Finite-Time Controller for Flexible Satellite Attitude Fast and Large-Angle Maneuver

You Li,Haizhao Liang,Lei Xing

doi:10.3390/sym14010045

You Li, Haizhao Liang + Show 1 more

Open Access

https://doi.org/10.3390/sym14010045

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Journal: Symmetry	Publication Date: Dec 30, 2021
Citations: 2	License type: CC BY 4.0

Affiliation: Xidian University, Harbin Institute of Technology

Abstract

In order to deal with the fast, large-angle attitude maneuver with flexible appendages, a finite-time attitude controller is proposed in this paper. The finite-time sliding mode is constructed by implementing the dynamic sliding mode method; the sliding mode parameter is constructed to be time-varying; hence, the system could have a better convergence rate. The updated law of the sliding mode parameter is designed, and the performance of the standard sliding mode is largely improved; meanwhile, the inherent robustness could be maintained. In order to ensure the system’s state could converge along the proposed sliding mode, a finite-time controller is designed, and an auxiliary term is designed to deal with the torque caused by flexible vibration; hence, the vibration caused by flexible appendages could be suppressed. System stability is analyzed by the Lyapunov method, and the superiority of the proposed controller is demonstrated by numerical simulation.

Highlights

Current space missions, such as push-broom imaging and stare imaging, need satellites that have the ability to perform fast large-angle maneuvers
The deformation and vibration of flexible appendages would bring unexpected torque on the satellite system; the overall goal of this paper is to develop a satellite attitude controller subject to fast large-angle attitude maneuvers with a better convergence rate compared to standard controllers
It is proven that by implementing the updated law of the sliding mode parameter, the system could converge to the field near the equilibrium point within finite time, without causing the singularity issue during the whole control process

Summary

Introduction

Current space missions, such as push-broom imaging and stare imaging, need satellites that have the ability to perform fast large-angle maneuvers. Standard controllers, such as the PID controller and the sliding mode controller, have the issue of a low convergence rate. In the field of satellite attitude control, PID control and sliding mode control are the most mature and widely used methods. They both have the advantage of simple structures and strong robustness; a lot of work has been performed by researchers. Li [1,2,3] developed

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