Abstract
A hybrid-stress formulation is presented for the analysis of multilayer cross-ply laminates under uniform inplane strain and a special-purpose element is developed for which the traction-free edge conditions are exactly satisfied. Results obtained for interlaminar stress distributions are shown to converge to large, but finite, values near the free edge. The importance of exact representation of the traction-free edge conditions is examined by comparison of results with those obtained by other investigators and by using an analogous multilayer hybrid-stress element in which the free-edge conditions are approximately satisfied. It is concluded that exact representation of the free-edge conditions is required if accurate point-by-point stress distribution in the vicinity of the free-edge are essential, as in the study of laminate strength and failure.
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