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Thermal Analysis of the MC-1 Chamber/NozzleThis paper will describe the thermal analysis techniques used to predict temperatures in the film-cooled ablative rocket nozzle used on the MC-1 60K rocket engine. A model was developed that predicts char and pyrolysis depths, liner thermal gradients, and temperatures of the bondline between the overwrap and liner. Correlation of the model was accomplished by thermal analog tests performed at Southern Research, and specially instrumented hot fire tests at the Marshall Space Flight Center. Infrared thermography was instrumental in defining nozzle hot wall surface temperatures. In-depth and outboard thermocouple data was used to correlate the kinetic decomposition routine used to predict char and pyrolysis depths. These depths were anchored with measured char and pyrolysis depths from cross-sectioned hot-fire nozzles. For the X-34 flight analysis, the model includes the ablative Thermal Protection System (TPS) material that protects the overwrap from the recirculating plume. Results from model correlation, hot-fire testing, and flight predictions will be discussed.
Document ID
20010038492
Acquisition Source
Marshall Space Flight Center
Document Type
Preprint (Draft being sent to journal)
Authors
Davis, Darrell W. (NASA Marshall Space Flight Center Huntsville, AL United States)
Phelps, Lisa H.
Date Acquired
September 7, 2013
Publication Date
January 1, 2001
Subject Category
Spacecraft Propulsion And Power
Meeting Information
Meeting: Space Technology and Applications International Forum 2001
Location: Albuquerque, NM
Country: United States
Start Date: February 11, 2001
End Date: February 14, 2001
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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