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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。
Under the action of high pressure and high heat flux, C / C composites which are commonly used in high Mach number aircraft heat-proof layer appear ablation phenomenon. Considering the high temperature thermal conductivity of C / C composites as a function of temperature, based on the Fourier heat transfer law and high temperature ablation mechanism, the thermal conductivity characteristics of C / C composite plate ablation were calculated by FORTRAN programming. The results show that the temperature change of the surface is different from that of the interior when the heat flux is lower. The temperature of the heated surface tends to be consistent with the temperature of the back surface while the temperature of the back surface is almost the same with the passage of time. High heat flux incident surface ablation, the temperature rises rapidly, and maintain a certain temperature to maintain the homeostasis.