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Thermal design of the Space Shuttle External TankThe history of the engineering and manufacturing requirements leading to the final Thermal Protection System (TPS) for the External Tank (ET) is presented. The thermal design for the ET must be optimized, based on considerations of cost, weight, and application of the TPS. The significant thermal requirements include the structural and component temperature limits, the propellant quality, the minimization of ice and frost, no air liquefaction, and no film boiling. The TPS materials selected to meet the requirements are a low density closed cell foam (CPR-488) and two light-weight ablators (SLA-56 and MA-25s). The first four flights of the Space Shuttle (1981) will measure and evaluate external environmental, structural, propulsion, electrical, and engine performance data. The ET will be instrumented to measure acoustics, pressures, heat transfer, vibration, temperatures, and structural strains. TPS weight reductions are planned for future ETs through the use of a comprehensive thermal instrumentation system.
Document ID
19820027368
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Warmbrod, J. D.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Vaniman, J. L.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Elam, B. F.
(Martin Marietta Aerospace New Orleans, LA, United States)
Date Acquired
August 10, 2013
Publication Date
July 1, 1981
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
ASME PAPER 81-ENAS-15
Meeting Information
Meeting: American Society of Mechanical Engineers, Intersociety Conference on Environmental Systems
Location: San Francisco, CA
Start Date: July 13, 1981
End Date: July 15, 1981
Sponsors: American Society of Mechanical Engineers
Accession Number
82A10903
Distribution Limits
Public
Copyright
Other

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