Searched for: subject%3A%22Fibre%255C%252Bmetal%255C%252Blaminates%22
(1 - 20 of 30)

Pages

List view
Grid view
document
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
document
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
document
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
document
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
document
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
document
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
document
Hashagen, F. (author)
doctoral thesis 1998
document
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
document
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
document
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
document
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
document
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
document
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
document
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
document
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
document
Hashagen, F. (author), Schellekens, J.C.J. (author), De Borst, R. (author), Parisch, H. (author)
journal article 1995
document
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
document
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
document
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
document
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
Searched for: subject%3A%22Fibre%255C%252Bmetal%255C%252Blaminates%22
(1 - 20 of 30)

Pages

List view
Grid view