This paper considers the modeling and control of the rigid–flexible satellite in large-range planar motion. Employing Hamilton’s principle, a novel modeling of planar motion is obtained to describe the relationship between vibration and planar motion. Furthermore, nonlinear terms in the vibration dynamics are analyzed, and the influence of rotation on the stiffness of the flexible appendage is discussed through numerical computation and theoretical deduction. We proposed the all-modal control method to control the vibration completely, and real vibration control load is synthesized with all-modal controllers. Eventually, numerical simulations are presented to validate the effectiveness of the controller in planar motion.
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