Experimental fatigue crack growth and crack-front shape analysis of asymmetric repaired aluminium panels with glass/epoxy composite patches

Hosseini‐Toudeshky, Hossein; Sadeghi, Gity Mir Mohamad; Daghyani, Hamid Reza

doi:10.1016/j.compstruct.2005.09.032

Cited by 54 publications

(15 citation statements)

References 7 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Adhesively bonded composite patches with reinforcements are more structurally efficient with much less damages on the structure than traditional repairs based on mechanically fasteners with metallic patches. The majority of the previous investigations on fracture analysis of repaired aluminum panels using composite patches were focused on the safety evaluation and life prediction of components under uniaxial loading in mode-I condition (Baker 1999;Lee and Lee 2004;Hosseini-Toudeshky et al 2005, 2007b. However, in the real applications, components are subjected to various forms of loading conditions and the crack growth and failure of them occur due to the conjoiner of such loadings.…”

Section: Introductionmentioning

confidence: 98%

Mixed-mode 3-D crack propagation of repaired thin aluminum panels using single-side composite patches

2008

Self Cite

View full text Add to dashboard Cite

Three dimensional finite element analyses of the single-side repaired panels using glass/epoxy composite are performed considering the general mixed mode conditions and real crack-front shape modeling (RCFM) during the crack propagation procedure. Variations of the fracture parameters through the thickness of the panels for the initial crack configuration and crack growth behavior of the repaired panels with various patch lay-ups are investigated. The effect of considering K III on the small and large crack growth of repaired panels are also studied. The obtained lives are compared with the previously obtained lives using simplified FEM procedure and experimental results by the authors.

show abstract

Section: Introductionmentioning

confidence: 98%

Mixed-mode 3-D crack propagation of repaired thin aluminum panels using single-side composite patches

2008

Self Cite

View full text Add to dashboard Cite

show abstract

“…[1][2][3] Thus, adhesively bonded composite patch repairs to notched metallic substrate structure have received increasingly attention, and static and fatigue strengths of repaired metallic panels with the thin (less than 12.7 mm) and thick (more than 12.7 mm) thickness have been widely investigated. 4 Generally, thin panels were analyzed by using 2-D models, [5][6][7][8][9][10][11][12][13] whereas thick panels were done as a 3-D problem. [14][15][16][17][18][19][20][21][22][23][24] With thin panels, Naboulsi and Mall 5 proposed a 2-D model for the analysis of adhesive layer, composite patch and thin notched substrate panel.…”

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

View full text Add to dashboard Cite

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.

show abstract

“…Hosseini-Toudeshky et al [3][4][5][6][7] performed 3-D finite elements fatigue crack growth analysis of single-side repaired aluminium panels to predict the crack trajectory, actual crack-front shape and crack growth life for various panels with cracks in mode-I and mixed mode conditions. They also performed experimental analyses of repaired panels using different composite patches under various fracture mode conditions to investigate the accuracy of the developed numerical methods and to obtain the realistic crack-front [3,[8][9][10]. Their experiments showed that debonding or delaminated patch area may also affect the crack propagation phenomena, Fig.…”

mentioning

confidence: 98%

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

2011

View full text Add to dashboard Cite

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.

show abstract

Experimental fatigue crack growth and crack-front shape analysis of asymmetric repaired aluminium panels with glass/epoxy composite patches

Cited by 54 publications

References 7 publications

Mixed-mode 3-D crack propagation of repaired thin aluminum panels using single-side composite patches

Mixed-mode 3-D crack propagation of repaired thin aluminum panels using single-side composite patches

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

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

Contact Info

Product

Resources

About