摘要
为获得一体化加力燃烧室中锥体的雷达隐身修形角度对发动机后向雷达散射截面(RCS)的影响规律,支撑一体化加力燃烧室雷达隐身修形设计,构建了配装轴对称喷管和一体化加力燃烧室的发动机后腔体RCS计算模型,利用弹跳射线法(SBR)和物理绕射理论(PTD)方法进行了电磁散射特性仿真研究,分析了锥体全锥角对发动机后向RCS的影响。结果表明:对一体化加力燃烧室的锥体进行雷达隐身修形设计能显著降低发动机后向RCS,可使发动机后向在0°~30°区间RCS均值缩小30%以上;在配装轴对称喷管的条件下,一体化加力燃烧室锥体全锥角的选取应重点避开70°~100°区域;当锥体全锥角小于62°时,一体化加力燃烧室具有较好的雷达隐身效果。
In order to obtain the influence law of radar stealth shaping angle of integrated afterburner cone to aeroengine backward radar cross section(RCS),and support the integrated afterburner radar stealth shaping design.The RCS calculation model of an engine rear cavity with axisymmetric nozzle and integrated afterburner was constructed,the shooting and bouncing ray(SBR)method and physical theory of diffraction(PTD)method were used in electromagnetic scattering characteristics simulation,the influences of the cone angle on aeroengine backward RCS were analyzed.The simulation results show that radar stealth shaping for the cone of the integrated afterburner can significantly reduce aeroengine backward RCS,the mean value of aeroengine backward RCS from 0°to 30°can be reduced by more than 30%;when assembled with axisymmetric nozzle,the cone angle of the cone of the integrated afterburner should not be selected in the range of 70°to 100°;when the cone angle is less than 62°,the integrated afterburner has a better radar stealth effect.
作者
王群
杨胜男
卢浩浩
邓洪伟
陈瀚赜
WANG Qun;YANG Sheng-nan;LU Hao-hao;DENG Hong-wei;CHEN Han-ze(AECC Shenyang Engine Research Institute,Shenyang 110015,China;National Key Laboratory of Aerospace Power System and Plasma Technology,Shenyang 110015,China)
出处
《航空发动机》
北大核心
2025年第1期65-69,共5页
Aeroengine
基金
国家级研究项目资助。
