Browse Items · UAH Archives, Special Collections, and Digital Initiatives

"Memorandum for General Ostrander."

Memorandum regarding a potential cost estimate for operational versions of the Saturn C1 and C2.

"Memorandum for the president: Responsibility and organization for certain space activities."

Memorandum discussing the responsibilities intended to be given to the President regarding certain space-related activities.

"Memorandum for the administrator."

Very poor photocopy. Memorandum requesting additional information regarding a file attached to this one.

"Memorandum to Mr. Horner from T. Keith Glennan, Administrator."

Memorandum discussing possibilities of obtaining or reallocating funding to speed up the 'super booster' program.

"Administrator's Statement on the Selection of a Contractor for the Saturn S-IV Stage."

engrsafeintomissspacsyst_070507103305.pdf

"Engineering Safety Into Missile-Space Systems."

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.

"Uses of Saturn."

Saturn and Apollo hardware will not have realized their ultimate potential for space exploration after the project lunar landing is complete. To accomplish the Apollo lunar landing program, an immense backlog of technology, facilities, and booster capability will have been built up, and we believe proper utilization of this resource will fill the needs for planetary, lunar and earth orbital space exploration for years to come.

"A survey of propulsion problems as related to space vehicle design."

Incomplete document. Displays errors in space-vehicle design as they relate to space travel.

"Opportunities for European Payloads on the Saturn 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.

"High Energy Missions for Saturn."

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.

EvolstepsinS-IVBdevelopment_061708170306.pdf

"Evolutionary Steps in S-IVB Development."

The injection stage of a multistage launch vehicle must be partially a velocity stage and partially a spacecraft; it must not only boost the payload, it must also perform cooperative mission operations with the payload after orbital insertion. These hybrid requirements result in intrinsic stage versatility which permits consideration of new and challenging missions for the stage which were unanticipated during initial design.; Prepared by T. J. Gordon, Director, Advance Space Stations and Planetary Systems, Space Systems Center, Douglas Aircraft Company, Huntington Beach, California.

"Minimax control of large launch boosters."

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.

"Payload integration for space experimentation."

Space experimentation requires an increasingly complex planning and systems engineering effort to meet the demand for highest precision and reliability of all measurements and observations. A companion paper discusses the interfaces between the scientific/technical areas of space experimentation and the instruments, subsystems and support systems within the spacecraft. This paper deals with the organization and the procedures which are needed to perform the difficult payload integration process for space experimentation. In the course of this process it is necessary to define the experiments completely, to describe all instruments in terms of engineering specifications, to investigate the commonality of equipment, to group the experiments into mission compatible payloads, to specify acceptable loads on all subsystems and astronauts (when present) and to plan for all contingencies during the flight.

Technical Reports" Bibliography.

Bibliography of technical reports from 1957-1963

phiandpraofrelasappinthedesofthesatinssys_013008103714.pdf

"Philosophy and practices of reliability as applied in the design of the Saturn Instrumentation System."

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.

"Liquid Rocket Engines."

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.

"The NASA/Grumman Apollo lunar module"

Handwritten in pencil on the document. Describes the layout and function of various sections of the Apollo lunar module.

"Structure of the NASA/Grumman lunar module."

Describes the structure and function of each part of the NASA Lunar Module

"Manufacturing history - LM-5."

Essay that focuses on the achievements of the Grumman Aerospace Corporation.

"LM System Description."

Report that describes the major systems of the Lunar Module.

"Development of the NASA/Grumman Lunar Module."

Paper regarding the actions and achievement of the Grumman Aerospace Corporation.

"Nuclear engine design considerations."

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.

Guidandcontrosatulaunvehi_080807145656.pdf

"Guidance and Control of Saturn Launch Vehicles."

The navigation, guidance, and control modes and problems of the Saturn launch vehicles are given as the requirements for the guidance and control methods. Two path adaptive guidance modes, featuring flight path optimization, in the form of a polynomial mode and an iterative mode are given in their computation form and compared with respect to mission flexibility, implementation requirements, and performance. Attitude control during the propelled flight phases requires consideration of various bending and sloshing modes; stability of the control system is obtained by phase stabilization of the low frequencies and by attenuation of the higher frequencies. Typical shaping networks and their transfer functions are given. The attitude control system during coasting periods is briefly described. The functional behavior and characteristic data of the main guidance and control hardware such as the inertial sensors, stabilized platform, digital computer, data adapter, control computer, and actuation system are described. Reliability requirements are emphasized. The principle of redundancy is extensively used to obtain highest reliability for long operating times. Data and results from recent Saturn I flights summarize the performance of the guidance schemes.

Briefing for Apollo 10.

This document contains a transcript of the briefing meeting for the launch of Apollo 10. Participants include George H. Hage, Colonel Thomas McMullen, and William J. O'Donnell.

"Nondestructive testing of space vehicle liquid propellant rocket engines."

Presented at the Western Metals Congress, Los Angeles, California, 15 March 1967.; Archive copy is a photocopy.; ABSTRACT: This report describes the various nondestructive test methods employed to evaluate materials and processes used in the manufacture of large liquid propellant rocket engines at the Rocketdyne Division of North American Aviation, Inc. The contents of the paper were purposely oriented for an audience of aerospace, design and materials engineers. A brief description of liquid propellant rocket engine reliability is presented. The relationship of standards and specifications to nondestructive testing is discussed and various test methods are described along with a discussion of their applications and limitations. The sequence of events leading up to the use of nondestructive testing in production inspection is presented. Finally, the organization of labor directly related to nondestructive testing is given.

"Manned Launch Vehicle Development."

Includes handwritten notes. Includes references to slides. Essay remarking on how space vehicles will interact on the moon's surface.

"Juno V Transportation Feasibility Study (U)."

The purpose of this report is to present an investigation to determine the feasible, practical and economical method of transporting the JUNO V thrust unit. This includes the first phase of transporting between Fabrication Laboratory, Systems Analysis and Reliability Laboratory and to the test stand, as well as the later phases, onto the Redstone Arsenal loading docks and from there down the Tennessee, Ohio and Mississippi Rivers to the Atlantic Missile Range, Florida.; Transportation and Packaging Section, Systems Support Equipment Laboratory.

Fabrofplentankbyexplformandelecbeamweld_111507104932.pdf

"Fabrication of Plenum Tanks by Explosive Forming and Electron Beam Welding."

This report presents the results of a program initiated to study the use of explosive forming and electron beam fusion welding techniques in the fabrication of pressurized cryogenic materials containers. Using these techniques, vessels were successfully formed from 304 stainless steel and X7106 aluminum alloy in the T63 condition.; Manufacturing Research and Technology Division.; Manufacturing Engineering Laboratory.; Research and Development Operations.

"Design and Use of Fault Simulation for Saturn Computer Design."

Describes different aspect of the Fault Simulation for Saturn computer design.

"Saturn and its mission."

Presentation from Harper, discussing the Saturn Project's then-status, background and plans.

theprooflartanforcryfue_071207131317.pdf

"The production of large tanks for cryogenic fuels"

Archive copy is a poor photocopy. Prepared for presentation at Deutsche Gesellschaft fur Raketentechnik und Raumfahrt. (German Society for Rocket Technology and Astronautics). Given by E. Harpoothian, Chief Engineer, Structures Department, Development Engineering.; Tanks for cryogenic fluids, as used in the Saturn space vehicles, have reached an advanced stage of design and development. Many of the structural features of the NASA/Douglas Saturn tanks, fabricated of 2014-T6 aluminum alloy, were first developed for the booster of the Thor ballistic missile, which later found extensive use in putting space vehicles into orbit. There is a mutual dependence of important factors related to design concepts, selection of materials, processing techniques, and fabrication methods. It is shown that this mutual dependence must be considered if a successful vehicle is to emerge from design and development. Details of vehicle structure, provision for insulation, and manufacturing methods are presented. Criteria for the selection of materials is shown to be dependent on strength, ductility, weldability, toughness, fabricability, behavior at cryogenic temperatures, and on manufacturing methods and inspection techniques.

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