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高超声速飞行器在高马赫数飞行时,前缘结构要经历严酷的气动加热.炭/炭复合材料是用于前缘结构的理想材料,由于炭/炭复合材料具有各向异性和高导热率,因此本文研究了材料热导率和各向异性结构,以及涂层的热导率对驻点温度的影响.数值模拟的结果表明,基体材料沿热传导方向的热导率对驻点温度有显著的影响,其它方向的热导率对驻点温度影响不大.在基体材料热导率较低的情况下,涂层对驻点温度的影响明显,当基体材料的热导率较高时,涂层对驻点温度的影响较小.“,”The leading edge of hypersonic vehicle will suffer extremely heating during the working hours.Carbon/Carbon composites is the most promising materials that can be used for the leading edge.This paper investigate effects of the high thermal conductivity and anisotropy of Carbon/Carbon leading edge,as well as the conductivity of layer on the temperature of stagnation.The results shows that the conductivity along the direction of heating plays an important role in the thermal protection effect while the conductivity in other direction can be ignored for the thermal protection.In addition,the high thermal conductivity layer also plays an important role in the thermal protection when the low conductivity Carbon/Carbon composites were used.