Effects of Thickness and Ply Orientation on Buckling of Laminated Plates
National Aeronautics and Space Administration, Langley Research Center, 1986 - Composite materials - 16 pages
The buckling loads of laminated plates are predicted using a new theory which takes into account transverse shearing ettects. This new theory assumes trigonometric terms through-the-thickness in the displacements to take into account transverse shearing effects in thick plates. Buckling loads predicted by the new theory and by traditional theories are compared for isotropic and laminated plates. The effect of ply orientation on the buckling loads predicted by each theory is demonstrated. (MM).
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36 percent lower account transverse shearing accurate approximations assumed displacement series buckling load parameter buckling load results buckling loads predicted classical plate theory classical theory Comparison of buckling compressive buckling conventional transverse shear Dawn developed in reference difference differential equations direction effect of ply EFFECTS OF THICKNESS flat plate function of thickness-to-length gives a buckling homogeneous materials include the trigonometric isotropic plate laminated plates length loading terms loads of laminated mmy/b NASA ORIENTATION ON BUCKLING Performing Organization plate with intermediate plates are predicted plates of homogeneous potential energy method predicted buckling loads predicting the buckling reduced Report represented respectively shear deformation theory shown in figure simply supported square plate stress at buckling Studied take into account theories are compared theory of reference thickness-to-length ratio obtained thin plates three theories traditional theories transverse shear deformation transverse shear stress transverse shearing effects transverse shearing theory Unclassified varies xz h