The lead crack fatigue lifing framework

Molent, L.; Barter, Simon; Wanhill, R.J.H.

doi:10.1016/j.ijfatigue.2010.09.009

Cited by 88 publications

(85 citation statements)

References 24 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…It has been recognized that accurate predictions of fatigue lives of metallic structures, particularly for physically small cracks still pose challenges and research in this field has been driven by increasing demand for improved performances and costs reductions during manufacture and service [1]. Fatigue cracks may start from small discontinuities in materials, manufacturing defects, design inadequacies and degradation processes such as corrosion [2].…”

Section: Introductionmentioning

confidence: 99%

Prediction of fatigue life in aluminium alloy (AA7050-T7451) structures in the presence of multiple artificial short cracks

Tan

Chen

2015

Theoretical and Applied Fracture Mechanics

View full text Add to dashboard Cite

Section: Introductionmentioning

confidence: 99%

Prediction of fatigue life in aluminium alloy (AA7050-T7451) structures in the presence of multiple artificial short cracks

Tan

Chen

2015

Theoretical and Applied Fracture Mechanics

View full text Add to dashboard Cite

“…Of particular interest to DST is the effect that repeated small amplitude cycles, with a high mean, has in retarding crack growth in the threshold region. Due to the inherently exponential crack growth rates [2,25] observed in common airframe alloys under aircraft loading, retardation of growth at the very early stages of fatigue nucleation/growth can have a significant impact on the total fatigue life of a component. A modification to a material model for AA7050-T7451 has been developed that accounts for such a subtle crack growth retardation produced by the use of CA cycles when blocked.…”

Section: Discussionmentioning

confidence: 99%

“…In the case of aluminium alloy aircraft structures, it has been found that the fatigue life is dominated by the initial growth rate of the lead crack in any component, i.e. the crack that leads to the component failure [2]. The majority of the component's fatigue life is therefore consumed while such cracks are small [3,4], and of the dimensions of the microstructure; typically nucleating from small naturally occurring material discontinuities, with an equivalent initial crack size, a i of ~20µm [5].…”

Section: Introductionmentioning

confidence: 99%

Microstructurally small fatigue crack growth rates in aluminium alloys for developing improved predictive models

et al. 2018

View full text Add to dashboard Cite

Abstract. The fatigue or durability life of a few critical structural metallic components often sets the safe and/or economic useful life of a military airframe. In the case of aluminium airframe components, growth rates, at or soon after fatigue crack nucleation are being driven by near threshold local cyclic stress intensities and thus are very low. Standard crack growth rate data is usually generated from large cracks, and therefore do not represent the growth of small cracks (typically <1mm). Discussed here is an innovative test and analysis technique to measure the growth rates of small cracks growing as the result of stress intensities just above the cyclic growth threshold. Using post-test quantitative fractographic examination of fatigue crack surfaces from a series of 7XXX test coupons, crack growth rates and observations of related growth phenomenon in the threshold region have been made. To better predict small crack growth rates under a range of aircraft loading spectra a method by which standard material data models could be adapted is proposed. Early results suggest that for small cracks this method could be useful in informing engineers on the relative severity of various spectra and leading to more accurate predictions of small crack growth rates which can dominate the fatigue life of airframe components..

show abstract

“…For a given surface roughness, the probability distribution of lead crack growth rate and hence fatigue life can be determined by that of the local fatigue threshold, and the role of the fatigue threshold is the effect of surface roughness [58,59]. Linking the probability distribution of the local fatigue threshold in Ref.…”

Section: Conclusion and Outlooksmentioning

confidence: 99%

“…Linking the probability distribution of the local fatigue threshold in Ref. [58,59] with that of the local fracture properties in our numerical model and to establish the relationship between the parameters in the above two probability distributions is stimulating to provide more insights into the fatigue life of metallic materials or structures.…”

Section: Conclusion and Outlooksmentioning

confidence: 99%

Local Monte Carlo Method for Fatigue Analysis of Coarse-Grained Metals with a Nanograined Surface Layer

Guo

Sun

Yang

et al. 2018

Metals

View full text Add to dashboard Cite

Abstract:The fatigue resistance of coarse-grained (CG) metals can be greatly improved by introducing a nanograined surface layer. In this study, the Weibull distribution is used to characterize the spatially-random fracture properties of specimens under axial fatigue. For the cylindrical solid specimen, the heterogeneity of element sizes may lead to unfavorable size effects in fatigue damage initiation and evolution process. To alleviate the size effects, a three-dimensional cohesive finite element method combined with a local Monte Carlo simulation is proposed to analyze fatigue damage evolution of solid metallic specimens. The numerical results for the fatigue life and end displacement of CG specimens are consistent with the experimental data. It is shown that for the specimens after surface mechanical attrition treatment, damage initiates from the subsurface and then extends to the exterior surface, yielding an improvement in the fatigue life. Good agreement is found between the numerical results for the fatigue life of the specimens with the nanograined layer and experimental data, demonstrating the efficacy and accuracy of the proposed method.

show abstract

The lead crack fatigue lifing framework

Cited by 88 publications

References 24 publications

Prediction of fatigue life in aluminium alloy (AA7050-T7451) structures in the presence of multiple artificial short cracks

Prediction of fatigue life in aluminium alloy (AA7050-T7451) structures in the presence of multiple artificial short cracks

Microstructurally small fatigue crack growth rates in aluminium alloys for developing improved predictive models

Local Monte Carlo Method for Fatigue Analysis of Coarse-Grained Metals with a Nanograined Surface Layer

Contact Info

Product

Resources

About