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Approximate Three-Dimensional Solutions for Symmetric Laminates Under Inplane Loading *

Battelle Memorial Institute Columbus, Ohio 43201

A three-dimensional equilibrium finite element analysis is used to obtain approximate stress solutions for some finite symmetric laminates under inplane loading. The analysis is based on a comple mentary energy formulation. Obtained stress solutions at the center section of the laminate are compared with solutions for uniform axial strain that are available in the literature. A comparison of the stress distributions obtained at the center and end sections of the laminate shows that a large _yz stress can occur at the end section and a large xz can occur at the center section. The influence of laminate stacking sequence on the predicted z is also presented.

Journal of Composite Materials, Vol. 5, No. 3, 354-360 (1971)
DOI: 10.1177/002199837100500305


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