Finite-time sliding mode control based 3D guidance law with impact angle constraints
ZHAO Yao1, LI Pu1,2, LIU Juan1, CHEN Zhe1, LIU Xiangdong3
1. China Academy of Launch Vehicle Technology, Beijing 100076, China;
2. National University of Defense Technology, Changsha 410073;
3. School of Automation, Beijing Institute of Technology, Beijing 100081, China
Abstract：To deal with the guidance problem of missile for intercepting ground fixed targets, a three-dimensional finite-time sliding mode control based guidance law is proposed in this paper. It is proved by the Lyapunov theory that the guidance law can steer the missile to intercept target with the desired impact angles in both azimuth and elevation. The guidance law has four advantages. First, model decoupling or model linearization is not needed in this work; second, the impact angles in both longitudinal and horizontal can be controled; third, the guidance command can be analytically derived; fourth, the closed-loop system is insensitive to external disturbance as well as parameter uncertainty. The simulation results show that high terminal accuracy and good robustness can be achieved by the proposed guidance law.
赵曜, 李璞, 刘娟, 陈喆, 刘向东. 带碰撞角约束的三维有限时间滑模制导律[J]. 北京航空航天大学学报, 2018, 44(2): 273-279.
ZHAO Yao, LI Pu, LIU Juan, CHEN Zhe, LIU Xiangdong. Finite-time sliding mode control based 3D guidance law with impact angle constraints. JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2018, 44(2): 273-279.
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2018, Vol. 44 
