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Comparison of structural response and fatigue endurance of aircraft flap-like box structures subjected to acoustic loading

Comparison of structural response and fatigue endurance of aircraft flap-like box structures subjected to acoustic loading
Comparison of structural response and fatigue endurance of aircraft flap-like box structures subjected to acoustic loading
The results of an extensive test program to characterize the behavior of typical aircraft structures under acoustic loading and to establish their fatigue endurance are presented. The structures tested were the three flap-like box-type of structures. Each structure consisted of one flat (bottom) and one curved (top) stiffener stiffened skin panel, front, and rear spars, and ribs that divided the structures into three bays. The three structures, constructed from three different materials (aircraft standard aluminum alloy, Carbon Fibre Reinforced Plastic, and a Glass Fibre Metal Laminate, i.e., GLARE) had the same size and configuration, with only minor differences due to the use of different materials. A first set of acoustic tests with excitations of intensity ranging from 140 to 160 dB were carried out to obtain detailed data on the dynamic response of the three structures. The FE analysis of the structures is also briefly described and the results compared with the experimental data. The fatigue endurance of the structures was then determined using random acoustic excitation with an overall sound pressure level of 161 dB, and details of crack propagation are reported.
0001-4966
2820-2834
Xiao, Y.
7ca8d021-0028-49f0-b6df-b2fefe95636b
White, R.G.
d67216d7-2691-4322-9dac-56b96add39e1
Aglietti, G.S.
e44d0dd4-0f71-4399-93d2-b802365cfb9e
Xiao, Y.
7ca8d021-0028-49f0-b6df-b2fefe95636b
White, R.G.
d67216d7-2691-4322-9dac-56b96add39e1
Aglietti, G.S.
e44d0dd4-0f71-4399-93d2-b802365cfb9e

Xiao, Y., White, R.G. and Aglietti, G.S. (2005) Comparison of structural response and fatigue endurance of aircraft flap-like box structures subjected to acoustic loading. Journal of the Acoustical Society of America, 117 (5), 2820-2834. (doi:10.1121/1.1853934).

Record type: Article

Abstract

The results of an extensive test program to characterize the behavior of typical aircraft structures under acoustic loading and to establish their fatigue endurance are presented. The structures tested were the three flap-like box-type of structures. Each structure consisted of one flat (bottom) and one curved (top) stiffener stiffened skin panel, front, and rear spars, and ribs that divided the structures into three bays. The three structures, constructed from three different materials (aircraft standard aluminum alloy, Carbon Fibre Reinforced Plastic, and a Glass Fibre Metal Laminate, i.e., GLARE) had the same size and configuration, with only minor differences due to the use of different materials. A first set of acoustic tests with excitations of intensity ranging from 140 to 160 dB were carried out to obtain detailed data on the dynamic response of the three structures. The FE analysis of the structures is also briefly described and the results compared with the experimental data. The fatigue endurance of the structures was then determined using random acoustic excitation with an overall sound pressure level of 161 dB, and details of crack propagation are reported.

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Published date: May 2005

Identifiers

Local EPrints ID: 23208
URI: http://eprints.soton.ac.uk/id/eprint/23208
ISSN: 0001-4966
PURE UUID: 3298f1e4-96a3-4dde-8ee5-5ebda817a7c4

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Date deposited: 14 Mar 2006
Last modified: 15 Mar 2024 06:44

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Contributors

Author: Y. Xiao
Author: R.G. White
Author: G.S. Aglietti

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