Fatigue Debonding Analysis of Repaired Aluminium Panels by Composite Patch using Interface Elements

Abstract

Repaired panels with composite patches subjected to fatigue loading may fail due to the progressive debonding between the composite patch and aluminium panel. The objective of this paper is to study the initiation and propagation of a possible fatigue debonding in the adhesive layer while the crack also growths in the panel for single-side repaired aluminium panels. For this purpose three dimensional finite elements method with a thin layer solid like interface element is employed. Fracture mechanics approach is used for the analysis of crack growth in aluminium panel and the interface elements with fatigue constitutive law for mixed mode debonding growth in the adhesive layer. A user element routine and a damage model material routine were developed to include the interface element and to simulate the initiation and propagation of damage in adhesive layer under cyclic loading. It is shown that, the debonding propagation and crack growth rate of the repaired panels depend on the composite patch material and interface bonding properties significantly. It is also shown that using of patch material with higher elastic module leads to the faster damage or debonding growth in the adhesive layer during the fatigue loading.

The effects of thermal residual stresses and interfacial properties on the transverse behaviors of fiber composites with different microstructures

“…Many attempts have been made in the past to investigate the effect of the interfacial properties on the transverse behavior of the composites [10][11][12][13]. Experimental studies have shown that the dominant damage mechanism involved in the transverse ply cracking of composites is the debonding occurring at the fiber-matrix interface [14].…”

Towards hybridization of composite patch in repair of cracked Aluminum panel

“…The comparative performance of metallic patches with respect to the composite patches is examined for selecting the right patch material (Bouiadjra et al, 2015). Also, numerous works are reported in examining the efficiency of composite patch repair for 868 IJSI 10,6 fatigue life extension under different loading condition (Kalestan et al2014;Seo and Lee, 2002;Liu et al, 2017;Hosseini-Toudeshky et al, 2011). The effect of aging and hygrothermal environment on the composite patch repair is also investigated in several studies (Bouiadjra et al, 2015;Gkikas et al, 2013;Rezgani et al, 2018).…”

Low‐cycle fatigue delamination initiation and propagation in fibre metal laminates

“…27 Furthermore, cohesive zone modelling was employed in Ref. Hosseini-Toudeshky et al 29 also proposed a CZM finite element model to simulate the progressive debonding between composite patch and cracked aluminium panels concurrent with the crack growth in the base panel under high-cycle fatigue loading. Hosseini-Toudeshky et al 29 also proposed a CZM finite element model to simulate the progressive debonding between composite patch and cracked aluminium panels concurrent with the crack growth in the base panel under high-cycle fatigue loading.…”

“…[28] to study the effects of delamination size and stacking sequence of laminates on delamination growth under quasi-static compression loading. Hosseini-Toudeshky et al 29 also proposed a CZM finite element model to simulate the progressive debonding between composite patch and cracked aluminium panels concurrent with the crack growth in the base panel under high-cycle fatigue loading. Hosseini-Toudeshky et al 30 also developed de-cohesive law to simulate delamination growth of post-buckled laminate under high-cycle fatigue loading.…”