Sliding-mode fault-tolerant attitude control for spacecraft using SGCMGs

Based on sliding-mode control and adaptive control, the passive fault-tolerant attitude control problem of rigid spacecraft using single gimbal control moment gyros (SGCMGs) was studied. First, the system mathematical model with fault of the speed of gyro framework was established. Then, a fault-tolerant controller, based on sliding-mode control theory, was designed to control the speed of gyro framework while an adaptive control law was employed in the controller to estimate the fault and disturbance message. Thus, it can achieve the attitude stability control with strong robustness in both defective and trouble-free cases, without knowing the prior information of the fault and disturbance. Finally, the simulation results of different fault modes of two configurations of SGCMGs verify the effectiveness and feasibility of this method.