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建立了飞行器蒙皮红外辐射特征计算的理论模型,较为完整地考虑了各种热源对蒙皮温度的作用,包括气动加热、发动机热部件以及各部分的传导、对流和辐射。利用反向蒙特卡罗(RMC)法,并结合表面的多重遮挡算法,计算了飞行器复杂几何外形之间的辐射特性,分析了飞行器表面在8～14μm空间特定方向上的红外辐射特征。结果表明:飞行器马赫数是影响其8～14μm红外辐射特征的重要因素之一,在超音速飞行状态下,气动加热对红外辐射特征的影响比亚音速的大;减小蒙皮表面发射率降低了它的红外辐射强度。该方法可为飞行器表面红外辐射特征计算提供参考。
The theoretical model of the infrared radiation characteristics calculation of the aircraft skin was established. The effects of various heat sources on the skin temperature were comprehensively considered, including the aerodynamic heating, the hot parts of the engine and the conduction, convection and radiation of the parts. By using the inverse Monte Carlo (RMC) method, combined with the multi-surface occlusion algorithm, the radiation characteristics of the complex geometric shape of the aircraft were calculated and the infrared radiation characteristics of the aircraft surface in the specific direction of 8 ~ 14μm were analyzed. The results show that the Mach number of the aircraft is one of the most important factors affecting the characteristics of 8 ~ 14μm IR radiation. Under supersonic flight, the effect of aerodynamic heating on the infrared radiation characteristics is greater than that of subsonic sound, and the decrease of the surface emissivity of the skin Its infrared radiation intensity. This method can provide a reference for the calculation of the infrared radiation characteristics of aircraft surface.