Response prediction of acoustically-excited composite honeycomb sandwich structures with double curvature
Response prediction of acoustically-excited composite honeycomb sandwich structures with double curvature
Composite honeycomb sandwich structures have been favoured in the aircraft industry for many years due to their low-weight, high stiffness, and improved fatigue resistance. The response of doubly curved, composite honeycomb sandwich panels to high intensity, random pressure loads has received little attention, and there is a need to update current design guides to include this type of structure.
A set of four doubly curved honeycomb sandwich panels were manufactured at the University of Southampton. The panels were tested to determine some of the resonance frequencies of vibration, and the results were used to validate the Finite Element models of the four panels. These FE models were used to study the effects of various design parameters on the free vibration response, and the work resulted in various sensitivity parameters which could potentially be used as a guide for designers.
The major part of the work involved testing the panels in a Progressive Wave Tube (PWT) facility with random acoustic excitation at grazing incidence to the concave panel surface. The measured strain response of the panels was predominantly in the fundamental bending mode, with face plate strain levels which differed between the inner and outer face plates, highlighting the significant effect that double curvature can have on the relative strain levels in the face plates.
A new method was developed for estimating the shear strain in the core of the sandwich panels using a finite difference approximation. The technique was validated using a cantilevered sandwich beam, giving excellent agreement between experiment and theory for both static and dynamic response. The work resulted in a new viable technique which has potential for use in generating S/N data for the core during random fatigue testing of sandwich coupon structures.
University of Southampton
Cunningham, Paul Robert
03625c86-b218-4c5b-aa03-7468f30165fa
2001
Cunningham, Paul Robert
03625c86-b218-4c5b-aa03-7468f30165fa
Cunningham, Paul Robert
(2001)
Response prediction of acoustically-excited composite honeycomb sandwich structures with double curvature.
University of Southampton, Doctoral Thesis.
Record type:
Thesis
(Doctoral)
Abstract
Composite honeycomb sandwich structures have been favoured in the aircraft industry for many years due to their low-weight, high stiffness, and improved fatigue resistance. The response of doubly curved, composite honeycomb sandwich panels to high intensity, random pressure loads has received little attention, and there is a need to update current design guides to include this type of structure.
A set of four doubly curved honeycomb sandwich panels were manufactured at the University of Southampton. The panels were tested to determine some of the resonance frequencies of vibration, and the results were used to validate the Finite Element models of the four panels. These FE models were used to study the effects of various design parameters on the free vibration response, and the work resulted in various sensitivity parameters which could potentially be used as a guide for designers.
The major part of the work involved testing the panels in a Progressive Wave Tube (PWT) facility with random acoustic excitation at grazing incidence to the concave panel surface. The measured strain response of the panels was predominantly in the fundamental bending mode, with face plate strain levels which differed between the inner and outer face plates, highlighting the significant effect that double curvature can have on the relative strain levels in the face plates.
A new method was developed for estimating the shear strain in the core of the sandwich panels using a finite difference approximation. The technique was validated using a cantilevered sandwich beam, giving excellent agreement between experiment and theory for both static and dynamic response. The work resulted in a new viable technique which has potential for use in generating S/N data for the core during random fatigue testing of sandwich coupon structures.
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Published date: 2001
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Local EPrints ID: 464337
URI: http://eprints.soton.ac.uk/id/eprint/464337
PURE UUID: f8e1e7ab-b75f-4e2d-9317-13949b0cfc82
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Date deposited: 04 Jul 2022 22:18
Last modified: 16 Mar 2024 19:25
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Author:
Paul Robert Cunningham
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