Adaptive Fixed-Time Terminal Sliding Mode Control on SE(3) for Coupled Spacecraft Tracking Maneuver. (4th February 2020)

• Record Type: Journal Article
• Authors: Gong, Kejie; Liao, Ying; Wang, Yong
• Other Names: Biggs James D. Academic Editor.
• Is Part Of: International journal of aerospace engineering. Volume 2020(2020)
• Publication Date: 2020-02-04
• Subjects: Aerospace engineering -- Periodicals; 629.105
• DOI: 10.1155/2020/3085495
• Languages: English
• ISSNs: 1687-5966

Abstract

Abstract : In this paper, a reaching law-based adaptive fixed-time terminal sliding mode control law, which is used for coupled spacecraft tracking maneuver in the presence of large inertia parametric uncertainties and external disturbances, is proposed. The coupled 6-DOF kinematics and dynamics for spacecraft motion are modeled on Lie group SE(3). The relative configuration is expressed by a local coordinate (exponential coordinate) of SE(3). In order to estimate the inertia parameters and external disturbances, we also propose a novel adaptive update law, which can make the control law be applied without the inertia parameters of the spacecraft a priori. Fixed-time convergence property of the closed-loop feedback system is proved in the framework of Lyapunov. Numerical simulations are performed to demonstrate the performances of the proposed control scheme for coupled spacecraft tracking maneuver.