Abstract: Input shaping and closedloop feedback control are combined to realize the vibration reduction of spacecraft with flexible appendages during the attitude maneuver control. To ensure the validity of input shaping for suppressing the vibration of flexible appendages, the effect of uncertain parameters, such as system inertia and modal matrix, are considered during the attitude maneuver. A method to calculate the model parameters of input shaper, which is based on maximum residual vibration, is proposed. And the impact of uncertain parameters to vibration reduction of flexible appendages is quantitatively analyzed, which can be as a theoretical basis for selecting proper input shaper. It reduces the conservation of traditional input shaper and contributes to enhance the control performance. Simulation analysis indicates that  the vibration suppression with considering system uncertain parameters is better than without them.

Key words: input shaper, attitude maneuver, vibration reduction, uncertain parameters