Optimization of a composite scarf repair patch under tensile loading

Breitzman, Timothy; Iarve, Endel V.; Cook, Benjamin M.; Schoeppner, G. A.; Lipton, Robert

doi:10.1016/j.compositesa.2009.04.033

Cited by 98 publications

(45 citation statements)

References 19 publications

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“…Results suggest that the location of 0°plies has a significant impact on the magnitude of stress concentration, with 0°p lies placed near or at at the free edge resulting in localised peak stress regions. These results concur with previously published results [22,23].…”

Section: Effect Of Stacking Sequencesupporting

confidence: 96%

Optimisation study of tapered scarf and stepped-lap joints in composite repair patches

Bendemra

Compston

Crothers

2015

Composite Structures

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Section: Effect Of Stacking Sequencesupporting

confidence: 96%

Optimisation study of tapered scarf and stepped-lap joints in composite repair patches

Bendemra

Compston

Crothers

2015

Composite Structures

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“…Roberto 27 presented optimum design scheme for composite bonding repair by using genetic algorithm and found a significant influence of geometry of composite patch on fracture and fatigue lives of repaired panel. Breitzman et al 28 conducted optimization design on the thickness and stacking sequence of composite repair patch under tensile loading by checking von Mises stress pattern. Ramji et al 29 performed geometry optimization of notched panel repaired with bonded symmetrical composite patches with circle, rectangle, square, ellipse, octagon and expanded octagon shapes based on 3-D FEA.…”

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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“…Patch repair is an efficient and cost effective way of extending the service life of damaged engineering structures as it allows a localised in-situ repair of the damaged structure instead of a complete replacement. Patch repair of damaged composite structures involves the removal of sufficient material from the damaged area and replacing the removed material by adhesive bonding of new undamaged repair material to the structure that is being repaired, see for example [1,2]. Pipes with external corrosion can also be repaired by adhesive bonding of composite overwrap on the external surface of the pipe [3].…”

Section: Introductionmentioning

confidence: 99%

Fracture initiation in bi-material joints subject to combined tension and shear loading

Akisanya

2017

Journal of Adhesion Science and Technology

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Linear elastic solution of the stress field near an interface corner of bi-material joints is of the form Hr -1 , where r is the radial distance from the corner, H is the stress intensity factor and 1 is the order of the singularity. Finite element analysis is used to determine the magnitude of H for a butt joint subject to remote shear; the obtained solution complements existing solution for remote tension and uniform change in temperature. The theoretical solution of the singular shear stress is shown to be in good agreement with the corresponding finite element solution. The effect of combined remote tension, remote shear and uniform change in temperature on the failure loads and failure mechanisms is experimentally determined for brass/araldite/brass butt joint. It is shown that the failure envelope in tensile stress -shear stress space is elliptical and the failure loads decrease with increasing cure temperature due to thermal residual stress associated with the curing process. The application of the results to the assessment of onset of failure in composite patch repair is discussed.

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Optimization of a composite scarf repair patch under tensile loading

Cited by 98 publications

References 19 publications

Optimisation study of tapered scarf and stepped-lap joints in composite repair patches

Optimisation study of tapered scarf and stepped-lap joints in composite repair patches

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

Fracture initiation in bi-material joints subject to combined tension and shear loading

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