Abstract
We investigate the vibration control issues of rigid-flexible satellites and present a novel control methodology for vibration suppression during attitude maneuvers. Within the vibration model, we derive the terms of the disturbance load on each vibration mode, meticulously analyzing their effects. To reduce the impact of the disturbance load on vibration modes, the prescribed modal vibration control is proposed for vibration suppression, encompassing model adjustment, optimization of actuator/sensor deployment, and controller design. The effectiveness and the advantage of the prescribed modal vibration control are demonstrated through numerical simulations. This methodology achieves proper controlled vibration modes selection and optimized deployment, thereby amplifying the effect of vibration suppression in the presence of disturbances relative to extant vibration control methodologies.
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