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High-performance sliding mode control for orbit keeping of spacecraft using hybrid low-thrust propulsion

CHEN Yicheng;QI Ruiyun;ZHANG Jiarui;WANG Huanjie;College of Automation Engineering,Nanjing University of Aeronautics and Astronautics;Key Laboratory of Navigation,Control and Health-Management Technologies of Advanced Aerocraft,Ministry of Industry and Information Technology,Nanjing University of Aeronautics and Astronautics;Shanghai Aerospace Control Technology Institute;Shanghai Key Laboratory of Aerospace Intelligent Control Technology;  
For a spacecraft using hybrid solar sail and solar electric propulsion,the station-keeping control of the heliocentric displaced orbit is investigated.To solve the problem that internal unmodeled dynamics and external unknown disturbances are not considered comprehensively in the existing methods,and to further improve the performance of the system,a highperformance sliding mode control strategy is designed.Firstly,considering the uncertainty of the model,the dynamic equation of the hybrid low-thrust spacecraft keeping on heliocentric displaced orbit is established in the cylindrical coordinate system.Secondly,the control law is designed based on the improved conditional integral sliding surface and Radial Basis Function(RBF)neural network,and the uncertain parameters are estimated online by combining the adaptive method.Then,under the optimum condition of propellant,the virtual control variables are converted into actual control variables,namely attitude angles of solar sail and solar electric propulsion.Finally,numerical simulation verifies that the above design enhances the robustness of the system,reduces the overshoot of orbit position,and hybrid propulsion improves the control accuracy by 4 orders of magnitude in shorter convergence time compared to single solar sail propulsion,while it can save about 89.6% propellants a year compared to single solar electric propulsion.
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