The thermal protection system design associated with vehicle trajectory, aeroheating, structural temperature and response for hypersonic vehicle is significant and complex. To improve the calculation accuracy of TPS structural temperature field, this paper introduces an aeroheating/structure coupled method to analyze the C/SiC non-ablative composite rigid external TPS based on the engineering algorithm for aeroheating. The result shows that the hot-wall heat flux actual action on the TPS is less than the initial calculation value achieved by engineering algorithm. Thus, the problem of aeroheating and structural coupling must be considered for TPS design.%高超声速飞行器热防护问题复杂,是弹道参数、外部流场、气动加热、结构温度场、结构变形响应等多物理场的耦合.为提高飞行器结构温度场预估精度,开展气动加热与结构温度场的耦合分析方法研究,基于气动加热工程算法,对典型C/SiC刚性非烧蚀式防热结构进行气动加热与温度场耦合分析.结果表明作用在结构上的净热流密度低于气动加热工程计算得到的冷壁热流密度,设计热防护系统时必须考虑气动加热/结构温度之间的耦合作用.
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