Fault-tolerant control for the linearized spacecraft attitude control system with Markovian switching |
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| Institution: | 1. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410000, China;2. School of Aeronautics and Astronautics, Sun Yat-sen University, Shenzhen 518055, China;3. Shenzhen Key Laboratory of Visual Object Detection and Recognition, Harbin Institute of Technology, Shenzhen, Shenzhen 518055, China;4. School of Intelligent Systems Engineering, Sun Yat-sen University, Shenzhen 518055, China;1. School of Electrical Engineering, Yanshan University, Qinhuangdao, China;2. School of Control Engineering, Northeastern University at Qinhuangdao, Qinhuangdao, China;1. Department of Electrical Engineering, Faculty of Engineering, University of Guilan, Rasht, Iran;2. Department of Mechanical and Industrial Engineering, Norwegian University of Science and Technology, Trondheim, Norway;1. Key Laboratory of Networks and Cloud Computing Security of Universities in Chongqing, School of Electronic and Information Engineering, Southwest University, Chongqing, China;2. School of Cyberspace Security, Beijing Institute of Technology, Beijing, China |
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| Abstract: | In this article, the fault-tolerant control is investigated for the spacecraft attitude control system described by a linearized model with Markovian switching. First, the evolution of sudden failures of the spacecraft’s actuators is described by a Markov process. Then, the mathematical model of the spacecraft attitude control system with the Markov jump characteristic fault is established. Taking the uncertainty of the system model and external interference into consideration, a fault-tolerant control scheme is proposed for the established spacecraft attitude control system with the Markov jump characteristic fault by using the sliding mode control technique. Compared with some existing sliding mode controller design methods, the proposed method requires a less total number of LMIs to be solved. The stability and reachability of the resulting closed-loop system under the presented sliding mode control scheme are proven by applying the Lyapunov stability theory. Finally, some simulation results are provided to show the effectiveness and advantages of the proposed control method for spacecraft attitude control. |
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