A Second-Order Sliding Mode Controller Design for Spacecraft Tracking Control

Yu-Xin Zhao,Gang Li,Tian Wu

doi:10.1155/2013/429101

Abstract

For spacecraft attitude tracking system, there exists the chattering phenomenon. In this paper, the spacecraft motion is decomposed into three-channel subsystems, and a second-order sliding mode control is proposed. This method has been proved to have good convergence and robustness. Combined with the proposed sliding surface, the three-channel controllers are designed. The control performance is confirmed by the simulation results, the approaching process is improved effectively, and a smooth transition is achieved without overshoot and buffeting.

Highlights

Sliding mode variable structure control (SMC) is very suitable for spacecraft control system design because of its unique advantages, such as the simple algorithm, no need of the precise mathematical model for the controlled object, and the invariability of the control system when the parameter perturbation exists and the external disturbance conforms exactly to the matching condition [1].But classical variable structure control system has a fatal flaw, namely “chattering” phenomenon, which is the main obstacle for SMC to promote in the engineering field [2]
The control performance is confirmed by the simulation results, the approaching process is improved effectively, and a smooth transition is achieved without overshoot and buffeting
The control methods used are based on a general variable structure control theory, which is very unfavorable for the normal operation of spacecraft control system due to the existence of the chattering phenomenon; it could lead to system instability

Summary

A Second-Order Sliding Mode Controller Design for Spacecraft Tracking Control

For spacecraft attitude tracking system, there exists the chattering phenomenon. The spacecraft motion is decomposed into three-channel subsystems, and a second-order sliding mode control is proposed. This method has been proved to have good convergence and robustness. Combined with the proposed sliding surface, the three-channel controllers are designed. The control performance is confirmed by the simulation results, the approaching process is improved effectively, and a smooth transition is achieved without overshoot and buffeting

Introduction

Spacecraft Model

Reaching Condition Design and Proof

Controller Design

Simulation Results

Conclusion