• Proceedings of the Korean Vacuum Society Conference
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• 2011.02a
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• pp.502-502
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• 2011

기존 연구에서는 단일 타겟으로부터 증착된 코팅층 내에 다상으로 이루어진 나노 복합구조를 형성하기 위하여, 나노 합금분말을 방전플라즈마 소결법 등으로 급속 소결하여 타겟을 제조하는 방법이 고려되어 왔다. 반면, 비정질 재료가 우수한 비정질 형성능을 가지는 경우 주조 방법에 의해서도 타겟 제조가 가능하며, 특히 최근 들어 금속 비정질 합금에서 합금의 주요 구성 원소들이 양의 혼합열을 가지는 경우, 액상 또는 과냉각 액상에서 상분리 현상이 발생한다는 것이 밝혀졌다. 이러한 사실에 기초하면, 우수한 비정질 형성능을 가지는 합금 시스템에 합금 구성 원소와 양의 혼합열 관계를 갖는 원소를 첨가함으로써, 비정질 기지 내에 화학적 불균일성을 유도하여 다상으로 이루어진 복합 구조를 형성시키는 것이 가능하다. 본 연구에서는 이러한 합금 설계법을 이용하여, 비정질 기지 내에 존재할 수 있는 불균일성 정도를 합금 조성과 주조 조건의 변화를 통하여 나노 크기에서 원자 크기까지 조절하고, 이에 따른 재료 특성과의 상관관계를 밝히고자 하였다. 이를 위하여 우수한 비정질 형성능을 가지는 Cu-(Zr, Hf)-Al 벌크 비정질 합금계에서 (Zr, Hf)과 (Y, Gd)간의 양의 혼합열 관계에 주목하여 Cu-(Zr, Hf)-(Y, Gd)-Al 벌크 비정질 형성 합금계를 설계하였으며, 이 합금계 내에서 조성과 냉각속도의 조절에 따라 나타나는 불균일성의 정도와 특성변화의 영향을 체계적으로 고찰하였다. 결과로서, Cu-(Zr, Hf)-Al 합금계에서 (Zr, Hf)을 (Y, Gd)으로 15 at.% 이상 치환한 경우, Cu-(Zr, Hf)-rich 와 Cu-(Y, Gd)-rich 비정질상으로 이상분리가 일어났으며, 이렇게 생성된 비정질-비정질 복합재는 응력 하에서 소성 변형을 거의 보이지 않았다. 반면, 5 at.% 이하로 (Zr, Hf)을 (Y, Gd)으로 치환한 경우에는 비정질 기지에 SAXS 혹은 WAXS로 확인 가능한 원자 크기의 불균일성이 나타났으며, 이 경우 비정질 합금의 점성 유동의 변화를 통해 합금의 연신 특성이 향상되었다. 특히, 본 연구에서는 비정질 기지내 불균일 제어를 통한 기계적 특성 향상을 위해서 조성 제어뿐 아니라 동역학적인 요소를 고려한 냉각속도 조절을 통한 원자단위 불균일성의 최적화가 필요함을 규명하였다. 이러한 연구 결과는 분말화 및 소결 과정을 배제하고 제조된 단일 타겟을 통해 코팅층에 다수의 합금원소를 혼합하고 나노/원자 스케일의 복합구조 형성 및 고집적화가 가능한, 타겟 모물질 설계의 새로운 방향을 제시함으로써 다기능성 복합소재 코팅층의 연구에 크게 기여할 것으로 사료된다.

• Composites Research
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• v.32 no.1
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• pp.65-70
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• 2019

The aircraft composites wing parts are usually integrated with adhesive or fastener. These laminated composites have weak interlaminar strength, which can lead to delamination. In order to compensate the disadvantages of laminated composites, it is possible to improve the strength, durability, shock and fatigue resistance by reinforcing the fiber in the thickness direction. In addition, using a single structure near-net-shape saves the manufacturing time and the number of fasteners, thus can reduce the overall cost of the composite parts. In this study, compression test, tensile test and open-hole tensile test are carried out for three structural architecture of 3D (three-dimensional) textile preforms: orthogonal(ORT), layer-to-layer(LTL) and through-the-thickness(TTT) patterns. Among these, the orthogonal textile composite shows the highest Young's modulus and strength in tensile and compression. The notch sensitivity of the orthogonal textile composite was the smallest as compared with UD (unidirectional) and 2D (two-dimensional) fabric laminates.

• Composites Research
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• v.24 no.1
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• pp.10-16
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• 2011

Many tests are required to predict the fatigue life of composite laminates made of various materials and having different layup sequences. Aiming at reducing the number of tests, a methodology was presented in this paper to predict fatigue life of composite laminates based on fatigue life prediction of constituents, i.e. the fiber, matrix and interface, using micromechanics of failure. For matrix, the equivalent stress model which is generally used for isotropic materials was employed to take care of multi-axial fatigue loading. For fiber, a maximum stress model considering only stress along fiber direction was used. The critical plane model was introduced for the interface of the fiber and matrix, but fatigue life prediction was ignored for the interface since the interface fatigue strength was presumed high enough. The modified Goodman equation was utilized to take into account the mean stress effect. To check the validity of the theory, the fatigue life of three different GFRP laminates, UDT[$90^{\circ}2$], BX[${\pm}45^{\circ}$]S and TX[$0^{\circ}/{\pm}45^{\circ}$]S was examined experimentally. The comparison between predictions and test measurements showed good agreement.

• Journal of the Korean Society of Propulsion Engineers
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• v.5 no.4
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• pp.20-30
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• 2001

This study represents the Nondestructive Test about impact damage of composite materials made by different lay-up patterns and degrees. For this study, they were examined by the drop test on composite materials of two type lap-up patterns with fabric and unidirectional prepreg and examined nondestructive test of those. Nondestructive methods were X-ray test with $ZnI_2$ penetrant and Ultrasonic C-scan. The defect detectability of X-ray and Ultrasonic test was compared according to defect species. And the amounts of damage on impacted zone wert compared according to impact energy on two type test specimens. At results, Ultrasonic test was more effective to detect delamination and Penetrant X-ray test was more effective to detect matrix crack and fiber fracture. There were some differences in defect shapes and grades according to lay-up patterns and degrees, and the trend appeared that matrix crack, delamination, fiber fracture occured and increasing defects sizes according to increasing impact energy.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.24 no.5 s.176
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• pp.1261-1270
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• 2000

This paper is concerned with the development of a general model for predicting material damping in laminates based on the strain energy method. In this model, the effect of interlaminar stress on damping is taken into accounts along with those of in-plane extension/compression and in-plane shear. The model was verified by carrying out the damping measurements on $90^0$ unidirectional composite beams varying length and thickness. The analytical predictions were favorably compared with the experimental data. The transverse shear($$\sigma$_{yz}$) appears to have a considerable influence on the damping behaviors in $90^0$ unidirectional polymer composites. However, the other interlaminar stresses($$\sigma$_{xz}$, $$\sigma$_z$) were shown to have little impact on vibration damping in $90^0$ laminated composite beam.

• Composites Research
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• v.33 no.5
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• pp.296-301
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• 2020

Laminated composite materials have excellent in-plane properties, but are vulnerable in thickness directions, making it easy to delamination when bending and torsion loads are applied. Thickness directional reinforcement methods of composite materials that delay delamination include Z-pinning, Stitching, Tufting, etc., and typically Z-pinning and Stitching method are commonly used. The Z-pinning is reinforcement method by inserting metal or carbon pin in the thickness direction of prepreg, and the conventional stitching process is a method of reinforcing the mechanical properties in the thickness direction by intersecting the upper and lower fibers on the preform. In this paper, I-fiber stitching method, which complement and improve weakness of Z-pinning and Stitching method, was proposed, and the static strength of composite single-lap joints using I-fiber stitching process were evaluated. The single-lap joints were fabricated by a co-curing method using an autoclave vacuum bag process. The thickness of the composite adherend was fixed, and 5 types of specimens were manufactured with varying the stitching pattern (5×5, 7×7) and angle (0°, 45°). From the test, the failure load of the specimen reinforced by the I-fiber stitching process was increased by up to 143% compared to that of specimen without reinforcement.

• Composites Research
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• v.36 no.1
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• pp.16-24
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• 2023

This paper presents a multi-scale progressive fatigue damage model incorporating the model for interfacial debonding between fibers and matrix. The micromechanics model for the progressive interface debonding was adopted, which defined the four different interface phases: (1) perfectly bonded fibers; (2) mild imperfect interface; (3) severe imperfect interface; and (4) completely debonded fibers. As the number of cycles increases, the progressive transition from the perfectly bonded state to the completely debonded fiber state occurs. Eshelby's tensor for each imperfect state is calculated by the linear spring model for a damaged interface, and effective elastic properties are obtained using the multi-phase homogenization method. The fatigue damage evolution formulas for fiber, matrix and interface were proposed to demonstrate the fatigue behavior of CFRP laminates under cyclic loading. The material parameters for the fiber/matrix fatigue damage were characterized using the chaotic firefly algorithm. The model was implemented into the UMAT subroutine of ABAQUS, and successfully validated with flat-bar UD laminate specimens ([0]₈,[90]₈, [30]₁₆) of AS4/3501-6 graphite/epoxy composite.

• The Journal of the Acoustical Society of Korea
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• v.13 no.6
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• pp.50-59
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• 1994

Spectral analysis of transient elastic waves were carried out in order to identify the propagation modes in glass and unidirectional carbon fibre reinforced plastic (CFRP) plates. Pencil leads were broken on the surface of plates to generate elastic waves, and two broad band transducers of 6.35 mm in diameter and 10 MHz center frequency were placed at the linear location from the source. The frequency spectra of detected signals showed that the wave propagation in the plates obeyed the Lamb wave dispersion relation. The transient signals were the fast propagating modes around maximum group velocity of the lowest and first order symmetric $modes(S_{0} and S_{1}),$ and first order antisymmetric $mode(A_{1})$. The transient signals were not severely distorted due to relatively small dispersion of those modes around the maximum group velocity. The fastest propagating mode in the plates was shown to be $S_{0}$ mode less the than cut-off frequency of $A_{1}$ mode.

• The Journal of the Acoustical Society of Korea
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• v.11 no.4
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• pp.22-30
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• 1992

The propagation of coherent time-harmonic elastic SH waves in a medium with random distribution of cylindrical inclusions is studied for characterizing the dynamic elastic modulus and the attenuation property of fiber-reinforced composite materials. A multiple scattering theory using the single scattering coefficients in conjunction with the Lax's quasicrystalline approximation is derived and from which the dispersion relation for such medium is obtained. The pair-correlation functions between the cylinders which are needed to formulate the multiple scattering interaction between the cylinders are obtained by Monte Carlo simulation method.From the numerically calculated complex wavenumbers, the propagation speed of the average wave, the coherent attenuation coefficient and the effective shear modulus are presented as functions of frequency and area density.

• Bulletin of the Society of Naval Architects of Korea
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• v.26 no.4
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• pp.67-80
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• 1989

This Paper is concerned with the fracture behavoir of Unidirectional Laminate(UD) and the characteristic length of Multidirectional Laminate(MD) around hole under the Uniform Tensial Strain. Two fracture mechanical concepts of the Waddoups-Eisenman-Kaminski(WEK) model based on the Linear Elastic Fracture Mechanics(LEFM) and the Whitney-Nuismer Model based on Point and Average Stress Criteria were applied. The characteristic length of a laminate with a hole is then obtained using the coefficient of stress reduction and the experimental results, and it can be utilized in predicting the stress level at which the specimen will fracture. The results of the fracture characteristics and the strength of the specimens having a hole in the center can be used as the important experimental data in the research branch of the mechanical fastening of laminated structures. The Ultrasonic scanning and the Acoustic Emission(AE) method were utilized in order to find out the initial defects and the fracture behavior, respectively.