The Space Station Freedom solar array program is required to provide a 75 kW power module that uses eight solar array (SA) wings over a four-year period in low Earth orbit (LEO). Each wing will be capable of providing 23.4 kW at the 4 yr design point. The design of flexible-substrate SAs that must survive exposure to the space environment, including atomic oxygen, for an operating life of fifteen years is discussed. The tradeoff study and development areas being investigated include solar cell module size, solar cell weld pads, panel stiffener frames, materials inherently resistant to atomic oxygen, and weight reduction design alternatives.


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    Title :

    Space Station Freedom solar array design development


    Additional title:

    Entwicklung des Sonnenbatterie-Entwurfs für die Raumstation Freedom


    Contributors:
    Winslow, C. (author) / Bilger, K. (author) / Baraona, C. (author)


    Publication date :

    1989


    Size :

    5 Seiten, 2 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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