• Proceedings of the Korea Institute of Fire Science and Engineering Conference
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• 2012.04a
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• pp.159-162
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• 2012

최근 국내에서 일어난 '9 15 전국규모 정전사태'를 통해 우리나라가 대규모 정전에 대해 얼마나 무방비한 상태인지 인지하게 되었고, 본 연구는 향후 대규모 정전 시 피해를 최소화 하기 위해 설문조사를 통해 데이터를 수집하였으며, 이를 PASW 18을 활용하여 통계적 해석을 실시하였다. 연구의 결과는 향후 대규모 정전에 대비한 관리체계 연구에 활용될 것으로 기대된다.

• Proceedings of the KIEE Conference
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• 2003.07d
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• pp.2432-2434
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• 2003

노내 중성자 분포 측정 설비는 원자로 내부의 중성자 분포를 측정하는 설비로서 원자로 내부를 이동하는 검출기의 구동 메커니즘 제어와 측정 데이터 취득을 위한 제어시스템이 요구된다. 이 설비는 발전소 건설 당시 도입되었던 제어시스템으로 운전되고 있으나 노후되어 디지털 제어시스템으로의 설비 개선 연구가 착수 되었다. 개발된 제어시스템은 산업표준 Programmable Logic Controller 및 소프트웨어 기반으로 설계되어 기능개선, 설계변경 및 예비품 확보에 유연하게 대처할 수 있고, 진보된 검출기 구동 메커니즘 제어와 검출기 데이터 취득 기능을 통하여 측정 작업의 완전 자동화가 가능하다. 특히, 다양한 진단 기법을 통하여 작업상황 및 설비의 상태를 파악하여 필요한 보호기능과 경보기능을 제공함으로써 설비의 안정적 운영과 정비가 편리하다. 현재 개발된 시스템은 고리1호기에 설치되어 주기적으로 노내 중성자 분포 측정 작업을 수행하고 있다.

• Proceedings of the KIPE Conference
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• 2015.11a
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• pp.103-104
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• 2015

전압형 HVDC 시스템은 다수의 모듈로 구성되며, 각각의 모듈은 DC/DC 컨버터, 게이트 드라이버, 커패시터, 그리고 IGBT 등의 소자로 구성된다. 각 모듈의 가동율 및 신뢰도 평가를 통해 멀티모듈형 컨버터의 고장율을 평가하였으며, 정상상태 운전조건에 필요한 모듈에 추가적으로 모듈전압 및 유지보수기간에 따라 필요한 모듈의 수량을 설계하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.5
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• pp.60-65
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• 2011

The development of an air data acquisition algorithm has been described in the supersonic flow at the preliminary design stage with pressure data acquisition device composed of major three total pressure sensors and two static pressure sensors which are installed on the surface of a cone type supersonic inlet. Through this algorithm, Mach number, angle of attack and sideslip angle can be very easily derived with simple interpolation algorithm and predefined data tables. The available range of Mach number is 1.6 to 4.0, angle of attack, $-12^{\circ}$ to $12^{\circ}$ and sideslip angle, $-12^{\circ}$ to $12^{\circ}$. In preliminary design stage, the data tables applied to the developed algorithm are constructed with data driven by Taylor Maccoll equation. The present algorithm would be useful to get supersonic flow air data for the various aerial vehicles and their flight tests.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.1
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• pp.97-104
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• 2014

In this study, preliminary thermal sizing was performed with the aim of developing a fuel supply and cooling system design to solve the heating problems in high-speed vehicles. First, an analysis model was used to satisfy an optional mission profile. The heat loads were computed under boundary conditions. The results were verified using the precedent design case. Then, fuel consumption rates were estimated for the analysis trajectory. Accordingly, the cooling capacity in the system was calculated using the heat sink capacity of the endothermic fuel. Lastly, the fulfillment of the design requirements was confirmed in comparison to the cooling needs.

• Economic and Environmental Geology
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• v.48 no.3
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• pp.199-204
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• 2015

In this study, we aimed to make antibiotic-intercalated smectite composites using amoxicillin and clarithromycin as hygroscopic antibiotics, and gentamicin, tobramycin and netilmicin as non-hygroscopic aminoglucosides, and to check their drug delivery potential in gastric system using preliminary in-situ column release test for clarithromycinsmectite composite. All antibiotics were successfully intercalated into the interlayer of smectite by cation-exchange reaction in the batch experiment. Equilibrium batch test showed that clarithromycin-intercalation followed Langmuir isotherm and the possible maximum amount was calculated as 1.811 mmole/g. Clarithromycin was continuously released by the solutions of pH=2, 3, and 4 and the amount was decreased with pH increase.

• Journal of Embryo Transfer
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• v.14 no.1
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• pp.69-77
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• 1999

본 연구는 돼지 정액의 동결과정동안 flow cytometric 분석에 의한 정액내 생존정자의 비율을 조사하여 주관적으로 평가되는 활력 및 정상첨체율(normal apical ridge ; NAR)과 비교하여 정자의 손상과 생존성에 대한 적절한 평가법을 찾기 위하여 실시하였다. 동결과정 중 정액채취, 냉각, 예비동결 및 동결융해 후에 flow cytometric 분석에 의한 정자 생존율은 각각 93.0$\pm$3.6, 85.1$\pm$3.9, 28.9$\pm$6.8 및 26.1$\pm$5.9%이었다. 동결처리동안에 생존율은 예비동결 및 동결융해 후 가장 많은 정자사멸로 동결상태 이전의 생존율보다 유의적으로 낮게 나타났다. (p<0.05). 평가기법으로 정액 채취시 활력, NAR율 및 생존율을 조사한 결과 각각 91.0$\pm$4.2, 96.8$\pm$2.5 및 92.2$\pm$3.2%로 NAR율이 생존성 및 활력보다 높게 평가되었으며, 생존율이 활력보다 다소 높게 평가되었다. 그러나 동결융해 후에는 각각 44.0$\pm$8.9, 49.0$\pm$7.9 및 35.6$\pm$9.7%로 활력이 생존율보다 다소 높게 평가되었다. 전체적으로 NAR율은 활력은 생존율보다 높게 평가되었으며, SYBR-14 / PI(propidium iodide) 이중형광염색법에 의한 flow cytometric 평가법으로 생존율은 동결되지 않은 정액에서의 활력 및 NAR 평가보다 다소 민감하게 나타났다. 이러한 결과로 미루어보아 SYBR-14 / PI 형광염색에 의한 flow cytometry의 생존성 평가는 동결되지 않은 정액의 평가방법으로는 적절하지만 동결된 정액의 생존성 평가는 부적절한 것으로 사료되었다.

• Bulletin of the Korean Space Science Society
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• 2005.04a
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• pp.129-132
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• 2005

This paper describes BAUSAT-2 orbital thermal analysis and preliminary design of thermal control subsystem. To design thermal control subsystem of HAUSAT-2, we have considered active & passive thermal control method based on basic theory and themal equilibrium equation. Using this result, suitable thermal control method and material have been selected. We have designed thermal control subsystem based on analysis of HAUSAT-2's thermal environments on sun synchronous orbit with altitude 650km, inclination $98^{\circ}$ and thermal distribution and range expectation of each HAUSAT-2's surface. Thermal analysis consists of system level, box level and board level analysis. We have completed system level and box level analysis. Till now, board level analysis of main heat dissipation board in progress. Thermal control subsystem has designed according to thermal analysis result. This design is to maintain all of the HAUSAT-2 components within the allowable temperature limits. In future, STM

• Journal of Aerospace System Engineering
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• v.12 no.4
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• pp.90-97
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• 2018

In this study, we propose a conceptual design tool to develop fuel supply and engine cooling systems for high-speed vehicles. The preliminary designing of the systems and their validation were performed using this tool. Improvement in the design tool program was made using the fluid-thermal system design framework, which was applied to ensure efficient data processing using combined modules. The model geometry and thermal environment values were entered into the program. The thermodynamic properties of the system components were computed using the design tool, and simulation was performed to check the satisfaction rate of the requirements. It is hypothesized that our proposed design tool would be suitable for designing components for use in fuel supply and engine cooling systems of high-speed vehicles.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.5
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• pp.474-480
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• 2011

Space Imaging Sensor operated on LEO is affected from the Earth IR and Albedo as well as the Sun Radiation. The Imaging Sensor exposed to extreme environment needs thermal control subsystem to be maintained in operating/non-operating allowable temperature. Generally, units are periodically dissipated on spacecraft panel, which is designed as radiator. Because thermal design of the imaging sensor inside a spacecraft is isolated, heat pipes connected to radiators on the panel efficiently transfer dissipation of the units. First of all, preliminary thermal design of radiating area and heater power is performed through steady energy balance equation. Based on preliminary thermal design, on-orbit thermal analysis is calculated by SINDA, so calculation for thermal design could be easy and rapid. Radiators are designed to rib-type in order to maintain radiating performance and reduce mass. After on-orbit thermal analysis, thermal requirements for Space Imaging Sensor are verified.