Numerical characterization of imperfection sensitive composite structures

Arbelo, Mariano A.; Degenhardt, Richard; Castro, Saullo G.P.; Zimmermann, Rolf

doi:10.1016/j.compstruct.2013.09.041

Cited by 89 publications

(35 citation statements)

References 11 publications

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“…: Critical axial buckling loads (݇ܰ) for the imperfect cylinders Z23, Z25 and Z26 measured imperfection amplitude (݉ ଵ = 120, ݉ ଶ = 30, ݊ ଶ = 55) proposed model with geometric imperfections caused by a lateral load, currently investigated by [35]), was verified for cylinder Z33 [36], with ܴ ଵ = 250 ݉݉ ), ply thickness 0.125 ݉݉ and lamina properties: ‫ܧ‬ ଵଵ = 123 695 ‫.ܽܲܩ‬ The results of Table 7 show that the proposed model results in an 25, ݊ ଶ = 45. show that the current implementation [28] was in average 8 times slower than Abaqus and the bottleneck is the numerical integration of the non-linear stiffness matrices ሾ‫ܭ‬ ሿ, ሾ‫ܭ‬ ீ ሿ and ሾ‫ܭ‬ ሿ. When these matrices ar for each integration point only the stiffness matrix corresponding to the element containing this integration point has to be evaluated, whereas in the Ritz method the whole stiffness matrix has to be evaluated for each s of freedom are the amplitudes of the approximation functions of the field variables.…”

Section: Buckling Of Imperfect Cylindersmentioning

confidence: 99%

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Evaluation of non-linear buckling loads of geometrically imperfect composite cylinders and cones with the Ritz method

Castro

Mittelstedt²,

Monteiro³

et al. 2015

Composite Structures

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Section: Buckling Of Imperfect Cylindersmentioning

confidence: 99%

“…to apply the proposed model many authors ( [16] [19] [31] [32] [33] [34][35] (−51/+51/−45/+45/−37/+37/−19/+19/0/0), ply thickness 8.708 ‫,ܽܲܩ‬ ߥ ଵଶ = 0.28, ‫ܩ‬ ଵଶ = ‫ܩ‬ ଵଷ = ‫ܩ‬ ଶଷ = 5.695 average error of 1.04% with ݉ ଵ = 120, ݉ ଶ = 25…”

mentioning

confidence: 99%

Evaluation of non-linear buckling loads of geometrically imperfect composite cylinders and cones with the Ritz method

Castro

Mittelstedt²,

Monteiro³

et al. 2015

Composite Structures

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“…Several preliminary studies performed by the authors can be found in Degenhardt et al [8,9], Castro et al [10] and Arbelo et al [11]. The main challenge for the modeling of this type of structures is how to define a reliable set of imperfections that can represent the original Fig.…”

Section: Buckling Load Estimation Of Curved Panels and Cylindrical Shmentioning

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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“…The imperfection sensitivity exhibited by cylindrical shells renders particular emphasis on their design against instability in axial compression. Therefore, robust design approaches are being developed and validated, such as single perturbation load, single perturbation displacement, single boundary perturbation approaches, and their modifications (see, e.g., [1][2][3][4][5][6][7]) in order to replace the existing overconservative design guidelines.…”

Section: Introductionmentioning

confidence: 99%

Applicability of the Vibration Correlation Technique for Estimation of the Buckling Load in Axial Compression of Cylindrical Isotropic Shells with and without Circular Cutouts

Skuķis

Ozoliņš

Andersons

et al. 2017

Shock and Vibration

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Applicability of the vibration correlation technique (VCT) for nondestructive evaluation of the axial buckling load is considered. Thin-walled cylindrical shells with and without circular cutouts have been produced by adhesive overlap bonding from a sheet of aluminium alloy. Both mid-surface and bond-line imperfections of initial shell geometry have been characterized by a laser scanner. Vibration response of shells under axial compression has been monitored to experimentally determine the variation of the first eigenfrequency as a function of applied load. It is demonstrated that VCT provides reliable estimate of buckling load when structure has been loaded up to at least 60% of the critical load. This applies to uncut structures where global failure mode is governing collapse of the structure. By contrast, a local buckling in the vicinity of a cutout could not be predicted by VCT means. Nevertheless, it has been demonstrated that certain reinforcement around cutout may enable the global failure mode and corresponding reliability of VCT estimation.

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Numerical characterization of imperfection sensitive composite structures

Cited by 89 publications

References 11 publications

Evaluation of non-linear buckling loads of geometrically imperfect composite cylinders and cones with the Ritz method

Evaluation of non-linear buckling loads of geometrically imperfect composite cylinders and cones with the Ritz method

Investigation of Buckling Behavior of Composite Shell Structures with Cutouts

Applicability of the Vibration Correlation Technique for Estimation of the Buckling Load in Axial Compression of Cylindrical Isotropic Shells with and without Circular Cutouts

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