直升机雷达散射截面计算与试验验证  

The Calculation and the Experimental Validation of the Radar Cross Section for Helicopter

作　　者：武庆中[1] 招启军[2] 

机构地区：[1]中国直升机设计研究所,江西景德镇333001 [2]南京航空航天大学直升机旋翼动力学国家级重点实验室,江苏南京210016

出　　处：《直升机技术》2012年第1期25-30,共6页Helicopter Technique

摘　　要：采用高频预估法,建立了一套基于"面元边缘"的直升机RCS计算方法,然后对某型直升机进行了RCS计算分析以及RCS测试。最后,对比分析直升机机身雷达散射试验和理论计算结果,得出了一些减缩直升机RCS的外形设计特征。结果表明:在设计要求许可的情况下,改变武器挂架长度比改变后掠角缩减RCS效果要明显;直升机头部鼻锥部位使用锥形结构,可以减小头向方位RCS;直升机主桨榖采用圆台形代替圆柱形,可以减缩头向和侧向方位的RCS。This paper set up the RCS calculation method of helicopter based on surface cell and edge adopting the high-frequency prediction method.And then,the RCS characteristics of a certain armed helicopter were calculated and experimental research on armed helicopter fuselage was conducted.Finally,the experimental results were compared with the calculation results,and some shape design features reducing the RCS of helicopter have been obtained.The conclusion displayed that changing length of the weapon girder compared with sweepback angle had better effect in reducing RCS and using the taper shape could reduce RCS in the head direction and the hub adopting the round desk shape compared with the column shape could reduce RCS in the head direction and the lateral direction.

关 键 词：高频 直升机 RCS 减缩 

分 类 号：V218[航空宇航科学与技术—航空宇航推进理论与工程]