Numerical Modelling of Fibre Metal Laminates Under Thermomechanical Loading

Hagenbeek, Michiel; Remmers, Jjc Joris; Borst, René de

doi:10.2514/6.2003-1676

Cited by 18 publications

(22 citation statements)

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“…The material parameters of the S2 glass fibre, the FM94 epoxy and the interfaces between fibres and epoxy and within the epoxy are listed in Table 2. The elastic material properties for the fibre and the epoxy matrix have been adopted from [26]. The value of the elastic stiffness K of the interfaces is taken relatively high, such that the interfacial deformations in the elastic regime are negligibly small.…”

Section: Finite Element Modelmentioning

confidence: 99%

Numerical homogenization of cracking processes in thin fibre-epoxy layers

Alfaro¹,

Suiker²,

Verhoosel³

et al. 2010

European Journal of Mechanics - A/Solids

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Section: Finite Element Modelmentioning

confidence: 99%

Numerical homogenization of cracking processes in thin fibre-epoxy layers

Alfaro¹,

Suiker²,

Verhoosel³

et al. 2010

European Journal of Mechanics - A/Solids

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“…Embedded heater elements in the leading edges of fibre metal laminate (FML) wing structures can provide anti-icing and de-icing capabilities 4 . However, the heating of leading edges of aircraft using embedded heater elements introduces strains and stresses in the structure due to the different thermal expansion coefficients of the different laminated materials 5,6 . Thus, heating might affect the shape of the leading edges.…”

Section: Introductionmentioning

confidence: 99%

Strain characterization of embedded aerospace smart materials using shearography

et al. 2015

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The development of smart materials for embedding in aerospace composites provides enhanced functionality for future aircraft structures. Critical flight conditions like icing of the leading edges can affect the aircraft functionality and controllability. Hence, anti-icing and de-icing capabilities are used. In case of leading edges made of fibre metal laminates heater elements can be embedded between composite layers. However this local heating causes strains and stresses in the structure due to the different thermal expansion coefficients of the different laminated materials. In order to characterize the structural behaviour during thermal loading full-field strain and shape measurement can be used. In this research, a shearography instrument with three spatially-distributed shearing cameras is used to measure surface displacement gradients which give a quantitative estimation of the in-and out-of-plane surface strain components. For the experimental part, two GLARE (Glass Laminate Aluminum Reinforced Epoxy) specimens with six different embedded copper heater elements were manufactured: two copper mesh shapes (straight and S-shape), three connection techniques (soldered, spot welded and overlapped) and one straight heater element with delaminations. The surface strain behaviour of the specimens due to thermal loading was measured and analysed. The comparison of the connection techniques of heater element parts showed that the overlapped connection has the smallest effect on the surface strain distribution. Furthermore, the possibility of defect detection and defect depth characterisation close to the heater elements was also investigated.

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“…For example GLARE 1 and GLARE 2 have fibers only in one direction, and they have excellent fatigue properties and high strength. GLARE 3 has 50% of the fibers in one direction and 50% in the transverse direction [11]. These composites are used for primary structures (structures subjected to heavy loads), as elements of the aircraft skin.…”

mentioning

confidence: 99%

“…1. a) Scheme of the layer arrangement in the GLARE 3 composite (b) the method of marking GLARE composites [11] A kilogram of GLARE composite is approx. 5 to 10 times more expensive in comparison to the aluminum alloy, conventionally used in aircraft.…”

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The Influence of Features of Aluminium Alloys 2024, 6061 and 7075 on the Properties of Glare-Type Composites / Wpływ Właściwości Stopów Aluminium 2024, 6061, 7075 Na Cechy Kompozytu Typu Glare

Wilk¹,

Śliwa²

2015

Archives of Metallurgy and Materials

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The above paper presents the assumptions and results of the research whose aim was to determine the influence of 2024, 6061 and 7075 aluminum alloys on the final properties of GLARE-type composites. GLARE 3 2/1 type composites, made of two layers of the epoxy prepreg, reinforced with unidirectional glass fibers, arranged in the direction of 0°/90°, and two sheets of aluminum with a thickness of 0.4 mm, were investigated. Composites of various stacking configurations of alloy layers, made of one type of aluminum alloy (so-called ‘homogeneous composites’), and two different alloys (mixed composites), were analyzed. The properties of the composites were evaluated with the use of the mixing rule and compared with the test results. The influence of the used aluminum alloys on mechanical properties of GLARE-type composites has been determined. GLARE-type composite made of 7075 alloy sheets had the most favorable mechanical properties in comparison to properties of composites with 2024 and 6061 sheets. It has been shown how the properties of GLARE-type composites depend on the type of the aluminum alloy. It has been also proved that the properties of GLARE-type composites can be evaluated with the use of the mixing rule.

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Numerical Modelling of Fibre Metal Laminates Under Thermomechanical Loading

Cited by 18 publications

References 0 publications

Numerical homogenization of cracking processes in thin fibre-epoxy layers

Numerical homogenization of cracking processes in thin fibre-epoxy layers

Strain characterization of embedded aerospace smart materials using shearography

The Influence of Features of Aluminium Alloys 2024, 6061 and 7075 on the Properties of Glare-Type Composites / Wpływ Właściwości Stopów Aluminium 2024, 6061, 7075 Na Cechy Kompozytu Typu Glare

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