• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.9
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• pp.49-56
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• 2004

With the wide application of fiber-reinforced composite material in aero-structures and mechanical parts, the design of composite joint have become a very important research area because they are often the weakest areas in composite structures. In this paper, the linear finite element analyses in which the pin of the composite joint was assumed to be the frictionless rigid body were performed and predict the strength of the mechanically fastened composite joint using the failure area index method. By the failure area index method, the strength of the mechanically fastened composite joint which has the specimen of different shape, hole size and stacking sequence could be predicted within 12.2%.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.3
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• pp.261-268
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• 2011

Generally, modeling procedure of cross section of composite rotor blade is complicated and time-consuming, because it is made up of various stiffeners and multiple layers of composite materials. For efficient modeling of cross section of composite rotor blade, a modeling program so called KSec2D, which provides a user friendly GUI, is developed by using a 2D modeling algorithm based on set operation. By the developed program KSec2D, a modeling of complicated cross section of rotor blade is carried out. Through the demonstration, the usefulness of developed program in modeling procedure of cross section of composite rotor blade is verified.

• Journal of the Society of Naval Architects of Korea
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• v.30 no.1
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• pp.134-144
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• 1993

Sandwich plate is consisted of equal two isotropic, thin, stiff and strong sheets of dense material separated symmetrically by an isotropic thick layer which may be much less stiff and strong. This study analyzed the dependency of the natural frequencies and mode shapes of sandwich plates on material properties, thicknesses of faces and cores, and various boundary conditions using Rayleigh-Ritz method. E-glass Woven Roving and another two kinds of materials were selected as a face, P.V.C. and another kinds of materials were selected as a core. Natural frequencies and mode shapes obtained by Rayleigh-Ritz method were compared with F.E.M. solutions using ADINA program.

• Journal of Aerospace System Engineering
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• v.11 no.2
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• pp.16-22
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• 2017

This paper investigates fretting wear damage in aerospace, biomedical, and nuclear components. Experimental parameters are identified that affect fretting wear damage. The parameters observed in industries are directly compared. The magnitudes of frequency, relative displacement, and normal force are found to differ depending on the contacting components where fretting wear occurs. In addition, recent solutions to minimize fretting wear damage are reviewed. The solutions include depositing of a low-friction coating, surface treatment, selection of substrate material, and optimal design of contact geometries. This comparative study suggests useful methods and solutions for analyzing fretting wear damage and for designing tribo-components.

• Proceedings of the KIEE Conference
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• 2003.07c
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• pp.1454-1456
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• 2003

전기절연재로서의 성능이 우수하며, 다른 물질과의 결합 및 성형의 편리성 및 경량화에 부합할 수 있는 실리콘 고무의 사용이 급증하고 있다. 이에 본 논문에서는 현수애자에 사용중인 실리콘 고무를 선택하여 제조시에 발생할 수 있는 내부보이드에 대한 전기적특성을 알아보기 위해 실리콘 고무를 3층으로 적층하여 중간층 중심에 비슷한 체적으로 인공보이드를 원통 및 삼각기등형의 보이드를 제작하여 보이드형상 변화에 따른 부분방전전하량을 측정하였다. 위상(${\Phi}$)-전하량(q)-빈도(n)에 대한 데이터를 3차원그래프로 나타냈으며, 또한 평균방전전류 및 방전전력 변화를 통한 보이드 결함 특성을 파악하였다. 그 결과, 전압인가 시간에 따라 원통보이드의 경우 초기에는 방전전류 및 방전전력이 증가 하다가 일정시간이 경과하면 감소하는 형태를 나타냈으며, 삼각기둥보이드의 경우 계속적으로 증가하는 모습을 보여주었다.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2010.05a
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• pp.540-543
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• 2010

POWER PC series are common to the Central Processing Unit for Military Single Board Computer. Among them, G4 group, which contains the 74xx series supported by Freescale manufacturer is mainly used in the Military applications. We focus on the Interface between memory and controller. PCB stacking method, component routing, impedance matching and harsh environment for Military spec are the main constraints for implementation. Also, we developed memory as a module for the consideration of Military environments. The overall type of SBC should be designed by the form of 6U VME or 3U VME.

• Proceedings of the Korean Institute of Electrical and Electronic Material Engineers Conference
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• 2006.06a
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• pp.42-43
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• 2006

LTCC 후막공정에서 일반적으로 사용되고 있는 스크린 프린팅 방법은 낮은 정밀도와 100um 이하의 선폭을 구현하는 데 한계를 보이고 있다. 이에 따라서 보다 미세한 라인을 형성 할 수 있는 반도체 미세라인 공정기술을 후막 공정에 응용한 후막 리소그라피 기술 (thick-film lithography technology)이 전자부품의 소형화에 대한 방안으로 연구 되고 있다. 본 연구에서는 후막 리소그라피 기술에 사용되는 감광성 Silver 페이스트에 영향을 미치는 각기 다른 크기와 형상의 Silver 파우더들과 인쇄 후 표면의 roughness 개선을 위한 여러 종류의 첨가제들을 첨가하여 최적의 조성을 연구 하였으며, 그린시트와 페이스트의 매칭성을 해결하기 위해서 Tg가 다른 글라스 파우더를 첨가하였다. 또한 전면 인쇄 한 후에 건조, 노광, 현상, 적층, 소성 과정을 걸치는 후막 리소그라피 기술을 이용하여 소성 후 20um이하의 선폭을 가지는 내장형 패턴 구현하였으며 투과엑스레이와 O/S 테스트 통하여 우수한 특성을 확인 할 수 있었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.1
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• pp.35-40
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• 2019

The objective of this paper is to identify the fatigue properties of carbon-fiber composite which is widely applied for the development of aircraft structures and obtain data for full-scale fatigue test. The durability and damage tolerance evaluation of composite structures is achieved by fatigue tests and parameters such as fatigue life factor and load enhancement factor. The specimens are made with carbon-fiber/epoxy UD tape and fabric prepreg. Fatigue tests are performed with several stress ratios and lay-up patterns. The Weibull shape parameters are analyzed by Sendeckyj model and individual fatigue lives with Weibull distribution. And the fatigue life factor and load enhancement factor considering reliability are evaluated.

• Composites Research
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• v.22 no.5
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• pp.30-36
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• 2009

The failure strengths and modes in carbon fiber reinforced polymeric composites, with two serial bolt-fastened composite joints, were investigated to evaluate the typical joint configurations of composite components. The parametric studies were performed experimentally at room temperature dry and elevated temperature wet, $82.2^{\circ}C$ on several different laminate configurations. Based on the experimental data presented, two basic load-displacements curves are observed. Each failure mode has the characteristic curve. It is showed that the bearing failure mode occurs in elevated temperature wet condition. It is analysed that the strength of bearing failure mode is not highly depending on the effective modulus of specimen. The failure strength at elevated temperature wet is decreased by the cause of interfacial deterioration between fiber and matrix with moisture absorption.

• Composites Research
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• v.29 no.4
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• pp.209-215
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• 2016

The failure of composite sandwich structures with thickness and material variation was studied. The main body of the structure is sandwich plate made of the carbon composite face and Aluminum honeycomb core. It is connected with composite laminated flange without core through transition region of tapered sandwich panel with foam core. Tension and compression tests were conducted for the total of 6 panels, 3 for each. Test results showed that the panels under compression are vulnerable to the face failure along the material discontinuity line between two different cores. However the failure load of which panel does not show such failure can carry 16% more load and fails in honeycomb core and face debonding. For the tensile load, the extensive delamination failure was observed at the corner radius which connects the panel and the flange. The average failure load for compression is about 7 times the tensile failure load. Accordingly, these sandwich structures should be applied to the components that endure the compressive loadings.