Adaptive neural finite-time control for space circumnavigation mission with uncertain input constraints |
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| Authors: | Hanlin Dong Xuebo Yang |
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| Institution: | 1. Research Institute of Intelligent Control and Systems, Harbin Institute of Technology, Harbin 150001, China;2. School of computer science, Harbin University of Science and Technology, Harbin 150001, China;1. Fair Friend Institute of Intelligent Manufacturing, Hangzhou Vocational and Technical College, Hangzhou 310018, PR China;2. Institute of Information and Control, Hangzhou Dianzi University, Hangzhou 310018, PR China;1. The School of Information and Control Engineering, Liaoning Shihua University, Fushun 113000, PR China;2. The Institute of Intelligence Science and Engineering, Shenzhen Polytechnic, Shenzhen 518055, PR China;3. National Laboratory of Industrial Control Technology, Institute of Cyber-Systems and Control, Zhejiang University, Yuquan Campus, Hangzhou Zhejiang 310027, PR China;1. Medical IT Convergence Research Section, Electronics and Telecommunications Research Institute (ETRI), Daegu 42994, Republic of Korea;2. School of Electronic and Electrical Engineering, Kyungpook National University, Daehak-ro 80, Republic of Korea;3. Smart Mobility Research Section, Electronics and Telecommunications Research Institute (ETRI), Daegu, Republic of Korea;4. Cyber Physical Systems & Control Laboratory, School of Electronic and Electrical Engineering, Kyungpook National University, Daehak-ro 80, Republic of Korea;1. College of Science, Hebei Agricultural University, Baoding 071001, China;2. School of Science, Nanjing University of Science and Technology, Nanjing 210094, China;3. School of Information Technology, Jiangxi University of Finance and Economics, Nanchang 330013, China;4. School of Mathematics and Physics, Anhui Polytechnic University, Wuhu 241000, China |
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| Abstract: | This paper explores the design of an anti-saturation adaptive finite-time control strategy with the neural network (NN) technique for the space circumnavigation mission. Before executing the controller design, the analytical solutions of the desired angular velocity and its derivative of the active spacecraft are calculated. Since there are uncertain saturation constraints on control forces and moments in the actual propulsion system, an auxiliary system compensated by an adaptive NN is adopted. The modified auxiliary system no longer needs the precise output values of the actuators. Besides, the hyperbolic tangent function is introduced to design the weight update law for the NN compensator, so that the derivative of the weight estimator will not be amplified by the quadratic of states when the system states are large. It is proved that tracking errors of the system states can converge to a residual set of the origin in finite time. Simulation results show that the maximum amplitudes of the control signals are greatly reduced compared to the classical non-singular terminal sliding-mode control scheme, and that the neural-based compensator can significantly weaken the overshoot and chattering. |
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