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在飞行器机身表面的温度场建模中综合考虑了超音速飞行气动加热、发动机舱内部流动换热,以及排气喷流对飞行器后体的传热等影响,采用数值计算的方法对飞行器8~14μm波段的蒙皮及发动机壁面红外辐射特征进行了研究,分析了飞行器机头、机身(含进气道)、机翼、发动机舱(含飞行器后体)、垂直尾翼、水平尾翼和发动机喷管腔体等部位的红外辐射。结果表明:蒙皮辐射是飞行器8~14μm波段红外辐射的主要组成部分,发动机壁面红外辐射主要集中在飞行器尾向±50°范围内;在不同的观测平面,飞行器不同部位对整机8~14μm波段的红外辐射贡献比例各有侧重,飞行器机身、机翼、发动机舱和垂直尾翼是飞行器8~14μm波段红外辐射的主要部分;飞行马赫数提高将加剧机身气动加热效果,飞行机不同部位所占的红外辐射比例将有所改变。
In the modeling of the temperature field of aircraft fuselage surface, the effects of supersonic aerodynamic heating, heat transfer inside the engine compartment and the heat transfer of the exhaust jet to the rear body of the aircraft are considered. ~ 14μm band of the skin and the infrared radiation characteristics of the engine wall were studied, the aircraft nose, the fuselage (including the intake port), the wing, the engine compartment (including aircraft body), the vertical tail, the tailplane and the engine Nozzle cavity and other parts of the infrared radiation. The results show that the skin radiation is the main component of the infrared radiation in the 8 ~ 14μm band of the aircraft. The infrared radiation of the engine wall mainly concentrates within ± 50 ° of the tail of the aircraft. In different observation planes, Infrared radiation contribution to the band has its own focus, the aircraft fuselage, wing, engine compartment and vertical tail wing aircraft 8 ~ 14μm band infrared radiation is the main part of the flight Mach number will aggravate the fuselage aerodynamic heating effect, different parts of the aircraft The proportion of infrared radiation will be changed.