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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    Titel :

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


    Weitere Titelangaben:

    NASA -- Tech Report


    Beteiligte:
    Smolak, G.R. (Autor:in) / Knoll, R.H. (Autor:in) / Wallner, L.E. (Autor:in)


    Erscheinungsdatum :

    1962


    Format / Umfang :

    92 pages


    Medientyp :

    Report


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


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

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


    Analysis of thermal protection systems for space vehicle cryogenic propellant tanks

    Smolak, George R. ;Knoll, Richard H. ;Wallner, Lewis E. | SLUB | 1962


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

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


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

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


    Lightweight Thermal Protection Systems for Space Vehicle Propellant Tanks

    Oglebay, Jon C. / Knoll, Richard H. | SAE Technical Papers | 1964