An experiment was conducted to evaluate the use of force actuators on a model aircraft interior trim panel as the control element for active control of interior noise. The trim panel, designed specifically for this study, was constructed in three large identical sections and hard mounted to the ring frames of the primary structure. Piezoceramic actuators were bonded to the outer surface of the trim panels. Studies of the interior pressure response due to both the primary source alone and control sources alone were conducted as well as the control cases. A single acoustic loudspeaker, centered at the axial midpoint, generated the acoustic field to be controlled.


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    Titel :

    Noise Reduction in an Aircraft Fuselage Model Using Active Trim Panels


    Beteiligte:


    Erscheinungsdatum :

    01.03.1996


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    A Study of Active Trim Panels for Interior Noise Reduction in an Aircraft Fuselage

    Lyle, K. H. / Silcox, R. J. | SAE Technical Papers | 1995


    A Study of Active Trim Panels for Interior Noise Reduction in an Aircraft Fuselage

    Lyle, K. H. / Silcox, R. J. / SAE | British Library Conference Proceedings | 1995




    Active Sandwich Trim Panels for Quieter Aircraft Interior

    Sun, J. Q. | British Library Online Contents | 1999