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Space Station Freedom solar array design developmentThe 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.
Document ID
19900051021
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Winslow, Cindy
(Lockheed Missiles and Space Co. Sunnyvale, CA, United States)
Bilger, Kevin
(Lockheed Missiles and Space Co., Inc. Sunnyvale, CA, United States)
Baraona, Cosmo
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Subject Category
Spacecraft Propulsion And Power
Meeting Information
Meeting: IECEC-89
Location: Washington, DC
Country: United States
Start Date: August 6, 1989
End Date: August 11, 1989
Accession Number
90A38076
Funding Number(s)
CONTRACT_GRANT: NAS3-25082
Distribution Limits
Public
Copyright
Other

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