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Ascent Heating Thermal Analysis on the Spacecraft Adaptor (SA) Fairings and the Interface with the Crew Launch Vehicle (CLV)When the crew exploration vehicle (CEV) is launched, the spacecraft adaptor (SA) fairings that cover the CEV service module (SM) are exposed to aero heating. Thermal analysis is performed to compute the fairing temperatures and to investigate whether the temperatures are within the material limits for nominal ascent aero heating case. Heating rates from Thermal Environment (TE) 3 aero heating analysis computed by engineers at Marshall Space Flight Center (MSFC) are used in the thermal analysis. Both MSC Patran 2007r1b/Pthermal and C&R Thermal Desktop 5.1/Sinda models are built to validate each other. The numerical results are also compared with those reported by Lockheed Martin (LM) and show a reasonably good agreement.
Document ID
20090008664
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Wang, Xiao-Yen (NASA Glenn Research Center Cleveland, OH, United States)
Yuko, James (NASA Glenn Research Center Cleveland, OH, United States)
Motil, Brian (NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
August 24, 2013
Publication Date
January 1, 2009
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
NASA/TM-2009-215474
E-16611
TFAWS08-1008
Meeting Information
Meeting: 2008 Thermal and Fluids Analysis Workshop
Location: San Jose, CA
Country: United States
Start Date: August 18, 2008
End Date: August 22, 2008
Funding Number(s)
WBS: WBS 931164.03.01.02.01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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