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Shuttle TPS thermal performance and analysis methodologyThermal performance of the thermal protection system was approximately as predicted. The only extensive anomalies were filler bar scorching and over-predictions in the high Delta p gap heating regions of the orbiter. A technique to predict filler bar scorching has been developed that can aid in defining a solution. Improvement in high Delta p gap heating methodology is still under study. Minor anomalies were also examined for improvements in modeling techniques and prediction capabilities. These include improved definition of low Delta p gap heating, an analytical model for inner mode line convection heat transfer, better modeling of structure, and inclusion of sneak heating. The limited number of problems related to penetration items that presented themselves during orbital flight tests were resolved expeditiously, and designs were changed and proved successful within the time frame of that program.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Neuenschwander, W. E.
(Rockwell International Corp. Downey, CA, United States)
Mcbride, D. U.
(Rockwell International Corp. Downey, CA, United States)
Armour, G. A.
(Rockwell International Corp. Downey, CA, United States)
Date Acquired
August 12, 2013
Publication Date
October 1, 1983
Publication Information
Publication: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Pt. 2
Subject Category
Space Transportation
Accession Number
Distribution Limits
Work of the US Gov. Public Use Permitted.
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