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围绕氟化镁共形整流罩的热障效应展开分析,模拟了真实飞行状态,建立了整流罩气动加热及其内部传热过程的有限元分析模型,计算不同飞行速度下整流罩的气动热载荷及平均温度;再根据红外探测基本原理,分析各个温度下整流罩的热辐射及其对探测系统成像质量的影响,计算探测器达到饱和状态时整流罩的临界温度,即研究热障效应产生机制;最后用成像试验对分析结果加以验证。分析结果表明,对于该红外成像探测系统,氟化镁共形整流罩的临界温度约为460 K,即在Ma=3的末制导阶段及Ma=4的情形下,热障效应显著,若想进一步加快红外成像制导武器的飞行速度,必须对热障效应加以抑制和校正。各项结论对认识热障效应机理及其校正方法有一定借鉴意义。
Based on the analysis of the thermal barrier effect of the conformal fairing of magnesium fluoride, the real flight condition was simulated, and the finite element analysis model of the aerodynamic heating of the fairing and the internal heat transfer process was established. The aerodynamic heat load of the fairing under different flight velocities And the average temperature. According to the basic principle of infrared detection, the heat radiation of the fairing and its influence on the imaging quality of the detection system are analyzed. The critical temperature of the fairing when the detector reaches the saturation state is calculated, that is, the mechanism of the thermal barrier effect Finally, the imaging test is used to verify the analysis results. The analysis results show that for the infrared imaging detection system, the critical temperature of the magnesium ferrite conformal fairing is about 460 K, ie the thermal barrier effect is significant under the condition of the terminal guidance stage of Ma = 3 and Ma = 4. To further speed up the flight speed of infrared imaging guided weapons, the thermal barrier effect must be suppressed and corrected. All conclusions have some reference to recognize the mechanism of thermal barrier effect and its correction method.