In order to solve the attitude maneuver problem for flexible spacecraft with time-varying parameters, the variable amplitudes zero vibration derivative shaper with stronger robustness was developed based on the variable amplitudes zero vibration shaper. The robust attitude maneuver strategy, in which its objective was to maneuver the spacecraft to the desired attitude state and cancel the residual vibration of the rotating flexible appendages at the same time, was proposed. Simulations were conducted by means of a spacecraft with rotating solar wings which undergoes three-axis maneuvers. The results indicate that this strategy is robust to frequency variations, uncertainties of damping coefficient and other uncertain factors.