Searched for: subject%3A%22Fibre%255C%252Bmetal%255C%252Blaminates%22
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Vlot, A. (author), Soerjanto, T. (author), Yeri, I. (author), Schelling, J.A. (author)
report 1995
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Hashagen, F. (author), Schellekens, J.C.J. (author), De Borst, R. (author), Parisch, H. (author)
journal article 1995
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Hashagen, F. (author), De Borst, R. (author)
In this contribution numerical models are discussed for describing failure mechanisms in fibre metal laminates. Fibre metal laminates form a new class of materials which are considered for a possible application to the fuselage of future aircraft generations. The intensive experimental analyses of these materials are focused on the assessment of...
journal article 1998
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Hashagen, F. (author)
doctoral thesis 1998
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Hagenbeek, M. (author)
Fibre metal laminates, such as Arall or Glare, can offer improved properties compared to monolithic materials. Glare for example shows improved fatigue, residual strength, burn-through, impact and corrosion properties with respect to aluminium 2024, together with a considerable weight reduction and competitive costs. A large research program has...
doctoral thesis 2005
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Randell, C.E. (author)
The investigation of the present thesis is concerned with the fatigue crack growth behaviour of part through the thickness cracks in Glare™ fibre metal laminate (FML) subjected to combined tension and bending. An experimental program was executed which required the development of a novel fatigue specimen, the Milled Open Hole Tension Bending ...
doctoral thesis 2005
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Van Rooijen, R.G.J. (author)
Fibre Metal Laminates (FMLs) are hybrid materials, which consist of thin metal sheets bonded together with alternating unidirectional fibre layers. This material concept has resulted in superior fatigue characteristics with respect to the metallic counterpart. Several static characteristics are however negatively influenced due to the fibre...
doctoral thesis 2006
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Vermeulen, B. (author)
The process of design aircraft systems is becoming more and more complex, due to an increasing amount of requirements. Moreover, the knowledge on how to solve these complex design problems becomes less readily available, because of a decrease in availability of intellectual resources and reduced knowledge transfer opportunities. Aerospace...
doctoral thesis 2007
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Rodi, R. (author)
The concept of damage tolerance is a key aspect in ensuring and maintaining safety of an airframe structure over its design life. Developments in materials and structural design have both contributed to improvements in the damage tolerance of modern aircraft structures. Indeed, new developments in metal alloys, composite materials, and hybrid...
doctoral thesis 2012
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Zhu, G. (author), Xiao, Y. (author), Yang, Y. (author), Wang, J. (author), Sun, B. (author), Boom, R. (author)
GLARE (glass fibre/epoxy reinforced aluminum laminate) is a member of the fiber metal laminate (FML) family, and is built up of alternating metal and fiber layers. About 500m2 GLARE is employed in each Airbus A380 because of the superior mechanical properties over the monolithic aluminum alloys, such as weight reduction, improved damage...
journal article 2012
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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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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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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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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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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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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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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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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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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), 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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