The nonlinear prebuckling response of short thin-walled laminated composite cylinders in bending

Purpose The purpose of this paper is to present a design sensitivity analysis continuum formulation for the cross-section properties of thin-walled laminated composite beams. These properties are expressed as integrals based on the cross-section geometry, on the warping functions for torsion, on shear bending and shear warping, and on the individual stiffness of the laminates constituting the cross-section. Design/methodology/approach In order to determine its properties, the cross-section geometry is modeled by quadratic isoparametric finite elements. For design sensitivity calculations, the cross-section is modeled throughout design elements to which the element sensitivity equations correspond. Geometrically, the design elements may coincide with the laminates that constitute the cross-section. Findings The developed formulation is based on the concept of adjoint system, which suffers a specific adjoint warping for each of the properties depending on warping. The lamina orientation and the laminate thickness are selected as design variables. Originality/value The developed formulation can be applied in a unified way to open, closed or hybrid cross-sections.

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Torsion of Open and Closed Thin-Walled Laminated Composite Sections

Journal of Composite Materials ◽

10.1177/0021998305047097 ◽

2005 ◽

Vol 39 (6) ◽

pp. 497-524 ◽

Cited By ~ 22

Author(s):

Hani A. Salim ◽

Julio F. Davalos

Keyword(s):

Laminated Composite ◽

Thin Walled

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Influence of Crack on the Instability of GFRP Composite Cylindrical Shells under Combined Loading

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.877.453 ◽

2018 ◽

Vol 877 ◽

pp. 453-459

Author(s):

B. Angelina Catherine ◽

R.S. Priyadarsini

Keyword(s):

Structural Integrity ◽

Cylindrical Shells ◽

Laminated Composite ◽

External Pressure ◽

Industrial Applications ◽

Combined Loading ◽

Finite Element Software ◽

Buckling Behavior ◽

Thin Walled ◽

Composite Cylindrical Shells

Buckling is a prominent condition of instability caused to a shell structure as a result of axial loadings. The process of buckling becomes more complex while analyzing thin walled structures like shells. Today such thin walled laminated composite shells are gaining more importance in many defense and industrial applications since they have greater structural efficiency and performance in relation to isotropic structures. Comprehensive understanding of the buckling response of shell structures is necessary to assure the integrity of these shells during their service life. The presence of defects, such as cracks, may severely compromise their buckling behavior and jeopardize the structural integrity. This work aims in conducting numerical analysis of cracked GFRP (Glass fibre-reinforced polymer) composite cylindrical shells under combined loading to study the effect of crack size on the buckling behavior of laminated composite cylindrical shells with different lay-up sequences. The numerical analyses were carried out using the finite element software, ABAQUS in order to predict the buckling behaviour of cracked laminated composite cylinders subject to different combinations of axial compression, torsion, internal pressure and external pressure from the interaction buckling curves.

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