Experimental investigation on impact performances of GLARE laminates

Chen, Qi; Guan, Zhidong; Li, Zengshan; Ji, Zhaojie; Yang, Zhuo

doi:10.1016/j.cja.2015.07.002

Cited by 27 publications

(17 citation statements)

References 21 publications

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“…In a complementary study, Chen et al [71] conducted low velocity impact experiments on GLARE 5-3/2-0.25 specimens at room temperature. The GLARE laminate was manufactured from S4-glass fiber reinforced epoxy plies and Al 2024-T3 alloy sheets.…”

Section: Model Verificationmentioning

confidence: 99%

“…These two independent experimental campaigns exhibited delamination of the GF/EP-90°/0° interface farthest from the impacted side, which agreed with the prediction of the numerical analysis of this study (see Figure 6). [71], and (c) numerical analysis of this study; 1 and 2 stand for the impacted side and the nonimpacted side, respectively; 3 stands for the GF/EP-90°/0° interface delamination at room temperature. [71], and (c) numerical analysis of this study; 1 and 2 stand for the impacted side and the non-impacted side, respectively; 3 stands for the GF/EP-90 • /0 • interface delamination at room temperature.…”

Section: Model Verificationmentioning

confidence: 99%

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Interface Failure of Heated GLARETM Fiber–Metal Laminates under Bird Strike

Hasan

2020

Aerospace

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Many high-strength composite materials have been developed for aircraft structures. GLAss fiber REinforced aluminum (GLARE) is one of the high-performance composites. The review of articles, however, yielded no study on the impact damage of heated GLARE laminates. This study, therefore, aimed at developing a numerical model that can delineate the continuum damage of GLARE 5A-3/2-0.3 laminates at elevated temperatures. In the first stage, the inter-laminar interface failure of heated GLARE laminate had been investigated at room temperature and 80 °C. The numerical analysis employed a three-dimensional GLARE 5A-3/2-0.3 model that accommodated volumetric cohesive interfaces between mating material layers. Lagrangian smoothed particles populated the projectile. The model considered the degradation of tensile and shear modulus of glass fiber reinforced epoxy (GF/EP) at 80 °C, while incorporated temperature-dependent critical strain energy release rate of cohesive interfaces. When coupled with the material particulars, an 82 m/s bird impact at room temperature exhibited delamination first in the GF/EP 90°/0° interface farthest from the impacted side. Keeping the impact velocity, interface failure propagated at a slower rate at 80 °C than that at room temperature, which was in agreement with the impact damage determined in the experiments. The outcomes of this study will help optimize a GLARE laminate based on the anti-icing temperature of aircraft.

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Section: Model Verificationmentioning

confidence: 99%

Section: Model Verificationmentioning

confidence: 99%

Interface Failure of Heated GLARETM Fiber–Metal Laminates under Bird Strike

Hasan

2020

Aerospace

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“…Superimposing a harmonic motion over the conventional axial feed results in a periodic chisel edge movement. This impact loading reduces the energy absorbed by the material for the following reasons [35,36]:…”

Section: Chip Morphologymentioning

confidence: 99%

Chip Morphology and Delamination Characterization for Vibration-Assisted Drilling of Carbon Fiber-Reinforced Polymer

Hussein

Sadek

Elbestawi

et al. 2019

JMMP

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Carbon fiber-reinforced polymers (CFRP) are widely used in the aerospace industry. A new generation of aircraft is being built using CFRP for up to 50% of their total weight, to achieve higher performance. Exit delamination and surface integrity are significant challenges reported during conventional drilling. Exit delamination influences the mechanical properties of machined parts and, consequently, reduces fatigue life. Vibration-assisted drilling (VAD) has much potential to overcome these challenges. This study is aimed at investigating exit delamination and geometrical accuracy during VAD at both low- and high-frequency ranges. The kinematics of VAD are used to investigate the relationship between the input parameters (cutting speed, feed, vibration frequency, and amplitude) and the uncut chip thickness. Exit delamination and geometrical accuracy are then evaluated in terms of mechanical and thermal load. The results show a 31% reduction in cutting temperature, as well as a significant enhancement in exit delamination, by using the VAD technology.

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“…Impact damage is an important type of failure in aircraft structure, as it can impair their load capacity performance. They are prone to damage caused by tool drops, hail and bird strike, shock stone, runway debris, engine debris, and ballistic impact [4], [5]. Therefore, impact properties of FMLs especially that are being used in aircraft industries are widely investigated.…”

Section: Introductionmentioning

confidence: 99%

Quasi-Static Indentation Response of Galvanized Iron Toughened Glass Fiber/Epoxy Laminates

Jumahat*,

Mohamad Nasir

2020

IJITEE

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This paper is aimed to study the quasi-static indentation response of fiber metal laminates (FMLs) that are made of various arrangement of galvanized iron (GI) alloy thin sheet, glass fibre and epoxy polymer. Unidirectional and woven types of glass fiber/epoxy pre-impregnated laminates and three different thickness of GI thin sheet, i.e. 0.5, 1.0 and 2.0 mm, were used to produce FML systems using combination of hand layup and hot press methods. The FML systems were coded as UGFRP, UGFML 1/2-2, UGFML 2/3-1, UGFML 4/5-0.5, WGFRP, WGFML 1/2-2, WGFML 2/3-1, WGFML 4/5-0.5 according to their types of glass fibers, thickness of GI and stacking sequence. Quasi-static indentation (QSI) tests were performed according to ASTM D6264 using hemispherical crosshead at 5 mm/min speed rate. It was found that both unidirectional and woven systems of FML 1/2-2 exhibited the highest energy absorption capacity, with enhancement of 28 times and 11 times more than UGFRP and WGFRP composite, respectively. At maximum compression, FML 2/3-1 displayed the highest ultimate load, while FML 1/2-2 displayed the highest displacement for both fiber systems. Damage area inspection revealed severe matrix crack, fiber fracture and delamination upon penetration and perforation

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Experimental investigation on impact performances of GLARE laminates

Cited by 27 publications

References 21 publications

Interface Failure of Heated GLARETM Fiber–Metal Laminates under Bird Strike

Interface Failure of Heated GLARETM Fiber–Metal Laminates under Bird Strike

Chip Morphology and Delamination Characterization for Vibration-Assisted Drilling of Carbon Fiber-Reinforced Polymer

Quasi-Static Indentation Response of Galvanized Iron Toughened Glass Fiber/Epoxy Laminates

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