Finite-Time Control for Attitude Tracking Maneuver of Rigid Satellite

Mingyi Huo,Xing Huo,Jianfei Ni,Hamid Reza Karimi

doi:10.1155/2014/302982

Abstract

The problem of finite-time control for attitude tracking maneuver of a rigid spacecraft is investigated. External disturbance, unknown inertia parameters are addressed. As stepping stone, a sliding mode controller is designed. It requires the upper bound of the lumped uncertainty including disturbance and inertia matrix. However, this upper bound may not be easily obtained. Therefore, an adaptive sliding mode control law is then proposed to release that drawback. Adaptive technique is applied to estimate that bound. It is proved that the closed-loop attitude tracking system is finite-time stable. The tracking errors of the attitude and the angular velocity are asymptotically stabilized. Moreover, the upper bound on the lumped uncertainty can be exactly estimated in finite time. The attitude tracking performance with application of the control scheme is evaluated through a numerical example.

Highlights

Satellites need to perform attitude tracking maneuvers to accomplish orbital missions
The attitude stabilization was achieved for a rigid spacecraft subject to disturbances and uncertain inertia by using terminal SMC (TSMC), the attitude was only stabilized to a small region instead of zero in finite time [37]
Many sliding mode control (SMC) or TSMC based attitude tracking control schemes have been developed with external disturbances and uncertain inertia parameters investigated, most of them include two drawbacks

Summary

Introduction

Satellites need to perform attitude tracking maneuvers to accomplish orbital missions. In [17], an attitude tracking controller was proposed to guarantee global asymptotic stability of the system in the presence of disturbances and parameter uncertainties. In [27], an SMC-based control algorithm was designed for rigid spacecraft to perform attitude stabilization maneuver. In [28], adaptive law was synthesized to estimate the disturbance; sliding mode controllers were designed to achieve attitude tracking of a rigid spacecraft subject to uncertain inertia and external disturbance. The problem of attitude tracking control in the presence of uncertain inertia and external disturbances was further studied in [29, 30]. Taking external disturbances into account, an adaptive TSMC law was designed to achieve finite-time attitude tracking [35]. The states of attitude control system only converged to a small region of the XO YO

Figure 1

System Description and Problem Formulation

Finite-Time Attitude Tracking Control Design

Numerical Example

Findings

Conclusions and Future Work