一体化加力燃烧室支板雷达隐身修形仿真

Study on Radar Stealth Shaping for Struts of Integrated Rear Frame and Afterburner

为获得一体化加力燃烧室中支板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,以配装轴对称喷管的某型发动机为载体,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,分析了支板倾斜角度和斜切角度对发动机后向RCS的影响。结果表明:对一体化加力燃烧室支板尾端进行雷达隐身修形设计能够显著降低发动机后向RCS均值,可使发动机后向0°~30°范围RCS均值下降40%以上;在配装轴对称喷管的情况下,支板倾斜角的选取应重点避开88°~98°区域,斜切角的选取应重点避开0°~8°区域,当支板尾端倾斜角为68°、斜切角为16°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 influencing law of radar stealth shaping angle of strats of integrated rear frame and afterburner to aeroengine rear aspect radar cross section(RCS),and to support the strats of integrated rear frame and afterburner radar stealth design,numerical simulation of the electromagnetic scattering characteristics an aeroengine equipped with an axisymmetric nozzle were conducted using shooting and bouncing ray(SBR)and physical theory of diffraction(PTD)method,the influences of struts tilt angle and obliquely-cut angle on aeroengine rear aspect RCS were analyzed. The simulation results show that the radar stealth shaping for struts can reduce aeroengine rear aspect RCS significantly. When equipped with axisymmetric nozzle,the struts tilt angle should avoid 88° to 98°,the struts obliquely-cut angle should avoid in 0° to 8°,when the tilt angle is 68° and the obliquely-cut angle is 16°,strats of integrated rear frame and afterburner exhibits a better radar stealth effect.