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Thermal design of composite material high temperature attachmentsAn evaluation has been made of the thermal aspects of utilizing advanced filamentary composite materials as primary structures on the shuttle vehicle. The technical objectives of this study are to: (1) establish and design concepts for maintaining material temperatures within allowable limits at TPS attachments and or penetrations applicable to the space shuttle; and (2) verify the thermal design analysis by testing selected concepts. Specific composite materials being evaluated are boron epoxy, graphite/epoxy, boron polyimide, and boron aluminum; graphite/polyimide has been added to this list for property data identification and preliminary evaluation of thermal design problems. The TPS standoff to composite structure attachment over-temperature problem is directly related to TPS maximum surface temperature. To provide a thermally comprehensive evaluation of attachment temperature characteristics, maximum surface temperatures of 900 F, 1200 F, 1800 F, 2500 F and 3000 F are considered in this study. This range of surface temperatures and the high and low maximum temperature capability of the selected composite materials will result in a wide range of thermal requirements for composite/TPS standoff attachments.
Document ID
19730012742
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Date Acquired
September 2, 2013
Publication Date
February 6, 1972
Subject Category
Materials, Nonmetallic
Report/Patent Number
PR-9
QPR-3
NASA-CR-124206
Accession Number
73N21469
Funding Number(s)
CONTRACT_GRANT: NAS8-27041
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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