• Composites Research
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• v.13 no.6
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• pp.63-72
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• 2000

In this paper, statistical treatments of effective properties for plain weave textile composites were presented. Configurations up to 32 layers with varied stacking phase shifts were considered. Effective properties were calculated by numerical simulation in which uni-axial tensile and shear load were applied at unit cell. Sample analysis was utilized to consider the inherent randomness in the phase shift and the results were treated statistically. It was found that effective properties were dependent on stacking phase shifts for thin plain weave textile composites. The distribution of $E_{xx}$ and $V_{xy}$ were skewed and the range of possible values was relatively large. As the number of layers increased, however, the distribution width became narrower and mean values converged. In contrast, $G_{xy}$ was not affected by phase shifts and thickness changes.

• Korean Journal of Materials Research
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• v.5 no.8
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• pp.979-987
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• 1995

This study has been investigated the Influence of layer thickness on the mechanical properties of cross laminated carbon fiber/epoxy composites. And also the difference of mechanical properties between cross laminated composites of unidirectional prepreg and fabric prepreg has been investigated. Experimental results are showed that the Interlamina Shear Strength(ILSS) of cross laminated carbon fiber/epoxy composites decreased with increasing thickness of unit ply and the decree of delamination in the laminated composites increased as ILSS decreased. Fracture toughness and impact values were found to increase as delamination occurs to some extent in the laminated composites. It Is also shown thats mechanical properties of cross laminates from unidirectional prepreg were better than those of cross laminates from fabric prepreg.

• Journal of the Korean Society of Propulsion Engineers
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• v.5 no.2
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• pp.59-64
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• 2001

The purpose of this work is to investigate the static strength, the stress distribution, and the failure process of quasi-isotropic composite laminates made of two different matrices when loading directions are changed. We carried out static tests of $[0/-60/+60]_s$ and $[+30/-30/90]_s$ laminates. Two types of matrices used are AS4/epoxy and AS4/PEEK. The damage mechanisms of the quasi-isotropic laminate, $[0/-60/+60]_s$, strongly depend on the load direction applied to the laminate.

• Transactions of the Korean Society of Mechanical Engineers
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• v.13 no.6
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• pp.1203-1214
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• 1989

본 연구에서는 화이버각도, 경계조건 및 하중형태의 변화에 따라 적층 복합재료원통 셸 구조물의 수치예를 제시하고, NASTRAN수치결과 및 기존 문헌들과 비교하여 구하여진 결과의 타당성을 입증하였다.

• Composites Research
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• v.12 no.4
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• pp.42-54
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• 1999

FMLC(Fiber-Metal Laminate Composites) is a new structural material combining thin metal laminate with adhesive fiber prepreg, it nearly include all the advantage of metallic materials, for example: good plasticity, impact resistance, processibility, light weight and excellent fatigue properties. This research studied the optimum design of the FMLC subject to various loading conditions using genetic algorithm. The finite element method based on the shear deformation theory was used for the analysis of FMLC. Tasi-Hill failure criterion and Miser yield criterion were taken as fitness functions of the fiber prepreg and the metal laminate, respectively. The design variables were fiber orientation angles. In genetic algorithm, the tournament selection and the uniform crossover method were used. The elitist model was also used to be effective evolution strategy and the creeping random search method was adopted in order to approach a solution with high accuracy. Optimization results were given for various loading conditions and compared with CFRP(Carbon Fiber Reinforced Plastic). The results show that the FMLC is more excellent than the CFRP in point and uniform loading conditions and it is more stable to unexpected loading because the deviation of failure index is smaller than that of CFRP.

• Korean Journal of Materials Research
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• v.7 no.9
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• pp.795-804
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• 1997

전면재를 알루미나, 후면재를 Kevlar또는 S-2 유리 섬유강화 복합재료로 접합한 이종재료 장갑에 대하여 알루미나의 두께 변화와 복합재료의 적층구조에 따른 고속충격 특성 변화에 대하여 연구하였다. 또한 시험재료의 동적 관통현상을 분석하기 위하여 고속촬영기법이 이용되었다. 시험결과, 전면재인 알루미나는 충격탄자 직경의 80% 상당하는 두께(본 실험에서는 6nm)인 경우 양호한 방탄성능을 보였다. 후면재인 복합재료는 섬유를 alternating 주조로 적층한 경우가 laminar구조로 적층한 것에 비하여 더 우수한 방탄성능을 나타내었다.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2001.11b
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• pp.916-921
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• 2001

형상기억합금 선(Shape Memory Alloy Fibers ： SMA Fibers)을 삽입한 복합재료 평판의 고온 환경에서의 열적 좌굴 및 진동 해석을 유한요소법을 이용하여 수행하였다 1 차 전단변형이론을 적용하여 적층판을 모델링하였고, 온도 변화 효과는 적층판의 전 영역에서 균일한 온도 분포로 가정하였다. 형상기억합금 선의 온도에 대한 비선형 재료 성질을 고려하여 열적 좌굴 해석 수행 시 반복 계산법을 이용하였고, 자유 진동 해석에서는 시스템의 자유도를 줄이기 위하여 Guyan-Reduction(CR)을 사용하였다. 온도 변화와 형상기억합금 선의 체적비(volume fraction) 및 초기 변형률(initial strain) 변화에 따른 임계 온도와 고유 진동수의 특성을 해석하였다.

• Composites Research
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• v.31 no.1
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• pp.37-41
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• 2018

The aim of the current work is to characterise a piecewisely-integrated composite bumper beam based on the IIHS bumper crash protocol. IIHS bumper crash FE analysis for an aluminium type bumper beam was carried out to get the information about the dominant loading types at several regions in the bumper beam during crash. In the meantime, robust stacking sequences against tension and compression have been searched for using FE analysis of a coupon type model. After determining most effective stacking sequences for tension and compression, three-point bending simulation was preliminarily carried out to investigate the combination performance of them. Finally, IIHS bumper crash FE analysis for the piecewisely-integrated composite bumper beam, which consisted of the combination of tension effective stacking sequence and compression efficacious stacking sequence, was conducted and the result was compared with other types of composite bumper beams. It was found that the newly suggested piecewisely-integrated composite bumper beam showed superior crashworthy behaviour to those of uni-modal stacking sequence composite bumper beams.

• Composites Research
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• v.36 no.6
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• pp.383-387
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• 2023

Carbon fiber-reinforced composites have excellent mechanical properties. However, the fracture toughness is a disadvantage due to brittle failure mode. The fracture toughness can be enhanced using hybridization with large-elongation fibers. In this study, polyamide (aramid) fibers are hybridized with carbon fiber with various stacking sequences. As a result, the Izod impact strength was enhanced by 63% with 25% aramid fiber hybridization. It is also shown that there is an optimal point in laminated composite hybridization, [CF/CAF₂/CF]_s stacking sequence.

• Composites Research
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• v.32 no.2
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• pp.108-112
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• 2019

There has been a continuous study on the weight reduction of structure by composites. Unlike isotropic materials, the physical properties of composites vary according to the direction of laminate and the order of lamination. Therefore, in the case of composite ladders, it is essential to perform structural analysis to verify the planned design. In this study, ladder was designed by applying fabric material. In addition, the effect of loading position on the ladder was analyzed through finite element analysis, and structural performance was analyzed by selecting the most problematic location. We analyzed the effect of stacking order on the structural strength of the ladder by analyzing the structure by applying various stacking sequence and measuring the failure value in each layer.