Ablative thermal protection systemsThe procedures used to establish the TPS (thermal protection system) design of the SRB (solid rocket booster) element of the Space Shuttle vehicle are discussed. A final evaluation of the adequacy of this design will be made from data obtained from the first five Shuttle flights. Temperature sensors installed at selected locations on the SRB structure covered by the TPS give information as a function of time throughout the flight. Anomalies are to be investigated and computer design thermal models adjusted if required. In addition, the actual TPS ablator material loss is to be measured after each flight and compared with analytically determined losses. The analytical methods of predicting ablator performance are surveyed.
Document ID
19830061039
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Vaniman, J. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Fisher, R. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Wojciechowski, C. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Dean, W. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1983
Subject Category
Fluid Mechanics And Heat Transfer
Meeting Information
Meeting: High temperature corrosion; International Conference