On the determination of out-of-plane elastic properties of honeycomb sandwich panels

Mujika, F.; Pujana, J; Olave, Mireia

doi:10.1016/j.polymertesting.2010.12.005

Cited by 32 publications

(21 citation statements)

References 14 publications

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“…Two ASTM standard test methods are followed in this study; ASTM D1621 [18] and ASTM C365/365M [19]. These are the most established test standards found in the literature for flatwise compressive tests of foam materials [10,11,13,[21][22][23]. The force and the displacement of the crosshead are recorded by a computer system connected to the test machine as per the recommendation in the standards.…”

Section: Methodsmentioning

confidence: 99%

Compression of structural foam materials – Experimental and numerical assessment of test procedure and specimen size effects

Rajput

Burman

Köll

et al. 2017

Jnl of Sandwich Structures & Materials

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Section: Methodsmentioning

confidence: 99%

Compression of structural foam materials – Experimental and numerical assessment of test procedure and specimen size effects

Rajput

Burman

Köll

et al. 2017

Jnl of Sandwich Structures & Materials

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“…Hu and al presented a complete review of the various Kinematics and theories concerning the sandwich composite modeling [8] Experimental methods on testing the elastic properties of honeycomb core have been developed. Young's moduli in the thickness direction were determined by compression tests [9]. Cunningham et al proposed a new measurement technique for estimating the shear strain in a totally enclosed core [10].…”

Section: Introductionmentioning

confidence: 99%

Numerical-Experimental characterization of honeycomb sandwich panel and numerical modal analysis of implemented delamination

Bendada¹,

Boutchicha

Chouiter

et al. 2019

Frattura Ed Integrità Strutturale

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In this paper, a numerical characterization of aluminum honeycomb sandwich panel and experimental validation are proposed. Firstly, numerical homogenization approach to predict the elastic properties of the core only are performed using initial finite element model of Representative Volume Element (RVE) which does not take into account the double thickness wall existing in aluminum core structure. According to these initial parameters, finite element model of sandwich composite plate is constructed to extract its elasto-dynamic characteristics. In order to validate the numerical achievements, Experimental Modal Analysis of sandwich plate was carried out. Secondly, the double thickness wall is selected to be introduced in the RVE because of important error between results, new comparative study validates the improved elastic parameters and illustrate that the double thickness wall play an important role in the homogenization procedure. Furthermore, the influence of the delamination defect on the vibration behavior of the composite panel is investigated using the validated 3-D finite element model.

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“…Fiber reinforced polymer composite sandwich panel (FRPCSP) with lattice truss cores are increasingly used in aerospace and shipping industry, which have been designed and fabricated during the last decade [1][2][3][4][5][6]. Their mechanical behaviors have been tested and analyzed at room temperature, and the superior mechanical properties have been revealed [7][8][9][10].…”

Section: Introductionmentioning

confidence: 99%

Localized damage response of carbon fiber reinforced polymer composite sandwich panel after thermal exposure

et al. 2016

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An experimental study was conducted to investigate the effect of thermal exposure on indentation behaviors of carbon fiber reinforced polymer composite sandwich panel (CFRPCSP) with pyramidal truss cores. Composite sandwich panelswere fabricated by the hot press molding method. Subsequently, composite sandwich panels were exposed to different temperatures for 6 h. After thermal exposure, quasi-static indentation tests were carried out at room temperature. Then, the effect of thermal exposure on the failure mechanism, indentation load and energy absorption were analyzed and discussed. The results showed that the indentation load and energy absorption decreased as exposure temperature increased, which was caused by the degradation of the matrix properties and fiber-matrix interface properties at high temperature. In addition to the decreasing of the indentation load and energy absorption, the failure modes also changed with exposure temperature. It is expected that this study can provide useful information for the design and application of composite sandwich panel with pyramidal truss cores at high temperature.

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On the determination of out-of-plane elastic properties of honeycomb sandwich panels

Cited by 32 publications

References 14 publications

Compression of structural foam materials – Experimental and numerical assessment of test procedure and specimen size effects

Compression of structural foam materials – Experimental and numerical assessment of test procedure and specimen size effects

Numerical-Experimental characterization of honeycomb sandwich panel and numerical modal analysis of implemented delamination

Localized damage response of carbon fiber reinforced polymer composite sandwich panel after thermal exposure

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