Abstract
In this paper, we focus on solving the problems of inertia-free attitude tracking control for spacecraft subject to external disturbance, unknown inertial parameters, and actuator faults. The robust control architecture is designed by using the rotation matrix and neural networks. In the presence of external disturbance and parametric uncertainties, a fault-tolerant control (FTC) scheme synthesized with the minimum-learning-parameter (MLP) algorithm is proposed to improve the reliability of the system when unknown actuator faults occur. These methods are developed based on backstepping to ensure that finite-time convergence is achievable for the entire closed-loop system states with low computational complexity. The validity and advantage of the designed controllers are highlighted by using Lyapunov-based analysis. Finally, the simulation results demonstrate the satisfactory performance of the developed controllers.
Highlights
With the rapid development of space engineering, spacecraft attitude control has been studied extensively by researchers for its essential role in various space missions, involving deep space exploration, earth observation, Mars detection, etc
Designing controllers with satisfactory performance for spacecraft still remains a challenging task, which can be attributed to complex external disturbance, unknown inertial parameters, and actuator faults
Though fruitful results have been obtained for attitude control of spacecraft during the last decades, it still remains a challenge to design finite-time controllers under the circumstances of the external disturbance and unknown inertial matrix
Summary
With the rapid development of space engineering, spacecraft attitude control has been studied extensively by researchers for its essential role in various space missions, involving deep space exploration, earth observation, Mars detection, etc. Designing controllers with satisfactory performance for spacecraft still remains a challenging task, which can be attributed to complex external disturbance, unknown inertial parameters, and actuator faults Despite these obstacles, numerous methods have been designed to address the attitude tracking control problem, including backstepping control [1,2,3,4], sliding mode control [5,6,7], prescribed performance control [8,9,10], and event-triggered control [11, 12]. Compared with existing methods [16, 33], inertial parameters could remain unavailable, making the tracking controllers more applicable in aerospace engineering (ii) Actuator faults and unknown system dynamics could be handled simultaneously with the aid of the FTC strategy proposed in this paper.
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