关键词: 智能旋翼, 后缘襟翼, 几何精确梁, 气动代理模型, 旋翼自由尾迹, 振动控制

Abstract:

A computational analysis was conducted to address the vibration reduction problem in the trailing-edge flap smart rotor system. First， a geometrically exact beam model based on Hamilton’s principle was employed to establish the aeroelastic coupling model of the system. 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 effectiveness was further investigated. The calculation analysis results demonstrate that when the flap was deflected at single frequencies of 3/rev， 4/rev， 5/rev， 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 components exhibited combined influences from the corresponding single-frequency components as the control phase shifted. Variations 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