Abstract Infrared transparent windows on aircraft and missiles can be subjected to extreme aerothermodynamics, which can cause thermal shock failure. Finite element analysis and oxygen–propane flame jet impingement tests were performed to investigate the thermal shock failure of an yttrium oxide-coated chemical vapor deposition (CVD) ZnS infrared window. Good agreement was achieved between the simulation and experimental results, which indicated that thermal shock failure occurs under high temperature differences and thermal stresses. The temperature and stress in the samples increased rapidly in a few seconds and then trended to be stable. The center area of the window surface failed most easily because the maximum temperature and stress both occurred in this area. No delamination of the Y2O3 films occurred during the thermal shock, which indicated good adhesion between the Y2O3 films and CVD ZnS substrate. In the experiment, the center area of the specimen surface was damaged in the form of pits and line cracks.

中文翻译：

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Y 2 O 3 涂层CVD ZnS红外窗热震失效的数值与实验研究

摘要 飞机和导弹上的红外透明窗口会受到极端空气热力学的影响，从而导致热冲击失效。进行了有限元分析和氧-丙烷火焰喷射冲击试验，以研究氧化钇涂层化学气相沉积 (CVD) ZnS 红外窗口的热冲击失效。模拟结果与实验结果吻合良好，表明在高温差和热应力下会发生热冲击失效。样品中的温度和应力在几秒钟内迅速升高，然后趋于稳定。窗面的中心区域最容易失效，因为该区域的温度和应力均出现在该区域。在热冲击过程中没有发生 Y2O3 薄膜的分层，这表明 Y2O3 薄膜和 CVD ZnS 基板之间具有良好的附着力。在实验中，试样表面的中心区域以凹坑和线裂纹的形式被破坏。