"Comments on Problems Relating to the Lunar-Landing Vehicle."
Saturn project
Lunar surface vehicles
"This technical note concerns some of the problems encountered with the landing of a payload on the moon. The main problem areas such as guidance, velocity control and impact considerations are discussed. Although no final conclusions or designs are intended, it is hoped that the material presented will serve as a guide for future detailed work."
Gardner, James P.
Ruppe, Harry O.
Straly, Warren H.
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
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Text
Technical Reports
Kennedy, John F. (John Fitzgerald), 1917-1963
Saturn 1 launch vehicles
Saturn 5 launch vehicles
A notation in the upper lefthand corner states "For the record: These are Dr. von Braun's comments to present to President Kennedy during his visit at Cape Canaveral, Fla., Nov. 16, 1963." A handwritten note is in the upper right corner. It appears that some of the pages to this document are missing.
Von Braun, Wernher, 1912-1977
Notes
"The Common Bulkhead for the Saturn S-II Vehicle: Unique Manufacturing Effort Adds to Space-Age Hardware Technology".
Design and construction
Liquid propellant rockets
Saturn S-2 stage
Bulkheads
Presentation regarding the construction of Apollo and Saturn rockets.
Cerquettini, C. Tony
Presentations
F-1 rocket engine
Combustion
The set of documents includes an introductory letter written by D. Brainerd Holmes and Tischler's report with the subject "F-1 Combustion Instability Report for Associate Administrator; Period March-April, 1963".
Holmes, D. Brainerd
Tischler, A. O.
Progress Reports
"Digest of FY-63 funded advanced studies : July 1966."
Astronautics--United States
George C. Marshall Space Flight Center. Research Program Office
This publication is, one of a planned series to summarize the advanced study program for each fiscal year beginning with FY-61. A separate report will cover the study program for each fiscal year. The purpose of these documents is to provide historical reference information which should be helpful in planning future study programs. The FY-63 funded studies are covered in this document. These investigations are covered under three categories: Launch Vehicle and Supporting Studies; Orbital and Lunar Studies; and Planetary Studies. The information presented on each study includes a brief description of the objective and results and pertinent contract data. In order to keep this report small and easy to use, no attempt was made to include conclusions based on the study results; however, the final reports documenting the investigations are referenced. If these reports are needed for permanent retention and are not available from the Technical Supervisor or the MSFC Library (MS-IPL), submit requests for the documents to the Scientific and Technical Information Facility, Attention: NASA Representative, P. O. Box 33, College Park, Maryland 20740.
Payne, William R.
Essay
"Digest of FY-62 Funded Advanced Studies : July 1966."
This publication is one of a planned series to summarize the MSFC advanced study program for each fiscal year beginning with FY-61. A separate report will cover the study program for each fiscal year. The purpose of these documents is to provide historical reference information which should be helpful in planning future study programs. The FY-62 funded studies are covered in this document. These investigations are covered under two major categories: Launch Vehicle Studies; and Lunar, Orbital, and Planetary Studies. The information presented on each study includes a brief description of the objectives and results and pertinent contract data. In order to keep this report small and easy to use, no attempt was made to include conclusions based on the study results ; however,the final reports documenting the investigations are referenced. If these reports are needed for permanent retention and are not available from the MSFC Library (MS-IPL), submit requests for the documents to the Scientific and Technical Information Facility, Attention: NASA Representative, P.0. Box 33, College Park, Maryland 20740.
Differences of configuration in successive Saturn IB and Saturn V vehicles- case 330.
Saturn launch vehicles.
Launch vehicle configurations
Saturn 1B launch vehicles
Includes memorandum for file. Configuration matrices reflecting present program status of differences in Saturn IB and Saturn V flight hardware on a mission to mission basis have been prepared. The attached matrices are arranged to show differences in major subsystems (Structures, Propulsion, Instrumentation and Range Safety, and Electrical) for each stage. The reason for the configuration difference and the mission effectivity are included.; DMD, 2031-SGE-eas, GRH; Includes "Recommendation for announcement and distribution of Bellcomm Report".
Bellcomm, Inc.
Memorandums
"Development Status for Arc Guidance, Weld Observation Systems, and a Review of Process Control Parameters."
Electric welding
Saturn launch vehicles
Saturn S-1C stage
Letter to David L. Christiensen from W. A. Wall, enclosing requested documents.
Wall, W. A.
Correspondence
"The Development of Servovalves with Improved Reliability for Space Vehicles."
Automatic control valves
Space vehicles
Servomechanisms
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.
Kalange, M. A.
Pollock, W. H., Jr.
Thayer, W. J.
Essays
"Development of the Saturn S-IV and S-IVB Liquid Hydrogen Tank Internal Insulation."
Liquid hydrogen
Liquid oxygen
Insulation
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.
Dearing, D. L.
North American Aviation. Space and Information Systems Division
George C. Marshall Space Flight Center. Test Laboratory
Development of LOX/RP-1 engines for Saturn/Apollo launch vehicles.
RP-1 rocket propellant
Apollo project
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.
Bostwick, Leonard C.
"Development of LOX/RP-1 Engines for Saturn/Apollo Launch Vehicles."
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.
"Development of LOX-Hydrogen Engines for the Saturn Apollo Launch Vehicles."
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.
Burks, A. J.
Development of LOX-Hydrogen engines_041207113632.pdf
"Development of Separable Connectors for the Saturn S-IV Stage."
Fluid transmission lines
Connectors
The purpose of this paper is to present information, in the area of separable connectors as they pertain to the Saturn S-IV Program.
Wilson, E. L.
Coronado, R. J.
Pierson, D. D.
"Development of the NASA/Grumman Lunar Module."
Paper regarding the actions and achievement of the Grumman Aerospace Corporation.
Grumman Aerospace Corporation
"Development Effort to Achieve Reliability."
Reliability (Engineering)
Space vehicles--Reliability.
Systems engineering.
Spacecraft reliability
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.
Clark, G. M.
Haigler, K. B.
"Development and Utilization of Computer and Test Programs for Checkout of Space Vehicles."
Computer systems design
Automatic test equipment
A computer system was designed to allow test engineers to progressively employ automation in the checkout of the Uprated Saturn I and Saturn V space vehicle programs and still allow manual control of the checkout process. A two-computer system was selected by National Aeronautics and Space Administration, and the International Business Machines Corporation was chosen to provide the programming engineering necessary to implement these objectives. Space vehicle checkout, prior to launch, may be characterized by controlling, monitoring, and testing the vehicle and its subsystems through the use of ground support equipment (GSE).; IBM Huntsville Library.; Presented at AIAA Conference, XVIIth International Astronautical Congress, Madrid, Spain, October 10-15, 1966 by Edward A. Robin, Manager, Vehicle Test Programming Department.
Robin, Edward A.
Design Analyses
"Design and Use of Fault Simulation for Saturn Computer Design."
Failure analysis
IBM computer
Logic design
Computerized simulation
Describes different aspect of the Fault Simulation for Saturn computer design.
Hardie, F.
Suhocki, R.
"Design of the Saturn S-IV Stage Propellant Utilization System."
Saturn S-4 stage
Describes the SIV vehicle and its components. Presented at: IRE International Convention.
Allen, D. J.
Bekemeyer, L. G.
"Design and Development of a 1,500,000-Pound-Thrust Space Booster Engine."
Research and development
Booster rocket engines
Describes the F-1 engine design and components.
Aldrich, D. E.
Sanchini, D. J.