A review: Fibre metal laminates, background, bonding types and applied test methods

Sınmazçelik, Tamer; Avcu, Egemen; Bora, Mustafa Özgür; Çoban, Onur

doi:10.1016/j.matdes.2011.03.011

Cited by 810 publications

(431 citation statements)

References 114 publications

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“…the aerospace and wind energy industries. Amongst these, fibre metal laminates (FMLs) have attracted considerable attention because of their outstanding mechanical performance including excellent fatigue, fracture and impact properties [1][2][3][4]. FMLs are constructed by stacking and adhesively bonding together relatively thin layers of metals and fibre-reinforced polymeric composites.…”

Section: Introductionmentioning

confidence: 99%

High-velocity impact deformation and perforation of fibre metal laminates

et al. 2017

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The quasi-static flexural and impact performance, up to projectile impact velocities of about 270 m s -1 , of fibre metal laminates (FMLs), which consist of relatively thin, alternately stacked, layers of an aluminium alloy and a thermoset glass fibre epoxy composite, have been investigated. The effects of varying (a) the yield strength, tensile strength and ductility of the aluminium alloy layer, (b) the surface treatment used for the aluminium alloy layers and (c) the number of layers present in the FML have been studied. It was found that increasing the strength of the aluminium alloy increases the quasi-static flexural strength of the FML, providing that good adhesion is achieved between the metal and the composite layers. Further, increasing the number of alternating layers of the aluminium alloy and fibre composite also somewhat increases the quasi-static flexural properties of the FML. In contrast, increasing the strength of the aluminium alloy had relatively little effect on the impact perforation resistance of the FML, but increasing the number of alternating layers of aluminium alloy and fibre composite did significantly increase the impact perforation resistance of the FML. The degree of adhesion achieved between the layers had only a negligible influence on the impact perforation resistance.

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Section: Introductionmentioning

confidence: 99%

High-velocity impact deformation and perforation of fibre metal laminates

et al. 2017

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“…The governing equation is shown in equation (1), and the detail procedure could be found from Ref [10]. The stress in aluminum layer is composed of internal stress due to applied stress to the laminate and the tensile curing stress due to the different thermal expansion coefficient [14].…”

Section: Stress In Al Layersmentioning

confidence: 99%

Fatigue in Fiber-Metal Laminates for Small Wind Turbine Blades Application

Sai

Chai

2018

MATEC Web Conf.

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Abstract. A methodology to study the fatigue of a wind turbine blade in a 10KW small wind turbine is proposed in this paper. Two working conditions (namely normal fatigue operation condition and extreme wind condition) are considered based on IEC61400-2. The maximum load calculated from both cases were used as a reference to perform material sample fatigue study. Fiber-metal laminate -GLARE 3/2 with a centre 1mm notch on the external aluminium layers was modelled based on fracture mechanics approach to calculate the stress intensity factor and fatigue crack growth rate at maximum applied stress of 240Mpa. GLARE panel fabrication and tensile tests were included. The fatigue tests were performed on unnotched samples with stress range from 80Mpa to 300Mpa and plotted into S-N curve.

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“…The FML concept was originally proposed for fatigue critical applications. While with its development, some potential advantages over the conventional metal alloys and fiber reinforced composites in structural components applications have also been recognized, which usually in terms of the high strength and excellent resistance to impact, corrosion and moisture [2][3][4][5].…”

Section: Introductionmentioning

confidence: 99%

Local Reinforcement in Notched Fiber Metal Laminates by Bonding Titanium Patch

et al. 2017

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Abstract. In order to reduce the stress concentration in notched fiber metal laminate (FML) and improve its damage tolerance, the local reinforcement concept was employed in present paper. Two different reinforced structures were proposed by bonding titanium patch on single side or double sides of the standard glass fiber reinforced aluminum laminate (GLARE). Tensile tests were conducted on these reinforced GLARE, and their mechanical properties were compared for evaluating the reinforced effect of titanium patch, as well as the damage behavior which dominated the mechanical response was analysed later to capture the failure mechanism of the reinforced GLARE. The reinforced effect of titanium patch on mechanical response of GLARE laminate was usually characterized by the improvements of modulus and yield strength, as well as the significant increase of ultimate strain and strength. Cohesive failure and adhesive failure were detected in the adhesive between titanium patch and GLARE laminate, where the adhesive failure corresponded to the weak reinforced case. In addition, the variation of delamination in GLARE laminate was also closely related to the reinforced effect on mechanical response. It is expected that the present investigation can provide technical support for damage tolerance design of fiber metal laminates.

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A review: Fibre metal laminates, background, bonding types and applied test methods

Cited by 810 publications

References 114 publications

High-velocity impact deformation and perforation of fibre metal laminates

High-velocity impact deformation and perforation of fibre metal laminates

Fatigue in Fiber-Metal Laminates for Small Wind Turbine Blades Application

Local Reinforcement in Notched Fiber Metal Laminates by Bonding Titanium Patch

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