Linearized global and local buckling analysis of sandwich struts with a refined quasi-3D model

Abstract

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Buckling and wrinkling of anisotropic sandwich plates

“…These remarks are next extended to a broader class of configurations, in particular by including the core orthotropy ratio E core 11 /E core 33 . Preliminary investigations indicated a high sensitivity of the internal strain energy distribution to this parameter ( D'Ottavio & Polit, 2015 ). Present results refer to the same sandwich panel investigated above, but the in-plane elastic moduli of the core C8 are now varied, while keeping constant E core 33 .…”

“…Exact solutions for global and local buckling of sandwich struts were derived referring to elasticity solutions ( Ji & Waas,20 07;20 08 ). D'Ottavio andPolit (2015) andD'Ottavio, Polit, Ji, andWaas (2016) obtained quasi-3D solutions for global buckling and wrinkling of uniaxially loaded orthotropic sandwich panels and struts by means of Naviertype solutions and high-order models formulated within a variable-kinematics approach. Two-dimensional structural models were considered by Rose, Moore, Knight, and Rankin (2002) , where 2D sandwich elements were implemented in the finite element code STAGS and complemented with a strip-based feature for local buckling analysis.…”

A Sublaminate Generalized Unified Formulation for the analysis of composite structures

“…Several works report LW models in which the same kinematic model is used for both faces and core of sandwich panels. For instance, Librescu and Hause [45] employ FSDT, Pai and Palazotto [46] apply the refined model of Lo et al [33] and D'Ottavio and Polit [47] use the most accurate RMVT-based CUF model LM4.…”

Benchmark solutions and assessment of variable kinematics models for global and local buckling of sandwich struts

“…Details about the way this approximation is formulated in this work are given in the subsequent section dedicated to the Sublaminate Generalized Unified Formulation (S-GUF). For the periodic buckling problem of orthotropic sandwich structures investigated in this study, a harmonic in-plane solution is formulated according to Navier's method [35,15]:…”

“…Failure mechanisms of sandwich panels can be very different from those of other composite structures due to the characteristic mismatch of mechanical and geometrical properties between skins and core [1,2]. In particular, instability phenomena occurring under compressive stress states have been given great attention through numerous experimental works [3][4][5][6] as well as theoretical and computational developments [7][8][9][10][11][12][13][14][15].…”