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 150 Hz), superposition of global and local intrapanel responses (proportional 150-450 Hz), and intrapanel motion alone (greater than or similar 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 150 Hz) is dominated by global structural modes that force the interior cavity. Local intrapanel responses (greater than or similar 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.


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    Title :

    The vibro-acoustic response and analysis of a full-scale aircraft fuselage section for interior noise reduction


    Contributors:

    Published in:

    Publication date :

    2005


    Size :

    12 Seiten, 19 Bilder, 34 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





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