A Novel Approach for Satellite Attitude Reconfigurable Fault-tolerant Control

This paper investigates the reconfiguration fault-tolerant control method of the on-orbit satellite attitude control system with recovered faults. A novel integrated approach is proposed includes a control effectiveness factor and a reconfigurable fault-tolerant controller. A two-stage Kalman filtering algorithm is developed to estimate the size of control effectiveness factor in the closed-loop attitude control system. From the size of control effectiveness factor, a statistical hypothesis tests is developed to replace the fault detection and diagnosis (FDD) frame to diagnose whether there is some fault happened. Then, a reconfiguration fault-tolerant controller is utilized to compensate the primary controller by using the size of control effectiveness factor if some fault has happened. Finally, simulation is carried out and the results indicate the validation and effectiveness of the proposed solution.