Abstract
Space vehicles which enter earth’s atmosphere require a thermal protection system (TPS) to protect them against aerodynamic pressure and heating impact. The use of material with high temperature capability in combination with low thermal conductivity, to limit transfer of heat into interior of the structure, is required of the TPS. Because these requirements cannot be accomplished by a single material layer, two material layers are proposed, and their functions are integrated through the TPS design. Future reentry vehicle’s capabilities will in great extent depend upon the capabilities of the materials used for these layers [1]. This paper is devoted to the protection layer of the TPS, to predict its strength and life under the aerodynamic pressure and heat impact loads.
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