Analytical techniques are presented that permit the calculation of heat-transfer rates with various thermal-protection systems for liquid-cryogenic-propellant tanks subjected to on-board, solar, and planetary heat fluxes . The effectiveness of these protection systems in reducing propellant heating is shown both for ideal heat-transfer models and for a 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


    Contributors:

    Publication date :

    1962-01-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




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

    Smolak, G.R. / Knoll, R.H. / Wallner, L.E. | Engineering Index Backfile | 1962


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

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


    Lightweight Thermal Protection Systems for Space Vehicle Propellant Tanks

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