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Space debris protection for a reusable orbital transfer vehicleThe protection of a reusable transfer vehicle from space debris is discussed. The results of a debris protection analysis are given. It was concluded that a shielding thickness of 0.62mm (24 mils) equivalent aluminum was needed when using a good double wall design. An additional 0.43 mm (18 mils) of shielding was needed during on-orbit storage time between flights.
Document ID
19850012898
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Davis, E. E. (Boeing Aerospace Co. Seattle, WA, United States)
Sperber, R. (Boeing Aerospace Co. Seattle, WA, United States)
Date Acquired
August 12, 2013
Publication Date
March 1, 1985
Publication Information
Publication: NASA. Lyndon B. Johnson Space Center Orbital Debris
Subject Category
Spacecraft Design, Testing And Performance
Accession Number
85N21208
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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IDRelationTitle19850012878Collected WorksOrbital Debris19850012878Collected WorksOrbital Debris
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