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Attitude and orbit Optimal control of Combined Spacecraft via a Fully-Actuated System Approach

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Journal of Systems Science & Complexity 2022年第2期35卷 623-640页

作者： DUAN Guangquan LIU Guo-Ping Center for control Theory and Guidance Technology Harbin Institute of TechnologyHarbin 150001China Department of Electronic and Electrical Engineering Southern University of Science and TechnologyShenzhen 518055China

This paper investigates the attitude and orbit control for the combined spacecraft formed after a target spacecraft without the autonomous control ability is captured by a service spacecraft.The optimal controller of fully-actuated system is proposed to realize the attitude and orbit stabilization control of combined spacecraft.The stability of the system is proved by introducing Lyapunov function.Numerical simulation of the combined spacecraft and physical experiment based on the combined spacecraft simulator(CSS)are completed.Both simulation and experiment results demonstrate the effectiveness and practicability of the optimal controller of fully-actuated system.

关键词： Attitude control combined spacecraft fully-actuated system optimal controller orbit control

Design and simulation of fault diagnosis based on NUIO/LMI for satellite attitude control systems

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Journal of Systems Engineering and Electronics 2012年第4期23卷 581-587页

作者： Yuehua Cheng Qian Hou Bin Jiang College of Automation Engineering Nanjing University of Aeronautics and Astronautics Nanjing 210016 R R. China Academy of Frontier Science Nanjing University of Aeronautics and Astronautics Nanjing 210016 P. R. China

This paper presents a scheme of fault diagnosis for flexible satellites during orbit maneuver. The main contribution of the paper is related to the design of the nonlinear input observer which can avoid false alarm arising from the disturbance from orbit control force. The effects of orbit control force on the fault diagnosis system for satellite attitude control systems, including the disturbing torque caused by the misalignments and the model uncertainty caused by the fuel consumed, are discussed, where standard Lu- enberger observer cannot work well. Then the nonlinear unknown input observer is proposed to decouple faults from disturbance, Besides, a linear matrix inequality approach is adopted to reduce the effect of nonlinear part and model uncertainties on the observer. The numerical and semi-physical simulation demonstrates the effectiveness of the proposed observer for the fault diagnosis system of the satellite during orbit maneuver.

关键词： orbit control flexible satellite attitude control system,nonlinear unknown input observer （NUIO） fault diagnosis.

A simplex method for the orbit determination of maneuvering satellites

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Science China(Physics,Mechanics & Astronomy) 2018年第2期61卷 49-55页

作者： JianRong Chen JunFeng Li XiJing Wang Jun Zhu DanNa Wang School of Aerospace Engineering Tsinghua University Beijing 100084 China State Key Laboratory of Astronautic Dynamics Xi'an 710043 China Shanghai Institute of Spaceflight control Technology Shanghai 201108 China

simplex method;;orbit determination;;electric propulsion;;orbit

关键词： simplex method orbit determination electric propulsion orbit control