A study of fastener pull-through failure of composite laminates. Part 1: Experimental

Banbury, A.; Kelly, Douglas J.

doi:10.1016/s0263-8223(99)00009-4

Cited by 39 publications

(9 citation statements)

References 11 publications

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“…As being reported in the literature [10,11], the specimen being pushed-through right past the first load drop, exhibited a single profound inter-laminar delamination crack at about the middle thickness of the plate, similar to the one shown in figure 8a.…”

Section: Push-through Testingsupporting

confidence: 77%

“… The damage modes experienced via sectioning and optical-microscopy resembled the ones reported in the literature [10,11].…”

Section: Modification To the Existing Pull-through Testing Proceduressupporting

confidence: 70%

“…Bending and shear failure modes can occur simultaneously depending on the specimen design, material property parameters and the loading level. The bigger the load, damage becomes widespread consisting of shear and tension failures, intra and inter-laminar interactions are bridging [10,11]. Similarly, various numerical investigations [12,13] have provided with further insights to the failure locations and failure modes in the pull-through loading scenario, partially reinforcing the above mentioned experimental results.…”

Section: Bolt Pull-through Testing Procedures and Research Findingsmentioning

confidence: 61%

“…Initial/subcritical failures and final failure of the joint can be evidenced on the load-displacement curve via minor/major drops in the load or variations in the curve tangency exceeding prescribed amounts of load differences and/or stiffness drops. Research in the public domain [10,11] has presented, for some material systems, the correlation between the microscopic material behavior of the fibrous composite laminates in the plate with the various significant failure events on the load-displacement graph. A good understanding of the microscopic failure mechanisms has been generated which in broad terms has many similarities to the damage caused by low velocity impact events on FRP laminated plates [7]; relative thin laminates experience failure related to bending deformation while for relative thicker ones, shear damage is a more profound failure mode.…”

Section: Bolt Pull-through Testing Procedures and Research Findingsmentioning

confidence: 99%

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Damage tolerance of CFRP airframe bolted joints in bearing, following bolt pull-through failure

Giannopoulos

Grafton

Guo

et al. 2020

Composites Part B: Engineering

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The experimental study presented herein, investigated the residual strength of bolted joints on Carbon Fiber Reinforced Polymer (CFRP) airframe structures within the context of structural damage tolerance and airworthiness regulations. The damage scenario assumed, subjected a series of bolted joint CFRP laminate specimens to quasistatic bearing loading following bolt pull-through failure events of different magnitude. Representative CFRP laminate specimens manufactured from AS7/8552 carbon fiber/epoxy matrix system were artificially damaged under bolt pull-through loading, following the herein proposed modifications to the current pull-through ASTM testing procedure. The specimens were subsequently tested in static bearing loading for examining the specimen residual bearing strength. The residual joint bearing strength was related to the displacement travelled passed the initial failure stage in pull-through mode and was measured up to a maximum of a 13% decrease for the tested samples and the maximum damage imposed. The study explored of safe utilization of bolted joints at higher operating loading levels within the context of the current airworthiness regulations. The inherent damage arrest features of the joints were highlighted. The study concluded with comments and suggestions on the expansion of the current utilization spectrum of damaged bolted joints from pull-through loading in airframe design, bound by the current airworthiness certification requirements.

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Section: Push-through Testingsupporting

confidence: 77%

“… The damage modes experienced via sectioning and optical-microscopy resembled the ones reported in the literature [10,11].…”

Section: Modification To the Existing Pull-through Testing Proceduressupporting

confidence: 70%

Section: Bolt Pull-through Testing Procedures and Research Findingsmentioning

confidence: 61%

Section: Bolt Pull-through Testing Procedures and Research Findingsmentioning

confidence: 99%

See 2 more Smart Citations

Damage tolerance of CFRP airframe bolted joints in bearing, following bolt pull-through failure

Giannopoulos

Grafton

Guo

et al. 2020

Composites Part B: Engineering

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“…This paper will numerically study pull-through failure of countersunk fastened joints in composite laminates, with a specific focus on high-rate dynamic failure. The failure mechanisms have been experimentally investigated by several authors both quasistatically [1,[10][11][12][13][14] and dynamically [3,4,6,7].…”

Section: Summary Of Experimental Resultsmentioning

confidence: 99%

A study of dynamic pull-through failure of composite bolted joints using the stacked-shell finite element approach

Pearce¹,

Johnson²,

Hellier³

et al. 2014

Composite Structures

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Pull-through failure of bolted joints in composites is due to the relatively low through-thickness properties of laminated materials. Recently it has been identified that pull-through failure also plays an important role in the ultimate bearing load and total energy absorption of bolted joints, especially under dynamic conditions. AbstractPull-through failure of bolted joints in composites is due to the relatively low through-thickness properties of laminated materials.Recently it has been identified that pull-through failure also plays an important role in the ultimate bearing load and total energy absorption of bolted joints, especially under dynamic conditions. It has been previously found that bolted joints loaded in bearing exhibit rate sensitivity whereas bolts loaded in pull-through experience very little sensitivity, for nearly identical joint configurations. The primary focus of this paper was to use explicit finite element simulation of pull-through failure to shed light on discrepancies between experimentally observed rate sensitivity for seemingly similar tests. The paper uses the stacked-shell modelling approach to efficiently model the interaction of delamination and ply failure under the complex dynamic load state.The results of the simulation indicated that the properties of the interface susceptible to loading rate sensitivity, Mode I and II strain energy release rates (SERR), did not have a great effect on the overall joint response; despite the prevalence of delamination during the failure process. A weak relationship between Mode II SERR and joint response was discovered which was consistent with experimental observations.

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References

2017

Handbook of Structural Life Assessment

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A study of fastener pull-through failure of composite laminates. Part 1: Experimental

Cited by 39 publications

References 11 publications

Damage tolerance of CFRP airframe bolted joints in bearing, following bolt pull-through failure

Damage tolerance of CFRP airframe bolted joints in bearing, following bolt pull-through failure

A study of dynamic pull-through failure of composite bolted joints using the stacked-shell finite element approach

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