Risk Analysis for Aging Aircraft Fleets

Berens, Alan P.; Burns, J. G.; Rudd, JL

doi:10.1007/978-3-642-84364-8_3

Cited by 56 publications

(51 citation statements)

References 3 publications

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“…It will be shown that these observations for the FCG rate histories associated with the fastest growing (i.e. lead) damage in these composites are consistent with the USAF approach to assessing the probability of failure in metallic airframes [72,73].…”

Section: Aims Of the Present Papersupporting

confidence: 58%

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

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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.

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Section: Aims Of the Present Papersupporting

confidence: 58%

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

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“…Indeed, the need to be able to account for small sub mm initial defects is reinforced in the US Federal Highway Administration Steel Bridge Design Handbook [3] where it was noted that crack growth essentially starts from day one and that the majority of the life of steel I bridges is consumed in growing to a size where a crack can be detected. As explained in [4] this observation coincides with that seen in the growth of cracks in operational aircraft [5,6]. In this context it is now known that the da/dN versus ΔK relationship associated with the growth of cracks in bridges steels and in the high strength aerospace steels D6ac and 4340 steel are similar and can be represented by the same Nasgro equation [4,7].…”

Section: Introductionsupporting

confidence: 78%

Effect of corrosion and fatigue on the remaining life of structures and its implication to additive manufacturing

Peng

Jones²,

Berto

et al. 2018

Frattura Ed Integrità Strutturale

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ABSTRACT. This paper investigates the combined effect of corrosion and fatigue on the growth of cracks that arise from natural corrosion in steel bridges. It is shown that if these two effects need to be simultaneously analyzed. If not, then the resulting life is not conservative. Consequently, to enable a better understanding of the remaining life of steel bridges this paper presents a simple methodology for performing this coupled analysis. The implication of this study to additively manufactured Ti-6Al-4V is also discussed. KEYWORDS. Steel bridges; Corrosion; Fatigue crack growth; Remaining life.Citation: Peng., D., Jones, R., Berto, F., Razavi, S.M.J., Effect of corrosion and fatigue on the remaining life of structures and its implication to additive manufacturing, Frattura ed Integrità Strutturale, 45 (2018) 33-44.

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“…Cracks considered included those grown from; semi-and quarter elliptical surface cuts, holes, pits and inherent material discontinuities in test specimens, full-scale aircraft fatigue tests, fuselage lap joints, welded butt joints, and complex tubular jointed specimens and include cracks grown under uniaxial and biaxial loading for both constant amplitude and complex in-service spectra. The apparent exponential rate of crack growth at small crack lengths has also been mentioned in references (Clark et al, 1997;Wang, 1982;Zhang, 2000;Berens et al, 1991) The work of Clark et al (1997) is particularly important in recognizing the usefulness of this relationship. As a result of its success in describing cracking in the RAAF Macchi fleet Clark et al stated that this law "will be used more widely and more confidentially in any similar applications in future.…”

Section: Crack Growth At Low ∆K'smentioning

confidence: 92%

Crack growth at low ?K’s and the Frost‐Dugdale law

Jones¹,

Barter

Molent

et al. 2004

Journal of the Chinese Institute of Engineers

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This paper examines the fatigue crack growth histories, at low ∆K's, of a range of test specimens and service loaded components and concludes that, as a first approximation, there is a linear relationship between the log of the crack length or depth and the service history (number of load cycles). We also show that, for the cases studied, that the log linear method can give a better prediction of experimental data than a conventional crack growth model.

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Risk Analysis for Aging Aircraft Fleets

Cited by 56 publications

References 3 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

Effect of corrosion and fatigue on the remaining life of structures and its implication to additive manufacturing

Crack growth at low ?K’s and the Frost‐Dugdale law

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