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Noise Reduction in an Aircraft Fuselage Model Using Active Trim PanelsAn 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.
Document ID
19960047666
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Silcox, Richard J.
(NASA Langley Research Center Hampton, VA United States)
Lyle, Karen H.
(Army Vehicle Structures Lab. Hampton, VA United States)
Date Acquired
August 17, 2013
Publication Date
March 1, 1996
Publication Information
Publication: Proceedings of the 4th Annual Workshop: Advances in Smart Materials for Aerospace Applications
Subject Category
Acoustics
Accession Number
96N33276
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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