| Summary: | 碩士 === 國立成功大學 === 航空太空工程學系 === 106 === 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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