A numerical and experimental investigation of delamination behaviour in the DCB specimen

Schön, Joakim; Nyman, Tonny; Blom, A.F.; Ansell, Hans

doi:10.1016/s0266-3538(99)00113-x

Cited by 80 publications

(30 citation statements)

References 18 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…This belief is erroneous. Indeed, the importance of working to the correct fatigue threshold, for a given set of stresses and initial flaws, was first highlighted by Schoen et al [ 10], who stated: Further details on this delamination test are given in [11]. Consequently, a focus of the present paper is on proposing a means for determining the fatigue threshold values via a fracture-mechanics approach and using the Hartman-Schijve variant of the Nasgro equation.…”

Section: Discussion Of the Above Statementsmentioning

confidence: 99%

Delamination growth in polymer-matrix fibre composites and the use of fracture mechanics data for material characterisation and life prediction

Jones

Kinloch

Michopoulos

et al. 2017

Composite Structures

View full text Add to dashboard Cite

The growth of delaminations in polymer-matrix fibre composites under cyclic-fatigue loading in operational aircraft structures has always been a very important factor which has the potential to significantly affect the service-life of such structures. The recent introduction by the Federal Aviation Administration (FAA) of a 'slow growth' approach to the certification of composites has further focused attention on the experimental data and the analytical tools needed to assess the growth of delaminations under fatigue loads. Specific attention is given to the test and data-reduction procedures required to determine a 'valid' rate of fatigue crack growth (FCG), da/dN, versus the range of the energy release-rate, ΔG, (or the maximum energy release-rate, G max , in a cycle) relationship (a) to characterise and compare different types of composites, and (b) for designing and lifing in-service composite structures. Now, fibre-bridging may occur behind the tip of the advancing delamination and may cause very significant retardation of the FCG rate. Such retardation effects cannot usually be avoided when using the Mode I double-cantilever beam test to ascertain experimentally the fatigue behaviour of composites, so that a means of estimating a valid (i.e. ideally a 'retardation-free' or, at least, a very low-retardation) relationship is needed. The present paper presents a novel methodology, that is based on a variant of the Hartman-Schijve equation, to ascertain a valid, 'retardation-free', upper-bound FCG rate curves.

show abstract

Section: Discussion Of the Above Statementsmentioning

confidence: 99%

Delamination growth in polymer-matrix fibre composites and the use of fracture mechanics data for material characterisation and life prediction

Jones

Kinloch

Michopoulos

et al. 2017

Composite Structures

View full text Add to dashboard Cite

show abstract

“…The material properties of 7075-T6 and IM7-8552 [26] and [27], are shown in Figure 5 and Table 2 respectively. The Fickian diffusion -8 -parameters of the composite are shown in Table 3 [6].…”

Section: Experimental Methodology and Materials Characterisationmentioning

confidence: 99%

Continuum damage modelling of environmental degradation in joints bonded with EA9321 epoxy adhesive

Hua

Crocombe

Wahab

et al. 2008

International Journal of Adhesion and Adhesives

View full text Add to dashboard Cite

“…The CTE used for the aluminium alloy was 2.36 × 10 −5 /K. The material properties for the uni-directional composite (cfrp) are taken from the work of Schön et al (2000) and are summarised in Table 2. The thermal properties for the cfrp used in the analyses were 0.06 and 2.86 × 10 −5 /K perpendicular and transverse to the fibres, respectively (Krueger et al 2001).…”

Section: Substratesmentioning

confidence: 99%

Damage modelling of adhesively bonded joints

et al. 2006

View full text Add to dashboard Cite

A cohesive zone model (CZM) has been used in conjunction with both elastic and elastoplastic continuum behaviour to predict the response of a mixed mode flexure and three different lap shear joints, all manufactured with the same adhesive. It was found that, for a specific dissipated CZM energy (Gamma(0)) there was a range of CZM tripping tractions (sigma(u)) that gave a fairly constant failure load. A value of sigma(u) below this range gave rise to global damage throughout the bonded region before any crack propagation initiated. A value above this range gave rise to a discontinuous process zone, which resulted in failure loads that were strongly dependent on sigma(u). A discontinuous process zone gives rise to mesh dependent results. The CZM parameters used in the predictions were determined from the experimental fracture mechanics specimen test data. When damage initiated, a deviation from the linear load-displacement curve was observed. The value for sigma(u) was determined by identifying the magnitude that gave rise to the experimentally observed deviation. The CZM energy (Gamma(0)) was then obtained by correlating the simulated load-crack length response with corresponding experimental data. The R-curve behaviour seen with increasing crack length was successfully simulated when adhesive plasticity was included in the constitutive model of the adhesive layer. This was also seen to enhance the prediction of the lap shear specimens. Excellent correlation was found between the experimental and predicted joint strengths

show abstract

A numerical and experimental investigation of delamination behaviour in the DCB specimen

Cited by 80 publications

References 18 publications

Delamination growth in polymer-matrix fibre composites and the use of fracture mechanics data for material characterisation and life prediction

Delamination growth in polymer-matrix fibre composites and the use of fracture mechanics data for material characterisation and life prediction

Continuum damage modelling of environmental degradation in joints bonded with EA9321 epoxy adhesive

Damage modelling of adhesively bonded joints

Contact Info

Product

Resources

About