Mode I fracture of epoxy bonded composite joints 2. Fatigue loading

Ashcroft, IA; Shaw, Stephen J.

doi:10.1016/s0143-7496(01)00050-1

Cited by 105 publications

(45 citation statements)

References 37 publications

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“…Ashcroft and Shaw. [132] also found higher growth at low temperature, suggesting that the effect of temperature may be strongly dependant on the matrix or adhesive material.…”

Section: Effect Of Environmental and Testing Conditionsmentioning

confidence: 95%

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Methods for the prediction of fatigue delamination growth in composites and adhesive bonds – A critical review

Pascoe

Alderliesten

Benedictus

2013

Engineering Fracture Mechanics

215

144

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An overview is given of the development of methods for the prediction of fatigue driven delamination growth over the past 40 years. Four categories of methods are identified: stress/strain-based models, fracture mechanics based models, cohesive-zone models, and models using the extended finite element method. It is highlighted that most models are phenomenological, based on the observed macro-scale behaviour of test specimens. It is suggested that a more physics based approach, focusing on elucidating the mechanisms involved, is needed to come to a full understanding of the problem of delamination growth.

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“…Ashcroft and Shaw. [132] also found higher growth at low temperature, suggesting that the effect of temperature may be strongly dependant on the matrix or adhesive material.…”

Section: Effect Of Environmental and Testing Conditionsmentioning

confidence: 95%

“…Burianek and Spearing [129] and Rans et al [130] studied the effect of temperature on delamination of FMLs. Ashcroft, Shaw and co-workers [131,132] investigated adhesively bonded composites.…”

Section: Effect Of Environmental and Testing Conditionsmentioning

confidence: 99%

Methods for the prediction of fatigue delamination growth in composites and adhesive bonds – A critical review

Pascoe

Alderliesten

Benedictus

2013

Engineering Fracture Mechanics

215

144

View full text Add to dashboard Cite

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“…This type of trend was observed in Xu, Crocombe, and Smith (1995) for an LSJ in three-point bending in which a lower FCG was found under a mixed mode of loading than in a pure mode I. On the other hand, comparison of the G th value at various temperatures was presented in Ashcroft and Shaw (2002), dealing with different joint configurations: DCB, LSJ and DLJ. It was observed that for all temperatures measured (À50 C, 22 C and 90 C), the variation of G th followed the relation (G th ) DLJ < (G th ) DCB < (G th ) LSJ, being almost constant for the temperature range used except for low temperatures in DLJ.…”

Section: Effect Of Mode MIXmentioning

confidence: 69%

Dynamic fractures of adhesively bonded carbon fibre-reinforced polymeric joints

Casas-Rodríguez¹,

Ashcroft

Silberschmidt

2015

Structural Integrity and Durability of Advanced Composites

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“…The most common approach in this case is based on fracture mechanics, e.g. Dessureautt and Spelt (1997), Curley et al (2000), Ashcroft and Shaw (2002), Abdel Wahab et al (2002), Nicoletto (2004, 2006), and Pirondi and Moroni (2009). In this approach, a version of Paris' law…”

Section: Introductionmentioning

confidence: 99%

High cycle fatigue crack growth in Mode I of adhesive layers: modelling, simulation and experiments

et al. 2014

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The capability to predict high cycle fatigue properties of adhesive joints is important for costefficient and rapid product development in the modern automotive industry. Here, the adaptability of adhesives facilitates green technology through the widening of options of choosing and joining optimal materials. In the present paper a continuum damage mechanics model is developed based on the adhesive layer theory. In this theory, through-thickness averaged variables for the adhesive layer are used to characterise the deformation, damage and local loading on the adhesive layer. In FE-simulations, cohesive elements can thereby be used to model the adhesive layer. This simplifies simulations of large scale complex built-up structures. The model is adapted to experimental results for two very different adhesive systems; one relatively stiff rubber based adhesive and one soft polyurethane based adhesive. The model is able to reproduce the experimental results with good accuracy except for the early stage of crack propagation when the loads are relatively large. The model also predicts a threshold value for fatigue crack growth below which no crack growth occurs. The properties of the model are also compared with the properties of Paris' law. The relations between the parameters of the continuum damage mechanics law and the parameters of Paris' law are used to adapt the new law. It also shows that the properties of a joined structure influence the Paris' law properties of A. Eklind (B) · T. Walander · T. Carlberger · U. Stigh the adhesive layer. Thus, the Paris' law properties of an adhesive layer are not expected to be transferable to joints with adherends having different mechanical properties.Keywords Mode I · Fatigue · Adhesive · DCB · Simulation · Damage law · Threshold List of symbols a Crack length (m) a 0 Initial crack length (m) B Out-of-plane width of DCB-specimen (m) C Compliance (m/N) C P Constant in Paris' law (m n+1 /N n ) D Damage (−) E Young's modulus of the adherends (N/m 2 ) E a Young's modulus of the adhesive (N/m 2 ) F Force applied to DCB-specimen (N) h Thickness of adhesive layer (m) J Energy release rate (J/m 2 ) J c Fracture energy (J/m 2 ) J cycle Measure of energy release rate during a load cycle (J/m 2 ) J f Final value of J cycle in an experiment (J/m 2 ) J th Threshold value of J cycle (J/m 2 ) K n Elastic stiffness of adhesive layer (N/m 3 ) L Length of adherend (m) n Exponent in Paris' law (−) 123 126 A. Eklind et al. M Bending moment applied to DCB-specimen (Nm) N Load cycle (cycle) p Constant in Berry's law (1/Nm q−1 ) q Exponent in Berry's law (−) R ε Load ratio (−) S Integration path (m) T Traction vector (N/m 2 ) u Displacement vector (m) U Strain energy density (J/m 3 ) w Separation of adherends along the adhesive layer (m) w t w at the start of the adhesive layer (m) Δ Separation of loading points of DCBspecimen (m) v a Poisson's ratio of the adhesive (−) α Damage growth proportionality parameter (1/cycle) β Damage growth exponent (−) σ (w) Cohesive law of adhesive (N/m 2 ) σ 0 Norma...

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Mode I fracture of epoxy bonded composite joints 2. Fatigue loading

Cited by 105 publications

References 37 publications

Methods for the prediction of fatigue delamination growth in composites and adhesive bonds – A critical review

Methods for the prediction of fatigue delamination growth in composites and adhesive bonds – A critical review

Dynamic fractures of adhesively bonded carbon fibre-reinforced polymeric joints

High cycle fatigue crack growth in Mode I of adhesive layers: modelling, simulation and experiments

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