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高超音速导弹在服役过程中其红外窗口承受着复杂的气动热/力环境。利用有限元方法对不同气动热/力情况下的窗口进行数值模拟,获得了不同热流密度下窗口的温度和热应力分布,应力沿膜厚方向几乎相同,但是在膜基界面附近会产生突变。在膜层表面,最大应力出现在边界旁。不同的膜层材料在相同条件下有相同的温度和应力分布规律,但是应力大不相同。比较发现,Y_2O_3比ZrN膜层具有更高的温度和应力。同时,进行了地面热冲击实验来观察红外窗口的破坏情况,10 s之后,发现窗口表面已经发生破坏,有些局部产生裂纹,有些局部会产生破碎的斑点。
Hypersonic missiles in the service process of its infrared window to withstand the complex aerodynamic heat / force environment. The temperature and thermal stress distribution of the window under different heat flux density were obtained by using the finite element method to simulate the window under different thermal and thermal conditions. The stress was almost the same along the film thickness direction, but a sudden change occurred at the film-based interface. On the surface of the film, the maximum stress appears beside the boundary. Different film materials under the same conditions have the same temperature and stress distribution, but the stress is very different. It is found that Y_2O_3 has higher temperature and stress than ZrN film. At the same time, the ground thermal shock experiment was conducted to observe the damage of the infrared window. After 10 s, it was found that the surface of the window had been damaged, some of the cracks were locally generated and some of the spots were broken.