Towards aerospace grade thin-ply composites: Effect of ply thickness, fibre, matrix and interlayer toughening on strength and damage tolerance

Botsis, J.; Amacher, R.; Kohler, S.; Brunner, J.; Kramer, Elissa L.; Dransfeld, Clemens; Smith, W.H. .; Scobbie, K.; Sorensen, L.

doi:10.1016/j.compscitech.2018.08.037

Cited by 100 publications

(36 citation statements)

References 27 publications

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“…Thin layers suppress transverse microcracking and free edge delamination. As a result, the occurring failure modes change from complex multi-mode failure to a quasi-brittle failure, from thick-to thin-ply [13][14][15]17,18]. For unnotched quasi-isotropic laminates, this leads to a significant increase in tensile strength, which utilises the potential of the constituents [13,19].…”

Section: Introductionmentioning

confidence: 99%

CFRP Thin-Ply Fibre Metal Laminates: Influences of Ply Thickness and Metal Layers on Open Hole Tension and Compression Properties

et al. 2020

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Thin-ply laminates exhibit a higher degree of freedom in design and altered failure behaviour, and therefore, an increased strength for unnotched laminates in comparison to thick-ply laminates. For notched laminates, the static strength is strongly decreased; this is caused by a lack of stress relaxation through damage, which leads to a higher stress concentration and premature, brittle failure. To overcome this behaviour and to use the advantage of thin-ply laminates in areas with high stress concentrations, we have investigated thin-ply hybrid laminates with different metal volume fractions. Open hole tensile (OHT) and open hole compression (OHC) tests were performed with quasi-isotropic carbon fibre reinforced plastic (CFRP) specimens. In the area of stress concentration, 90° layers were locally substituted by stainless steel layers of differing volume fractions, from 12.5% to 25%. The strain field on the specimen surface was evaluated in-situ using a digital image correlation (DIC) system. The embedding of stainless steel foils in thin-ply samples increases the OHT strength up to 60.44% compared to unmodified thin-ply laminates. The density specific OHT strength is increased by 33%. Thick-ply specimens achieve an OHC strength increase up to 45.7%, which corresponds to an increase in density specific strength of 32.4%.

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Section: Introductionmentioning

confidence: 99%

CFRP Thin-Ply Fibre Metal Laminates: Influences of Ply Thickness and Metal Layers on Open Hole Tension and Compression Properties

et al. 2020

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“…Several experimental investigations on thin ply laminates have highlighted their main properties [7,8,9,10,11,12,13]: increased fiber content; more uniform packing of fibers; delay and even suppression of intralaminar cracking (called also transverse-, matrix-or micro-cracking) and delamination. A very insightful work documenting how these phenomena are affected by the morphology of thin-ply laminates is the microscopic study of Saito & al.…”

Section: R a F Tmentioning

confidence: 99%

Energy release rate of the fiber/matrix interface crack in UD composites under transverse loading: debond-debond and debond-free boundary interactions

Stasio¹,

Vārna²,

Ayadi³

2019

Preprint

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The effects of crack shielding, finite thickness of the composite and fiber content on fiber/matrix debond growth in thin unidirectional composites are investigated analyzing Representative Volume Elements (RVEs) of different ordered microstructures. Debond growth is characterized by estimation of the Energy Release Rates (ERRs) in Mode I and Mode II using the Virtual Crack Closure Technique (VCCT) and the J-integral. It is found that increasing fiber content, a larger distance between debonds in the loading direction and the presence of a free surface close to the debond have all a strong enhancing effect on the ERR. The presence of fully bonded fibers in the composite thickness direction has instead a constraining effect, and it is shown to be very localized. An explanation of these observations is proposed based on mechanical considerations.

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“…In this research it is found that an optimized interlayer toughened thin-ply composite, based on 68 microns plies of intermediate modulus fibre can reach both outstanding strength properties with comparable or better CAI and OHT strength compared to current aerospace grade composites. [4] Estelle Kalfon-Cohen et al, studied about synergetic effects about thin ply. Thin-ply carbon fiber laminates show superior mechanical properties, including higher initiation and ultimate strength compared to standard thickness plies and also greater flexibility.…”

Section: Literature Surveymentioning

confidence: 99%

Layerwise Damage Investigation of Ply Orientation on Strength Characteristics of Carbon Fibre Composite

Karale¹

2019

IJRASET

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Synthetic composites have higher strength to weight ratio and are extensively used in industrial applications. Most of the composites have orthotropic properties and their strength varies as per orientation. Carbon fibers are one of the synthetic fibres having extensively high tensile strength. Laminates having different ply orientations have different properties and strengths. Hence, to enhance strength properties, reducing layerwise damage becomes of up most important. It is not possible to investigate the layerwise damage of each ply separately by experimentation. This can be done by using ACP tool in ANSYS 19.2 software. In this project, two laminates having orientations as 0°-45°-0° and 0°-30°-60° are considered for analysis. Advance composite pre-post [ACP] tool from ANSYS software is used for simulation of these layers. From this analysis total deformation, equivalent stress and damage of each layer is determined. After getting layerwise damage, experimentation is done. Experimental tensile test is done on specimens above ply orientations to obtain force vs. deflection diagrams. Comparative analysis is made between simulation and experimental results. Results and conclusion is drawn. Experimental and simulation values differ by only 1%. This validates the simulation value of force reaction. Also from the result it can be seen that 0°-45°-0° laminate gives better results than that of 0°-30°-60° laminate. Hence, it can be concluded that Plate 1 has higher strength than Plate 2 i.e., 0°-45°-0° is better ply orientation than 0°-30°-60° ply orientation. Also it is observed that different ply orientations have different strengths.

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Towards aerospace grade thin-ply composites: Effect of ply thickness, fibre, matrix and interlayer toughening on strength and damage tolerance

Cited by 100 publications

References 27 publications

CFRP Thin-Ply Fibre Metal Laminates: Influences of Ply Thickness and Metal Layers on Open Hole Tension and Compression Properties

CFRP Thin-Ply Fibre Metal Laminates: Influences of Ply Thickness and Metal Layers on Open Hole Tension and Compression Properties

Energy release rate of the fiber/matrix interface crack in UD composites under transverse loading: debond-debond and debond-free boundary interactions

Layerwise Damage Investigation of Ply Orientation on Strength Characteristics of Carbon Fibre Composite

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