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Performance of full size metallic and RSI thermal protection systems in a Mach 7 environmentThe integrity and reusability of three flight-weight metallic and RSI thermal protection systems, designed for the Shuttle entry environment, have been demonstrated. Each model successfully survived over 23 entry thermal cycles without serious degradation. The metallic systems were more tolerant of the hostile environment and provided a higher degree of reusability than did the RSI. Thermal expansion slip joints of the metallic TPS successfully prevented hot gas ingress to the substructure. The RSI demonstrated high damage tolerance and field repairs increased its reusability. Heat-transfer tests to further assess RSI gap heating indicate that stacked tile orientations may impose a penalty on tile thickness. Parameters influencing RSI impingement heating were determined, and the heating data were correlated.
Document ID
19750048602
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bohon, H. L.
Sawyer, J. W.
Hunt, L. R.
Weinstein, I.
(NASA Langley Research Center Structures and Dynamics Div., Hampton, Va., United States)
Date Acquired
August 8, 2013
Publication Date
May 1, 1975
Subject Category
Metallic Materials
Report/Patent Number
AIAA PAPER 75-800
Meeting Information
Meeting: AIAA, ASME, and SAE, Structures, Structural Dynamics, and Materials Conference
Location: Denver, CO
Start Date: May 27, 1975
End Date: May 29, 1975
Sponsors: AIAA, SAE, ASME
Accession Number
75A32674
Distribution Limits
Public
Copyright
Other

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