http://chineseinput.net/에서 pinyin(병음)방식으로 중국어를 변환할 수 있습니다.
변환된 중국어를 복사하여 사용하시면 됩니다.
김중일(Joongil Kim),고민호(Minho-Ko),김이중(Leejung Kim),서중규(Jungyu Seo),김형육(Hyungyuk Kim),김유(Yoo Kim),고영성(Youngsung Ko) 한국추진공학회 2013 한국추진공학회 학술대회논문집 Vol.2013 No.12
본 논문에서는 예비설계를 통한 고공환경모사 시험설비의 각 파트별 냉각수 공급시스템의 요구유량을 제시하였으며 요구유량에 따라 펌프식 및 가압식으로 나누어 냉각수 공급시스템을 설계ㆍ제작하였다. 펌프식 냉각수 공급시스템 및 가압식 냉각수 공급시스템의 cavitation venturi 검증실험을 통해 안정한 냉각수 유량을 공급할 수 있음을 확인하였다. In this paper, mass flow rate of a cooling water supply system was presented through preliminary design of high-altitude test facility(HATF). The cooling water supply system consisted of pressurization and pump type to satisfy flow rate requirements. Hydraulic tests were performed to verify mass flow rate of cooling water. The experimental result showed that the cooling water supply system could supply accurate mass flow rate to each part by cavitation venturies.
문근환(Keunhwan Moon),김재선(Jaesun Kim),고민호(Minho Ko),전유림(Yulim Jeon),이종덕(Jongdeok Lee),이범석(Beomseok Lee),지상연(Sangyeon Ji),이준성(Junseong Lee),김철웅(Cheulwoong Kim),임석희(Seokhee Lim) 한국추진공학회 2023 한국추진공학회 학술대회논문집 Vol.2023 No.5
This paper introduces the test plan of a 1tonf-class vertical take-off and vertical landing(VTVL) demonstrator. The test facility for the VTVL demonstrator performance tests was constructed. The test facility was composed of a vertical test bed, propellant and pressurizing gas supply/drain system, and a control room. The test plan is to conduct leak and cold flow tests, vertical hot fire tests, and tethered flight tests. And free flight test will be conducted for verification of VTVL demonstrator.
임태흥(Tae Heung Lim),왕성식(Sungsik Wang),고진원(Jinwon Ko),고민호(Minho Go),서철헌(ChulHun Seo),추호성(Hosung Choo) 대한전자공학회 2019 전자공학회논문지 Vol.56 No.1
본 논문에서는 AREPS(Advanced Refractive Effects Prediction System) 시뮬레이션을 사용하여 공대공 AESA 레이다 전파특성 및 표적 탐지를 위한 경로손실 값을 분석하였다. 국내 도심 지역의 지형 정보를 반영하고 실측 대기 특성을 기반으로 한 trilinear 수정 대기 굴절률을 모델링하여, normal, surface duct, elevated duct, combined atmospheric condition 대기에 대한 네 가지 시나리오를 설정하였다. 또한, zx-plane에서 4.4°의 HPBW와 35.7dB의 SLL을 가지는 AESA 레이다 배열안테나의 방사패턴을 적용하여 네 가지 시나리오에 따른 경로손실 값을 도출하였다. 고도 5000 m에 위치시킨 AESA 레이다를 전면 방향으로 조향 하였을 때, combined condition에서 150 km 거리의 경로 손실 값이 171 dB로 계산되어 전면방향으로 표적 탐지 성능이 저하되는 결과를 확인하였다. Combined atmospheric condition의 대기 상태에서 trap의 높이와 두께를 변화시키며 고도 5000 m의 전면방향 표적 위치에 대한 경로손실을 분석하였으며, trap이 발생한 높이 h2가 AESA 레이다 위치와 유사한 4800 m부터 5200 m까지 위치할 때 표적탐지 성능이 많이 열화되는 것을 확인하였다. In this paper, we analyzed the radar wave propagation characteristics for air-to-air AESA radars and calculated the path loss for estimating target detection performance using Advanced Refractive Effects Prediction System (AREPS) simulation software. Four atmospheric scenarios of normal, surface duct, elevated duct, and combined atmospheric conditions were set up by using the trilinear modified refractivity model, including the terrain data of the urban area of Korea. In addition, we applied the radiation pattern of the AESA radar array antenna with HPBW of 4.4° and SLL of 35.7 dB in zx-plane to the path loss simulations with four atmospheric scenarios. When AESA radar located at a height of 5000 m is steered to the bore-sight direction, the path loss of 171 dB is obtained at a distance of 150 km in the combined atmospheric condition, which indicates that the target detection performance in the bore-sight direction may be degraded. In the combined atmospheric condition, the path losses according to the variation of the trap height and thickness were obtained when the target was located at the height of 5000 m. It is found that the target detection performance is drastically deteriorated when the height h2 resides between 4800 m and 5200 m, where the trap height is similar to the AESA radar altitude.
지상연(Sangyeon Ji),이성민(Seongmin Lee),전유림(Yulim Jeon),한상두(Sangdu Han),김광원(Kwangwon Kim),유지성(Jisung Yoo),이종덕(Jongdeok Lee),이범석(Beomseok Lee),고민호(Minho Ko),이준성(Junseong Lee),김철웅(Cheulwoong Kim),임석희(Seokhee 한국추진공학회 2023 한국추진공학회 학술대회논문집 Vol.2023 No.5
This paper introduces the development of a 1tonf-class vertical take-off and vertical landing(VTVL) demonstrator designed to verify the core technology of reusable launch vehicles. The VTVL demonstrator has a pressure-fed engine system and uses liquid oxygen and liquid methane as propellants. Major autonomous tests of its subsystems and components have been completed. Hot fire tests and tethered flight tests will be conducted on the VTVL demonstrator to verify the functionality and performance.