Saturn project
Saturn launch vehicles--Design and construction
Saturn S-1C stage
AIAA Second Annual Meeting, San Francisco, California. Discusses the fabrication process of the Saturn S-IC booster.
Smith, Whitney G.
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
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Text
Essays
"Fabrication of Plenum Tanks by Explosive Forming and Electron Beam Welding."
Cryogenic tanks
Electron beam welding
Pressure vessels
Aluminum alloys
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.
Hamilton, L. O.
Memorandums
Earth orbital rendezvous
Interplanetary spacecraft
Mission planning
Moon
Apollo project
Saturn V launch vehicles
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.
Bromberg, Jack L.
Aircraft
North American Aviation, Inc.
Still Images
Organizational Charts
"Evolutionary Steps in S-IVB Development."
Saturn S-4 stage
Space vehicles--Design and construction
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.
Gordon, Theodore J.
Design Analyses
Illustration depicting the history of airplanes across a graph.
North American Aviation. Los Angeles Division
Diagrams
"Engineering Safety Into Missile-Space Systems."
Industrial safety
Space vehicles
System safety
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.
Gordon, Rex B.
Saturn S-2 stage
North American Rockwell Corporation. Space Division
Organizational chart diagram of the North American Rockwell Corporation Engineering division: 10-14-1968
Raiklen, H.
"Engineering Capabilities Presentation."
Aerospace industries
Project management
Aerospace engineering
This Engineering Capabilities Presentation lists the competence and capability that has been demonstrated by the Space Support Division of Sperry Rand Corporation while fulfilling contractual commitments in the aerospace industry. This is a preliminary presentation; the preparation of a complete capabilities history of the division is currently in the developmental stage. The Capabilities Experience Summary is comprised of ten categories. e.g. Category 1 - Aeronautics, etc. The capabilities reported herein were performed by the Space Support Division under Contract NAS8-20055 to the National Aeronautics and Space Administration, George C. Marshall Flight Center, Astrionics Laboratory, Huntsville, Alabama.
Sperry Rand (Corporation). Space Support Division
Presentations
Liquid propellant rockets
8 x 10 inch black and white photograph.; Images included are: A-3 oxygen-hydrogen, H-1 oxygen-kerosene, J-2 oxygen-hydrogen, F-1 oxygen-Kerosene, M-1 oxygen-hydrogen. The thrust pounds is also listed.Shows them in reference to a human as a scale.
George C. Marshall Space Flight Center
"Program Submission FY-1969: Electronics Systems."
Electronic equipment
George C. Marshall Space Flight Center. Research Program Office
United States. National Aeronautics and Space Administration
Program Submissions
"Historical Profile: North American Aviation, Inc."
History
Paper written as a study of functional management in NASA.
Historical Analyses
"Historical Notes on Oral History in NASA."
Prepared for the Second National Colloquium on Oral History, Columbia University. Contains notes on the oral history of NASA.
Emme, Eugene Morlock
Grimwood, James M.
Putnam, William D.
Laboratories -- Astronautics
A rocket from the George C. Marshall Space Flight Center will carry the first American to the moon, and the deadline is 1970. Because of the Center's expanding role in space, there are increasing requests for information about our activities. This brief historical sketch should help to answer questions about our past, our present, and our hopes for the future. Marshall Space Flight Center (MSFC) is the largest installation of the National Aeronautics and Space Administration (NASA). The Marshall Center is NASA's agency responsible for large space rockets and related research. MSFC employs about 7500 civil service employees with an annual payroll of more than {dollar}82 million. In addition approximately 4300 contractor employees work for MSFC on the Arsenal, earning an estimated {dollar}43 million. The Center occupies about 1800 acres near Huntsville, Alabama; in this large area are 270 buildings with floor space totalling about 4,000,000 square feet for a real estate and property value of about {dollar}325 million. MSFC's 1966 fiscal year budget was {dollar}1.8 billion. Obviously MSFC has much human and monetary worth behind United States round trips to the moon and beyond. In addition to its size, MSFC is unique because it has a large rocket development team with more than three decades of experience. Prior to the rocket work that dates back to Peenemuende [sic] the world heard little and cared less concerning rockets and space. As a group Marshall has always thought big. It has worked together as a group, and equally well with fellow scientists throughout the Free World, to get the most into space soonest. This is why there is increasing interest in larger and larger rockets and rocket programs from our Center, a fact generating more and more questions about our Center, and in turn generating a "workload" request for this sketch by the Historical Office. We hope that you enjoy our historical sketch, which could as well be entitled "Closer and Closer Views of the Moon and Beyond." David S. Akens, MSFC Historian.
Akens, David S.
"History of MSFC Reliability Philosophy."
Reliability engineering
Paper given to North East Chapter , Mississippi Society of Professional Engineers. Essay discussing the history of the MSFC Reliability Philosophy.
Beal, John D.. Jr.
"Highlights of General Electric's Participation in the U.S. Missile and Space Program."
Press release covering the system of functional management in NASA.
Scott, P. H.
Press Releases
Astronautics--United States
Research and development
Saturn 5 launch vehicles
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.
Wheeler, D. D.
"Helium Utilization in the Apollo/Saturn V Vehicle."
Helium
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.
Nunnelley, J. R.
Saturn 1B launch vehicles
Saturn 1 launch vehicles
H-1 engine
Data Sheets
"Guidance and Control of Saturn Launch Vehicles."
Launch vehicles (Astronautics)--Control systems
Launch vehicles (Astronautics)--Guidance systems
Navigation
Spacecraft guidance
Spacecraft control
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.
Haeussermann, Walter