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Thermodynamic energy balance equations for Space Shuttle Orbiter gas compartment during ascent and re-entryThermodynamic energy balance equations are derived and applied to midsection Orbiter-payload atmospheric thermal math models (TMMs) to predict Orbiter component, element, compartment, internal insolation and structure temperatures in support of NASA/JSC mission planning, postflight thermal analysis and payload thermal integration planning. The equations are extended and applied to the forward section, midsection, and aft section of the TMMs for five Orbiter mission phases: prelaunch on pad with purge, lift-off to ascent, re-entry to touchdown, post landing without purge, and post-landing with purge. Predicted results from the 390 node/DFI atmospheric TMM are in good agreement with STS-1 flight measurement data.
Document ID
19820048333
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ting, P. C.
(Rockwell International Corp. Houston, TX, United States)
Date Acquired
August 10, 2013
Publication Date
June 1, 1982
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 82-0844
Meeting Information
Meeting: Joint Thermophysics, Fluids, Plasma and Heat Transfer Conference
Location: St. Louis, MO
Start Date: June 7, 1982
End Date: June 11, 1982
Sponsors: American Institute of Aeronautics and Astronautics and American Society of Mechanical Engineers
Accession Number
82A31868
Funding Number(s)
CONTRACT_GRANT: NAS9-14000
Distribution Limits
Public
Copyright
Other

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