Thermal environment of space radiator will vary widely during Earth-orbital mission; weight and area limitations make it undesirable to design for worst-case conditions; criteria for minimizing radiator capacity; through models, thermal environments were defined for complete range of ascending node locations and solar declinations for typical orbit inclination; radiator was sized for mission requirements and worst average heating orbit; transient performance of environmental control and life support (EC/LS) system utilizing this radiator design was evaluated in generalized computer program. (30888)


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    Title :

    Spacecraft radiator analysis


    Additional title:

    ASME Aviation Space -- Progress Prospects


    Contributors:

    Conference:

    ASME Annual Aviation and Space Conference ; 1968 ; United States , Beverly Hills, CA Heat problems



    Publication date :

    1968


    Size :

    9 pages


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English


    Keywords :


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