Interlaminar Stresses in Composite Laminates—An Approximate Elasticity Solution

[+] Author and Article Information
R. B. Pipes

University of Delaware, Newark, Del.

N. J. Pagano

Air Force Materials Laboratory, Nonmetallic Materials Division, Wright-Patterson AFB, Ohio

J. Appl. Mech 41(3), 668-672 (Sep 01, 1974) (5 pages) doi:10.1115/1.3423368 History: Received September 01, 1973; Revised March 01, 1974; Online July 12, 2010


An approximate elasticity solution is developed for the response of the finite-width, angle-ply composite laminate under uniform axial strain. The solution yields components of the displacement vector, strain tensor, and stress tensor in the form of sinusoidal-hyperbolic series. Results of the approximate solution are compared to numerical solutions of the exact equations for four-layer, symmetric laminate geometries. The nature of the boundary disturbance in the eight-layer laminate is also examined by the approximate solution.

Copyright © 1974 by ASME
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