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Alderliesten, R.C.; Hagenbeek, Michiel; Homan, J. J.; Hooijmeijer, P. A.; Vries, Teun J. de; Vermeeren, C. A. J. R.

doi:10.1023/a:1025537818644

Cited by 80 publications

(18 citation statements)

References 2 publications

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“…Due to military budgetary constraints and civilian industry requirements, all of these older aircraft either have encountered ageing problems, such as fatigue cracking, stress corrosion cracking (SCC) or corrosion [1,2]. Fatigue cracks often initiate from impact damage occurring during pre-flight and taxiing operations, dropped tools during maintenance, runaway debris, hail or bird strike [3,4]. Such damaged structures are frequently required to remain in service for extended periods, despite the occurrence of damage.…”

Section: Introductionmentioning

confidence: 99%

“…As a consequence of these problems, other patch materials, such as titanium or fibre-metal laminates (FML) such as GLARE have been investigated, showing their effectiveness in retarding or arresting the crack [10,11]. FMLs combine good fatigue performance with the excellent impact resistance [2,[12][13][14][15][16][17][18][19][20]. The use of FMLs as crack retarders may help to improve the damage tolerance of structures and a number of recent papers have demonstrated the benefits of following this approach, e.g.…”

Section: Introductionmentioning

confidence: 99%

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The response of aluminium/GLARE hybrid materials to impact and to in-plane fatigue

Bagnoli¹,

Bernabei²,

Figueroa-Gordon

et al. 2009

Materials Science and Engineering: A

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a b s t r a c tFibre metal laminates (FMLs), such as glass reinforced aluminium (GLARE), are a family of materials with excellent damage tolerance and impact resistance properties. This paper presents an evaluation of the low velocity impact behaviour and the post-impact fatigue behaviour of GLARE laminate adhesively bonded to a high strength aluminium alloy substrate as a fatigue crack retarder. The damage initiation, damage progression and failure modes under impact and fatigue loading were examined and characterised using an ultrasonic phased array C-scan together with metallography and scanning electron microscopy (SEM). After impact on the substrate, internal damage to the GLARE bonded on the opposite side of the substrate occurred in the form of fibre and matrix cracking. No delamination was detected at the GLARE/substrate bond. Before impact the bonded GLARE strap caused reductions in substrate fatigue crack growth rate of up to a factor of 5. After impact the retardation was a factor of 2. The results are discussed in terms of changes to the GLARE stiffness promoted by the impact damage.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

The response of aluminium/GLARE hybrid materials to impact and to in-plane fatigue

Bagnoli¹,

Bernabei²,

Figueroa-Gordon

et al. 2009

Materials Science and Engineering: A

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“…All the specimens were tested in an instrumented drop weight impact testing machine (FRACTOVICS PLUS make) under low velocity (< 11 m/s) 9,15 . The specimens were clamped in a fixture between two steel plates with a circular central opening of 76 × 76 mm.…”

Section: Evaluation Of Impact Propertiesmentioning

confidence: 99%

“…The impact energy has been varied from plastic denting of the outer aluminium layer up to perforation of the whole specimen. The specific minimum cracking energy and the specific perforation energy are obtained by dividing the energy values by the areal density of the specimen 15 . The specific cracking energy and the specific perforation energy for the hybrid laminates is of the order of 2.4 and 6.3 J.m 2 .kg -1 .…”

Section: Effect Of Fiber Volume Fraction On the Impact Performancementioning

confidence: 99%

Impact properties of aluminium - glass fiber reinforced plastics sandwich panels

Periasamy¹,

Manickam

Hariharasubramanian³

2012

Mat. Res.

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Aluminium -glass fiber reinforced plastics (GFRP) sandwich panels are hybrid laminates consisting of GFRP bonded with thin aluminum sheets on either side. Such sandwich materials are increasingly used in airplane and automobile structures. Laminates with varying aluminium thickness fractions, fiber volume fractions and orientation in the layers of GFRP were fabricated by hand lay up method and evaluated for their impact performance by conducting drop weight tests under low velocity impacts. The impact energy required for initiating a crack in the outer aluminium layer as well as the energy required for perforation was recorded. The impact load-time history was also recorded to understand the failure behavior. The damage depth and the damage area were measured to evaluate the impact resistance. Optical photography and scanning electron micrographs were taken to visualize the crack and the damage zone. The bidirectional cross-ply hybrid laminate (CPHL) has been found to exhibit better impact performance and damage resistance than the unidirectional hybrid laminate (UDHL). Increase in aluminium thickness fraction (Al tf ) and fiber volume fraction (V f ) resulted in an increase in the impact energy required for cracking and perforation. On an overall basis, the sandwich panels exhibited better impact performance than the monolithic aluminium.

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“…Alderliesten [3] performed fatigue tests on FMLs based on a glass fiber reinforced epoxy and showed that a fiber bridging mechanism at the crack tip dramatically reduced the rate of crack growth in an FML relative to that in a plain metal alloy. Alderliesten et al [4] studied the low and high velocity impact response of FMLs and showed that they offered damage threshold energies that were significantly greater than those exhibited by a plain aluminum alloy. Cortes and Cantwell [5] conducted low and high velocity impact tests on titanium-based FMLs and showed that interfacial and interlaminar delaminations were the principal energy-absorbing mechanism during the impact loading on these materials.…”

Section: Introductionmentioning

confidence: 99%

The morphing properties of a smart fiber metal laminate

et al. 2008

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This article investigates the activation characteristics of a novel fiber-metal laminate (FML) based on a nickel-titanium (Ni-Ti) shape memory alloy. Initial attention focuses on manufacturing this smart FML in which a woven glass fiber reinforced epoxy material is sandwiched between two shape memory alloy (SMA) outer skins. Activation tests on cantilever beams using a hot air gun have shown that the FMLs exhibits a distinct actuation capability in which beam rotations of up to 118 were recorded. An examination of the edges of polished samples indicated that no damage was incurred by the FML during the activation process. The functionality of the FMLs was enhanced through the introduction of embedded electrical resistance wires located between the composite and metal plies. Here, the embedded electrical wires were heated by passing an electric current through them, thereby activating the SMA plies in a more effective and controllable manner. As before, significant beam tip rotations were recorded in the FMLs in a relatively short time period. Finally, polymer-based optical fiber (POF) and fiber-bragg grating (FBG) sensors were introduced into the FMLs in order to monitor their deflection during the activation process. The results of these tests showed that such sensing elements can be successfully employed to monitor the actuation response of these layered laminates.

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Cited by 80 publications

References 2 publications

The response of aluminium/GLARE hybrid materials to impact and to in-plane fatigue

The response of aluminium/GLARE hybrid materials to impact and to in-plane fatigue

Impact properties of aluminium - glass fiber reinforced plastics sandwich panels

The morphing properties of a smart fiber metal laminate

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