摘要
为了降低临近空间飞艇的雷达散射截面(RCS)特性,研究了X型尾翼变形角的不同对临近空间飞艇RCS特性的影响.采用物理光学法仿真出X型尾翼不同变形角对临近空间飞艇头向、侧向和尾向RCS特性的影响,并分别采用物理光学法和多层快速多极子法(MLFMM)计算对比球的RCS.对比说明了物理光学法是准确合适的.仿真结果表明,X型尾翼变形角的不同对飞艇头向RCS影响较小,对侧向的RCS影响较大.变形角从0°增加到20°时,侧向RCS减小到0°时的13.7%.X型尾翼的变形可以显著改善临近空间飞艇侧向隐身性能,同时增大了其他方向的RCS.
In order to reduce the radar cross section（ RCS） of near space airship,the effect on the RCS of near space airship was studied,when its X-tail has different deformation angles. The RCS character effect of head,side and tail in the near space airship was simulated,when X-tail has different deformation angles based on physical optics method. Physical optics and multilevel fast multipole method（ MLFMM） were applied to simulate the RCS of contrast ball,and the results show that the physical optics method is accurate and appropriate. The simulation results show that the X-tail angle on different deformation has less influence on head RCS of airship,but has great influence on side RCS of airship. The side RCS reduced to 13. 7% when deformation angle changed from 0 ° to 20 °. The deformation of X-tail can significantly improve the performance of near space airship lateral stealth,while increasing the other direction RCS.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2015年第1期181-186,共6页
Journal of Beijing University of Aeronautics and Astronautics
基金
航空科学基金资助项目(2012ZA51009)
