Embedded delamination growth in composite panels under compressive load

Riccio, Aniello; Scaramuzzino, F.; Perugini, P.

doi:10.1016/s1359-8368(00)00057-3

Cited by 57 publications

(44 citation statements)

References 14 publications

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“…Use of the latter would give a prediction of propagation that is up to 85 per cent higher than the experimental value. For all but the [0 2 /90] and [0/45] cases considered above, the strip model actually gives better agreement with experimental values than FEA initiation. This may be due to the inadequacy of the mixed-mode formulation of equation (2.20) to capture all combinations of mode mixity.…”

Section: (D) Strip Model Resultsmentioning

confidence: 88%

“…Hence, nonlinear finite element analyses (FEAs) employing interface elements or virtual crack closure techniques are the methods usually adopted (e.g. [1][2][3][4]). However, such methods are complex, requiring large computational effort, and do not lend themselves to understanding the mechanisms that promote or reduce damage tolerance across a range of laminates.…”

Section: Introductionmentioning

confidence: 99%

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Compressive strength of delaminated aerospace composites

Butler

Rhead

Liu

et al. 2012

Phil. Trans. R. Soc. A.

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An efficient analytical model is described which predicts the value of compressive strain below which buckle-driven propagation of delaminations in aerospace composites will not occur. An extension of this efficient strip model which accounts for propagation transverse to the direction of applied compression is derived. In order to provide validation for the strip model a number of laminates were artificially delaminated producing a range of thin anisotropic sub-laminates made up of 0• , ±45• and 90• plies that displayed varied buckling and delamination propagation phenomena. These laminates were subsequently subject to experimental compression testing and nonlinear finite element analysis (FEA) using cohesive elements. Comparison of strip model results with those from experiments indicates that the model can conservatively predict the strain at which propagation occurs to within 10 per cent of experimental values provided (i) the thin-film assumption made in the modelling methodology holds and (ii) full elastic coupling effects do not play a significant role in the post-buckling of the sub-laminate. With such provision, the model was more accurate and produced fewer non-conservative results than FEA. The accuracy and efficiency of the model make it well suited to application in optimum ply-stacking algorithms to maximize laminate strength.

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Section: (D) Strip Model Resultsmentioning

confidence: 88%

Section: Introductionmentioning

confidence: 99%

Compressive strength of delaminated aerospace composites

Butler

Rhead

Liu

et al. 2012

Phil. Trans. R. Soc. A.

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“…A great of effort of researches have been carried out to fully understand the compressive behavior of delaminated composite panels. The present research results have shown that the compressive strength and the fatigue performance are dramatically dependent of delamination area, delamination location and stacking sequences [2][3][4]. In particular, the larger delamination area may often lead to the lower compressive strength and the lower load-carrying capacity.…”

mentioning

confidence: 64%

Statistical Study of Delamination Area Distribution in Composite Components Fabricated by Autoclave Process

Xie

Wang

et al. 2009

Appl Compos Mater

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As the most frequent defect in composite structures during fabricated by autoclave process, delamination has evidently influence on compressive behavior of delaminated composite panels. For structure design purposes, delamination area is of great importance parameter to be considered. Based on considerable delamination information from nondestructive identification for composite components, a statistical study was in detail presented to investigate how delamination area in different composite components distributed. The distribution model of delamination area was hypothesized and tested by normal W test and normal D test. With consideration combined by the dispersibility and the qualified rate of delamination area, an effective method for estimating the manufacturing quality of composite components was also established. The results indicated that a lognormal distribution was found to represent the delamination area quite well and about 100 mm 2 had the maximum probability. Moreover, the complexity and the thickness of composite structures had significantly influence on the qualified rate of delamination area. The more complex structure and the thinner or the thicker composites decreased the qualified rate of delamination area.

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“…Coefficients of the stiffness matrices are required to reduce to zero for tensile and compressive failure modes. However, in order to avoid numerical problems, the stiffness matrix is equated to a very small number [18]. Majority of material Poisson's ratios are reduced to zero.…”

Section: Materials Properties Of Pre-assumed Damage Zonesmentioning

confidence: 99%

“…Investigations of the buckling-driven behaviour of panels with circular cut-outs as damages are reported to be comparatively easier to model and reproduce experimentally [16] and [17]. The artificial damage (soft-inclusion) was inserted into laminates during manufacturing to determine and correlate critical buckling load and validate the experimental results [18]. The method of artificial damage with known positions, sizes and shapes is also reported to be very useful in experimental studies [19], [20] and [12].…”

Section: Introductionmentioning

confidence: 99%