Stress Distribution in Bonded Joints *

Ratwani, M.

doi:10.1177/002199837100500308

Cited by 165 publications

(42 citation statements)

References 1 publication

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“…The adhesive layer is treated as a shear spring rather than as an elastic continuum. This method of treating adhesives has been used before in the analysis of bonded joints and cracked, adhesively bonded structures (References [1][2][3][4]6). In the finite element analysis, the continuous shear spring is represented by shear elements (Reference 1).…”

Section: Finite Element Methods Of Analysismentioning

confidence: 99%

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

Ratwani¹

1977

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Section: Finite Element Methods Of Analysismentioning

confidence: 99%

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

Ratwani¹

1977

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“…The adhesive along with each ply in the laminate was divided into multiple steps and one layer of solid element was used for every step. The first problem involves the linear analysis of a two-dimensional scarf joint previously considered by [Erdogan and Ratwani 1971]. The scarf joint is subjected to in-plane stress, and its geometry is shown in Figure 7.…”

Section: Resultsmentioning

confidence: 99%

“…Analytical and numerical methods have been used in the past to examine scarf joints [Hart-Smith 1973;Erdogan and Ratwani 1971]. These methods are two dimensional in nature and the scarf repair is analyzed based on a representative scarf joint.…”

Section: Introductionmentioning

confidence: 99%

Three-dimensional nonlinear analyses of scarf repair in composite laminates and sandwich panels

Das

Madenci

Ambur

2008

JOMMS

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A special-purpose analysis tool based on the finite element method is presented for parametric design studies of composite laminates and sandwich panels with scarf repairs. This design tool provides the complete three-dimensional stress and strain fields in scarf-repaired panels without any requirements on the nature of the lamination and the type of loading. The adherends are modeled using a plate element based on a higher-order single-layer theory, and the adhesive is modeled using a solid element. The higher-order nature of the plate theory makes it suitable for analyzing thick laminates and sandwich panels comprised of numerous plies. The model takes into account geometric nonlinearity in the adherends and assumes a bilinear stress-strain relationship for the adhesive. The responses of composite laminates with single-and double-sided repairs and sandwich panels with both full and partial repairs of the top face sheets are investigated.

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“…First, there is only a small area of the adhesive layer near the joint that can effectively transfer the load by shear. In the longer part of the joint, the adhesive layer transfers less load (Endogan and Ratwani, 1971). This situation makes a patch layer behave like a staple, which pulls the crack sides together.…”

Section: Patch Length Effect On the Sif Valuesmentioning

confidence: 99%

Bonded composite repair structures multiple site damage analysis

Chen

Tran

Volinsky

2013

Aircraft Engineering and Aerospace Technology

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Purpose -The purpose of this work is to describe the effects of the length of cracks and the patch size on the stress intensity factors in a bonded composite repair structure containing multiple site damage. Design/methodology/approach -Finite element method was applied to simulate a bonded repair of a cracked aluminum plate with multiple site damage. A two-dimensional three-layer technique was utilized to model damage in a typical aluminum plate with collinear twin cracks. Findings -This research has found that the stress intensity factors of collinear twin cracks can be reduced significantly through bonded composite repair, and their values strongly depend on the relative position of the cracks. Moreover, the composite patch should be 1.5 to two times longer than the crack length and the patch thickness should be 30-40 percent of the plate thickness for the best repair performance. Research limitations/implications -Patch debonding can significantly reduce the repair efficiency and should be avoided if possible. Originality/value -It is seen that, instead of the three-dimensional finite element model, which is computationally intense, the two-dimensional three-layer finite element model has an adequate accuracy to obtain stress intensity factors in a bonded composite repair structure with multiple site damage.

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Stress Distribution in Bonded Joints *

Cited by 165 publications

References 1 publication

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

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

Three-dimensional nonlinear analyses of scarf repair in composite laminates and sandwich panels

Bonded composite repair structures multiple site damage analysis

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