球面收敛调节片喷管RCS数值模拟研究  

Numerical Simulation of RCS for Spherical Convergent Flap Nozzle

作　　者：崔金辉[1] 杨青真[1] 陈立海[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空发动机》2012年第2期46-50,共5页Aeroengine

摘　　要：结合物理光学迭代法(IPO)和等效棱边电磁流法(EEC),自主开发了电大尺寸腔体电磁散射特性计算程序,并通过对某试验模型雷达散射截面积(RCS)进行计算,完成了程序的可靠性验证。利用该程序对带有电磁信号遮挡板且采用3种不同尾缘修形技术的球面收敛调节片矢量喷管(SCFN)进行了RCS数值模拟研究。结果表明:随着入射方位角的增大,喷管的RCS整体上有减小的趋势;喷管尾缘的修形只有在雷达波以较大方位角入射时对减小RCS效果明显;电磁信号遮挡板的存在很大程度上减弱了喷管的电磁信号特征。Combining Iterative Physical Optic （IPO） and Equivalent Edge Currents （EEC）, a code for calculating the electromagnetic scattering characteristics of electrically large cavities was developed. The reliability of the code was validated through calculating Radar Cross Section （RCS） of an experiment model. Based on the code, RCS of Spherical Convergent Flap Nozzles （SCFN） with the electromagnetic signal shade and three different trailing edges shaping techniques was simulated. The results show that the RCS of the three nozzles has a decreasing tendency on the whole with the increase of the azimuth angles. The effect of traihng edges shaping technique on RCS is obvious only when the electromagnetic wave incidents at large azimuth angles. The electromagnetic signature characteristics of the nozzle is weaken largely by the external shelf weakens.

关 键 词：球面收敛调节片矢量喷管 修形技术 雷达散射截面积 物理光学迭代法 等效棱边电磁流法 航空发动机 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]