Experimental and numerical studies on indentation and perforation characteristics of honeycomb sandwich panels

Sun, Guangyong; Chen, Dongdong; Huo, Xintao; Zheng, Gang; Li, Qing

doi:10.1016/j.compstruct.2017.09.025

Cited by 131 publications

(46 citation statements)

References 52 publications

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“…The identified failure modes were permanent indentation on the impacted facesheet and localized honeycomb core crush under the impact location. Sun et al [31] studied the effect of skin thickness, core thickness, core height and cell size on indentation characteristics, such as peak forces, failure modes and energy absorption, for sandwich panels with aluminum facesheets and honeycomb core. The principal failure mechanisms identified were shear and tension damage for the facesheets and plastic folding and buckling for the honeycomb core.…”

Section: Introductionmentioning

confidence: 99%

Low velocity failure and integrity assessment of foam core sandwich panels

Mocian

Constantinescu

Sorohan

et al. 2019

Frattura Ed Integrità Strutturale

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Impact resistance and energy absorbing capability are of great interest in the design of composite sandwich structures. This paper experimentally studies damage, failure and energy absorption properties of foam core sandwich panels with aluminum and glass fiber reinforced plastic (GFRP) facesheets subjected to low velocity impact. Tests are performed using a drop weight impact tower at different impact velocities. The energy absorbing capabilities of aluminum and composite facesheet sandwich panels with PUR and PS foam core are evaluated by means of absorbed energy-time histories and by specific parameters as normalized absorbed energy, specific energy absorption, and crush force efficiency. Stiffer panels behave better at lower impact velocities, while more ductile ones do better if impact energy is increased.

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Section: Introductionmentioning

confidence: 99%

Low velocity failure and integrity assessment of foam core sandwich panels

Mocian

Constantinescu

Sorohan

et al. 2019

Frattura Ed Integrità Strutturale

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“…In recent years, digital image correlation (DIC) technique has been extensively applied for its remarkable capability in strain field data collecting and real‐time data processing. Sun et al [ 30 ] characterized the indentation and perforation of honeycomb sandwich panels by means of the skin deformation collected by DIC technique. Mao et al [ 31 ] studied the mechanical properties and cracking propagation resistance behaviors of C/SiC composites under tensile loading through the strain evolution.…”

Section: Introductionmentioning

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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“…Honeycomb structures have been widely used in sandwich panel as a light energy absorber. Sun et al [2] have investigated the effect of face sheet's thickness and height of honeycomb on energy absorption capacity under quasi-static compression loading using experimental and numerical methods.…”

Section: Introductionmentioning

confidence: 99%

Collapse of honeycomb cell as a result of buckling or plastic hinges, analytical, numerical and experimental study

Galehdari

Kadkhodayan

2019

J Braz. Soc. Mech. Sci. Eng.

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The honeycomb structure collapse during energy absorption and deformation is considered as one of the important subjects for researchers. In this paper, a combined analytical, numerical and experimental analysis on the collapse load of hexagonal aluminum honeycombs due to buckling or plastic collapse of the unit cells under flatwise compressive loading is performed. To analyze the collapse load, some analytical equations are derived for buckling and forming plastic hinges using the frame element. The amounts of these loads are measured for a single-row aluminum honeycomb structure, and the smallest one is selected as collapse load. The results show that the main cause of structure collapse is the formation of plastic hinges. To evaluate the analytical results and to propose a valid numerical simulation method, the quasi-static pressure test is performed. Furthermore, the structure collapse is also simulated by Abaqus software. The maximum difference between the numerical and experimental collapse load is 2.5%. Moreover, the deformed shape of the structure is very similar to the experimental one. The numerical simulation method and the proposed analytical relations can be used to analyze the collapse in other metal honeycomb structures.

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Experimental and numerical studies on indentation and perforation characteristics of honeycomb sandwich panels

Cited by 131 publications

References 52 publications

Low velocity failure and integrity assessment of foam core sandwich panels

Low velocity failure and integrity assessment of foam core sandwich panels

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

Collapse of honeycomb cell as a result of buckling or plastic hinges, analytical, numerical and experimental study

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