Searched for: subject%3A%22Fibre%255C%252Bmetal%255C%252Blaminates%22
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Alcaraz, Mathilde (author), Alderliesten, R.C. (author), Mosleh, Yasmine (author)
Fibre metal laminates (FML) were originally developed as a hybrid material, to create synergy between the impact resistance of metals and excellent fatigue and corrosion resistance of fibre reinforced polymers, and to overcome the shortcomings of monolithic materials. Yet, the scope of the FML concept is predominantly limited to GLAss REinforced...
abstract 2023
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Liu, S. (author), Sinke, J. (author), Dransfeld, C.A. (author)
Hot-pressing can be an attractive fabrication method that enables the forming of hybrid materials like thermoset based fibre metal laminates. However, the process simulation on press forming requires accurate material characterization and boundary conditions to facilitate part design for a defect-free component. In order to improve the overall...
conference paper 2022
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Keller, A. (author), Geissberger, R. (author), Studer, J. (author), Leone, F. (author), Stefaniak, D. (author), Pascoe, J.A. (author), Dransfeld, C.A. (author), Masania, K. (author)
The effect of ply thickness on the notch sensitivity and bearing properties on carbon fibre reinforced polymer composites and their hybrid laminates with steel foils were studied. Laminates with ply thicknesses of 0.3 mm and 0.03 mm comprising of CFRP and hybrid laminates were manufactured and characterized using tension, open hole tension...
journal article 2021
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Alderliesten, R.C. (author)
With the introduction of fibre metal laminates (FMLs) as a (fatigue) damage tolerant material concept in aeronautics, an interesting field emerged where fatigue damage interaction plays a dominant role. The hybrid concept effectively demands evaluating fatigue damage growth based on fracture phenomena typical for both metals and fibre...
journal article 2019
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Zhao, Y. (author), Alderliesten, R.C. (author), Zhou, Zhengong (author), Fang, Guodong (author), Zhang, Jiazhen (author), Benedictus, R. (author)
In general, a finite width correction to stress intensity factor (SIF) is required in the fatigue crack growth. The finite width correction factor can be explained physically from the energy point of view. It is assumed that the finite width correction factor primarily constitutes an energy correction factor, i.e. it corrects the applied load...
journal article 2018
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Wang, W. (author), Rans, C.D. (author), Benedictus, R. (author)
Mechanically fastened joints are susceptible to the presence of multiple-site damage (MSD) cracks in the critical fastener row. Different from the MSD growth in joints consisting of metallic substrates, the two coupled metal crack growth and interfacial delamination propagation failure mechanisms in Fibre Metal Laminates (FMLs) make the...
journal article 2018
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Nardi, D. (author), Abouhamzeh, M. (author), Leonard, R.A. (author), Sinke, J. (author)
Gaps and overlaps between pre-preg plies represent common flaws in composite materials that can be introduced easily in an automated fibre placement manufacturing process and are potentially detrimental for the mechanical performances of the final laminates. Whereas gaps and overlaps have been addressed for full composite material, the topic...
journal article 2018
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Alderliesten, R.C. (author)
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...
journal article 2018
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Anisimov, A. (author), Muller, B. (author), Sinke, J. (author), Groves, R.M. (author)
Current trends in aircraft design are to increase the economic efficiency by integrating different features in multifunctional materials. One strategy is to embed resistance heater elements between glass-fibre epoxy layers in (heated) fibre metal laminates and to use them as anti or de-icing devices in leading edges of wings. Heated glass...
journal article 2018
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Abouhamzeh, M. (author), Nardi, D. (author), Leonard, R.A. (author), Sinke, J. (author)
During the automated manufacturing of fibre reinforced laminates, defects can be produced. Gaps and overlaps between adjacent prepreg layers can be produced in composites during the tape-layup process. However, the topic is not yet studied for hybrid materials, in which metal sheets and thin prepreg layers lead to different effects due to the...
journal article 2018
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Wang, W. (author), Rans, C.D. (author), Benedictus, R. (author)
This paper proposes an analytical model for predicting the non-symmetric crack growth and accompanying delamination growth in FMLs. The general approach of this model applies Linear Elastic Fracture Mechanics, the principle of superposition, and displacement compatibility based on the understanding of deformation behaviour in eccentrically...
journal article 2017
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Muller, B. (author), Palardy, G. (author), Teixeira De Freitas, S. (author), Sinke, J. (author)
Autoclave manufacturing of fibre metal laminates, such as GLARE, is an expensive process.Therefore, there is an increasing interest to find cost effective out-of-autoclave manufacturing processes without diminishing the laminate quality. The aim of this study is to evaluate the quality of fibre metal laminate...
journal article 2017
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Wang, W. (author)
Fibre metal laminates (FMLs)were developed and refined for their superior crack growth resistance and critical damage size that complimented the damage tolerance design philosophy utilized in the aerospace sector. Robust damage tolerance tools have been developed for FMLs. However, they tend to focus on the evolution of an isolated crack. There...
doctoral thesis 2017
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Abouhamzeh, M. (author)
GLARE is used in fuselage panels for its improved fatigue and residual strength. In this thesis, predictive models are developed for residual stresses and distortions of GLARE induced by manufacturing. Material behaviour of the epoxy adhesive and the glass-epoxy prepreg is characterised for thermal and curing circumstances. The derived...
doctoral thesis 2016
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Zhang, Z. (author), Wang, W. (author), Rans, C.D. (author), Benedictus, R. (author)
This paper provides an experimental investigation into the pin loading effects on the crack growth behaviour in Fibre Metal Laminates. The pin loading effects and bypass loading effects are incorporated in two different tested joints. The analysis of the test results shows that pin loading dominates the crack growth only in the vicinity of the...
journal article 2016
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Şen, I. (author)
The lower wing skin is one of the primary structures of an aircraft. To further improve the fatigue and damage tolerance (F&DT) performance of the lower wing, fibre metal laminates (FML) are proposed as a new material solution. FML consist of thin metal layers bonded with layers of fibre composites. This concept has potentially a large design...
doctoral thesis 2015
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Anisimov, A. (author), Muller, B. (author), Sinke, J. (author), Groves, R.M. (author)
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...
conference paper 2015
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Moriniere, F.D. (author)
Generating high-energy absorbing FML concepts is challenging because aluminium and composite failure mechanisms are acting concurrently during the impact process. Because the impact process involves energy transformation, an analytical energy balance method was used to assess the contribution of the material constituents in the low-velocity...
doctoral thesis 2014
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Khan, S. (author)
This thesis presents the investigation into the fatigue propagation and delamination growth of Fibre Metal Laminates under variable amplitude loading. As explained in the first chapter, the motivation of the research is twofold: first, to obtain a clear understanding and detailed characterization of the failure mechanisms in GLARE under variable...
doctoral thesis 2013
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Zhu, G. (author)
Aerospace aluminium alloys (7xxx and 2xxx series Al alloy) is one of the important Al alloys in our life. The recycling of aerospace Al alloy plays a significant role in sustainable development of Al industry. The fibre reinforced metal laminates GLARE including 67 wt.% 2024 Al alloy was used as upper fuselage in Airbus A380, but the solution...
doctoral thesis 2012
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