Low‐cycle fatigue delamination initiation and propagation in fibre metal laminates

Mazaheri, Firoozmehr; Hosseini‐Toudeshky, Hossein

doi:10.1111/ffe.12254

Cited by 14 publications

(10 citation statements)

References 43 publications

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“…• Numerical simulation model incorporated with real time material data accurately predicts the stress intensity factor range with less than 2% error. • An empirical mathematical model presented in Eqs (13) and (18) accurately predicts the intercept and slope of different FML given the fatigue life of metal.…”

Section: O N C L U S I O N Smentioning

confidence: 99%

“…Fibre metal laminates are commonly produced by autoclave process but nowadays a process called Vacuum Assisted Resin Transfer Moulding (VARTM) is becoming more popular because of its ability to produce high‐quality reinforced composite products at low cost . During fabrication of these laminates, mechanical, chemical, electrochemical and dry surface treatments are applied to metal sheets prior to adhesive bonding . These treatments promote different adhesion mechanisms like chemisorption, physisorption and mechanical interlocking which not only improves the adhesive bond strength but also influence its failure mechanism by improving its structural integrity …”

Section: Introductionmentioning

confidence: 99%

“…[9][10][11][12] During fabrication of these laminates, mechanical, chemical, electrochemical and dry surface treatments are applied to metal sheets prior to adhesive bonding. 1,13,14 These treatments promote different adhesion mechanisms like chemisorption, physisorption and mechanical interlocking which not only improves the adhesive bond strength but also influence its failure mechanism by improving its structural integrity. 15 Aerospace components are subjected to fatigue loads throughout their service life.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Investigation of fatigue crack growth rate in CARALL, ARALL and GLARE

Asghar

Nasir

Qayyum

et al. 2017

Fatigue Fract Eng Mat Struct

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Fibre metal laminates (FMLs) are being used to manufacture many structural components in aerospace industry because of their very high strength to weight ratios, yet the exact model for estimating fatigue crack propagation in FMLs cannot be developed because of many variable parameters affecting it. In this research, tensile strength, fatigue life and fracture toughness values of 2/1 configuration carbon reinforced aluminium laminate (CARALL), aramid reinforced aluminium laminate and glass laminate aluminium reinforced epoxy specimens have been investigated. Mechanical, chemical and electrochemical surface treatments were applied to AA 1050 face sheets to improve the adhesive properties of the laminates. The specimens were prepared using vacuum assisted resin transfer moulding technique and were cut to desired shapes. Fatigue tests were conducted on centre notched specimens according to ASTM Standard E399. Real time material data and properties of adhesive were used in definition of numerical simulation model to obtain the values of stress intensity factor at different crack lengths. It was observed that CARALL shows very superior tensile and fatigue strength because of stress distribution during failure. Numerical simulation model developed in this research accurately predicts fracture toughness of aramid reinforced aluminium laminate, CARALL and glass laminate aluminium reinforced epoxy with less than 2% error. An empirical analytical model using experimental data obtained during research was developed which accurately predicts the trend of FMLs fatigue life.

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Section: O N C L U S I O N Smentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Investigation of fatigue crack growth rate in CARALL, ARALL and GLARE

Asghar

Nasir

Qayyum

et al. 2017

Fatigue Fract Eng Mat Struct

View full text Add to dashboard Cite

show abstract

“…Mazahari and Hosseini-Toudeshiky in [84] present a three-dimensional element for Ansys based on cohesive zone model formulation which included mixed-mode bilinear elastic-plastic-damage constitutive law. The authors of mentioned work proposed a solution that can be valid in lowcycled fatigue contrary to a proposition based on the Paris law valid mostly in the high-cycled regime.…”

Section: Numerical Simulation Of the Fatigue Behavior Of Fmlsmentioning

confidence: 99%

A Review on Finite-Element Simulation of Fibre Metal Laminates

Smolnicki

Lesiuk

Duda

et al. 2022

Arch Computat Methods Eng

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Fibre metal laminates (FML) are layered materials consisting of both metal and reinforced composite layers. Due to numerous possibilities of configuration, constituent materials, etc., designing and testing such materials can be time- and cost-consuming. In addition to that, some parameters cannot be obtained directly from the experiment campaign. These problems are often overcome by using numerical simulation. In this article, the authors reviewed different approaches to finite element analysis of fibre metal laminates based on published articles and their own experiences. Many aspects of numerical modelling of FMLs can be similar to approaches used for classic laminates. However, in the case of fibre metal laminates, the interface between the metal and the composite layer is very relevant both in experimental and numerical regard. Approaches to modelling this interface have been widely discussed. Numerical simulations of FMLs are often complementary to experimental campaigns, so an experimental background is presented. Then, the software used in numerical analysis is discussed. In the next two chapters, both static and fatigue failure modelling are discussed including several key aspects like dimensionality of the model, approaches to the material model of constituents and holistic view of the material, level of homogenization, type of used finite elements, use of symmetry, and more. The static failure criteria used for both fibres and matrix are discussed along with different damage models for metal layers. In the chapter dedicated to adhesive interface composite—metal, different modelling strategies are discussed including cohesive element, cohesive surfaces, contact with damage formulation and usage of eXtended Finite Element Method. Also, different ways to assess the failure of this layer are described with particular attention to the Cohesive Zone Model with defined Traction–Separation Law. Furthermore, issues related to mixed-mode loading are presented. In the next chapter other aspects of numerical modelling are described like mesh sensitivity, friction, boundary conditions, steering, user-defined materials, and validation. The authors in this article try to evaluate the quality of the different approaches described based on literature review and own research.

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“…Crocombe and Sugiman [25] conducted experimental and numerical investigations on metal laminate (ML) and Glare ® laminates with doublers under fatigue tension loading, using the cohesive zone model proposed by Khoramishad et al [24] for the simulation of damage evolution at interfaces. More recently Hosseini-Mazaheri and Toudeshky [26] developed an elastic-plastic-damage constitutive law to simulate delamination initiation and propagation in FMLs; however this model was limited to a low-cycle fatigue loading regime.…”

Section: Introductionmentioning

confidence: 99%

A modified cohesive zone model for fatigue delamination in adhesive joints: Numerical and experimental investigations

Al-Azzawi

Kawashita

Featherston

2019

Composite Structures

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A modified cohesive zone model (CZM) has been developed to simulate damage initiation and evolution in Fibre-Metal Laminates (FMLs) manufactured in-house but based on the Glare ® material specifications. Specimens containing both splice and doubler features under high cycle fatigue loading. The model uses a novel trapezoidal traction-separation law to describe the elastic-plastic behaviour of this material under monotonic and high-cycle fatigue loading. The model is implemented in the software Abaqus/Explicit via an user-defined cohesive material subroutine. Several models of increasing complexity were investigated to validate the proposed approach. A two-stage experimental testing programme was then conducted to validate the numerical analyses. Firstly, quasi-static tests were used to determine the ultimate tensile strength (UTS) of a series of specimens with and without internal features. Secondly, high-cycle fatigue tests were conducted on both laminate types with variable load amplitude so that S-N curves could be built. Tests were monitored using digital image correlation (DIC) for full-field strain mapping and acoustic emission (AE) sensing to detect the initiation and propagation of damage during quasi-static and fatigue tests. Good correlation was observed between predicted onset and growth of delaminations and the history of cumulative AE energy during the tests, which supports the validity of the cohesive modelling approach for FMLs.

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Low‐cycle fatigue delamination initiation and propagation in fibre metal laminates

Cited by 14 publications

References 43 publications

Investigation of fatigue crack growth rate in CARALL, ARALL and GLARE

Investigation of fatigue crack growth rate in CARALL, ARALL and GLARE

A Review on Finite-Element Simulation of Fibre Metal Laminates

A modified cohesive zone model for fatigue delamination in adhesive joints: Numerical and experimental investigations

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