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Silica RSI for Application to the Shuttle OrbiterSilica reusable surface insulation is analyzed for its cold soak properties, bond properties at low temperature, gap and step heating effects, and aerodynamic surface roughness effects to determine space shuttle weight and cost sensitivity to structure subsystem weights. Computerized simulation studies show that total program cost savings of silica (vs. mullite) exceed thermal protection system design and development costs and that an early introduction of silica increases total program cost savings.
Document ID
19730024763
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Forsberg, K. J. (Lockheed Missiles and Space Co. Sunnyvale, CA, United States)
Jue, J. (Lockheed Missiles and Space Co. Sunnyvale, CA, United States)
Kural, M. H. (Lockheed Missiles and Space Co. Sunnyvale, CA, United States)
Velligan, F. A. (Lockheed Missiles and Space Co. Sunnyvale, CA, United States)
Date Acquired
August 7, 2013
Publication Date
September 1, 1973
Publication Information
Publication: NASA. Ames Res. Center Symp. on Reusable Surface Insulation for Space Shuttle, Vol. 3
Subject Category
Materials, Nonmetallic
Accession Number
73N33496
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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IDRelationTitle19730024757Collected WorksSymposium on Reusable Surface Insulation for Space Shuttle. Volume 3: Thermal Protection System Design and Optimization
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