Shear-Lag Analysis of a Hybrid, Unidirectional Composite with Fiber Damage


This study considers the development of method of analysis capable of predicting accurately the fracture behavior of unidirectional hybrid (buffer strip) composite laminates. Three particular solutions are discussed in detail: first, the case of broken fibers in a unidirectional half-plane; second, the case of adjoined half-planes of different fiber and matrix properties; and finally, the solution of two half-planes bounding a third distinct region of finite width. this finite width region represents a bufer strip and primary attention is given to the potential of this strip to arrest a crack that originates in one of the half-planes. The analysis is based on a materials modeling approach using the classical shear-lag assumption to describe the stress transfer between fibers. Explicit fiber and matrix properties of the three regions are retained, and changes in the laminate behavior as a function of relative material properties, buffer strip width, and initial crack length are discussed.


Mechanical and Aerospace Engineering

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Article - Journal

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© 1983 National Aeronautics and Space Administration (NASA), All rights reserved.

Publication Date

01 Jan 1983

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