Interaction Curves for Composite Laminates Subjected To Biaxial In-plane Loads
N. G. R. Iyengar
|Published in:||International Journal of Structural Stability and Dynamics, December 2005, n. 4, v. 5|
In this study, an attempt has been made to incorporate the effect of transverse shear on the stability analysis of moderately thick/very thick composite laminated plates under in-plane compressive loading using a "Simple Higher-Order Shear Deformation Theory" based on four unknown displacement functions (u0, v0, wb, ws) instead of five which is commonly used in most of the higher-order theories. The finite element method is employed to study the initial buckling load of laminated plates. The change in initial buckling response of thick rectangular anti-symmetric laminates with respect to the fiber orientation angle has been studied. The interaction curves (between Nxand Nyfor different parameters of the laminates) are studied in detail. The interaction curves for Nxand Nyare either linear or piecewise linear. There are some combinations of biaxial in-plane loads for which laminates with different lay-up sequences have the same initial buckling loads.
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