On the influence of laminate stacking on buckling of composite cylindrical shells subjected to axial compression

Geier, B.; Meyer-Piening, H.-R.; Zimmermann, Rolf

doi:10.1016/s0263-8223(01)00175-1

Cited by 73 publications

(30 citation statements)

References 2 publications

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“…Critical buckling loads of rectangular laminated composite plates were also studied by Shukla et al (2005), using Chebyshev series for spatial discretization, reporting results for different boundary conditions. Geier et al (2002) presented the influence of the stacking sequence on the buckling. Baba (2007) studied the buckling behavior of laminated composite plates focusing on the influence of the boundary conditions and the studies are based on experimental and numerical analyses.…”

Section: Buckling Of Laminated Compositesmentioning

confidence: 99%

Laminated Composites Buckling Analysis Using Lamination Parameters, Neural Networks and Support Vector Regression

Koide

Ferreira

Luersen

2015

Lat. Am. j. solids struct.

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This work presents a metamodel strategy to approximate the buckling load response of laminated composite plates. In order to obtain representative data for training the metamodel, some laminates with different stacking sequences are generated using the Latin hypercube sampling plan. These stacking sequences are converted into lamination parameters so that the number of inputs of the metamodel becomes constant. The buckling load for each laminate of the training set are computed using finite elements. In this way the inputs-outputs metamodel training pairs are the lamination parameters and the corresponding bucking load. Neural network and support vector regression metamodels are employed to approximate the buckling load. The performances of the metamodels are compared in a test case and the results are shown and discussed.

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Section: Buckling Of Laminated Compositesmentioning

confidence: 99%

Laminated Composites Buckling Analysis Using Lamination Parameters, Neural Networks and Support Vector Regression

Koide

Ferreira

Luersen

2015

Lat. Am. j. solids struct.

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“…In addition, it is shown that the imperfection sensitivity also depends on it; cf. Geier et al [16]. Another parameter influencing imperfection sensitivity is the ratio of radius over thickness of the cylindrical shell, NASA SP-8007 [3].…”

Section: Buckling Load Estimation Of Curved Panels and Cylindrical Shmentioning

confidence: 99%

“…The benchmark cylinder called "Z33" is used for the analyses. The Cylinder Z33 is originally designed by Zimmermann and published by Geier et al [16]. The cylinder is 510 mm height and 250 mm radius, laminated using carbon fiber prepeg.…”

Section: Modeling Of Cylindrical Shells With a Cutoutmentioning

confidence: 99%

Investigation of Buckling Behavior of Composite Shell Structures with Cutouts

et al. 2014

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Thin-walled cylindrical composite shell structures can be applied in space applications, looking for lighter and cheaper launcher transport system. These structures are prone to buckling under axial compression and may exhibit sensitivity to geometrical imperfections. Today the design of such structures is based on NASA guidelines from the 1960's using a conservative lower bound curve generated from a database of experimental results. In this guideline the structural behavior of composite materials may not be appropriately considered since the imperfection sensitivity and the buckling load of shells made of such materials depend on the lay-up design. It is clear that with the evolution of the composite materials and fabrication processes this guideline must be updated and / or new design guidelines investigated. This need becomes even more relevant when cutouts are introduced to the structure, which are commonly necessary to account for access points and to provide clearance and attachment points for hydraulic and electric systems. Therefore, it is necessary to understand how a cutout with different dimensions affects the buckling load of a thin-walled cylindrical shell structure in combination with other initial geometric imperfections. In this context, this paper present some observations regarding the buckling load behavior vs. cutout size and radius over thickness ratio, of laminated composite curved panels and cylindrical shells, that could be applied in further recommendations, to allow identifying when the buckling of the structure is dominated by the presence of the cutout or by other initial imperfections.

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“…With the recent developments in composite manufacturing science and technology, the range of allowable ply angles can now be increased. For the optimal thickness determined during global optimization, the stability limit of the structure can further be increased by exploiting the influence of stacking sequence of critical buckling loads [13] as well as natural frequency [14]. The optimization of fiber reinforced composite structures can broadly be classified as minimization of thickness, maximization of stability limit and maximization of natural frequencies.…”

Section: Introductionmentioning

confidence: 99%

Optimization of Stacking Sequence of Composite Cylindrical Shells using Genetic Algorithm

J¹,

Tjprc²

2018

IJMPERD

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On the influence of laminate stacking on buckling of composite cylindrical shells subjected to axial compression

Cited by 73 publications

References 2 publications

Laminated Composites Buckling Analysis Using Lamination Parameters, Neural Networks and Support Vector Regression

Laminated Composites Buckling Analysis Using Lamination Parameters, Neural Networks and Support Vector Regression

Investigation of Buckling Behavior of Composite Shell Structures with Cutouts

Optimization of Stacking Sequence of Composite Cylindrical Shells using Genetic Algorithm

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