基于TLC方法的空-空导弹三维末制导律研究  

An Investigation of Three Dimension Terminal Guidance Law Based on TLC Method for Air-to-air Missile

作　　者：朱秋芳[1] 姜长生[1] 朱亮[1] 谢祥华[1] 

机构地区：[1]南京航空航天大学自动化学院,南京210016

出　　处：《弹箭与制导学报》2007年第1期86-89,92,共5页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：国家自然科学基金资助(90405011)

摘　　要：针对导弹与目标之间的非线性运动学关系,在平行接近原理的基础上,结合轨迹线性化控制(TLC,trajectory linearization control)方法,为某型空-空导弹研究设计了一种新型的三维末制导律。仿真结果表明,所设计的基于TLC方法的制导律是有效的,且在目标机动情况下比传统的比例制导律以及滑模变结构制导律具有更好的制导性能。Aim at the nonlinear kinematics relation between the missile and target, based on the parallel approach principle, this paper studies and designs a novel three terminal guidance law. The simulating results show that the guidance law designed in this paper based on TLC method is effective and has better guidance performance than that of the conventional proportional and sliding model guidance law in the situation of target maneuver.

关 键 词：三维末制导律 轨迹线性化控制 目标机动 空空导弹 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]