大离轴角发射空空导弹制导律研究  

Research on Guidance Law of Air-to-air Missile for High Off-boresight Launch Condition

作　　者：何素娟[1] 周军[1] 周凤岐[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《弹箭与制导学报》2006年第S5期165-166,171,共3页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：讨论了空空导弹在大离轴角发射时的快速转弯控制律。在推力矢量控制下,在给定的时间内,使平行于初始视线方向上的速度分量达到最大,并使终端速度最大。数字仿真表明,该控制律在打击载机后半球目标方面具有很好的性能。An guidance law of agile turn of air to air missile in off-borsight launching is discussed.Under thrust vector control,the missile is demanded to maximize the velocity component in parallel director of initial sight in given time,and its final velocity becomes maximum.The digital simulation based on this control law denotes that it possesses very well performance in attacking the targets from the rear hemisphere.

关 键 词：空空导弹 离轴发射 推力矢量控制 快速转弯 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]