Assessment of the effect of impact damage in composites: Some problems and answers

Jones, Rhys; Paul, J.; Tay, T.E.; Williams, Jenny

doi:10.1016/0167-8442(88)90021-3

Cited by 21 publications

(6 citation statements)

References 40 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Here it should be recalled that, when originally formulating the equations for crack growth, Paris argued that, since Irwin [20,21] had shown that the stress-intensity factor, K, uniquely characterises the near tip stress field, then the rate of FCG should be a function of ΔK and K max [22,23]. In [24] [2,[41][42][43][44][45][46][47][48][49][50][51][52][53][54][55]. (Where ∆√G is given by (�G max -�G min ); and G min is the minimum value of the energy release-rate in a fatigue cycle.…”

Section: Analysis Of the Measured Fcg Datamentioning

confidence: 99%

“…The use of Mode I DCB tests is the most common approach employed to characterise delamination growth as a function of the energy release-rate, G [2,4,5,19,26,[38][39][40][41][42][43][44][45][46][47][48][49][50][51][52][53][54][55][76][77][78]. However, a major problem with this method is the large retardation that can develop due to fibres bridging the delamination [4,5,13,14,36,42,49].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

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

Self Cite

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: Analysis Of the Measured Fcg Datamentioning

confidence: 99%

Section: Introductionmentioning

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

Self Cite

View full text Add to dashboard Cite

show abstract

“…Low energy impact damage in composite structures has been the subject of numerous studies, e.g., [3][4][5][6][7][8][9][10][11]. However, few studies have been reported on modeling the progressive failure in thin shell composites.…”

Section: Introductionmentioning

confidence: 99%

Progressive Failure Analysis of Thin Walled Composite Tubes Under Low Energy Impact

Yen¹,

Cassin²,

Patterson³

et al. 2007

View full text Add to dashboard Cite

show abstract

“… Delamination is a failure mechanism of laminated composites 2 . While delamination usually occurs at plate edges, it may also occur internally during the manufacturing process or later as a result of moisture wicking from environmental exposure. Interfacial debonding can occur when the antioxidation coating applied to fibers used in continuous fiber‐reinforced polymeric composites and the matrix material bond fail under stress 3 . The failure at this interface affects the strength of the laminate because the matrix does not transfer load to the fiber.…”

mentioning

confidence: 99%

“…Interfacial debonding can occur when the antioxidation coating applied to fibers used in continuous fiber‐reinforced polymeric composites and the matrix material bond fail under stress 3 . The failure at this interface affects the strength of the laminate because the matrix does not transfer load to the fiber.…”

mentioning

confidence: 99%

Application of Novel Nanosensor Technology to Filament Wound Composite Structures

et al. 2008

View full text Add to dashboard Cite

Assessment of the effect of impact damage in composites: Some problems and answers

Cited by 21 publications

References 40 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

Progressive Failure Analysis of Thin Walled Composite Tubes Under Low Energy Impact

Application of Novel Nanosensor Technology to Filament Wound Composite Structures

Contact Info

Product

Resources

About