飞行器蒙皮红外辐射特征的反向蒙特卡罗计算与分析方法

Numerical calculation and analysis of infrared radiation characteristics from aircraft skin by using RMC method

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。

A theoretical model calculating infrared radiation characteristics of aircraft skin was established, the various heat sources effecting the temperature of the aircraft skin was considered completely, including the aerodynamic heating, engine component and the conduction, convection, radiation in different parts. The infrared model for aircraft was represented with reverse Monte Carlo method（RMC）, combining the algorithm of surface＇s multi-occulation, the infrared radiation characteristics of the complex geometry contour of aircraft was calculated. The radiation characteristics of aircraft surface of 8-14 μm waveband in the given spatial direction were analyzed. The results show that the Mach number is one of the important factors that affecting infrared radiation characteristics on 8-14 μm band. In supersonic flight, effects of aerodynamic heating on infrared radiation characteristics are more evident than that in subsonic flight. To reduce emissivity of the aircraft skin can reduce its infrared radiation intensity. The methods provide reference on calculating infrared radiation characteristics of aircraft skin.