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Mechanical design of a low concentration ratio solar array for a space station applicationThis paper describes a preliminary study and conceptual design of a low concentration ratio solar array for a space station application with approximately a 100 kW power requirement. The baseline design calls for a multiple series of inverted, truncated, pyramidal optical elements with a geometric concentration ratio (GCR) of 6. It also calls for low life cycle cost, simple on-orbit maintainability, 1984 technology readiness date, and gallium arsenide (GaAs) of silicon (Si) solar cell interchangeability. Due to the large area needed to produce the amount of power required for the baseline space station, a symmetrical wing design, making maximum use of the commonality of parts approach, was taken. This paper will describe the mechanical and structural design of a mass-producible solar array that is very easy to tailor to the needs of the individual user requirement.
Document ID
19840047360
Document Type
Conference Paper
Authors
Biss, M. S. (Rockwell International Corp. Downey, CA, United States)
Hsu, L. (Rockwell International Corp. Shuttle Integration and Satellite Systems Div., Downey, CA, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1983
Subject Category
SPACECRAFT DESIGN, TESTING AND PERFORMANCE
Funding Number(s)
CONTRACT_GRANT: NAS8-34214
Distribution Limits
Public
Copyright
Other