Fibre bridging effect on the Paris relation of mode I fatigue delamination in composite laminates with different thicknesses

Yao, Liaojun; Sun, Yi; Guo, Licheng; Alderliesten, R.C.; Benedictus, Rinze; Zhao, Minghua; Jia, Liyong

doi:10.1016/j.ijfatigue.2017.06.004

Cited by 24 publications

(23 citation statements)

References 33 publications

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“…This means this new similitude parameter can appropriately represent the consistency or similitude in fibre-bridged FDG in composite laminates. Comparing to the results interpreted via the basic Paris relation [25], these data shown in Fig. 3 highlight the importance of using an appropriate similitude parameter in correctly interpreting FDG behaviors.…”

Section: Fibre-bridged Fdg In Composite Laminates With Different Thicmentioning

confidence: 66%

“…6 demonstrates that the use of the new fatigue model is an effective and convenient way to determine zero-bridging FDG. Furthermore, the use of the modified Paris relation in FDG study takes an advantage of resulting in a lower exponent, as compared to the basic Paris relation [25]. A smaller value of the exponent indicates less sensitivity of the prediction model.…”

Section: Further Discussion On the Modified Paris Relationmentioning

confidence: 99%

“…3 provides a summary of this interpretation. And detailed Paris law representation of these fatigue data can be found in literature [25], in which the effects of fibre bridging on the Paris relation were carefully examined. Considering the scatters usually observed in fatigue [3,4,22,26], two important features of the results shown in Fig.…”

Section: Fibre-bridged Fdg In Composite Laminates With Different Thicmentioning

confidence: 99%

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Thickness effects on fibre-bridged fatigue delamination growth in composites

Yao

Cui

Alderliesten

et al. 2018

Composites Part A: Applied Science and Manufacturing

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This paper provides an investigation on thickness effects on fibre-bridged fatigue delamination growth (FDG) in composite laminates. A modified Paris relation was employed to interpret experimental fatigue data. The results clearly demonstrated that both thickness and fibre bridging had negligible effects on FDG behaviors. Both energy principles and fractography analysis were subsequently performed to explore the physical reasons of this independence. It was found that the amount of energy release of a given crack growth was not only independent of fibre bridging, but also thickness. Fibre print was the dominant microscopic feature located on fracture surfaces, physically making the same energy dissipation during FDG. Furthermore, the present study provides extra evidence on the importance of using an appropriate similitude parameter in FDG studies. Particularly, the strain energy release rate (SERR) range applied around crack front was demonstrated as an appropriate similitude parameter for fibre-bridged FDG study.

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Section: Fibre-bridged Fdg In Composite Laminates With Different Thicmentioning

confidence: 66%

Section: Further Discussion On the Modified Paris Relationmentioning

confidence: 99%

Section: Fibre-bridged Fdg In Composite Laminates With Different Thicmentioning

confidence: 99%

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Thickness effects on fibre-bridged fatigue delamination growth in composites

Yao

Cui

Alderliesten

et al. 2018

Composites Part A: Applied Science and Manufacturing

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“…A second main requirement for any methodology used to determine FCG rate data as a function of G, where this relationship could be considered as an accurate and valid materialallowable property, is to take into account the relatively large inherent scatter that is observed in the laboratory tests, whatever its source. It is now appreciated [2,16,19,21,24,28,[32][33][34][35][36][37]39] that fibrebridging effects may give rise, at least in part, to the relatively large scatter that is typically seen in fatigue tests on FRPs. However, there are other likely sources of such scatter [2,16,19,25,33].…”

Section: Introductionmentioning

confidence: 99%

“…The aim of the present paper is, therefore, to investigate whether this methodology can be extended to a carbon-fibre reinforced-plastic (CFRP) composite for which a very extensive testing programme has been previously undertaken and reported [26,[35][36][37]46].…”

Section: Introductionmentioning

confidence: 99%

Delamination fatigue growth in polymer-matrix fibre composites: A methodology for determining the design and lifing allowables

Yao

Alderliesten

Jones

et al. 2018

Composite Structures

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The introduction, originally in 2009, by the FAA of a 'slow growth' approach to the certification of polymer-matrix fibre composites has focused attention on the experimental data and the analytical tools needed to assess the growth of delaminations under cyclic-fatigue loads. Of direct relevance is the fact that fatigue tests on aircraft composite components and structures reveal that no, or only little, retardation of the fatigue crack growth (FCG) rate occurs as delamination/impact damage grows. Therefore, of course, the FCG data that are ascertained in laboratory tests, and then employed as a material-allowable property to design and life the structure, as well as for the development, characterisation and comparison of composite materials, must also exhibit no, or only minimal, retardation. Now, in laboratory tests the double-cantilever beam (DCB) test, using a typical carbon-fibre reinforced-plastic (CFRP) aerospace composite, is usually employed to obtain fracture-mechanics data under cyclic-fatigue Mode I loading. However, it is extremely difficult to perform such DCB fatigue tests without extensive fibre-bridging developing across the crack faces. This fibre-bridging leads to significant retardation of the FCG rate. Such fibre-bridging, and hence retardation of the FCG, is seen to arise even for the smallest values of the pre-crack extension length, a p-a 0 , that are typically employed. The results from the DCB tests also invariably exhibit a relatively large degree of inherent scatter. Thus, a methodology is proposed for predicting an 'upper-bound' FCG curve from the laboratory test data which is representative of a composite laminate exhibiting no, or only very little, retardation of the FCG rate under fatigue loading and which takes into account the inherent scatter. To achieve this we have employed a novel methodology, based on using a variant of the Hartman-Schijve equation, to access this 'upperbound' FCG rate curve, which may be thought of as a material-allowable property and which is obtained using an 'A basis' statistical approach. Therefore, a conservative 'upper-bound' FCG curve may now be calculated from the DCB laboratory test data for material development, characterision and comparative studies, and for design and lifing studies.

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