The general logic of a material testing program designed to test the Hermes Thermal Protection System (TPS) is described. Mission specifications during launch, orbital mission and reentry are taken into consideration in the program. Two types of materials, carbon-carbon and carbon-silicon carbide composites are selected as candidates for the TPS system. The specifications of each of these materials are presented with respect to the nominal design. Definition of antioxidation processes is discussed. Optimal material development is outlined.
Materials for Hermes Hot Structural Parts: Requirements and Testing
1990
7 pages
Report
No indication
English
Ablative Materials & Ablation , Composite Materials , Engineering Materials , Manned Spacecraft , Carbon-carbon composites , Hermes manned spaceplane , Silicon carbides , Thermal protection , Ablative materials , Performance tests , Carbon compounds , Heat shielding , Spacecraft construction materials , Foreign technology , Ceramic matrix composites , Fiber composites
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