在高压高热流作用下，高马赫数飞行器防热层常用耐高温的C／C复合材料出现烧蚀现象。考虑到C／C复合材料的高温导热系数为温度的函数，基于傅里叶传热定律和高温烧蚀机制，利用FORTRAN语言编程计算分析了C／C复合材料板烧蚀中热传导特性。结果表明：较低热流入射时，物体表面温度变化速率与内部的不同；随时间的推移，受热表面的温度趋于一致，而背面温度相差较大；物体内部温度分布趋势大体相同。较高热流入射时，表面出现烧蚀现象，温度急速升高，并维持在某一温度值保持动态平衡。
Carbon/carbon（C/C） composites are often used in heat-resistant layers of aircrafts with a high Mach number as they can withstand a high temperature, yet which may be ablated due to high pressure and heat flow. According to Fourier heat transfer law and high temperature ablation mechanism, we utilized FORTRAN programming to calculate and analyze the performance of thermal conduction in C/C plates with ablation, considering the thermal conductivity of C/C composites as a function of temperature at high temperature. The results show： when lower heat flow acts, compared with that the thermal conductivity is constant, the temperature change rate of object surface is different from that of interior~ over time, the surface temperature is gradually consistent, but the back temperature is distinct extremely; the distribution trend of object interior temperature is basically same. When higher heat flow acts, the ablation phenomenon occurs on the surface, at the same time, the temperature rapidly increases, which will maintain dynamic equilibrium.
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