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Origin and Development of Ablator for Space Shuttle External Tank
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English
Abstract
THE SPACE SHUTTLE EXTERNAL FUEL TANK (ET) is covered with a Thermal Protection System (TPS). The TPS materials are designed to prevent structural overheating during ascent/descent and maintain good quality cryogenic propellents until main engine cut off.
The primary TPS materials consist of a nonmetallic rigid foam and a composite ablator. These materials and processes were developed through an evolutionary procedure, driven by changing requirements, definitions, and progressively increasing delivery rates. The evolution, from contract start in 1973 to the present, is reviewed.
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Topic
Citation
Ronquillo, L., "Origin and Development of Ablator for Space Shuttle External Tank," SAE Technical Paper 851385, 1985, https://doi.org/10.4271/851385.Also In
References
- Space Shuttle External Tank Thermal Protection System Mills John P. Ronquillo Leon Brown Howard J. Greater New Orleans Mini symposium 1983
- The History of Heat Shields for U.S. Manned Spacecraft Ronquillo Leon 18th IAA International Symposium on the History of Astronautics (35th International Astronautical Congress)
- Thermal Design of The Space Shuttle External Tank Bachtel Frederick D. Vaniman Jerold L. Stuckey James M. Dr. Gray Carroll Widofsky Bernard Space Shuttle Technical Conference June 1983
- An Advanced Therml Protection System for the Aft Dome of the Space Shuttle External Tank Ronquillo L. Williams C. Gray C. AIAA 19th Thermophysics Conference
- Spray-on-foam Insulation Development for the Space Shuttle External Tank Thermal Protection System SAE 840921 Gray C. Ronquillo L. Williams C. 14th Intersociety Conference on Environmental Systems
- External Tank LWT Thermal Data Book July 1982
- External Tank Thermal Data Book May 1981
- Systems Definition Hand Book, Space Shuttle External Tank August 1980
- Gray Carroll Mills John Miller Christopher Huber Ron Williams Chuck Sharpe Boyd Unpublished Work on External Fuel Tank Program