直接力/气动力复合控制拦截弹末制导精度研究  

Terminal Guidance Accuracy of Aerodynamics/Side-Jet Compound Control Interception Missile

作　　者：李玉林[1] 万自明[2] 

机构地区：[1]北京理工大学宇航科学技术学院,北京100081 [2]中国航天科工集团公司二院二部,北京100854

出　　处：《现代防御技术》2008年第2期55-60,共6页Modern Defence Technology

摘　　要：建立复合控制导弹的末制导回路;研究了天线罩折射率、目标机动、目标角闪烁对气动力控制和复合控制时的末制导精度影响。研究表明复合控制对天线罩折射误差率的要求更为严格;复合控制对拦截大机动目标更为有效,但只考虑目标角闪烁时,空气动力控制的效果更好;综合目标机动和角闪烁的影响,复合控制可提高制导精度。The terminal guidance loop of compound control interception missile is established.The effects caused by the radome slopes,target maneuver and target glint noise are analyzed.Simulation shows the compoud control interception missile is more sensitivity to radome slopes and more efficient for intercepting target bearing large maneuver than the aerodynamics control,however,only considering target glint noise,the aerodynamics control is better.Considering target maneuver and glint noise,the guidance accuracy o...

关 键 词：拦截弹 直接力控制 复合控制 制导精度 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]