A comparative study of the pin-bearing responses of two glass-based fibre metal laminates

Frizzell, Ronan; McCarthy, Conor T.; McCarthy, Michael A.

doi:10.1016/j.compscitech.2008.08.021

Cited by 20 publications

(11 citation statements)

References 15 publications

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“…Another beneficial feature of GLARE is that the number and orientation of composite layers can be selected to best suit different applications, and such material features make it attractive for structural applications [37]. For the certification of GLAREs for aircraft structures, several lay-up patterns are already defined as a standard grade: the schematic view of GLARE 3/2 is shown in Figure 7.…”

Section: Glare Gradesmentioning

confidence: 99%

The Guidelines of Material Design and Process Control on Hybrid Fiber Metal Laminate for Aircraft Structures

Park¹,

Choi²

2019

Optimum Composite Structures

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Fiber metal laminate (FML) is a hybrid material system that consists of thin metal sheets bonded into a laminate with intermediate thin fiber reinforced composite layers. The aerospace industry has recently increased their use of FMLs due to the considerable weight reduction and consequent benefits for critical load-carrying locations in commercial aircraft, such as upper fuselage skin panels. All FML materials and their processes should be qualified through enough tests and fabrication trials to demonstrate reproducible and reliable design criteria. In particular, proper surface treatment technologies are prerequisite for achieving long-term service capability through the adhesive bonding process. This chapter introduces a brief overview of design concept, material properties and process control methodologies to provide detailed background information with engineering practices and to help ensure stringent quality controls and substantiation of structure integrity. The guidelines and information found in this chapter are meant to be a documentation of current knowledge and an application of sound engineering principles to the FML part development for aerospace usage.

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Section: Glare Gradesmentioning

confidence: 99%

The Guidelines of Material Design and Process Control on Hybrid Fiber Metal Laminate for Aircraft Structures

Park¹,

Choi²

2019

Optimum Composite Structures

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“…Basic idea for the development of fibre metal laminates was to develop a material with a high crack growth resistance for fatigue prone areas of modern civil aircraft [7,8]. It is reported that FMLs originated at Fokker/TU Delft in the Netherlands about 1970s, and since then have undergone extensive development [9,10]. Aluminium alloys are most commonly used in FMLs as metal, and the fibres can be Kevlar or glass [11].…”

mentioning

confidence: 99%

“…Even though these properties have been the subject of investigations in the literature [6][7][8][9][10][11][15][16][17], many of these areas are still open for further studies and developments.…”

mentioning

confidence: 99%

Studying the Tensile Behaviour of GLARE Laminates: A Finite Element Modelling Approach

et al. 2010

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Numerical simulations based on finite element modelling are increasingly being developed to accurately evaluate the tensile properties of GLARE (GLAss fibre REinforced aluminium laminates). In this study, nonlinear tensile behaviour of GLARE Fibre Metal Laminates (FML) under in-plane loading conditions has been investigated. An appropriate finite element modelling approach has been developed to predict the stress-strain response and deformation behaviour of GLARE laminates using the ANSYS finite element package. The finite element model supports orthotropic material properties for glass/epoxy layer(s) and isotropic properties with the elastic-plastic behaviour for the aluminium layers. The adhesion between adjacent layers has been also properly simulated using cohesive zone modelling. An acceptable agreement was observed between the model predictions and experimental results available in the literature. The proposed model can be used to analyse GLARE laminates in structural applications such as mechanically fastened joints under different mechanical loading conditions.

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“…They found that the bearing strength and the failure mode of FML joints strongly depend on parameters such as the ratio of E/D, metal volume fraction, and fiber orientation. Frizzell et al [9] examined the progression of damage from initiation up to ultimate failure in pin-loaded GLARE joints by using microscopy. They also found that GLARE 2 joints displayed significantly higher ultimate bearing strength and strain than GLARE 3 joints.…”

Section: Introductionmentioning

confidence: 99%

“…The bearing properties of FML joints have been experimentally researched by scholars [4][5][6][7][8][9].Wu and Slagter. [5]found that the bearing strength depends on failure mode as influenced by specimen geometry.…”

Section: Introductionmentioning

confidence: 99%

Tightening torque and washer size effects on bearing strength of fiber metal laminate bolted-joints

Zhou

et al. 2017

MATEC Web Conf.

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Abstract. The study investigated the effect of tightening torque and washer size on the mechanical properties of double-lap, single bolt fiber metal laminate (FML) joints. The tightening torque under the examination was 0.1Nm, 3 Nm, 5 Nm, 10 Nm and 15 Nm, and the washer size was changed by varying the value of outer diameter of washer (Dwo=11mm, Dwo=13mm, Dwo=15mm, Dwo=17mm and Dwo=19mm). A three-dimensional (3D) failure finite element model was used to predict the bearing behaviour of FML joints. The comparison between simulation and experimental results showed a good agreement in strength. The results showed that the effect of bolt tightening torque on the failure loads of bolt-loaded FML joints was obvious, and the effect of washer size on the load-bearing capacity was not sensitive. The present work provided supporting information for the design of FML joints.

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A comparative study of the pin-bearing responses of two glass-based fibre metal laminates

Cited by 20 publications

References 15 publications

The Guidelines of Material Design and Process Control on Hybrid Fiber Metal Laminate for Aircraft Structures

The Guidelines of Material Design and Process Control on Hybrid Fiber Metal Laminate for Aircraft Structures

Studying the Tensile Behaviour of GLARE Laminates: A Finite Element Modelling Approach

Tightening torque and washer size effects on bearing strength of fiber metal laminate bolted-joints

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