Vol. 6, No. 6, 2011

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ISSN: 1559-3959
Stress and buckling analyses of laminates with a cutout using a $\{3,0\}$-plate theory

Atila Barut, Erdogan Madenci and Michael P. Nemeth

Vol. 6 (2011), No. 6, 827–868
Abstract

A semianalytical solution method to predict stress field and structural bifurcation in laminates having a cutout by employing a simple {3,0}-plate theory is presented. The stress analysis includes both in-plane and bending stress fields. In this theory, the in-plane and out-of-plane displacement fields are respectively assumed in the forms of cubic and uniform through-the-thickness expansions. The cubic expansion ensures the correct behavior of transverse shear deformations while satisfying the condition of zero transverse shear stresses at the laminate faces. The equations of equilibrium for the stress and buckling analysis are derived based on the principle of stationary potential energy. Comparison against the classical laminate and {1,2}-plate theories proves this semianalytical method credible.

Keywords
composite, cutout, transverse shear deformation, bending, buckling
Milestones
Received: 24 May 2010
Accepted: 22 November 2010
Published: 11 December 2011
Authors
Atila Barut
Department of Aerospace and Mechanical Engineering
The University of Arizona
Tucson, AZ 85721
United States
Erdogan Madenci
Department of Aerospace and Mechanical Engineering
The University of Arizona
Tucson, AZ 85721
United States
Michael P. Nemeth
Structural Mechanics and Concepts Branch
NASA Langley Research Center
Hampton, VA 23681-2199
United States