Design of multiple-row bolted composite joints under general in-plane loading

Eriksson, Ingvar; Bäcklund, Jan; Möller, Peter

doi:10.1016/0961-9526(95)00044-n

Cited by 32 publications

(7 citation statements)

References 20 publications

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“…Especially, most of the mechanical joints encountered in aircraft structures have multiple fasteners. Therefore, a lot of studies [10,14,15,20,21,25] have been focused on the analysis of multiple fasteners. However, based on the geometry of the parts being fastened sometimes a single row or column may also be used.…”

Section: Introductionmentioning

confidence: 99%

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Failure loads of mechanical fastened pinned and bolted composite joints with two serial holes

Özen

Sayman

2011

Composites Part B: Engineering

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Section: Introductionmentioning

confidence: 99%

“…This kind of failure cannot be avoided by any modification of the structure, because it is progressive and related to compressive failure [6,7]. Various numerical methods have been proposed in the literature to determine the fastener forces in mechanically bolted joints, including the finite element method [8][9][10].…”

Section: Introductionmentioning

confidence: 99%

Failure loads of mechanical fastened pinned and bolted composite joints with two serial holes

Özen

Sayman

2011

Composites Part B: Engineering

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“…For the OHT problem, the mesh size effect is minimized by setting the characteristic length (CL) proposed by Whitney and Nuismer 71 equal to the radial distance of the point from the hole boundary; e.g. see Chang et al, 72 Ramkumar et al, 73 Ramkumar et al, 74 Eriksson et al, 75 Whitworth et al, 76 Camanho and Lambert. 77 This did not completely eliminate the dependence of the numerical solution upon the mesh density.…”

Section: Progressive Damage Modelmentioning

confidence: 99%

Micromechanical progressive damage analysis of inter- and intra-layer failures in fiber-reinforced composite laminates

Zhao

Jiang

Huang

et al. 2020

Journal of Composite Materials

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We analyze progressive damage and failure of composite laminates by using a micromechanical bridging model and compare numerical and experimental results for three fracture problems, namely, the four-point bending, the simple tension, and the simple tension of a laminate with an open hole at its centroid. These problems involve fiber–matrix interface debonding, constituents’ damage, interlayer delamination, and localized damage due to stress concentration. Macroscopic constitutive equations of unidirectional lamina, derived from those of the fiber and the matrix by using the bridging model with the fiber material assumed to be linearly elastic and the matrix to be elasto-plastic obeying the Drucker–Prager yield criterion, are employed. Strains in each constituent of the composite are assumed to be infinitesimal for the additive decomposition of strains into elastic and plastic parts to be valid, and the incremental plasticity theory is used. Stresses in the two constituents are found from their values in the homogenized material by using a dehomogenization technique. The intra-layer damage is assumed to initiate at a material point when the failure criterion for either the fiber or the matrix is satisfied. Young’s modulus of a constituent is degraded by following a Weibull distribution. A finite element is deleted when an energy-based failure criterion is satisfied in it, and the analysis is continued till the structure fails. The delamination between adjacent plies is simulated by including a thin resin layer at the interface and studying failure initiation and propagation in it. The computed reaction force versus the displacement curves and the failure patterns in the three problems are found to agree with the corresponding experimental data.

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“…Therefore, determination of the ratio of loading proportion for each element becomes an important problem in the optimal design of multi-fastened joints. However, because it is a statically indeterminate mechanical problem, most of the previous studies have focused on the use of finite element analysis [7][8][9][10][11][12][13][14].…”

Section: Introductionmentioning

confidence: 99%

Bearing Deformation Behavior of Carbon/Bismaleimide Composites Containing One and Two Bolted Joints

Xiao¹

2003

Journal of Reinforced Plastics and Composites

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This paper presents an experimental investigation of the behavior in mechanically fastened composite structures. The experimental work will be presented in two parts: one fastened joint and two fastened joints. For the problem of one fastened joint, the bearing strength and failure process for a double lap bolted joint were characterized. During static tensile testing, the load-displacement response and acoustic emission (AE) were monitored and measured in order to understand the fracture process in joined specimens. Several specimens were unloaded at different loading levels and the damage behavior was observed using soft X-rays and Scanning Electron Microscope (SEM) to assess the damage progress, failure mechanisms, and the relationship with bearing strength. Finally, the ratio of loading proportion was determined by examining the problem of two fastened joints.

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Design of multiple-row bolted composite joints under general in-plane loading

Cited by 32 publications

References 20 publications

Failure loads of mechanical fastened pinned and bolted composite joints with two serial holes

Failure loads of mechanical fastened pinned and bolted composite joints with two serial holes

Micromechanical progressive damage analysis of inter- and intra-layer failures in fiber-reinforced composite laminates

Bearing Deformation Behavior of Carbon/Bismaleimide Composites Containing One and Two Bolted Joints

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