Fracture mechanics using a 3D composite element

Falzon, Brian; Hitchings, D.; Besant, T.

doi:10.1016/s0263-8223(99)00011-2

Cited by 17 publications

(6 citation statements)

References 15 publications

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“…4). The Virtual Crack Closure Technique [12] was used whereby, under constant displacement, the change in strain energy, DU, for a given increase in crack propagation, Da, yields the total strain energy release rate, G T ¼ ÀqU/qa [13]. The change in strain energy was calculated by the removal of the adhesive elements between the skin and the stiffener to represent Table 1 Material properties for IM7/8552, measured in-house, and FM300.…”

Section: Energy Release Rate Across Widthmentioning

confidence: 99%

Design of composite stiffener run-outs for damage tolerance

Psarras

Pinho

Falzon

2011

Finite Elements in Analysis and Design

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Section: Energy Release Rate Across Widthmentioning

confidence: 99%

Design of composite stiffener run-outs for damage tolerance

Psarras

Pinho

Falzon

2011

Finite Elements in Analysis and Design

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“…Continuum shell elements in ABAQUS discretize the entire 3D model in which they are used, and their thickness is determined by the nodal connectivity in the FE mesh. From a modelling point of view, continuum shell elements look just like brick elements, but their kinematic and constitutive behaviour is similar to that of conventional shell elements [11,12].…”

Section: Finite Element Model Featuresmentioning

confidence: 99%

Numerical Analysis of Stiffener Runout Sections

Faggiani

Falzon

2007

Appl Compos Mater

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The recent trend of incorporating more composite material in primary aircraft structures has highlighted the vulnerability of stiffened aerostructures to through-thickness stresses, which may lead to delamination and debonding at the skin-stiffener interface, leading to collapse. Stiffener runout regions are particularly susceptible to this problem and cannot be avoided due to the necessity to terminate stiffeners at rib intersections or at cutouts, interrupting the stiffener load path. In this paper, experimental tests relating to two different stiffener runout specimens are presented and the failure modes of both specimens are discussed in detail. A thinner-skinned specimen showed sudden and unstable crack propagation, while a thicker-skinned specimen showed initially unstable but subsequent stable crack growth. Detailed finite element models of the two specimens are developed, and it is shown how such models can explain and predict the behaviour and failure mode of stiffener runouts. The models contain continuum shell elements to model the skin and stiffener, while cohesive elements using a traction-separation law are placed at the skinstiffener interface to effectively model the debonding which promotes structural failure.

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“…The I-stiffened panel, I-P1, discussed in Section 2.1, was modelled using an in-house finite element code FE77XM (27) which incorporated the developments presented in Section 3.3. The panel model was developed using quadratic three-dimensional thick-shell composite elements incorporated in the code (28) . This allowed for detailed modelling of the stiffeners' geometric features including the flange taper (refer to Fig.…”

Section: Numerical Analysis 41 I-stiffened Panelmentioning

confidence: 99%

A study of secondary instabilities in postbuckling composite aerostructures

Falzon

Cerini

2007

Aeronaut. j.

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A number of experimental studies have shown that postbuckling stiffened composite panels, loaded in uniaxial compression, may undergo secondary instabilities, characterised by an abrupt change in the buckled mode-shape of the skin between the supporting stiffeners. In this study high-speed digital speckle photogrammetry is used to gain further insight into an I-stiffened panel’s response during this transient phase. This energy-dissipating phenomenon will be shown to be able to cause catastrophic structural failure in vulnerable structures. It is therefore imperative that an accurate and reliable methodology is available to predict this phenomenon. The shortcomings of current non-linear implicit solution schemes, found in most commercially-available finite element codes, are discussed. A robust and efficient strategy, which utilises an automated quasi-static/pseudo-transient hybrid scheme, is presented in this paper and validated using a number of experimental tests. This approach is shown to be able to predict mode-jumping with good accuracy.

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Fracture mechanics using a 3D composite element

Cited by 17 publications

References 15 publications

Design of composite stiffener run-outs for damage tolerance

Design of composite stiffener run-outs for damage tolerance

Numerical Analysis of Stiffener Runout Sections

A study of secondary instabilities in postbuckling composite aerostructures

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