Fuzzy robust attitude maneuvers and active vibration suppression of flexible spacecraft

A robust control approach is presented for the attitude maneuvering control and vibration damping of a spacecraft with flexible appendages. Firstly, a fuzzy logic system is used to approximate the unknown dynamics of the spacecraft system. A new attitude controller is derived to control the attitude motion of spacecraft, in which the asymptotic stability is shown using a Lyapunov analysis. Secondly, for actively suppressing the induced vibration, strain rate feedback control methods are presented by using piezoelectric materials. Numerical simulations demonstrate the feasibility and effectiveness of the control strategy.