Nonlinear Dynamics of a Post-Buckled Beam for Actuating Helicopter Trailing Edge Flap

摘要

Active trailing edge flaps are one of the potential candidates for helicopter vibration reduction. Smart actuators likernpiezoelectric stack actuators (PEAs) are used for trailing edge flap actuation. Piezostack actuators possess high energyrndensity and have large force in dynamic condition but have small displacements. In this study, we develop a pinnedpinnedrnpost-buckled beam linear to rotary motion amplification mechanism (AM-2) to actuate trailing edge flaps. Arnlinear motion amplification mechanism (LX-4) is coupled with AM-2 to achieve the enhanced angular flap deflections.rnMaximum flap angle deflections of the order of 25 degrees is achieved in static case. An optimization study is alsornperformed to maximize the flap deflections. The optimal beam dimensions are checked for stability analysis and arnsensitivity analysis is performed for helicopter operational frequencies. With AM-2 mechanism, a reduction of 91%rnin helicopter vibrations is obtained with multiharmonic control inputs.