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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。
Hypersonic vehicle thermal protection is a complex problem, which is a multi-physics coupling of ballistic parameters, external flow field, aerodynamic heating, structural temperature field and structural deformation response. In order to improve the prediction accuracy of aircraft structure temperature field, the coupling analysis method of aerodynamic heating and structural temperature field is studied. Based on the aerodynamic heating engineering algorithm, the aerodynamic heating and temperature field coupling analysis of typical C / SiC rigid non-ablative heat-resistant structure is carried out. . The results show that the net heat flux density acting on the structure is lower than the heat flux density calculated by the aerodynamic heating engineering, and the coupling between the aerodynamic heating and the structural temperature must be considered when designing the thermal protection system.