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"Why internal insulation for the Saturn S-IV liquid hydrogen tank?."
Prepared for presentation at the Cryogenic Engineering Conference, Los Angeles, California, August 14-16, 1962.; There is no page 8. -
"Apollo Vehicle Propulsion Systems."
This paper discusses the propulsion requirements for various stages of the Apollo vehicles and the development of these engines. -
Telegraphic message containing an Apollo Program Flash Report.
This message for the Apollo Program Director contains a report of the Apollo launch vehicles, problem that occurred, and actions required. The photocopy is difficult to read. -
Telegraphic message containing an Apollo Program Flash Report.
This message for the Apollo Program Director contains a report of the Apollo launch vehicles, problem that occurred, and actions required. The photocopy is difficult to read. -
"Advances in Pumping Technology and Rocket Engine Turbopump Applications."
Presented by Charles A. MacGregor, Supervisor, Advanced Turbomachinery during Workshop D, Royce Hall, Room 160 at UCLA on 2 June 1964, as a part of the NASA-UCLA Symposium and Workshop on the Transformation of Knowledge and Its Utilization. The introduction notes, "This report is divided into two general parts. The first part is a description of turbopumps for liquid rocket engines as they exist today. For completeness and understanding, some background information is included on why turbopumps have evolved to their present configurations. The second part suggest portions of this effort that may have some applicability to the general economy." -
S-IVB cutaway and J-2 engine."
8 x 10 inch black and white diagram of the JII engine and the Saturn IV. -
"Saturn I : the first generation of heavy launch vehicles designed for peaceful exploration of space."
A basic description of the Saturn rockets alongside diagrams for context. -
"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%. -
"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.