摘要
为了研究中心锥顶角和电磁波入射方位改变对航空发动机腔体的电磁散射特性的影响,采用物理光学（P0）法和等效棱边电磁流（EEC）法,对带中心锥发动机腔体在C波段入射频率f=6 GHz下进行电磁散射计算.计算结果表明：在水平极化下入射角为4＆#176;～28＆#176;范围内,中心锥顶角30＆#176;的发动机腔体的雷达散射截面（RCS）值较小;由等效电流图上得到特定角度下发动机腔体散射强弱分布,为发动机腔体关键散射区域采取隐身措施以提高隐身性能提供参考.
In order to research the effect of centrocone angle and electromagnetic wave incident direction changing on the electromagnetic scattering characteristics of engine cavity, the electromagnetic scattering of engine cavity with centrocone was calculated at 6GHz in C wave band using PO（ physical optics） and EEC （equivalent edge currents）. The calculation results indicate that the engine cavity with 30° cone angle presents low RCSs in horizontal polarization at 0=4°-28°; the electromagnetic scattering distribution by engine cavities at angle of interest is given by equivalent currents contour, which provide references to improve stealth capability of engine cavities by taking actions to key areas.
出处
《航空发动机》
2014年第1期48-53,59,共7页
Aeroengine
基金
航空科学基金(2011ZA06001)资助
关键词
中心锥
发动机腔体
雷达散射截面
物理光学法
等效棱边电磁流法
隐身
centrocone
engine cavity
radar cross section （RCS）
physical optics （PO）
equivalent edge currents （EEC）
stealth
