TY - GEN
T1 - Large Flexible Spacecraft Simulation System
T2 - 41st Chinese Control Conference, CCC 2022
AU - Wang, Xiping
AU - Yu, Changli
AU - Zhang, Dali
AU - Wu, Mengxuan
AU - Ma, Guangcheng
AU - Xia, Hongwei
N1 - Publisher Copyright:
© 2022 Technical Committee on Control Theory, Chinese Association of Automation.
PY - 2022
Y1 - 2022
N2 - This paper proposes a simulation system design together with an effectiveness evaluation method for large flexible spacecraft. To handle the vibration problem of the flexible accessory of the spacecraft simulation system, a sliding mode controller is used to suppress the flexible vibration. To realize the on-orbit identification of the moment of inertia of the flexible spacecraft and improve the identification accuracy, a parallel recursive method is proposed by combining generalized Kalman filtering with recursive least squares. The simulation results verify that the proposed sliding mode control algorithm has strong stability and can effectively suppress the vibration of flexible accessories, and its adjustment time is about 1/10 of PID control. Meanwhile, the proposed identification method has improved accuracy compared with traditional methods, and the identification error can be reduced to 4%. Furthermore, the analytic hierarchy process (AHP) is used to evaluate the effectiveness of the spacecraft simulation device proposed in this paper. The reliability of the simulation system is calculated to be 96.7%, which can be used as a verification platform for related algorithm research.
AB - This paper proposes a simulation system design together with an effectiveness evaluation method for large flexible spacecraft. To handle the vibration problem of the flexible accessory of the spacecraft simulation system, a sliding mode controller is used to suppress the flexible vibration. To realize the on-orbit identification of the moment of inertia of the flexible spacecraft and improve the identification accuracy, a parallel recursive method is proposed by combining generalized Kalman filtering with recursive least squares. The simulation results verify that the proposed sliding mode control algorithm has strong stability and can effectively suppress the vibration of flexible accessories, and its adjustment time is about 1/10 of PID control. Meanwhile, the proposed identification method has improved accuracy compared with traditional methods, and the identification error can be reduced to 4%. Furthermore, the analytic hierarchy process (AHP) is used to evaluate the effectiveness of the spacecraft simulation device proposed in this paper. The reliability of the simulation system is calculated to be 96.7%, which can be used as a verification platform for related algorithm research.
KW - Effectiveness evaluation
KW - Kalman filter
KW - Large flexible spacecraft
KW - Simulation system design
KW - Sliding mode control
KW - Unconstrained mode
UR - https://www.scopus.com/pages/publications/85140452742
U2 - 10.23919/CCC55666.2022.9902847
DO - 10.23919/CCC55666.2022.9902847
M3 - 会议稿件
AN - SCOPUS:85140452742
T3 - Chinese Control Conference, CCC
SP - 1396
EP - 1401
BT - Proceedings of the 41st Chinese Control Conference, CCC 2022
A2 - Li, Zhijun
A2 - Sun, Jian
PB - IEEE Computer Society
Y2 - 25 July 2022 through 27 July 2022
ER -