Damage Resistance Characteristics of Thick-Core Honeycomb Composite Panels

Feraboli, Paolo

doi:10.2514/6.2006-2169

Cited by 12 publications

(29 citation statements)

References 15 publications

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“…It has been shown frequently in the literature that their value is independent of impact energy, and it stays constant for increasing values of available kinetic energy. [3][4][5][6]11 Furthermore, for modern composite systems, which are relatively strain-rate insensitive in this low-velocity regime, it has been found that the value of the critical force is very close to the mean static failure load (MSFL) of the laminate, obtained by means of quasi-static indentation tests.…”

Section: A Force-and Energy-time Historiesmentioning

confidence: 67%

“…This trend has been verified for solid laminates of various span/thickness ratios, 3−6 panel curvature, 4 stacking sequences, 3 as well as honeycomb-core sandwich panels. 5 The advantages of em- ploying the force-energy curve of Fig. 12, obtained by preliminary QSI testing, are dual.…”

Section: Force-energy Curves and Analogy Between Quasi-static And mentioning

confidence: 99%

“…12 shows the quasi-static force-energy curves obtained by indentation of thick-core, thick-face sheet honeycomb panels for a candidate blended-wing-body (BWB) crown panel. 5 The three curves refer to three different face sheet thicknesses. Superimposed on the curve are the peak force-energy data points recorded during subsequent impact testing of three and four panels per face sheet thickness.…”

Section: Force-energy Curves and Analogy Between Quasi-static And mentioning

confidence: 99%

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Some Recommendations for Characterization of Composite Panels by Means of Drop Tower Impact Testing

Feraboli

2006

Journal of Aircraft

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Instrumented drop tower impact-test devices have been long used for inflicting impact damage onto test specimens for damage tolerance characterization of composite panels. However, there are many considerations that need to be made regarding the test setup to avoid the inconveniences related to the acquisition and interpretation of the impact data. Because there are many advantages associated with this type of experiment, to benefit fully from the amount of information available from an impact test, a multiparameter approach needs to be used, and the entire test history needs to be interpreted. The previously demonstrated similitude between impact and quasistatic indentation tests is used to gain even further understanding in the mechanics of the event and its associated damage mechanisms. The fundamental characteristics of damage resistance tests are illustrated for the engineer being initiated to this type of work, particularly with regards to the understanding of impact traces. A summary of lessons learned is reported, and guidelines for the setup of the test and the interpretation of the results are given. A set of recommendations for best practice is given with the intent of laying down the foundation for a standard approach to future research programs.

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Section: A Force-and Energy-time Historiesmentioning

confidence: 67%

Section: Force-energy Curves and Analogy Between Quasi-static And mentioning

confidence: 99%

Section: Force-energy Curves and Analogy Between Quasi-static And mentioning

confidence: 99%

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Some Recommendations for Characterization of Composite Panels by Means of Drop Tower Impact Testing

Feraboli

2006

Journal of Aircraft

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“…Interestingly, the high variation in modulus values observed previously for this material form is not to be attributed to a variability in the manufacturing process, and hence a variation in specimen to specimen or batch to batch, but as variability within a single specimen due to the nature of the material substructure. 13 From a technical standpoint, use of strain gages imposes great limitations, as their length is smaller than the dominant length scale of the material. Strain gages 0.125 and 0.250 in long (3.2 and 6.3 mm respectively) have shown to yield unacceptably high variation in modulus measurements depending on their location, and should therefore not be used for this material form.…”

Section: Discussionmentioning

confidence: 99%

Modulus Measurement for Prepreg-based Discontinuous Carbon Fiber/Epoxy Systems

Feraboli

Peitso

Cleveland

et al. 2009

Journal of Composite Materials

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The elastic modulus of discontinuous carbon fiber/epoxy laminates produced by compression molding of chopped unidirectional prepreg tape is measured by several means. Commercial applications for this type of material form already exist, such as Hexcel HexMC Õ . Although the average elastic modulus of this material has been shown to be as high as that of the continuous fiber quasiisotropic benchmark, its non-homogenous nature gives rise to variations as high as 19% in the measurement by means of strain gage or extensometer. This phenomenon would be attributed to the variability of the manufacturing process, were it not for the fact that strength variation is much lower, with a maximum of 9%. In order to assess whether the variation observed is a result of the measurement technique and not an actual variation in material properties, a series of tensile tests is conducted while systematically varying strain gage length and location. The measurements are then compared relative to each other as well as to multiple extensometer readings along the length and opposite sides of the specimen. Digital image correlation (DIC) technique is used to gain further insight on the observed phenomena, and it has shown to be fundamental to obtain a full-field strain measurement, which is more repeatable than any of the traditional measurement techniques. Furthermore, DIC shows that complex strain distributions exist on the surface of the specimen, varying greatly along the width and across the length of the specimen, and these are associated to the non-homogeneous nature of the sub-structure.

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“…Hazizzian and Cantwell [9] have investigated low velocity impact of sandwich structures and attended to absorbed energy in structures. Feraboly [10] and Olsson and McManus [11] have experimentally and numerically studied of damage resistance characteristics of honeycomb composite panels. For numerical research authors have used popular code ABAQUS [12] or LS-DYNA [13].…”

Section: Introductionmentioning

confidence: 99%

Characterization of Low Velocity Local Impact of Sandwich Panels

Dolganina¹,

Sapozhnikov²

2014

PNRPU MB

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The present paper deals with analysis of local indentation and their energies in point loading of sandwich panel with thin orthotropic composite faces and honeycomb core as an introduction for low velocity impact loading and energy absorbing in sandwich structures.Energy is consumed in two stages: local indentation of sandwich panel skin and bending of sandwich panel. If the impact is located near support or clamping only first stage (indentation of sandwich panel) will be presented. Here the analytical model has been used assuming a rigid-perfectly plastic compressive behaviour of the honeycomb core and membrane behaviour of orthotropic skin for large indentation of sandwich panel. In experimental work were investigated two types of sandwich panels, which consisted of different laminated skins: cross-ply of unidirectional CFRP and AFRP (aramid fabric reinforced plastic) and core honeycomb materials (impregnated paper like Nomex and one layer of glass fabric reinforced plastic). Length of cell side is 2.5 mm. Skins were made with symmetrical lay-ups [0/90]s and [45/-45]s. For indentation test we used steel balls with radius 5-30 mm, speed of loading was 2 mm/min. The experimental results are in good agreement with the analysis. These results can be used in impact loading and energy absorption studies of laminated structures by integrating of "local load vs deflection" curve.

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Damage Resistance Characteristics of Thick-Core Honeycomb Composite Panels

Cited by 12 publications

References 15 publications

Some Recommendations for Characterization of Composite Panels by Means of Drop Tower Impact Testing

Some Recommendations for Characterization of Composite Panels by Means of Drop Tower Impact Testing

Modulus Measurement for Prepreg-based Discontinuous Carbon Fiber/Epoxy Systems

Characterization of Low Velocity Local Impact of Sandwich Panels

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