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Structural-acoustic coupling in aircraft fuselage structuresResults of analytical and experimental investigations of structural-acoustic coupling phenomenon in an aircraft fuselage are described. The structural and acoustic cavity modes of DC-9 fuselage were determined using a finite element approach to vibration analysis. Predicted structural and acoustic dispersion curves were used to determine possible occurrences of structural-acoustic coupling for the fuselage. An aft section of DC-9 aircraft fuselage, housed in an anechoic chamber, was used for experimental investigations. The test fuselage was excited by a shaker and vibration response and interior sound field were measured using accelerometer and microphone arrays. The wavenumber-frequency structural and cavity response maps were generated from the measured data. Analysis and interpretation of the spatial plots and wavenumber maps provided the required information on modal characteristics, fuselage response and structural-acoustic coupling.
Document ID
19930071859
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mathur, Gopal P.
(NASA Langley Research Center Hampton, VA, United States)
Simpson, Myles A.
(Douglas Aircraft Co. Long Beach, CA, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1992
Publication Information
Publication: In: International Congress on Recent Developments in Air- and Structure-Borne Sound and Vibration, 2nd, Auburn Univ., AL, Mar. 4-6, 1992, Proceedings. Vol. 1 (A93-55851 24-31)
Publisher: Auburn University
Subject Category
Aircraft Design, Testing And Performance
Accession Number
93A55856
Funding Number(s)
CONTRACT_GRANT: NAS1-18037
Distribution Limits
Public
Copyright
Other

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