A study into the interaction of intergranular cracking and cracking at a fastener hole

Jones, Rhys; Lo, Michael Chie Siung; Peng, Daren; Bowler, Adam; Dorman, Michael F.; Janardhana, Madabhushi; Iyyer, Nagaraja

doi:10.1007/s11012-013-9849-x

Cited by 16 publications

(43 citation statements)

References 26 publications

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“…In this formulation D is a constant, Kmax and Kmin are the maximum and minimum values of K seen in a cycle, ΔKopl is the long crack value of ΔKop (= Kop -Kmin), Kop is the value of the stress intensity factor at which the crack first opens, λ is a material dependent constant and the terms Kthr and A are best interpreted as parameters chosen so as to fit the measured da/dN versus K data, see [3] for more details. It has also been shown [3,[15][16][17] that variations in the small crack length histories can be modelled by allowing for small changes in the value of Kthr. The review paper [3] also illustrated how this approach can be used to compute the crack growth history seen in operational aircraft via the problem of crack growth in the 1969 General Dynamics, now Lockheed Martin, F-111 wing fatigue test which used a representative F-111 usage spectrum.…”

Section: Computing Crack Growth Associated With Aircraft Sustainment mentioning

confidence: 99%

“…As in [16], which studied the growth of long cracks in tests in this material, crack growth was computed using the Harman-Schijve variant of the NASGRO equation, i.e. equation (2) with m = p, q = p/2 and p = 2.…”

Section: Crack Growth Under a Representative Raaf Ap3c (Orion) Spectrummentioning

confidence: 99%

“…However, since in this instance we are analysing cracks that grow from small naturally occurring material discontinuities closure effects were set to zero, as recommended in [3] for this class of problems. The values of D and A used in the analysis were as given in [16,17] for this material so that the crack growth equation became:…”

Section: Crack Growth Under a Representative Raaf Ap3c (Orion) Spectrummentioning

confidence: 99%

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Crack Growth from Naturally Occurring Material Discontinuities in Operational Aircraft

Jones

Peng

Huang

et al. 2015

Procedia Engineering

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This paper focuses on problems associated with aircraft sustainment related issues and illustrates how cracks that grow from small naturally occurring material discontinuities in operational aircraft behave. The example discussed in this paper, which is associated with crack growth under a representative maritime aircraft load spectrum, when taken in conjunction with previous studies into cracks growing under combat aircraft load spectra illustrates how for cracks that grow from naturally occurring material discontinuities under such operational load spectra there is generally little crack closure so that the crack growth history from its initial equivalent pre-crack size (EPS) through to final failure can be easily and accurately computed.

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Section: Computing Crack Growth Associated With Aircraft Sustainment mentioning

confidence: 99%

Section: Crack Growth Under a Representative Raaf Ap3c (Orion) Spectrummentioning

confidence: 99%

Section: Crack Growth Under a Representative Raaf Ap3c (Orion) Spectrummentioning

confidence: 99%

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Crack Growth from Naturally Occurring Material Discontinuities in Operational Aircraft

Jones

Peng

Huang

et al. 2015

Procedia Engineering

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“…In the fracture and fatigue analyses, the associated SIFs were computed using the weight function method as per Refs 35,36 . Models were created for both with and without IGC.…”

Section: O M P U T I N G T H E S T R E S S I N T E N S I T Y F a C mentioning

confidence: 99%

“…In this context, a survey of the open literature suggests that Ref 35 was perhaps one of the first studies into the influence of MLIGC. The subsequent study in Ref 36 revealed that different levels of load transfer in MLIGC, which can arise as a result of various levels of contact between the IGC surfaces, did not significantly change the stress field at the hole.…”

Section: Introductionmentioning

confidence: 99%

Crack growth at fastener holes containing intergranular cracking

Jones

Bowler

et al. 2017

Fatigue Fract Eng Mat Struct

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This paper examines the growth of cracks at a fastener hole containing intergranular cracking with a focus on ‘dome nut hole’ coupons that are representative of a critical location in the Royal Australian Air Force AP‐3C Orion wing. It is shown that crack growth under operational flight loads can be captured using the NASGRO formulation and that the scatter in these various tests can also be captured by allowing for small variations in the value of the cyclic stress intensity fatigue threshold. In this context, it is shown that crack growth can be captured using both a cycle‐by‐cycle analysis and also a United States Air Force ‘characteristic K’ approach. We also see that, for the operational load spectra considered, the crack growth history is approximately exponential so that the United States Air Force risk assessment computer program (PRobability Of Fracture) can be used to assess the risk of failure by fracture. The results of this study also suggest that, provided that intergranular cracking does not turn and break through to a free surface, it should have little effect on crack growth at a fastener hole.

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On the Growth of Fatigue Cracks from Material and Manufacturing Discontinuities Under Variable Amplitude Loading

Jones

Peng

Huang

et al. 2015

JOM

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A study into the interaction of intergranular cracking and cracking at a fastener hole

Cited by 16 publications

References 26 publications

Crack Growth from Naturally Occurring Material Discontinuities in Operational Aircraft

Crack Growth from Naturally Occurring Material Discontinuities in Operational Aircraft

Crack growth at fastener holes containing intergranular cracking

On the Growth of Fatigue Cracks from Material and Manufacturing Discontinuities Under Variable Amplitude Loading

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