飞行器气动加热烧蚀工程计算

Calculation of Aerodynamic Heating and Ablation of Multi-layer Thermal Protection Material

高超声速飞行器设计时,为了对防热层气动热烧蚀情况及温度场进行快速预估,提出了集成气动热、材料烧蚀、瞬态温度场的耦合计算方法。通过算例对计算方法和程序进行了验证,表明该方法具有较高的效率和精度。在给定弹道条件下,实现了气动热、热防护材料烧蚀性能和弹体温度场耦合计算。通过该方法可以在高速飞行器设计阶段,快速计算出指定飞行工况下的防热材料烧蚀情况及温度场分布,为飞行器热防护层设计提供依据。

It is inevitable to evaluate the aerodynamic heat and the ablation of thermal protection material for designing a hypersonic aircraft. A coupling method is presented for the calculation of aerodynamic heat,material ablation and transient temperature distribution. The method and program are validated by experimental data. The results indicate that the method has higher precision and efficiency. For a given trajectory,the aerodynamic heat,ablation performance of thermal protection layer and temperature filed are predicted by the coupling method. The proposed method can be used to calculate the ablation and temperature distribution in given operation conditions in design phase which is referable for the design of multi-layer thermal protection material for hypersonic aircrafts.