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Effects of selected trajectory parameters on weight trends in the shuttle thermal protection systemAn empirical heating model, thermal protection system unit weight correlation, and trajectory analysis were used to develop a computation procedure for studying the sensitivity of thermal protection system weights to variations in pertinent trajectory parameters. The analytical techniques used in developing this computer program are described. Application of the analysis to a Space Shuttle Orbiter configuration was performed to demonstrate gross thermal protection system weight trends with selected entry trajectory parameters.
Document ID
19740009532
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Curry, D. M. (NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Tolin, J. W., Jr. (NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Goodrich, W. D. (NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1974
Subject Category
Thermodynamics And Combustion
Report/Patent Number
JSC-08585
NASA-TM-X-58113
Report Number: JSC-08585
Report Number: NASA-TM-X-58113
Accession Number
74N17645
Funding Number(s)
PROJECT: RTOP 986-15-31-04-72
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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