Characterization of Fatigue Crack Growth in Bonded Structures. Volume 2. Analysis of Cracked Bonded Structures

Ratwani, M.

doi:10.21236/ada046179

Cited by 18 publications

(8 citation statements)

References 4 publications

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“…Since the three-layer technique models the adhesive as a continuum, an elastic± plastic analysis of the adhesive has been performed, where debond was assumed to initiate when the effective stress reached the yield value. The results (see reference [29] for full details) based on this technique showed that the debond in adhesively bonded repairs is elliptical in shape, which is consistent with the results in references [6], [7], [16] and [39]. An adhesively bonded composite patch is an effective technique to repair economically a cracked aircraft structure and to extend its life expectancy.…”

Section: Resultssupporting

confidence: 82%

“…adhesive crack) for an imperfectly bonded patch is also investigated using the present three-layer technique. An elliptical debond embedded between the plate and the adhesive, which is consistent with experimental observations [6,7,16,39], is considered in the present study. An elliptical debond between the cracked plate and the adhesive is introduced.…”

Section: Resultssupporting

confidence: 74%

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Methodology to analyse aerospace structures repaired with a bonded composite patch

Naboulsi

Mall

1999

The Journal of Strain Analysis for Engineering Design

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Adhesively bonded composite repair of metallic structures is one of the candidate technologies that has enormous potential in the ageing aircraft. A computational tool to analyse the repaired aerospace structure using an adhesively bonded composite patch is presented. This involves the three-layer technique based on the two-dimensional finite element method for adhesively bonded composite patch repair of cracked structures. This technique is capable of characterizing the crack growth and debond growth behaviour, as well as predicting the fatigue life extension of the repaired structure with a perfectly or imperfectly bonded patch. Also, the thermal effects which may develop during bonding or during service and the non-linear material behaviour of the adhesive are incorporated in this technique. The results from the three-layer technique show good agreement with experimental results as well as a previous investigator's published numerical results. Besides the accuracy of the technique, the advantage of the twodimensional three-layer technique is cost-effectiveness when compared with the three-dimensional finite element or performing expensive experiments on various patch configurations for design purposes. An overview of the three-layer technique to investigate a cracked metallic plate repaired with bonded composite patch is presented in this paper.

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Section: Resultssupporting

confidence: 82%

Section: Resultssupporting

confidence: 74%

Methodology to analyse aerospace structures repaired with a bonded composite patch

Naboulsi

Mall

1999

The Journal of Strain Analysis for Engineering Design

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“…Further to this, the single-sided patch repairs under cyclic loading generate a curvilinear crack front that 2D plate FE model lacks ability to exactly represent. Ratwani [1] was the first to address the bending effect in an aluminum patch bonded to a cracked aluminum plate. In his early study, a correction factor for the bending effect was suggested for use with Rose's analytical solution [2].…”

Section: Introductionmentioning

confidence: 99%

Fatigue Behavior of Composite Patch Repaired Aluminum Plate

Lee

2005

Journal of Composite Materials

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Experimental and analytical studies are conducted to characterize the fatigue crack growth behavior of precracked aluminum plates repaired with asymmetric bonded composite patch. For single-sided repairs, due to the asymmetry and the presence of out-of-plane bending, crack front shape would become skewed curvilinear starting from a uniform through crack profile, as observed from previous studies. As the stress intensity factor (SIF) calculated at the crack tip is much influenced by crack front shape, it is necessary to predict and consider the actual crack front shape evolution for the accurate analysis of fatigue behavior. Nevertheless, in most previous studies, crack front has been modeled as a uniform straight one, which may cause inaccuracy. In this study, the actual crack front evolution is predicted and considered in estimating the fatigue life by implementing the successive analysis technique based on the three-dimensional finite element scheme. Experimental tests with various plate thicknesses (2, 4, 6, 8, and 10 mm) are also carried out to verify the present approach. The analytical predictions of both the crack front shape evolution and the fatigue life are in good agreement with the experimental observations. By both experimental and analytical approaches, the characteristics of the fatigue crack growth behavior and the effectiveness of single-sided repairs according to the plate thickness are investigated.

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“…For this, the case of an elliptical debond embedded between the plate and the adhesive is chosen to study debond growth. Elliptical debonds are consistence with experimental observations, [17][18][19][20], In this paper, a 180 x 120 x 2.29 mm aluminum plate, 76 x 38 x 0.762 mm Boron/Epoxy composite patch for single sided patch and 0.127 mm thickness for double sided repair are used. The adhesive thickness is 0.1016 mm .…”

Section: Resultsmentioning

confidence: 92%