Decentralized sliding-mode control for spacecraft attitude synchronization under actuator failures |
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| Institution: | 1. Research Center of Satellite Technology, Harbin Institute of Technology, Harbin 150080, China;2. School of Electrical and Electronics Engineering, Nanyang Technological University, Nanyang Avenue, Singapore 639798, Singapore;3. DSO National Laboratories, Singapore 118230, Singapore;1. Department of Dynamics and Control, Beihang University, Beijing 100191, China;2. Department of Statistics and Mathematics, Inner Mongolia University of Finance and Economics, Huhhot 010070, China;3. Department of Mathematics, Southeast University, Nanjing 210096, China;4. Faculty of Engineering, King Abdulaziz University, Jeddah 21589, Saudi Arabia;1. Department of Aerospace Engineering, Ryerson University, Toronto, Ontario M5B 2K3, Canada;2. Department of Earth and Space Science and Engineering, York University, Toronto, Ontario M3J 1P3, Canada;1. Department of Mechanical Engineering, Sharif University of Technology, Tehran, Iran;2. Department of Aerospace Engineering, Sharif University of Technology, Tehran, Iran;1. Northwestern Polytechnical University, 127 West Youyi Road, Beilin District, Xi’an 710072, China;2. China Academy of Launch Vehicle Technology, No. 1 Nan Da Hong Men Road, Fengtai District, Beijing 100076, China |
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| Abstract: | This paper examines attitude synchronization and tracking problems with model uncertainties, external disturbances, actuator failures and control torque saturation. Two decentralized sliding mode control laws are proposed and analyzed based on algebraic graph theory. Using Barbalat?s Lemma, it is shown that the control laws guarantee each spacecraft approaches the desired time-varying attitude and angular velocity while maintaining attitude synchronization among the other spacecraft in the formation. The first controller is designed in the presence of model uncertainties, external disturbances, and actuator failures. The results are extended to the case with control input saturation in the second controller. Both control laws do not require online identification of failures. Numerical simulations are presented to show the effectiveness of the proposed attitude synchronization and tracking approaches. |
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| Keywords: | Attitude synchronization Sliding mode control Fault tolerant Attitude tracking Attitude control |
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