TY - GEN
T1 - Attitude synchronization for flexible spacecraft formation with actuator faults
AU - Wang, Qishao
AU - Huang, Di
AU - Duan, Zhisheng
AU - Wen, Guanghui
N1 - Publisher Copyright:
© 2016 IEEE.
PY - 2016
Y1 - 2016
N2 - In this paper, the problem of attitude synchronization for flexible spacecraft system with actuator faults is investigated. The spacecraft formation is studied in a leader-following architecture and the reference attitude is represented by a virtual leader. A distributed unit quaternion-based synchronization control law is proposed for flexible spacecraft with loss of actuator effectiveness fault. To damp out the induced oscillations of the spacecraft's flexible appendages, an adaptive parameter is introduced. Numerical simulations are presented to demonstrate the effectiveness of the proposed method.
AB - In this paper, the problem of attitude synchronization for flexible spacecraft system with actuator faults is investigated. The spacecraft formation is studied in a leader-following architecture and the reference attitude is represented by a virtual leader. A distributed unit quaternion-based synchronization control law is proposed for flexible spacecraft with loss of actuator effectiveness fault. To damp out the induced oscillations of the spacecraft's flexible appendages, an adaptive parameter is introduced. Numerical simulations are presented to demonstrate the effectiveness of the proposed method.
UR - https://www.scopus.com/pages/publications/85015177445
U2 - 10.1109/ICARCV.2016.7838728
DO - 10.1109/ICARCV.2016.7838728
M3 - 会议稿件
AN - SCOPUS:85015177445
T3 - 2016 14th International Conference on Control, Automation, Robotics and Vision, ICARCV 2016
BT - 2016 14th International Conference on Control, Automation, Robotics and Vision, ICARCV 2016
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 14th International Conference on Control, Automation, Robotics and Vision, ICARCV 2016
Y2 - 13 November 2016 through 15 November 2016
ER -