• Composites Research
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• 제15권2호
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• pp.18-23
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• 2002

군사적 목적뿐만 아니라 상업적 목적에서도 레이더나 기타 전자파를 방출하는 기기들로부터 생성되는 전자파의 흡수 또는 차폐는 매우 중요한 일이다. 본 연구에서는 다른 유전적 성질을 가지는 복합재층을 배열하여 전자기파의 반사를 최소화하는 연구를 수행하였다. Glass fabric/epoxy에 전도성을 가지는 카본블랙 분체를 혼합한 복합재와 Carbon fabric/epoxy 복합재 대만 유전성질을 측정하였고, 이를 이용하여 X-band(8.2 GHz-l2.4GHz)에 대한 전자기파 반사의 최소화 구조를 구성하였다. 두께2.6mm의 다층 구조로 최대 30dB 이상의 반사 손실과 최대 흡수 주파수로부터 2GHz 주파수 대역에 걸쳐 10dB이상의 반사손실을 일으킬 수 있었다.

• Composites Research
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• 제17권2호
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• pp.1-8
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• 2004

본 논문은 겹판 스프링의 정적 스프링 상수를 가지고 복합재료 데이퍼 스프링을 최적설계 하였다. 두께와 폭을 설계변수로 실정하였다. 회귀모형의 목적함수는 상용 해석 프로그램을 통해 얻었다. 회귀모형의 함수를 가지고 회귀계수를 계산한 후, DOT를 이용하여 최적해를 구하였다. 설계에 이용된 복합재료로는 E-glass/epoxy와 carbon/epoxy를 선정하였고 겹판 스프링과 비교 해석하였다. 그 결과 정적 스프링 상수는 최적화된 복합재료 스프링들과 겹판 스프링이 1％내로 일치함을 보였다.

• 한국산학기술학회논문지
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• 제11권2호
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• pp.426-434
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• 2010

본 논문에서는 충격손상을 갖는 유리섬유강화 복합재료의 강도 저하 특성과 이의 통계적 특성을 실험적으로 평가하였다. 평직 복합재료의 주요 충격손상은 섬유파단과 모재균열로서 이는 층간분리가 주된 충격손상인 일방향 적층복합재료와는 상이한 양상이다. 일방향 적층복합재료에 대하여 제안된 기존의 잔류강도 예측모델을 이용하여 충격손상을 갖는 평직 glass/epoxy 복합재료의 잔류강도를 평가하였다. 그 결과 Avva 및 Caprino의 잔류강도 예측모델은 평직 복합재료의 잔류강도에 대해서도 잘 평가되었다. 또한 유리섬유강화 복합재료의 잔류강도에 대한 통계적 특성 평가를 위한 모델을 제안하였으며, 이를 통한 예측결과는 복합재료의 두께와 관계없이 실험결과를 잘 묘사하였다.

• 대한기계학회논문집A
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• 제24권11호
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• pp.2853-2865
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• 2000

During the curing process of thick glass/epoxy laminates, a substantial amount of temperature lag and overshoot at the center of the laminates is usually experienced due to the large thickness and low thermal conductivity of the glass/epoxy composites. Also, it takes a longer time for full and uniform consolidation. In this work, temperature, degree of cure and consolidation of a 20 mm thick unidirectional glass/epoxy laminate were investigated using an experiment and a 3-dimentional numerical analysis. From the experimental and numerical results, it was found that the experimentally obtained temperature profile agreed well with the numerical one, and the cure cycle recommended by the prepreg manufacturer should be modified to prevent a temperature overshoot and to obtain full consolidation.

• 한국정밀공학회지
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• 제7권4호
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• pp.29-39
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• 1990

The purpose of this research is to analyze the impact behaviors of laminated composite plates subjected to the transverse low-velocity impact by the steel ball. A plate finite element model based on Whitney and Pagano's the first-order shear deformation theory (FSDT) in conjunction with experimental static contact laws is formulated and then compared with the results of the impact experiments. Because the input data and the output data printed at every integration time step are lots of amount, these are interactively poecessed by the developed pre-processor(PREPLOT) and postprecessor(POSTPLOT). All results from these procesors are automatically generated by CALCOMP plotter. Test materials are glass/expoxy composite materials. The specimens are composed of [$0^{\circ} /45^{\circ}/0^{\circ}/-45^{\circ}/0^{\circ}/]2s\ and \[90^{\circ}/45^{\circ}/90^{\circ}/-45^{\circ}/90^{\circ}/$]2s stacking sequences and have $4.5^t{\times}200^w{\times}200^l$(mm) and $4.5^t{\times}300^w{\times}300^l$(mm) dimensions.

• Advanced Composite Materials
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• 제18권3호
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• pp.209-219
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• 2009

Carbon nanotubes (CNTs) have shown great potential for the reinforcement of polymers or fiber-reinforced composites. In this study, mechanical properties of multi-walled carbon nanotube (MWNT)-filled plain-weave glass/epoxy composites intended for use in radar absorbing structures were evaluated with regard to filler loading, microstructure, and fiber volume fraction. The plain-weave composites containing MWNTs exhibited improved matrix-dominant and interlaminar fracture-related properties, that is, compressive and interlaminar shear strength. This is attributed to strengthening of the matrix rich region and the interface between glass yarns by the MWNTs. However, tensile properties were only slightly affected by the addition of MWNTs, as they are fiber-dominant properties.

• Tribology and Lubricants
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• 제36권3호
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• pp.133-138
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• 2020

In this paper, we present an experimental investigation of the friction coefficient and wear area change of carbon/epoxy and E-glass/epoxy composites depending on the fiber direction (0°/90°). We compared the results of the case where the sliding direction is parallel to the fiber direction (0°) with that of the case where it is perpendicular to the fiber direction (90°). The ball-on-plate wear test equipment was used to cause wear in both directions. Two types of specimens were prepared with thicknesses of 3 mm-one made of carbon fiber reinforced plastic composite (CFRP) and the other of glass fiber reinforced plastic composite (GFRP). A normal force of 20 N was applied to the specimen and the sliding speed was 10 mm/s and the sliding distance was set to 20 m to perform the wear test. The CFRP demonstrates superior tribological characteristics compared to the GFRP. This outcome is attributed to graphitization of carbon, which serves as solid lubricating particles. In addition, both CFRP and GFRP are worn more in the 90° direction than in the 0° direction. This is due to the greater occurrence of fiber breakage and separation in the 90° direction than in the 0° direction. This study is expected to be utilized as basic data for understanding the friction and wear characteristics of CFRP and GFRP composites along the fiber direction and to apply the appropriate material.

• 한국재료학회:학술대회논문집
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• 한국재료학회 1996년도 재료학회 춘계학술발표회
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• pp.125-125
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• 1996

• 한국재료학회:학술대회논문집
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• 한국재료학회 1996년도 재료학회 추계학술발표회
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• pp.120-120
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• 1996

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2000년도 추계학술발표대회 논문집
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• pp.187-190
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• 2000

Cyclocopter is air vehicle to vertically take-off and land like a helicopter. This is an efficient and quiet means of being able to direct thrust compared to a helicopter. The rotor consists of several blades rotating about a horizontal axis perpendicular to the direction of normal flight. The direction of blade span is parallel to rotating axis and both end roots are connected to the hub to resist centrifugal force and to transmit the power. The pitch of the individual blades to the tangent of the circle of the blade's path is varied cyclically to gain thrust. In the paper, the design and manufactures of cyclocopter rotor blades are presented. Stress at the roots of cyclocopter blades is great due to centrifugal and aerodynamic forces and aeroelastic instabilities appear. The blades consist of main spar, front spar, polyurethan foam, weight, and skin and spars and skin are made of glass/epoxy composite.