作　　者： ; ;

机构地区： 西安电子工程研究所

出　　处： 《火控雷达技术》 2007年第3期35-40,共6页

摘　　要： 针对末制导采用角度导引、比例导引两种制导律的导弹进行数值仿真,结果显示,角度导引飞行过程平稳,对导引头稳定伺服机构隔离度,对天线罩瞄准误差要求较低,但制导精度会随着目标运动速度增大变差;比例导引导弹飞行过程运动变化相对剧烈,对天线罩要求较高,但制导精度明显高于角度导引系统。 Digital simulations of missiles respectively using the angle guidance law and the proportional navigation law are simulated in this paper. The results show that, using angle guidance law leads to stable guidance process, thus reduces the requirement of antenna servo＇s stabilization performance and the seeker＇s sensitivity to radome boresight error, but the miss distance will become unacceptable with the increase of target speed. For the missile adopting proportional guidance law, its flying process is not so stable, and the radome boresight errors will also affect the guidance process, but the miss distance will not be affected by the target speed.

关 键 词： 制导律 导引头 数值仿真 天线罩

领　　域： [电子电信] [电子电信] [自动化与计算机技术] [自动化与计算机技术]