一种新的具有攻击角度约束的末制导律设计  

Adaptive Robust Guidance Law Design for Air-to-Ground Missile with Impact Angle Constraint

作　　者：郭建国[1] 周军[1] 

机构地区：[1]西北工业大学精确制导与控制研究所,陕西西安710072

出　　处：《计算机仿真》2013年第8期70-73,172,共5页Computer Simulation

基　　金：航天支撑基金项目(N11XW0001)

摘　　要：研究导弹末制导性能优化问题,在末端要满足攻击角度的约束条件,要求优化空地导弹末制导命中目标精度性能。针对导弹和地面目标所形成动态系统的非线性运动学关系,通过分析导弹在终端命中点角度约束条件,并利用零化视线角速率的设计思想,根据滑模变结构控制理论,提出了一种非线性滑模设计方法,得到了具有攻击角度约束的导弹的末制导律。同时利用Lyapunov稳定理论严格证明了制导系统的全局渐近稳定性。把末制导律应用于导弹系统并进行仿真,结果表明,在不需要任何目标运动信息的情况下,导弹都能获得期望的攻击角度约束和制导精度,证明导弹制导算法对地面目标有较强的鲁棒性。According to impact angle requirement in the case of air-to-surface missile attacking the target,based on variable structure theory,a nonlinear terminal guidance law was proposed by zeroing the rate of line-of-sight angle with a study of the condition of terminal angle corresponding to the state equation of a missile-target relative motion system.The asymptotic stability of guidance system was proven by Lyapunov stability theory.When the guidance law was used,the expected impact angle and guidance precision were met.Simulation results with the guidance law show that the guidance law is a strongly robust guidance law against targets in the ground in the case of no any target information.

关 键 词：末制导律 终端角度 滑动模态 视线角速率 

分 类 号：TJ765.43[兵器科学与技术—武器系统与运用工程]