SE(3)-based Finite-time Fault-tolerant Control of Spacecraft Integrated Attitude-orbit

Authors

Yafei Mei, College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China;Follow
Ying Liao, College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China;Follow
Kejie Gong, College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China;
Xingyu Zheng, College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China;

Abstract

Abstract: For relative motion spacecraft, when the actuator fails and the external disturbance and system uncertainty occur simultaneously, a finite-time fault-tolerant control method is proposed on the basis of the robustness of sliding mode control. A single-rigid spacecraft integrated attitude-orbit model is established based on Lie Group SE(3), and the relative motion spacecraft error dynamic equation is derived in exponential coordinates. A class of non-singular fast terminal sliding surface is designed, and the equivalent adaptive method is adopted to design the controller to estimate and compensate the total disturbance. The proposed fault-tolerant control algorithm can be independent from fault diagnosis and detection. Lyapunov method is used to prove the stability and fast convergence of the system under multiple constraints such as faults and disturbances. The analysis on numerical simulation results also verifies the fastness, accuracy and reliability of the fault-tolerant controller.

Recommended Citation

Mei, Yafei; Liao, Ying; Gong, Kejie; and Zheng, Xingyu (2023) "SE(3)-based Finite-time Fault-tolerant Control of Spacecraft Integrated Attitude-orbit," Journal of System Simulation: Vol. 35: Iss. 2, Article 5.
DOI: 10.16182/j.issn1004731x.joss.21-0988
Available at: https://dc-china-simulation.researchcommons.org/journal/vol35/iss2/5

First Page

277

Revised Date

2021-11-22

DOI Link

https://doi.org/10.16182/j.issn1004731x.joss.21-0988

Last Page

285

CLC

TP271+.62

Recommended Citation

Yafei Mei, Ying Liao, Kejie Gong, Xingyu Zheng. SE(3)-based Finite-time Fault-tolerant Control of Spacecraft Integrated Attitude-orbit[J]. Journal of System Simulation, 2023, 35(2): 277-285.

Corresponding Author

Ying Liao,liaoying1104@aliyun.com

DOI

10.16182/j.issn1004731x.joss.21-0988