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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    Titel :

    Conceptual Design Studies for Large Free-Flying Solar-Reflector Spacecraft


    Beteiligte:
    J. M. Hedgepeth (Autor:in) / R. K. Miller (Autor:in) / K. P. W. Knapp (Autor:in)

    Erscheinungsdatum :

    1981


    Format / Umfang :

    125 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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

    Hedgepeth, J. M. / Miller, R. K. / Knapp, K. P. W. | NTRS | 1981


    Free-flying solar reflector spacecraft

    Hedgepeth, J. M. | NTRS | 1981



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