3D Numerical Investigation of Aluminum 2024-T3 Plate Repaired with Asymmetric and Symmetric Composite Patch

Makwana, Alpesh H.; Shaikh, A. A.; Bakare, A.K.; Chitturi, Saikrishna

doi:10.1016/j.matpr.2018.10.153

Cited by 8 publications

(7 citation statements)

References 18 publications

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“…Albedah et al (2018a, b) studied the effect of patch length on one-side bonded composite patches for aluminum panels. Makwana et al (2018) compared symmetric and asymmetric composite patches. They discovered that symmetric patches reduce the stress in a cracked aluminum plate more effectively than asymmetric patches, resulting in a more significant SIF reduction.…”

Section: Introductionmentioning

confidence: 99%

Experimental and numerical analysis of the behavior of rehabilitated aluminum structures using chopped strand mat GFRP composite patches

Althahban,

Nowier,

El-Sagheer

et al. 2024

FEBE

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PurposeThis paper comprehensively addresses the influence of chopped strand mat glass fiber-reinforced polymer (GFRP) patch configurations such as geometry, dimensions, position and the number of layers of patches, whether a single or double patch is used and how well debonding the area under the patch improves the strength of the cracked aluminum plates with different crack lengths.Design/methodology/approachSingle-edge cracked aluminum specimens of 150 mm in length and 50 mm in width were tested using the tensile test. The cracked aluminum specimens were then repaired using GFRP patches with various configurations. A three-dimensional (3D) finite element method (FEM) was adopted to simulate the repaired cracked aluminum plates using composite patches to obtain the stress intensity factor (SIF). The numerical modeling and validation of ABAQUS software and the contour integral method for SIF calculations provide a valuable tool for further investigation and design optimization.FindingsThe width of the GFRP patches affected the efficiency of the rehabilitated cracked aluminum plate. Increasing patch width WP from 5 mm to 15 mm increases the peak load by 9.7 and 17.5%, respectively, if compared with the specimen without the patch. The efficiency of the GFRP patch in reducing the SIF increased as the number of layers increased, i.e. the maximum load was enhanced by 5%.Originality/valueThis study assessed repairing metallic structures using the chopped strand mat GFRP. Furthermore, it demonstrated the superiority of rectangular patches over semicircular ones, along with the benefit of using double patches for out-of-plane bending prevention and it emphasizes the detrimental effect of defects in the bonding area between the patch and the cracked component. This underlines the importance of proper surface preparation and bonding techniques for successful repair.Graphical abstract

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Section: Introductionmentioning

confidence: 99%

Experimental and numerical analysis of the behavior of rehabilitated aluminum structures using chopped strand mat GFRP composite patches

Althahban,

Nowier,

El-Sagheer

et al. 2024

FEBE

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“…In order to make the repair more efficient, several authors have worked to analyze numerically the mechanical and failure behavior of the repaired structure and then to optimize the composite and the adhesive by looking for more suitable mechanical properties to absorb, as much as possible, the stresses of the damaged area; others have searched to optimize the geometric shape to reduce more and more stresses at the crack tip. The numerical analysis is an important tool to determine the stress distribution in the different substrates; several authors have proposed simulation methods taking into account mechanical parameters of the adhesive and composite [10][11][12][13][14].…”

Section: Introductionmentioning

confidence: 99%

Analysis of the effect of modifying the thickness of a damaged and repaired plate by composite patch on the J-Integral; effect of bonding defects

Kaddouri¹,

Madani²,

Rezgani

et al. 2020

J Braz. Soc. Mech. Sci. Eng.

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The composite patch bonding technique in the damaged area has demonstrated its effectiveness in reducing stresses at the stress concentration zones and has ensured a long service life of the repaired structure. The search for a suitable adhesive and patch for good load transfer has led researchers to develop, by mechanical tests, analytical or numerical methods, ideas about the shape, nature, stacking sequence type of adhesive for a better combination of patch and adhesive. Our work fits into this context; the aim is to provide a method to reduce the stresses on the plate by protecting the adhesive against the effect of aging, which significantly affects the mechanical properties of the adhesive and the composite patch. Several factors have been highlighted namely, the effect of the composite stacking sequence, modification of the thickness of the plate, the presence of bonding defects in different positions. The analysis of the J-Integral and the stresses in the adhesive and the patch shows clearly that their values depend strongly on these different parameters. However, the modification made to the plate has no effect on the stress concentration.

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“…The analysis of composite patch repair has a long history and initially Rose (1981) developed an analytical solution for SIF in the repaired plate considering stiffness ratio and characteristic crack length. Several investigations are reported with the two-dimensional and three-dimensional models of cracked structure repaired with the composite patch (Wang and Pidaparti, 2002; Salehi-Khojin et al , 2006; Bezzerrouki et al , 2008; Madani et al , 2009; Gu et al , 2011; Albedah et al , 2011; Bouanani et al , 2013; Makwana et al , 2018a). The three-dimensional models capture the bending effect due to an asymmetric patch, which offers accurate results and preferred for the analysis.…”

Section: Introductionmentioning

confidence: 99%

Performance assessment and optimization of hybrid composite patch repair of aircraft structure

Makwana

Shaikh

2020

MMMS

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PurposeIn this article, a novel hybrid composite patch consisting of unidirectional carbon fiber and glass fiber is considered for repair of the aircraft structure. The purpose of this paper is to assess the performance of hybrid composite patch repair of cracked structure and propose an optimized solution to a designer for selection of the appropriate level of a parameter to ensure effective repair solution.Design/methodology/approachElastic properties of the hybrid composites are estimated by micromechanical modeling. Performance of hybrid composite patch repair is evaluated by numerical analysis of stress intensity factor (SIF), shear stress, and peel stress. Design of experiment is used to determine responses for a different combination of design parameters. The second-order mathematical model is suggested for SIF and peel stress. Adequacy of the model is checked by ANOVA and used as a fitness function. Multiobjective optimization is carried out with a genetic algorithm to arrive at the optimal solution.FindingsThe hybrid composite patch has maintained equilibrium between the SIF reduction and rise of the peel stress. The repair efficiency and repair durability can be ensured by selection of an optimum value of volume fraction of glass fiber, applied stress, and adhesive thickness.Originality/valueThe composite patch with varying stiffness is realized by hybridization with different volume fraction of fibers. Analysis and identification of optimum parameter to reduce the SIF and peel stress for hybrid composite patch repair are presented in this article.

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3D Numerical Investigation of Aluminum 2024-T3 Plate Repaired with Asymmetric and Symmetric Composite Patch

Cited by 8 publications

References 18 publications

Experimental and numerical analysis of the behavior of rehabilitated aluminum structures using chopped strand mat GFRP composite patches

Experimental and numerical analysis of the behavior of rehabilitated aluminum structures using chopped strand mat GFRP composite patches

Analysis of the effect of modifying the thickness of a damaged and repaired plate by composite patch on the J-Integral; effect of bonding defects

Performance assessment and optimization of hybrid composite patch repair of aircraft structure

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