Hypervelocity impact on carbon fibre reinforced plastic / aluminium honeycomb: Comparison with whipple bumper shields

Taylor, Emma A.; Herbert, M.K.; Vaughan, Brian; McDonnell, J. A. M.

doi:10.1016/s0734-743x(99)00132-3

Cited by 57 publications

(21 citation statements)

References 5 publications

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“…The sandwich structure considered in this work is made of an aluminium honeycomb core and carbon composite skins, this last being a typical combination of materials employed in some real-world aerospace engineering applications, like those presented in [8,9,12,25]. The material properties of the aluminium alloy used for the honeycomb core as well as those of the elastic air (these last taken from [2]) are listed in Table 3.…”

Section: Numerical Studymentioning

confidence: 99%

A multi-scale approach for the optimum design of sandwich plates with honeycomb core. Part I: homogenisation of core properties

Catapano

Montemurro

2014

Composite Structures

118

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This work deals with the problem of the optimum design of a sandwich panel. The design process is based on a general two-level optimisation strategy involving di erent scales: the meso-scale for both the unit cell of the core and the constitutive layer of the laminated skins and the macro scale for the whole panel. Concerning the meso-scale of the honeycomb core, an appropriate model of the unit cell able to properly provide its e ective elastic properties (to be used at the macro-scale) must be conceived. To this purpose, in this rst paper, we present the numerical homogenisation technique as well as the related nite element model of the unit cell which makes use of solid elements instead of the usual shell ones. A numerical study to determine the e ective properties of the honeycomb along with a comparison with existing models and a sensitive analysis in terms of the geometric parameters of the unit cell have been conducted. Numerical results show that shell-based models are no longer adapted to evaluate the core properties, mostly in the context of an optimisation procedure where the parameters of the unit cell can get values that go beyond the limits imposed by a 2D model.

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Section: Numerical Studymentioning

confidence: 99%

A multi-scale approach for the optimum design of sandwich plates with honeycomb core. Part I: homogenisation of core properties

Catapano

Montemurro

2014

Composite Structures

118

View full text Add to dashboard Cite

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“…A more commonly held view is that the presence of a honeycomb core is unfavorable to the shielding performance. Taylor et al [3] quantified the degradation in performance through inclusion of a scaling factor which acts to reduce the effective rear facesheet thickness by 50% in definition of the panel https://ntrs.nasa.gov/search.jsp?R=20090016347 2018-05-10T20:13:11+00:00Z ballistic limit at hypen-elocities (i.e. molten and/or vaporized ejecta).…”

Section: Honeycomb Sandwich Panelsmentioning

confidence: 99%

Honeycomb vs. foam: Evaluating potential upgrades to ISS module shielding

2010

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“…[12]. Schaefer and Ryan [13] conducted numerous HVI tests on different sandwich configurations with varying projectile sizes, velocities, and impact angles.…”

Section: Wicklein Et Al / International Journal Of Impact Engineeringmentioning

confidence: 99%

Hypervelocity impact on CFRP: Testing, material modelling, and numerical simulation

Wicklein

Ryan

White³

et al. 2008

International Journal of Impact Engineering

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This paper describes the derivation and validation of a numerical material model that predicts the highly dynamic behaviour of CFRP (carbon fibre reinforced plastic) under hypervelocity impact. CFRP is widely used in satellites as face sheet material in CFRP-Al/HC sandwich structures (HC = honeycomb), that can be exposed to space debris. A review of CFRP-Al/HC structures typically used in space was performed. Based on this review, a representative structure in terms of materials and geometry was selected for study in the work described here. An experimental procedure for the characterisation of composite materials is documented in [1]. The test results from the CFRP of the current study allow for the derivation of an experimentally based orthotropic continuum material model data set that is capable of predicting the mechanical behaviour of CFRP under hypervelocity impact. Such a data set was not previously available. In [2] an orthotropic material data set was used for modelling HVI on AFRP (aramid fibre reinforced plastic), which shows relatively high deformability before failure. The enhancements of the modelling approaches in [1] and [3] necessary to model brittle CFRP are specified. An experimental hypervelocity impact campaign was performed at two different two stage light gas guns which encompassed both normal and oblique impacts for a range of impact velocities and projectile diameters. Validation of the numerical model is provided through comparison with the experimental results. For that purpose measurements of the visible damage of the face sheets and of the HC core are conducted. In addition, the numerically predicted damage within the CFRP is compared to the delamination areas found in ultrasonic scans.

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Hypervelocity impact on carbon fibre reinforced plastic / aluminium honeycomb: Comparison with whipple bumper shields

Cited by 57 publications

References 5 publications

A multi-scale approach for the optimum design of sandwich plates with honeycomb core. Part I: homogenisation of core properties

A multi-scale approach for the optimum design of sandwich plates with honeycomb core. Part I: homogenisation of core properties

Honeycomb vs. foam: Evaluating potential upgrades to ISS module shielding

Hypervelocity impact on CFRP: Testing, material modelling, and numerical simulation

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