Finite‐time attitude stabilization of rigid spacecrafts based on control Lyapunov functions

• Published in: IET control theory & applications Vol. 16; no. 7; pp. 663 - 673
• Main Authors: Wu, Yu‐Yao, Zhang, Ying, Wu, Ai‐Guo
• Format: Journal Article
• Language: English
• Published: Stevenage John Wiley & Sons, Inc 01.04.2022; Wiley
• Subjects: Attitude stability; Control systems; Controllers; Design; Energy consumption; Investigations; Liapunov functions; Parameter estimation; Parameter uncertainty; Performance indices; Sliding mode control; Spacecraft; Spacecraft attitude control; Spacecraft control; Spacecraft stability; State observers
• ISSN: 1751-8644; 1751-8652
• DOI: 10.1049/cth2.12256

In this paper, the control Lyapunov function (CLF) approach is adopted to investigate the finite‐time attitude control of rigid spacecraft subject to parameter uncertainty and external disturbance. By using an extended state observer to estimate the parameter uncertainty and external disturbance, a finite‐time CLF controller is proposed for attitude stabilization of the spacecraft system. The designed finite‐time CLF controller includes two parts. The first part is a classical CLF based attitude controller, which is proposed to ensure the globally asymptotical stability of the nominal spacecraft system. The second one is a sliding mode controller, which is used to ensure the finite‐time convergence performance of the spacecraft control system. The advantage of the designed controller is that the states of the system can converge into a small neighourhood of zero in finite time, and simultaneously the given performance index can be minimized. The practical finite‐time stability of the resulted closed‐loop system is proven via Lyapunov stability theory. Finally, simulation results illustrate the effectiveness of the developed finite‐time controller.