ORCID Profile
0000-0002-9482-5980
Current Organisation
RMIT University
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Publisher: Elsevier BV
Date: 2008
Publisher: Elsevier BV
Date: 12-2013
Publisher: Elsevier BV
Date: 07-1993
Publisher: Elsevier BV
Date: 2008
Publisher: Elsevier BV
Date: 11-2023
Publisher: Elsevier BV
Date: 02-2005
Publisher: Wiley
Date: 02-2002
Publisher: Elsevier BV
Date: 10-2008
Publisher: Wiley
Date: 02-2002
Publisher: Elsevier BV
Date: 04-2009
Publisher: Elsevier BV
Date: 11-2015
Publisher: Trans Tech Publications, Ltd.
Date: 03-2014
DOI: 10.4028/WWW.SCIENTIFIC.NET/AMR.891-892.1059
Abstract: Aircraft full-scale fatigue tests are expensive to conduct and they are a critical item on the certification path of any aircraft design or modification. Two aspects that contribute to the cost of a test are its duration and the loads spectrum development process. This paper provides a summary of a proposed supplemental pseudo full-scale fatigue test (FSFT) aimed at rapid certification. In this instance the method was developed with the aid of extant FSFTs that were found to be deficient. The proposed process involves the development of proof loads, damage size estimates, a loads application rig, insertion of the target damage or modifications and conducting proof testing. As all locations with a propensity to crack are known, the process is considered to be the equivalent of having conducted a representative fatigue test for the required service life target and then demonstrating adequate residual strength (i.e. proof testing the damage state at the end of a FSFT).
Publisher: Trans Tech Publications, Ltd.
Date: 03-2014
DOI: 10.4028/WWW.SCIENTIFIC.NET/AMR.891-892.948
Abstract: It has often been observed that the growth of short fatigue cracks under variable litude (VA) cyclic loading is not well predicted when utilising standard constant litude (CA) crack growth rate/stress intensity data (da/dN v DK). This paper outlines a coupon fatigue test program and analyses, investigating a possible cause of crack growth retardation from CA-only testing. Various test loading spectra were developed with sub-blocks of VA and CA cycles, then using quantitative fractography (QF) the sub-block crack growth increments were measured. Comparison of these results found that, after establishing a consistent uniform crack front using a VA load sequence, the average crack growth rate then progressively slowed down with the number of subsequent CA load cycles applied. Further fractographic investigation of the fracture surface at the end of each CA and VA sub-block crack growth, identified significant crack front morphology differences. Thus it is postulated that a variation or deviation from an efficient crack path is a driver of local retardation in short crack growth during CA loading. This may be a source of error in analytical predictions of crack growth under VA spectra loading that may need to be considered in addition to other potential effects such as less closure whilst cracks are small . For aircraft designers, using solely CA data for fatigue life predictions this may result in non-conservative estimates of total crack fatigue life, producing unexpected failures or an increased maintenance burden.
Publisher: Elsevier BV
Date: 12-2013
Publisher: Elsevier BV
Date: 08-2012
Publisher: Elsevier BV
Date: 07-2008
Publisher: Elsevier BV
Date: 12-2013
Publisher: Elsevier BV
Date: 04-2014
Publisher: Elsevier BV
Date: 10-2013
Publisher: Elsevier BV
Date: 11-2009
Publisher: Elsevier BV
Date: 10-2012
Publisher: Elsevier BV
Date: 06-2007
Publisher: Elsevier BV
Date: 07-2010
Publisher: Elsevier BV
Date: 06-2009
Publisher: Wiley
Date: 11-2007
Publisher: Elsevier BV
Date: 10-2011
Publisher: Trans Tech Publications, Ltd.
Date: 03-2014
DOI: 10.4028/WWW.SCIENTIFIC.NET/AMR.891-892.93
Abstract: The corrections incorporated in fatigue crack growth prediction programs for crack closure are usually tested by their ability to predict retardation following an overload and for the accuracy of their prediction lives for long cracks greater than about 1mm. They should, however, be examined on their ability to predict the life of cracks that grow from small sizes, such as small inherent material discontinuities, to failure, which is more typical of service situations and the growth produced by small cycles as well as the larger cycles. To examine the extent of crack closure in aluminium alloy 7050-T7451 and the prediction of that growth, quantitative fractography measurements of short periods of fatigue crack growth produced with a specially engineered spectrum were conducted and are reported here. The spectrum contained bands of constant litude loads with diminishing mean stress designed to examine the extent of closure. The quantitative fractography results are compared to predictions by the common analytical programs FASTRAN and AFGROW and further with a basic effective stress intensity calculation method at a crack depth of about 1mm. The results showed that the analytical programs were able to predict the presence of closure however, the extent of the closure was not accurately predicted.
Publisher: Elsevier BV
Date: 04-2009
Publisher: Trans Tech Publications, Ltd.
Date: 03-2014
DOI: 10.4028/WWW.SCIENTIFIC.NET/AMR.891-892.739
Abstract: LAU-7 missile launcher housings, which are fitted to most Royal Australian Air Force (RAAF) F/A-18A/B aircraft, can experience cracking in the guide rail. This paper covers the design, manufacture and validation of a life extension repair for cracked launcher housings. The repair development uses DSTO's rework shape optimisation technology and fatigue testing capabilities. The rework design reduces peak stresses by 33 %, resulting in significant fatigue life enhancements, as demonstrated by representative coupon testing. A special manufacturing jig has been designed and transitioned to the RAAF, which has used it to repair housings. These housings have performed well in flight tests, with no cracking detected.
Publisher: Elsevier BV
Date: 12-1994
Publisher: Elsevier BV
Date: 09-2007
Publisher: BENTHAM SCIENCE PUBLISHERS
Date: 24-03-2010
Publisher: Emerald
Date: 30-08-2011
DOI: 10.1108/17579861111162860
Abstract: This paper aims to present some aspects associated with the life prediction of structures with fatigue cracks growing from small natural discontinuities in aluminium alloy (AA)7050‐T7451 for a surface condition that is present in F/A‐18 A/B aircraft critical structure. Fatigue results are presented for thick section AA7050 plate coupons loaded with a representative fighter aircraft wing root bending moment loading spectrum. Detailed quantitative fractography (QF) was used to gain a deeper understanding of issues relevant to an improved fatigue life predictive capacity for this material by using the QF results to investigate the “effectiveness” of the fatigue initiating discontinuities. Estimates of the “effectiveness” of the fatigue initiating discontinuities as quasi pre‐existing fatigue cracks (“equivalent pre‐crack size” (EPS) here) were made with the aid of a simple crack growth model. This model, based on experience, was found to be valid for the applied spectrum and stress levels used. These stress levels were chosen to represent those that may be found in highly stressed locations of fighter aircraft and as such would usually lead to the limiting fatigue life of such a structure. The method has been extended to other crack growth situations and is being used to build a database large enough to determine the best probability distribution of the “effectiveness” of the fatigue initiating discontinuities for not only the surface condition reported here but several other surface conditions typical of aircraft metallic structure. The EPS of the discontinuities from which the cracks grew were used to investigate distributions that may be used in a risk‐based assessment using deterministic crack growth measurements from such discontinuities. Some of the problems that remain to be resolved in such an analysis, prior to its use in a risk‐based assessment are discussed. This work improves the understanding of the interaction of small fatigue cracks generated by representative loading spectra with the small discontinuities from which they grow and shows that the fatigue process is remarkably consistent down to very small sizes.
Publisher: Elsevier BV
Date: 02-2005
Publisher: Elsevier BV
Date: 04-2010
Publisher: Elsevier BV
Date: 12-2006
Publisher: Elsevier BV
Date: 09-1996
Publisher: Elsevier BV
Date: 11-2014
Publisher: Elsevier BV
Date: 07-2005
Publisher: Elsevier BV
Date: 03-2011
Publisher: ASME International
Date: 04-2003
DOI: 10.1115/1.1493804
Abstract: This paper presents a closure model for predicting the growth behavior of short cracks in the presence of large-scale yielding and residual compressive stresses, representative of structures that have been shot-peened. The plasticity-induced crack closure model developed by Newman is first extended by using the cyclic crack-tip opening displacement as the correlating parameter for fatigue crack growth rates. This new approach also enables a better characterization of the effect of large-scale yielding on short crack growth. The effect of residual stress on crack closure is then analyzed by adding to the loading spectrum an equivalent stress, which varies with the applied load level and the crack size. It is shown that predictions of the extended closure model are within a factor of two of the experimental results of etched specimens tested under spectrum loading, highlighting the capability of the predictive model along with some important issues for future research in this area.
Publisher: Trans Tech Publications, Ltd.
Date: 06-2010
DOI: 10.4028/WWW.SCIENTIFIC.NET/MSF.654-656.887
Abstract: -annealed Ti-6Al-4V ELI alloy has a special chemical composition and manufacturing process, intended to optimise its fatigue and fracture properties. This alloy is used in primary fatigue-critical structures of advanced military aircraft, but little has been generally published about its properties, particularly the fatigue and crack growth behaviour under service loading. A test programme has been set up to assess the fatigue durability and damage tolerance properties of the alloy, in the context of the two most relevant analysis methods. The first is strain – life analysis, used to estimate safe lives (durability). The second is fatigue crack growth analysis, used to assess the damage tolerance behaviour. This paper presents preliminary results of the test programme.
No related grants have been discovered for Simon Barter.