基于状态观测器的变结构末制导律设计  

A variable structure terminal guidance design based on state observer

作　　者：蒋瑞民[1] 周军[1] 郭建国[1] 王国庆[2] 

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 [2]中国运载火箭技术研究院研究发展中心,北京100076

出　　处：《电子设计工程》2013年第21期148-150,154,共4页Electronic Design Engineering

基　　金：航天支撑基金资助(N11XW0001)

摘　　要：本文针对仅有相对距离和视线角可测的导弹,设计了一种基于状态估计的变结构末制导律。将非线性项和目标机动视为新的状态变量实现对原相对运动方程进行的扩张,设计扩张状态观测器实现对不可测的相对距离变化率和视线角变化率的估计。基于扩张观测器的估计值,利用变结构控制理论设计了保证切向速度趋向于零的末制导律,从而实现导弹直接命中目标,并从理论上对制导回路的稳定性进行了证明。最后进行了数学仿真,仿真结果表明在设计的制导律脱靶量较小,验证了扩张观测器和制导律的可行性。A variable structure terminal guidance law based on state observer was proposed for the missile only with the relative distance and angle of sight information.The relative motion equation was expanded by choosing the nonlinear parts and the target maneuvering accelerations as new state variable.A expanded state observer was designed to estimate the rate of relative distance and sight angular velocity.A terminal guidance law was designed based on variable structure control theory that ensured the tangential velocity of the missile tending to zero.The stability of the closed-loop guidance system was proved.Numerical simulation was conducted and the simulation results show that the proposed guidance law has small miss-distance which proved the feasibility of the state observer and guidance law.

关 键 词：扩张状态观测器 变结构控制理论 末制导律 切向速度 

分 类 号：TN919[电子电信—通信与信息系统]