TY - GEN
T1 - Hybrid control and steering logic for the CMG-based spacecraft attitude control system
AU - Xin, Xing
AU - Li, Zhen
AU - Liu, Xiangdong
AU - Chen, Zhen
N1 - Publisher Copyright:
© 2015 IEEE.
PY - 2015/11/4
Y1 - 2015/11/4
N2 - Considering the momentum singularity characteristics, an integrated control strategy for the control moment gyros based attitude control systems is proposed, in which the angular momentum conservation between the spacecraft and the CMG is utilized to improved the system performance both in the closed loop responsiveness and the singularity controllability. The moment exchange capability of the CMGs can be fully developed by the control logic under normal operation, while the exchange space is specifically restrained to guarantee the effectiveness of the singularity avoidance steering when gimbal lock occurs. An online uncertainty identification method based on the momentum exchange property is applied in the hybrid control logic to improve the robustness of the system for the first place, and the remaining uncertainty is further handled by an adaptive control law. Numerical simulations for the practical agile spacecraft maneuvering are conducted to verify the effectiveness of the proposed algorithms.
AB - Considering the momentum singularity characteristics, an integrated control strategy for the control moment gyros based attitude control systems is proposed, in which the angular momentum conservation between the spacecraft and the CMG is utilized to improved the system performance both in the closed loop responsiveness and the singularity controllability. The moment exchange capability of the CMGs can be fully developed by the control logic under normal operation, while the exchange space is specifically restrained to guarantee the effectiveness of the singularity avoidance steering when gimbal lock occurs. An online uncertainty identification method based on the momentum exchange property is applied in the hybrid control logic to improve the robustness of the system for the first place, and the remaining uncertainty is further handled by an adaptive control law. Numerical simulations for the practical agile spacecraft maneuvering are conducted to verify the effectiveness of the proposed algorithms.
UR - http://www.scopus.com/inward/record.url?scp=84964319913&partnerID=8YFLogxK
U2 - 10.1109/CCA.2015.7320712
DO - 10.1109/CCA.2015.7320712
M3 - Conference contribution
AN - SCOPUS:84964319913
T3 - 2015 IEEE Conference on Control and Applications, CCA 2015 - Proceedings
SP - 780
EP - 785
BT - 2015 IEEE Conference on Control and Applications, CCA 2015 - Proceedings
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - IEEE Conference on Control and Applications, CCA 2015
Y2 - 21 September 2015 through 23 September 2015
ER -