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.
Large solar array design
Entwurf, Fertigung und Prüfung von großen Sonnenzellengruppenstrukturen (100 kW-Bereich) für Anwendungen im Weltraum
Space Power ; 8 , 1/2 ; 11-22
1989
12 Seiten, 12 Bilder, 1 Tabelle
Aufsatz (Zeitschrift)
Englisch
Large area solar array design Quarterly report
NTRS | 1967
AIAA | 1964
|AIAA | 1966
|Structural Analysis and Design of a Large Area Solar Array*
SAE Technical Papers | 1967
|Large Solar Array Development in UK
NTIS | 1969
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