An Adaptive Fault Compensation Scheme for Formation Control of Spacecraft Formation Flying

The relative position model is established to meet the requirement of the leader-follower spacecraft formation. In this model, we consider the follower spacecraft actuator fault which the fault model is combined with loss of effectiveness and constant deviation fault. The adaptive controller is designed to solve the uncertainty caused by the actuator fault. Based on the Lyapunov theory, it is proved that the relative position error and velocity error can converged to zero under the controller. Simulation result proves the effectiveness of this method.