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  • 1
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    Method and apparatus for suppressing ignition overpressure in solid rocket propulsion systems (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The transient overpressure wave produced upon ignition of a solid rocket booster is suppressed by providing within the launch platform, a plurality of pipes and spray heads disposed around the periphery of the exhaust gas plume near its upper end and spraying water into the upper end of the plume during ignition. A large amount of water, preferably equivalent in mass of exhaust products being ejected, is sprayed into the plume in a direction generally perpendicular to plume flow.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Molecular absorption cryogenic cooler for liquid hydrogen propulsion systems (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A light weight, long life molecular absorption cryogenic cooler (MACC) system is described which can use low temperature waste heat to provide cooling for liquid hydrogen propellant tanks for interplanetary spacecraft. Detailed tradeoff studies were made to evaluate the refrigeration system component interactions in order to minimize the mass of the spacecraft cooler system. Based on this analysis a refrigerator system mass of 31 kg is required to provide the .48 watts of cooling required by a 2.3 meter diameter liquid hydrogen tank.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 82-0830 , Joint Thermophysics, Fluids, Plasma and Heat Transfer Conference; Jun 07, 1982 - Jun 11, 1982; St. Louis, MO
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Mechanism associated with the Space Shuttle main engine oxidizer valve/duct system anomalous high amplitude discrete acoustical excitation (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Anomalous high frequency pressure fluctuations in the Space Shuttle main engine have been experienced during hot firings. Through diagnostic analysis of hot firing engine data, it was determined that this excitation originated at the main oxidizer valve. The intensity of these fluctuations was such that the main oxidizer valve was partially consumed in fire, experienced fretting, and had seal damage. Delineated in this paper are the associated dynamical phenomena and the methodologies leading toward understanding the excitation mechanism. The results presented demonstrate that the source of the anomalous frequencies was suppressed by a simple fix and all main oxidizer valve damage was terminated.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 80-0781 , Structures, Structural Dynamics, and Materials Conference; May 12, 1980 - May 14, 1980; Seattle, WA
    Format: text
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    NASA TECHNICAL REPORTS
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