複合材料在航空產業已經有大量的實際應用，其中複合疊層夾心材料模擬於在靜態及動態相關研究上雖有一些文獻可供參考，但在結構振動控制部分較少見，且較少研究是建立在真實的複材機翼結構。而在致動器及感測器配置問題上，大多是採用同位的方式黏貼於結構物上下表面，較少文獻有提及分開任意擺放的形式。
本文研究複材機翼感測器與致動器最佳配置問題，以考量翼型函數之複材機翼為模型，致動器與感測器黏貼於機翼上下翼面之任意位置，透過有限元素軟體ANSYS撰寫複材機翼振動控制參數語言，感測器輸出值及輸入電壓構成之二次形式為目標函數，搭配其軟體內部之最佳化模組，探討感測器與致動器擺放的最佳位置。除此之外，對於配置方面額外討論了複合夾心樑、複合夾心板等例，並以翼面漸縮之機翼進行驗證及探討。

Composite materials have been used extensively in the aviation industry. Although some investigations in static and dynamic performances of composite laminated sandwich materials can be found, it’s rarely seen the research about structural vibration suppression, and less research is based on the composite wing structures. Besides, in the configuration of actuators and sensors, less literature has been mentioned in the form of separate placement.
This paper discusses the optimal placement of sensors and actuators. A composite wing with an airfoil function is considered as a model. The actuators and the sensors are glued to any position on the upper and lower wing surfaces. Simulations of active vibration control are done by ANSYS. In optimization problem, a quadratic function related to the vibration amplitude and control input is defined as the objective function. With optimization module in the software, the optimal placement of the sensors and actuators is discussed. In addition, the composite sandwich beam and panel are extra discussed in terms of configuration, and the composite wing with tapered airfoil is verified and discussed.

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