The paper describes in detail one of the preliminary baseline concepts for the solar power satellite (SPS). A large space freighter with payload capacity of 424 metric tons will deliver the material to a construction base in low earth orbit where the eight modules of the satellite are constructed. Electric thrusters will propel the modules to a smaller geosynchronous base, where the modules are docked and the solar arrays are deployed to form a satellite capable of providing 5 GW power from each of two end-mounted antennas to the two ground rectennas. The solar array is 5.3 km by 21.3 km to provide a total platform area of 113 sq km. The solar array employs silicon solar cells with a concentration ratio of unity. Details on transportation, construction bases, rectenna, and solar array design are given along with material requirements and cost estimates.


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    Title :

    The solar power satellite concept evaluation program


    Contributors:

    Conference:

    Radiation energy conversion in space; Conference ; 1978 ; Moffett Field, CA


    Publication date :

    1978-01-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English