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Integrated maneuvering and vibration control for spacecraft with single high-flexible structure based on global modal dynamic model

In order to improve maneuvering control performance for the spacecraft with single large flexible structure, an integrated maneuvering and vibration controller is proposed based on the global dynamic model. the global dynamic model is constructed by combing rigid modes and flexible modes. Piezoelectric patches are modeled into the model for active vibration suppression. Compared with the maneuvering controller without active vibration suppression, vibration magnitudes of rigid body's angular velocity and linear velocity are largely reduced by the integrated controller. Higher accuracy and stability are realized for the attitude control of the rigid body.