中心锥锥角对航空发动机腔体RCS的影响  

Effect on RCS of central cone angle in aero-engine cavity

作　　者：邓雪姣 李晓明 马健 卢婷 DENG Xue-jiao;LI Xiao-ming;MA Jian;LU Ting(AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China)

机构地区：[1]中国航发四川燃气涡轮研究院

出　　处：《燃气涡轮试验与研究》2019年第6期31-35,共5页Gas Turbine Experiment and Research

摘　　要：为研究航空发动机中心锥锥角对发动机腔体电磁散射特性的影响,采用迭代物理光学法和矩量法计算了不同锥角下雷达散射截面(RCS)随探测角度的变化,分析了不同探测角度范围下RCS平均值的变化趋势。结果表明:在-6°~6°探测角下,中心锥半锥角45°为RCS均值峰值点,半锥角40°及60°时出现RCS均值波谷值;40°或60°半锥角可作为航空发动机中心锥设计参考值。The effect on electromagnetic scattering characteristics of central cone angle in aero-engine cav⁃ity was analyzed.The Radar Cross Section(RCS)of models with different central cone angles was calculated through Iterative Physical Optics(IPO)and Method of Moments(MOM),and the variation trend of the aver⁃age RCS of different angular range was analyzed.The calculation results show that at detecting angle-6°~6°,the model with half central cone angle at 45°shows the highest average RCS at backward direction.With half central cone angle at 40°and 60°,the average RCS reaches the trough value.The half central cone angles at 40°and 60°are the recommended values for the design of aero-engine central cone.

关 键 词：航空发动机 隐身性 中心锥锥角 腔体 雷达散射截面 迭代物理光学法 矩量法 

分 类 号：V218[航空宇航科学与技术—航空宇航推进理论与工程]