Analytical techniques presented permit calculation of heat transfer rates with various thermal protection systems for tanks subjected to on-board, solar, and planetary heat fluxes; effectiveness of systems in reducing propellant heating is shown for ideal heat transfer models and simplified hydrogen oxygen terminal stage used for typical Mars missions.


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    Title :

    Analysis of thermal-protection systems for space-vehicle cryogenic-propellant tanks


    Additional title:

    NASA -- Tech Report


    Contributors:
    Smolak, G.R. (author) / Knoll, R.H. (author) / Wallner, L.E. (author)


    Publication date :

    1962


    Size :

    92 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English




    Analysis of thermal-protection systems for space-vehicle cryogenic-propellant tanks

    Smolak, George R. / Knoll, Richard H. / Wallner, Lewis E. | TIBKAT | 1962


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    Analysis of Thermal-Protection Systems for Space-Vehicle Cryogenic-Propellant Tanks

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