Stress and Failure Analyses of Adhesive-Bonded Composite Joints Using ASTM D3165 Specimens

Armanios, Erian A.; Bucinell, RB; Wilson, David G.; Yang, Charles; Tomblin, John; Harter, P

doi:10.1520/ctr10563j

Cited by 13 publications

(5 citation statements)

References 13 publications

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“…mode I, mode II, and total strain energy release rates of an initial surface-ply delamination, a, of 1.27 mm under a 1.78 kN tensile load for a C/Ep adherend with Hysol EA 9394 adhesive of bondline thicknesses from 0.127 mm to 3.175 mm are shown in Figs. [17][18][19] show the results with Gl/Ep adherends. The strain energy release rate values for C/Ep and Gl/Ep are plotted vs bondline thickness to depict the purpose of the present analytical model in dealing with thick bondlines.…”

Section: Resultsmentioning

confidence: 97%

“…Yang and Pang [18] derived an analytical model that provided the stress distributions of adhesively bonded single-lap composite joints subjected to axial tension. Huang et al [19] and Yang et al [20] also derived an elastic-plastic model for adhesively bonded single-lap composite joints. Their approaches have included important capabilities such as the asymmetry of the adherend laminates and effects due to transverse shear deformation.…”

Section: Introductionmentioning

confidence: 99%

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Adhesive-Bonded Composite Joints Analysis with Delaminated Surface Ply Using Strain-Energy Release Rate

Chadegani

Yang

Smeltzer

2012

Journal of Aircraft

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This paper presents an analytical model to determine the strain energy release rate due to an interlaminar crack of the surface ply in adhesively bonded composite joints subjected to axial tension. Single-lap shear-joint standard testspecimen geometry with thick bondline is followed for model development. The field equations are formulated by using the first-order shear-deformation theory in laminated plates together with kinematics relations and force equilibrium conditions. The stress distributions for the adherends and adhesive are determined after the appropriate boundary and loading conditions are applied and the equations for the field displacements are solved. The system of second-order differential equations is solved to using the symbolic computation tool Maple 9.52 to provide displacements fields. The equivalent forces at the tip of the prescribed interlaminar crack are obtained based on interlaminar stress distributions. The strain energy release rate of the crack is then determined by using the crack closure method. Finite element analyses using the J integral as well as the crack closure method are performed to verify the developed analytical model. It has been shown that the results using the analytical method correlate well with the results from the finite element analyses. An attempt is made to predict the failure loads of the joints based on limited test data from the literature. The effectiveness of the inclusion of bondline thickness is justified when compared with the results obtained from the previous model in which a thin bondline and uniform adhesive stresses through the bondline thickness are assumed.

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Section: Resultsmentioning

confidence: 97%

Section: Introductionmentioning

confidence: 99%

Adhesive-Bonded Composite Joints Analysis with Delaminated Surface Ply Using Strain-Energy Release Rate

Chadegani

Yang

Smeltzer

2012

Journal of Aircraft

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“…Results stated that, the plasma treated joints all failed when the surface free energy was increased more than 40 mj/m 2 and mechanically treated composites joints strength increased with optimal surface roughness and adhesive thickness. Huang H. et al [16] developed an analytical model for estimating the stress and strain distributions of single-lap adhesive-bonded composite joints under tension. In FRC composite adhesive joints, according to the standard ASTM D5573.…”

Section: Introductionmentioning

confidence: 99%

Failure Studies on Adhesive Bonded and Bolted Joints of Natural Fiber Composites

Atmakuri

Palevičius

Madhusudan

et al. 2021

mech

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Composites with natural fibers as reinforcements are playing a vital role in recent developments. The present work deals with the fabrication of okra and empty fruit bunch banana fiber polyester matrix composites with varying reinforcement content (5%, 10%, and 15%). Composites were fabricated by using the hand layup technique. After the fabrication process, composites were then adhesively bonded and also joined with bolts. The main objective of this work is to analyse the failure studies on adhesive bonded and bolted joints of okra and empty fruit bunch banana composite specimens. The specimens were tested under tensile load, flexural creep studies, and SEM analysis. It has been observed that empty fruit bunch banana fiber composites exhibited better joint strength properties under tensile loading when compared to the okra fiber composites. To estimate the flexural creep behaviour, all the samples were tested at a constant load of 2.5kg and 5kg. The deflections obtained during regular time intervals (four months) were noted. The presence of internal defects and void content was observed by using the scanning electron microscope. The results showed that adhesive-bonded composites were exhibited less deflection compared to the bolted joints. The empty fruit banana fiber composites exhibited higher creep than okra fiber composites. Decreased creep with the increased fiber has been observed in both cases. SEM Adhesively bonded joints possessing better sustainability as compared to the bolted joints in both the fiber-reinforced composites.

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“…9 Other researchers have also investigated different methods to predict the failure loads of SLJs. [10][11][12][13][14][15] Up to now, most investigations have been focusing on the mechanical performance and failure mechanism of SLJs made by materials of similar properties. However, work on SLJs composed of dissimilar materials is quite limited.…”

Section: Introductionmentioning

confidence: 99%

“…9 Other researchers have also investigated different methods to predict the failure loads of SLJs. 10–15…”

Section: Introductionmentioning

confidence: 99%

Damage investigation on the adhesively bonded single-lap joints of three-dimensional braided composite and laminates

Liu

Wei

et al. 2017

Journal of Reinforced Plastics and Composites

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Adhesive bonding is usually used to fabricate composite structures that are hard to manufacture in one piece, however, their lightweight advantage is usually impaired by low failure strength. For high performance composite structures, bonding properties of joints dominate the failure performance and commonly are the primary target of structural optimization. Both experimental and numerical studies of failure behavior of single-lap joints with three-dimensional braided composite laminate adherends are presented in this paper. First, tensile failure tests were performed on braid-laminates single-lap joints bonded with epoxy resin. Compared with the laminates–laminates single-lap joints, the failure load of the braid–laminates single-lap joints increased by 18.4%. Then, the Finite Element Method (FEM) coupled with cohesive zone models (CZM), considering different value of overlap length (L), was used to perform the detail stress distribution of the overlap sections of SLJs. Further, damage initialization and crack growth of single-lap joints are analyzed in detail to fully characterize the failure process, and both experimental and numerical results lead to the same conclusion. Lastly, the effect of three-dimensional braided adherends’ braiding angle on braid-laminates single-lap joints’ performance was investigated, which provides suggestions for the design and optimization for adhesive bonded composite structures.

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Stress and Failure Analyses of Adhesive-Bonded Composite Joints Using ASTM D3165 Specimens

Cited by 13 publications

References 13 publications

Adhesive-Bonded Composite Joints Analysis with Delaminated Surface Ply Using Strain-Energy Release Rate

Adhesive-Bonded Composite Joints Analysis with Delaminated Surface Ply Using Strain-Energy Release Rate

Failure Studies on Adhesive Bonded and Bolted Joints of Natural Fiber Composites

Damage investigation on the adhesively bonded single-lap joints of three-dimensional braided composite and laminates

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