Fault-Tolerant Control for Flexible Spacecraft Attitude Maneuver via Integral Sliding Mode Control Approach

An integral sliding mode fault-tolerant control scheme is developed to investigate the problem of flexible spacecraft attitude maneuver. The designed approach is robust and insensitive to external perturbations and model uncertainty resulted from measuring error of the inertia matrix and partial loss of actuator effectiveness. The use of proportional-integral controller reduce the chattering phenomena in sliding mode control scheme. Hence, we can achieve a more appropriate control accuracy. Finally, simulation results are included to demonstrate the effectiveness of this method.