• Composites Research
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• v.17 no.6
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• pp.52-57
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• 2004

In this study, mechanical tensile properties of carbon fiber reinforced polymeric (CFRP) composite cycled with thermo-mechanical loading under cryogenic temperature (CT) were measured using cryogenic environmental chamber. Thermo-mechanical tensile cyclic loading (up to 10 times) was applied to graphite/epoxy unidirectional laminate composites far room temperature (RT) to $-50^{\circ}C$, RT to $-100^{\circ}C$ and RT to $-150^{\circ}C$. Results showed that tensile stiffness obviously increased as temperature decreased while the thermo-mechanical cycling has little influence on it. Tensile strength, however, decreased as temperature down to CT while the reduction of strength showed little after CT-cycling. For the analysis of the test results, coefficient of thermal expansion (CTE) of laminate composite specimen at both RT and CT were measured and the interface between fiber and matrix was observed using SEM images.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2009.10a
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• pp.220-221
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• 2009

One of the important performance measure for productivity at container terminals is the working productivity in the quay. working scheduling of quay cranes (QCs) gives a significant impact on the quay working productivity. The recent managers of the terminals pay high interests in equipment investment and operation methods with a new concept in order to enhance the quay working productivity. The double cycle or dual cycle, which is a method to increase the quay productivity with no application of new equipment, but with the change of operations, has been received strong attention in academic research. The majority of studies until this time has been realized the quay work as the bottleneck and focused on those works. However, if the QCs do notver, it the Cs d-trotver,(CT) if t the Cs, there would be the pos ibilf tes that the effectiveness of them is decreasedveaused by the longer, if t the Cs. Thus, this paper, suggests the solutions on the con th scheduling for the dual cycle operation considering the YT.

• Review of KIISC
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• v.16 no.4
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• pp.77-86
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• 2006

향후의 유비쿼터스 사회(U-Society)는 정보화에 따른 여러가지 새로운 위험들이 나타나는 사회가 될 것이며, 개인정보 생성, 수집 등을 통해 개인정보 지식베이스 형성을 가능하게 하는 정보위험사회의 도래가 예상되고 있다. 따라서, 사용자의 상황에 맞게 적응적(Adaptive)이고 적시적(Just-In-Time)으로 개인정보보호 서비스 제공이 가능한 새로운 프레임워크 개발이 요구된다. 본 논문에서는 U-Society와 프라이버시 개념의 변화 과정을 검토하고, 개인정보 및 프라이버시 침해의 유형을 비교 분석한다. 아울러, 기존 프라이버시 보호 프레임워크 모델인 WASP 아키텍쳐와 IBM의 TPM 작동 과정과 주요 기능을 살펴보고 이에 따른 문제점을 지적한다. 또한, 개인정보보호 대책을 수립하기 위해 개인정보의 라이프사이클 관점에서 수집, 저장/관리, 이용/제공, 폐기의 4단계로 분석하고 개인정보 라이프사이클에 따른 프라이버시 보호 프레임워크 모델을 제시한다.

• Proceedings of the Korean Society of Computer Information Conference
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• 2021.01a
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• pp.337-339
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• 2021

본 연구는 최근 펜데믹 위기에서 교육의 변화하는 모습을 점검하고 미래의 학습에 대한 모습들을 예측하기 위해 이러닝과 학습분석에 대한 신흥기술의 동향을 살펴보고자 한다. 연구방법으로 신흥기술의 '하이프 사이클'과 '이러닝 예측 하이프 커버'를 기반으로 하여 각 단계별 기술들을 점검하고 펜데믹 위기에서 더 공고히 된 이러닝과 학습 관련 기술들이 무엇인지 살펴본다. 또한 하이프 사이클의 5단계인 기술촉발 단계, 부풀려진 기대의 정점 단계, 환멸 단계, 계몽 단계, 생산성 안정 단계인 각 단계별 학습과 관련된 기술들은 어떤 것이 있으며, 그 기술들이 이러닝과 학습분석에 어떠한 영향을 미칠 것인지 예측해 본다. 향후 연구로는 본 연구를 기반으로 인공지능이 이러닝과 학습분석에서의 역할을 알아보고자 한다.

• Composites Research
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• v.14 no.2
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• pp.33-42
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• 2001

The cure kinetic equation fur 52-glass/polyester prepreg composites was established through DSC (differential scanning calorimetry). Using the established kinetic equation, the temperature distribution of the thick composite was calculated considering the change of heat transfer resistance due to resin impregnation of bleeder plies used. In order to reduce the overheat during cure of thick glass fiber composites, the cure cycle was modified by introducing the cooling and reheating steps. Then the thick glass composites were cured both by the conventional cycle without any cooling or reheating step and the modified cure cycle. The mechanical properties of the thick composites cured by the both cycles were tested by the short beam shear test and the Barcol hardness test, and then their results were compared.

• Aerospace Engineering and Technology
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• v.12 no.1
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• pp.111-119
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• 2013

Conceptual design of RBCC (Rocket Based Combined Cycle) engine is performed through the thermodynamic cycle analysis. The engine is designed to take off at sea level and accelerate to Mach 8 at 30 km altitude. According to the flight speed, the engine operating modes are categorized into 3 modes : Ejectorjet (~ Mach 3), Ramjet (Mach 3~6), Scramjet (Mach 6~8). As a design result, the engine has a diameter of 1 m and a length of 6.7 m. In the prediction results, its maximum thrust is 16.5 ton. In Ramjet and Scramjet modes, design condition of the engine intake influence the engine thrust according to the flight speed.

• Journal of Welding and Joining
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• v.13 no.4
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• pp.7-13
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• 1995

마이크로솔더링에 의한 전자기기는, 사회기능의 중추가 되는 컴퓨터, 통신 기기, 항공기 인공위성 등의 제어계를 구성하므로, 그 접속부에 대한 높은 신뢰성의 요구는 그 무엇보다 중요하다. 전자기기에 있어서의 솔더 접속부는 집과 기판의 전기 적.기계적 접속의 역할을 하고 있으며, 따라서 개개의 접속부의 파단은 전체의 불량 으로 연결된다. 실제 전자콤포넌트와 그 시스템의 단선 등의 사고에 있어서 자주 발생 하는 사고중의 하나가 솔더접속부의 단선에 의한 것이며, 그 단선중에서도 가장 보편 적이며 또한 대단히 심각한 문제로서 주목을 받고 있는 것이 솔더접속부의 열피로파단 이다. 전자기기를 사용할 때, 스위치의 on-off에 의한 power cycle과 환경의 온도변화 에 기인하는 반복열 사이클은 솔더접속부의 피로를 일으키게 되고, 결국에는 사용중에 파단을 초래하게 된다. 이러한 온도변화의 범위는 약 -55.deg. - 150.deg.C로 예상할 수 있으며, 여기서 최고온도인 150.deg.C는 Pb-Sn 공정합금의 경우 0.9Tm.p.이상의 고온에 해당한다. 이 피로는 등온적으로 또는 열사이클중에 발생하기도 한다. 솔더접 속부의 열피로수명은 대부분의 공업재료에서 나타나는 저사이클피로거동과 유사하게 발생하며, 솔더 접속부에 인가되는 열변형/응력(thermal strain/stress)의 크기에 크게 의존하는 것으로 알려져 있다. 솔더는 서로 다른 열팽창계수를 갖는 칩과 회로 기관의 두종류의 재료를 접속하기 때문에, 상기한 바와 같은 반복열사이클에 의하여 발생하는 열변형/응력이 접속부의 피로.파단을 야기시킨다. 이러한 솔더접속부에 대한 주기적인 응력/변형의 인가는 접속부에 내.외적으로 현저한 변화를 야기시키게 되고, 열피로로 연결되며 결국에는 시스템의 전기적 단선을 초래하게 된다. 또한 열피로파단 현상는 변형/응력의 크기 뿐 만아니라 솔더합금자체의 야금학적인 물성에도 크게 의존 하며, 내적.외적인 열변화에 의한 야금학적인 특성변화도 크게 영향을 미친다. 솔더 접속부의 신뢰성에 대한 연구는, 그 중요성에 비추어 볼 때, 지금까지 수많은 연구가 행하여져 왔다. 그러나 신뢰성과 관련된 열피로파단현상에 대한 야금학적인 면에서의 연구는 비교적 적은 편이다. 따라서 본 해설에서는 전자기기의 마이크로 솔더접속부 에서 발생하는 열피로파단현상에 대한 야금학적인 면에 중점을 두어 서술하고자 한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.10
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• pp.21-26
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• 2003

In this research, the change of coefficient of thermal expansion (CTE) of graphite/epoxy composite laminate under space environment was measured using fiber optic sensors. Two fiber Bragg grating (FBG) sensors have been adopted for the simultaneous measurement of thermal strain and temperature. Low Earth Orbit (LEO) conditions with high vacuum, ultraviolet and thermal cycling environments were simulated in a thermal vacuum chamber. As a pre-test, a FBG temperature sensor was calibrated and a FBG strain sensor was verified through the comparison with the electric strain gauge (ESG) attached on an aluminun specimen at high and low temperature respectively. The change of the CTE in a composite laminate exposed to space environment was measured for intervals of aging cycles in real time. As a whole, there was no abrupt change of the CTE after 1000 aging cycles. After aging, however, the CTE decreased a Little all over the test temperature range. These changes are caused by outgassing, moisture desorption, matrix cracking etc.

• Transactions of the Korean Society of Mechanical Engineers
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• v.13 no.2
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• pp.307-315
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• 1989

In recent years, the fatigue design method by analysis for the mechanical components and the welded structures has much increased, instead of the fatigue design method by rule that has been widely used from the past days. When a fatigue design is conducted by that method, the basic informations, fatigue life curves are mainly obtained from the results of the strain controlled low cycle fatigue test. From these point of views, the low cycle fatigue test is coming to be given a much importance lately. In this paper, the strain controlled low cycle fatigue properties at room temperature in air environment were investigated for the low carbon forged steel, SF45A, and the rolled steel for the welded structure, SM 41B. Throughout the test, strain ratio, R, was maintained constant with the fully reversed condition, -1. As the experimental results, the cyclic stress-strain behaviours of the test materials were different each other, but the low cycle fatigue life-time of them appeared to show little difference in the region of this test conditions.

• Transactions of the Korean hydrogen and new energy society
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• v.9 no.4
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• pp.135-141
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• 1998

The effects of heat-treatment on discharge characteristics of $TiFe_{1-x}Ni_x$ alloy were investigated. The content of Ni in alloy was varied from x = 0.1 to 0.6 by each 0.1 increment. Discharge capacity change of each alloy with C/D cycles was measured. With increasing Ni-content initial discharge capacity was increased. but at x = 0.6 it was deceased again. With increasing C/D cycles discharge capacity was rapidly decreased in the alloy of high Ni-content. In order to investigate the effects of heat-treatment on cycle life, $TiFe_{0.5}Ni_{0.5}$ alloy having maximum initial discharge capacity was heat-treated at various temperatures in the range of $700{\sim}900^{\circ}C$ and tested. The loss of initial discharge capacity was appeared at all temperatures. but cycle characteristics of the alloy was improved. The electrodes heat-treated for 1 hour in the range of $700{\sim}850^{\circ}C$ showed good recovery of discharge capacities through repeated cycles, and from SEM observation results these were considered as 1 hour in the range of $700{\sim}850^{\circ}C$ showed good recovery of discharge capacities through repeated cycles, and from SEM observation results these were considered asbeing due to increased electrode strength and small loss of porosity during heat-treatment. The electrode heat-treated for 1 hour at $900^{\circ}C$ showed poor discharge characteristics because of low porosity.