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Research Papers

Robust Fault Tolerant Control for Spacecraft Attitude Stabilization Under Actuator Faults and Bounded Disturbance

[+] Author and Article Information
Bing Xiao, Qinglei Hu

 Department of Control Science and Engineering, Harbin Institute of Technology, Harbin 150001, China

Michael I. Friswell

 College of Engineering, Swansea University, Singleton Park, Swansea SA2 8PP, UK

J. Dyn. Sys., Meas., Control 133(5), 051006 (Aug 01, 2011) (8 pages) doi:10.1115/1.4004061 History: Received June 10, 2010; Revised March 21, 2011; Published August 01, 2011; Online August 01, 2011

This paper investigates the design of spacecraft attitude stabilization controllers that are robust against actuator faults and external disturbances. A nominal controller is developed initially, using the adaptive backstepping technique, to stabilize asymptotically the spacecraft attitude when the actuators are fault-free. Additive faults and the partial loss of actuator effectiveness are considered simultaneously and an auxiliary controller is designed in addition to the nominal controller to compensate for the system faults. This auxiliary controller does not use any fault detection and isolation mechanism to detect, separate, and identify the actuator faults online. The attitude orientation and angular velocity of the closed-loop system asymptotically converge to zero despite actuator faults providing the nominal attitude system is asymptotically stable. Numerical simulation results are presented that demonstrate the closed-loop performance benefits of the proposed control law and illustrate its robustness to external disturbances and actuator faults.

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Copyright © 2011 by American Society of Mechanical Engineers
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Figures

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Figure 1

Simulation results with healthy actuators, case 1

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Figure 2

Simulation results with the partial loss of actuator effectiveness, case 2

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Figure 3

Simulation with time varying loss of actuator effectiveness and time varying additive faults, case 3

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