Sliding mode control based guidance law with impact angle constraint

查看全文 作　　者：Zhao [1,2]Yao;Sheng [1,2]Yongzhi;Liu [1,2]Xiangdong

机构地区：[1]School of Automation,Beijing Institute of Technology;[2]Key Laboratory for Intelligent Control & Decision of Complex Systems,Beijing Institute of Technology

出　　处：《Chinese Journal of Aeronautics》索引2014年第27卷第1期,共8页

基　　金：co-supported by National Natural Science Foundation of China (No. 61104153);National Basic Research Program of China (No. 2012CB720000) 摘　　要：The terminal guidance problem for an unpowered lifting reentry vehicle against a stationary target is considered. In addition to attacking the target with high accuracy,the vehicle is also expected to achieve a desired impact angle. In this paper,a sliding mode control(SMC)-based guidance law is developed to satisfy the terminal angle constraint. Firstly,a specific sliding mode function is designed,and the terminal requirements can be achieved by enforcing both the sliding mode function and its derivative to zero at the end of the flight. Then,a backstepping approach is used to ensure the finite-time reaching phase of the sliding mode and the analytic expression of the control effort can be obtained. The trajectories generated by this method only depend on the initial and terminal conditions of the terminal phase and the instantaneous states of the vehicle.In order to test the performance of the proposed guidance law in practical application,numerical simulations are carried out by taking all the aerodynamic parameters into consideration. The effectiveness of the proposed guidance law is verified by the simulation results in various scenarios. 关键词：滑模控制角度约束制导律空气动力学参数再入飞行器碰撞解析表达式攻击目标

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Sliding mode control based guidance law with impact angle constraint

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