Bending failure mechanism and flexural properties of GLARE laminates with different stacking sequences

Li, Huaguan; Xu, Yiwei; Hua, Xiaoge; Liu, Cheng; Tao, Jie

doi:10.1016/j.compstruct.2017.12.068

Cited by 69 publications

(26 citation statements)

References 26 publications

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“…e interlaminar shear strength refers to the bonding strength between fibers and the matrix resin in FML [46]. e interlaminar shear strength of composites is closely related to the interlaminar bonding quality of materials [47,48]. When the shear stress is greater than the maximum interlaminar shear stress, the composite material will be damaged or fail [49,50].…”

Section: Failure and Control Methods Under Shear Stressmentioning

confidence: 99%

“…Under the bending stress, the laminate is subjected to both normal stress and shear stress. erefore, the failure mode is more complicated, and the changes in structure and layer design will affect the failure behavior of the material [48,57].…”

Section: Failure and Control Methods Under Bending Stressmentioning

confidence: 99%

“…e short-beam method (SBS) is simple to operate and it can save material. It can be used not only as a primary means to evaluate the interlaminar shear property of FMLs but also to evaluate interlaminar fracture toughness and to test bending property by using three-point bending SBS [48].…”

Section: Short-beam Methodmentioning

confidence: 99%

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Research Progress on Interlaminar Failure Behavior of Fiber Metal Laminates

Chen

Wang

2020

Advances in Polymer Technology

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Fiber metal laminate (FML) is a kind of lightweight material with excellent mechanical properties combining advantages of metal laminates and fiber reinforced composites. It has been widely used in the aerospace and transportation fields and is especially used as structural material such as aircraft skins, wings, and tails. However, under complex service conditions, interlaminar failure in FMLs greatly reduced mechanical properties of the material, even leading to serious economic and safety disasters. The failure and destruction of important structural parts of aircraft and other manned transportation vehicles are extremely unsafe for people. Therefore, it is of great significance to summarize the interlaminar failure behavior of FMLs and find ways to avoid these defects. This review paper is a collection of various researches done by many groups, which systematically discuss the interlaminar failure behaviors and their control methods of FMLs. The application status of several common FMLs in aircraft structures was given. The common interlaminar failure modes of FMLs and the testing and evaluation methods of interlaminar properties were stated. The failure mechanisms and the corresponding control methods were analyzed. Finally, the future developments of FMLs were also discussed by the authors. Through this review article, readers can obtain new research progress about the control method, the mechanism and future development on the failure behavior of FMLs in a more efficient way.

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Section: Failure and Control Methods Under Shear Stressmentioning

confidence: 99%

Section: Failure and Control Methods Under Bending Stressmentioning

confidence: 99%

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Research Progress on Interlaminar Failure Behavior of Fiber Metal Laminates

Chen

Wang

2020

Advances in Polymer Technology

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“…[10][11][12][13][14][15] A well-known example of a fibre-metal-laminate is GLARE, where glass fibre-reinforced epoxy layers and aluminium sheets are used. [16][17][18][19][20] In contrast, the present study is focussed on the usage of thermoplastic matrix materials, which offer significantly more energy absorption than thermosets, and thus are preferably used for impact-specific laminates. [21][22][23] In contrast, the adhesion of thermoplastic matrix materials to metals is often lower than those of thermosets.…”

Section: Introductionmentioning

confidence: 99%

An experimental study on the bending response of multi-layered fibre-metal-laminates

Kuhtz

Buschner

Henseler

et al. 2019

Journal of Composite Materials

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The combination of thin light metal sheets with fibre-reinforced thermoplastic layers in multi-layered fibre-metal-laminates advantageously combines the properties of both material classes. In this way, components can be developed which have both significantly increased specific properties (strength and stiffness with respect to density) and high energy absorption capacity compared with conventional design with mono materials. However, the structural behaviour of crash structures is decisively determined by material behaviour of the thermoplastic and metal constituents as well as the interface properties between both constituents and the corresponding delamination behaviour. To evaluate the structural response of multi-layered fibre-metal-laminates under highly dynamic loading conditions, Charpy tests were performed, where the test parameters, light metal material configuration, support length and laminate thickness, were varied. Moreover, the metal sheet surfaces were pre-treated by embossing to achieve different surface topologies. The influence of the different test parameters on the specific energy absorption capacity was characterised by the analysis of force–displacement curves.

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“…It seems that these characteristics have led to various potential applications. They have many advantages such as weight saving, good impact resistance, and damage tolerance [3][4][5]. Impact-related damage is one of the important issues in aerial structures.…”

Section: Introductionmentioning

confidence: 99%

Postfatigue Life Prediction of Glare Subjected to Low-Velocity Impact

et al. 2019

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In this study, at first, the dynamic of progressive failure of Glass-Fiber-Reinforced aluminum laminates (GLARE) under low-energy impact with intra laminar damage models implementing strain-based damage evolution laws, Puck failure criteria using ABAQUS-VUMAT, were modeled. For interface delamination, bilinear cohesive model; and for aluminum layers the Johnson-Cook model was implemented; and the fatigue life of the fiber metal laminates of GLARE subjected to impact was obtained and the numerical and experimental results of the model were compared with each other. With regard to the very good match between the numerical and experimental results, the results of the finite element model were generalized and expanded, and with the use of the multilayer neural network, the numerical model was extracted and then, by applying the meta-innovative algorithm, the maximum fatigue life of GLARE was determined at the highest level with very low-velocity impact, and the best configuration of three-layer GLARE was selected. The findings indicated that the best configuration of hybrid composite GLARE based on conventional commercial laminates that can tolerate low-velocity impacts with 18J impact energy and a 349MPa fatigue load with a frequency of 10Hz was [

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Bending failure mechanism and flexural properties of GLARE laminates with different stacking sequences

Cited by 69 publications

References 26 publications

Research Progress on Interlaminar Failure Behavior of Fiber Metal Laminates

Research Progress on Interlaminar Failure Behavior of Fiber Metal Laminates

An experimental study on the bending response of multi-layered fibre-metal-laminates

Postfatigue Life Prediction of Glare Subjected to Low-Velocity Impact

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