采用SBR法研究飞机进气道的雷达散射截面  

Research on RCS of airplane duct based on SBR method

作　　者：万顺生[1] 罗屹洁[1] 郭荣伟[1] 

机构地区：[1]南京航空航天大学无人机研究院,南京210016

出　　处：《航空动力学报》2006年第6期1033-1036,共4页Journal of Aerospace Power

摘　　要：采用弹跳射线法(SBR)对飞机发动机进气道的雷达散射截面(RCS)进行了分析计算.通过光学射线跟踪、场强跟踪及口径积分方法,研究了任意截面和形状的管道电磁散射特性,通过在微波暗室的实际测量,频率在X波段,分别进行垂直极化和水平极化两种方式测试,比较了一实际进气道的计算与实验结果,验证了此方法的有效性,与其他方法相比较,具有物理概念清晰、数学模型容易建立等特点,满足了实际应用的需要.RCS of engine duct was calculated and analyzed using SBR method. EM scattering characteristics of the pipe with arbitrary section and shape were studied by the methods of shooting and bouncing rays, field intensity track and aperture integral. In the ways of vertical polarization and horizontal polarization, real measurement at the frequency of X wave band was done in the anechoic chamber. The calculation was compared with the experimental result for a real engine duct. It proves that this method is very effective. Compared with other methods, its physical conception is clear, mathematical models can be set up more easily and it also meets practical needs in engineering.

关 键 词：航空 航天推进系统 射线 进气道 雷达散射截面 微波暗室 隐身技术 

分 类 号：V218[航空宇航科学与技术—航空宇航推进理论与工程]