Abstract: A computational analysis was conducted to address vibration reduction in the trailing-edge flap smart rotor system. First, a geo-metrically exact beam model based on Hamilton's principle was employed to establish the aeroelastic coupling model of the sys-tem. Following validation through case studies, the effects of single- and combined-frequency deflection parameters on the rotor hub vibration components were analyzed. The influence of rotor blade stiffness characteristics on the vibration reduction effec-tiveness was further investigated. Results demonstrated that when the flap was deflected at single frequencies of 3, 4, 5, and 6/rev, over 60% vibration reduction could be achieved for specific 4/rev hub load. However, simultaneous suppression of multiple 4/rev hub force and moment components proved challenging. For combined-frequency deflections, the hub vibration compo-nents exhibited combined influences from the corresponding single-frequency components as the control phase shifted. Varia-tions in the trailing-edge flap deflection amplitude revealed that the optimal and worst vibration reduction initial phase values did not change obviously. Furthermore, the bending-torsion coupling of elastic blade dominated the actuation effectiveness of the trailing-edge flap while introducing additional system nonlinearities.

Key words: smart rotor, trailing-edge flap, geometrically exact beam, aerodynamic surrogate model, rotor free wake, vibration control