Buckling of Rectangular Cross-Ply Laminated Plates With Nonlinear Stress-Strain Behavior

[+] Author and Article Information
Harold S. Morgan

Missile and Ordnance Division, Texas Instruments, Inc., Dallas, Texas 75222

Robert M. Jones

Civil and Mechanical Engineering Department, Southern Methodist University, Dallas, Texas 75275

J. Appl. Mech 46(3), 637-643 (Sep 01, 1979) (7 pages) doi:10.1115/1.3424619 History: Received March 01, 1978; Revised February 01, 1979; Online July 12, 2010


The Jones-Nelson-Morgan nonlinear material model is used in the derivation of a buckling criterion for laminated plates with nonlinear stress-strain behavior characteristic of many fiber-reinforced composite materials. A search procedure is developed to solve this buckling criterion which is transcendental because of interdependence of the buckling load and the coefficients relating the variations in laminate forces and moments to the variations in strains and curvatures. The effect of stress-strain curve nonlinearities on laminate buckling loads is illustrated by comparing solutions of the buckling criterion to buckling loads for laminates with linear stress-strain behavior.

Copyright © 1979 by ASME
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