• Composites Research
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• 제19권1호
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• pp.29-35
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• 2006

첨단 전자무기체계의 지속적인 발전으로 인하여 현대전의 승패는 적 레이더 탐지의 회피에 크게 좌우된다고 할 수 있다. 반사되는 레이더의 탐지신호를 최소화시키기 위한 다양한 연구가 수행되어 왔는데, 본 연구에서는 뛰어난 기계적, 전자기적 물성으로 응용분야가 지속적으로 확대되고 있는 섬유강화 복합재료를 이용하여 레이더 전자파 흡수체(Radar absorbing structure, RAS)를 제작하고 레이더 단면적(Radar cross section, RCS)을 평가하였다 유리섬유 복합재에 뛰어난 유전적 특성을 지닌 나노 크기의 카본블랙(Carbon-black)을 첨가하여 흡수층을 구성하고, 반사특성이 탁월한 탄소섬유 복합재를 후면의 반사층으로 배치하여 "C" 및 "U" 형상의 하이브리드 복합재 RAS 겔을 제작하였다. RAS 쉘의 제작간 서로 다른 두 재료의 열적물성치 차이로 스프링 백이라 불리는 변형이 발생하였는데, 금형의 굽힘각도 제어를 통하여 효과적으로 보정할 수 있었다. 또한 상용 유한요소해석 프로그램인 ANSYS를 이용하여 스프링 백 보정 결과를 예측하고 실험결과와 비교하였다. 제작된 RAS쉘의 RCS는 근사적 계산기법인 물리광학법을 이용하여 예측하고 컴팩트 레인지(Compact range)를 이용하여 측정한 실힘결과와 비교하였다 두가지 형상의 RCS 모두 측정결과와 예측된 RCS 값이 일치하며 우수한 레이더 전자파 흡수 특성을 지닌 것을 확인하였다.

• 한국정보통신학회논문지
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• 제5권4호
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• pp.777-790
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• 2001

광통신용 광섬유의 최저손실 파장영역인 1.55w에서 고출력으로 안정하게 동작하는 SLD를 설계하기 위하여 이론적인 해석을 수행하였다. 활성영역과 SCH층의 재료는 Int-xGaxAsyPl-y를 이용하였다. 활성영역의 측방향과 횡방향 모드해석으로부터 단일모드 고출력 동작을 위한 광전력분포와 광가둠계수를 구하였으며, 이들 계산으로부터 최대 광가둠계수를 얻기 위한 SCH층의 조성과 두께를 계산하였다. 낮은 반사도를 얻기 위하여 후면 에 윈도우 영역을 두었고 활성영역과 윈도우 영역의 계면이 측방향으로 각도를 가지게 하였으며 가우시안빔 근사와 모드해석으로부터 반사도를 계산하였다. $1.3\mum$ InGaAsP를 SCH층으로 하였을 때 최대의 광가둠계수를 얻기 위한 SCH층의 두께는$0.08\mum$정도이었다. 10-4정도의 반사도를 얻기 위해서는 활성층의 두께를 $0.2\mum$, SCH 층의 두께를 $0.08\mum$ 로 하였을 때 무반사코팅을 하지 않을 경우 윈도우 영역의 길이는 $100\mum$ 정도이고, 반사도 1% 정도의 무반사 코팅을 할 경우 $10\mum$ 정도가 된다. 측면 경사각이 $10~15^{\circ}$이면 반사도는 10-3정도가 된다. 이들 결과로부터 AR코팅을 하지 않고도 윈도우 영역의 길이와 측면 경사각을 적당히 조절한다면 안정적으로 동작하는 SLD의 제작이 가능하다는 것을 알 수 있다.

• 대한인간공학회지
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• 제27권2호
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• pp.1-7
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• 2008

This study quantified 7 trunk muscles' physiological cross-sectional areas (PCSAs) and developed prediction equations for the physiological cross-sectional area as a function of anthropometic variables for Korean people. Nine females and nine males were participated in the magnetic resonance imaging (MRI) scans approximately from S1 through T8. Muscle fiber angle corrected cross-sectional areas (anatomical cross sectional areas: ACSAs) were recorded at each vertebral level and maximum value of ACSAs were determined as physiological cross sectional area (PCSA). There was a significant gender difference in PCSAs of all muscles (p<0.05). Stepwise linear regression techniques using anthropometric measures (e.g., height, weight, trunk depths and widths) as independent variables were conducted to develop prediction equations for the PCSA for each muscle. For males, six muscles' significant prediction equations (p<0.05) were developed except quadratus lumborum. For females, three prediction equations were developed for psoas, quadratus lumborum, and erector spinae muscles (p<0.05).

• Advances in aircraft and spacecraft science
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• 제4권6호
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• pp.679-699
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• 2017

The aim of this study is to perform a finite element analysis of the Von Mises stresses distribution in the adhesive layer and of the J-Integral for a damaged plate repaired by a composite patch. Firstly, we study the effect of the fiber orientation, especially the position of the layers that have orientation angle different of $0^{\circ}$ from the first layer which is in all cases of our study oriented at ($0^{\circ}$) on the J-Integral. Secondly, we evaluate the effects of the mechanical properties of the patch and the use of a hybrid patch on the reduction of stresses distribution and J-Integral. The results show clearly that the stacking sequence for the composite patch must be selected to absorb optimally the stresses from the damaged area and to position the various layers of the composite under the first layer whose fibers orientation will remain in all cases equal to $0^{\circ}$. The use of a hybrid composite reduces significantly the J-Integral and the stresses in both damaged plate and the adhesive layer.

• 대한기계학회논문집A
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• 제26권3호
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• pp.570-575
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• 2002

It is well-known that the bond strength between CFRP(Carbon Fiber Reinforced Plastic) and aluminum is significantly affected by the surface treatment of the CFRP and the aluminum. This study investigates the surface treatment of CFRP to improve the T-peel strength of CFRP/aluminum composites. The surface of %CFRP([0^0]_{14})$ was treated by the ion assisted reaction method under oxygen environment. T-peel strength tests were performed based on the procedure of ASTM D1876-95. The T-peel strength of surface-treated CFRP/aluminum composites was compared with that of untreated CFRP/aluminum composites. The results showed that the T-peel strength of surface-treated CFRP/aluminum composites was about 5.5 times higher than that of untreated CFRP/aluminum composites. SEM examination showed that the improvement of T-peel strength was attributed to the uniform spread and fracture of epoxy adhesive.

• Journal of the Korean Wood Science and Technology
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• 제9권1호
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• pp.1-12
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• 1981

The structure of spiral thickenings, particulary the appearance, arrangement and orientation of thickenings in compression wood of Torreya nucifera, were studied in detail by light and polarizing microscope, scanning and transmission electron microscope. The results obtained are as follows: (1) Using the inclined sections at an angle of 45 degrees to the fiber axis, it seems that we can not only observe the more accurate transverse view of the thickenings but also investigate the formation of their thickenings. (2) Generally 2-4 pieces of thickenings are projected to the cell lumen as nipple-like appearance in transverse section and are as frequent, well developed, forming pair and have the rope-like appearance in radial surface. (3) The secondary wall of early wood is composed of 3 layers (S1, S2, S3) and orientation of thickening appears S helix but that of late wood is of 2 layers (S1, S2) and that orientation shows Z helix. Above two regions are demaracted at several tracheid cells from the growth ring boundary. (4) Orientation of thickening seems to be a element showing the characteristics of compression wood in Torreya nucifera. (5) It believes that the thickenings of compression wood are integral part of the S3 in early wood tracheids and of the S2 in late wood and have the same orientations as the inner-most microfibrils in these layers. (6) Thickening and cavities seem to be not formed together in a secondary cell wall of same tracheids.

• 대한기계학회논문집A
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• 제21권11호
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• pp.1765-1772
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• 1997

The layered composites have a character to change of structure stiffness with respect to the layup angles. The deformations in the fan-blades to be initially designed by considering efficiency and noise, etc., which arise due to the pressure during the fan operation, can make the fan inefficient. Thus, so as to minimize the deformations of the blades, it is needed to increase the stiffness of the blades. An investigation has been performed to develop the three dimensional layered composite shell element with the drilling degree of freedom and the optimization module for finding optimal layup angles with sensitivity analysis. And then they have been verified. In this study, the analysis model is engine cooling fan of automobile. In order to analyzes the stiffness of the composite fan blades, finite element analysis is performed. In addition, it is linked with optimal design process, and then the optimal angles that can maximize the stiffness of the blades are found. In the optimal design process, the deformations of the blades are considered as multiobjective functions, and this results minimum bending and twisting simultaneously.

• 한국자동차공학회논문집
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• 제4권2호
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• pp.69-79
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• 1996

Dynamic stress intensity factors are derives when the crack is propagating with constant velocity under longitudinal shear stress in orthotropic disk plate. General stress fields of crack tip propagating with constant velocity and least square method are used to obtain the dynamic stress intensity factor. The dynamic stress intensity factors of GLV/GTV=1(=isotropic material or transversely isotropic material) which is obtained in out study nearly coincides with Chiang's results when mode Ⅲ stress is applied to boundary of isotropic disk. The D.S.I.F. of mode Ⅲ stress is greater when α(=angle of crack propagation direction with fiber direction) is 90° than that when α is 0°. In case of a/D(a:crack length, D:disk diameter)<0. 58, the faster crack propagation velocity, the less D.S.I.F. but when crack propagation velocity arrive on ghear stress wave velocity, the D.S.I.F. but when crack propagation velocity arrive on shear stress wave velocity, the D.S.I.F. unexpectedly increases and decreases to zero.

• 복합신소재구조학회 논문집
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• 제1권1호
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• pp.1-8
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• 2010

The dynamic instability analysis of delaminated composite structures subjected to in-plane pulsating forces is carried out based on the higher order shell theory of Sanders. In the finite element (FE) formulation, the seven degrees of freedom per each node are used with transformations in order to fit the displacement continuity conditions at the delamination region. The boundaries of the instability regions are determined using the method proposed by Bolotin. The numerical results obtained for skew plates and shells are in good agreement with those reported by other investigators. The new results for delaminated skew plate and shell structures in this study mainly show the effect of the interactions between the radius-length ratio and other various parameters, for example, skew angles, delamination size, the fiber angle of layer and location of delamination in the layer direction. The effect of the magnitude of the periodic in-plane load on the instability regions is also investigated.

• 복합신소재구조학회 논문집
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• 제1권2호
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• pp.36-43
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• 2010

본 연구는 원형 및 비원형(타원형)단면을 갖는 복합폐합쉘의 좌굴하중 및 모드형상을 비교 분석하였다. 이때, 면내 회전자유도를 갖는 평면응력 요소와 추가변형률과 대체전단변형률을 도입한 휨 요소를 결합한 4절점 쉘 요소(4EAS-FS)를 작성하여 좌굴해석을 수행하였다. 해석모델의 매개변수는 기하학적 형상, 종횡비 및 화이버 보강각도로 설정하여 그에 따른 영향을 고찰하였다. 본 연구에서 제시한 원형 및 비원형 단면을 갖는 폐합쉘의 임계좌굴하중과 모드형상에 대한 폐합쉘 길이, 두께, 단면계수 및 화이버 보강각도 등 설계변수의 영향을 비교 분석하였다.