To fast analyze the flow-thermal coupling problems for multi-layered complex TPS of hypersonic aircraft,an equivalent one-dimensional unsteady heat transfer model is established. For curved TPS,an equivalent computational method is proposed by forming the equivalent thermal resistance at the stagnation point and wing leading edge through using the correctional factor. For arbitrary multi-layered complex TPS,a fast coupling technique of aerodynamic heating of the outside air and the heat transfer in the stru...
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