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General Model for Multicomponent Ablation ThermochemistryA previous paper (AIAA 94-2042) presented equations and numerical procedures for modeling the thermochemical ablation and pyrolysis of thermal protection materials which contain multiple surface species. This work describes modifications and enhancements to the Multicomponent Ablation Thermochemistry (MAT) theory and code for application to the general case which includes surface area constraints, rate limited surface reactions, and non-thermochemical mass loss (failure). Detailed results and comparisons with data are presented for the Shuttle Orbiter reinforced carbon-carbon oxidation protection system which contains a mixture of sodium silicate (Na2SiO3), silica (SiO2), silicon carbide (SiC), and carbon (C).
Document ID
20020004356
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Milos, Frank S.
(NASA Ames Research Center Moffett Field, CA United States)
Marschall, Jochen
(National Academy of Sciences - National Research Council Moffett Field, CA United States)
Rasky, Daniel J.
Date Acquired
August 20, 2013
Publication Date
January 1, 1994
Subject Category
Inorganic, Organic And Physical Chemistry
Meeting Information
Meeting: AIAA 29th Thermophysics Conference
Location: San Diego, CA
Country: United States
Start Date: June 19, 1995
End Date: June 22, 1995
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
PROJECT: RTOP 232-01-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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