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

Kaddouri, Nadia; Madani, K.; Rezgani, L.; Mokhtari, Mohamed; Feaugas, X.

doi:10.1007/s40430-020-02515-y

Cited by 11 publications

(3 citation statements)

References 24 publications

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“…[10] Compared the limit load solutions with finite element method FEM results, for thick cracked pipelines with circumferential cracks under combined loadings internal pressure and axial tension. The limit load analysis for plates with semi-elliptical crack has been used by Dilistrom et al [11] by finite element calculations and limit load results for plates with rectangular cracks embedded in the net collapse section have been obtained by Lei et al [12]. The development of finite element methods and calculation tools has stimulated limit load analysis for structures.…”

Section: Concept Of Plastic Limit Load Analysis (Pll)mentioning

confidence: 99%

Failure behavior of a notched plate repaired by a hybrid repair technique (Stop hole bonded composite

Belhamiani

Djebbar

Oudad

et al. 2023

Preprint

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Generally, bonded repairs are only approved if the primary aircraft structure is cracked and the residual strength significantly exceeds the design limit charge before the bonded repair can be applied.. In order to improve the maintenance effect of the stop hole approach for cracks, a solution of using both techniques (stop hole / bonded composite repairs) are proposed and investigated by finite element analysis. This work presents a study on the effectiveness of the hybrid repair technique in notched panels using both stop drilling hole and bonded composite repair techniques. Several parameters are taken into account: the diameter of the size of hole drilling, the width and the thickness of the composite patch and other parameters are modeled with a elastoplastic behavior of the plate using Abaqus software. A limit-load analysis determines a lower bound to the limit charge of a component and provides an alternative way to estimate plastic collapse for the limit loads. In addition, the limit load analysis had helped to provide an evaluation of the behaviors of structures or components for other failures. The plastic limit load (PLL) was evaluated by a convergent load increment in a wellconfigured finite element analysis with a load of a sufficiently small increment for an elastic-perfectly plastic behavior of the structure. The allowable limit stress on the aircraft is calculated by applying design factors to the plastic limit load (PLL) so that the onset of plastic collapse does not occur. The results proved that the hybrid repair provided the largest percentage in terms of maintenance and the smallest values for the notch stress intensity factor (NSIF) and von Mises stress for most of the hybrid configuration compared to the single repair technique.

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Section: Concept Of Plastic Limit Load Analysis (Pll)mentioning

confidence: 99%

Failure behavior of a notched plate repaired by a hybrid repair technique (Stop hole bonded composite

Belhamiani

Djebbar

Oudad

et al. 2023

Preprint

View full text Add to dashboard Cite

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“…Because the cost of replacing parts directly is too high, it is a good choice to repair damaged parts [6][7][8][9][10][11][12]. Many researches have been done on the repair of composite materials in the world: Kaddouri et al [13] 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. Moreira et al [14] address the fracture characterization of scarf adhesive repairs on carbon epoxy composites under high-cycle fatigue loading.…”

Section: Introductionmentioning

confidence: 99%

Strain monitoring using carbon nanotube Buckypaper sensor on composite repaired structure

Wang

Zhang

et al. 2021

Appl. Phys. A

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Repair of composite materials is an important cost savings for the aviation industry, and it is also very important to monitor the repaired structure. In this paper, a novel micro-nano sensor which is combined with Flexible Printed Circuit and Buckypaper (BP) sensor is introduced, and has the characteristics of multidirectional, real time and high sensitivity. These sensors are used to monitor the strain at different positions on the composite repair structure. The piezoresistive response of BP sensor is obtained and the main working mechanism of BP sensor is explained. Experiments show that this sensor can preliminarily judge the damage position and degree of the repaired structure, and monitor whether it reaches the strength limit. And it can judge the loading history of the structure. This ensures the safety of the repaired structure in the process of continuous service to a certain extent.

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“…The evaluation of the stress intensity factor (SIF) or the J-integral, and the different stresses in the substrates, adhesive, or respective interfaces, makes it possible to estimate the effectiveness and the durability of the repair [8]. Most of the studies undertaken in this eld are focused on the composite repair of cracked panels under the in uence of mode I loading [11] [12]. However, in practical applications, the components of cracked panels are subjected to mixed-mode loading, and pure-mode I analysis has limited practical interest [13] [14].…”

mentioning

confidence: 99%

Analysis of the performance of carbon fiber patches on improving the failure strength of a damaged and repaired plate

Sebaibi,

Mhamdia,

Kaddouri

et al. 2023

Preprint

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Since the implementation of the composite patch bonding repair technique, this process has gradually replaced the traditional methods of bolting or welding. The correct choice of fiber type for the composite patch ensures better repair durability. Carbon fiber composites, which are preferred for the most advanced aeronautical and industrial applications, have shown great effectiveness in reducing stresses at the damaged area. They are chosen for their high strength, low weight, and high stiffness, compared to other fibers. This work consists of a finite element method to evaluate the performance of carbon fiber composite patches (high-modulus fiber and high-strength fiber) for load transfer and thus stress concentration reduction at the damaged area. The composite patches are bonded by the Adekit A-140 adhesive to repair an aluminum 2024-T3 plate. The geometric models for the study are a plate with a lateral crack and another plate with a crack emanating from a notch. The aim is to highlight the advantage of using high-modulus (HM) or high-strength (HS) carbon fibers to repair a plate with a variable stress concentration damaged area, and to assess the performance of different composites for variable crack lengths. The effects of crack size, the presence of a notch, the applied stress, and the use of a hybrid composite (combination of HM fibers and HS fibers) have been demonstrated.

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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

Cited by 11 publications

References 24 publications

Failure behavior of a notched plate repaired by a hybrid repair technique (Stop hole bonded composite

Failure behavior of a notched plate repaired by a hybrid repair technique (Stop hole bonded composite

Strain monitoring using carbon nanotube Buckypaper sensor on composite repaired structure

Analysis of the performance of carbon fiber patches on improving the failure strength of a damaged and repaired plate

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