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Finite element modelling of sandwich panels with graded core under various boundary conditions

Published online by Cambridge University Press:  27 January 2016

M. Kashtalyan  and
B. Woodward
B. Woodward
Affiliation:
Centre for Micro- and Nanomechanics (CEMINACS), School of Engineering, University of Aberdeen, Aberdeen, UK
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Abstract

Sandwich panels are widely used in the aerospace industry instead of solid plates due to their high flexural stiffness-to-weight and flexural strength-to-weight ratios. However due to the mismatch of properties between the face sheets and the core, stress concentrations can occur at the face sheet/core interfaces, often leading to delamination. One possible solution to this problem is the introduction of a graded core — a core in which the properties vary gradually from the face sheets to the core centre, eliminating any abrupt changes in properties. In this paper a 3D finite element method, fully validated through comparison with results from the literature and a 3D elasticity solution, is applied to modelling of sandwich panels with graded core. The approach makes use of graded elements to study the effect of varying the boundary conditions on the elastic deformation of the panel subject to uniformly distributed loading. Comparative analysis of stress and displacement fields in sandwich panels with homogeneous and graded cores is carried out under various combinations of simply supported, clamped and free edges.

Type
Research Article
Information
The Aeronautical Journal , Volume 116 , Issue 1186 , December 2012 , pp. 1289 - 1314
Copyright
Copyright © Royal Aeronautical Society 2012 

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