UAH Archives, Special Collections, and Digital Initiatives

Browse Items (8239 total)

  • "Saturn V first stage annual progress report : fiscal year 1966."

    This report is the consolidation of D5-11994, "Quarterly Technical Progress Report," for the fourth fiscal quarter and the fiscal year 1966 Annual Progress Report and places special emphasis on activities on the fourth fiscal quarter.
  • "Saturn V derivatives."

    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.
  • "Saturn V Apollo lunar orbit rendezvous mission."

    Diagram explaining the process of a lunar mission from liftoff to recovery.
  • "Saturn V Apollo flight configuration."

    Diagram displaying the internal rooms, pieces and functions of the Saturn V as well as the space-suits of the astronauts.
  • "Saturn V Apollo Flight Configuration."

    Drawn by Don Sprague at the Huntsville Engineering section of Boeing.
  • "Saturn V America's moon rocket."

    Diagram that displays the Saturn V rocket with a page beneath detailing the function of each stage.
  • "Saturn V : non-stage procured launch vehicle ground support equipment."

    The functions, authority, management relationships, and responsibilities of the Launch Vehicle Ground Support Equipment Project Office are described. Functions and examples of non-stage procured Launch Vehicle Ground Support Equipment (LVGSE) are described and illustrated.
  • "Saturn television system for SA-6."

    The Saturn television system is an instrumentation device intended to provide visual information on vehicle performance in real time. The system covers the entire problem from the original image presented to the television camera to the presentation of the finished photographs for analyses.
  • "Saturn technical information handbook. Volume III of four volumes : SA-203."

    The "Saturn Technical Information Handbook" provides up-to-date reference material to the Launch Operations Center personnel. This material shows the assembly and operation of the Saturn Vehicle components for systems analysis.; Volume II is available on the NASA Technical Reports Server (NTRS) as a PDF.
  • "Saturn system study II."

    Study regarding the three-stage carrier vehicle E-1 engines.
  • "Saturn stages S-II : July 7, 1961 : Minutes of the phase II pre-proposal conference for stage S-II procurement."

    Transcription of a confrence aiming to propose ideas for new rocket designs. Includes references to slides.
  • "Saturn ST-124-M inertial guidance platform."

    a press release which focuses around the Apollo 9 flight and what role the ST-124-M inertial guidance platform has in it.
  • "Saturn SA-1 flight and its instrumentation."

    Presentation focusing on empahsising the importance of space programs such as Saturn.
  • "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.
  • "Saturn S-IVB quarterly technical progress report."

    Douglas Aircraft Company Report DAC-56445, 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 August and September 1966. This report is prepared for the National Aeronautics and Space Administration under Contract NAS7-101.
  • "Saturn S-IV first firing."

    Press release detailing the firing of the Saturn S-IV in California.
  • "Saturn S-IV engines."

    Folder of information.
  • "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.
  • "Saturn S-IV cryogenic weigh system. Part II : weigh operations."

    Two basic methods for mass determination are: (1) direct measurement, (2) volume and density determination. Both methods or variations have been used to determine space vehicle propellant mass with varying degrees of success. Stringent propellant loading accuracy requirements of k0.5 percent for the Saturn S-IV Stage have led to the development of a Cryogenic Calibration Weigh System. The method employs accurate electronic force transducers and measuring systems as the standard and experimental weighings have verified achievement of better than the required accuracy.
  • "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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