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飞机由于高频涡流的作用 ,局部复合材料构件承受面外脉动冲击载荷 ,产生累积疲劳损伤 .本文采用 13型压电片粘贴在复合材料构件表面 ,测量构件在交变气动载荷下的应变 ,应用自适应振动前馈控制原理 ,施加电压主动控制压电驱动器的变形 ,实现对复合材料构件的应变驱动 ,从而提高壁板构件的模态阻尼 ,减小动态响应 ,达到减小复合材料构件疲劳损伤的目的 .实验结果表明构件的应变幅值得到了有效的抑制
Due to the effect of high-frequency eddy current, the local composite material subjected to out-of-plane pulsating impact load has accumulated fatigue damage.In this paper, a 13-type piezoelectric film is pasted on the surface of the composite material to measure the strain of the component under alternating aerodynamic loads. Adaptive vibration feedforward control principle, the applied voltage to actively control the deformation of the piezoelectric actuator, to achieve the strain of the composite material driven components, thereby increasing the modal damping wall panels to reduce the dynamic response, to reduce the composite component fatigue damage The experimental results show that the component strain amplitude is effectively suppressed