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采用内置高温热管的热防护结构是一种新型高效的热防护方式。建立了内置高温热管的C/C复合材料热防护结构模型,并通过罚函数的方法引入C/C复合材料与高温热管间装配关系,推导了一种顺序耦合的热力耦合有限元格式,在此基础上对热防护结构进行了热力耦合计算分析,最后对影响结构温度场与应力场的若干参数进行了参数影响分析。计算结果表明,在典型飞行状态下,采用内置高温热管的C/C复合材料热防护结构能确保结构驻点温度在材料许用温度范围内;同时,采用预留装配间隙的方法可有效降低结构界面的接触应力。该方法也可进一步用于研究由接触热阻引起的热力耦合问题。
The use of built-in heat pipe heat protection structure is a new type of efficient thermal protection. The thermal protection structure model of C / C composite material with built-in high temperature heat pipe was established. By means of penalty function, the assembly relationship between C / C composite material and high temperature heat pipe was introduced. A coupled thermal coupled finite element method Based on the calculation of thermal protection structure thermal coupling, the final parameters of the structure of the temperature field and stress field parameters were analyzed. The calculation results show that the C / C composite thermal protection structure with built-in high-temperature heat pipe can ensure the stagnation temperature of the structure within the material allowable temperature range under typical flight conditions. Meanwhile, the method of pre-assembly clearance can effectively reduce the structure Interface contact stress. This method can be further used to study the thermal coupling problems caused by the thermal contact resistance.