Energy effect removal technique to model circular/elliptical holes in relatively thick composite plates under in-plane compressive load

摘要: Abstract A new technique is introduced in this study to model laminates with circular and elliptical holes . Post-buckling nonlinear behaviors of these perforated plates are examined when they under uniaxial in-plane compressive load Since the moderately thick, plate theory used embody shear effects thickness direction first order deformation Von Karman’s assumptions also incorporate geometric nonlinearity The formulations founded upon principle minimum potential energy approximation displacement fields based on Ritz method obtained by Chebyshev polynomials. Convergence tests have been performed determine total number terms be assumed functions. results from removing contribution perfect plate. All integrations numerically applying Guess quadrature rule, however, case or cutouts, required nodes Gauss-Chebyshev arranged two different ways; Cartesian polar arrangements. cutout shape, size location for composite boundary conditions extensively investigated show capability proposed technique. accuracy present work comparing finite element