Large deflection effects of cracked aluminum plates repaired with bonded composite patches

Klug, John C.; Sun, C. T.

doi:10.1016/s0263-8223(98)00018-x

Cited by 31 publications

(17 citation statements)

References 6 publications

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“…They are assumed to be constant across the adhesive thickness. This assumption is a natural extension of that widely used in adhesive bonded joints and/or repairs to flat surfaces or plates [10,[12][13][14]. (c) The thin-walled parent structure and bonded patch can be modeled using the first-order or moderately thick plate and shell theory.…”

Section: Fundamental Formulation Of Adhesive Elementmentioning

confidence: 99%

“…Based on assumptions common to the theories of Goland Reissner [10] and Ojalvo and Eidinoff [11], Carpenter [12] developed two adhesive elements in which both shear and peel stresses are included in the finite element formulation of the adhesive element. Sun et al [13] and Klug and Sun [14] presented an efficient model for bonded repair to cracked aluminum plates. In their model, both aluminum plate and composite patch are modeled separately by the Midlin plate element, whereas the adhesive layer is modeled with effective springs connecting the patch and aluminum plate.…”

Section: Introductionmentioning

confidence: 99%

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Adhesive elements for stress analysis of bonded patch to curved thin-walled structures

Tong

Sun

2003

Computational Mechanics

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Bonded composite patching has been recognized as an efficient and economical method to extend the service life of cracked aluminum components. However, current analysis methods and empirical databases for designing composite bonded joint and patch repair are limited to flat plate and/or flat laminate geometries, and the effect of curvature on the performance and durability of composite bonded joints and repairs is not known. This paper presents a novel finite element formulation for developing adhesive elements for conducting quick stress analysis of bonded repairs to curved structures. Illustrative examples are presented to demonstrate the effect of curvature and the effect of patch location, i.e., internal and external patches, patch size and patch thickness on stresses in adhesive layer.

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Section: Fundamental Formulation Of Adhesive Elementmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Adhesive elements for stress analysis of bonded patch to curved thin-walled structures

Tong

Sun

2003

Computational Mechanics

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“…4 Generally, thin panels were analyzed by using 2-D models, [5][6][7][8][9][10][11][12][13] whereas thick panels were done as a 3-D problem. [14][15][16][17][18][19][20][21][22][23][24] With thin panels, Naboulsi and Mall 5 proposed a 2-D model for the analysis of adhesive layer, composite patch and thin notched substrate panel. Sun and Klug 6 developed an effective spring model of adhesive layer from the Mindlin plate theory.…”

Section: Introductionmentioning

confidence: 99%

“…15 Klug and Sun 16 undertook edge crack propagation tests around central notch of thick panel. Jones and Chiu 17 achieved experimental investigation and numerical analysis on notch repair for thick structures.…”

Section: Introductionmentioning

confidence: 99%

Material parameter modeling and solution technique using birth–death element for notched metallic panel repaired with bonded composite patch

Tong

Shi-qiu

Xiong

2014

Chinese Journal of Aeronautics

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This paper seeks to outline a novel three-layer model and a new birth-death element solution technique to evaluate static strength of notched metallic panel repaired with bonded composite patch and to optimize material parameters. The higher order 3D, 8-node isotropic solid element and 8-node anisotropic layered solid element with three degrees of freedom per node are respectively implemented to model substrate panel, adhesive layer and composite patch to establish three-layer model of repaired panel. The new solving technique based on birth-death element is developed to allow solution of the stress pattern of repaired panel for identifying failure mode. The new model and its solution are used to model failure mode and residual strength of repaired panel, and the obtained results have a good agreement with the experimental findings. Finally, the influences of material parameter of adhesive layer and composite patch on the residual strength of repaired panel are investigated for optimizing material properties to meet operational and environmental constraints.

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“…If the number of crack is limited and the crack or hole size is small compared to the damaged component, repairs are less expensive, otherwise the component should be replaced [4].…”

Section: Introductionmentioning

confidence: 99%

Some aspects and aerodynamic effects in repairing battle damaged wings

Djellal¹,

Ouibrahim²

2009

WIT Transactions on Modelling and Simulation

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This paper concerns an experimental investigation, conducted to estimate the aerodynamic effects of aircraft battle-damage repair patches. Of particular concern in this study are the wings. Three different repair schemes are considered, lower (repair at the intrados), upper (repair at the extrados) and full repairs (both intrados and extrados at the same time). Preliminary results clearly showed that repair patches improve the aerodynamic performances of the damaged aircraft model. The full repair was shown to achieve the best recovery of the aerodynamic performances provided that the patch is thin enough. Repairs performed on only one surface (i.e. upper or lower) were also shown to provide significant aerodynamic improvements. The improvement tendency decreases with the increase of the patch thickness. Above a certain thickness value, the fineness decreases below the fineness of the damaged unrepaired model.

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Large deflection effects of cracked aluminum plates repaired with bonded composite patches

Cited by 31 publications

References 6 publications

Adhesive elements for stress analysis of bonded patch to curved thin-walled structures

Adhesive elements for stress analysis of bonded patch to curved thin-walled structures

Material parameter modeling and solution technique using birth–death element for notched metallic panel repaired with bonded composite patch

Some aspects and aerodynamic effects in repairing battle damaged wings

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