• Transactions of the Korean Society of Mechanical Engineers A
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• v.28 no.4
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• pp.394-401
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• 2004

In this study the mechanical behaviors of fiber metal laminates(FMLs) such as ARALL, GLARE and CARE which are recently developed as new structural materials and known to have excellent fatigue resistant characteristics while with relatively low densities compared to the conventional aluminum materials, are considered through the classical lamination theory. The mechanical properties such as elastic moduli, thermal expansion coefficients and hygro-thermally induced residual stresses in the fiber metal laminates are obtained and compared each other. Also, carpet plots of effective elastic moduli, Poisson's ratio and the thermal expansion coefficient for GLARE FML are plotted.

• Structural Engineering and Mechanics
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• v.25 no.6
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• pp.733-751
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• 2007

The metis element method (Hung 1978) has been applied to analyse free edge interlaminar stresses and delamination in composite laminates, which are subjected to extension and bending. The paper recalls Lekhnitskii's solution for generalized plane strain state of composite laminate and Wang's singular solution for determination of stress singularity order and of eigen coefficients $C_m$ for delamination problem. Then the formulae of metis displacement finite element in two-dimensional problem are established. Computation of the stress intensity factors and the energy release rates are presented in details. The energy release rate, G, is computed by Irwin's virtual crack technique using metis elements. Finally, results of interlaminar stresses, the three stress intensity factors and the energy release rates for delamination crack in composite laminates under extension and bending are illustrated and compared with the literature to demonstrate the efficiency of the present method.

• Steel and Composite Structures
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• v.33 no.2
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• pp.245-259
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• 2019

The present study aims to investigate the ultimate strength and geometric nonlinear behavior of composite plates containing initial imperfection subjected to combined end-shortening strain and lateral pressure loading by using a semi-analytical method. In this study, the first order shear deformation plate theory is considered with the assumption of large deflections. Regarding in-plane boundary conditions, two adjacent edges of the laminates are completely held while the two others can move straightly. The formulations are based on the concept of the principle of minimum potential energy and Newton-Raphson technique is employed to solve the nonlinear set of algebraic equations. In addition, Hashin failure criteria are selected to predict the failures. Further, two distinct models are assumed to reduce the mechanical properties of the failure location, complete ply degradation model, and ply region degradation model. Degrading the material properties is assumed to be instantaneous. Finally, laminates having a wide range of thicknesses and initial geometric imperfections with different intensities of pressure load are analyzed and discuss how the ultimate strength of the plates changes.

• Advances in aircraft and spacecraft science
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• v.11 no.1
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• pp.1-21
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• 2024

The stiffness reduction of cross-ply composite laminates featuring a transverse cracking and delamination within the mid-layer is predicted through utilization of a modified shear-lag model, incorporating a stress perturbation function. Good agreement is obtained by comparing the prediction models and experimental data. The material characteristics of the composite are affected by fluctuations in temperature and transient moisture concentration distribution in desorption case, based on a micro-mechanical model of laminates. The transient and non-uniform moisture concentration distribution induces a stiffness reduction. The obtained results demonstrate the stiffness degradation dependence on factors such as cracks density, thickness ratio and environmental conditions. The present study underscores the significance of comprehending the degradation of material properties in the failure progression of laminates, particularly in instances of extensive delamination growth.

• Journal of the Institute of Electronics Engineers of Korea SD
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• v.44 no.2
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• pp.1-6
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• 2007

This study investigated the magnetic properties of $Ni_{80}Fe_{20}/SiO_2$ laminates with shape-induced magnetic anisotropy. The multilayer films were deposited on Si or upilex substrates, from separate $Ni_{80}Fe_{20}$ and $SiO_2$ (at %) alloy targets using a rf diode sputtering system. $Ni_{80}Fe_{20}/SiO_2$ laminates with a various number of bilayers (N) were prepared. The laminates with ellipse array patterns were prepared using photolithographic technique. The magnetic properties were measured at room temperature using a B-H hysteresisgraph and a high frequency permeameter. The several steps during domain wall reversal were observed in multilayer films, attributing to inter-magnetic layer coupling. Intrinsic uniaxial anisotropy field increases with N. The experimental values of the total anisotropy field are found to be in good agreement with the calculated values. This study utilized the shape anisotropy of the laminated film objects with small ellipse array patterns to induce a larger uniaxial anisotropy so as to maximize their operating frequency.

• Proceedings of the Korean Society For Composite Materials Conference
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• 2001.10a
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• pp.111-115
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• 2001

Thermo-acoustic emission (AE) from composite laminates under the repetitive thermal cyclic loads have been quantitatively analyzed in consideration of AE source mechanisms. The repetitive thermal load brought about a large reduction, i.e. an exponential decrease in AE total ringdown counts and AE amplitudes. It was thought that generation of thermo-AE during the first thermal cycle was not caused by crack propagation but by secondary microfracturing due to abrasive contact between crack surfaces.

• Proceedings of the Korean Institute of Electrical and Electronic Material Engineers Conference
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• 2001.07a
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• pp.897-900
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• 2001

Space charge distributions in silane crosslinked polyethylene (SXLPE)/ crosslinked polyethylene (XLPE) laminates was investigated using a pulsed electroacoustic (PEA) method. XLPE shows heterocharge while SXLPE shows homocharge. Positive charge is accumulated at the interface of SXLPE/XLPE laminate when applied electric field is more than 20 kV/mm. The charge profile at various temperatures was also acquired using temperature-controllable PEA system. Although applied electric field is only 8.6 kV/mm, positive interfacial charge starts to appear near 50$^{\circ}C$.

• Proceedings of the Korean Society For Composite Materials Conference
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• 2002.10a
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• pp.56-59
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• 2002

This paper presents a study on the permittivities of the E-glass fabric/epoxy composite laminates containing carbon black dispersions at microwave frequency. Measurement showed that the complex permittivities of the composites depend strongly on the natures and concentrations of the carbon black dispersion. A new scheme to obtain a mixing law for the estimation of complex permittivity is proposed. The experimental values of the complex permittivities were compared to those calculated. Simultaneously, the complex permittivity of carbon black itself was also calculated by the scheme.

• Proceedings of the KSME Conference
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• 2001.06a
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• pp.734-739
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• 2001

In this paper, an algorithm for stacking sequence optimization which deals with discrete ply angles is used for optimization of composite laminated plates. To handle discrete ply angles, the branch and bound method is modified. Numerical results show that the optimal stacking sequence is found with fewer evaluations of objective function than expected with the size of feasible region, which shows the algorithm can be effectively used for layup optimization of composite laminates..

• Proceedings of the Korean Institute of Electrical and Electronic Material Engineers Conference
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• 1996.11a
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• pp.287-290
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• 1996

The behaviour of interfacial charge in EPDM/XLPE laminates has been investigated by measuring charge distributions using a pulsed electroacoustic (PEA) method. Homocharge develops in EPDM while heterocharge develops in XLPE. A broadly interfacial charge peak is observed at EPDM/XLPE interface. When EPDM /XLPE laminates are treated in high temperature for different times, the amount and polarity of interfacial charge are changed.