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TECHNICAL PAPERS

Structural-Acoustic Optimization of Sandwich Panels

[+] Author and Article Information
Francesco Franco

Department of Aerospace Engineering, University of Naples “Federico II,” Naples, Italyfrancof@unina.it

Kenneth A. Cunefare

School of Mechanical Engineering, Georgia Institute of Technology, Atlanta, GA 30332ken.cunefare@me.gatech.eduSchool of Aerospace Engineering, Georgia Institute of Technology, Atlanta, GA 30332ken.cunefare@me.gatech.edu

Massimo Ruzzene1

School of Mechanical Engineering, Georgia Institute of Technology, Atlanta, GA 30332massimo.ruzzene@aerospace.gatech.eduSchool of Aerospace Engineering, Georgia Institute of Technology, Atlanta, GA 30332massimo.ruzzene@aerospace.gatech.edu

1

Corresponding author.

J. Vib. Acoust 129(3), 330-340 (Oct 05, 2006) (11 pages) doi:10.1115/1.2731410 History: Received July 06, 2005; Revised October 05, 2006

Sandwich panels comprising face sheets enclosing a core are increasingly common structural elements in a variety of applications, including aircraft fuselages, flight surfaces, vehicle panels, lightweight enclosures, and bulkheads. This paper presents the optimization of various innovative sandwich configurations for minimization of their structural-acoustic response. Laminated face sheets and core geometries comprising honeycomb and trusslike structures are considered. The design flexibility associated with the class of considered composite structures and with truss-core configurations provides the opportunity of tailoring the structure to the load and dynamic response requirements of a particular application. The results demonstrate how the proper selection of selected key parameters can achieve effective reduction of the radiated sound power and how the identified optimal configurations can achieve noise reduction over different frequency ranges and for various source configurations.

Copyright © 2007 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Sandwich panel configuration

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Figure 2

Hexagonal model geometry in the xy plane

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Figure 3

Random core geometry in the xy plane

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Figure 4

Predicted spatial mean-square velocity for different configurations of core with prismatic axis in the plane of the panel, uniform pressure load

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Figure 5

Geometry of the trusslike unit cell

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Figure 6

Predicted spatial mean-square velocity for different trusslike core configurations, uniform pressure load

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Figure 7

Monopole source configurations

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Figure 8

Predicted spatial mean-square velocity for CORNER excitation versus that with uniform pressure for panel with hexagonal core

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Figure 9

Predicted spatial mean-square velocity for different truss core panels, MIDDLE source configuration. Truss_Double_Ax section area of the truss along x is double that of the section area along z. Truss_No_Ax section area of the truss along x is zero, i.e., the truss along x does not exist.

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Figure 10

Predicted spatial mean-square velocity for different truss core panels, MIDDLE source configuration. Truss_Double_Az section area of the truss along z is double that of the section area along x. Truss_No_Az section area of the truss along z is zero, i.e., the truss along z does not exist.

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Figure 11

Predicted spatial mean-square velocity for truss core panels with composite versus aluminum face sheets. MIDDLE source excitation.

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Figure 12

Predicted spatial mean-square velocity spanning 100–3500Hz for panels with reference and optimized composite face sheet and truss core, MIDDLE source excitation, optimization performed over 1800–2200Hz

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Figure 13

Predicted spatial mean-square velocity spanning 1800–2200Hz for panels with reference and optimized composite face sheet and truss core, MIDDLE source excitation, optimization performed over 1800–2200Hz

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Figure 14

Predicted spatial mean-square velocity for aluminum and resin-core configurations, composite face sheets, MIDDLE source excitation

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Figure 15

Predicted spatial mean-square velocity for optimized panel with resin truss-core and composite face sheets versus reference results with aluminum core

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