Accession Number : ADP006811

Title :   Three-Dimensional Elasticity Analysis of Buckling of Laminated Plates,

Corporate Author : NOTTINGHAM UNIV (UNITED KINGDOM) DEPT OF THEORETICAL MECHANICS

Personal Author(s) : Spencer, A. J.

Report Date : APR 1992

Pagination or Media Count : 5

Abstract : The analysis of failure mechanisms for laminated composite materials depends, in the first place, on obtaining a three-dimensional analysis of the elastic stress and deformation in the material, with particular regard to interlaminar stresses. The author and colleagues have developed a procedure for the solution of the equations of three-dimensional linear elasticity for the determination of stress and deformation in laminated plates. The plate is assumed to be composed of anisotropic elastic material containing any number of orthotropic plies with any specified orientations. A transfer matrix method is used which determines, to any desired degree of accuracy, the stress and displacement at any point in the plate in terms of the stress and displacement at a reference surface, for example the mid-plane. The two-dimensional differential equations governing these reference surface values are found to be the same as those for an equivalent homogeneous plate whose constant elastic moduli are appropriately weighted through thickness averages of the ply elastic moduli.

Descriptors :   *PLATES, *LAMINATES, *MILITARY AIRCRAFT, *BUCKLING, ACCURACY, COMPOSITE MATERIALS, CONSTANTS, DEFORMATION, DETERMINATION, DIFFERENTIAL EQUATIONS, DISPLACEMENT, STRESSES, SURFACES, THICKNESS, THREE DIMENSIONAL, TWO DIMENSIONAL, SYMPOSIA, FAILURE(MECHANICS), MODULUS OF ELASTICITY, STRESS ANALYSIS, EQUILIBRIUM(GENERAL), REPRINTS, NATO.

Subject Categories : Laminates and Composite Materials
      Aircraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE