A growth model for catastrophic cracking in an RAAF aircraft

Goldsmith, N.T.; Clark, Graham; Barter, Simon

doi:10.1016/1350-6307(96)00014-3

Cited by 11 publications

(5 citation statements)

References 4 publications

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“…Regions of striations are interrupted by bands which reveal ductile fracture. A similar surface feature has been reported on many fatigue fracture surfaces of aluminium alloy aircraft components, particularly for in-service failures [14][15][16][17]. Forming such zone of ductile fracture is mostly referred to stable tearing.…”

Section: Failured Partssupporting

confidence: 60%

Structural overloading evaluation based on the identification of subcritical crack increments

Šedek

Běhal

2015

Engineering Failure Analysis

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Section: Failured Partssupporting

confidence: 60%

Structural overloading evaluation based on the identification of subcritical crack increments

Šedek

Běhal

2015

Engineering Failure Analysis

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“…The model is based on two significant features of fatigue crack growth when examining cracks grown with realistic aircraft fighter sequence loading. These are that the dominant cracks initiate very early, 1,16–21 typically within the first loading block applied, and that they often grow at approximately a constant exponential rate for most of their life 1,15–18 . This growth can be modelled, sometimes over several decades of crack growth using a simple exponential representation of the form:…”

Section: Equivalent Precrack Size Determinationmentioning

confidence: 99%

“…Inclusions or secondary phase particles are common sites for fatigue crack initiation 18–26 . Newman et al 2,26 .…”

Section: Characteristics Of Fatigue Initiation Sitesmentioning

confidence: 99%

Initiation and early growth of fatigue cracks in an aerospace aluminium alloy

Barter

Sharp

Holden

et al. 2002

Fatigue Fract Eng Mat Struct

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Material imperfections usually play a substantial role in the early stages of fatigue cracking. This article presents some observations concerning fatigue crack initiating flaws and early crack growth in 7050‐T7451 aluminium alloy specimens and in full‐scale fatigue test articles with a production surface finish. Equivalent initial flaw size (EIFS) approaches used to evaluate the fatigue implications of metallurgical, manufacturing and service‐induced features were refined by using quantitative fractography to acquire detailed information on the early crack growth behaviour of individual cracks; the crack growth observations were employed in a simple crack growth model developed for use in analysing service crack growth. The use of observed crack growth behaviour reduces the variability which is inherent in EIFS approaches which rely on modelling the whole of fatigue life, and which can dominate EIFS methods. The observations of realistic initial flaws also highlighted some of the significant factors in the fatigue life‐determining early fatigue growth phase, such as surface treatment processes. Although inclusions are often regarded as the single most common type of initiating flaw, processes which include etching can lead to etch pitting of grain boundaries with significant fatigue life implications.

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“…Stable tearing, a recurring process whereby fatigue crack growth is interspersed by substantial jumps of crack front, is a major issue affecting accurate and reliable predictions of fatigue life and fatigue crack growth. [1][2][3][4][5][6] A stable tearing band sometimes forms upon the application of an overload or high loads in a variable-amplitude loading sequence. However, a single high-load cycle (overload), referring to Fig.…”

Section: Introductionmentioning

confidence: 99%

Predictive models for stable tearing crack growth due to overloading in fatigue

Rahman

Clark

Wang

2012

Fatigue Fract Eng Mat Struct

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Stable tearing is a recurring process in which fatigue crack growth is interspersed by substantial jumps of crack growth, commonly at the central cross‐section of the component while the crack front nearer the surface lags behind. These tearing bands have been observed to start very early during fatigue life and can make up the majority of the fatigue fracture surface. This paper presents the development of predictive models, in which the tongue‐shaped stable tearing band is first idealised as trapezoidal shape, and then two alternative fracture criteria are formulated with the aid of the finite element (FE) method and the Forsyth stable tearing concept. Parametric solutions of the stress intensity factor at the front of the trapezoidal crack front are obtained using the FE method. Comparisons between the model predictions and experimental results indicate that both models produce satisfactory prediction of the stable tearing crack jump length in aluminium alloy coupons of varying cross‐sectional thickness.

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A growth model for catastrophic cracking in an RAAF aircraft

Cited by 11 publications

References 4 publications

Structural overloading evaluation based on the identification of subcritical crack increments

Structural overloading evaluation based on the identification of subcritical crack increments

Initiation and early growth of fatigue cracks in an aerospace aluminium alloy

Predictive models for stable tearing crack growth due to overloading in fatigue

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