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Bending Characteristics of CFRP Hexagon Honeycombs Stiffened with Corrugated Cores under Transverse Quasi-Static Impact Loading

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Iranian Journal of Science and Technology, Transactions of Mechanical Engineering Aims and scope Submit manuscript

Abstract

This paper aims to suggest analytical bending characteristics models for CFRP hexagon honeycomb panels stiffened with new versatile configurations of rectangular, circular, elliptical, and corrugated cores. Stiffened sandwich panels have broad application to improve bending and torsional stiffness of the automotive, aerospace, and marine body structures and their crashworthiness durability. In this study, analytical bending characteristics and elastic response equations for each introduced stiffened hexagon honeycomb panel were derived when subjected to transverse quasi-static impact loading. These equations are based on the theory of curved laminated beams, the classical lamination method, and the Tsai-Hill failure theory. The employed finite element method (FEM) and the performed digital image correlation low-velocity impact tests demonstrated that the present analytical bending characteristics equations can reasonably predict the elastic behavior of stiffened hexagon honeycomb panels with an accuracy of more than 80%. As a result of quasi-static impact loading, stiffened CFRP hexagon honeycomb panel equipped with corrugated plate cores showed a positive elastic behavior of more than 89% compared to the non-stiffened traditional honeycomb unit. In addition, the effect of corrugation on the Tsai-Hill failure index of corrugated core CFRP honeycombs decreased with layer thickness enhancement because it is more proximate to the same configuration as flat plates.

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Abbreviations

a:

Panel length

b:

Panel width

\({\mathrm{D}}_{\mathrm{ij}}\) :

Bending stiffness matrix

\(\left[ {D_{\left( k \right), \, ij}^{\prime } } \right]\) :

The curved beam stiffness matrix

\(\left[ {D_{\left( k \right), \, ij, \, eq \, , \, panel} } \right]_{i,j = 1,2,6}\) :

Panel bending stiffness

\(\left[ {{\text{D}}_{{\left( {\text{k}} \right){\text{, ij, skin}}}} } \right]_{{\text{i,j = 1,2,6}}}\) :

Skin bending stiffness

\(\left[ {{\text{D}}_{{\left( {\text{k}} \right){\text{, ij, stiff}}}} } \right]_{{\text{i,j = 1,2,6}}}\) :

Stiffeners bending stiffness

\({\text{E}}_{{\text{L}}}\) :

Longitudinal Young’s modulus

\({\text{E}}_{{\text{T}}}\) :

Transverse Young’s modulus

F:

Low-velocity impact loading

\({\text{G}}_{{{\text{LT}}}}\) :

Shear modulus

m:

Fourier series counter

n:

Fourier series counter

N:

Number of vertical stiffeners

\(Q_{\left( k \right),ij}^{{\theta_{k} }}\) :

Transformation tensor

R:

Corrugated woven plate wave radius

\({\text{S}}_{{{12}}}\) :

In-plane shear strength

\(T^{(k)}\) :

Tsai-Hill failure index for each laminate of composite plate

\(T^{\prime (k)}\) :

Multi-configuration stiffened honeycomb panels Tsai-Hill failure index

\(w_{\left( k \right)}\) :

Out of plane deflection of each flat laminate

\(w{^\prime}_{k}\) :

Multi-configuration stiffened honeycomb panels out of plane deflection

X:

Longitudinal tensile strength

x:

The longitudinal location from the unit reference point

\(x_{0}\) :

Impact longitudinal location from the unit reference point

Y:

Transverse tensile strength

y:

The lateral location from the unit reference point

\({y}_{0}\) :

Impact lateral location from the unit reference point

\({\text{Z}}_{{k}}\) :

Ply thickness

\(\upsilon_{{{\text{LT}}}} ,\upsilon_{{{\text{TL}}}}\) :

Poisson’s ratios

\(\theta_{{_{{\text{k}}} }}\) :

Ply rotated angle

\(\mathrm{\alpha }\) :

Hexagonal outer angle

\(\varepsilon_{x}^{k}\) :

Flat plate longitudinal strain

\(\varepsilon_{x}^{\prime k}\) :

Multi-configuration stiffened honeycomb panels longitudinal strain

\({\upvarepsilon }_{{\text{y}}}^{{^{{\text{k}}} }}\) :

Flat plate transverse strain

\(\varepsilon_{y}^{\prime k}\) :

Multi-configuration stiffened honeycomb panels transverse strain

\(\sigma_{x}^{k} ,\sigma_{1}^{k}\) :

Flat plate longitudinal stress

\(\sigma _{x}^{{\prime k}} ,\sigma _{1}^{{\prime k}}\) :

Multi-configuration stiffened honeycomb panels longitudinal stress

\(\sigma_{y}^{k} ,\sigma_{2}^{k}\) :

Flat plate transverse stress

\(\sigma _{1}^{{\prime k}} ,\sigma _{2}^{{\prime k}}\) :

Multi-configuration stiffened honeycomb panels transverse stress

\(\tau_{xy}^{k} ,\tau_{12}^{k}\) :

Flat plate shear stress

\(\tau_{1}^{\prime k} ,\tau_{12}^{\prime k}\) :

Multi-configuration stiffened honeycomb panels shear stress

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Authors and Affiliations

  1. Department of Automotive Engineering, Iran University of Science and Technology, Tehran, Iran

    M. Shirzadifar & J. Marzbanrad

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  1. M. Shirzadifar
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  2. J. Marzbanrad
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Correspondence to J. Marzbanrad.

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The authors declare that the first and second authors are with IUST University. They have no known competing financial interests that could have appeared to influence the results reported in this manuscript.

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Shirzadifar, M., Marzbanrad, J. Bending Characteristics of CFRP Hexagon Honeycombs Stiffened with Corrugated Cores under Transverse Quasi-Static Impact Loading. Iran J Sci Technol Trans Mech Eng 47, 779–808 (2023). https://doi.org/10.1007/s40997-022-00550-9

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  • DOI: https://doi.org/10.1007/s40997-022-00550-9

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