高速飞行器空气舵前缘三维烧蚀/温度耦合分析研究

为了准确预测空气舵前缘三维烧蚀/温度场,针对通用有限元软件采用自编热流加载和烧蚀移动边界用户子程序方法,仿真分析了空气舵前缘局部模型的三维烧蚀/温度场,给出了空气舵前缘烧蚀外形、烧蚀量和三维温度分布,并与试验结果进行了对比,结果表明:理论计算的烧蚀量和表面温度与实测值的偏差均小于10%,证明方法正确可行。

Three-Dimensional Ablation/Temperature Coupling Analysis of Air Rudder Leading Edge of High Speed Aircraft

In order to accurately predict the three-dimensional ablation/temperature field of the leading edge of the air rudder,the general finite element calculation software is used to simulate the three-dimensional temperature field of the air rudder leading edge by using self-programmed heat flux loading and ablation moving sub-user method.The ablation profile,ablation amount and three-dimensional temperature distribution of the leading edge are given and compared with the experimental results.The results show that the theoretically calculated ablation and surface temperature deviate from the measured value by less than 10%,proving that the calculation method is correct.