Postbuckling and failure of stiffened composite panels under axial compression

Kong, Cheol-Won; Lee, In-Cheol; Kim, Chun-Gon; Hong, Chang Sun

doi:10.1016/s0263-8223(98)00044-0

Cited by 61 publications

(49 citation statements)

References 11 publications

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“…A comprehensive review of the early experimental studies of buckling and postbuckling behaviour of laminated composite plates with cut-outs was given in Nemeth (1996). Subsequently, the influence of stiffeners on the behaviours of damaged and undamaged plates was experimentally studied in Greenhalgh et al (1996), Greenhalgh, Singh, Hughes, and Roberts (1999), Jegley (1992Jegley ( , 1998, Kong, Lee, Kim, and Hong (1998) and Stevens, Ricci, and Davies (1995). The postbuckling compressive strength of undamaged panels with I-stiffeners was reported to be 5e7 times higher than the buckling load for the same plate (Kong et al, 1998).…”

Section: Bounds For the Critical Controlled Parameters For Materials mentioning

confidence: 99%

Compressive fracture of layered composites caused by internal instability

Guz

Menshykova

Soutis

2015

Structural Integrity and Durability of Advanced Composites

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Section: Bounds For the Critical Controlled Parameters For Materials mentioning

confidence: 99%

Compressive fracture of layered composites caused by internal instability

Guz

Menshykova

Soutis

2015

Structural Integrity and Durability of Advanced Composites

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“…The first two tests were done by Kong et al (1998) and the last one was done by Smith and Dow (1985).…”

Section: Validationmentioning

confidence: 99%

Parametric study on average stress-average strain curve of composite stiffened plates using progressive failure method

Morshedsolouk

Khedmati

2014

Lat. Am. j. solids struct.

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The post-buckling behavior of composite ships' stiffened plate panels has been studied. In this study, the average strain-average stress curves for these panels are derived using progressive failure method as well as nonlinear finite element method. The boundary conditions are appropriate for the continuous plate panels used in shipbuilding. The effects of the aspect ratio, initial geometrical imperfection and stiffener size on the post-buckling of these stiffened panels are evaluated. KeywordsProgressive failure analysis, hat stiffened plate panel, initial imperfection, Finite Element Method (FEM).Parametric study on average stress-average strain curve of composite stiffened plates using progressive failure method

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“…A nonlinear finite element analysis code for composite structures, COSAP(COmposite Structure Analysis Program) which was developed in the papers [6][7][8], was used to analyze buckling and postbuckling behavior of composite plates and stiffened panels in this study. A brief formulation procedure of the analysis is stated below.…”

Section: Nonlinear Finite Element Analysis For Composite Structuresmentioning

confidence: 99%

“…Genetic algorithm [7] was used as the optimization method in this study. It simulates the natural evolution so that multiple design points evolve to be converged to a global optimum.…”

Section: Genetic Algorithmmentioning

confidence: 99%

Minimum-weight design of compressively loaded composite plates and stiffened panels for postbuckling strength by Genetic Algorithm

Kang

Kim

2005

Composite Structures

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SUMMARY:The minimum-weight design of compressively loaded laminated plates and stiffened panels was aimed under constrained postbuckling strength in this paper. A nonlinear finite element code, COSAP(COmposite Structure Analysis Program) was applied to analyze the precise buckling and postbuckling behaviour. As an optimization technique, Genetic Algorithm was used to find the optimum points in the design space. A conventional genetic algorithm was modified with two new techniques. One is the use of the pre-calculated result to reduce the calculation cost, and the other is the use of variable population size in genetic algorithm to find better optimum points. The modified Genetic Algorithm code was then parallelized with MPI(Message Passing Interface) library and the optimization was executed with a parallel-computing supercomputer, CRAY T3E. The optimal design was performed in two cases; a composite plate and a composite stiffened panel. The design variables were number of plies and the ply angle in each ply. In case of the stiffened panels, the size and spacing of the stiffeners were also considered as the design variables. The objective function was defined as the product of the nondimensional weight and strength. The optimization was performed with two chosen examples, and the results showed that the optimal designs have better performances than conventional designs.

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Postbuckling and failure of stiffened composite panels under axial compression

Cited by 61 publications

References 11 publications

Compressive fracture of layered composites caused by internal instability

Compressive fracture of layered composites caused by internal instability

Parametric study on average stress-average strain curve of composite stiffened plates using progressive failure method

Minimum-weight design of compressively loaded composite plates and stiffened panels for postbuckling strength by Genetic Algorithm

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