English (United Kingdom)

https://curated-unify.zendy.io/wp-json/zendy-region/v1/featured_content/oa?rat=en

https://curated-unify.zendy.io/wp-json/zendy-region/v1/highlighted_journal/

Global: Zendy Plus annual

Presents the access of premium content as premium feature

Premium Content

Presents the keyphrase highlighting as premium feature

Keyphrase Highlighting

Presents the summarisation as premium feature

Summarisation

Insights

Presents the pdf analysis as premium feature

PDF Analysis

Presents the zaia usage as premium feature

ZAIA

Global: Zendy Plus monthly

Global: Zendy Tools annual

Global: Zendy Tools monthly

Global: Zendy Free Plan

This article investigates the large deflection and post-buckling of compositeplates by employing the Carrera Unified Formulation (CUF). As a consequence,the geometrically nonlinear governing equations and the relevant incrementalequations are derived in terms of fundamental nuclei, which are invariant ofthe theory approximation order. By using the Lagrange expansion functionsacross the laminate thickness and the classical finite element (FE)approximation, layer-wise (LW) refined plate models are implemented. TheNewton-Raphson linearization scheme with the path-following method based on thearc-length constraint is employed to solve geometrically non-linear compositeplate problems. In this study, different composite plates subjected to largedeflections/rotations and post-buckling are analyzed, and the correspondingequilibrium curves are compared with the results in the available literature orthe traditional FEM-based solutions. The effects of various parameters, such asstacking sequence, number of layers, loading conditions, and edge conditionsare demonstrated. The accuracy and reliability of the proposed method forsolving the composite plates' geometrically nonlinear problems are verified.

Buckling and post-buckling of anisotropic at panels subjected to axial  and shear in-plane loadings accounting for classical and refined structural  and nonlinear theories