Sliding mode control based guidance law with impact angle constraint

作     者：Zhao Yao Sheng Yongzhi Liu Xiangdong 

作者机构：School of AutomationBeijing Institute of Technology Key Laboratory for Intelligent Control & Decision of Complex SystemsBeijing Institute of Technology 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2014年第27卷第1期

页      面：145-152页

核心收录：

学科分类：08[工学] 081105[工学-导航、制导与控制] 0802[工学-机械工程] 0825[工学-航空宇航科学与技术] 0811[工学-控制科学与工程] 0801[工学-力学（可授工学、理学学位）] 

基　　金：co-supported by National Natural Science Foundation of China (No. 61104153) National Basic Research Program of China (No. 2012CB720000) 

主　　题：Backstepping Impact angle Sliding mode control Terminal guidance Unpowered lifting reentryvehicle 

摘      要：The terminal guidance problem for an unpowered lifting reentry vehicle against a sta- tionary 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 effec- tiveness of the proposed guidance law is verified by the simulation results in various scenarios.