Browse Items (8239 total)

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  "Saturn S-IV cryogenic weigh system. Part I : propellant utilization."

  In order to achieve maximum vehicle efficiency, it is essential that the vehicle propellants be loaded to desired values and that these propellants approach simultaneous depletion at the end of powered flight. To accomplish precise loading and assure minimum residuals, a highly accurate and repeatable, vehicle located, propellant management (PM) or propellant utilization (PU) system must be used. As the ability to load propellants to predetermined values depends directly on the ability of the system to accurately sense the propellant masses, it is essential that the system be calibrated with respect to propellant mass under conditions resembling those to be experienced during final loading and powered flight. The use of a cryogenic weight system will reduce the unknown factors in capacitance sensor element shaping, tank geometry, and propellant properties to a degree which will permit the determination of propellant masses to with .025%.
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  "Saturn S-IV cryogenic weigh system. Part IV : safety."

  During cryogenic weigh system operation, hydrogen when combined with oxygen can create an unsafe condition. Therefore the concentration of the residual oxygen and hydrogen from leaks in the cryogenic weigh environmental bags must be known at all times during the cryogenic weigh. Hydrogen and oxygen detectors will provide the optimum method for maintaining safe conditions. Hydrogen properties and safe mixtures are reviewed. The method selected to analyze the oxygen content is discussed. The selection, development, and testing of a hydrogen detector system is examined.
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  "Saturn S- II quality & reliability assurance : quality and reliability assurance" Organizational Chart.

  Organizational Chart of the Rockwell Corperation, 1968
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  "Saturn S-IVB quarterly technical progress report."

  Douglas Aircraft Company Report DAC-56533, Saturn S-IVB Quarterly Technical Progress Report, covers design and development progress on the Saturn IB and Saturn V configurations of the S-IVB stage during January, February, and March 1967. This report is prepared for the National Aeronautics and Space Administration under Contract NAS7-01.; Prepared for National Aeronautics and Space Administration under NASA contract NAS7-101.; Approved by A. P. O'Neal, Director, Saturn Development Engineering.
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  "Saturn launch vehicles : security classification guide."

  This security classification guide is a compilation of previous individual classification assignments. Consideration of international affairs, the use and development of advanced technological information, and requirements of flight safety have influenced these assignments.
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  "Saturn illustrated chronology : April 1957 - November 1962."

  Document detailing the history of the saturn project between April, 1957 through November, 1962.
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  "Saturn I/IB quarterly film report no. 26."

  Memo is from Chief, Program Management Information, I-RM-D.; The date and time of the interlock for the final I.O. approval is given.
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  "Saturn I flight test evaluation."

  As this paper is being written, the Saturn I flight test program includes five flights launched between October, 1961 and January, 1964. All five fiights were complete successes, both in achieving all major test missions and in obtaining an unprecedented volume of system performance data for flight analysis.
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  "Saturn IB/V instrument unit."

  This brochure provides some basic, general information about the lnstrument Unit, a very important part of the Saturn IB and Saturn V launch vehicles. These launch vehicles are being developed primarily for the Apollo program for manned lunar exploration but will also be used for future space missions.
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  "Saturn IB : presentation to Little Rock Group."

  Speech by H.D. Lowrey, SAE Meeting, Detroit, Michigan. Focuses on the Apollo project, the technology involved and what the goals of the project are.