Experimentally Investigating Active Vibration Control of Panel Structure of Airplane
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摘要: 压电材料的机电耦合特性使其在智能结构和振动控制中得到了广泛的应用。本文中以压电材料作为传感器和作动器,选用飞机壁板为控制对象,在Patran中对控制对象建立了有限元模型,利用Nastran对建立的模型数据进行了计算,分析出了壁板各阶模态的最大应变位置。根据分析结果在壁板合理位置上粘贴多片压电陶瓷片,运用基于Filter-X LMS(Least Means Squares)自适应算法对壁板进行了单模态和多模态的主动控制试验并取得了良好的控制效果,1阶模态降低了约10 dB,2阶模态降低了约5 dB。Abstract: Piezoelectric materials are widely applied to smart structures and active vibration control fields due to their good electromechanical performance.We select piezoelectric materials as sensor and actuator and take the panel of an airplane as the control object.We also use the Patran to build its finite element model and calculate its data with Nastran,thus obtaining the maximum stress position of the panel in every-order mode.According to the analysis results,we place the possible position and number of piezoelectric patches on the panel.We use the filterX LMS(least means squares) adaptive algorithm to perform the active vibration control of the panel in its singleorder mode and multi-order modes,achieving good control effects,namely first-order mode and second-order mode decreases by 10 dB,5 dB respectively.
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Key words:
- actuators /
- intelligent structures /
- modal analysis /
- piezoelectric materials
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