Design and optimization of laminated conical shells for buckling

Goldfeld, Yiska; Arbocz, J.; Rothwell, A.

doi:10.1016/j.tws.2004.07.003

Cited by 43 publications

(25 citation statements)

References 11 publications

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“…As the orientation of fiber increased from 0˚ to 90˚, the value of stress decreased with minimum value of stress in layer having fibers oriented at 90˚. Higher stiffness in circumferential direction leads to higher buckling load and least amount of stress [11]. The peak-to-peak magnitude (waviness) of stress was higher in shafts with 0/90˚ and 60/30˚ fiber orientation, while the magnitude of stress remained almost consistent in shafts with ±45˚ and ±55˚ fiber orientation, due to symmetric off-axis loading.…”

Section: Resultsmentioning

confidence: 99%

Numerical Analysis of Stresses on Layer-by-Layer Basis in FML Composite Cylinder Subjected to External Hydrostatic Loading

Sumana¹,

Sagar²,

Sharma³

et al. 2015

MSA

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The aim of the research work was to numerically investigate the residual stresses induced between the layers of fiber metal laminate (FML) cylinder (glass/epoxy reinforced aluminum laminates) under buckling hydrostatic loading. For the analysis of buckling behavior of FML cylinders, various fiber orientations such as 0/90˚, 60/30˚, ±45˚ and ±55˚ and different FRP thickness of 1, 2, and 3 mm were considered. The aluminum cylinder of inner diameter 80 mm, length 800 mm and wall thickness 1 mm was modeled with SHELL281 element type and a total of 1033 elements were used for computing the induced residual stresses between the layers. The results show that magnitude of residual stresses between the layers decreased along the thickness from outer layer towards the inner layer in sine wave form. The maximum residual Von-Mises stress was at inner aluminum layer while the maximum residual radial stress was at the outermost layer of FML cylinder due to the inward pressure. Among all types of FML cylinder 0/90˚ fiber oriented FML cylinder exhibited the least radial stress and a maximum Von-Mises stress along the FRP thickness.

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Section: Resultsmentioning

confidence: 99%

Numerical Analysis of Stresses on Layer-by-Layer Basis in FML Composite Cylinder Subjected to External Hydrostatic Loading

Sumana¹,

Sagar²,

Sharma³

et al. 2015

MSA

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“…Rezadoust et al [190] investigated the crush behavior of conical composite shells. Goldfeld et al [191] presented design and optimization of laminated conical shells for buckling. Kosonen [192] described specification for mechanical analysis of conical composite shells.…”

Section: Shell Geometriesmentioning

confidence: 99%

“…Other buckling analyses include Matsunaga [53], Shen [69], Sofiyev et al [73], Wang et al [86], Huang [97], Wang et al [102], Weaver et al [118], Huang and Lu [119], Shen and Xiang [120], Diaconu et al [121], Wang and Dong [125 ], Hilburger and Starnes [143], Semenyuk et al [144], Tafreshi [145], Zang et al [176], Goldfeld et al [186,191], Singh and Babu [188], Wu and Chiu [189], Kadoli and Ganesan [198], and Pinto Correiaa [205].…”

Section: Buckling Analysismentioning

confidence: 99%

Review of Recent Literature on Static Analyses of Composite Shells: 2000-2010

Qatu¹,

Asadi²,

Wang³

2012

OJCM

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Laminated composite shells are frequently used in various engineering applications including aerospace, mechanical, marine, and automotive engineering. This article reviews the recent literature on the static analysis of composite shells. It follows up with the previous work published by the first author [1-4] and it is a continuation of another recent article that focused on the dynamics of composite shells [3]. This paper reviews most of the research done in recent years (2000-2010) on the static and buckling behavior (including postbuckling) of composite shells. This review is conducted with an emphasis on the analysis performed (static, buckling, postbuckling, and others), complicating effects in both material (e.g. piezoelectric) and structure (e.g. stiffened shells), and the various shell geometries (cylindrical, conical, spherical and others). Attention is also given to the theory being applied (thin, thick, 3D, nonlinear …). However, more details regarding the theories have been described in previous work [1,3]

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“…The ply-angle y i and the layer thickness h i for the filament wound angle-ply shells are expressed as [14,15] y i ¼ arcsin…”

Section: Formulationmentioning

confidence: 99%

Postbuckling of angle-ply laminated cylindrical shells with meridional curvature

Singh

Patel

Nath

2009

Thin-Walled Structures

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Design and optimization of laminated conical shells for buckling

Cited by 43 publications

References 11 publications

Numerical Analysis of Stresses on Layer-by-Layer Basis in FML Composite Cylinder Subjected to External Hydrostatic Loading

Numerical Analysis of Stresses on Layer-by-Layer Basis in FML Composite Cylinder Subjected to External Hydrostatic Loading

Review of Recent Literature on Static Analyses of Composite Shells: 2000-2010

Postbuckling of angle-ply laminated cylindrical shells with meridional curvature

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