Modeling of Nomex® Honeycomb Cores, Linear and Nonlinear Behaviors

Gornet, Laurent; Marguet, Steven; Marckmann, Gilles

doi:10.1080/15376490701675370

Cited by 20 publications

(8 citation statements)

References 13 publications

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“…They showed the stages of core crush in Nomex and Aluminum honeycomb cores, including buckling initiation, progressive folding, and finally, densification using experimental examples. Gornet, Marguet, and Marckmann [15]; Heimbs [16]; and Kaman, Solmax, and Turan [17] also developed computationally implemented models for honeycomb core crush response with good results. The current model will implement an idealization of the flatwise compression response showed experimentally in these works.…”

Section: A Current Cai Modelsmentioning

confidence: 99%

Compression After Impact on Honeycomb Core Sandwich Panels with Thin Facesheets, Part 2: Analysis

McQuigg

Kapania

Scotti

et al. 2012

53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

3
2
8
0

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A two part research study has been completed on the topic of compression after impact (CAI) of thin facesheet honeycomb core sandwich panels. The research has focused on both experiments and analysis in an effort to establish and validate a new understanding of the damage tolerance of these materials. Part 2, the subject of the current paper, is focused on the analysis, which corresponds to the CAI testings de-

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Section: A Current Cai Modelsmentioning
confidence: 99%

Compression After Impact on Honeycomb Core Sandwich Panels with Thin Facesheets, Part 2: Analysis
McQuigg
¹
,
Kapania
²
,
Scotti
³

et al. 2012
53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
3
2
8
0
View full text Add to dashboard Cite

show abstract

“…They showed the stages of core crush in Nomex and aluminum honeycomb cores, including buckling initiation, progressive folding, and finally densification using experimental examples. Gornet et al [15]; Heimbs [16]; and Kaman et al [17] also developed computationally implemented models for honeycomb core crush response with good results. The current model will implement an idealization of the flatwise compression response showed experimentally in these works.…”

Section: A Current Cai Modelsmentioning
confidence: 99%

“…Experimental flatwise core crush results for Nomex material generally show a brittle wall collapse and folding that results in a succession of rising and falling stress resultant for a displacement controlled test [14][15][16][17]. This behavior is averaged to a single stress value, which was selected based on the idealization of core crush experimental results.…”

Section: B Honeycomb Core Behaviormentioning
confidence: 99%

Compression After Impact Analysis on Thin Face Sheet Honeycomb Core Sandwich Panels
McQuigg¹,
Kapania²,
Scotti³
et al. 2014
Journal of Spacecraft and Rockets
2
0
1
0
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A research study has been conducted on compression after impact of thin facesheet honeycomb core sandwich panels. This paper is focused on the modeling and analysis used to simulate the tests described in a companion paper. Of interest are composite sandwich panels with aerospace applications, which contain either a 3 or 6 lb∕ft 3 honeycomb core. It was found that compression after impact testing of these coupons resulted in either an indentation propagation failure for the lower density core or a crack propagation failure mode for the higher density core. An analysis model is developed to account for both modes through the inclusion of progressive failure analysis of the facesheets and a homogenized, nonlinear material model for the honeycomb core. In addition, significant impact damage detail is included in the model based on experimental observation. Analysis results are compared with the experimental results for each of the 24 sandwich panel specimens tested. Good agreement of failure mode predictions with test results demonstrates the importance of considering both facesheet and core failure, as well as the initial damage severity. Finally, a parametric study highlights the strength benefits compared with mass penalty for various core densities.Young's modulus G = shear modulus h max = maximum dent depth I = stress invariant i = subscript indicator W = waviness coefficient x = global coordinate or axis, coupon width direction y = global coordinate or axis, coupon load direction z = global coordinate or axis, coupon through the thickness direction ϵ = strain σ = stress υ = Poisson's ratio ϕ f = fiber volume fraction ϕ m = matrix volume fraction

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“…One of the leading simulation approaches is FE-based homogenization whose principles were first formulated in [23]. Such approach may be also applied to the periodic heterogeneous microstructures like in sandwich panels involving honeycomb cores discussed in [24]. As concern analysis of damage evolution different simulation tools have been applied for metal-matrix composites [25] and ceramic-matrix composites [26].…”

Section: Introductionmentioning
confidence: 99%

Damage evolution in AA2124/SiC metal matrix composites under tension with consecutive unloadings
Rutecka
¹
,
Kursa
²
,
Pietrzak
³

et al. 2020
Archiv.Civ.Mech.Eng
8
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0
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Nonlinear properties of metal matrix composites (MMCs) are studied. The research combines results of loading–unloading tensile tests, microstructural observations and numerical predictions by means of micromechanical mean-field models. AA2124/SiC metal matrix composites with SiC particles, produced by the Aerospace Metal Composites Ltd. (AMC) are investigated. The aluminum matrix is reinforced with 17% and 25% of SiC particles. The best conditions to evaluate the current elastic stiffness modulus have been assessed. Tensile tests were carried out with consecutive unloading loops to obtain actual tensile modulus and study degradation of elastic properties of the composites. The microstructure examination by scanning electron microscopy (SEM) showed a variety of phenomena occurring during composite deformation and possible sources of elastic stiffness reduction and damage evolution have been indicated. Two micromechanical approaches, the incremental Mori–Tanaka (MT) and self-consistent (SC) schemes, are applied to estimate effective properties of the composites. The standard formulations are extended to take into account elasto-plasticity and damage development in the metal phase. The method of direct linearization performed for the tangent or secant stiffness moduli is formulated. Predictions of both approaches are compared with experimental results of tensile tests in the elastic–plastic regime. The question is addressed how to perform the micromechanical modelling if the actual stress–strain curve of metal matrix is unknown.

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Modeling of Nomex® Honeycomb Cores, Linear and Nonlinear Behaviors

Cited by 20 publications

References 13 publications

Compression After Impact on Honeycomb Core Sandwich Panels with Thin Facesheets, Part 2: Analysis

Compression After Impact on Honeycomb Core Sandwich Panels with Thin Facesheets, Part 2: Analysis

Compression After Impact Analysis on Thin Face Sheet Honeycomb Core Sandwich Panels

Damage evolution in AA2124/SiC metal matrix composites under tension with consecutive unloadings

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