BUCKLING ANALYSIS OF SIMPLY SUPPORTED SQUARE SYMMETRIC LAMINATED COMPOSITE PLATE

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dc.citation.epage80
dc.citation.spage77
dc.citation.volume21
dc.contributor.authorJeremić, Dejan
dc.contributor.authorRadić, Nebojša
dc.contributor.authorVučetić, Nikola
dc.contributor.editorKiss, Imre
dc.date.accessioned2024-02-22T10:46:51Z
dc.date.available2024-02-22T10:46:51Z
dc.date.issued2023
dc.description.abstractTo usethe laminated composite plates efficiently, it is necessary to develop appropriate analysis theories to predict accurately their structural and dynamical behavior. The analysis of the behavior of the laminated plates is an active research area because of their complex behavior. The structural instability becomes an important concern in a reliable design of composite plates. The majority of the investigations on laminated plates utilize either the classical lamination plate theory (CLPT), or the first-ordershear deformation theory (FSDT). Various geometries of the plates subjected to compressive load are studied. The present work deals about a buckling analysis of simply supported symmetric composite plate with four layers. It is assumed that composite plate is surrounded by external elastic fundation. Composite plate is modeled by the finite element method and subjected to biaxial compression load. Governing equations are derivedbased on Classical Laminated Plate Theory (CLPT) and computed critical buckling loads were compared with numerical results.
dc.identifier.issn2601 – 2332
dc.identifier.urihttps://vaseljena.ues.rs.ba/handle/123456789/984
dc.language.isoen
dc.publisherUniversity POLITEHNICA Timisoara
dc.sourceANNALS of Faculty Engineering Hunedoara – INTERNATIONAL JOURNAL OF ENGINEERING
dc.subjectbuckling; symmetric composite plate; orientation of layers; compression load
dc.titleBUCKLING ANALYSIS OF SIMPLY SUPPORTED SQUARE SYMMETRIC LAMINATED COMPOSITE PLATE
dc.typeArticle
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