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TECHNICAL PAPERS

Wrinkling of Wide Sandwich Panels∕Beams With Orthotropic Phases by an Elasticity Approach

[+] Author and Article Information
G. A. Kardomateas

 Georgia Institute of Technology, Atlanta, GA 30332-0150

J. Appl. Mech 72(6), 818-825 (Nov 04, 2004) (8 pages) doi:10.1115/1.1978919 History: Received February 11, 2003; Revised November 04, 2004

There exist many formulas for the critical compression of sandwich plates, each based on a specific set of assumptions and a specific plate or beam model. It is not easy to determine the accuracy and range of validity of these rather simple formulas unless an elasticity solution exists. In this paper, we present an elasticity solution to the problem of buckling of sandwich beams or wide sandwich panels subjected to axially compressive loading (along the short side). The emphasis on this study is on the wrinkling (multi-wave) mode. The sandwich section is symmetric and all constituent phases, i.e., the facings and the core, are assumed to be orthotropic. First, the pre-buckling elasticity solution for the compressed sandwich structure is derived. Subsequently, the buckling problem is formulated as an eigen-boundary-value problem for differential equations, with the axial load being the eigenvalue. For a given configuration, two cases, namely symmetric and anti-symmetric buckling, are considered separately, and the one that dominates is accordingly determined. The complication in the sandwich construction arises due to the existence of additional “internal” conditions at the face sheet∕core interfaces. Results are produced first for isotropic phases (for which the simple formulas in the literature hold) and for different ratios of face-sheet vs core modulus and face-sheet vs core thickness. The results are compared with the different wrinkling formulas in the literature, as well as with the Euler buckling load and the Euler buckling load with transverse shear correction. Subsequently, results are produced for one or both phases being orthotropic, namely a typical sandwich made of glass∕polyester or graphite∕epoxy faces and polymeric foam or glass∕phenolic honeycomb core. The solution presented herein provides a means of accurately assessing the limitations of simplifying analyses in predicting wrinkling and global buckling in wide sandwich panels∕beams.

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Copyright © 2005 by American Society of Mechanical Engineers
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Figures

Grahic Jump Location
Figure 1

Definition of the geometry for a sandwich wide panel∕beam under axial compression

Grahic Jump Location
Figure 3

(a) Thickness-wise variation of the transverse displacement, W, for isotropic phases and f∕h=0.02 (at the critical point). The displacement is normalized with the mid-point (z=0) transverse displacement of the core, Wc0. (b) Thickness-wise variation of the axial displacement, U, for isotropic phases and f∕h=0.02 (at the critical point). The displacement is normalized with the mid-point (z=0) transverse displacement of the core, Wc0.

Grahic Jump Location
Figure 4

(a) Thickness-wise variation of the transverse displacement, W, for the orthotropic phases examined and f∕h=0.01 (at the critical point). The displacement is normalized with the corresponding mid-point (z=0) transverse displacement of the core, Wc0. (b) Thickness-wise variation of the axial displacement, U, for the orthotropic phases examined and f∕h=0.01 (at the critical point). The displacement is normalized with the corresponding mid-point (z=0) transverse displacement of the core, Wc0.

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