Numerical and experimental investigation of fiber metal laminates with elastomeric layers under low‐velocity impact

Zarezadeh‐mehrizi, Mohammad Amin; Liaghat, Gholamhossein; Ahmadi, Hamed; Taherzadeh‐Fard, Alireza; Khodadadi, Amin

doi:10.1002/pc.26509

Cited by 16 publications

(13 citation statements)

References 35 publications

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“…[1] From another point of view, FML can also be reinforcement for composite structures, as it can provide more resistance to impact load and moisture. [2][3][4][5] Thus, FML is thought to be one of the most promising damage tolerance materials in aircraft and other engineering industries. Among the factors associated with the damage tolerance, residual strength is the one of utmost importance.…”

Section: Introductionmentioning

confidence: 99%

Quasi‐static fracture characterization of fiber metal laminate with crack resistance curve based on δ₅

et al. 2022

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Fiber metal laminate (FML) is a hybrid composite typical in aircraft industry. It is necessary to effectively characterize the quasi‐static fracture performance of FML, considering the importance of damage tolerance design of aircraft structures and the complicated fracture mechanism of FML. In present investigation, glass fiber reinforced aluminum laminates (Glare) with middle cracks were tested under quasi‐static tensile load. The experimental crack resistance curve (R curve) based on the special crack opening displacement at original crack tip (δ5) was used for revealing the superior crack resistance of Glare laminate to aluminum sheet, which expressed in crack extension aspect was the extended critical crack length. This was thought to be benefit from the contributions of glass fiber layers and fiber/metal delamination, by performing the progressive damage analysis. Since δ5 can embody the elastic–plastic response of the crack but without need to interactively correct for crack tip plasticity. The δ5‐R curve‐based macro and meso fracture models were proposed to accurately predict the residual strength and stable crack extension of Glare laminate, which gave further evidence for the effectiveness of δ5‐R curve in characterizing the quasi‐static fracture performance of FML.

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Section: Introductionmentioning

confidence: 99%

Quasi‐static fracture characterization of fiber metal laminate with crack resistance curve based on δ₅

et al. 2022

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“…In most cases, the above scenarios are classified as low‐velocity impacts. Compared to high‐speed and hypervelocity impacts, such impacts do not cause particularly visible signs of damage to the surface of the composite structure, but irreversible damage often occurs to the interior of the structure, which not only is detrimental to the safety of the crew for inspection but also reduces the service life of the aircraft 5–7 . Consequently, the impact damage resistance of CFRP structures has gained significant attention.…”

Section: Introductionmentioning

confidence: 99%

Influence of various damage mechanisms on the low‐velocity impact response of composite laminates

Zou,

Gao,

2023

Polymer Composites

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This study exhibits the effect of different damage mechanisms on the mechanical behavior of composite laminates subjected to low‐velocity impact load. To achieve this, seven low‐velocity impact energies were applied to laminates with five different thicknesses and four unique stacking sequences. The extent of damage was quantitatively evaluated through contact measurements and ultrasonic C‐scan techniques. Numerical simulations, showing good agreement with experimental results, characterized the distribution and evolution of damage within the laminates. The findings reveal that when matrix and delamination damage are predominant, the dent depth increases slowly and is visually invisible, while the delamination area expands almost linearly. Conversely, When fiber damage prevails, the laminate absorbs more energy, leading to rapid increases in dent depth, the appearance of visible cracks, and the occurrence of sharp fluctuations with multiple peaks in contact force and displacement curves. Nonetheless, the delamination area and projection tend to be stable and unchanged. Furthermore, alterations in thickness and stacking sequence directly affect the damage characteristics and energy absorption properties. This research offers valuable theoretical insights and serves as a reference for enhancing the comprehension of the failure mechanism of laminates and optimizing their performance.Highlights Demonstrate the utility of dent depth in identifying changes in damage mechanisms. Evaluate the delamination damage of laminates after impacts by ultrasonic C‐scan techniques. Reveal the regulation of impact response parameters for different damage mechanisms. Investigate the effect of variation in thickness on damage characteristics and energy absorption. Evaluate the impact resistance of laminates with different stacking sequences.

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“…[13,14] However, these structural components are very vulnerable to the low velocity impact (LVI) loading while the airplane is flying. [15][16][17][18] Therefore, it is of great importance to research and predict the residual compressive mechanical properties of the composite stiffened panel thoroughly to ensure the security of the structure of the aircraft.…”

Section: Introductionmentioning

confidence: 99%

A novel methodology to research the residual compressive mechanical properties of composite stiffened panel after low velocity impact based on quantification damage simulation

Xiao

et al. 2022

Polymer Composites

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Composite stiffened panels have become one of the most usual components in the design process of the aircraft's structure due to their splendid mechanical properties in the last decades. The main purpose of this work is investigating and presenting a more precise method to forecast the residual compressive mechanical behavior of the composite stiffened panel. First of all, an axial compression after impact (CAI) test is performed to understand the failure mechanism of different type of L‐shaped stiffened carbon fiber reinforced polymer panels with barely visible impact damage, which is introduced by the low velocity impact test. Subsequently, a finite element model, which contains a quantification damage model, is established in ABAQUS software based on the CAI test results to predict the mechanical behavior of these composite stiffened panels during the CAI test process. Both of the experimental and predicted results demonstrate that the propagation of the delamination caused by LVI is going to exert a destructive influence on the total failure of the composite stiffened panel, and the prediction results of the residual compressive strength of these composite stiffened panels are well consistent to that measured in the CAI test.

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Numerical and experimental investigation of fiber metal laminates with elastomeric layers under low‐velocity impact

Cited by 16 publications

References 35 publications

Quasi‐static fracture characterization of fiber metal laminate with crack resistance curve based on δ₅

Quasi‐static fracture characterization of fiber metal laminate with crack resistance curve based on δ₅

Influence of various damage mechanisms on the low‐velocity impact response of composite laminates

A novel methodology to research the residual compressive mechanical properties of composite stiffened panel after low velocity impact based on quantification damage simulation

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Numerical and experimental investigation of fiber metal laminates with elastomeric layers under low‐velocity impact

Cited by 16 publications

References 35 publications

Quasi‐static fracture characterization of fiber metal laminate with crack resistance curve based on δ5

Quasi‐static fracture characterization of fiber metal laminate with crack resistance curve based on δ5

Influence of various damage mechanisms on the low‐velocity impact response of composite laminates

A novel methodology to research the residual compressive mechanical properties of composite stiffened panel after low velocity impact based on quantification damage simulation

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Quasi‐static fracture characterization of fiber metal laminate with crack resistance curve based on δ₅

Quasi‐static fracture characterization of fiber metal laminate with crack resistance curve based on δ₅