanetary Society, 12, No. I (January 1953) , 23. "Education and the Age of Space," Science Newsletter, 3, No. 2 (Spring 1958) , I . "Einen Wetter - Satelliten Fiir Deutschland" (Interview) , Der Spiegel, 19, No. 39 (September 22, 1965), 137. "Einsatzaufgaben wissenschaftlicher,, kommerzieller und bemannter Raumflugkoeper , Weltraumfahrt ,13, No. 5 (September/October , 1962) , 129. , Universtas (Tuebingen), 18, No. 7 (July 1963), 673. "Electric Power in Space, " Popular Science, 187, No. 2 (August 1965) , 58. "Electronique Spatiale, " Electronique Automatisme, No. 2 (March-April 1960) , 53. El Viajea l a Luna. Cordoba: DirecciounGeneral de Publicaciones, 1964. N "El Viaje Espacialy Nuestra Revolucion Technologica, I' Resena Tecnologica de Ingenieria, 11, No. 2 (March - April 1962) , 22. '!The Engineer and Space, (Interview) American Engineer, 28, No. 2 ( February 1958) , 12. "The Engines, Grumman Horizons, 4, No. 2 ( 1964) , 18. Erste Fahrt zum Mond. Frankfurt/Main , Hamburg: Fischer ~ i i c h e r e i ;Berlin, Darmstadt: Deut. Berch-Gemeinschaft, 1961. , New York: American Book Co. , 1963. . LIEsplorazione d i Mate (with Willy Ley) Milan: Feltrinelli, 1959. (Italian translation of The Exploration of Mars). �"Exploring the Space Sea," Ordnance, 49, No. 265 (July-August, 1964), 49. Exploration of Mars (with Willy Ley). New York: Viking P r e s s , 1956. (Also serialized in The Boston Daily Globe, 1956). "Exploration of Space a New Frontier," Space Age News (University of South Carolina) (April 24-25, 1959) , 2. "Exploration to the Farthest Planets, " New Scientist, 22, No. 387 (April 16, 1964), 147. , The World in 1984, Vol. I, Ed. N. Calder. Penquin Books, 1965, 39. Middlesex, Eng. : "The Explorers, " Astronautica Acta, V, No. 2 ( 1959) , 126. , Proceedings IXth International Astronautical Congress, Amsterdam 1958, Vol. 2, ed. F Hecht. Vienna: Springer -Verlag , 1959, 914. . "Face t o Face with IMr. Space" (Interview) , Our Times, 24, No. I (September 8-12, 1958), 8. I1The Feedback of Curiosity in Space Exploration, " Birmingham News, July 2 1 , 1962. (Nationally syndicated guest column for Victor Riesel) . "Festvortrag vor der Studentenschaft ,I' Berliner Breenpunkt: Raumfahrt. Mainz : Krausskopf -Flugwelt -Verlag, 1963, 35. F i r s t Men to the Moon. New York: Holt, Rinehart, and Winston, 1960. "First Men to the Moon, This Week Magazine, October 5 , 1958, 8 ( P a r t I of F i r s t Men to the Moon). , Reader's Digest, 78, No. 465 (January 196 I ) , 175. (Condensation of novel F i r s t Men to the Moon). "Five Days on the Moon, This Week Magazine, March 8, 1959. ( P a r t 3 of F i r s t Men on the Moon). "Foreword" to Soviet Space Technology, A. J. Zaehrenger. and Brothers, 196 1. New York: Harper �, Space Flight, C. C. Adams, with F. I. Ordway, 111; H. E. Canney; R. C. Wakeford. New York: McGraw-Hill Book Co. 1958. , Inc., , Design Guide to Orbital Flight, J. Jensew, e t al. New York: McGraw-Hill Book Co., Inc., 1962. , Beyond the Solar System, Willy Ley. New York: Viking P r e s s , 1964. "Forget Spilled Sputniks, " Mar.yville-Alcoa (Tenn. ) Times, February 28, 196 1, 13. 0 0 Fbrst P a Manen, Copenhagen: Munksgaards Forlag, 1961. of F i r s t Men to the Moon). (Danish translation "From Now On," (Interview), Challenge (General Electric Co. ) , 1, No. 3 (Winter 1962), 2. "From Small Beginnings," Project Satellite, ed. K. W. Gatland. British Book Centre, 1958, 19. New York: "The Future of Space, " in Fourth National Conference on the Peaceful Uses of Space, Boston, Massachusetts, April 29-May 1 , 1964, National Aeronautics and Space Administration. Washington, D. C. : U. S. Government Printing Office, 1964, 73. "Geleitwort , Epoche Atom und Automation, Vol. 9 (Die Luftfahct -Die Weltraumfahrt) Frankfurt/Main: Wilhelm Limpert Verlag, 1959. . , Steht Uns d e r Himmel Offen?, W. Pons, Wiesbaden: Kraus skopf -Verlag , 1960. "Guiding Spacecraft to Other Worlds, 14. Popular Science, 182, No. 6 (June 1963) , "How Propellants a r e Fed to Liquid Rocket Engines, No. 6 (December 1964), 98. Popular Science, 185, "How Satellites Will Change Your Life, I ' This Week Magazine, June 8 , 1958, 8. "How Spacemen Can Use Laser Beams, " Popular Science, 185, No. 4 (October 1964), 128. �"How t o do Business with the George C. Marshall Space Flight Center" (Inter view) , GSE, 2, No. 4 ( August-September 1960) , 70. "How We a t Marshall Feel about United Giving, " Community, 39, No. 4 ( May-June 1964) , 4. "How We '11 Travel on the Moon, " Popular Science, 184, No. 2 ( February 1964) , 18. "How We Track our Spacecraft, " Popular Science, No. 187, 5 ( November 1965) , 108. "The Importance of Satellite Vehicles in Interplanetary Flight, " Proceedings of the Second International Congress on Astronautics. London. Esslingen, Germany: Bechtle Verlag, 1951. , J our nal of the British Interplanetary Society, 10, No. 5 (September 1951) , 237. "Industryls Role at Marshall, " Grumman Horizon, (Spring 1963) , 2. " I n ' ~ o c k e t r y ," A Guide to Career Opportunities ( The Harvard Crimson) , (February 1959) , 24. ?!Interview,I ' Guideposts, 15, No. 8 (October 1960) , 2. "Introduction, The Challenge of the Sea, A. C. Clarke. Rinehart, and Winston, 1960. New York: Holt, . , Aerospace Dictionary, ed. F Gaynor. New York: Philosophical Library, 1960. , The Birth of the Missile, E. Klee and 0. Merk. E. P. Dutton, 1965. , Peenemiinde to Canaveral , D. Huzel. N. J. : Prentice-Hall, Inc. , 1962. New York: Englewood Cliffs, , The Rocket Pioneers on the Road to Space, ed. B. Williams and S. Epstein. New York: Julian Messner, Inc. , 1958. , Rocket to the Moon, E. Bergaust and S. Hull. Princeton, N. J. : Van Nostrand, 1958. �, Treasury of World Science, ed. D. D. Runes. New York: Philosophical Library, 1962. 1960. , NASA -Industry Program Plans Conference, September 27 -28, Huntsville, Alabama: George C. Marshall Space Flight Center, , Dictionary of Atomics, ed. A. Del Vecchio. Philosophical Library, 1964. New York: "The Journey," Collier's, 130, No. 16 (October 18, 1952) , 52. "The Journey to the Moon," Man and the Moon, ed. R. S. Richardson. Cleveland: World P r e s s , 1961, 95. Kasei Tanken. Tokyo: ~ a k u ~ 6 - s h a1958. , ( Exploration of Mars) "Keeping a Date in Space, " Operations Research Symposium, March 30-31 April 1, Proceedings P a r t i. U. S. Army Missile Command, Redstone Arsenal, Ala. , 1965, 333. "Konstruktive, theoretische, und experimentelle Beitrzge zu dem Problem der Fliissigkeitsrakete," PhD dissertation presented a t the FriedrichWilhelms -Universif$t of Berlin, April 16, 1934. Reprinted in Raketentechnik und Raumfahrtforschung , Sonderheft 1, Frankfurt: Umschau Verlag, n. d. La Gaba Tho. Rangoon: Con Yawng, 1960. (Conquest of the Moon). "Launch Vehicle Programs, Proceedings of First National Conference on the Peaceful Uses of Space. Washington, D. C. : U. S. Government Printing Office, 1961, 64, "Launch Vehicles and Launch Operations," Proceedings of the Second National Conference on the Peaceful Uses of Space, Seattle, May 8-10, 1963. Washington: U. S. Government Printing Office, 1962, 147. "La Vida en Marte, " Hablemos Mazine, (October 2-16, 1960). A "L'Espace , Ultime Conquete de 1'hornme?" Aviation Magazine, No. 432 (December I , 1965) , 18. Les P r g m i e r s Hommes Sur l a Lune. Paris: Editions Albin Michel, 1961. ( French translation of F i r s t Men to the Moon) . �"Libraries in the Space Age, ALA Bulletin, 56, No. 6 (June 1962) , 525. "Life on Mars, " This Week Magazine, April 24, 1960, 8 ( P a r t 1); May I , 1960 28 ( P a r t 2 ) ; May 8, 1960, 18 ( P a r t 3 ) . "Logistic Aspects of Orbital Supply Systems, " American Rocket Society Reprints, Vol. 185, No. 54 (December 1954). "Looking Toward Saturn, ' I The Washington Daily News ( Space Supplement) , December 5 , 1960, 31. 'ILos Proyectos de von Braun Adelante" (Interview) , (Chihuahua, Mex. ) , p. 1. Heraldo de -la Tarde "Management in Rocket Research, " Business Horizons, 5 , No. 4 (Winter 1962) , 41. "Management of Manned Space Programs, " Science, Technology, and Manage ment, eds. F. E. Kast and J. E, Rosenzweig. New York: McGraw-Hill, 1963, 248. "Management of the Space Program a t a Field Center, " Proceedings of the Conference on Space-Age Planning, Chicago, May 6 -9, 1963. Washington: U. S. Government Printing Office, 1963, 239. "Managing Man's Greatest Adventure" (Interview ) , The General Electric Forum, 5, No. 3 (July-September 1962) , 34. , Aerospace Engineering, 21, No. 9 (September 1962) , 16. "Man in Space, " Encyclopedia of Science and Technology Year Book, 1962. New York: McGraw-Hill Book Co., Inc., 14. "Man-made Radiation in Space, " Second %mposium on Protection against Radiations in Space, NASA SP-71. Washington, D. C. : National Aeronautics and Space Administration, 1964, i. "Man May Walk among the Stars, '' Nashville (Tenn. ) Tennessean, Sect. B, July 4 , 1965, p. 1. "Manned Platform in Space, Man on the Moon. Army Information Digest, October 1958, 32. London: Sidgwick and Jackson, 1953. �"Man on the Moon: The Exploration, " (with F. Whipple) , Collier's, 130, No. 17 (October 25, 1952) , 38. "Man's Survival in Space, I' ( ed. Cornelius Ryan) , Collier's, 131, No. 9 (February 28, 1953) , 40. "Man's Survival in Space: Emergency, l1 (with J. P. Henry and W. Ley) , Collier's 131, No. 11 (March 14, 1953), 38. "Man's Survival in Space: Testing the Men," (with H. Strughold, F. Haber, D. W. Hastings, and J. P. Henry), Collier's, 131, No. 10 (March 7 , 1953), 56. 17Mars," Popular Science, 183, No. 2 (August 1963) , 18. Mars Aller-Retour , F. L. Neher. P a r i s : Calmann-Levy , 1955. translation of Menschen Zwischen den Planeten) . (French The Mars Project. Urbana, Ill. : University of Illinois P r e s s , 1953. translation of Das Marsprojekte) . (English Menschen zwischen den Planeten, der Roman der Raumfahrt, F. L. Neher. Esslingen: Bechtle Verlag, 1953. (Material for this book supplied to Neher by von Braun) . , Die Buntezeite, (August 15, 1953-September 21, 1953). Mensen op de Maan. Amsterdam, Brussels: Elsevier, 196 1. lation of F i r s t Men to the Moon). (Dutch trans - I1Mighty Saturn Rockets, " U. S. News and World Report, 53, No. 6 (October 1), 1962, 74. "Missiles and Civilization, l 1 Together, 3 , No. 10 (October 1959) , 14. "Mond-Programm, l' Flugwelt, 10/15 (October 1963) , 843. "Moon crew to feel like giants;" Birmingham (Ala. ) News, July 4, 1964, 1. [Guest column for Victor Riesel. ] "Moon Shot, l 1 The North American Review, (Cornell University) , ( Summer 1964). �"More Answers to Your Questions About Space," Popular Science, 182, No. 2 ( F e b r u a r y 1963) , 92. "Motive d e r Neltraumfahrt , " Naturwissenschaft und Medizin, 6 , ( March, 1964) , 3. "Multi-Stage Rockets and Artificial Satellites, I f Space Medicine, ed. J. P. Marberger. Urbana, Illinois: University of Illinois P r e s s , 1951, 14. "My Faith, I f The American W e e k ' , February 10, 1963, 2. "My Most Exciting Moment, 86. " Popular Mechanics, 114, No. 3 (September 1960) , "Nachwort ,' I Damals i n Peenemuende, E r n s t Klee and Otto Merk. Stalling Verlag, 1963, 1i6. Oldenburg: "NASA Space Flight P r o g r a m s , " Proceedings of the F i r s t National Conference on the Peaceful Uses of Space, Tulsa, May 26-27, 1961. Washington: U. S. Government Printing Office, 196 1 , 64. !'Next - The Manned Satellite, I f A i r , 8 ( 1958) , 2. "The Next 20 Years of Interplanetary Exploration, ' I Aeronautics and Astronautics, 3, No. 11 (November 1965), 24. "Nous Serons s u r l a Lune en 1968" (Interview), Science e t Vie, No. 547 (April 1963), 162. "Observatories in Space, " Popular Science, 182, No. 5 (May 1963) , 14. "Our Problem- Yours and Mine, I ' The Instructor, 68, No. 1 (September 1958) , i. , Space Journal, 1, No. 4 ( F a l l 1958), 2. 0s P r i m i r o s Homens na Lua. Lisbon: Livraria Bertrand , 1962. translation of F i r s t Men t o the Moon). ( Portugese "Plain Talk f r o m von Braun" (Interview), Life, 43, No. 21 (November 18, 1957), 136. �"Postface, l1 Les Pionniers d e 1'Espace, E. Klee et 0. Merk. 1964, 187. Paris: Albin Michel, "Practical Application of Space, l1 Alabama School Journal, 78, No. 6 (February 1961) , 10. P r i m e r Viaje a l a Luna. Barcellona: Libreria Editorial Argos , 1961. (Spanish translation of F i r s t Man to the Moon). "Progress Toward Space Flight: Space Travel and Our Technological Revolution, " Missiles and Rockets, 2 , No. 7 (July 1957) , 75. "Progress toward Exploration of the Universe, The Consulting Engineer, 22, No. 8, August 1962, 104. "Propulsion Systems, " Lectures in Aerospace Medicine, January 16 -20, 1961 , Conducted a t the School of Aviation Medicine. USAF Aerospace Medical Center (ATC) , Brooks AFB, Texas : Air Force School of Aviation Medicine, 1961, 10. "Quel P a r t en Allemagne , Von Braun Nous Recoit en Secret, " ( Interview) , P a r i s Match, No. 856 (September 4 , 1965) , 18. "Raumfahrt in Dienste d e r Astronomie, l 1 Knut Lundmark och varldsrymdeus erbvring (a memorial volume) . &teburg: Varld och Ventande Fblag, 196 1, 19 (Also in Swedish on 16) . "The Redstone, Jupiter, and Juno, " Technology and Culture, 4, No. 4 ( F a l l 1963), 452. , The History of Rocket Technology, ed. E. M. Emme. Detroit: Wayne University P r e s s , 1964, 107. "Reminiscences of German Rocketry, Journal of the British Interplanetary Society, 15, No. 3 (May-June 1956) , 125. "The Return of a Winged Rocket Vehicle from a Satellite Orbit t o the Earth, " Physics and Medicine of the Upper Atmosphere, ed. C. S. White and 0. 0. Benson, Jr. Albuquerque, New Mexico: University of New Mexico P r e s s , 1952, 432. "Road t o the Moon and Beyond1' (Interview) , New Republic, 139, No. 16 (October 20, i958), 9. �"The Rocket Comes of Age," Interavia, 12, No. 8 (August 1957) , 789. "Rocket into Space, Space World, 3, No. 10 (October 1962) , 11. "Rocket Propulsion, in Listen to Leaders in Engineering, eds. A. Love and J. S. Childers. New York: Holt, Rinehart, & Winston, 1964. "Rocket-Riding Cameras Show how Boosters Behave, No. 6 (December 1965) , 106. Popular Science, 187, "Rundown on Jupiter C ,I ' Astronautics, 3, No. 10 (October 1958) , 32. "Saturn and the Future, Astronautics, 7, No. 2 (February 1962) , 22. "The Saturn Family, " Spaceflight, 3, No. i ( January 1961), 19. "The Saturn 5/Apollo Moon Mission," Hokkoku Shimbum, January 13, 1964, 5. "Saturn Our Best Hope, Space World, 1, No. 8 (June 1961), 10. "The Saturn Rocket, I' Explorers Journal, 40, No. i (February 1962) , 2. "The Saturn Rockets for America's Moon Programme, 335 (April 18, 1963) , 136. I' New Scientist, 18, No. "Sending Up the Saturn, I T Industrial Photography, 10, No. 6 (June 1961), 29. "SFRN and the Nation," Astronautics, 6 , No. 10 (October 1961), 66. "Ships and Satellites Navigated by Satellites, (May 1965), 76. "Solid vs. Liquid Rockets, Popular Science, 186, No. 5 Popular Science, 183, No. 5 (November 1963) , 61. "The Space Age - An Educational Challenge, " Journal of Physics ( Manhattan College), 1, No. 1 (Winter 1959), 4. , Pi Mu Epsilon Journal, 2, No. 10 (Spring 1959), 492. ''Space Age Construction is Next," The Modern Builder, (Kansas City, Mo. ) 1961, 19. �"Space Flight, " New International Year Book, 1965. "Space Flight and our Technological Revolution, Society, 1957 ( ARS Preprint 398-57). "Space Flight: A Look Ahead, New York: American Rocket Astronautics, 3, No. I 1 (November 1958) , 24. "Space is Big Business, " Industrial Relations Magazine, I , No. 2 (Summer 1962), 16 "Space Man - The Story of My Life, " The American Weekly, July 20, 1958, 7 , P a r t 1; July 27, 1958, 10, P a r t 2; August 3, 1958, 12, P a r t 3. "Space Power from Fuel Cells, I ' Popular Science, 185, No. 2 (August 1964) , 80. "Space-Probing Workhorse is Saturn's Destiny, " (May 1961) , 74. 69, No. 5 "Space Research is Impelled by Curiosity, " Newark Sunday News, Mqr 7 , 1961 , 14. "Space Rocketry, " A Journey Through Space and the Atom, ed. S. T. Butler and H. Messel. Sidney, Australia: Shakespeare Head P r e s s Pty. Ltd., 1962, 103. "Space Station Status Report, " Challenge (General Electric Co. ) , 2, No. 4 (Winter 1964) , 2. "Space Superiority," Ordnance, Vol. 37, No. 197 (March-April 1953), 770. "Space Travel, Best Articles and Stories, 2, No. 6 (June-July 1958) , I . , Foreign Service Journal, 35, No. 4 (April 1958) , 20. "Space Travel and Our Technological Revolution, No. 7 (July 1957), 75. " Missiles and Rockets, 2, "Space Travel, When It Is Coming, What It Will Be Like" (Interview) , U. S. News and World Report, 43, No. 16 (October 18, 1957) , 36 "Space Travel Sooner Than You Think" ( Interview) , U. S. News and World Report, 4 3 , No. 16 (September 9 , 1955), 62. �"Space Vehicles, " (with Frederick I. Ordway , 111) , The Encyclopedia Americana, Vol. 25, 1962 ed. New York: Americana Corp. , 1962, 320. "The Strange World of Zero Gravity, " Popular Science, 186, No. 6 , (June 1965) , 68. Start in den Weltraum; ein Buch iiber Raketen, Satelliten und Raumfahrzenge (With W. Ley) ~rankfurt/Main: S. Fischer , 1958. . "Station in Space, " The Complete Book of Outer Space, ed. J . Logan. New York: Maco Magazine Corp. , 1953, 16. (Reprinted in 2nd ed. , 1957, together with "A Plea for a Coordinated Space Program. ") Station in Weltraum. Frankfurt/Main: S. Fischer , 1953. by Heinz Gartmann of Across the Space Frontier. ) (German translation "Status Report on the Saturn Space C a r r i e r Vehicle and Its Potential Applications, I' Astronautica Acta, 7 , No. 2-3 (1961), 92. "The Story Behind the Explorers, " This Week Magazine, April 13, 1958, 8. "Sulla Luna con il mio Saturno, " I1 Giorno , August 24, 1965, 5. "Survey of Development of Liquid Rockets in Germany and Their Future Prospects, " Journal of the British Interplanetary Society, 10, No. 2 (March 1951) , 75. "Teamwork: Key to Success in Guided Missiles, No. I (October 1956), 38. " Missiles and Rockets, 1, "The Time for Space Exploration, " IEEE Spectrum, 2 , No. 12 (December 1965) , 44. "The Timing of Satellite and Space Probe Launchings, ' I Physics and Medicine of the Atmosphere and Space, ed. 0. 0. Benson, Jr. , and H. Strughold. New York: John Wiley and Sons, Inc., 1960, 259. "Tiniest Computers Steer Mightiest Rockets; Popular Science, 187, No. 4 (October 1965), 94. "To get to the Moon, Yale Daily News, C a r r e e r Opportunities in Research and Development Supplement, October 1963, 2. �&. nr Stockholm: Gebers F&lag, 1961. F i r s t Men on the Moon). Tur -Retur Manen. Oslo: Nosjanalfarlaget , 1961. F i r s t Men on the Moon). (Swedish translation of ( Norwegian translation of "The United States Space C a r r i e r Vehicle Program, I ' Proceedings of the Eleventh International Astronautical Congress, Vol. 1 , Stockholm, 1960. Vienna: Springer-Verlag, 1961, 638. "Un Bambino per la Luna , (Interview) LIEuropeo, January 19, 1964, 34. "U. S. Can Be F i r s t On Moon, I ' New York World Telegram, April 23, 1962, 30. U. S. Patent 2,967,393, January 10, 1961. "Rocket-propelled Missile." "Visit with a Prophet of the Space Age" (Interview) , The New York Times Magazine, October 20, 1957, 14. "Von Braun a t Marshall Tells of NASA Booster Plans, " DATA 9 , No. 1 (January 1964), 15. "Von Braun en la Argentina, " (Interview) , Revista Nacional Aeronautica y Espacial, 23, No. 259 (December 1963) , 5. "Von Braun Offers Plan for Station in.Space, I ' Aviation Age, 18, No. 6 (December 1952) , 15. "Von Braun Vous Fait Vivre l e Premier Voyage dans l a Lune," P a r i s Match, No. 532 (June 20, 1959) , 57. "Von Braun Reveals Progress in Space-Age Race, I' Honolulu Star Bulletin, January 27, 1961, 18. "Von Braun S w s Key to Space Tempo is: Change," Chicago's American, (Sect. 7) , April 7 , 1963, 2. "Von Braun says 'Your Ain't Seen Nothing, April 29, 1962, 31. '" Nashville Tennessean, "Vortwort, " Die Rakete zu den Planetenraum, H. Oberth. Verlag , 1960. Niirnberg: Uni- �, Roald Amundsen-Der Letzte Wikinger , E. Calis. Diisseldorf : Hoch-Verlag , 1960. , Vortstoss in den Weltraum, E. Dolezai. Solothurn, Switzerland: Schweizer Jugend-Verlag, 1964, 5. "Warum Raumfahrt ?" Arbeits -und Forschungsgemeinschaft "Graf Zeppelin1' Stuttgarter Gespraeche, June 1959, 26. "We Land on the Moon, '' This Week Magazine, October 12, 1958, ( P a r t 2 of F i r s t Men on the Moon. ) "Weltraumfahrt, eine Aufgabe fiir die internationale wissenschaftliche zusammenarbeit ,l 1 Probleme aus d e r Astronautisc hen Grundlagen forschung, ed. H. H. Koelle. Stuttgart: Gesellschaft fiir Weltraum forschung, 1952, 246. "We Need a Coordinated Space Program;" Space-Flight Problems (P'roceedings of the IV International Astronautical Congress, Zurich, 1953). BielBienne, Switzerland: 1954, 206. , The Yale Scientific Magazine, 31, No. 4 (January 1957), 40. "We Need to Know More About the Sun, l 1 Popular Science, 184, No. 3 (March 1964), 14. "Wernher von Braun, l1 Mitteilungen, 12, No. 44 (March 1959) , 5. (Reply to an e a r l i e r article in this publication that criticized Hermann Oberth. ) 'Wernher von Braun Answers Your Questions, " Popular Science, 182, No. I (January 1963) , 92. (Monthly column beginning with this issue and having various titles. ) "Wernher von Braun antwortet, l 1 Alfa, Zeitschrift fiir Technik und Fortbildung, I , No. I (1960) , 24. "Wernher von Braun Explores Seven Mysteries of Space'' (Interview), This Week Magazine, September 13, 1959, 18. 'Wernher von Braun on the Creative Artist ," School A r t s , 59, No. 2 (October 1959), 17. �I'What a n Astronaut will w e a r on the Moon, 1965), 87. Popular Science, 186, No. 4 (April "Whatever Happened to t h e Manned Space Station, " Popular Science, 186, No. 2 ( F e b r u a r y 1 9 6 5 ) , 88. "What I Believe, " Space World, I, No. 4 (November 1960) , 20. "What is a n Optimum P r o g r a m , '' Astronautics, 5 , No. 11 (November 1960) , 24. "What It Takes t o Survive i n Space, I ' Popular Science, 183, No. 6 (December 1963), 12. "What's Happening in the Race t o the Moon" (Interview), U. S. News and World Report, 56, No. 22 ( J u n e 1, 1964), 154. "What is Space All About?" Explorers J o u r n a l , 41, No. I ( M a r c h 1963) , 35. "What Space Control Means to U. S. , " U. S. News and World Report, 43, No. 126 (December 27, 1957) , 43. ( Excerpts f r o m testimony before senate committee) . "When Will We Land on Mars?'! Popular Science, 186, No. 3 ( M a r c h 1965) , 86. "Where A r e We Going?" Space Journal, 1 , No. 1 (Summer 1957), 10. "Where A r e We in Space?'' This Week Magazine, January 1 , 196 1, 1. "Where We Stand and Where We A r e Going, " ( I n t e r v i e w ) , E r i k Bergaust, This Week Magazine, September 30, 1962 , 4. "Why and How of the Countdown, ' I Popular Science, 186, No. 1 (January 1965) , 66. "Why a Satellite Stays Up, " Popular Science, 183, No. 4 (October 1963) , 16. "Why I Believe, I ' This Week, ( J u l y 18, 1965) , 2. "Why I Believe i n Immortality, " The Third Book of Words to Live By, ed. W. Nichols. New York: Simon and Schuster, 1962, 119. "Why I Chose America, " A m e r i c a n Map-azine, 154, No. 1 (July 1952), 15. "Why Must We Conquer Space, ' I Alabama School Journal, 78, No. 7 ( F e b r u a r y , 1961), 14. �, Virginia Journal of Education, 54, No. 4 (December 1962), 11. "Why Rockets Have Fins, " Popular Science, 185, No. 3 (September 1964) , 68. "Why Should America Conquer Space?ll This Week Magazine, March 20, 1960, 8. I7WhyShould I Be a Space Scientist?" Phamphlet published and distributed by the New York Life Insurance Co. , 1963. "Why the Challenge Must be Met, " Insulation Magazine, 8 , No. 2 ( February 1962) , 37. "Will Astronauts 'Fly' Rocket Boosters?" Popular Science, 184, No. 2 (June 1964), 72. "You Can't Duck the Space Age," The Emory Magazine, 41, No. 4 (July 1965), 10. "Your Most Important Problem, '' Hi Way, (November 1959) , 3 . "Zum amerikanischen Raumfahrtprogramm , " Starten und Fliegen, ed. H. -J. Luz. Stuttgart: Deutsche Verlags-Anstalt, 1959, 366. � Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000030 Title A name given to the resource "A Bibliography of Wernher von Braun, 1965." Creator An entity primarily responsible for making the resource Sharpe, Mitchell R. Date A point or period of time associated with an event in the lifecycle of the resource 1965-12 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) Von Braun, Wernher, 1912-1977 Type The nature or genre of the resource Bibliographies Text Source A related resource from which the described resource is derived Saturn V Collection Box 15, Folder 38 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050 https://digitalprojects.uah.edu/files/original/20/1284/spc_stnv_000142.pdf 77fbfe010026bb6e2d609c82c4d4a9a7 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000142 Title A name given to the resource "A Bibliography of Wernher von Braun, 1967." Description An account of the resource This official bibliography includes English- and foreign-language books, articles, and interviews. Creator An entity primarily responsible for making the resource George C. Marshall Space Flight Center Date A point or period of time associated with an event in the lifecycle of the resource 1968-01-01 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Von Braun, Wernher, 1912-1977 Communication in science German Americans Saturn Project (U.S.) Type The nature or genre of the resource Bibliographies Text Source A related resource from which the described resource is derived Saturn V Collection Box 25, 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_000119_000149 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/17815 https://digitalprojects.uah.edu/files/original/20/1281/spc_stnv_000139.pdf c9d0a1266d372271d5b8c89d34985d6a Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000139 Title A name given to the resource "A Bibliography of Wernher von Braun." Alternative Title An alternative name for the resource. The distinction between titles and alternative titles is application-specific. IN-MS-I-64-1 Description An account of the resource The document is designated for internal use only. Creator An entity primarily responsible for making the resource Sharpe, Mitchell R. George C. Marshall Space Flight Center Date A point or period of time associated with an event in the lifecycle of the resource 1964-02 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Von Braun, Wernher, 1912-1977 Communication in science German Americans Saturn Project (U.S.) Type The nature or genre of the resource Bibliographies Text Source A related resource from which the described resource is derived Saturn V Collection Box 15, Folder 38 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000119_000149 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/17369 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 <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context 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/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 <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context 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 <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context 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 <i>G.E. Challenge</i>, 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 <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context 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 <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context 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 <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000034 Title A name given to the resource "A Discussion of the Lunar Landing Problem." Description An account of the resource Digesu worked in the Astrionics Division of MSFC. This paper was presented at the AIAA Guidance & Control Conference, Massachusetts Institute of Technology, Cambridge, Massachusetts, August 12-14, 1963. Creator An entity primarily responsible for making the resource Digesu, Fred E. George C. Marshall Space Flight Center Date A point or period of time associated with an event in the lifecycle of the resource 1963-08-12 Temporal Coverage Temporal characteristics of the resource. 1960-1969 Subject The topic of the resource Saturn Project (U.S.) Space flight to the moon Lunar landing Type The nature or genre of the resource Reports Text Source A related resource from which the described resource is derived Saturn V Collection Box 9, Folder 25 University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama Language A language of the resource en Rights Information about rights held in and over the resource This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections. Relation A related resource spc_stnv_000027_000050 https://digitalprojects.uah.edu/files/original/20/1138/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 <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_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 <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_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 <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_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 <i>G. E. Challenge</i>, 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 <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context 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/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 <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_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 <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_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/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 <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context 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/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 <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context 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 https://digitalprojects.uah.edu/files/original/20/2340/spc_stnv_000112.pdf d4c88127fd9a2484ec76db78592484d6 Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Title A name given to the resource Saturn V Collection Relation A related resource <a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a> Identifier An unambiguous reference to the resource within a given context Saturn V Collection Description An account of the resource <p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p> <p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p> <p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p> Dublin Core The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/. Identifier An unambiguous reference to the resource within a given context spc_stnv_000112 Title A name given to the resource "A Review of Cryogenic Technology Aspects of Space Flight." Description An account of the resource This paper was presented at the International Cryogenic Engineering Conference in Kyoto, Japan. It details the use of cryogenic technology in rocketry and how its usage created "many new techniques and deeply stimulated many fields of cryogenic technology." Creator An entity primarily responsible for making the resource Paul, H. G. Wood, Charles C. Date A point or period of time associated with an event in the lifecycle of the resource 1967-04 Subject The topic of the resource Cryogenic rocket propellants Liquid propellant rocket engines Liquid propellant rockets--Fuel systems Liquid propellants Low temperature engineering Saturn Project (U.S.) Source A related resource from which the described resource is derived Saturn V Collection Box 22, Folder 3 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/17663%E2%80%9D">View this item in ArchivesSpace</a> Temporal Coverage Temporal characteristics of the resource. 1960-1969 Type The nature or genre of the resource Reports Still image Text