The Space Shuttle External Tank (ET) represents the largest element of the Space Shuttle transportation system. The ET is the fuel tank which contains cryogenic propellants, including liquid oxygen and liquid hydrogen. The task of providing a suitable Thermal Protection System (TPS) which is mass producible for the ET represented a challenge for the aerospace industry. The difficulties were compounded by stringent insulation and ablation requirements for the materials to maintain their integrity over a wide range of operating temperatures during prelaunch and ascent. Attention is given to the configuration of the Space Shuttle system, the configuration of the external tank, the initial ET TPS concept, TPS materials and processes concepts, design rationale, TPS materials structural considerations, material and processes development, development tests, material/process verification, and flight results.
Origin and development of ablator for Space Shuttle external tank
1985-07-01
Conference paper
No indication
English
Origin and Development of Ablator for Space Shuttle External Tank
SAE Technical Papers | 1985
|Apollo composite ablator material used on Space Shuttle
AIAA | 1982
|NTRS | 1973
|Space Shuttle External Tank Instrumentation Evaluation
NTIS | 1979
|Space shuttle external tank performance enhancemnets
TIBKAT | 1996
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