飞行器结构部件导热/ 辐射耦合传热特性预测方法.

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 healing 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 obtruned 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. [ABSTRACT FROM AUTHOR]