Henry J K, Clark R L
Department of Mechanical Engineering and Materials Science, Duke University, Durham, North Carolina 27708-0302, USA.
J Acoust Soc Am. 1999 Sep;106(3 Pt 1):1400-7. doi: 10.1121/1.427143.
Current research in Active Structural Acoustic Control (ASAC) relies heavily upon accurately capturing the application physics associated with the structure being controlled. The application of ASAC to aircraft interior noise requires a greater understanding of the dynamics of the curved panels which compose the skin of an aircraft fuselage. This paper presents a model of a simply supported curved panel with attached piezoelectric transducers. The model is validated by comparison to previous work. Further, experimental results for a simply supported curved panel test structure are presented in support of the model. The curvature is shown to affect substantially the dynamics of the panel, the integration of transducers, and the bandwidth required for structural acoustic control.
当前有源结构声学控制（ASAC）的研究在很大程度上依赖于准确捕捉与被控制结构相关的应用物理原理。将ASAC应用于飞机内部噪声控制需要更深入地了解构成飞机机身蒙皮的曲面面板的动力学特性。本文提出了一个带有附着压电换能器的简支曲面面板模型。通过与先前的工作进行比较对该模型进行了验证。此外，还给出了简支曲面面板测试结构的实验结果以支持该模型。结果表明，曲率对面板的动力学特性、换能器的集成以及结构声学控制所需的带宽有显著影响。
