Geometrically non-linear analysis of laminated composite structures using a 4-node co-rotational shell element with enhanced strains

Kim, Ki-Du; Han, Sang-Eon; Suthasupradit, Songsak

doi:10.1016/j.ijnonlinmec.2007.03.011

Cited by 19 publications

(19 citation statements)

References 34 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…(Basar,et al, 1993) solved this problem using a fully nonlinear formulation accounting for finite rotations along with higher order shear defamation theory. Our (FOSD FRT) results agree very well with those of (Basar, et al, 1993), (LRT56-Kreja, 2013) and (Kim,et al, 2007). On the other hand, the FOSD FRT solution differs from the other simplified nonlinear models LRT5 and MRT5.…”

Section: Fig2 Two Edges Hinged Composite Laminated Platesupporting

confidence: 89%

“…Due to the dual symmetry of the analyzed structure, a quarter of the plate is modeled. In Figure 3 the normalized transverse deflection is compared with the existing literature given by (LRT56-Kreja, 2013), (Kim, et al, 2007), (Kreja and Schmidt, 2006) (LRT5, MRT5) together with the reference solutions of (Reddy, 1990) and (Basar,et al, 1993).…”

Section: Asymmetric Cross-ply Laminated Plate Strip Under Uniformly Dmentioning

confidence: 99%

“…The EAS method was studied by (Andelfinger and Ramm, 1993) and (Fontes Valente,et al, 2005) to improve the behavior of the shell elements. (Kim,et al, 2007) developed 4-node co-rotational shell element with assumed natural strain and with enhanced strains to analyze the laminated composite structures. (Caseiro,et al, 2013) gave brief description and development of EAS three-dimensional finite elements for the alleviation of locking phenomena.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

“Snap-through” Buckling of Laminated Cylindrical Shells at Finite Rotations

Rao¹

2010

Int.J.of Curr. Engg. and Technol

View full text Add to dashboard Cite

show abstract

Section: Fig2 Two Edges Hinged Composite Laminated Platesupporting

confidence: 89%

Section: Asymmetric Cross-ply Laminated Plate Strip Under Uniformly Dmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

“Snap-through” Buckling of Laminated Cylindrical Shells at Finite Rotations

Rao¹

2010

Int.J.of Curr. Engg. and Technol

View full text Add to dashboard Cite

show abstract

“…[1][2][3] Composite structures are generally orthotropic in nature, often showing unique response even under simple loading conditions and geometric con¯gurations, and thus present challenging technical problems in their modeling. 2,[4][5][6][7][8][9][10][11] Computational theories for the modeling of composite shells can be categorized as: (i) classical laminated plate theory; [12][13][14] (ii)¯rst-order shear deformation laminated plate theory; 9,15-20 (iii) higher-order shear deformation laminated plate theories; 2,21-25 (iv) layer-wise theories; 2,26 and (v) zig-zag theories. [27][28][29][30] The number of unknown variables employed in the¯rst three theories are independent from the number of constitutive layers, thus they belong to equivalent single-layer theories.…”

Section: Introductionmentioning

confidence: 99%

A 4-Node Co-Rotational Quadrilateral Composite Shell Element

Zheng

Vu‐Quoc

et al. 2016

Int. J. Str. Stab. Dyn.

View full text Add to dashboard Cite

A 4-node co-rotational quadrilateral composite shell element is presented. The local coordinate system of the element is a co-rotational framework defined by the two bisectors of the diagonal vectors generated from the four corner nodes and their cross product. Thus, the element rigid-body rotations are excluded in calculating the local nodal variables from the global nodal variables. Compared with other existing co-rotational finite-element formulations, the present element has two features: (i) The two smallest components of the mid-surface normal vector at each node are defined as the rotational variables, leading to the desired additive property for all nodal variables in a nonlinear incremental solution procedure; (ii) both element tangent stiffness matrices in the local and global coordinate systems are symmetric owing to the commutativity of the nodal variables in calculating the second derivatives of strain energy with respect to the local nodal variables and, through chain differentiation with respect to the global nodal variables. In the modeling of composite structures, the first-order shear deformable laminated plate theory is adopted in the local element formulation, where both the thickness deformation and the normal stress in the direction of the shell thickness are ignored, and an assumed strain method is employed to alleviate the membrane and shear locking phenomena. Several examples involving composite plates and shells with large displacements and large rotations are presented to testify to the reliability and convergence of the present formulation

show abstract

“…An assumedstrain Hu-Washizu variational framework was utilized[31]. Kim et al adopted the corotational formulation in combination with enhanced assumed strain and assumed natural strain methods to derive an improved 4-node shell element for nonlinear analysis[32].…”

mentioning

confidence: 99%