ORCID Profile
0000-0003-3197-2796
Current Organisations
Swinburne University of Technology
,
Monash University
,
Emeritus Professor, Monash University
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Research Topics
In Research Link Australia (RLA), "Research Topics" refer to ANZSRC FOR and SEO codes. These topics are either sourced from ANZSRC FOR and SEO codes listed in researchers' related grants or generated by a large language model (LLM) based on their publications.
Top 5 Research Topics
ANZSRC Field of Research (FoR)
Mechanical Engineering | Mechanical Engineering | Aerospace Engineering | Engineering/Technology Instrumentation | Aerospace Structures | Transport Engineering | Optical Physics | Manufacturing Engineering Not Elsewhere Classified | Civil Engineering | Optical Physics Not Elsewhere Classified | Packaging, Storage And Transportation | Manufacturing Processes and Technologies (excl. Textiles) | Solid Mechanics | Interdisciplinary Engineering Not Elsewhere Classified | Materials Engineering Not Elsewhere Classified | Automotive Engineering | Cad/Cam Systems | Interdisciplinary Engineering
ANZSRC Socio-Economic Objective (SEO)
Rail equipment | Transport | Aerospace equipment | Scientific instrumentation | Air Force | Combined operations | Coal | Coal | Industrial instrumentation | Mining machinery and equipment | Automotive equipment | Multimodal transport | Automotive Equipment |
Related Links
Publications
Continued airworthiness of composite repairs to primary structures for military aircraft
Publisher: Elsevier BV
Date: 1995
On the role of the interface on the damage tolerance and durability of cold spray repairs to AA7075-T7351 aluminium alloy wing skins
Publisher: Elsevier BV
Date: 03-2021
Crack patching: An experimental evaluation of fatigue crack growth
Publisher: Elsevier BV
Date: 02-2005
Directional dependence of spectra of fiber bragg gratings due to excess loss
Publisher: Optica Publishing Group
Date: 11-2006
Abstract: The reflectance spectra of chirped fiber Bragg gratings can depend substantially on the direction from which the measurement is taken. The measured difference between forward and backward reflectance spectra measured in a linearly chirped grating was shown to be due to the measured excess loss. Simulation using the popular transfer-matrix model demonstrated that the observed asymmetric behavior could be obtained only when excess loss has an asymmetric spectral shape about the local Bragg wavelengths. Application of cladding mode excess losses to the result of a transfer-matrix model accounted for the experimental observation.
Using hybrid element method to solve 3D elliptic crack problems with multi-materials structure
Publisher: Elsevier BV
Date: 04-2002
Analysis of the Effect of Machining of the Surfaces of WAAM 18Ni 250 Maraging Steel Specimens on Their Durability
Publisher: MDPI AG
Date: 13-12-2022
DOI: 10.3390/MA15248890
Abstract: It is now well-known that the interaction between surface roughness and surface-breaking defects can significantly degrade the fatigue life of additively manufactured (AM) parts. This is also aptly illustrated in the author’s recent study on the durability of wire and arc additively manufactured (WAAM) 18Ni 250 Maraging steel specimens, where it was reported that failure occurred due to fatigue crack growth that arose due to the interaction between the surface roughness and surface-breaking material defects. To improve the durability of an AM part, several papers have suggested the machining of rough surfaces. However, for complex geometries the fully machining of the entire rough surface is not always possible and the effect of the partial machining on durability is unknown. Therefore, this paper investigates if partial machining of WAAM 18Ni 250 Maraging steel surfaces will help to improve the durability of these specimens. Unfortunately, the result of this investigation has shown that partial machining may not significantly improve durability of WAAM 18Ni 250 Maraging steel specimens. Due to the order of surface roughness seen in WAAM 250 Maraging steel, the improvement to durability is only realized by full machining to completely remove the remnants of any print artefacts.
Damage tolerance based shape design of a stringer cutout using evolutionary structural optimisation
Publisher: Elsevier BV
Date: 2007
Computational methods in modern repair technology
Publisher: Springer Science and Business Media LLC
Date: 1987
DOI: 10.1007/BF00296419
Bonded composite repair of cracked load-bearing holes
Publisher: Elsevier BV
Date: 06-1994
A simple method for computing the stress intensity factors for cracks at notches
Publisher: Elsevier BV
Date: 12-2002
The generalised Frost–Dugdale approach to modelling fatigue crack growth
Publisher: Elsevier BV
Date: 12-2008
Modelling the Variability and the Anisotropic Behaviour of Crack Growth in SLM Ti-6Al-4V
Publisher: MDPI AG
Date: 13-03-2021
DOI: 10.3390/MA14061400
Abstract: The United States Air Force (USAF) Guidelines for the Durability and Damage Tolerance (DADT) certification of Additive Manufactured (AM) parts states that the most difficult challenge for the certification of an AM part is to establish an accurate prediction of its DADT. How to address this challenge is the focus of the present paper. To this end this paper examines the variability in crack growth in tests on additively manufactured (AM) Ti-6Al-4V specimens built using selective layer melting (SLM). One series of tests analysed involves thirty single edge notch tension specimens with five build orientations and two different post heat treatments. The other test program analysed involved ASTM standard single edge notch specimens with three different build directions. The results of this study highlight the ability of the Hartman–Schijve crack growth equation to capture the variability and the anisotropic behaviour of crack growth in SLM Ti-6Al-4V. It is thus shown that, despite the large variability in crack growth, the intrinsic crack growth equation remains unchanged and that the variability and the anisotropic nature of crack growth in this test program is captured by allowing for changes in both the fatigue threshold and the cyclic fracture toughness.
A numerical study of crack monitoring in patched structures using a piezoelectric sensor
Publisher: IOP Publishing
Date: 09-1992
Thermomechanical analysis of composite specimens
Publisher: Elsevier BV
Date: 1989
Calculating crack growth from small discontinuities in 7050-T7451 under combat aircraft spectra
Publisher: Elsevier BV
Date: 10-2013
Compliance measurements for assessing structural integrity
Publisher: Elsevier BV
Date: 08-2001
The tool for assessing the damage tolerance of railway wheel under service conditions
Publisher: Elsevier BV
Date: 02-2012
Delamination fatigue growth in polymer-matrix fibre composites: A methodology for determining the design and lifing allowables
Publisher: Elsevier BV
Date: 07-2018
The role of energy related parameters in life enhancement procedures
Publisher: Elsevier BV
Date: 1989
Elastic-plastic finite element analysis of spall formation in gears
Publisher: Elsevier BV
Date: 09-1996
Tools and methods for addressing the durability of rolling stock
Publisher: Elsevier BV
Date: 12-2013
A methodology for structural optimisation with damage tolerance constraints
Publisher: Elsevier BV
Date: 08-2000
Application of the extended Kantorovich method to the vibration of clamped rectangular plates
Publisher: Elsevier BV
Date: 04-1976
Australian developments in the analysis of composite structures with material and geometric nonlinearities
Publisher: Elsevier BV
Date: 03-1998
Compression failures of damaged graphite epoxy laminates
Publisher: Elsevier BV
Date: 1985
Understanding delamination behaviour in a circular laminate
Publisher: Elsevier BV
Date: 05-1990
Potential failure mechanisms of bonded composite repairs for metal and concrete
Publisher: Elsevier BV
Date: 09-1994
Analysis of composite laminates and fibre composite repair schemes
Publisher: Elsevier BV
Date: 11-1981
The analysis of stress intensity factors in two interacting collinear asymmetric cracks in a finite plate
Publisher: Elsevier BV
Date: 02-2015
Reducing the effects of rivet holes on fatigue life by adhesive bonding
Publisher: Elsevier BV
Date: 05-1985
Examining the application of the Hartman-Schijve equation to the analysis of cyclic fatigue fracture of polymer-matrix composites
Publisher: Elsevier BV
Date: 12-2017
Three-dimensional fatigue-based structural design optimisation of fuel flow vent holes
Publisher: Elsevier BV
Date: 2009
The development of combination mechanical contact and thermal braking loads for railway wheel fatigue analysis
Publisher: Elsevier BV
Date: 08-2012
An engineering approach to the fracture assessment of hopper wagons
Publisher: Elsevier BV
Date: 06-2017
An investigation of the influence of rail chill on crack growth in a railway wheel due to braking loads
Publisher: Elsevier BV
Date: 2013
Composite repairs to bridge steels demystified
Publisher: Elsevier BV
Date: 06-2017
A simplified approach to the large amplitude vibration of plates and membranes
Publisher: Elsevier BV
Date: 02-1977
Bonded-composite repair of representative multi-site damage in a full-scale fatigue-test article
Publisher: Elsevier BV
Date: 08-1994
Finite element modeling to determine thermal residual strain distribution of bonded composite repairs for structural health monitoring design
Publisher: SPIE
Date: 11-2002
DOI: 10.1117/12.471968
Thermography as a tool for damage assessment
Publisher: Elsevier BV
Date: 02-2005
Thoughts on the scatter seen in cyclic Mode I fatigue delamination growth in DCB tests
Publisher: Elsevier BV
Date: 2017
On the mechanical behaviour of aging and recycled paper structures under cyclic humidity
Publisher: Elsevier BV
Date: 12-1999
Evaluation of spectrum fatigue crack growth using variable amplitude data
Publisher: Elsevier BV
Date: 2008
Fatigue based three-dimensional structural design optimisation studies implementing the generalised Frost–Dugdale crack growth law
Publisher: Elsevier BV
Date: 08-2008
An artificial PPR scaffold for programmable RNA recognition
Publisher: Springer Science and Business Media LLC
Date: 17-12-2014
DOI: 10.1038/NCOMMS6729
Abstract: Pentatricopeptide repeat (PPR) proteins control erse aspects of RNA metabolism in eukaryotic cells. Although recent computational and structural studies have provided insights into RNA recognition by PPR proteins, their highly insoluble nature and inconsistencies between predicted and observed modes of RNA binding have restricted our understanding of their biological functions and their use as tools. Here we use a consensus design strategy to create artificial PPR domains that are structurally robust and can be programmed for sequence-specific RNA binding. The atomic structures of these artificial PPR domains elucidate the structural basis for their stability and modelling of RNA-protein interactions provides mechanistic insights into the importance of RNA-binding residues and suggests modes of PPR-RNA association. The modular mode of RNA binding by PPR proteins holds great promise for the engineering of new tools to target RNA and to understand the mechanisms of gene regulation by natural PPR proteins.
Further thoughts on EIDS and the durability analysis of WAAM 18Ni 250 steel with rough surfaces
Publisher: Wiley
Date: 2023
DOI: 10.1111/FFE.13938
Analysis of cold-expansion for cracked and uncracked fastener holes
Publisher: Elsevier BV
Date: 1991
Transverse vibrations of shallow shells by the method of constant-deflection contours
Publisher: Acoustical Society of America (ASA)
Date: 11-1974
DOI: 10.1121/1.1903468
Abstract: A method for the analysis of vibration of shallow shells is presented. The method is based upon the concept of iso- litude contour lines on the vibrating surface of the shell. The problem of transient axisymmetric vibrations of shallow elliptical dome is investigated. It is shown that in the limiting case, when the elliptical dome reduces to the spherical dome, Reissner's well-known result is obtained.
Crack patching revisited
Publisher: Elsevier BV
Date: 11-2006
Repairs using fibre reinforced plastics
Publisher: CRC Press
Date: 14-01-1999
Low-velocity impacts on preloaded GFRP specimens with various impactor shapes
Publisher: Elsevier BV
Date: 11-2006
Topology optimisation of a bulkhead component used in aircrafts using an evolutionary algorithm
Publisher: Elsevier BV
Date: 2011
Structural optimisation with damage tolerance constraints
Publisher: Elsevier BV
Date: 03-2005
A finite element analysis of delamination behaviour in a circular laminate
Publisher: Elsevier BV
Date: 1989
On the Glinka and Neuber methods for calculating notch tip strains under cyclic load spectra
Publisher: Elsevier BV
Date: 10-2000
Determination of symmetric end-loadings from the bulk stress on the lateral surface of a rectangular prism
Publisher: Springer Science and Business Media LLC
Date: 1992
DOI: 10.1007/BF00370087
Unified constitutive model for thermoset adhesive, FM73
Publisher: Elsevier BV
Date: 07-1995
A Comparison of the Damage Tolerance of AA7075-T6, AA2024-T3, and Boeing Space, Intelligence, and Weapons Systems AM-Built LPBF Scalmalloy
Publisher: MDPI AG
Date: 20-08-2023
DOI: 10.3390/AEROSPACE10080733
Abstract: This paper first presents the results of an experimental study into the damage tolerance of AA7075-T6, which is widely used in both fixed- and rotary-wing aircraft, space structures, and laser bed powder fusion (LBPF) Scalmalloy specimens built by Boeing Space, Intelligence, and Weapons Systems. To this end, four single edge notch AA7075-T6 specimens and four identical single edge notch LBPF Scalmalloy specimens were tested. The resultant crack growth curves reveal that Boeing Space, Intelligence, and Weapons Systems AM-built Scalmalloy is more damage tolerant than conventionally built AA7075-T6. This finding leads to the observation that the da/dN versus ΔK curves associated with Scalmalloy and conventionally manufactured AA2024-T3 are similar. These findings highlight the potential for Boeing Space, Intelligence, and Weapons Systems AM-built Scalmalloy to be used to extend the operational lives of military aircraft by the on-demand printing of limited-life Scalmalloy replacement parts.
Delamination growth in polymer-matrix fibre composites and the use of fracture mechanics data for material characterisation and life prediction
Publisher: Elsevier BV
Date: 11-2017
Computing the growth of naturally-occurring disbonds in adhesively-bonded patches to metallic structures
Publisher: Elsevier BV
Date: 02-2016
Designing for damage-tolerant composite repairs
Publisher: Elsevier BV
Date: 1994
Designing for damage tolerant bonded joints
Publisher: Elsevier BV
Date: 1993
Is fatigue testing of impact damaged laminates necessary?
Publisher: Elsevier BV
Date: 1987
Design of structures for optimal static strength using ESO
Publisher: Elsevier BV
Date: 02-2005
Fatigue crack growth and damage tolerance
Publisher: Wiley
Date: 14-02-2014
DOI: 10.1111/FFE.12155
Lock-in infrared thermography for the evaluation of the structural performance of corrugated paperboard structures
Publisher: Elsevier BV
Date: 09-2010
Interaction of ultrasonic waves with structural damage: A diffraction analogy
Publisher: Elsevier BV
Date: 08-2006
Further studies in the application of the method of constant deflection lines to plate bending problems
Publisher: Elsevier BV
Date: 05-1975
A fibre optic corrosion fuse sensor using stressed metal-coated optical fibres
Publisher: Elsevier BV
Date: 05-2008
The Vlasov foundation model
Publisher: Elsevier BV
Date: 1977
On the use of supersonic particle deposition to restore the structural integrity of damaged aircraft structures
Publisher: Elsevier BV
Date: 09-2011
A study into the ability of SPD to restore the buckling strength and modes of rib stiffened panels with simulated stress corrosion cracks
Publisher: Emerald
Date: 06-02-2017
DOI: 10.1108/IJSI-09-2015-0037
Abstract: The purpose of this paper is to describe the results of a combined numerical and experimental study into the ability of supersonic particle deposition (SPD) to restore the load carrying capacity of rib stiffened wing planks with simulated stress corrosion cracking (SCC). In this context the experimental results reveal that SCC can result in a dramatic reduction in the load carrying capacity of the structure and catastrophic failure via cracking that tears the length of the structure through buckling. A combined numerical and experimental study then reveals how this reduction, in the load carrying capacity can be overcome by using SPD. This paper is the first to show that SPD can be used to restore the load carrying capacity of rib stiffened structures with SCC. It also shows that SPD repairs can be designed to have only a minimal effect on the local stiffness and hence on the load path. However, care should be taken to ensure that the design is such that premature failure of the SPD does not occur. This is the first paper to show that a thin layer of SPD deposited 7,075 aluminium alloy powder on either side of the SCC-simulated stiffener has the potential to restore the load carrying capability of a rib stiffened structure. As such it represents an important first step into establishing the potential for SPD to restore the buckling strength of rib stiffened wing panels containing SCC.
Repair of Multi-Site Damage
Publisher: Elsevier
Date: 2002
Health monitoring of composite repairs and joints using optical fibres
Publisher: Elsevier BV
Date: 11-2002
Fatigue crack growth in epoxy polymer nanocomposites
Publisher: The Royal Society
Date: 21-06-2021
Abstract: The present paper describes detailed analyses of experimental data for the cyclic-fatigue behaviour of epoxy nanocomposite polymers. It has been shown that the data may be interpreted using the Hartman–Schijve relationship to yield a unique, ‘master’, linear relationship for each epoxy nanocomposite polymer. By fitting the experimental data to the Hartman–Schijve relationship, two key materials parameters may be deduced: (i) the term A , which may be thought of as the fatigue equivalent to the quasi-static value of the fracture energy, G c , and (ii) the fatigue threshold value, Δ G thr , below which no significant fatigue crack growth (FCG) occurs. It has then been established that the values of these parameters, together with the slope, n , and intercept, D , of the Hartman–Schijve master relationship, may be used (i) to compute the experimental results measured for the fatigue behaviour of the epoxy nanocomposite polymers, (ii) to understand the observed fracture and fatigue behaviour of these materials with respect to the structure of the epoxy nanocomposite polymers, and (iii) to deduce the ‘upper-bound’, i.e. ‘worst-case’, FCG rate curve which may be used by industry as a material development, material selection, design and service-life prediction tool when these epoxy nanocomposite polymers are used in engineering applications such as structural adhesives and/or as matrices in fibre-reinforced composites. This article is part of a discussion meeting issue ‘A cracking approach to inventing new tough materials: fracture stranger than friction’.
Determination of arbitrary, non-shearing end-loadings from the bulk stress on the lateral surface of a rectangular prism
Publisher: Elsevier BV
Date: 02-1996
Weight functions for composite repairs to stiffened panels
Publisher: Elsevier BV
Date: 02-2004
A numerical study of two integral type elasto-plastic fracture parameters under cyclic loading
Publisher: Elsevier BV
Date: 1987
Thermomechanical behaviour of composites
Publisher: Springer Science and Business Media LLC
Date: 1989
DOI: 10.1007/BF01046942
The effect of size on the quantitative estimation of defect depth in steel structures using lock-in thermography
Publisher: AIP Publishing
Date: 15-05-2007
DOI: 10.1063/1.2732443
Abstract: An investigation into the effect of size on the quantitative estimation of defect depth in a steel specimen has been undertaken using lock-in thermography. Phase contrast measurements over circular defects of varying diameter and depth are presented for a range of excitation frequencies. It was found that the diameter of a defect had an appreciable effect on the observed phase angle which consequently has significant implications with regard to estimating defect depth. Phase contrast measurements for a range of defects in a 10mm steel specimen indicate that an excitation frequency of 0.02Hz is the optimal frequency for defect detection. Results obtained with an excitation frequency of 0.02Hz are used to discuss the limitations of determining the size and depth of defects. A finite element analysis was found to have good correlation with experimental data and thus demonstrates potential in providing improved estimates of defect depth.
Increasing the fatigue life of cracked fastener holes using bonded repairs
Publisher: Elsevier BV
Date: 04-1989
On the Vlasov and Kerr foundation models
Publisher: Springer Science and Business Media LLC
Date: 03-1976
DOI: 10.1007/BF01176928
A study into the interaction of intergranular cracking and cracking at a fastener hole
Publisher: Springer Science and Business Media LLC
Date: 12-12-2013
A study of the effect of CPCs on fatigue crack propagation in a representative fuselage lap joint specimen
Publisher: Elsevier BV
Date: 06-2012
Predicting the fatigue life and crack aspect ratio evolution in complex structures
Publisher: Elsevier BV
Date: 10-2006
Residual strength of impact-damaged composites
Publisher: Elsevier BV
Date: 1984
An equivalent block method for computing fatigue crack growth
Publisher: Elsevier BV
Date: 09-2008
Assessment of mechanical and fatigue crack growth properties of wire + arc additively manufactured mild steel components
Publisher: Wiley
Date: 20-07-2022
DOI: 10.1111/FFE.13797
Abstract: A study has been conducted to evaluate the mechanical and fatigue crack propagation properties of wire + arc additively manufactured ER70S‐6 components. A parallel‐built deposition strategy was employed to fabricate the additively manufactured wall. The hardness values were slightly higher at the bottom and top of the wall due to the presence of Widmanstätten ferrite and carbides. The characterization of mechanical properties in both orientations parallel and perpendicular to the deposition direction showed a marginal difference in yield strength and ultimate tensile strength. The crack growth rates were correlated with linear elastic fracture mechanics parameter Δ K and compared with an oscillation‐built deposition strategy from the literature. The crack growth rates of both deposition strategies were found to be very similar to each other. Furthermore, it has been demonstrated that the variability in the crack growth histories can be reasonably well captured by using the NASGRO crack growth equation.
Residual Strength Optimisation of a Vent Hole in an Aircraft Component Using a Heuristic Method
Publisher: Trans Tech Publications, Ltd.
Date: 07-2011
DOI: 10.4028/WWW.SCIENTIFIC.NET/AMR.275.105
Abstract: The paper presents application of damage tolerance optimisation principles to the design of industrial components. It is illustrated via design optimisation of a Fuel Flow Vent Hole (FFVH) located in the Wing Pivot Fitting (WPF) of an F-111 aircraft. The aim is to determine the shape of the cutout that will maximise its residual strength under the operating loading conditions. Damage tolerance shape optimisation is performed using a heuristic optimisation method known as the ‘Biological algorithm’. The maximum stress intensity factor (SIF) for all of the cracks around the boundary of the optimal cutout is found to be significantly lower compared to that of the initial shape. This shows that an improved residual (fracture) strength is achieved for the optimal designs. The variability in SIF around the cutout boundary is reduced, thereby making the shape more evenly fracture critical. The shapes of the residual strength optimal vent holes are found to depend on the initial crack sizes. It is also shown that a damage tolerance optimisation additionally produces a lighter WPF component design, which is highly desirable for aerospace industries.
An implicit algorithm using explicit correctors for the kinematic hardening model with multiple back stresses
Publisher: Wiley
Date: 2001
DOI: 10.1002/NME.111
NDTE using pulse thermography: Numerical modeling of composite subsurface defects
Publisher: Elsevier BV
Date: 09-2006
Understanding crack growth in fuselage lap joints
Publisher: Elsevier BV
Date: 02-2008
Three-dimensional structure optimal design for extending fatigue life by using biological algorithm
Publisher: Elsevier BV
Date: 02-2008
Crack patching: Predicting fatigue crack growth
Publisher: Elsevier BV
Date: 04-2006
Analysis of bonded repairs to damaged fibre composite structures
Publisher: Elsevier BV
Date: 1983
A Numerical Study into the Effect of Machining on the Interaction between Surface Roughness and Surface Breaking Defects on the Durability of WAAM Ti-6Al-4V Parts
Publisher: MDPI AG
Date: 29-06-2022
DOI: 10.3390/MET12071121
Abstract: The airworthiness certification of military aircraft requires a durability analysis be performed using linear elastic fracture mechanics (LEFM). Furthermore, such analyses need to use a valid small crack growth equation. This paper focuses on the effect of rough surfaces and the effect of machining the surface on the durability of AM parts using LEFM and a valid small crack growth equation for the material. To this end, this paper analyses the effect of surface roughness on wire and arc additively manufactured (WAAM) Ti-6Al-4V titanium parts and the effect of machining on the durability of a part. The analysis reveals that the life of the component is a relatively strong function of the degree of surface roughness, and that the durability of a specimen is a strong function of the local radius of the curvature of the trough. It also appears that surfaces with tall narrow roughness will not overly benefit from partial machining of the surface.
Repairs using fibre reinforced plastics
Publisher: Elsevier
Date: 1999
Numerical analysis of bonded repairs for fastener holes with three-dimensional cracks
Publisher: Elsevier BV
Date: 1989
Numerical analysis of subsurface crack failure beneath the pitch line of a gear tooth during engagement
Publisher: Elsevier BV
Date: 06-1995
Composite repairs to rib stiffened panels
Publisher: Elsevier BV
Date: 12-1999
Influence of cyclic stress intensity threshold on the scatter seen in cyclic Mode I fatigue delamination growth in DCB tests
Publisher: Elsevier BV
Date: 06-2017
Composite repairs to cracked holes under bi-axial loading
Publisher: Elsevier BV
Date: 07-2002
On the analysis of composite structures with material and geometric non-linearities
Publisher: Elsevier BV
Date: 12-2000
In situ health monitoring of bonded composite repairs using a novel fiber Bragg grating sensing arrangement
Publisher: SPIE
Date: 11-2002
DOI: 10.1117/12.471965
Finite Element Analysis of Patched Cracks
Publisher: Informa UK Limited
Date: 1979
Effect of debonding on adhesively bonded composite to metal joints in compression
Publisher: Elsevier BV
Date: 1986
Cyclic-fatigue crack growth in composite and adhesively-bonded structures: The FAA slow crack growth approach to certification and the problem of similitude
Publisher: Elsevier BV
Date: 07-2016
Modelling creep behaviour of orthotropic composites by the coincident element method
Publisher: Elsevier BV
Date: 10-2004
Experimental Studies into the Analysis Required for the Durability Assessment of 7075 and 6061 Cold Spray Repairs to Military Aircraft
Publisher: MDPI AG
Date: 19-08-2020
Abstract: This paper presents an experimental study into the analysis required for the durability assessment of 7075 and 6061 cold spray repairs to military aircraft. To this end, it is first shown that provided the bulk stress in a 7075 cold spray coating can be kept beneath approximately 150 MPa, then the coating should not crack. A range of ex les are presented in which the interface between the coating and the substrate only fails subsequent to crack growth in the substrate. We also show that failure of cold spray repaired/coated panels can also be due to the nucleation and growth of cracks in the substructure immediately adjacent to the coated/repaired region. As such, when performing a durability analysis for a cold spray repair, the growth of such small naturally occurring cracks, both at the interface and immediately adjacent to the ends of the coating, need to be accounted for.
A convenient way to represent fatigue crack growth in structural adhesives
Publisher: Wiley
Date: 29-09-2014
DOI: 10.1111/FFE.12241
Development of a 3D Biological method for fatigue life based optimisation and its application to structural shape design
Publisher: Elsevier BV
Date: 02-2009
Characterization of the durability of adhesive bonds
Publisher: Wiley
Date: 06-06-2012
Stiffness properties for Nucleus standard straight and contour electrode arrays
Publisher: Elsevier BV
Date: 10-2004
DOI: 10.1016/J.MEDENGPHY.2004.05.001
Abstract: Trauma and damage during insertion of electrode arrays into the human cochlea are strongly related to the stiffness of the array. The stiffness properties of electrode arrays, which were determined by three-point flexural bending and buckling tests, are reported in this paper. To date there has been limited publication on mechanical properties of these electrode arrays. Previous studies mainly focused on characterizing the stiffness of the tip of the Nucleus straight array with little emphasis on characterizing the stiffness of its whole length. In this study, stiffnesses of the Nucleus straight and contour electrode arrays have been determined along their length. Young's modulus of elasticity of the Nucleus straight array has been found to increase from the tip (182 MPa) to the rear end (491 MPa), whereas the stiffness of the contour array is greatest near the tip (480 MPa) and is fairly uniform in the middle and rear sections of the electrode array (380-400 MPa). Buckling experiments have shown that the contour array has much higher critical buckling load (about four times) than the Nucleus straight array. The results from three-point flexural bending and buckling experiments provide significant data for the development of electrode arrays, from which new array designs with improved flexibility can be developed. The results of stiffness properties are also important input for use in finite element models to predict the trajectories during insertion and to help evaluate the effects of different electrode array designs on damage sustained during insertion.
Thermomechanical assessment of damage in composites
Publisher: Elsevier BV
Date: 05-1990
An experimental investigation into the effect of impact damage on the compressive strength of step lap joints
Publisher: Elsevier BV
Date: 1989
A scientific evaluation of the approximate 2D theories for composite repairs to cracked metallic components
Publisher: Elsevier BV
Date: 2009
Analysis of bonded inserts for the repair of fastener holes
Publisher: Elsevier BV
Date: 1986
Eine geeignete Näherung für das Brechen von Fahrbahnen
Publisher: Springer Science and Business Media LLC
Date: 03-1978
DOI: 10.1007/BF01261191
Computing the Growth of Small Cracks in the Assist Round Robin Helicopter Challenge
Publisher: MDPI AG
Date: 14-07-2020
DOI: 10.3390/MET10070944
Abstract: Sustainment issues associated with military helicopters have drawn attention to the growth of small cracks under a helicopter flight load spectrum. One particular issue is how to simplify (reduce) a measured spectrum to reduce the time and complexity of full-scale helicopter fatigue tests. Given the costs and the time scales associated with performing tests, a means of computationally assessing the effect of a reduced spectrum is desirable. Unfortunately, whilst there have been a number of studies into how to perform a damage tolerant assessment of helicopter structural parts there is currently no equivalent study into how to perform the durability analysis needed to determine the economic life of a helicopter component. To this end, the present paper describes a computational study into small crack growth in AA7075-T7351 under several (reduced) helicopter flight load spectra. This study reveals that the Hartman-Schijve (HS) variant of the NASGRO crack growth equation can reasonably accurately compute the growth of small naturally occurring cracks in AA7075-T7351 under several simplified variants of a measured Black Hawk flight load spectra.
Intragrating strain sensing using a chirped FBG and an integration method
Publisher: IEEE
Date: 06-2007
Crack Growth in a Range of Additively Manufactured Aerospace Structural Materials
Publisher: MDPI AG
Date: 09-11-2018
Abstract: The aerospace industry is now beginning to adopt Additive Manufacturing (AM), both for new aircraft design and to help improve aircraft availability (aircraft sustainment). However, MIL-STD 1530 highlights that to certify airworthiness, the operational life of the airframe must be determined by a damage tolerance analysis. MIL-STD 1530 also states that in this process, the role of testing is merely to validate or correct the analysis. Consequently, if AM-produced parts are to be used as load-carrying members, it is important that the d a / d N versus ΔK curves be determined and, if possible, a valid mathematical representation determined. The present paper demonstrates that for AM Ti-6Al-4V, AM 316L stainless steel, and AM AerMet 100 steel, the d a / d N versus ΔK curves can be represented reasonably well by the Hartman-Schijve variant of the NASGRO crack growth equation. It is also shown that the variability in the various AM d a / d N versus Δ K curves is captured reasonably well by using the curve determined for conventionally manufactured materials and allowing for changes in the threshold and the cyclic fracture toughness terms.
On the three dimensional analysis of thick laminated plates
Publisher: Elsevier BV
Date: 05-1983
Crack growth and repair of multi-site damage of fuselage lap joints
Publisher: Elsevier BV
Date: 03-1993
On the determination of stress components in 3-d from thermoelastic data
Publisher: Elsevier BV
Date: 1990
Optimal topology design of industrial structures using an evolutionary algorithm
Publisher: Springer Science and Business Media LLC
Date: 12-01-2011
A crack opening displacement approach to crack patching
Publisher: Elsevier BV
Date: 1980
Strain-independent temperature measurements using a standard and a chirped fibre bragg grating
Publisher: IEEE
Date: 07-2006
Fatigue crack growth in a diverse range of materials
Publisher: Elsevier BV
Date: 07-2012
A preliminary study into the matrix dominated non-linear behaviour of graphite/epoxy laminates
Publisher: Elsevier BV
Date: 1995
Bonded repairs to rib stiffened wing skins
Publisher: Elsevier BV
Date: 07-2002
Numerical Analysis and Design
Publisher: Elsevier
Date: 2002
Evaluation of trajectories and contact pressures for the straight nucleus cochlear implant electrode array — a two-dimensional application of finite element analysis
Publisher: Elsevier BV
Date: 03-2003
DOI: 10.1016/S1350-4533(02)00150-9
Abstract: A two-dimensional (2D) finite element analysis has been used in this study to model the insertion of the Nucleus electrode array with different stiffness properties in order to evaluate the propensity of damage by visualizing the predicted trajectories and by comparing the buckling stresses and the contact pressures at the tip (and its distribution along the length) of the electrode array. Previous temporal bone studies have shown that damage during insertion of an electrode array around the basal turn of the cochlear spiral could be related to the design and the stiffness properties of the electrode array. However, it is difficult to evaluate different designs of electrode arrays purely by experimental methods as the experimental conditions and their results are difficult to reproduce. Three electrode arrays with different mechanical properties, i.e. uniform stiffness, graded stiffness, and a soft tip have been modelled. Buckling stress and contact pressure at the tip of the electrode array were found to be highest for the arrays with uniform stiffness. The contact pressures at the tip of the electrode array appeared strongly influenced by the stiffness profile and were optimal for graded stiffness. The results indicate the importance of the electrode array design and stiffness properties in minimizing trauma. However, there are a number of limitations in the present 2D evaluation which will require further analysis using a three-dimensional model to obtain definitive results.
Optical fibre sensors for health monitoring of bonded repair systems
Publisher: Elsevier BV
Date: 12-2000
A new approach to structural optimization
Publisher: Elsevier BV
Date: 1990
Modelling Crack Growth in Additively Manufactured Inconel 718 and Inconel 625
Publisher: MDPI AG
Date: 20-07-2023
DOI: 10.3390/MET13071300
Abstract: This paper first examines crack growth in a range of tests on additively manufactured (AM) and conventionally manufactured Inconel 718. It is shown that whereas when the crack growth rate (da/dN) is plotted as a function of the range of the stress intensity factor (ΔK), the crack growth curves exhibit considerable scatter/variability, when da/dN is expressed in terms of the Schwalbe crack driving force (Δκ), then each of the 33 different curves essentially collapse onto a single curve. This relationship appears to hold over approximately six orders of magnitude in da/dN. The same phenomenon also appears to hold for 20 room temperature tests on both conventionally and additively manufactured Inconel 625. Given that the 53 studies examined in this paper were taken from a wide cross section of research studies it would appear that the variability in the da/dN and ΔK curves can (to a first approximation) be accounted for by allowing for the variability in the fatigue threshold and the cyclic fracture toughness terms in the Schwalbe crack driving force. As such, the materials science community is challenged to address the fundamental science underpinning this observation.
Repair of mirage III aircraft using the BFRP crack-patching technique
Publisher: Elsevier BV
Date: 10-1984
Study of multi-site damage of fuselage lap joints
Publisher: Elsevier BV
Date: 09-1999
Determination of anti-symmetric end-loadings from volumetric stress on lateral surface of a rectangular bar
Publisher: Elsevier BV
Date: 12-1993
A design study in crack patching
Publisher: Elsevier BV
Date: 02-1981
Health monitoring of draglines using ultrasonic waves
Publisher: Elsevier BV
Date: 04-2004
Closure effects in delaminated graphite epoxy laminate under compression
Publisher: Elsevier BV
Date: 10-1987
A numerical study of MSD in aluminium alloys
Publisher: Elsevier BV
Date: 04-1995
Tools for Assessing the Damage Tolerance of Primary Structural Components
Publisher: Springer US
Date: 2009
On the potential of supersonic particle deposition to repair simulated corrosion damage
Publisher: Elsevier BV
Date: 03-2015
Damage tolerance analysis of a helicopter component
Publisher: Elsevier BV
Date: 06-2009
A hybrid formulation for 3D fracture analysis
Publisher: Elsevier BV
Date: 2002
A simple method based for computing crack shapes
Publisher: Elsevier BV
Date: 2016
A penalty finite element formulation for the analysis of composite structures
Publisher: Elsevier BV
Date: 1991
Implementation of a new algorithm for evaluating 3D fracture analysis
Publisher: Springer Science and Business Media LLC
Date: 2002
Observations on fatigue crack growth in a range of materials
Publisher: Elsevier BV
Date: 09-2011
Development of life extension strategies for Australian military aircraft, using structural health monitoring of composite repairs and joints
Publisher: Elsevier BV
Date: 10-2004
Life cycle analysis of steel railway bridges
Publisher: Elsevier BV
Date: 10-2018
Application of constitutive modelling and advanced repair technology to F111C aircraft
Publisher: Elsevier BV
Date: 10-2004
Piezomagnetic and piezoelectric poling effects on mode I and II crack initiation behavior of magnetoelectroelastic materials
Publisher: Elsevier BV
Date: 09-2003
Implementation of integration of differences method for extraction of temperature profiles along chirped fibre Bragg gratings
Publisher: IEEE
Date: 07-2006
Residual strength of impact damaged composites
Publisher: Springer Science and Business Media LLC
Date: 1984
DOI: 10.1007/BF00020278
An assessment of stress intensity factors for surface flaws in a tubular member
Publisher: Elsevier BV
Date: 02-2005
Recent developments in fatigue crack growth assessment
Publisher: Elsevier BV
Date: 12-2006
An experimental evaluation of crack face energy dissipation
Publisher: Elsevier BV
Date: 12-2006
Supersonic particle deposition as a means for enhancing the structural integrity of aircraft structures
Publisher: Elsevier BV
Date: 11-2014
Damage tolerance based design optimisation of a fuel flow vent hole in an aircraft structure
Publisher: Springer Science and Business Media LLC
Date: 24-06-2008
Lock-in thermographic inspection of squats on rail steel head
Publisher: Elsevier BV
Date: 03-2013
On the Growth of Fatigue Cracks from Material and Manufacturing Discontinuities Under Variable Amplitude Loading
Publisher: Springer Science and Business Media LLC
Date: 27-05-2015
On the analysis of bonded step lap joints
Publisher: Elsevier BV
Date: 10-2018
Theoretical Assessment of Cracking in Orthotropic Material under Symmetrical Heat Flow/Mechanical Loading
Publisher: MDPI AG
Date: 13-05-2022
Abstract: This paper studies a cracked orthotropic solid under symmetric heat flow, and symmetric mechanical loading is studied. A modified partially impermeable crack model is employed to simulate thermal load transfer. With the application of the Fourier transform technique and superposition theory, the related physical quantities and fracture parameters are obtained in explicit forms. The advantage of this paper is that the obtained solutions are explicitly closed. As a result, the calculation of the stress intensity factors of various cracks with different lengths becomes very convenient and fast. Some simple ex les are used to demonstrate the method provided in this paper. The analysis results show the dimensionless thermal resistance (ϖc) between the upper and lower crack regions and the proposed coefficient (ε) greatly influence the related physical quantities and fracture parameters. In addition, the numerical analysis results also revealed that the calculated results of fracture parameters at the crack tip will not be physically meaningful unless certain conditions are met.
Further Studies into Crack Growth in Additively Manufactured Materials
Publisher: MDPI AG
Date: 12-05-2020
DOI: 10.3390/MA13102223
Abstract: Understanding and characterizing crack growth is central to meeting the damage tolerance and durability requirements delineated in USAF Structures Bulletin EZ-SB-19-01 for the utilization of additive manufacturing (AM) in the sustainment of aging aircraft. In this context, the present paper discusses the effect of different AM processes, different build directions, and the variability in the crack growth rates related to AM Ti-6Al-4V, AM Inconel 625, and AM 17-4 PH stainless steel. This study reveals that crack growth in these three AM materials can be captured using the Hartman–Schijve crack growth equation and that the variability in the various da/dN versus ΔK curves can be modeled by allowing the terms ΔKthr and A to vary. It is also shown that for the AM Ti-6AL-4V processes considered, the variability in the cyclic fracture toughness appears to be greatest for specimens manufactured using selective layer melting (SLM).
Cracking in D6ac steel
Publisher: Elsevier BV
Date: 02-2010
Designing cutouts for optimum residual strength in plane structural elements
Publisher: Springer Science and Business Media LLC
Date: 04-2009
An analysis of delamination behaviour
Publisher: Elsevier BV
Date: 1986
A CAD-based on biological method for designing optimal fatigue life
Publisher: Springer Science and Business Media LLC
Date: 30-05-2008
Environmental evaluation of repairs to fuselage lap joints
Publisher: Elsevier BV
Date: 1992
Rail wheel removal and its implication on track life: A fracture mechanics approach
Publisher: Elsevier BV
Date: 08-2007
Bonded repairs to surface flaws
Publisher: Elsevier BV
Date: 10-1984
Bonded repair of metallic components: Thick sections
Publisher: Elsevier BV
Date: 02-1988
Application of the Hartman–Schijve equation to represent Mode I and Mode II fatigue delamination growth in composites
Publisher: Elsevier BV
Date: 03-2012
Additively manufactured Ti-6Al-4V replacement parts for military aircraft
Publisher: Elsevier BV
Date: 07-2019
Design of an all boron/epoxy doubler reinforcement for the F-111C wing pivot fitting: Structural aspects
Publisher: Elsevier BV
Date: 1989
Similitude and the Paris crack growth law
Publisher: Elsevier BV
Date: 10-2008
Crack growth in a naturally corroded bridge steel
Publisher: Wiley
Date: 22-12-2016
DOI: 10.1111/FFE.12568
Assessment of multiple flat elliptical cracks with interactions
Publisher: Elsevier BV
Date: 11-2002
Computing the Fatigue Life of Cold Spray Repairs to Simulated Corrosion Damage
Publisher: MDPI AG
Date: 09-08-2021
DOI: 10.3390/MA14164451
Abstract: This paper summarises the findings of an investigation into the durability of cold spray repairs, also known as supersonic particle deposition or SPD repairs, to simulated corrosion damage in AA7075-T7351 aluminium alloy specimens. A feature of this paper is that it is the first to show how to perform the mandatory durability analysis of repaired corroded structures, where the corroded material is first removed by machining and then repaired using cold spray, in a fashion consistent with the requirements delineated in USAF Structures Bulletin EZ-19-01, MIL-STD-1530D, and the US Joint Services Structural Guidelines JSSG2006.
Characterisation of pure and mixed mode fracture in composite laminates
Publisher: Elsevier BV
Date: 04-1987
Structural optimisation with fracture strength constraints
Publisher: Elsevier BV
Date: 09-2002
Fatigue crack growth discrepancies with stress ratio
Publisher: Elsevier BV
Date: 02-2009
Effects of plasticity on several fracture parameters for impact damage and related problems
Publisher: Elsevier BV
Date: 1991
Damage tolerance of graphite/epoxy composites
Publisher: Elsevier BV
Date: 1985
<title>Monitoring of crack growth beneath a bonded repair using Bragg gratings</title>
Publisher: SPIE
Date: 14-11-1997
DOI: 10.1117/12.293570
Localized strain measurements using an integration method to process intensity reflection spectra from a chirped FBG
Publisher: SPIE
Date: 04-07-2007
DOI: 10.1117/12.738392
Experimental studies into short crack growth
Publisher: Elsevier BV
Date: 10-2011
Weight functions, CTOD, and related solutions for cracks at notches
Publisher: Elsevier BV
Date: 02-2004
Application of the T*-integral and S criteria in finite element analysis of impact damage at fastener holes in graphite/epoxy laminates under compression
Publisher: Elsevier BV
Date: 1987
Residual strength of composites with multiple impact damage
Publisher: Elsevier BV
Date: 1994
Crack growth at fastener holes containing intergranular cracking
Publisher: Elsevier BV
Date: 03-2015
Application of infrared thermography to study crack growth and fatigue life extension procedures
Publisher: Wiley
Date: 29-09-2010
New thoughts on stropping cracks which emanate from holes
Publisher: Springer Science and Business Media LLC
Date: 08-1981
DOI: 10.1007/BF00036197
Fatigue crack growth in nano-composites
Publisher: Elsevier BV
Date: 05-2013
A study into crack growth in a railway wheel under thermal stop brake loading spectrum
Publisher: Elsevier BV
Date: 10-2012
Thermoelastic constant or thermoelastic parameter?
Publisher: Elsevier BV
Date: 1987
An imidazopiperidine series of CCR5 antagonists for the treatment of HIV: The discovery of N -{(1 S)-1-(3-fluorophenyl)-3-[(3- endo)-3-(5-isobutyryl-2- methyl-4,5,6,7-tetrahydro-1 H -imidazo[4,5- c ]pyridin-1-yl)-8-azabicyclo[3.2.1] oct-8-yl]propyl}acetamide (PF-232798)
Publisher: American Chemical Society (ACS)
Date: 03-12-2011
DOI: 10.1021/JM100978N
Abstract: Preventing entry of HIV into human host cells has emerged as an attractive approach to controlling viral replication. Maraviroc 1 is an approved antagonist of the human CCR5 receptor which prevents the entry of HIV. Herein, we report the design and discovery of a series of imidazopiperidine CCR5 antagonists which retain the attractive antiviral profile and window over hERG activity of maraviroc 1, combined with improved absorption profiles in rat and dog. Furthermore, this series of compounds has been shown to retain activity against a laboratory generated maraviroc-resistant HIV-1 strain, which indicates an alternative resistance profile to that of maraviroc 1. Compound 41f (PF-232798) was selected as a clinical candidate from the imidazopiperidine series and is currently in phase II clinical trials.
Characterising crack growth in commercially pure titanium
Publisher: Elsevier BV
Date: 04-2021
Distinct Advantages of Circumferential Notch Tensile (CNT) Testing in the Determination of a Threshold for Stress Corrosion Cracking (KISCC)
Publisher: MDPI AG
Date: 27-09-2021
DOI: 10.3390/MA14195620
Abstract: Stress corrosion cracking (SCC) is a vexing problem for load-bearing equipment operating in a corrosive environment in various industries, such as aerospace, chemical and mineral processing, civil structures, bioimplants, energy generation etc. For safe operation, effective maintenance and life prediction of such equipment, reliable design data on SCC (such as threshold stress intensity for SCC, i.e., KISCC) are invaluable. Generating reliable KISCC data invariably requires a large number of tests. Traditional techniques can be prohibitively expensive. This article reviews the determination of KISCC using the circumferential notch tensile (CNT) technique, the validation of the technique and its application to a few industrially relevant scenarios. The CNT technique is a relatively recent and considerably inexpensive approach for the determination of KISCC when compared to traditional techniques, viz., double-cantilever beam (DCB) and compact tension (CT) that may be fraught with prohibitive complexities. As established through this article, the CNT technique circumvents some critical limitations of the traditional techniques.
A stress versus crack growth rate investigation (aka stress – cubed rule)
Publisher: Elsevier BV
Date: 06-2016
Determination of the position of a localized heat source within a chirped fibre Bragg grating using a Fourier transform technique
Publisher: IOP Publishing
Date: 02-05-2006
A review of composite product data interoperability and product life-cycle management challenges in the composites industry
Publisher: Informa UK Limited
Date: 02-10-2017
The response of composite structures with pre-stress subject to low velocity impact damage
Publisher: Elsevier BV
Date: 10-2004
Studies in the matrix dominated failures of composite joints
Publisher: Elsevier BV
Date: 1999
Crack growth in conventionally manufactured pure nickel, titanium and aluminum and the cold spray additively manufactured equivalents
Publisher: Elsevier BV
Date: 12-2022
Implications of the lead crack philosophy and the role of short cracks in combat aircraft
Publisher: Elsevier BV
Date: 04-2013
Three-dimensional structural design optimisation based on fatigue implementing a genetic algorithm and a non-similitude crack growth law
Publisher: Elsevier BV
Date: 2009
Crack growth of physically small cracks
Publisher: Elsevier BV
Date: 09-2007
Thermoelastic assessment of damage growth in composites
Publisher: Elsevier BV
Date: 1989
On the analysis of cracking under a combined quadratic thermal flux and a quadratic mechanical loading
Publisher: Elsevier BV
Date: 04-2019
Assessment of the effect of impact damage in composites: Some problems and answers
Publisher: Elsevier BV
Date: 04-1988
Modelling of the lock-in thermography process through finite element method for estimating the rail squat defects
Publisher: Elsevier BV
Date: 03-2013
Determination of the stress components of an array of piezoelectric sensors: a numerical study
Publisher: IOP Publishing
Date: 04-1997
Fracture Analysis for a Crack in Orthotropic Material Subjected to Combined 2i-Order Symmetrical Thermal Flux and 2j-Order Symmetrical Mechanical Loading
Publisher: MDPI AG
Date: 04-03-2021
Abstract: The problems of crack formation in orthotropic materials under 2i order polynomial function heat flow and 2j order polynomial function mechanical loading are considered. An extended local insulation crack model is proposed, and fracture analysis is carried out for the above problems. Utilizing Fourier transform technique (FTT) and principle of superposition, the jumps of temperature, elastic displacements on the crack, and so on are obtained. The advantage of this analysis is that the explicit closed form solutions of main parameters in classical fracture mechanics, i.e., the stress intensity factor, the energy release rate, and the energy density have been presented. A simple ex le is used to demonstrate the method proposed in this paper. The analysis results show that the non-dimensional thermal conductivity and the combined ratio of the heat flux per thickness perpendicular to the crack surface to the mechanical load have a great influence on the calculation of fracture parameters. Only when they meet certain conditions can the correct fracture parameter calculation results be obtained.
A numerical study of adhesively bonded lap joints
Publisher: Elsevier BV
Date: 10-1992
Crack size and speed interaction characteristics at micro-, meso- and macro-scale
Publisher: Elsevier BV
Date: 03-2003
Computing the durability of WAAM 18Ni 250 maraging steel specimens
Publisher: Wiley
Date: 29-08-2022
DOI: 10.1111/FFE.13828
Abstract: MIL‐STD 1530D requires that the certification of an aircraft part employ analytical tools that are capable of modeling crack growth. It is further stated that the durability and damage tolerance (DADT) analyses should be based on linear elastic fracture mechanics (LEFM) and follow a building block approach. This paper illustrates the durability analysis required to certify an additively manufactured part by using the ex les of durability tests performed on two wire arc additively manufactured (WAAM) 18Ni 250 Maraging steel specimens.
Crack growth from naturally occurring material discontinuities under constant amplitude and operational loads
Publisher: Elsevier BV
Date: 10-2016
Crack Growth from Naturally Occurring Material Discontinuities in Operational Aircraft
Publisher: Elsevier BV
Date: 2015
Vibration and buckling of plates at elevated temperatures
Publisher: Elsevier BV
Date: 1980
From NASGRO to fractals: Representing crack growth in metals
Publisher: Elsevier BV
Date: 2016
Effects of temperature on the shear stress-strain behaviour of structural adhesives (FM73)
Publisher: Elsevier BV
Date: 11-1994
Optimisation of damage tolerant structures using a 3D biological algorithm
Publisher: Elsevier BV
Date: 04-2006
Behavior of floating ice sheets
Publisher: Elsevier BV
Date: 1977
Crack Patching: Analysis and Design
Publisher: Informa UK Limited
Date: 1982
Similitude: Fatigue cracking in steels
Publisher: Elsevier BV
Date: 10-2007
Repair of impact damaged composites
Publisher: Elsevier BV
Date: 1992
On the USAF ‘risk of failure’ approach and its applicability to composite repairs to metal airframes
Publisher: Elsevier BV
Date: 05-2017
An approximate expression for the fundamental frequency of vibration of elastic plates
Publisher: Elsevier BV
Date: 02-1975
An approach based on biological algorithm for three-dimensional shape optimisation with fracture strength constrains
Publisher: Elsevier BV
Date: 09-2008
Stress intensity factor solutions for finite body with quarter-elliptical flaws emanating from a notch
Publisher: Elsevier BV
Date: 06-2005
Assessment of the effect of impact damage in composites: Some problems and answers
Publisher: Elsevier BV
Date: 1988
The influence of cyclic stress intensity threshold on fatigue life scatter
Publisher: Elsevier BV
Date: 2016
Structural optimisation of 3D damage tolerant components comparing the biological and genetic algorithm solutions
Publisher: Elsevier BV
Date: 04-2009
Assessment of partly circumferential cracks in pipes
Publisher: Springer Science and Business Media LLC
Date: 05-2005
Mode I, II and Mixed Mode I/II delamination growth in composites
Publisher: Elsevier BV
Date: 04-2014
NDI of Rail Squats and Estimating Defect Size and Location Using Lock-In Thermography
Publisher: Scientific Research Publishing, Inc.
Date: 2013
Synchrotron radiation microcomputed tomography for assessing internal cracks in cold spray repairs
Publisher: Wiley
Date: 06-01-2020
DOI: 10.1111/FFE.13172
Designing for tolerance to impact damage at fastener holes in graphite/epoxy laminates under compression
Publisher: Elsevier BV
Date: 02-1986
An experimental description of the response of paper
Publisher: Elsevier BV
Date: 09-1996
The effect of impactor shape on the impact response of composite laminates
Publisher: Elsevier BV
Date: 02-2005
A unified constitutive theory for paper
Publisher: Elsevier BV
Date: 05-1998
Computing the Durability of WAAM 18Ni-250 Maraging Steel Specimens with Surface Breaking Porosity
Publisher: MDPI AG
Date: 03-03-2023
Abstract: The durability assessment of additively manufactured parts needs to account for both surface-breaking material discontinuities and surface-breaking porosity and how these material discontinuities interact with parts that have been left in the as-built state. Furthermore, to be consistent with the airworthiness standards associated with the certification of metallic parts on military aircraft the durability analysis must be able to predict crack growth, as distinct from using a crack growth analysis in which parameters are adjusted so as to match measured data. To partially address this, the authors recently showed how the durability of wire arc additively manufactured (WAAM) 18Ni-250 maraging steel specimens, where failure was due to the interaction of small surface-breaking cracks with surface roughness, could be predicted using the Hartman–Schijve variant of the NASGRO crack growth equation. This paper illustrates how the same equation, with the same material parameters, can be used to predict the durability of a specimen where failure is due to surface-breaking porosity.
A simple method for calculating the stress intensity factors for complex 3D cracks at a notch
Publisher: Elsevier BV
Date: 06-2016
Application of supersonic particle deposition to enhance the structural integrity of aircraft structures
Publisher: Springer Science and Business Media LLC
Date: 16-12-2013
Review of Requirements for the Durability and Damage Tolerance Certification of Additively Manufactured Aircraft Structural Parts and AM Repairs
Publisher: MDPI AG
Date: 15-03-2020
DOI: 10.3390/MA13061341
Abstract: The USAF requirements for the durability and damage tolerance certification for additively manufactured (AM) aircraft structural parts, which are detailed in Structures Bulletin EZ-19-01, raise a number of new and, as yet, unanswered questions. The present paper attempts to address three questions: How to perform a fracture mechanics-based analysis of crack growth in an AM part so as to account for the residual stresses, how to perform a fracture mechanics-based durability analysis of a cold spray repair so as to account for both the induced residual stresses and the presence of multiple co-located cracks, and how to perform a fracture mechanics-based durability analysis of an AM part so as to account for the presence of multiple collocated surface braking cracks. In this context, the present paper reveals the potential of the Hartman–Schijve variant of the NASGRO crack growth equation to accurately predict the growth of each of the in idual (collocated) cracks that arose in a cold spray-repaired specimen and in a specimen from a crack that nucleated and grew from a rough surface.
Adhesively bonded joints under cyclic loading spectra
Publisher: Wiley
Date: 02-2002
Neutral axis offset effects due to crack patching
Publisher: Elsevier BV
Date: 1983
Requirements and Variability Affecting the Durability of Bonded Joints
Publisher: MDPI AG
Date: 23-03-2020
DOI: 10.3390/MA13061468
Abstract: This paper firstly reveals that when assessing if a bonded joint meets the certification requirements inherent in MIL-STD-1530D and the US Joint Services Standard JSSG2006 it is necessary to ensure that: (a) There is no yielding at all in the adhesive layer at 115% of design limit load (DLL), and (b) that the joint must be able to withstand design ultimate load (DUL). Secondly, it is revealed that fatigue crack growth in both nano-reinforced epoxies, and structural adhesives can be captured using the Hartman–Schijve crack growth equation, and that the scatter in crack growth in adhesives can be modelled by allowing for variability in the fatigue threshold. Thirdly, a methodology was established for estimating a valid upper-bound curve, for cohesive failure in the adhesive, which encompasses all the experimental data and provides a conservative fatigue crack growth curve. Finally, it is shown that this upper-bound curve can be used to (a) compare and characterise structural adhesives, (b) determine/assess a “no growth” design (if required), (c) assess if a disbond in an in-service aircraft will grow and (d) to design and life in-service adhesively-bonded joints in accordance with the slow-growth approach contained in the United States Air Force (USAF) certification standard MIL-STD-1530D.
Characteristics of the design surface of damage tolerance parameters and their relation to shape optimisation
Publisher: Elsevier BV
Date: 2015
Combined effect of both surface finish and sub‐surface porosity on component strength under repeated load conditions
Publisher: Wiley
Date: 19-08-2020
DOI: 10.1002/ENG2.12248
Abstract: High duty engineering component life is usually demonstrated through extensive testing and statistical analysis applied to empirical curve‐fit equations. Because of this, the extent of the testing required is huge and costly: it must consider the load cycle range and test to high numbers of cycles. Additive Manufacturing (AM) for high duty components has brought to the fore the question of the effect of porosity and surface roughness on fatigue life, and how the true life of a critical component can be assessed conservatively. The authors propose the first step toward the development of a fatigue model based on well‐established engineering physics principles, by creating computational specimens with modeled surface roughness and porosity, and subjected to cyclic loading using Finite Element Analysis. They show that the combination of roughness features and sub‐surface pores leads to an equivalent plastic strain distribution pattern that suggests an emergent physical process that has not been reported before, and which indicates that the component strength and life reduction arising from surface roughness can be made significantly worse by the presence of porosity. The development of such phenomenological understanding should lead to improved life prediction techniques, more cost effective test procedures, and the development of better AM methods.
An experimental evaluation of fatigue crack growth
Publisher: Elsevier BV
Date: 02-2005
Thermal Considerations in the Patching of Metal Sheets with Composite Overlays
Publisher: Informa UK Limited
Date: 1980
Finite Element Method Study on the Squats Growth Simulation
Publisher: Scientific Research Publishing, Inc.
Date: 2013
The USAF characteristic K approach for cracks growing from small material discontinuities under combat aircraft and civil aircraft load spectra
Publisher: Elsevier BV
Date: 10-2017
Fatigue life enhancement of structures using shape optimisation
Publisher: Elsevier BV
Date: 12-2009
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