Practical Finite-Time Control of Missiles–A Terminal Sliding Mode Approach
作者单位：Harbin Institute of Technology
会议名称：《第36届中国控制会议》
会议日期：2017年
学科分类：08[工学] 081105[工学-导航、制导与控制] 0804[工学-仪器科学与技术] 0811[工学-控制科学与工程]
基 金：supported by the Major Program of National Natural Science Foundation of China under Grant Numbers 61690210,61690211 and 61690212 National Natural Science Foundation of China(No.61503100,61203125) China Postdoctoral Science Foundation(No.2014M550189) Heilongjiang Postdoctoral Fund(No.LBHZ13076) Self-Planned Task (NO.SKLRS201716A) of State Key Laboratory of Robotics and System(HIT)
关 键 词：missile control terminal sliding mode finite-time robust control
摘 要：This paper investigates the missile attitude control problem. The model used in this paper is with respect to the Euler attitude angles and their derivatives which can be measured and computed easily. A robust practical finite-time control algorithm is proposed based on the terminal sliding mode approach. It is proved that all of the signals in the closed-loop system are bounded and the tracking error can be driven into a given small neighborhood of the origin in the pre-specified time. The simulation results show the effectiveness of the proposed results.