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우주 탐사용 액체 로켓을 위한 단일 밸브 기반 광범위 추력 제어 시스템 설계 및 성능 평가
문용준(Yongjun Moon),허선욱(Seonwuk Heo),장동욱(Dongwook Jang),권세진(Sejin Kwon) 한국추진공학회 2013 한국추진공학회 학술대회논문집 Vol.2013 No.12
캐비테이팅 벤츄리 기반 유량 제어 밸브만을 이용한 이원추진제 추력기의 광범위 추력 제어 기법의 가능성을 확인하였다. 이를 위해 수동 구동의 캐비테이팅 벤츄리 유량 제어 밸브를 제작하여 수류 및 실매질 시험을 수행하였고, 산화제/연료 밸브의 임계 압력비는 각각 약 85%와 75%로 확인되었다. 추력 제어 시험을 위해 기 개발된 진공추력 1200 N 급 H2O2/Kerosene 이원추진제 추력기와 유량 제어 밸브를 연결하여 연소 시험을 진행하였다. 설계 추력의 약 70%에서 23%까지의 범위에서 모두 안정적인 연소 성능을 보였으며 촉매의 성능이 감소하게 되었음에 유량이 일정하게 공급되었기 때문에 안정적으로 연소하는 경향을 확인하였다. A feasibility study for a deep throttle-able space propulsion system configured with a conventionally-designed H2O2/kerosene bipropellant thruster and cavitating venturi-type flow control valves was conducted. Manually-actuated flow control valves were designed and tested. The critical pressure ratio of the oxidizer and the fuel valves were found to be 85% and 75%, respectively. Hot fire throttling tests were performed using those valves and a 1000 N-class H2O2/kerosene bipropellant thruster with a thrust range from 23% to 70% of the rated thrust. All the results showed a stable combustion, and also the combustion efficiency was almost constant although catalyst performance was reduced.
능동형 대함 유도탄 기만기의 추진 시스템 요구 조건 분석
문용준(Yongjun Moon),권세진(Sejin Kwon) 한국추진공학회 2012 한국추진공학회 학술대회논문집 Vol.2012 No.11
능동형 대함 유도탄 기만기의 추진 시스템 요구 조건 및 저장성 액체 이원추진제 로켓 엔진의 적용가능성을 파악하기 위해 개념 설계를 수행하였다. 이미 미국과 오스트레일리아에서 공동 개발하여 운용 중인 Nulka의 제원을 통해 시스템의 기본적인 무게, 크기 등을 가정하였고, 1,000 N 급 과산화수소/케로신 로켓 엔진과 가압식 추진제 공급 방식으로 추진 시스템을 가정하였다. 이를 바탕으로 최적 궤적을 설계하였고 그 결과를 통해 하부 시스템들의 무게 분포를 예측하고 실현 가능성을 확인하였다. 그 결과, 100 초 이상의 운용 시간, 엔진 재점화, 그리고 최대 지상 추력 1,000 N의 경우 최소 35%까지의 추력 제어 성능이 추진 시스템의 요구 조건으로 도출 되었다. An active anti-ship missile decoy system was designed conceptually to analyze propulsion system requirements and feasibility to use a liquid bi-propellant rocket engine. Overall mass, size, and shape were assumed referring to specifications of Nulka which was developed by US and Australia in 1990s. The propulsion system was assumed to be a 1,000 N-class H2O2/kerosene rocket engine with a pressurized feed system. A three-degree-of-freedom optimal trajectory was calculated based on the assumptions, and mass budget was designed from the calculation results. It was found that the requirements for the propulsion system is that it shall be operated more than 100 s; it shall be re-ignitable; it shall have a throttle capability of a range from 35% to 100% when the maximum thrust at sea level is 1,000 N.
능동형 대함 유도탄 기만기의 추진 시스템 요구 조건 분석
문용준(Yongjun Moon),권세진(Sejin Kwon) 한국추진공학회 2013 한국추진공학회지 Vol.17 No.4
An active anti-ship missile decoy system was designed conceptually to analyze propulsion system requirements and feasibility to use a liquid bi-propellant rocket engine. Overall mass, size, and shape were assumed referring to specifications of Nulka which was developed by US and Australia in 1990s. The propulsion system was assumed to be a 1,000 N-class H₂O₂/kerosene rocket engine with a pressurized feed system. A three-degree-of-freedom optimal trajectory was calculated based on the assumptions, and mass budget was designed from the calculation results. It was found that the requirements for the propulsion system is that it shall be operated more than 100 sec; it shall be re-ignitable; it shall have a throttle capability of a range from 35% to 100% when the maximum thrust at sea level is 1,000 N.
박현철(Hyunchul Park),문용준(Yongjun Moon),박대종(Daejong Park),권세진(Sejin Kwon) 대한기계학회 2012 대한기계학회 춘추학술대회 Vol.2012 No.11
The tire pressure monitoring system (TPMS) market is rapidly growing with legislation making TPMS installation obligatory among automotive developed countries?i.e., Japan, EU, and Korea?in 2012, after the same bill progressed in the USA in 2007. So far, TPMS research is mostly concentrated in the ultralow-power circuit field. However, one of the biggest challenges is overcoming the unavoidable replacement of batteries owing to the self-discharging, unstable performance, etc. of the batteries. Energy-harvesting technology is the only candidate to substitute battery technology. Energy harvesters are modules that generate electric power to operate sensing nodes by gathering wasted energy in the surrounding area. There were two core questions for the key challenges examined in this study: “Which energy source do we use?” and “How much energy do we generate?” The answers would be the design constraints included with the suggested volume of energy harvester.
직교 배열표를 이용한 휠 기반 회전형 전자기 유도 방식 에너지 하베스터 개발
박현철(Hyunchul Park),문용준(Yongjun Moon),권세진(Sejin Kwon) 대한기계학회 2013 大韓機械學會論文集B Vol.37 No.2
TPMS(Tire pressure monitoring system)의 의무장착에 대한 법률개정에 따른 개발의 활성화를 토대로, WSN(Wireless Sensor Network)의 ‘설치하고 잊어버린다’는 기본 명제 하에, 차량수명과 동일한 성능의 배터리 대체용 에너지 하베스터에 대한 연구가 활발히 진행되고 있다. 본 논문은 자동차의 메커니즘적인 측면에서 가장 유용한 회전운동 성분을 이용하여 회전하는 휠과 고정된 브레이크 디스크 사이의 상대운동을 통한 전자기 유도방식 발전을 채택하였다. 휠 측에 구성된 코일과 브레이크 디스크에 매립된 자석의 다양한 배열과 코일 권선수 등을 설계변수로 잡고 직교배열표를 이용하여 최적의 조합을 찾아낸 후 실험을 통해 실제 축전되는 전기 에너지의 양을 측정하여 도출된 특성함수를 바탕으로 본 모듈의 타당성을 검증하였다. According to the law revision of TPMS mounting obligations in Korea, researches about energy harvester which is the alternative of the battery are actively performed by many groups. Because WSN (Wireless Sensor Network) has the proposition of “Install and forget” and the power supplier also has the same performance as the vehicle’s lifetime. In this paper, electromagnetic induction type of energy harvester through the relative motion between the rotating wheel and the fixed brake disc is introduced by using the most efficient source as the rotating motion in the view of vehicle’s mechanism. The coil on the wheel and the permanent magnet at the brake disc are arranged in several ways. These various arrangements are the number of coil turns are consisted of design variables. By using the orthogonal array to reduce the experimental cost, the optimal composition is verified through the experiment. Finally the validity of the module is considered by measuring the level of storable electrical energy.
전동현(Donghyun Jun),문용준(Yongjun Moon),이열(Yeol Lee),김진곤(Jinkon Kim) 대한기계학회 2008 대한기계학회 춘추학술대회 Vol.2008 No.5
The flow characteristics of sonic/supersonic jets issuing from a thin rectangular nozzle (high aspect ratio=11:1) have been experimentally investigated by multi-Pitot tube measurements and Schlieren flow visualizations. The paper is particularly concerned with the streamwise/spanwise variation of the thin jet flow fields. The characteristics of the perfectly-expanded thin supersonic jet of Mach 2.0, such as shock structures, decay of the centerline velocity and axis-switching, have been observed, and the present results are compared with previous studies.