CAJ | 학술논문

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，Y2O3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。
고초음속도탄재복역과정중기홍외창구승수착복잡적기동열/력배경。이용유한원방법대불동기동열/력정황하적창구진행수치모의，획득료불동열류밀도하창구적온도화열응력분포，응력연막후방향궤호상동，단시재막기계면부근회산생돌변。재막층표면，최대응력출현재변계방。불동적막층재료재상동조건하유상동적온도화응력분포규률，단시응력대불상동。비교발현，Y2O3비 ZrN 막층구유경고적온도화응력。동시，진행료지면열충격실험래관찰홍외창구적파배정황，10 s지후，발현창구표면이경발생파배，유사국부산생렬문，유사국부회산생파쇄적반점。
Infrared window in hypersonic missile usually suffers complex aerodynamic force/heat during high-speed flight. A finite element method was adopted to simulate the thermal and stress response of microscale functional film for infrared window under different aerodynamic heats/forces conditions. Temperature and stress distribution were obtained with different heat fluxes. There is almost constant stress distribution along the film thickness except a sudden decrease near the substrate. The maximum stresses are located at the points which are 0.5 mm away from the edges. Different film materials result in different stress values. The temperature and stress in ZrN are larger than those in Y2O3. Besides the numerical simulation, an oxygen propane flame jet impingement test was performed to investigate thermal shock failure of the infrared window. Some place of the window surface has spots damage and some place has line crack damage after thermal shock.