• 우주기술과 응용
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• 제2권1호
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• pp.1-12
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• 2022

본 논문에서는 초소형위성용 항력 증대 장치 개발에 대해 기술하였다. 최근 우주 개발이 New Space 시대에 접어들며, 소형 로켓 및 초소형위성 거대 군집 운용 등 인공물체의 저궤도 진입 장벽이 상당히 낮아지는 추세이다. 이로 인해 우주 환경에 존재하는 우주쓰레기의 수가 기하급수적으로 늘어나고 있으며, 현재 운용중인 인공위성뿐만 아니라 앞으로 발사될 인공위성들에 큰 위협으로 다가오고 있다. 이를 방지하기 위해 국제적으로 우주쓰레기 경감 대책을 제시하고 있으며, 대표적으로 IADC(Inter-Agency Space Debris Coordination Committee)에서는 '25년 가이드라인'을 권고하고 있다. 한국항공우주연구원에서는 국내 최초로 랑데부/도킹 기술검증용 초소형위성인 KARDSAT(KARI Rendezvous & Docking demonstration SATellite) 프로젝트를 진행하였으며, KARDSAT 위성의 임무 후 폐기 기동(post-mission disposal)을 위한 항력 증대 장치 개발을 통해 우주쓰레기에 대한 국제적 가이드라인을 준수하고자 하였다.

• 시스템엔지니어링학술지
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• 제16권2호
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• pp.87-96
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• 2020

In this paper we proposed the test design method of reliability growth management. First, we presented the process for establishing the reliability growth management test design considering the number of failures and the termination test time. Reliability growth analysis of continuous system was performed in accordance with the test design process presented. In case the reliability test result is not met with the reliability target value after more than three failures occurred, the required test times were analyzed that 1,725 hrs for one corrective action, 1,950 hrs for two corrective actions. If the number of failures is less than three, design a reliability demonstration test according to confidence level 80% and 90% was performed using RGA 11 Software. As a result, it is possible to establish the reliability growth management test design with sufficient use of available resources. The results of this study can be used when establishing a test design for assessment of reliability growth management of all continuous systems.

• 한국전산구조공학회논문집
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• 제19권4호
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• pp.325-335
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• 2006

본 논문에서는 설계와 해석을 거쳐 인발성형으로 제작된 중공단면 복합소재 교량 바닥판에 대해 휨 성능시험, 바닥판-거더 연결부시험, 바닥판-방호벽 연결부시험 등을 통해 구조적 특성을 분석하였다. 휨시험체에 지간 중앙에 변위계와 상 하부판의 주요부에 변형률계를 부착하여 파괴하중 재하시까지 거동을 계측하고 그 결과를 분석하였다. 휨시험체에 대한 유한요소해석도 실시하여 시험결과와 비교분석하였으며, 휨에 대한 극한 내하력을 추정하였다. 또한, 시범시공된 복합소재 바닥판 플레이트 거더 교량에 대한 현장 재하시험결과와 현장적용사례를 기술하였다.

• 시스템엔지니어링워크숍
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• 통권4호
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• pp.17-22
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• 2004

This paper present the brief generation process of system requirements or mart UAV from a development obejective. The current Snart UAV requirements deal with the restricted life cycle from development to test and verification exclusive of full life cycle beacuse of the new technology demonstration research program funded by goverments. The Smart UAV system consists of flight vechicle, avionics, communication link, payload, ground control stationand ground supporting system. In thus paper, top-down flown requirememts are intoduced how to allocate to each sub-system.

• 대한전기학회:학술대회논문집
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• 대한전기학회 1998년도 하계학술대회 논문집 G
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• pp.2436-2438
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• 1998

The operating characteristics of a 3 kW grid-connected photovoltaic (PV) power system was studied by analying annual photovoltaic data. The system performance for grid connection was investigated using a DC/ AC inverter. The results of a demonstration test show that the system utilization rate is 15.6% and the system efficiency is 8.03%.

• Journal of Electrical Engineering and information Science
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• 제2권5호
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• pp.45-50
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• 1997

This paper present an advanced fault diagnosis expert system to assist the operators at local control center. The system utilizes all th information available in a local control center for the better diagnostic performance. The major feature of the system is dealing with multiple faults diagnosis based on the certainty factor method for the reasoning process. the overall performance and the generality are also enhanced by utilizing the general topological knowledge. ASCADA simulator is also developed for he test and demonstration.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.628-637
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• 2008

The JAXA's TechCLEAN project(2003-present) is summarized, with the interim technical achievements. TechCLEAN is collateral program with the NEDO engine project to accelerate R&D work of small passenger aircraft engine as well as to develop innovative environment technologies applicable to the future improvements. In the project NOx reduction, CO2 reduction and noise reduction are targeted. Component level researches and system demonstrator validation are planned with test facility renovation and demonstration base engines.

• Journal of Astronomy and Space Sciences
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• 제34권3호
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• pp.213-223
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• 2017

The deep space orbit determination software (DSODS) is a part of a flight dynamic subsystem (FDS) for the Korean Pathfinder Lunar Orbiter (KPLO), a lunar exploration mission expected to launch after 2018. The DSODS consists of several sub modules, of which the orbit determination (OD) module employs a weighted least squares algorithm for estimating the parameters related to the motion and the tracking system of the spacecraft, and subroutines for performance improvement and detailed analysis of the orbit solution. In this research, DSODS is demonstrated and validated at lunar orbit at an altitude of 100 km using actual Lunar Prospector tracking data. A set of a priori states are generated, and the robustness of DSODS to the a priori error is confirmed by the NASA planetary data system (PDS) orbit solutions. Furthermore, the accuracy of the orbit solutions is determined by solution comparison and overlap analysis as about tens of meters. Through these analyses, the ability of the DSODS to provide proper orbit solutions for the KPLO are proved.

• 신재생에너지
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• 제2권2호
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• pp.118-125
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• 2006

The target of this work was the process development of demonstration plant to produce the high quality alternative fuel oil by the pyrolysis of mixed plastic waste. In the first step of research, the bench-scale units of 70 t/y and the pilot plant of 360 t/y had been developed. Main research contents in this step were the process performance test of pilot plant of 360 ton/year and the development of demonstration plant of 3,000 t/y, which was constructed at Korea R & D Company in Kimjae City. The process performance of pilot plant of 360 t/y showed about 80% yield of liquid product, which was obtained by both light gas oil(LGO) and heavy gas oil(HGO), The boiling point range distribution of LO product that was mainly consisting of olefin components in PONA group appeared at between that of commercial gasoline and kerosene. On the other hand, HO product was mainly paraffin and olefin components and also appeared at upper temperature distribution range than commercial diesel. Gas product showed a high fraction of $C_3\;and\;C_4$ product like LPG composition, but also a high fraction of $CO_2$ and CO by probably a little leak of process.

• 한국방사성폐기물학회:학술대회논문집
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• 한국방사성폐기물학회 2005년도 Proceedings of The 6th korea-china joint workshop on nuclear waste management
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• pp.149-155
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• 2005

The $ACP^1$ is under development for effective management of spent fuel by converting $UO_2$ into U-metal. For demonstration of this process, $\alpha-\gamma$ type new hotcell was built in the $IMEF^2$ basement. To secure against radiation hazard, this facility needs radiation monitoring system which will observe the entire operating area before the hotcell and service area at back of it. This system consists of 7 parts; Area Monitor for $\gamma$-ray, Room Air Monitor for particulate and iodine in both area, Hotcell Monitor for hotcell inside high radiation and rear door interlock, Duct Monitor for particulate of outlet ventilation, Iodine Monitor for iodine of outlet duct, CCTV for watching workers and material movement, Server for management of whole monitoring system. After installation and test of this, radiation monitoring system will be expected to assist the successful ACP demonstration.