Stabilisation of a Flexible Spacecraft Subject to External Disturbance and Uncertainties

Yun Fu,Lingyan Hu,Yu Liu,Lingxi Peng

doi:10.1155/2020/2906546

Abstract

This paper addresses the problems of vibration reduction and attitude tracking for a flexible spacecraft subject to external disturbances and uncertainties. Based on Hamilton’s principle, flexible spacecraft is modelled by a coupled nonlinear partial differential equation with ordinary differential equations. Adaptive boundary control scheme is adopted to stabilize the vibration displacement of flexible appendage into a small neighbourhood of original position and simultaneously maintain attitude angle within the desired angle region. Two disturbance adaptive laws are constructed to attenuate the effect of unknown external disturbances. The well posedness of the controlled system is proven by using the semigroup theory. The proposed adaptive boundary control scheme can guarantee the uniform boundedness of the closed-loop system. Numerical simulation results illustrate the effectiveness of the proposed control scheme.

Highlights

Spacecraft with flexible appendage is playing a key role in the development of the communication industry and remote sensing
In the complex space environment, flexible appendage may vibrate under the effects of external disturbances and attitude maneuver
We investigate the vibration reduction and attitude control of a flexible spacecraft with parameter uncertainties. e accurate dynamic model of flexible spacecraft is given by a set of coupled partial differential equation with ordinary differential equations

Summary

Introduction

Spacecraft with flexible appendage is playing a key role in the development of the communication industry and remote sensing. In the complex space environment, flexible appendage may vibrate under the effects of external disturbances and attitude maneuver. In [4], a variable structure control based on pulse-width pulse-frequency technology is designed to suppress the vibration of a flexible spacecraft with parameter uncertainties and input nonlinearity. Ese results motivate us to design an adaptive boundary control scheme for the flexible spacecraft system. The robustness of the disturbance observers proposed in these papers is weak and the structure physical parameters of flexible spacecraft are uncertain. Handling the effect of external disturbances in control design for a flexible spacecraft with uncertain parameters is still challenging. We investigate the vibration reduction and attitude control of a flexible spacecraft with parameter uncertainties.

Dynamics Analysis

Stability Analysis

Simulation

Conclusion