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Free-flying solar reflector spacecraftResults of investigations of requirements and design concepts for large solar-reflecting spacecraft are given. The emphasis is on the one kilometer diameter self contained spacecraft that can be packaged and launched in the space shuttle. The configuration consists of a compression rim stabilized by stays coming from each end of the central compression hub. The stays are stowed on reels on the ends of the hub. The hub consists of two Astromasts which are deployed after launch. The reflector membrane is a two micron thick Kapton film with a vapor deposited aluminum coating.
Document ID
19810010676
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Hedgepeth, J. M. (Astro Research Corp. Carpinteria, CA, United States)
Date Acquired
August 11, 2013
Publication Date
February 1, 1981
Publication Information
Publication: NASA. Langley Research Center The 1980 Large Space Systems Technol., Vol. 2
Subject Category
Launch Vehicles And Space Vehicles
Accession Number
81N19203
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19810010669Collected WorksThe 1980 Large space systems technology. Volume 2: Base technology
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