Abstract: A dual-stage robust design method is concerned for the rotational maneuver and vibration stabilization of a flexible spacecraft. Based on the backstepping-based adaptive technique, a new attitude control law for attitude maneuvering is derived to control the attitude motion of spacecraft, in which the asymptotic stability is guaranteed by using Lyapunov analysis. Furthermore, for actively suppressing the induced vibration, strain rate feedback control compensator is designed using piezoelectric materials as additional sensors and actuators. Numerical simulations are performed to show that both maneuvering and vibration suppression can be accomplished effectively.