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Thermal response of Space Shuttle wing during reentry heatingA structural performance and resizing (SPAR) finite element thermal analysis computer program was used in the heat transfer analysis of the space shuttle orbiter that was subjected to reentry aerodynamic heatings. One wing segment of the right wing (WS 240) and the whole left wing were selected for the thermal analysis. Results showed that the predicted thermal protection system (TPS) temperatures were in good agreement with the space transportation system, trajectory 5 (STS-5) flight-measured temperatures. In addition, calculated aluminum structural temperatures were in fairly good agreement with the flight data up to the point of touchdown. Results also showed that the internal free convection had a considerable effect on the change of structural temperatures after touchdown.
Document ID
19840019716
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gong, L. (NASA Ames Research Center Moffett Field, CA, United States)
Ko, W. L. (NASA Ames Research Center Moffett Field, CA, United States)
Quinn, R. D. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1984
Subject Category
Space Transportation
Report/Patent Number
AIAA PAPER 84-1781
NAS 1.15:85907
H-1254
NASA-TM-85907
Meeting Information
Meeting: AIAA Thermophys. Conf.
Location: Snowmass, CO
Country: United States
Start Date: June 24, 1984
End Date: June 28, 1984
Accession Number
84N27785
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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