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首页> 外文期刊>The Journal of the Acoustical Society of America >The vibro-acoustic response and analysis of a full-scale aircraft fuselage section for interior noise reduction
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The vibro-acoustic response and analysis of a full-scale aircraft fuselage section for interior noise reduction

机译：全尺寸飞机机身截面的振动声响应及内部降噪分析

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摘要

The surface and interior response of a Cessna Citation fuselage section under three different forcing functions (10-1000 Hz) is evaluated through spatially dense scanning measurements. Spatial Fourier analysis reveals that a point force applied to the stiffener grid provides a rich wavenumber response over a broad frequency range. The surface motion data show global structural modes (less than or similar to 150 Hz), superposition of global and local intrapanel responses (similar to 150-450 Hz), and intrapanel motion alone (greater than or similar to 450 Hz). Some evidence of Bloch wave motion is observed, revealing classical stop/pass bands associated with stiffener periodicity. The interior response (less than or similar to 150 Hz) is dominated by global structural modes that force the interior cavity. Local intrapanel responses (greater than or similar to 150 Hz) of the fuselage provide a broadband volume velocity source that strongly excites a high density of interior modes. Mode coupling between the structural response and the interior modes appears to be negligible due to a lack of frequency proximity and mismatches in the spatial distribution. A high degree-of-freedom finite element model of the fuselage section was developed as a predictive tool. The calculated response is in good agreement with the experimental result, yielding a general model development methodology for accurate prediction of structures with moderate to high complexity. (c) 2005 Acoustical Society of America.
机译：通过空间密集的扫描测量，评估了塞斯纳奖状机身截面在三种不同的强迫作用下（10-1000 Hz）的表面和内部响应。空间傅立叶分析表明，施加在加劲肋网格上的点力在很宽的频率范围内提供了丰富的波数响应。表面运动数据显示整体结构模式（小于或类似于150 Hz），全局和局部面板内响应的叠加（类似于150-450 Hz）以及单独面板内运动（大于或类似于450 Hz）。观察到Bloch波运动的一些证据，揭示了与加劲肋周期性相关的经典止动/通过带。内部响应（小于或类似于150 Hz）由强制内部空腔的整体结构模式主导。机身的局部面板内响应（大于或类似于150 Hz）提供了宽带体积速度源，该源强烈激发了高密度的内部模式。由于缺乏频率接近性和空间分布不匹配，结构响应和内部模态之间的模态耦合似乎可以忽略不计。开发了机身截面的高自由度有限元模型作为预测工具。计算出的响应与实验结果非常吻合，从而产生了一种通用的模型开发方法，可以对中度到高复杂性的结构进行准确的预测。 （c）2005年美国声学学会。

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