Lay-up optimisation of fibre metal laminates based on fatigue crack propagation and residual strength

Sen, Indrani; Alderliesten, R.C.; Benedictus, Rinze

doi:10.1016/j.compstruct.2014.12.060

Cited by 29 publications

(20 citation statements)

References 22 publications

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“…Nowadays, FMLs are extensively being used by aerospace industry, for example in manufacturing fuselage of Airbus A380, lower wing skin panels of previous Fokker 27 aircraft and cargo door of Boeing C‐17 . Research is being carried out to develop FMLs having even higher strength to weight ratios which might be used to manufacture futuristic aircrafts and structures …”

Section: Introductionmentioning

confidence: 99%

“…6,7 Research is being carried out to develop FMLs having even higher strength to weight ratios which might be used to manufacture futuristic aircrafts and structures. 8 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. [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.…”

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

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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: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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

“…Although this research has brought a lot of knowledge and insight, it has only a limited contribution to the application of this structural concept so far . Recent studies have illustrated that the design space of Fiber Metal Laminates despite theoretically unlimited, is practically constrained . One constraint identified is that most of the developed theories cannot be reversed into a form, where predicted performance is used as input following from design requirements.…”

Section: Fiber Metal Laminatesmentioning

confidence: 99%

“…This knowledge may aid in optimization studies for hybridizing structures. However, optimization requires a different formulation of theories compared to the currently available forms . These theories relate the performance or property to the known load case and preselected laminate configuration, while optimizations aim to identify the laminate configuration based on required performance in relation to identified load cases.…”

Section: Introductionmentioning

confidence: 99%

The Challenge of Reversing Theories to Hybridize Structures with Fiber Metal Laminate Design Concepts

Alderliesten

2018

Adv Eng Mater

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To further optimize aeronautical structures, an increased level of material hybridization is required. Optimization efforts aim to identify optimal design solutions that satisfy prescribed requirements. However, this demands reversal of currently available knowledge on hybrid structural technologies, which are often formulated as theories predicting performance based on known load cases and selected material configurations. After briefly reviewing the available fundamental theories for strength, fatigue, and damage tolerance of hybrid structures, this paper discusses the challenges in reversing these theories. Solutions are proposed in which theories can be approximated to significantly reduce the computational time while maintaining the required level of accuracy.

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“…In general, carbon‐based FMLs have superior characteristics, such as concerns energy‐absorption capacity, yield strength, tensile modulus, and fatigue strength, in comparison with aramid or glass fibre–based FMLs . FLMs present another exceptional peculiarity; mechanical properties can be easily tailored to specific requirements by changing the composite ply orientation, the thickness, and the number of layers; moreover, is some cases, they can simplify the manufacturing process …”

Section: Introductionmentioning

confidence: 99%

Flexural strength of aluminium carbon/epoxy fibre metal laminates

Bellini

Cocco

Iacoviello

et al. 2019

Mat Design Process Comm

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Fibre‐metal laminate (FML) is a material constituted by composite laminae and metal sheets, whose mechanical properties can be tailored by varying the thickness and the number of layers. For this reason, in the present work different types of FML made of carbon‐fibre–reinforced polymer and aluminium sheets were produced and tested; in particular, the influence of both the layer thickness and the layer adhesion was analysed through three‐point bending tests. It was found that both the abovementioned factors influenced the flexural strength of FML; precisely, the presence of an adhesive layer between the composite plies and the metal sheet made the flexural strength decrease, while this mechanical parameter increased passing from two metal sheets to only one.

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Lay-up optimisation of fibre metal laminates based on fatigue crack propagation and residual strength

Cited by 29 publications

References 22 publications

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

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

The Challenge of Reversing Theories to Hybridize Structures with Fiber Metal Laminate Design Concepts

Flexural strength of aluminium carbon/epoxy fibre metal laminates

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