Observer-Based Sliding Mode Control for Flexible Spacecraft With External Disturbance

Yu-Tian Xu,Rui-Qi Dong,Qing-Hua Zhu,Ai-Guo Wu

doi:10.1109/access.2020.2973657

Yu-Tian Xu, Rui-Qi Dong + Show 2 more

Open Access

https://doi.org/10.1109/access.2020.2973657

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Journal: IEEE Access	Publication Date: Jan 1, 2020
Citations: 5	License type: CC BY 4.0

Affiliation: Harbin Institute of Technology

Abstract

In this paper, attitude stabilization control for flexible spacecraft subject to external disturbance without angular velocity and flexible mode variables measurement is considered. First, an adaptive law is constructed to estimate the upper bound of a lumped disturbance consisting of flexible accessories and external disturbance. Based on the proposed adaptive law, an adaptive observer is established to estimate angular velocity and the lumped disturbance. Besides, for the case where flexible modal variables cannot be measured, a flexible modal variable observer-based sliding mode control law is proposed. Simulations are performed to verify the validity of the proposed control law. The simulation results show that the proposed control law can eliminate the influence of external disturbance for flexible spacecraft under the situation that angular velocity and flexible modal variables cannot be measured.

Highlights

Flexible spacecraft is composed of a central rigid body structure and flexible accessories [1]
Based on this disturbance observer, an adaptive finite-time attitude control law was constructed for rigid spacecraft
An adaptive law is proposed to estimate the upper bound of the lumped disturbance including external disturbance and flexible accessories

Summary

Introduction

Flexible spacecraft is composed of a central rigid body structure and flexible accessories [1]. In order to reduce the influence of the external and internal disturbance, a feasible method is to design disturbance observer. Such an idea has been adopted in [4], [5]. In [6], a second-order observer was used to estimate the disturbance combined by external disturbance, rigid spacecraft inertia uncertainty, and actuator fault. Based on this disturbance observer, an adaptive finite-time attitude control law was constructed for rigid spacecraft. In [7], external and internal disturbances were treated as a lumped disturbance, and a disturbance observer was designed to estimate

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