Thermomechanical buckling of laminated composite and sandwich plates using global–local higher order theory

Wu, Zhen; Wanji, Chen

doi:10.1016/j.ijmecsci.2006.10.006

Cited by 35 publications

(9 citation statements)

References 35 publications

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“…As table shows, the present results have a good agreement with Refs. [19,20,21] and finite element method using Ansys. Table 2 presents a comparison of the lowest critical buckling loads of three-layer cross-ply laminated plates with analytical solutions [20,21] and finite element method for various values of the degree of orthotropy of the individual layers E1/E2.…”

Section: Numerical Results and Discussionmentioning

confidence: 99%

Behaviors of Simply Supported Cross-Ply Rectangular Symmetric Laminates Plates with Consideration of Prebuckling In-Plane Deformation

Lairedj¹,

Bouazza²,

Amara³

et al. 2015

AMS

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This paper addresses the elastic buckling of simply supported cross-ply rectangular symmetric laminates with allowance for the effects of prebuckling in-plane deformation and higher-order strain terms (curvature terms), using the first order shear deformation theory. The governing plate equations are derived by considering the stationary condition for the derived energy functional by applying the calculus of variations. The buckling load of symmetric cross-ply laminated rectangular plates, which are subjected to uniaxial compression, biaxial compression, and biaxial compression and tension, are determined whilst the effects of different parameters, the plate aspect ratio, the relative thickness degrees of material orthotropy and numbers of layers are investigated.

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Section: Numerical Results and Discussionmentioning

confidence: 99%

Behaviors of Simply Supported Cross-Ply Rectangular Symmetric Laminates Plates with Consideration of Prebuckling In-Plane Deformation

Lairedj¹,

Bouazza²,

Amara³

et al. 2015

AMS

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“…The thermal-buckling mode shapes of laminated composites with varying fiber orientations, stacking sequences and E1/E2 ratios are studied in 12 . The thermomechanical-buckling response of laminated composites and sandwich plates was investigated by Wu and Chen 13 .…”

Section: Introductionmentioning

confidence: 99%

Investigation of hole effects on the critical buckling load of laminated composite plates

Kurşun¹,

Topal²

2016

Mater. Tehnol.

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In this study, the effects of the hole diameter on the buckling behavior of glass-fiber-reinforced, laminated composite rectangular plates were investigated both experimentally and numerically. As the test specimens, E-glass/epoxy symmetric-ply composites with eight layers were manufactured using the hand lay-up technique and drilled with different hole diameters ranging from 10 to 40 mm. The laminated composite plates were arranged with different symmetric orientation angles such as [(0°/90°)2]s, [(-15°/15°)2]s, [(-30°/30°)2]s and [(-45°/45°)2]s. The experimental critical-buckling loads of the plates were found by clamping the bottom and upper edges and then these results were compared with the results obtained with the numerical analysis. The determination of the critical buckling loads for the laminated composite plates with different hole diameters was performed using the ANSYS 12.1 ® finite-element-analysis software. The numerical analysis showed good agreement with the experimental results for different hole diameters and fiber orientation angles. It was concluded that the critical buckling loads strongly depend on the diameter of the hole and fiber orientation angles. Keywords: buckling, glass fibers, finite element method (FEM) V tej {tudiji je bil eksperimentalno in numeri~no preiskovan vpliv premera luknje na obna{anje pri upogibu s steklenimi vlakni laminirane kompozitne {tirioglate plo{~e. Kompozitni vzorci so bili izdelani s simetri~nim polaganjem E-steklo/epoksi, z osmimi plastmi, z uporabo tehnike ro~nega polaganja in vrtanja lukenj razli~nega premera od 10 do 40 mm. Laminirane kompozitne plo{~e so bile izdelane z razli~nimi, simetri~no orientiranimi koti vlaken, [(0°/90°)2]s, [(-15°/15°)2]s, [(-30°/30°)2]s in [(-45°/45°)2]s. Eksperimentalna kriti~na upogibna obremenitev plo{~je bila ugotovljena z vpetjem spodnjega in zgornjega roba, rezultati pa so bili primerjani z rezultati numeri~ne analize. Dolo~itev kriti~ne upogibne obremenitve za laminirane kompozitne plo{~e z luknjami z razli~nim premerom, je bila izvr{ena z uporabo programa za analizo kon~nih elementov ANSYS 12.1 ®. Numeri~na analiza je pokazala dobro ujemanje z rezultati preizkusov, za razli~ne premere lukenj in orientacijske kote vlaken. Ugotovljeno je, da je kriti~na upogibna obremenitev mo~no odvisna od premera luknje in od kota orientacije vlaken. Klju~ne besede: upogibanje, steklena vlakna, metoda kon~nih elementov (FEM)

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“…Bottega [7] presented sling shot buckling of composite plates and shells under thermomechanical loading. Wu and Chen [8] using a global higher order theory developed thermomechanical buckling of laminated and sandwich plates. Shariyat [9] presented a generalized higher order global-local theory for buckling analysis of imperfect sandwich plates subjected to thermomechanical loads.…”

Section: Introductionmentioning

confidence: 99%

Thermomechanical buckling of hybrid cross-ply laminated rectangular plates

Bohlooly

Mirzavand

2016

Advanced Composite Materials

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A thermomechanical buckling analysis is presented for simply supported rectangular symmetric cross-ply laminated composite plates that are integrated with surfacemounted piezoelectric actuators and are subjected to the combined action of in-plane compressive edge loads, two types of thermal loads, and constant applied actuator voltage. The formulation of equations is based on the classical laminated plate theory and the von-Karman non-linear kinematic relations. The analysis uses an exact method to obtain closed-form solutions for the buckling load. The effects of applied actuator voltage, thermal and mechanical loads, plate geometry, and lay-up configuration of the laminated plates are investigated. The novelty of the present work is to obtain closed-form solutions for electro-thermomechanical buckling of hybrid composite plates, and to cover non-uniform temperature distribution loading. The results for various states are verified with known data in the literature.

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Thermomechanical buckling of laminated composite and sandwich plates using global–local higher order theory

Cited by 35 publications

References 35 publications

Behaviors of Simply Supported Cross-Ply Rectangular Symmetric Laminates Plates with Consideration of Prebuckling In-Plane Deformation

Behaviors of Simply Supported Cross-Ply Rectangular Symmetric Laminates Plates with Consideration of Prebuckling In-Plane Deformation

Investigation of hole effects on the critical buckling load of laminated composite plates

Thermomechanical buckling of hybrid cross-ply laminated rectangular plates

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