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김문기(Munki Kim),한영민(Yeoung-Min Han),김종규(Jonggyu Kim),안규복(Kyubok Ahn),이광진(Kwang-Jin Lee),최환석(Hwan-Seok Choi) 한국추진공학회 2009 한국추진공학회 학술대회논문집 Vol.2009 No.11
한국형 발사체용 액체로켓엔진을 개발하기 위한 75톤급 연소기 기술검증 시제를 제작하여 수류시험 및 점화시험을 수행하였다. 기존의 연소기에 새롭게 도입된 기술인 점화, 막냉각, 산화제 선공급방식을 반영하기 위해 시험설비를 수정 및 개량하였다. 산화제 및 연료 수류시험을 통해 공급라인, 점화기 라인, 연소기의 수력학적 특성, 추진제 충전시간을 파악하여 점화순서를 결정하였다. 점화 cyclogram을 통해 점화기의 점화시험을 성공적으로 수행하였으며, 향후 연소시험을 위한 기초 자료를 습득하였다. Cold flow and ignition tests were performed for a technology demonstration model of a 75-tonf thrust chamber which is a candidate liquid rocket engine for a next Korea Space Launch Vehicle. The test facility was modified to support the new concepts of the thrust chamber such as ignition system, film cooling and LOx leading supply. The hydrodynamic characteristics of the supply pipelines, thrust chamber and igniter as well as the filling time of the propellants were obtained through the cold flow tests on the LOx and kerosene and the ignition cyclogram was determined using the results. The ignition test was successfully accomplished according to the cyclogram and therefore, a basic information was obtained for further hot firing tests.
Determination of Cyclogram for Liquid-Propellant Rocket Engine
Ha, Seong-Up,Kwon, Oh-Sung,Lee, Jung-Ho,Kim, Byoung-Hun,Kang, Sun-Il,Han, Sang-Yeop,Cho, In-Hyun,Lee, Dae-Sung The Korean Society for Aeronautical and Space Scie 2002 International Journal of Aeronautical and Space Sc Vol.3 No.2
A vertical test stand based on launcher propulsion system was constructed and several tests for the determination of cyclogram were carried out. To make an accurate estimation, static and dynamic pressures were measured and analyzed. Especially, static pressure measurements using fast response sensors without extension tubes were used to determine operation sequence more evidently. The standard operation times of final valves were determined in cold flow tests with an engine head, and fire formation time in combustion chamber was checked in an ignition test with an ignitor only. On the basis of these tests, ignition sequence was established and combustion test cyclogram was finally determined. According to combustion test, test results were well matched with the determined cyclogram within 0.05 sec.
임병직(Byoungjik Lim),한영민(Yeoung-Min Han),김종규(Jong-Gyu Kim),서성현(Seonghyeon Seo),안규복(Kyubok Ahn),김문기(Munki Kim),이광진(Kwang-Jin Lee),최환석(Hwan-Seok Choi) 한국추진공학회 2010 한국추진공학회 학술대회논문집 Vol.2010 No.5
한국형발사체 엔진에 사용될 것으로 예상되는 75톤급 연소기의 기술검증시제를 이용하여 2회 연소시험을 수행하였다. 설비 공급 능력과 구조물 강도 제한으로 정상 유량의 50% 수준에서 시험이 수행되었다. 채널냉각 연소기를 이용한 저압연소시험을 통해 점화구간과 연소구간에서의 신뢰도와 안정성이 확인되었다. 더불어 75톤 연소기가 성능요구조건을 만족시킬 수 있을 것으로 추정할 수 있었다. Using the technology demonstration model of 75-tonf-class combustor which is expected to be used to the rocket engine of a korean space launch vehicle, 2 times of firing tests were carried out. Firing tests were done at 50% of the nominal flow rate because of incapability of the test facility and limit of the test bed strength. Through the low pressure firing tests of 75-tonf-class channel cooling thrust chamber, reliability and stability at the ignition and combustion phases were confirmed. Additionally it was foreseen that the 75-tonf-class thrust chamber would satisfy the performance requirements.
임병직(Byoungjik Lim),한영민(Yeoung-Min Han),김종규(Jong-Gyu Kim),최환석(Hwan-Seok Choi) 한국추진공학회 2011 한국추진공학회지 Vol.15 No.1
Firing tests have been carried out for a technology demonstration model of 75-tonf-class combustor which is to be used on the liquid rocket engine of a Korean space launch vehicle. Firing tests were done at 50% of the nominal flow rate because of incapability of the test facility and limit of the test bed strength. Through the low pressure firing tests of 75-tonf-class channel cooling thrust chamber, operability and stability at the ignition and combustion phases were confirmed. Additionally it was foreseen that the 75-tonf-class thrust chamber would satisfy the performance requirements.