Some of the more significant interactions between the radiator and vehicle of nuclear electric spacecraft are considered. This includes the selection of indirect versus direct condensing in the radiator; meteoroid armor and bumper criteria; booster constraints; aero shroud and structural integration; the significance of headers and feeds, electric transmission lines, and nuclear radiation shielding; and the magnitude of the structure contribution to system optimization. It is concluded that a conical or cylindrical radiator is the lightest and most generally applicable configuration from an overall system viewpoint.


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    Title :

    Integration of Large Radiators with Nuclear Electric Spacecraft Systems


    Additional title:

    Sae Technical Papers


    Contributors:

    Conference:

    SAE World Congress & Exhibition ; 1964



    Publication date :

    1964-01-01




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English







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