Approximation-free Attitude Fault-tolerant Tracking Control of Rigid Spacecraft with Global Stability and Appointed Accuracy

For tumbling or non-cooperative targets in space missions, the prior knowledge of the target trajectory is unknown, which leads to the property of prescribed tracking accuracy with assigned settling time hard to achieve. In addition, the unknown inertia characteristics and the presence of actuator f...

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Bibliographic Details
Published in:IEEE transactions on aerospace and electronic systems 2023-10, Vol.59 (5), p.1-13
Main Authors: Huang, Xiuwei, Dong, Zhiyan, Zhang, Kai, Zhang, Feng, Zhang, Lihua
Format: Article
Language:English
Subjects:
Accuracy
Actuators
Appointed accuracy
Approximation
Approximation-free control
Attitude control
Attitude tracking control
Closed loops
Control methods
Control systems design
Control theory
Fault tolerance
Fault tolerant systems
Fault-tolerant control
Feedback control
Global stability
Inertia
Mathematical analysis
Space missions
Space vehicles
Spacecraft attitude control
Spacecraft control
Spacecraft stability
Spacecraft tracking
Target tracking
Tracking control
Tracking errors
Trajectory
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Summary:For tumbling or non-cooperative targets in space missions, the prior knowledge of the target trajectory is unknown, which leads to the property of prescribed tracking accuracy with assigned settling time hard to achieve. In addition, the unknown inertia characteristics and the presence of actuator faults will also reduce the robustness of the existing spacecraft control methods. To overcome these difficulties, a new approximation-free attitude tracking control scheme of spacecraft with unknown dynamics, external disturbance and actuator fault is proposed. For the designed controller, no inertia matrix is used, and no approximation-based or adaptive method is applied. Besides, it is rigorously proved that the developed control theory can also ensure that tracking error converges to the prescribed accuracy in appointed time even when the actuator fault occurs. Furthermore, a modified tuning function is used to relax the constraint of the initial value, which ensures the global stability of the closed-loop system. Simulation results verify effectiveness of the proposed method.
ISSN:0018-9251
1557-9603
DOI:10.1109/TAES.2023.3284415