Analysis of the adhesive failure in bonded composite repair of aircraft structures using modified damage zone theory

Bouanani, M. Fari; Benyahia, F.; Albedah, A.; Aid, A.; Bouiadjra, B. Bachir; Belhouari, M.; Achour, T.

doi:10.1016/j.matdes.2013.03.017

Cited by 22 publications

(9 citation statements)

References 27 publications

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“…Recently, several papers describing the damage zone theory published. We note the work of [7,8] which work on the effect of the corrosion on the damage of the adhesive (FM73) on the repair efficiency and we noted also that [19] has estimated the adhesive damage and failure in the bonds composite repair of aircraft structures using modified damage zone theory. Benyahia et al and Ramji et al [20,21] analysed four different shapes (rectangular, trapezoidal, circular and elliptical).…”

Section: Introductionmentioning

confidence: 84%

Effect of the angles of the cracks of corroded plate in bonded composite repair

Salem

Berrahou²,

Mechab³

et al. 2018

Frattura Ed Integrità Strutturale

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In this study a three-dimensional finite element method analysis of repairing plate with bonded composite patch subjected to tensile load was presented. The effect of the corrosion on the damage of the adhesive (FM73) in the length of inclined crack is presented. The obtained results show that the increase of (DR) is due to the increase of the inclination of the crack against it leads to the decrease of the values of the stress intensity factor in mode I (K I). KEYWORDS. Composite repair; Corrosion; Damage ratio; Finite element method (FEM); Stress intensity factor in mode I and mode II (KI, KII).

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Section: Introductionmentioning

confidence: 84%

Effect of the angles of the cracks of corroded plate in bonded composite repair

Salem

Berrahou²,

Mechab³

et al. 2018

Frattura Ed Integrità Strutturale

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“…The ability to transfer load is critical in the selection of an adhesive for use in composite repairs. 142 The adhesive selected must have good fatigue life characteristics and withstand the stresses which are likely to be encountered in the repair. The critical areas for the repair are in the bond edges where stress profiles will be largest.…”

Section: Design Of Composite Repairsmentioning

confidence: 99%

Design and ageing of adhesives for structural adhesive bonding – A review

Pethrick

2014

Proceedings of the Institution of Mechanical Engineers, Part L:

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This review outlines some of the issues which have to be addressed when selecting an adhesive for a particular structural adhesive bonding application. The designer may find that a number of adhesives provide the required load bearing properties and the selection may require a more detailed consideration of the processes involved in the fabrication of the joint, the temperature over which it is to work and the environment in which it will have to operate. The article attempts to provide the reader with an insight into the effects of factors such as time and temperature used in the cure process, details of the components in the mixture and the effects of various additives on the physical properties of the adhesives which are created. The performance of an adhesive may vary with time as a consequence of stress-induced changes which are triggered by thermal effects or by hygrothermal factors. The review considers joints created using metal substrates and carbon fibre composites. The performance and durability of an adhesive bond is critically dependent on the stability of the interface between the adhesive and adherend and is sensitive to the pre-treatment processes used in the creation of the bond. The review outlines how broadband dielectric measurements can be used to non-destructively monitor the cure of adhesive bonds and the processes involved in ageing of joint. The dielectric method gives an insight into the fundamental processes which are giving rise to the changes in the mechanical properties of the joint as they age.

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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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Analysis of the adhesive failure in bonded composite repair of aircraft structures using modified damage zone theory

Cited by 22 publications

References 27 publications

Effect of the angles of the cracks of corroded plate in bonded composite repair

Effect of the angles of the cracks of corroded plate in bonded composite repair

Design and ageing of adhesives for structural adhesive bonding – A review

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

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