The test facility presented herein uses a groundbased rocket combustor to test the durability of new ceramic composite and metallic materials in a rocket engine thermal environment. A gaseous H2/02 rocket combustor (essentially a ground-based rocket engine) is used to generate a high temperature/high heat flux environment to which advanced ceramic and/or metallic materials are exposed. These materials can either be an integral part of the combustor (nozzle, thrust chamber etc) or can be mounted downstream of the combustor in the combustor exhaust plume. The test materials can be uncooled, water cooled or cooled with gaseous hydrogen.
A Combustion Research Facility for Testing Advanced Materials for Space Applications
AIAA Aerospace Sciences Meeting and Exhibit ; 2003 ; Reno, NV, United States
2003-01-06
Conference paper
No indication
English
A Combustion Research Facility for Testing Advanced Materials for Space Applications
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