二元俯仰矢量喷管排气系统红外特征模拟实验  

Experiment on infrared signature of two dimensional convergent-divergent vectoring nozzle exhaust system

作　　者：卢浩浩[1] 吉洪湖[1] 刘健[1] 王丁[1] 王浩[1] 周兵[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2017年第8期1861-1868,共8页Journal of Aerospace Power

摘　　要：实验研究了二元俯仰矢量喷管排气系统在几何偏转角0°,10°,20°三种状态下的壁面温度分布与红外辐射特征,并与基准轴对称喷管排气系统进行了对比分析。结果表明:二元俯仰矢量喷管排气系统的红外辐射特征相对基准轴对称喷管排气系统有明显下降,正尾向降幅约10%;随着几何偏转角的增加,隔热屏与收敛段的温度逐渐上升,偏转段压力侧壁面温度略有上升,吸力侧壁面温度略有下降,最大变化幅值30K;排气系统红外辐射强度随偏转角增大而增大,尾向15°~45°和-15°^-60°范围内增幅明显,最大增幅可达70%。Experiments was conducted to study the distribution of wall temperature and infrared radiation characteristics on two dimensional convergent-divergent （2D-CD） vectoring nozzle exhaust system in three geometric deflection states,deflection of 0,10,20 degrees,and the results were compared with the reference axisymmetric nozzle exhaust system.The experimental results show that the infrared radiation characteristics is significantly lower than the reference axisymmetric nozzle exhaust system with a decline of 10% in the tail direction.With the increase of geometric deflection angle,the temperature of heat shield wall,convergent section wall increase,and the temperature of pressure side wall in deflection section increase slightly,while the temperature of suction side wall in deflection section decrease slightly,where the maximum change value is 30K;the increasing angle also significantly enhances the infrared radiation intensity,especially,in the tail direction from 15° to 45° and from-15° to-60°,where the maximum increase reaches 70%0.

关 键 词：排气系统 二元俯仰喷管 矢量偏转 红外辐射 轴对称喷管排气系统 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]