In the early 1970s, in conjunction with the initiation of the first Space Station solar array technology studies, a set of basic design decisions were made on the best generic approach to the design of solar arrays in sizes from tens to hundreds of kilowatts. Considerations were maximum potential for low weight, low launch package volume, adequate deployed structural stiffness and damping, at least a ten-year temperature cycle life, and adaptability to low-cost automated assembly. In the intervening 18 years between then and now, a number of programs contributed to the develoment of this basic design concept and the associated manufacturing processes. These developments form the foundation for the current Space Station Freedom Solar Array and platform designs and for two operational satellite programs. These current designs are unchanged in basic concept from the original studies in 1972, but they now reflect the mature technology which has been developed and proven out since then. To manufacture and test these systems, an integrated manufacturing, assembly and test facility has been constructed and is in operation with many automated features, including cell welding and substrate manufacture.


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    Title :

    Large solar array design


    Additional title:

    Entwurf, Fertigung und Prüfung von großen Sonnenzellengruppenstrukturen (100 kW-Bereich) für Anwendungen im Weltraum


    Contributors:

    Published in:

    Space Power ; 8 , 1/2 ; 11-22


    Publication date :

    1989


    Size :

    12 Seiten, 12 Bilder, 1 Tabelle


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





    Large Area Solar Cell Array

    Taylor, J. Edward / Szego, George C. | AIAA | 1966


    Large area solar cell array

    RAY, K. / WINICUR, D. | AIAA | 1964


    Structural Analysis and Design of a Large Area Solar Array*

    Weikel, R. C. | SAE Technical Papers | 1967


    Large Solar Array Development in UK

    F. C. Treble | NTIS | 1969