Abstract
Previous research in active structural acoustic control (ASAC) has focused primarily on flat plates. In order to facilitate the realistic evaluation of the closed loop performance of ASAC systems for aircraft cabin noise reduction, efforts are being made to consider complicating effects in panel dynamics to more accurately reflect the service conditions of aircraft fuselage panels. As part of these efforts, a model of a curved piezo-structure was developed and used to determine the effects of curvature on panel dynamics and transducer integration. Curvature was shown to affect transducer coupling and control system bandwidth. The present work considers the effects of internal pressure loading created by aircraft cabin pressurization. Internal pressure loading is shown to affect panel dynamics significantly, raising further issues in control system design and transducer integration for structural acoustic control applications. [Research supported by NASA Langley Research Center under Grant No. NCC 1 250.]
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