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Oxidation protected carbon-carbonPyrolized carbon-carbon has one unique advantage over other materials that makes its application to the space shuttle thermal protection system very attractive. This unique characteristic is the increase in material strength and modulus with increase in temperature up to about 2500 K (4040 F). Offsetting this unique advantage are disadvantages which include brittleness, high cost, and the tendency of the material to react with oxygen, particularly at high temperatures. The development of an oxidation inhibitor for the material and the definition of fabrication processes for selected full-scale components are considered.
Document ID
19720023228
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Pavlosky, J. E.
(NASA Lyndon B. Johnson Space Center Houston, TX, United States)
St. Leger, L. G.
(NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Date Acquired
August 6, 2013
Publication Date
July 1, 1972
Publication Information
Publication: NASA Space Shuttle Technol. Conf.
Subject Category
Thermodynamics And Combustion
Accession Number
72N30878
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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