飞行器结构部件导热/辐射耦合传热特性预测方法

Method of Predicting Conduction-Radiation Coupled Heat-Transfer Characteristics for Vehicle Structural Component

采用数值方法求解气动热环境,基于蒙特卡罗方法求解内部空腔辐射换热及有限元方法求解三维导热,建立了沿弹道求解导热/辐射耦合的热响应预测方法,计算并获得了沿给定飞行弹道条件下的考虑内部辐射和不考虑内部辐射时的某高超声速飞行器结构部件的热响应特性。研究表明,所发展的耦合计算方法具有较高的精度和较好的工程适用性;考虑内部辐射时,结构部件局部最高温度明显低于不考虑辐射时,最高相差400 K以上,且温度分布趋于均匀,温度梯度减小。相关研究对高超声速飞行器防热结构设计与优化具有重要参考意义。

A prediction method for solving the conduction-radiation coupled thermal response of the vehicle structural components along the trajectory is established, based on the numerical method solving the aerodynamic heating environment, the Monte Carlo method solving the radiation heat transfer of cavities, and the finite element method solving the three-dimensional heat conduction. The calculations are carried out and the thermal response of the hypersonic vehicle structural components along the given trajectory are obtained in both cases of with and without considering the radiation heat transfer of the cavities. The research results show that the coupled calculation method developed in this paper has a good precision and better engineering applicability. The highest local temperature under the condition of considering the radiation heat transfer of cavities is obviously lower, and the maximum difference of the local temperatures in two cases is more than 400 K. The temperature distribution is more uniform and the temperature gradient is smaller under the condition of considering the radiation heat transfer of cavities. The related results are important for the design and optimization of the hypersonic vehicle thermal protection system.