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Type is exactly "Essays"
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Northern Alabama Railroad History - copies
Bibb-Wyatt Genealogy
Bell Factory Paper (Found in Frances C. Roberts Files)
Steger History and Related
History of Walnut Grove Community
Madison County Politics, 1811 - 1955
Handwritten Notes on Local Banking and Commerce
Highlights of Madison County History
Frank James record book and miscellaneous notes, 1900 -1969
History of the Huntsville Daily Times - copies
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comparadvcoolingtech.pdf
Compcontpowe.pdf
compfaileffeonsystananalmode.pdf
compflowcont.pdf
Computerredundancy.pdf
Convenertranstel.pdf
corrprobasso.pdf
Deciprocforminicost_082007100247.pdf
Deciprocforminicost_100107112756.pdf
desconofgroddasinsat1BVESE.pdf
desdevzerogvapliq.pdf
deveffortachrel.pdf
Development of LOX-Hydrogen engines_041207113632.pdf
Deveofthenasagrum_052510145157.pdf
Devesepaconnsatu_082007102245.pdf
devloxrp1eng.pdf
devloxrp1engsatapollaunveh_041107135046.pdf
devofthesatsIVandsIVBliqhydtanintins.pdf
devolservovalve.pdf
Devsatsys.pdf
DigeofFY-64fundadvastudaugu1966.pdf
Digitrans_072011195719.pdf ONE ADDITIONAL COPY
digsim.pdf
drafinfoworkpaptechhistsaturn.pdf
dynaenvioftheS-IVandS-IVBsatuvehi.pdf
dynpro.pdf
EffHighpreSTEELS.pdf
engrsafeintomissspacsyst.pdf
Extesatu.pdf
Fabrsatus-icboos.pdf
Fligsoftdevelabo_082013164007.pdf
freedomadober2_022607111422.pdf
fultheaerengresforprorel_051308141557.pdf
govegrantscontracts_031507091859.pdf
Heliutilapol.pdf
Highenermissforsatur.pdf
HisMSFC.pdf
Impamanudesi.pdf
imptheuprsatI.pdf
InflapolsatuV.pdf
insspaveh.pdf
Instprogcompcont.pdf
Liqurockengi.pdf DIVIDED INTO TWO FILES ACTUALLY TITLED liqrockeng_1 and liqrockeng_2
Liqurockprop.pdf DIVIDED INTO TWO FILES
manmachandautotestoper_061807141628.pdf
mannlaunvehideve_032707091130.pdf
mannlunalandviarend_051107100817.pdf
manpofacmakfut_021208085025.pdf TWO COPIES
Manprowitpri_011608082119.pdf
ManuhistLM5_052510151514.pdf TWO COPIES
manwelcon_060707141124.pdf
Mastplanfordocu.pdf
Methcleaeleccomp_022008153249.pdf
minimax_081607145436.pdf
Mscapolprog.pdf DIVIDED INTO THREE FILES
Nexuconc.pdf
Operexpesatu_012309125536.pdf
oppeurpaylsatveh_071907142613.pdf
orgofacou_060508114422.pdf
phiandpraofrelasappinthedesofthesatinssys_013008103714.pdf
pracautomanufcheck_051107090838.pdf
probassolargscal_062007152941.pdf
Procseconasa.pdf
Propkey.pdf
Propkeymoontrav.pdf
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r07_02-09
recenasaexphydeng_070307131651.pdf
recnasexpwithydeng_041207110126.pdf
Reduemplmajo_112707122212.pdf
reliallupconc_070507141213.pdf
reliasseliqurockengi_062107153119.pdf
Reliengiprog.pdf
Rockengiturbspactrav_101507142613.pdf
Satuibinflight.pdf
satuIengigimbandthruvectcontsyst_041007110502.pdf
satuinstrsystems_041707143924.pdf
Satusyststud.pdf
SatuVDeri_062308104520.pdf
SatuVgrouwindprog_091207152652.pdf
Satuvmanainfo.pdf
SatuVprojdev.pdf
SatuVspacprog_111307143135.pdf
Selemethforupra_022410132604.pdf
Sourcredandpers_040709154214.pdf
spc_stnv_000204
spc_stnv_000205
spc_stnv_000206
spc_stnv_000207
spc_stnv_000220
spc_stnv_000221
spc_stnv_000227
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spc_stnv_000764
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spc_stnv_000862
spc_stnv_000867
spc_stnv_000881
spc_stnv_000895
spc_stnv_000896
spc_stnv_000897
spc_stnv_000899
spc_stnv_000904
spc_stnv_000905
spc_stnv_000908
spc_stuh_000012
spc_stuh_000012_transcript
spc_stuh_000013
spc_stuh_000013_transcript
spc_stuh_000014
spc_stuh_000014_transcript
survofsatustagtestandcheccompprogdeve_file1_102507115235 survofsatustagtestandcheccompprogdeve_file2_102507115246 survofsatustagtestandcheccompprogdeve_file3_102507115256 survofsatustagtestandcheccompprogdeve_file4_102507115304 survofsatustagtestandcheccompprogdeve_file5_102507115314
survpropprob_060607132313.pdf
Systappl_122007135157.pdf
systengrpropIII_1_062607092622.pdf systengrpropIII_2_062607092635.pdf systengrpropIII_3_062607092643.pdf
techimpllaunautom_072707115336.pdf
telsysdesforsatveh_110907094526.pdf
Testprocvalidbycompsimulation_071508150442.pdf
Thedeveofacheclangatol_110907113826.pdf
thedevofaboncombulforsat_090707133327.pdf
thehisofarmmisdev_121707120332.pdf
ThermalModels_081108112916.pdf
Theroleofsimuinthedeveofanautochecsyst_110507111856.pdf
theuseofwindsheainthedesiofaerovehi_103107103412.pdf
Thinclea_022508152049.pdf
Title
Select...
"A Comparison of Advanced Cooling Techniques for Rocket Thrust Chambers".
"A comparison of four control systems proposed for Saturn V launch vehicles."
"A survey of propulsion problems as related to space vehicle design."
"Communication from the President of the United States transmitting the report of the President's Materials Policy Commission, June 1952."
"Component Failure Effect on Systems: An Analytical Model".
"Computer Controlled Power Application for the Saturn Launch Vehicle".
"Computer Redundancy: Design, Performance, and Future".
"Corrosion problems associated with the Saturn space vehicles."
"Decision Procedure for Minimizing Costs of Calibrating Liquid Rocket Engines."
"Design and Development of a Zero-G Vapor Liquid Separator For Use in Cryogenic Fluid Power Systems."
"Design Concepts of Ground DDAS in Saturn 1B/V ESE."
"Development Effort to Achieve Reliability."
"Development of LOX-Hydrogen Engines for the Saturn Apollo Launch Vehicles."
"Development of LOX/RP-1 Engines for Saturn/Apollo Launch Vehicles."
"Development of Separable Connectors for the Saturn S-IV Stage."
"Development of the NASA/Grumman Lunar Module."
"Development of the Saturn S-IV and S-IVB Liquid Hydrogen Tank Internal Insulation."
"Digest of FY-64 Funded Advanced Studies: August 1966."
"Digital Simulation of an Aerospace Vehicle."
"Digital Transducers."
"Dynamic Environments of the S-IV and S-IVB Saturn Vehicles."
"Dynamic Problems in Launch Vehicles and Spacecraft."
"Effects of High-Pressure Hydrogen on Steels."
"Engineering Safety Into Missile-Space Systems."
"Extensions of Saturn."
"Fabricating the Saturn S-IC Booster."
"Flight Software Development Laboratory."
"Fulfilling the Aerospace Engineer's Responsibility for Product Reliability."
"Government Grants & Contracts."
"Helium Utilization in the Apollo/Saturn V Vehicle."
"High Energy Missions for Saturn."
"History of MSFC Reliability Philosophy."
"Improving the Uprated Saturn I."
"Instrumentation Programming for Computer Controlled Digital Data Processing."
"Liquid Rocket Engines."
"Liquid Rocket Propellant Compatibility Testing."
"Man, Machine, and Automatic Test Operations."
"Management problems faced in making future manned space exploration decisions."
"Manned Launch Vehicle Development."
"Manned Lunar Landing via Rendezvous."
"Manufacturing history - LM-5."
"Manufacturing problems with printed circuit boards and how to avoid them."
"Manufacturing welding control by E. R. Seay, Group Engineer, Lockheed-Georgia Company."
"Master plan for documentation management and use."
"Methods for cleaning electronic components and subassemblies."
"Minimax control of large launch boosters."
"MSC/Apollo program management"
"NEXUS concept of a large reusable earth launch vehicle."
"Old Gainesville 1832–1875" Paper by Holt, Thad, 1876 -1955
"Operational Experiences on the Saturn V S-IVB stage."
"Opportunities for European Payloads on the Saturn Vehicle."
"Organization of a countdown"
"Philosophy and practices of reliability as applied in the design of the Saturn Instrumentation System."
"Practicalities in automated manufacturing checkout."
"Problems associated with large scale high pressure testing."
"Proceedings : second NASA-wide reliability & quality assurance meeting : NASA Headquarters, November 29 - December 1, 1966."
"Propulsion : the key to moon travel."
"Propulsion : the key to space travel."
"Recent NASA experience with hydrogen engines."
"Redundancy employing majority voting for a Saturn servoactuator."
"Reliability assessment of liquid rocket engines."
"Reliability engineering program provisions for Space System contractors. Revision 2."
"Rocket engine turbo pumps for space travel."
"Saturn I engine gimbal and thrust vector control systems."
"Saturn IB inflight photographic instrumentation system."
"Saturn instrumentation systems."
"Saturn system study II."
"Saturn V derivatives."
"Saturn V ground winds program."
"Saturn V space program and aluminum welding technology."
"Saturn Vehicle Cryogenic Programs."
"Selected methods for uprating Saturn vehicles."
"Survey of Saturn stage test and checkout computer program development."
"System engineering propulsion, III-C-1."
"Systems applications in orbital launch operations."
"Technical History of Saturn."
"Techniques of implementing launch automation programs" (Saturn IB space vehicle system).
"Telemetry system design for Saturn vehicles."
"Test procedure validation by computer simulation."
"The development of a bonded common bulkhead for Saturn."
"The development of a checkout language : ATOLL."
"The Development of Servovalves with Improved Reliability for Space Vehicles."
"The development of the Saturn system safety program."
"The history of Army missile development."
"The impact of manufacturing on design as related to accessibility."
"The Influence of Apollo/Saturn V Launch Operations on Lunar Site Selection: Case 330."
"The instrumentation of space vehicle in connection with the successful Saturn flight tests."
"The reliability of the all-up concept."
"The role of simulation in the development of an automatic checkout system"
"The use of wind shears in the design of aerospace vehicles."
"Thermal models of Jupiter and Saturn"
Convective Energy Transport in Stellar Atmospheres: A Convective Cell Model.
2409 Dairy Lane (Chapman Residence)
300 Gates (Weeden House/Museum) Restoration, "The Weeden House" by Milberger, Eric
515 Franklin (Erskine-DilworthHouse)
558 Franklin (Morgan-Neal-Wingiton House)
A "Think Clean" training program.
A Brief History of Huntsville
Baldridge Family
Beirne/Patton/Echols/Spragins Families
Bell Factory Paper (Found in Frances C. Roberts Files)
Bibb-Wyatt Genealogy
Brandon Family
Butler, James
Catholic Churches History
Chambers, Henry H.
Church of Nativity (Episcopal) "Fight the Good Fight" Paper
Church of Nativity (Episcopal) History
Church of Nativity (Episcopal) Sermons, Historical Sketch. 1930s
Clay Letters - copies, Duke MSS, 1842-1865
Concerning Lakeside Methodist Church - African-American
Darwin, Mattie
Development of LOX/RP-1 engines for Saturn/Apollo launch vehicles.
Erskine, Albert Russel
Fearn, Dr. Thomas
Fire Department Utilities
Fisk, Sarah Huff, Library
Frances C. Roberts' essay "The Romance and Realism of Monte Sano" and her notes
Frank James record book and miscellaneous notes, 1900 -1969
German Settlement in Huntsville by Frances C. Roberts
Handwritten Notes on Local Banking and Commerce
Hereford, Theodorick Matthews, Family History
Highlights of Madison County History
History of the Huntsville Daily Times - copies
History of the Newspapers of Huntsville, Alabama by Keel, Edna Arnette, 1812-1939
History of Walnut Grove Community
Huntsville Female College, Notes, Article Excerpt - reprint, 1940
Huntsville Schools Typed History (1 of 2)
Huntsville Street Plan, 1993
Irmgard Stuhlinger School Essays, 1934-1935
Irmgard Stuhlinger School Essays, from No. 15
Irmgard Stuhlinger School Essays, No. 1 to No. 13
Jones, George Washington, Jones Family
Lily Flagg, Famous Cow (1 of 2)
Madison County Politics, 1811 - 1955
Marshall Space Flight Center History
Mastin, Dr. Claudius H.
McCartney, Charles
Miscellaneous Family Notes
Monte Sano History by Monroe, D.C., 1925
Moore, Dr. David, and Copy of Frye Painting
North Alabama College
Northern Alabama Railroad History - copies
Notes Concerning Huntsville Schools
O'Neal, Edward
Otey, Octavia Wyche
Pope, LeRoy/Poplar Grove,1814
Publications and Brochures
Roberts, Frances C. Gainesville History Paper, undated
Saturn V management information : August 1964 : Volume VI.
Saturn V project development plan : November 1967.
Source credibility and personal influence in three contexts : a study of dyadic communication in a complex aerospace organization.
Steger History and Related
Stuhlinger, Ernst, 1992
The Hub of Rocket and Guided Missile Research
The Huntsville Female College
Transcript of Irmgard Stuhlinger School Essays, 1934-1935
Transcript of Irmgard Stuhlinger School Essays, from No. 15
Transcript of Irmgard Stuhlinger School Essays, No. 1 to No. 13
William Council Biography by Jones, Florence, undated
Withers, Dr. S. J.
Yeatman, Preston
Alternative Title
Select...
1-65-19
1370-60
67-WA/MGT-2
69-662
AIAA Paper No. 65-294
AIAA Paper No. 68-569
Douglas Engineering Paper No. 3511
Douglas Paper 3809
Douglas Paper No. 1814
Douglas Paper No. 4045.
IBM No. 67-U60-0015.
IBM No. 67-U60-0019
IBM No. 68-U60-0022
NASA TM X-53274
OAP - 143.
X-53572
Description
Select...
A man-in-the-loop computer facility has been created using a digital computer, display terminal,and space vehicle flight computer to enable programmers to check out flight programs in a simulated space flight environment. The simulation requires a real time multi-programmed environment, which is supplied by a control system capable of scheduling programs on 32 levels of priority interrupt as well as answering demands for service at the display terminal. A special interface device permits visibility and control of the flight program as it executes in the flight computer. On-line inputs from the programmer at the display terminal and outputs from data collection and reduction routines to the display screen are executed in real time. The Flight Software Development Laboratory has proved to be very useful in reducing program preparation time and increasing flight program confidence.
A number of considerations are necessary in instrumentation programming, many of which are either not applicable or applicable to a lesser degree in other types of programming. This paper discusses these problems in general terms and illustrates how they have been dealt with specifically. The latter is done by describing the programming and operation of a data reduction system.
A Part of the development of the Saturn S-IV/S-IVB stage the Douglas Aircraft Company has pioneered in the development of the cryogenic common bulkhead. The term common bulkhead is derived from the design function of the bulkhead, which is to separate the two cryogenics, liquid hydrogen and liquid oxygen, in a single tank, thereby shortening the stage and eliminating the necessity for two separate bulkheads and the associated interstage structure. The common bulkhead is structurally adequate to withstand both the thermal and the pressure loads from both the hydrogen and the oxygen tanks, and it has sufficient insulation properties to prevent the liquid hydrogen from freezing the liquid oxygen. Another benefit from the common bulkhead is that it permits a reduction in the total length of the vehicle, thereby reducing the bending moments.
Abstract to "A thesis submitted to the faculty of Purdue University fo Gary Marshall Richetto in partial fulfillment of the requirements for the degree of Doctor of Philosophy, January 1969".; Handwritten note on front page: Return to Internal Communication, Room 223, 4202.
Addresses improving spacecraft safety by resolving various known dynamic problems.
AIAA Second Annual Meeting, San Francisco, California. Discusses the fabrication process of the Saturn S-IC booster.
Aspects of Earth-to-orbit delivery are discussed and a cost analysis of the logistic operation and the cost of orbital operations are presented. Probabilities of success of orbital delivery and the operational and economic aspects of establishing large orbital installations and maintaining a large transportation volume in the 1975/85 time period are compared for the two cases using a large number of Saturn V versus a smaller number of 1-stage chemical Post-Saturn launch vehicles. Performance parameters of chemical, chemonuclear and nuclear launch vehicles are compared. The concept of a blunt launch vehicle configuration referred to as NEXUS is presented in detail. Applications of this configuration to chemonuclear propulsion and to a 50 ft diameter version of Saturn V with recoverable first stage are discussed.
ATOLL was developed to fulfill the requirements for a common computer language that could be used by the test engineers for launch and factory checkout. "ATOLL" is the abbreviated name for Acceptance, Test, Or Launch Language.
Churches
Considerations for improvement in the reliability of the Saturn engine gimbal servosystems are briefly covered. The Saturn I servovalves operate with increased electrical input power. The Saturn V vehicle stages will use mechanical feedback actuators with increased electrical input power, larger orifices and nozzle sizes, larger torque motor wire size, and greater spool driving forces.
Contains a correspondence between Richard Holland and Frances C. Roberts regarding unspecified editing suggestions to a tourism booklet. Contains tourism booklet in essay-form.
Corrosion problems associated with space vehicles, in general, are discussed as contrasted to those problems experienced with structures in an earth atmosphere. Primary emphasis is placed on structural alloys in this discussion, although some corrosion failures experienced in various mechanical components are described. General corrosion prevention measures are indicated, and solutions to specific corrosion failures described. Major failures experienced have been attributed to stress corrosion cracking, rather than general or galvanic type corrosion. Most such failures have occurred with only five different materials: three aluminum alloys - 7075-T6, 7079-T6, and 2024-T6; and two precipitation hardening stainless steels - 17-7PH and AM 355. Corrective actions were different in each case, but involved either a complete change to another material, a change to a different temper of the same alloy, or a modification of the heat treatment and/or general processing techniques. General conclusions are that the types of failures described could be avoided by: a more suitable selection of alloys in the initial design, a realistic review of the environments that could be encountered in the service lifetime of the component, lowering stresses, improving process controls, and effecting better familiarization of design personnel with the with the overall stress corrosion problem in an effort to reduce human error.; Preprint 18e.; Materials for re-entry and spacecraft systems - spacecraft materials.; Materials Conference, Philadelphia, Pennsylvania, March 31 - April 4, 1968.
Cover has: P. D. Castenholz and H. K. Griggs, Advanced Systems, Advanced Projects Department. D. W. Hege, Manager, Advanced Projects. Paper regarding the importance of propulsion technology and the future missions that would require advancements in that field.
Digital computer simulation of the Saturn I Instrument Unit electrical networks was accomplished using the Discrete Network Simulation programs. The schematics were analyzed and a logic model prepared which consisted of a series of Boolean equations. The test procedures, which are written in the Acceptance, Test, or Launch Language (ATOLL), consist of a sequential set of computer instructions for the RCA llOA checkout computer to control the operation of the electrical networks. The procedures also contain the predicted results for each operation. The driving functions for the simulation of the model are generated from the ATOLL test tape by the Input Generator Program. The time sequenced operation of the networks is indicatedby the output from the simulation program in addition to the number of times each component in the system changes state. The results of the simulation are compared to the test procedure predictions on the ATOLL tape by the Comparator Program and any differences are listed. The Comparator Program also lists any component which did not change state at least once.
Discusses the importance of redundancy as a safety measure in electronic systems.
Draft of working paper. Typed with handwritten notes (title and author) and pages. Copy in MSFC files noted on first page.
During long coast periods of zero-gravity, storage vessels for the cryogenic liquids proposed for use in some power transmission systems undergo random distribution of the liquid and vapor phases therein. Thus, when heat flow into the vessel causes the vessel pressure to build-up requiring venting to maintain a safe value, the likelihood of venting the valuable liquid phase, as well as the vapor, results. To preclude this eventuality, various devices for separating the liquid and vapor phases and venting just the vapor have been studied and carried into the experimentation stages.
During the development of the RL-10 and J-2 engines, many problems were encountered. Solutions to the significant problems are contained. A description of these LOX-Hydrogen engines, outlining the unique features of each will be given. Performance parameters for both engine systems are tabulated. Specific applications to various stages are shown.
Essay detailing the relationship between men and machines."
Essay that focuses on the achievements of the Grumman Aerospace Corporation.
Families
Finding the turbopump arrangement which is best suited for a given rocket engine - space travel applications - constitutes an important task. The arrangement depends upon a large variety of different factors, such as, the engine cycle, weight, the liquids to be pumped, the cavitation performance, the bearings and their lubrication, the seals and the turbine. In this report these factors and their influence on the turbopump configuration are discussed. It is shown that three of them: weight, propellants to be pumped and obtainable suction performance have the largest influence on the selection of the turbopump. A systematic approach is outlines for the design process, which allows to arrive at a turbopump arrangement best suited for a given application.
For publication in Luftfahrttechnik Raumfahrttechnik. Discusses the uses and advantages to using simulations.
Helium is used extensively throughout the Apollo/Saturn V space vehicle for a number of applications. The welding use is not discussed since it is a special topic. In the first stage (S-IC), helium is used for liquid oxygen tank pressurization during vehicle checkout and launch.
Houses
Hydrogen embrittlement of steels is hardly a new subject, but the effects of high-pressure hydrogen have been treated in detail only more recently and to a much more limited extent. Thus, most investigations of hydrogen embrittlement have been concerned with hydrogen in metals, while for the high-pressure hydrogen problem, we are more concerned with metals in(in contact with) hydrogen. I believe there is a difference and, certainly,different mechanisms of embrittlement are at least possible.; Presented at the Central Florid Section, American Welding Society, Orlando, Florida, 14 November 1967 and North Alabama Chapter, American Society for Metals, Huntsville, Alabama, 16 November 1967.
In April of 1960 the Douglas Aircraft Company was awarded a contract to develop the second and uppermost stage for the Saturn I space booster. In order to realize the high specific impulse available, this stage, called the S-IV, was to utilize liquid hydrogen and liquid oxygen as the propellants. After burn-out of the first stage, the S-IV Stage was to ignite its engines at an altitude of approximately 200,000 feet, burn for approximately 8 minutes, and inject a 20,000 lb spacecraft into a low earth orbit. This program represented Douglas's first major endeavor with liquid hydrogen. It was necessary to develop an insulation for the S-IV Stage that was capable of withstanding the thermal shock associated with loading, could provide adequate insulative properties to limit the flow of heat into the hydrogen, and was of minimum weight. This latter fact cannot be over emphasized because every extra pound of insulation is one less pound of available payload weight.
In describing the cleaning of electronic components and subassemblies, it must be taken into consideration that each part to be cleaned presents an individual problem. The method of cleaning must be tailored to the type of part to be cleaned as well as to the type of soil to be removed. This paper reviews some of the methods used in cleaning electronic arts, particularly printed circuits, as well as other critical hardware which is used in support of electronic assemblies. Some of the methods covered include the use of abrasives, acids, solvents and alkalies, and the employment of these in combination with ultrasonic and other automatic systems. The clean room in use at IBM Huntsville is described briefly, along with the solutions and solvents used in cleaning electronic and supporting parts. Cleanliness- requirements for the area and the materials, together with procedures for meeting them give added emphasis to the critical nature of today's contamination control programs. The paper concludes with a summary of the cleaning procedures and the cleanroom benefits to be obtained by using present day technologies to improve them.
In the Saturn IB/V programs the sheer quantity of data required for computer processing and ESE display makes it necessary to provide an efficient data acquisition system. For much of the data originating in the launcher this requirement is satisfied by the Ground Digital Data Acquisition System (DDAS). This paper provides a technical description of the Ground DDAS with emphasis placed on the unique design concepts of this telemetry system.
Includes bibliographical references.; Original format: paperback book (42 pages); Cover title: Resources for freedom : the outlook of energy resources, volume III. Contains plans and analyses of potential future energy sources.
Includes handwritten notes. Includes references to slides. Essay remarking on how space vehicles will interact on the moon's surface.
Incomplete document. Displays errors in space-vehicle design as they relate to space travel.
Irmgard Stuhlinger was the wife of Ernst Stuhlinger, a scientist acquired in Operation Paperclip. In these school essays, she discusses her daily life in Stuttgart, Germany, as a child. When writing these essays she was 8 years old. Some of the topics include a letter to family members, Christmas, descriptions of the weather, and talking about field trips.
Irmgard Stuhlinger was the wife of Ernst Stuhlinger, a scientist acquired in Operation Paperclip. In these school essays, she discusses her daily life in Stuttgart, Germany, as a child. When writing these essays she was 8-9 years old. Some of the topics include letters to family members, a fictional story, Christmas, descriptions of the weather, and talking about field trips.
Irmgard Stuhlinger was the wife of Ernst Stuhlinger, a scientist acquired in Operation Paperclip. In these school essays, she discusses her daily life in Stuttgart, Germany, as a child. When writing these essays she was 9-10 years old. Topics of the essays include family life, a fictional moral story, descriptions of the weather, as well as significant historic events such as the Saarabstimmung (1935 Saar status referendum). Furthermore, she mentions Adolf Hitler (German chancellor) and the Sturmabteilung (Paramilitary organization run by Nazi Germany) in these essays. In this collection, she includes an illustration with each essay.
Irmgard Stuhlinger was the wife of Ernst Stuhlinger, a scientist acquired in Operation Paperclip. In these school essays, she discusses her daily life in Stuttgart, Germany, as a child. When writing these essays she was 9-10 years old. Topics of the essays include family life, a fictional moral story, descriptions of the weather, as well as significant historic events such as the Saarabstimmung (1935 Saar status referendum). Furthermore, she mentions Adolf Hitler (German chancellor) and the Sturmabteilung (Paramilitary organization run by Nazi Germany) in these essays. The transcript includes a description of each illustration.
Keith D. Graham is principal mathematician, Systems and Research Center, Honeywell, Inc., 2345 Walnut Street, St. Paul, Minnesota.; Work done under NASA contract NAS 8-11206 from the George C. Marshall Space Flight Center.; ABSTRACT: A method of specifying the gains of a linear controller for a large launch booster using a new application of optimal control theory is described in this paper. Results for a specific example are included. An important control requirement is to maintain cost variables (such as bending moment, engine gimbal deflection, and lateral deviation from desired trajectory) within specified limits in the presence of load disturbances. This requirement is met by using a performance index which depends explicitly on maximum achievable values of the cost variables in a finite time interval.
Libraries
Material-propellant compatibility as related to liquid rocket propulsion system design criteria is discussed and applicable test methods to derive usable design data are presented. Test methods, with emphasis on metallic materials, are discussed and the shortcomings of a number of these test methods are pointed out. These tests include static immersion tests, stress-corrosion tests, flow tests, impact tests, and tests to determine the effect of cracks and notches in metals on compatibility. A general outline for the evaluation of metallic and nonmetallic materials with respect to propellant compatibility is presented.
NASA and MSFC
One of the orange Aid Preprint Series in Nuclear Astrophysics by W. B. Hubbard, California Institute of Technology, Pasadena, California.; Argues that the Saturnian models are flawed as their predictions do not line up with detected gravitational events.
One of the Orange Aid Preprint Series in Nuclear Astrophysics, September 1968.; Supported in part by the National Science Foundation [GP-7976], the Office of Naval Research [Nonr-220(47)]. ; ABSTRACT: The motion in a convectively unstable region is expanded into an ensemble of convective cells. Each of these cells interacts with the surrounding medium according to the semiempirical model proposed by Turner (1963 ). Possible detailed models of the flow patterns within each cell are presented. The radius and velocity of these cells are given as functions of distance moved. The convective flux and rms velocity are given as averages over the ensemble of cells. As in the standard mixing length theory the principle uncertainty remains the average initial radius of the cells.
Only the cover page is present in the online resource. The rest is restricted.
Page numbering is inconsistent; there are no pages numbered 14 - 17. Some pages have handwritten numbers, others have no numbers at all.; The print quality of many pages is poor. Discusses the definition and function of propulsion as well as how to most effectively employ it .
Paper detailing the problems identfified in high pressure testing.
Paper focusing on past and future moon missions. Contains graphics of rockets and modules
Paper from the 1965 Cryogenic Engineering Conference at Rice University, Houston, Texas, paper K-4. The abstract states, "This paper covers the cryogenic propellant and gaseous application to the George C. Marshall Space Flight Center Saturn Programs. Emphasis is placed on the overall application and the resultant logistic considerations. The planning of facilities, storage, and transportation required to ensure an adequate supply of cryogenic fluids when needed is traced from the engine and stage requirements. The entire cycle of technical requirements, estimating the quantities required from production and management of the program is developed, spacecraft application and other trends that affect cryogenic production are reviewed."
Paper given at the American Ordnance Association Welding Section Panel. Focuses on the process of welding and development programs.
Paper given to North East Chapter , Mississippi Society of Professional Engineers. Essay discussing the history of the MSFC Reliability Philosophy.
Paper regarding the actions and achievement of the Grumman Aerospace Corporation.
Paper to be presented at the IAS National Meeting on Manned Space Flight. Focuses on operations leading to injection of the space craft into the lunar transfer trajectory.
Paper to be presented at the Third International Flight Test Instrumentation Symposium College of Aeronautics. A brief description of the Saturn vehicles is given, delineating the makeup of and differences between the Saturn I, Saturn IB, and Saturn V.
Parks
Prepared by R. L. Parkhill, Section Chief, Saturn S-IVB Reliability Analysis and J. Pauperas JR., Asst. Section Chief, Saturn S-IV Reliability Analysis. Presented to the 4th Annual Seminar on Reliability for Space Vehicles, Los Angeles, California, December 6, 1963. This paper presents techniques originated by Douglas Engineering working under NASA contract NAS7-1. Prepared as a record of the study conducted for the Administrative Engineer on the Department Overhead Account No. 9703.; SUMMARY: In today's complex systems, such as Saturn, many traditional reliability analysis concepts are not acceptable. Because of time and budget restrictions, and the requirement to provide a "man rated" space vehicle, the Douglas Saturn Engineering Reliability Section has developed a new analytical approach; it is called "criticality ranking". It is a "totem pole" of components whose single failure may lead to system loss. "Criticality ranking" is one of the results of an analytical model which encompasses failure effect and reliability prediction. This paper describes this analytical model, discusses some of the techniques and ground rules, and presents examples. A discussion of the application of the results is also included.
Prepared for George C. Marshall Space Flight Center, Huntsville, Alabama under contract NAS8-11087. Publication No. 294-02-12-440. Special Technical Report No. 13.; INTRODUCTION: The Saturn/Apollo Systems Office at the George C. Marshall Space Flight Center (MSFC) requested ARINC Research Corporation to make a brief study of the reliability aspects of the All-Up concept. Under the requirements of Task 294-02 of Contract NAS8-11087, the study included a comparison between the reliability of the first Saturn V vehicle if All-Up, and its reliability with dummy upper stages.
Prepared for National Aeronautics and Space Administration, George C. Marshall Space Flight Center, Huntsville, Alabama. Accepted by V.C. Sorensen, Chief, Management Services Office. Management Services Project, RCA; SUMMARY: The objective of this study is to describe a comprehensive plan for the development and full utilization of methods and means to be employed in the years prior to 1976 for the effective acquisition, collection, storage, retrieval, distribution, and use of engineering documentation. Because of the violently changing state of the art of data acquisition, storage, and retrieval the description of the plan does not embrace the details of a total decade of phased change. Rather it describes actions that can and should be taken in the relatively near future, and proposes a continuing series of later studies to keep this plan current for the full decade.
Prepared for presentation at the 23rd Meeting of the Structures and Materials Panel, AGARD, October 4-11,1966, ONERA, Paris, France.; ABSTRACT: The relative influence of various wind profile properties and disturbances on launch vehicle flight dynamic response is studied. Particular emphasis is placed on the influence of wind shears and turbulence on dynamic response during the boost phase of the flight. Four hundred and seven individual detailed (Jimsphere) wind profiles are the primary wind inputs for this analysis. Time response of the vehicle to each profile is computed and a statistical evaluation of the results made. Results are obtained for the Saturn V space vehicle and conclusions drawn as to the relative influence of wind shears and turbulence vs the degree of refinement of the dynamic model of the space vehicle.
Prepared for presentation to the Eurospace Conference. In this paper, we will not deal with the first two questions, which must be of interest to every potential experimenter, but only with the last question of vehicle availability.
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 .
Presented at the 6th West Coast Reliability Symposium, University of California at Los Angeles, Los Angeles, California, 20 February 1965.The development of a large liquid rocket engine can represent the expenditure of several hundred million dollars of effort. Before 30 percent of the contracted development funds have been expended, however, the engine will probably have operated for the mission duration. The capability to operate at least one successful test early in a development program is evidence of achieving a minimal reliability level, but the major objective of the development program is producing a design which performs reliably. A rocket engine reliability prediction must view reliability as a dynamic concept, constantly being altered by development effort.
Presented on September 21, 1962, at the Eleventh Tagung Der Deutchen Raketen - Gesellschaft, Koblenz, West Germany. Instrumentation sf the Saturn space vehicle represents a considerable effort during the development phase, for proper design evaluatian of this new configuration, its propulsion system, and its structure and control characteristics, an unprecedented number of measurements are required to be carried onboard and to be recovered, These measurements are expected to work properly and to furnish the design engineer with information that is not available by ground testing,
Presented to Society of Automotive Engineers, Advanced Launch Vehicle & Propulsion Systems. When the Apollo lunar landing project is complete, the Saturn and Apollo hardware will only have begun to realize their ultimate potential for space exploration. The immense reserve of Apollo technology, facilities, and booster capability can then be directed to the achievement of national goals which lie far beyond the initial lunar landing. In achieving the Apollo lunar objectives, large investments will have been made in launch facilities, tracking systems, propulsion techniques, reentry systems, lunar landing systems and rendezvous technologies. Although developnent in these specialized areas has been tailored to the needs of Apollo, numerous studies by NASA and industry have demonstrated the feasibility of using the spacecraft, launch vehicles, and operating techniques for missions far more complex than lunar landings. Amortization of this hardware will prove cost-effective for missions of more sophisticated applications.
Prior to acceptance of a liquid rocket engine for use in Saturn vehicles, the average thrust of two consecutive tests without an intervening calibration must satisfy specification requirements. The contractor may recalibrate after the first and subsequent tests if he so chooses, based upon decision limits, until the above requirement is met.
Proposed for the 10th National Symposium on Reliability & Quality Control. This paper will deal with various techniques of treatment of such data and associated graphic displays.
Published as "Army Missile Development," Army Information Digest, XI. Establishes the development and history of weaponized rocket ordenance.
R-ASTR-NF.; ABSTRACT: The servoactuator was developed to improve the reliability of the Saturn S-IVB thrust vector control system by insuring continued system operation if single point failures occur. The selection of the majority voting technique is discussed. Its simplicity is cited along with the advantages of minimum weight, size, power consumption, and compatibility with existing control electronics. Operational features, design mechanization, and the analysis of test results are covered.
Redstone Arsenal (RSA)
Safety Engineering, as applied to complex missile and space systems, has developed a new methodology referred to as "System Safety Engineering." The requirement for a comprehensive approach to safety which is included as a contractually covered adjunct to the design, development, and operational phases of a systems life cycle has become apparent from costly missile mishap experience. The general concepts and accomplishments of this new engineering discipline are described along with possible beneficial relationships with Reliability and other recognized organizational elements engaged in safety related activities.
Schools
Study regarding the three-stage carrier vehicle E-1 engines.
The Army medical contract, grant, and research interest in the bio-science area.
The basic engineering approach used in the Saturn instrumentation system has evolved to provide a highly reliable design for short periods of operation. The airborne measuring and telemetry systems including preflight tests, inspection, documentation, and feedback between the users and designers are discussed. The apparent differences between the practice and theory of reliability are rationalized. Some consideration is given to new problems in designing systems that must operate in hostile environments for long periods. The potential contribution of redundancy as a design concept is discussed.; This paper is concerned with the airborne measuring and telemetry systems; it does not attempt to treat the entire Saturn instrumentation system which consists of tracking devices including optical, radar, and Doppler, plus television, film cameras, and a myriad of instruments connected with factory checkout, ground test, and launch.
The concept on Saturn V was to "budget" an amount for the dynamic portion of the wind load as a factor on the steady state drag. Wind tunnel tests paralleled the development and fabrication phases. The results indicated that the system was unable to withstand the design winds; thus, a decision was made to implement a viscous damper "fix" on the facility vehicle at the Kennedy Space Center. Damping tests in the Vertical Assembly Building (VAB) will have been completed and response tests on the pad will be in progress at the time of this symposium. This paper will present the history and status of this program to date.
The development of liquid rocket engines follow similar patterns regardless of engine size. During the development of the H-1 and F-1 engines, many problems were encountered. Methods of solving the combustion instability problem are discussed. A description is given of the major components of each engine, outlining their unique features. The requirements for an insulation cocoon are discussed. Problems associated with materials substitution are provided; also highlighted is the fact that problems occur after engine deliveries and require continued development support. Safety features incorporated on the engines are mentioned. Solution to problems encountered in flight are discussed. Upratings of both engines systems are presented graphically.; On the NASA Technical Reports Server (NTRS) unclassified. Can also be found on AIAA.
The development of liquid rocket engines follow similar patterns regardless of engine size. During the development of the H-1 and F-1 engines, may problems were encountered. Mehtods of solving the combustion instability problem are discussed.; AIAA 4th Propulsion Joint Specialist Conference, Cleveland, Ohio, June 10-14, 1968.; Also available on NASA Technical Reports Server (NTRS) as unclassified. Can be ordered. Also on AIAA.
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."
The hydraulic systems for the two-stage block II Saturn I vehicle are described with the evolution of their development.
The management techniques described in the paper support the Saturn S-IVB Program which is being conducted for the National Aeronautics and Space Administration, Marshall Space Flight Center.
The objective is to examine the technical requirements and feasibility of conducting orbital launch operations with systems now in the development phase. In order to maintain realistic constraints on the analysis, the Saturn S-IVB stage has been used as an example of present stage technology. The requirements, procedures and complexity of operations for orbital assembly and launch are discussed. The primary design requirement for orbital assembly and launch operations is increased orbital stay time (from hours to days or weeks).
The objective of this study is to describe a comprehensive plan for the development and full utilization of methods and means to be employed in the years prior to 1976 for the effective acquisition, collection, storage, retrieval, distribution, and use of engineering documentation. Because of the violently changing state of the art of data acquisition, storage, and retrieval the description of the plan does not embrace the details of a total decade of phased change. Rather it describes actions that can and should be taken in the relatively near future, and proposes a continuing series of later studies to keep this plan current for the full decade.
The Organization of a Countdown was developed over 8 years of missiles and space systems testing at the Douglas Aircraft Company, Sacramento test Center. The experience on which this study was based includes the Thor development and acceptance testing, Titan I second stage engine development testing, Development of liquid hydrogen handling techniques, Saturn S-IV and S-IVB development and acceptance testing. The intent of this paper is to examine the static test countdown organization and discuss the need for a systematic method to organize a countdown.
The papers presented at the second NASA-Wide Reliability and Quality Assurance Meeting are published to disseminate current experiences and information. These papers, presented at NASA Headquarters on November 29 - December 1, 1966, are one means of exchanging current NASA reliability and quality assurance knowledge between projects and programs. This publication has been marked "FOR NASA USE" since it contains management opinions and contract experiences. Publication of papers suitable for wide dissemination in the Government, industry and University community is expected to be made separately. John E. Condon, Director, Reliability & Quality Assurance.
The purpose of this document is to describe how the Manned Spacecraft Center is managing its responsibilities in the Apollo Program The organization, procedures, and management philosophy described herein, represent the accumulated knowledge gained from our experience with the Mercury, Gemini, and Apollo Programs. It should be remembered, however, that managing a research and development program of Apollo's size and complexity, is an experimental "R&D" process in itself.
The purpose of this paper is to emphasize the need for accessibility in the assembly and maintenance of spacecraft. This is especially pertinent because accessibility to subsystems for replacement, repair, and maintenance has proven to be one of the more costly phases of preflight preparation. The most successful programs in this day and age have been when the design and manufacturing engineers work side by side around a mockup where solutions to the problems can be visually seen and solved, keeping in mind the assembly as related to accessibility. Therefore, it will be shown that in order to overcome the difficulties, designers should adapt a hard, fast ground rule that each unit must be accessible and individually removable without disturbing the other units.; Aeronautic and Space Engineering and Manufacturing Meeting, Los Angeles, Calif. Oct. 7 - 11, 1968.
The purpose of this paper is to present information, in the area of separable connectors as they pertain to the Saturn S-IV Program.
The rapid development of computer technology and the creation of new engineering oriented languages has established that general purpose digital computers are now extremely suitable to perform simulation of large scale physical systems. With Aerospace Vehicle Simulation (AVS), an effort has been undertaken at MSFC to simulate continuous and discrete dynamics of an aerospace vehicle and its ground support equipment on a large digital computer. This simulation produces a copy of the physical vehicle configuration and its functions in the form of a large scale mathematical model in the computer. AVS will be an essential part of an integrated information system which can be used by several laboratories and offices at MSFC for the design, checkout, test, and management of aerospace vehicles.
The vibration and acoustic environments of the S-IV and S-IVB Stages of the Saturn vehicle are summarized. A brief review of techniques used to predict the dynamic environments of the S-IV and S-IVB vehicles is presented. This review includes discussions on the prediction of rocket exhaust noise, boundary layer noise, sinusoidal vibrations, and random vibrations for the S-IV and S-IVB vehicles. In addition, sine-random vibration conversions are given.
This document contains copies of management charts maintained in the Managerial Data Center of the executive Staff on the Saturn V project. To facilitate use of this document, all Saturn V classified data has been removed and will be published in Volume XI. A list of these charts are shown on the "Table of Contents". Information on other MSFC activities will be published in separate volumes as indicated on the "Schedule for Publication of Data Bank Charts" contained in this volume.
This document revises and supersedes the Saturn V Project Development Plan, dated March, 1967. Approved: Arthur Rudolph, Manager, Saturn V Program; Samuel C. Phillips, Major General, USAF, Director, Apollo Program.
This document was cited in the Saturn contracts before NPC-250-1 was written. The sense of this document is the backbone of NASA reliability today and has become a generally accepted element of engineering rationale.
This folder contains the Old Gainesville paper by Thaddeus Holt, numerous photographs, paintings, papers and scripts.
This Internal Note presents the development of the Saturn inflight photographic instrumentation program from its original development requirement concept to the flight hardware application on Saturn vehicles. A comprehensive description of the infight photographic instrumentation system is given along with data concerning testing, operation, application, and evaluation of the system after recovery. This Internal Note shows that the system has been successfully developed,that valuable information has been obtained from film retrieved from recovered capsules, and that the system can be used with a high degree of reliability.
This paper desciibes an evolutionary family concept of !h turn V derivative launch vehicle systems, discusses their performance capabilities, and outlines their ability to perform orbital and hlgh-energy missions at minimum total program cost.
This paper describes a real-time digital computer program that controls the application of electrical power to the S-IVB stage of the Saturn vehicle at Cape Kennedy, Florida. Douglas Aircraft Company, the S-IVB stage manufacturer, provided NASA with the program requirements relative to the energizing sequence, voltage and current measurement tolerances, and vehicle system operational tests. International Business Machines Corporation provided NASA with the computer program to satisfy the task requirements. The program conjoined the components of the Electrical Support Equipment (two RCA 110A computers and control and instrumentation devices) into a closed loop system. The supporting operating system program by IBM is described.
This paper describes the major highlights or milestones passed in the development of a System Safety Program at MSFC since early 1967. it discusses accomplishments, problems resolved, and decisions made for Apollo Saturn vehicles AS-501 and AS-502, and projects that are to be accomplished on future Saturn vehicles.
This paper discusses five improved versions of the Uprated Saturn I that were studied by the Chrysler Corporation Space Division, supported by the Douglas Aircraft Corporation.
This paper discusses the data system requirements for large space vehicles and describes a flexible telemetry system design which is used on all stages of the Saturn IB and Saturn V vehicles. The basic vehicle telemetry design provides standard assembly building blocks forming a versatile catalogue of parts from which a stage telemetry subsystem may be assembled to meet almost any conceivable monitoring requirement. In addition to its inflight monitoring function, the telemetry subsystem also provides real time data acquisition for automatic vehicle checkout.
This paper discusses the flaws and limitations with welding technology, specifically with the techniques involved.
This paper discusses the possible applications of Saturn vehicles to future space exploration. Potential missions utilizing Apollo derived hardware are examined. Research, development, and operations in earth orbit as well as lunar exploration, unmanned and manned interplanetary exploration are reviewed. These hypothetical missions are discussed in the context of the present and potential capability of three configurations of the Saturn vehicle; an uprated Saturn I, a three-stage Saturn V and a four-stage Saturn V. NOTE: Work presented herein was conducted by the Douglas Missiles and Space Systems Division under company-sponsored research and development funds. Therefore, the concepts and objectives described within this paper reflect the opinions of the authors and do not necessarily constitute endorsement by NASA, the Air Force, or any other U.S. Government organization. The nominal performance numbers presented are typical of the current configurations and possible future vehicle configurations.
This paper identifies the methods and equipment through which automation is becoming a major factor in testing and launching Saturn IB space vehicles. The merits of a digital guidance computer and its impact in extending automated checkout are stressed; also a logical basis is established for computer and manual test control. Hardware and software elements of the automated system are described, and details pertaining to reliability are emphasized. A concluding appraisal suggests that automation will play an expanding role in future test and launch operations.
This paper outlines steps involved in preparing and presenting an instruction course on clean rooms. The training area, personnel, equipment, and program outline will be described. A summary of the results obtained over the first year of operation will be presented.
This paper outlines the major advantages of digital transducers and describes the principles and features (1) direct digital transducers, (2) indirect digital transducers, (3) quasi-digital transducers, and (4) A to D transducers.
This paper outlines the major advantages of digital transducers and describes the principles and features (1) direct digital transducers, (2) indirect digital transducers, (3) quasi-digital transducers, and (4) A to D transducers. The mutual effect of transducers and systems will be discussed briefly, and some trends of transducer research and development will be presented.
This paper presents a discussion on liquid propellant rocket engines. The first part contains a discussion on liquid propellants, including a description of various propellant types such as cryogenic, storable,bipropellant, and monopropellant. This part also points out desirable physical properties and includes a section on performance outlining the methods by which performance is calculated and shows performance for various liquid rocket propellant combinations.
This paper presents a light, but reverent, discussion of some of the Douglas operational experiences on the Saturn V/S-IVB stage. Certain relevant aspects of earlier work on the Thor intermediate range ballistic missile, the Saturn I S-IV stage, and the Uprated Saturn I S-IVB stage are also discussed.; Aeronautic and Space Engineering and Manufacturing Meeting, Los Angeles, Calif., Oct. 7 - 11, 1968.
This paper presents a number of solutions to a number of unanswered questions regarding the Saturn projects.
This paper presents a review of the experience which has accumulated in the development of the Liquid Hydrogen J-2 and RL10 rocket engines. These engines are being developed by the Rocketdyne Division of North American Aviation and Pratt & Whitney Aircraft, a Division of United Aircraft Corporation respectively.; On NASA Technical Reports Server (NTRS) as Unclassified; No Copyright; Unlimited; Publicly available. Also found on AIAA site.
This paper presents a review of the experience which has accumulated in the development of the Liquid Hydrogen J-2 and RL10 rocket engines. These engines are being developed by the Rocketdyne Division of North American Aviation and Pratt & Whitney Aircraft, a Division of United Aircraft Corporation respectively.; On NASA Technical Reports Server (NTRS) as Unclassified; No Copyright; Unlimited; Publicly available. Also found on AIAA site.
This paper presents in synoptic form, an analysis of the management problems being faced in making fuhlre manned spaceflight decisions. It is an attempt to view the manned space program in total perspective - its relationship to other scientific research, other national programs, the role of Congress, the President's role, industry's role, and then show their relative influence and impact on decisior, making for the Post-Apollo period.
This paper presents some relationships between Apollo/Saturn V launch operations and multiple lunar landing sites, including the means by which site selection could facilitate launch operations.
This paper will discuss selected methods for increasing the Saturn launch vehicle payload capabilities. These methods involve system changes or additions that give large step performance'increases aver those which can be obtained by product improvements. The selected philosophy of approach and the established designed systems wil1,be described, as well as anticipatedsystem concepts that may be used to increase the Saturn vehicles' capabilities.
This section contains information booklets from the National Archives and Records Service as well as correspondence, pamphlets and post cards from Alpine Cave.
This survey of the Saturn Stage Test and Checkout Computer Program Development contains a summary description of the systems developed for factory and static test of the stages of the SATURN IB and SATURN V Vehicles. The responsibilities of the MSFC and stage contractor organizations that are involved in test and checkout computer program development are briefly described. The test and checkout hardware and software (computer program) systems are given for each stage and for each site where tests are conducted. The systems and procedures that are used for program production verification, documentation, and change control required for the implementation of planned computer programs are included. Notes are included in the report to indicate what material is missing or incomplete. No attempt has been made to draw any conclusions regarding the automatic test and checkout systems being developed for each stage and the manner in which the efforts are organized, scheduled, and implemented. This document has been based on material provided by stage contractors and by components of MSFC through May 1, 1966. COMPUTER SYSTEMS SECTION. VEHICLE SYSTEMS INTEGRATION BRANCH. VEHICLE SYSTEMS CHECKOUT DIVISION.; SR-QUAL-66-3.
To be presented at the NASA / Rocketdyne Manufacturing Technology Review. Focuses on how best to avoid printed circuit boards.
Transportation
Utilities and Services
Creator
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Alpine Lodge
American Rocket Society
Anderson, Philip N.
Angele, Wilhelm
Balentine, R. C.
Bauer, H. E.
Beal, John D.. Jr.
Belew, Leland F.
Boden, Robert H.
Bodie, William G.
Bombara, E. L.
Bostwick, Leonard C.
Bromberg, Jack L.
Burks, A. J.
Casby, J. P.
Castenholz, P. D.
Chandler, W. T.
Clark, G. M.
Coronado, R. J.
Countess, Mary Bivins Geron
Craig, Ann B.
Davis, A. J.
Dearing, D. L.
Digesu, Fred E.
DiStefano, John F.
Drummond, Floyd M.
Ehricke, Krafft A.
Eley, C. H.
Farish, Preston T.
Felber, Henry D.
Fisk, Sarah Huff
Franklin, William J.
Frost, W. O.
Garrett, S. W.
George C. Marshall Space Flight Center
George C. Marshall Space Flight Center. Aero-Astrodynamics Laboratory
George C. Marshall Space Flight Center. Future Projects Office
George C. Marshall Space Flight Center. Managerial Data Center
George C. Marshall Space Flight Center. Research Program Office
George C. Marshall Space Flight Center. Test Laboratory
Gordon, Rex B.
Gordon, Theodore J.
Graham, Keith D.
Grayson, Isabel
Griffin, M. A.
Griggs, H. K.
Grumman Aerospace Corporation
Haigler, K. B.
Haire, John H.
Hassler, P.L.
Herman, B. J.
Heuring, Harvey
Heuring, Harvey F.
Hewett, Charles G.
Hoberg, Otto A.
Holland, Richard
Holt, Thaddeus
Hoppes, R. V.
Howard, Milford W.
Huffard, W. B.
Hughes, J. S.
Hunt, Robert M.
Jackson, T. T.
Jaegly, Robert L.
Jaekel, Haile H.
Johnson, Edith
Jones, Florence L.
Jones, John Rison
Kalange, M. A.
Keel, Edna Arnette
Kuehn, Ralph E.
Lacey, Marguerite
Lishman, Sidney H.
Lovett, Rose
Manitou Cave
Maroney, Marion Leach
Martin, C. W.
McFarlen, William T.
Meister, George F.
Meister, George F., Jr.
Milberger, Eric
Mitchell, J. R.
Monroe, D. C.
Mustain, R. W.
NASA Manned Spacecraft Center-- Manned Analysis Branch
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National Aeronautics & Space Administration. Office of Reliability & Quality Assurance.
National Archives and Records Service
Neiland V.R.
North American Aviation. Space and Information Systems Division
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Orillion, Alfred G.
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Parkhill, R. L.
Patton, F. T.
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Rorex, J. E.
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Sampson, Robert
Sapp, T. P.
Schuler, Albert E.
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Seader, J. D.
Seay, E. R.
Shields, Johanna
Shiozawa, Shiro
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Smith, J. D.
Smith, Robert L.(Robert Lee), 1924-
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Steinberg, Alvin.
Stewart, Rodney D.
Stuhlinger, Ernst, 1913-2008
Stuhlinger, Irmgard Lotze
Sumrall, Phil
Sutton, George P.
Tharratt, C. E.
Thayer, W. J.
The Gainesville Dispatch
The Radio Corporation of America
Toftoy, Holger N.
Truman, Harry S.
Ulrich, Roger K.
United States. Army Ballistic Missile Agency. Development Operations Division
United States. National Aeronautics and Space Administration
Wagner, William R.
Walker, R. D.
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Witzel, T. H.
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“Rocket City USA”
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Erskine, Alexander, Dr.
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Fort Payne (Ala.)
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Redstone Arsenal (Huntsville, Ala.)
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Stuttgart (Germany)
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The Huntsville Times
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United States. National Aeronautics and Space Administration--Management
V-2 missile
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Weeden House Museum (Huntsville, Ala.)
Weeden, Howard, 1847-1905
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Williams Street (Huntsville, Ala.)
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