TY - GEN
T1 - Tracking control of spacecraft formation flying with time delay and H2/H∞ constraints
AU - Gong, Ligang
AU - Wang, Qing
AU - Li, Jun
AU - Dong, Chaoyang
N1 - Publisher Copyright:
© 2014 IEEE.
PY - 2015/1/12
Y1 - 2015/1/12
N2 - In this paper, the tracking control of relative motion of two spacecraft in a leader-follower form is investigated. The time delay of signal transmission between the two spacecraft and external disturbances are explicitly considered. For time delay, we model the relative motion in a linear form and utilize the Lyapunov-Krasovskii functional combining with free-weighting matrix method to complete the stability analysis. The external disturbances are then attenuated in the H∞ sense. Besides, we take the integral quadratic of the tracking error and control input as the tracking performance index, which is in the H2 sense. A set of linear matrix inequalities (LMIs) is then derived incorporating all the design requirements and cone complementarity linearization technique is used to solve the LMIs. The theoretical analysis is completed based on the general motion model of circular reference orbit for leader spacecraft and numerical simulation results demonstrate the validity of the designed controller.
AB - In this paper, the tracking control of relative motion of two spacecraft in a leader-follower form is investigated. The time delay of signal transmission between the two spacecraft and external disturbances are explicitly considered. For time delay, we model the relative motion in a linear form and utilize the Lyapunov-Krasovskii functional combining with free-weighting matrix method to complete the stability analysis. The external disturbances are then attenuated in the H∞ sense. Besides, we take the integral quadratic of the tracking error and control input as the tracking performance index, which is in the H2 sense. A set of linear matrix inequalities (LMIs) is then derived incorporating all the design requirements and cone complementarity linearization technique is used to solve the LMIs. The theoretical analysis is completed based on the general motion model of circular reference orbit for leader spacecraft and numerical simulation results demonstrate the validity of the designed controller.
UR - https://www.scopus.com/pages/publications/84922568966
U2 - 10.1109/CGNCC.2014.7007233
DO - 10.1109/CGNCC.2014.7007233
M3 - 会议稿件
AN - SCOPUS:84922568966
T3 - 2014 IEEE Chinese Guidance, Navigation and Control Conference, CGNCC 2014
SP - 177
EP - 182
BT - 2014 IEEE Chinese Guidance, Navigation and Control Conference, CGNCC 2014
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 6th IEEE Chinese Guidance, Navigation and Control Conference, CGNCC 2014
Y2 - 8 August 2014 through 10 August 2014
ER -