基于终端角度约束的滑模制导律设计  

Sliding mode guidance law design based on terminal angle constraint

作　　者：李志平[1] 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：《飞行力学》2012年第4期345-348,共4页Flight Dynamics

基　　金：航天科技创新基金资助(N11XW0001);西北工业大学基础研究基金资助(JC201024)

摘　　要：针对打击地面目标的制导问题,提出了一种新的具有终端角度约束的鲁棒滑模制导律。在建立地面目标和导弹的相对运动学关系的基础上,基于零化弹目视线角速率的思想,采用变结构控制理论的方法,通过选择理想的终端角度确定一个光滑的非线性滑动模态,代替传统末制导律设计的滑动模态,利用Lyapunov稳定理论设计得到了具有鲁棒性的滑模末制导律,实现了在有限时间精确打击目标,满足终端角度的要求。数字仿真表明,这种制导律对目标的运动具有很好的鲁棒性和适应性,并能获得良好的制导精度和指定的终端角度要求。For the guidance of attacking target on the ground,a new robust nonlinear sliding mode guidance law with terminal angle constraint is proposed.The mathematic model was built according to nonlinear relationship between missile and target whose acceleration as disturbance was introduced.Based on variable structure control theory and the method of zeroing the rate of line-of-sight angle between missile and target,a suitable nonlinear terminal sliding mode with ideal terminal angle is chosen instead of conventional sliding mode,a new nonlinear sliding mode guidance law is designed,and the reachability and stability of sliding mode is strictly proved by Lyapunov stability theory to satisfy the condition of terminal angle.Finally,the digital simulation results show that the sliding mode guidance law is adopted to attack the ground target,both the impact angle and guidance precision are met in the case of no any target information.

关 键 词：滑动模态 非线性 LYAPUNOV方法 稳定性 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]