Effect of structural parameters on low-velocity impact behavior of aluminum honeycomb sandwich structures with CFRP face sheets

He, Wentao; Lu, Yao; Meng, Xiangjian; Sun, Guangyong; Xie, De; Liu, Jingxi

doi:10.1016/j.tws.2019.01.022

Cited by 141 publications

(51 citation statements)

References 49 publications

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“… Note : The subscripts f and m represent fiber and matrix; t and c denote tensile and compression. [ 38–41 ] …”

Section: Numerical Modelsmentioning

confidence: 99%

Mechanical response and critical failure mechanism characterization of notched carbon fiber reinforced polymer laminate subjected to tensile loading

Wang

et al. 2020

Polymer Composites

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The purpose of this article is to investigate the mechanical responses and critical failure mechanisms of notched composite laminates with the aid of numerical and experimental approaches, considering the effect of notch geometry, notch size and off-axis angle. Quasi-static tensile tests are implemented to study the influence of design variables on the mechanical response, during which the relationship of force vs displacement and strain distributions are collected by means of digital image correlation technique. Subsequently, the numerical simulation is implemented in ABAQUS/Explicit through a progressive damage model integrated with a VUMAT subroutine. Meanwhile, the initiation and propagation of damage are explored through the damage morphologies, combining with the logarithmic strain components from numerical predictions. Results show that notch strength and failure strain are more closely associated with off-axis angle and notch size compared with notch geometry. In addition, with the increase of off-axis angle, the contribution of fiber is increasingly weakened, the damage mode gradually varies from fiber fracture to pull out accompanied with the damage near the notch changing from fiber fracture to delamination. Meanwhile, the critical failure mechanism varies from tension dominated to tension-shear/ shear dominated as the off-axis angle grows larger. K E Y W O R D S composite laminates, digital image correlation, failure mechanism, notch strength 1 | INTRODUCTION Carbon fiber reinforced polymer (CFRP) laminate has been increasingly applied in light of its outstanding performance and superior damage tolerance. Compared with traditional materials, it has many typical advantages, such as high specific strength and stiffness, [1-3] improved impact and fatigue resistance, [4-6] perfect corrosion resistance and moistureproof ability, [7] and so forth. During the application, in addition to the complicated loading conditions, the unavoidable notches for mechanical connections also pose a risk to the load-bearing capacity and service life. In addition, notch geometry and notch size are usually diversified to facilitate the connection of structural components, which significantly diminishes the mechanical properties and further complicates the exploration of mechanical behaviors. Furthermore, due to the anisotropy, brittleness, heterogeneity, and obvious difference between the interlaminar and intralaminar property, damage patterns, and failure mechanisms of composites also present complexity and diversity. [8]

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“… Note : The subscripts f and m represent fiber and matrix; t and c denote tensile and compression. [ 38–41 ] …”

Section: Numerical Modelsmentioning

confidence: 99%

Mechanical response and critical failure mechanism characterization of notched carbon fiber reinforced polymer laminate subjected to tensile loading

Wang

et al. 2020

Polymer Composites

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“…Once the damage initiation is met at a material point ( Ri≥1.0), the corresponding stiffness degradation in different directions ( ft, fc: fiber tension and compression; mt, mc: matrix tension and compression; ld: inter-laminar delamination) can be obtained based on damage variable ( 0≤di≤1) in which n is set to be 1. 37–39 Because of the irreversible energy dissipation results from material damage, the damage variable should be updated according to the previous damage state …”

Section: Progressive Damage Models Of Fmlsmentioning

confidence: 99%

“…in which n is set to be 1. [37][38][39] Because of the irreversible energy dissipation results from material damage, the damage variable should be updated according to the previous damage state…”

Section: Damage Model Of Carbon Fiber Composite Materialsmentioning

confidence: 99%

Tensile mechanical behavior and failure mechanisms of multihole fiber metal laminates—Experimental characterization and numerical prediction

Wang

et al. 2020

Journal of Reinforced Plastics and Composites

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This work mainly investigates the effects of the hole number and layer direction on the tensile mechanical behavior and failure mechanisms of multihole fiber metal laminates by experimental and numerical methods. With the aid of digital image correlation technique, tensile tests are implemented to obtain mechanical responses of different multihole fiber metal laminates. Subsequently, numerical simulation considering thermal residual stress is conducted to elucidate the failure modes and progressive damage evolution of multihole fiber metal laminates, which integrates the progressive damage model of composite laminates and a cohesive zone model between aluminum sheet/composite laminates. Finally, numerical predictions are found in a good agreement with experimental measurements, in terms of mechanical responses and fracture morphologies. Results demonstrate that the number of holes has negligible influence on the ultimate tensile strength, whereas affects the final failure strain of multihole fiber metal laminates evidently. With the increase of layer direction, the fracture morphology changes from evident brittle fracture to fiber pull-out and matrix damage, which indicates that the critical failure mechanism of multihole fiber metal laminates changes from tension dominated to tension–shear dominated. Additionally, the longer loading history from initial damage to final failure of composite laminates demonstrates the significance of considering progressive damage behavior in numerical simulation.

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“…He et al investigated the effect of design parameters on the impact behaviors of honeycomb sandwich composites. The parameters affecting impact loading the most were found to be face sheet thickness and honeycomb cell wall thickness, while core height was determined to be the most ineffective parameter 26 .…”

Section: Introductionmentioning

confidence: 95%

The Flexural Fatigue Behavior of Honeycomb Sandwich Composites Following Low-Velocity Impacts

Solmaz¹,

Topkaya

2020

Preprint

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This study experimentally investigated the flexural fatigue behaviors of honeycomb sandwich composites subjected to low velocity impact damage by considering the type and thickness of the face sheet material, the cell size and the core height parameters. First, the static strength of undamaged specimens was determined by three-point bending loads, and calculating their fatigue lives; secondly, the fatigue lives of the specimens damaged by low velocity impact tests were then determined. Increasing the face sheet thickness and core height increased the flexural strength, while increasing the cell size decreased the flexural strength. Low velocity impact damage decreased the flexural strength and fatigue lives but increased the damping ratio for all specimens.

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Effect of structural parameters on low-velocity impact behavior of aluminum honeycomb sandwich structures with CFRP face sheets

Cited by 141 publications

References 49 publications

Mechanical response and critical failure mechanism characterization of notched carbon fiber reinforced polymer laminate subjected to tensile loading

Mechanical response and critical failure mechanism characterization of notched carbon fiber reinforced polymer laminate subjected to tensile loading

Tensile mechanical behavior and failure mechanisms of multihole fiber metal laminates—Experimental characterization and numerical prediction

The Flexural Fatigue Behavior of Honeycomb Sandwich Composites Following Low-Velocity Impacts

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