A Numerical and Experimental Investigation into the Impact Response of Sandwich Composites under Different Boundary Conditions

Feng, Dianshi; Loi, Gabriela; Aymerich, Francesco

doi:10.3390/jcs6030088

Cited by 5 publications

(4 citation statements)

References 33 publications

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“…Analyses using x-ray and microscopy show that the damage inflicted on the tested structures comprises a mix of fiber failures, delamination, and tensile/shear matrix cracks. 56,57 When subjected to similar impact energies, 0 3 = þ 45= À 45 ½ s and 0 3 =90 3 ½ s laminates showed quite different damage patterns. The damage process of LVI involves bending at the bottom of the composite laminate structure, which triggers the generation of matrix tensile cracks at the bottom.…”

Section: Resultsmentioning

confidence: 99%

“…Figure 5 presents the x‐ray images of impact damage at different energy levels. Analyses using x‐ray and microscopy show that the damage inflicted on the tested structures comprises a mix of fiber failures, delamination, and tensile/shear matrix cracks 56,57 . When subjected to similar impact energies,

{([], 0_{3} / + 45 / - 45)}_{s}

and

{([], 0_{3} / 90_{3})}_{s}

laminates showed quite different damage patterns.…”

Section: Resultsmentioning

confidence: 99%

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Research on low‐velocity impact resistance of carbon fiber composite laminates

Hou,

Aymerich,

Feng

2024

Polymer Composites

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This research conducts a comprehensive experimental and numerical analysis of carbon fiber composite laminates under low‐velocity impact conditions. Split Hopkinson Pressure Bar (SHPB) was employed to conduct impact testing on laminates with two layup sequences ( and ) under impacts ranging from 2 to 6 J. For assessing damage in laminates, a comprehensive progressive damage model and a simplified model were developed. The primary distinction between these models lies in the fact that the former incorporates the strengthening effect of compression on the delamination behavior, while the latter does not. Both models produce a good agreement with experimental results in terms of force–time, force–displacement curves, and absorbed energies. However, notable differences were noted in the predicted internal damage; the simplified model was underpredicted in terms of damage size and distribution compared to the comprehensive progressive damage model.Highlights Impact tests were conducted on and composites. In order to simulate damage caused by impacts in laminates, an energy‐based damage model was created, and cohesive elements were utilized to model interlaminar delamination. The strengthening effect of compression was explored. Distinct damage criteria were established for two cases. Damage detection of composites by x‐rays.

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Section: Resultsmentioning

confidence: 99%

{([], 0_{3} / + 45 / - 45)}_{s}

and

{([], 0_{3} / 90_{3})}_{s}

laminates showed quite different damage patterns.…”

Section: Resultsmentioning

confidence: 99%

Research on low‐velocity impact resistance of carbon fiber composite laminates

Hou,

Aymerich,

Feng

2024

Polymer Composites

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“…There will be a reduction in structural stability due to internal damage caused by impact loading [2, 3]. Internal damage and indentation are linked by the delamination threshold force, and delamination in composite materials has previously been studied using stress‐based damage accumulation mechanisms [4, 5]. Three‐point bending and charpy impact test results were also used to ascertain the impact response and flexural behaviour patterns of numerous laminates during three‐point bending [6].…”

Section: Introductionmentioning

confidence: 99%

Effect of ply orientation and laminate thickness on carbon fibre reinforced polymers under low‐velocity impact

Hiremath

Reddy

2022

Materialwissenschaft Werkst

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Composite materials, which have gained prominence in the aerospace industry due to their high strength-to-weight ratio, are vulnerable to delamination damage when struck by low-speed projectiles due to their low through-thickness strength. This paper presents the experimental evaluation of a composite plate subjected to low-velocity impact. The plates under discussion were constructed using a carbon fibre reinforced polymer laminate with a quasi-isotropic ply structure. Experiments were carried out using a conical-shaped impactor on carbon/epoxy laminated plates with three different orientations ([0/0] 4 s, [0/90] 2 s, and [45/0-45/90] s) that were put through two distinct impact energies (7 J and 14 J). Impact response is determined using drop-weight impact tests. The techniques of ultrasonic C-scan, field emission scanning electron microscopy (FESEM), and surface micrographs were integrated to provide a new and in-depth understanding of damage evolution and failure mechanisms in composite laminates. Damage resistance appears to decrease as impact energy increases. Furthermore, thicker laminates have lower absorbed energy but, on the other hand, more widespread delamination due to increased bending stiffness. Furthermore, quasi-isotropic laminates outperform in terms of damage resistance and increased energy absorption rates by 8 % to 15 %. The efficacy and logic of the suggested model were shown by a strong connection between experimental results.

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“…The fatigue damage formulations are extensions of bilinear cohesive laws for quasistatic loading [6][7]. The propagation of fatigue delamination is described by a variant of the Paris law:…”

Section: Methodsmentioning

confidence: 99%

Prediction of Fatigue-Driven Delaminations in Composite Laminates Using Cohesive Zone Model

Xiang,

Feng

Proceedings of the Eleventh International Conference on Engineering Computational Technology

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This paper presents an improved strategy based on Cohesive Zone Model (CZM) for prediction of delamination growth in composite laminates under fatigue loading. The fatigue delamination models describe the crack growth rate as a function of the number of cycles using coefficient of the Paris law-like curve, no crack tip tracking algorithm being required. The proposed CZM fatigue models were implemented into ABAQUS/Explicit via a user-written subroutine VUMAT. The developed models were finally used to simulate fatigue-driven delaminations in composite laminates subjected to mode I, mode II and mixed-mode loading scenarios. Numerical predictions was compared with experimental data that are available from open literature, and a good agreement were obtained.

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A Numerical and Experimental Investigation into the Impact Response of Sandwich Composites under Different Boundary Conditions

Cited by 5 publications

References 33 publications

Research on low‐velocity impact resistance of carbon fiber composite laminates

Research on low‐velocity impact resistance of carbon fiber composite laminates

Effect of ply orientation and laminate thickness on carbon fibre reinforced polymers under low‐velocity impact

Prediction of Fatigue-Driven Delaminations in Composite Laminates Using Cohesive Zone Model

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