Abstract: The structure of leading thermal protection is considered as thermal protection system (TPS) to prevent hypersonic vehicle from the serious aerodynamic heating. By the use of finite element method and finite volume method, we calculate the solid domain and fluid domain of sharp leading-edge which is flying under given conditions. And it is proved that high thermal conductivity materials which are embedded in the leading-edge have an effect on thermal protection. The maximum temperature of the head decreases by 13.6%, and the minimum temperature of after-body increases by 16.7% when Mach number is 6.5. The transfer of heat from head to after-body is achieved, the front head of the thermal load is weakened and the ability of leading-edge thermal protection is strengthened. Considering that heat loading increases with increase of thickness, we propose the optimal thickness value of heat-resistant material which is the minimum value that can ensure the thermal structural stability of sharp leading-edge. The effects of black level of heat-resistant materials and thermal conductivity of high-conductivity materials on the wall temperature are discussed, which provides some references for the selection of thermal protection materials of sharp leading-edge.

Key words: leading thermal protection, aerodynamic heating, leading-edge, high thermal conductivity materials, heat-resistant materials