Velocity-Free State Feedback Fault-Tolerant Control for Satellite with Actuator and Sensor Faults

Mingjun Liu,Bing Xiao,Aihua Zhang

doi:10.3390/sym14010157

Abstract

A velocity-free state feedback fault-tolerant control approach is proposed for the rigid satellite attitude stabilization problem subject to velocity-free measurements and actuator and sensor faults. First, multiplicative faults and additive faults are considered in the actuator and the sensor. The faults and system states are extended into a new augmented vector. Then, an improved sliding mode observer based on the augmented vector is presented to estimate unknown system states and actuator and sensor faults simultaneously. Next, a velocity-free state feedback attitude controller is designed based on the information from the observer. The controller compensates for the effects of actuator and sensor faults and asymptotically stabilizes the attitude. Finally, simulation results demonstrate the effectiveness of the proposed scheme.

Highlights

As an important component of the satellite, the attitude control system plays a key role in practical aerospace missions, such as space on-orbit services and spacecraft pointing and turning
This work mainly studies the fault tolerant control (FTC) of attitude stabilization guaranteed in the case of actuator and sensor faults
Simulation results are presented to verify the effectiveness of the proposed observer (Equation (27)) and velocity-free state feedback fault-tolerant attitude controller (VSFTC) (Equation (41))

Summary

Introduction

As an important component of the satellite, the attitude control system plays a key role in practical aerospace missions, such as space on-orbit services and spacecraft pointing and turning. Numerous studies on attitude control methods have emerged, such as adaptive variable structure control (VSC) [1,2], robust control [3,4,5,6,7], output feedback control [8,9], time-delayed control [10], and finite-time control [11,12,13] The premise of these control methods is the assumption that there exists no actuator or sensor fault during satellite maneuvers. If the designed attitude control system does not have the ability to deal with the faults, it may lead to the failure of the target space missions or even the destruction of the satellite [14]. This work mainly studies the fault tolerant control (FTC) of attitude stabilization guaranteed in the case of actuator and sensor faults

Objectives

Results

Conclusion