Calculating crack growth from small discontinuities in 7050-T7451 under combat aircraft spectra

Jones, Rhys; Molent, L.; Barter, Simon

doi:10.1016/j.ijfatigue.2013.06.009

Cited by 58 publications

(81 citation statements)

References 20 publications

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“…Furthermore, equation (5) also predicts that this relationship should hold regardless of the material or the nature of the spectra. The accuracy of this prediction 11 is illustrated in both [27,28] and is shown in Figure 11, see [28] for more details.…”

Section: A Master Curve Representation For Crack Growth In Operationamentioning

confidence: 95%

“…It was subsequently also shown to hold for cracks growing in both operational aircraft and in full scale fatigue tests under representative operational load spectra [36], see Figure 11. Nevertheless, as shown in [27,28], this approach predicts that, for tests on centre cracked panels and surface and edge cracks under repeated block loading, for the majority of the fatigue life we should see a near linear relationship between the number of load blocks and the log of the crack length. Furthermore, equation (5) also predicts that this relationship should hold regardless of the material or the nature of the spectra.…”

Section: A Master Curve Representation For Crack Growth In Operationamentioning

confidence: 96%

“…to a steel bridge, then it is essential that, in these tests, the cracks are first allowed to developed naturally and then patched/repaired. One means of achieving this is to grow cracks from small etch pits [28], another way is to use lasers to create small near micron size initial notches [29,30].…”

Section: Experimental Test and Analysis Requirements For Cfrp Repairsmentioning

confidence: 99%

“…The physical reason for this 7 formulation is that, as explained in [49,50], the growth of cracks that initiate from small naturally occurring material discontinuities behave, as explained by 4 Nevertheless limited crack growth was observed in operational aircraft. 5 Here it should be noted that it is now know that for a range of materials tested under a range of operational load spectra the growth of cracks that initiate and grow from small naturally occurring material discontinuities can be accurately computed using the R ratio independent da/dN versus ΔK small crack relationship and setting closure effects to zero [27,28,[34][35][36][37]. 6 This is also referred to as exponential crack growth.…”

Section: Exponential Crack Growthmentioning

confidence: 99%

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Section: A Master Curve Representation For Crack Growth In Operationamentioning

confidence: 95%

Section: A Master Curve Representation For Crack Growth In Operationamentioning

confidence: 96%

Section: Experimental Test and Analysis Requirements For Cfrp Repairsmentioning

confidence: 99%

Section: Exponential Crack Growthmentioning

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“…The Hartman-Schijve equation used in [1,8,11,20,24,25,32,36,[39][40][41][42][43][44] is basically an empirical equation that for metals takes the form:…”

Section: Introductionmentioning

confidence: 99%

Cyclic-fatigue crack growth in composite and adhesively-bonded structures: The FAA slow crack growth approach to certification and the problem of similitude

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Kinloch

2016

International Journal of Fatigue

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Combined effect of both surface finish and sub‐surface porosity on component strength under repeated load conditions

McMillan

Jones

2020

Engineering Reports

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High duty engineering component life is usually demonstrated through extensive testing and statistical analysis applied to empirical curve-fit equations. Because of this, the extent of the testing required is huge and costly: it must consider the load cycle range and test to high numbers of cycles. Additive Manufacturing (AM) for high duty components has brought to the fore the question of the effect of porosity and surface roughness on fatigue life, and how the true life of a critical component can be assessed conservatively. The authors propose the first step toward the development of a fatigue model based on well-established engineering physics principles, by creating computational specimens with modeled surface roughness and porosity, and subjected to cyclic loading using Finite Element Analysis. They show that the combination of roughness features and sub-surface pores leads to an equivalent plastic strain distribution pattern that suggests an emergent physical process that has not been reported before, and which indicates that the component strength and life reduction arising from surface roughness can be made significantly worse by the presence of porosity. The development of such phenomenological understanding should lead to improved life prediction techniques, more cost effective test procedures, and the development of better AM methods.

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Calculating crack growth from small discontinuities in 7050-T7451 under combat aircraft spectra

Cited by 58 publications

References 20 publications

Composite repairs to bridge steels demystified

Composite repairs to bridge steels demystified

Cyclic-fatigue crack growth in composite and adhesively-bonded structures: The FAA slow crack growth approach to certification and the problem of similitude

Combined effect of both surface finish and sub‐surface porosity on component strength under repeated load conditions

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