The 1 km diameter reflecting film surface is supported by a lightweight structure which may be automatically deployed after launch in the Space Shuttle. A twin rotor, control moment gyroscope, with deployable rotors, is included as a primary control actuator. The vehicle has a total specific mass of less than 12 g/sq m including allowances for all required subsystems. The structural elements were sized to accommodate the loads of a typical SOLARES type mission where a swam of these free flying satellites is employed to concentrate sunlight on a number of energy conversion stations on the ground.


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    Title :

    Conceptual design studies for large free-flying solar-reflector spacecraft


    Contributors:

    Publication date :

    1981-06-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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