Buckling and postbuckling behavior of cross - ply composite plate subjected to nonuniform in - plane loads / Sarat Kumar Panda in Journal of engineering mechanics, Vol. 137 N° 9 (Septembre 2011)  

Public ISBD [article]  inJournal of engineering mechanics > Vol. 137 N° 9 (Septembre 2011) . - pp.589-597 Titre : Buckling and postbuckling behavior of cross - ply composite plate subjected to nonuniform in - plane loads Type de document : texte imprimé Auteurs : Sarat Kumar Panda, Auteur ; L. S. Ramachandra, Auteur Année de publication : 2011 Article en page(s) : pp.589-597 Note générale : Mécanique appliquée Langues : Anglais (eng) Mots-clés : Buckling loads Postbuckling analysis Nonuniform in-plane Ritz method Galerkin Résumé : This paper presents a study of buckling and postbuckling behaviour of simply supported composite plates subjected to nonuniform in-plane loading. The mathematical model is based on higher order shear deformation theory incorporating von Kármán nonlinear strain displacement relations. Because the applied in-plane edge load is nonuniform, in the first step the plane elasticity problem is solved to evaluate the stress distribution within the prebuckling range. Using these stress distributions, the governing equations for postbuckling analysis of composite plates are obtained through the theorem of minimum potential energy. Adopting Galerkin’s approximation, the governing nonlinear partial differential equations are reduced into a set of nonlinear algebraic equations in the case of postbuckling analysis, and homogeneous linear algebraic equations in the case of buckling analysis. The critical buckling load is obtained from the solution of associated linear eigenvalue problem. Postbuckling equilibrium paths are obtained by solving nonlinear algebraic equations employing the Newton-Raphson iterative scheme. Explicit expressions for the plate in-plane stress distributions within the prebuckling range are reported for isotropic and composite plates subjected to parabolic in-plane edge loading. Buckling loads are determined for three plate aspect ratios (a/b = 0.5, 1, 1.5) and three different types of in-plane load distributions. The effect of shear deformation on the buckling loads of composite plate is reported. The present buckling results are compared with previously published results wherever possible. DEWEY : 620.1 ISSN : 0733-9399 En ligne : http://ascelibrary.org/emo/resource/1/jenmdt/v137/i9/p589_s1?isAuthorized=no [article] Buckling and postbuckling behavior of cross - ply composite plate subjected to nonuniform in - plane loads [texte imprimé] / Sarat Kumar Panda, Auteur ; L. S. Ramachandra, Auteur . - 2011 . - pp.589-597. Mécanique appliquée Langues : Anglais (eng) in Journal of engineering mechanics > Vol. 137 N° 9 (Septembre 2011) . - pp.589-597 Mots-clés : Buckling loads Postbuckling analysis Nonuniform in-plane Ritz method Galerkin Résumé : This paper presents a study of buckling and postbuckling behaviour of simply supported composite plates subjected to nonuniform in-plane loading. The mathematical model is based on higher order shear deformation theory incorporating von Kármán nonlinear strain displacement relations. Because the applied in-plane edge load is nonuniform, in the first step the plane elasticity problem is solved to evaluate the stress distribution within the prebuckling range. Using these stress distributions, the governing equations for postbuckling analysis of composite plates are obtained through the theorem of minimum potential energy. Adopting Galerkin’s approximation, the governing nonlinear partial differential equations are reduced into a set of nonlinear algebraic equations in the case of postbuckling analysis, and homogeneous linear algebraic equations in the case of buckling analysis. The critical buckling load is obtained from the solution of associated linear eigenvalue problem. Postbuckling equilibrium paths are obtained by solving nonlinear algebraic equations employing the Newton-Raphson iterative scheme. Explicit expressions for the plate in-plane stress distributions within the prebuckling range are reported for isotropic and composite plates subjected to parabolic in-plane edge loading. Buckling loads are determined for three plate aspect ratios (a/b = 0.5, 1, 1.5) and three different types of in-plane load distributions. The effect of shear deformation on the buckling loads of composite plate is reported. The present buckling results are compared with previously published results wherever possible. DEWEY : 620.1 ISSN : 0733-9399 En ligne : http://ascelibrary.org/emo/resource/1/jenmdt/v137/i9/p589_s1?isAuthorized=no

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