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为了降低飞行器的红外辐射,适应发动机排气系统与飞机后机身的匹配,设计了一种非常规的S弯二元喷管,喷管出口中心线与发动机轴线不共线,有一个小偏距.在商业软件中计算该S弯二元喷管的温度场、速度场、压力场和组分浓度的分布,采用自主开发的红外软件,用反向蒙特卡罗法计算该喷管的红外辐射特性,并与基准轴对称喷管的计算结果进行对比,计算结果表明:采用小偏距S弯二元喷管后,能够对排气系统内部高温部件有一定的遮挡,对红外辐射特征有一定的抑制作用,最大能够降低33%的红外辐射.
In order to reduce the infrared radiation of the aircraft and to adapt the matching between the engine exhaust system and the rear fuselage of the aircraft, an unconventional S-bend binary nozzle is designed. The nozzle outlet centerline is not collinear with the engine axis, and has a small deviation The calculation of the distribution of the temperature field, velocity field, pressure field and component concentration of the S-bend binary nozzle in the commercial software uses the infrared software developed by ourselves and the inverse Monte-Carlo method to calculate the infrared The results show that the nozzle with small offset S-bend can effectively block the high temperature components inside the exhaust system, and have the characteristics of infrared radiation A certain inhibition, the maximum can reduce 33% of the infrared radiation.