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RISS 인기검색어
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- 저자 : 원수희(Su-Hee Won) (검색결과 96 건)
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원수희(Su-Hee Won),윤형주(Hyungjoo Yoon),이춘우(Choon-Woo Lee),전현진(Hyeon-Jin Jeon) 한국추진공학회 2022 한국추진공학회 학술대회논문집 Vol.2022 No.5
2000년대 이후 수행된 해외 달 착륙선 추진시스템 사례 조사를 조사하였다. 미국의 CLPS 프로그램을 비롯해 중국, 유럽, 이스라엘, 인도의 달 착륙선 추진시스템 사례를 조사하였으며, 국내 달 착륙선 추진시스템 개발 방향 수립에 참고할 수 있는 시사점을 도출하였다. The lunar lander propulsion systems performed since the 2000s were investigated. The US CLPS program, as well as cases of China, Europe, Israel, and India were investigated, and implications were derived that can be referred to in the development of a domestic lunar lander propulsion system.
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HyShot-Ⅱ 스크램제트 연소기 설계 조건에 대한 3차원 전산해석
원수희(Su-Hee Won),정인석(In-Seuck Jeung),최정열(Jeong-Yeol Choi) 한국연소학회 2010 KOSCOSYMPOSIUM논문집 Vol.- No.40
HyShot-Ⅱ scramjet combustor flowfield, where gaseous hydrogen is transversely injected into a supersonic cross flow, is numerically investigated using detached-eddy simulation and finite-rate chemistry model. The amount of fuel injection is considered for the design condition which corresponds to equivalence ratio of 0.3. This work features detailed resolution of the flow and flame dynamics in the combustor, which was not typically available in most of the pervious studies. Results indicate that fuel-air mixing is caused by Kelvin-Helmholtz instability and enhanced by the impingement of oblique shocks at the fuel-air interface. While the numerical results reproduce well the pressure distribution for non-reacting region and self-ignition location, the pressure rise by combustion is over-predicted.
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원수희(Su-hee Won),김수겸(Su-kyum Kim),채종원(Jong-won Chae),한조영(Cho-young Han),전형열(Hyoung-yoll Jun),이준희(Jun-hui Lee),박수향(Su-hyang Park),이재원(Jae-won Lee) 한국추진공학회 2013 한국추진공학회 학술대회논문집 Vol.2013 No.5
1N급 단일추진제 하이드라진 추력기 개발모델에 대한 인수수준 랜덤 진동시험이 수행되었다. 랜덤 진동시험은 기존 항공우주연구원의 1lbf 추력기의 시험절차를 참고하여 진행되었다. 랜덤 진동시험 결과로부터 1N급 추력기 개발모델로 구성된 이중추력기모듈의 고유진동수는 기준치를 훨씬 상회하였으며, 구조적으로 강건하다는 것을 확인하였다. 또한 진동시험 동안 추력기 내부 촉매의 손상은 없었으며, 이로 인한 연료공급 유로의 막힘 현상도 발생하지 않았다. Acceptance level random vibration test for development model of 1N-class monopropellant thruster has been performed. The random vibration test was carried out based on the KARI test procedure for 1lbf thruster. From the test results of random vibration, the natural frequency of the dual thurst module composed of 1N-class development model thrusters was much higher than the standard and the structural robustness was verified. The catalyst damage during the vibration test was not observed and the plugging phenomenon was not occurred either.
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Su-Hee Won(원수희),In-Seuck Jeung(정인석),Jeong-Yeol Choi(최정열) 한국연소학회 2007 KOSCOSYMPOSIUM논문집 Vol.- No.-
This paper describes numerical efforts to investigate combustion characteristics of HyShot scramjet combustor, where gaseous hydrogen is transversely injected into a supersonic cross flow. The corresponding altitude, angle of attack, and equivalence ratio are 35-23 ㎞, 0°, and 0.426 respectively. Two-dimensional simulation reasonably predicts combustor inner pressure distribution and reveals periodic combustion characteristics of HyShot scramjet combustor. Altitude effects are also investigated and the strength of flow instability and subsonic boundary layer thickness affect the combustion efficiency according to altitudes. Frequency analyses provide the flow instability effects on the turbulent combustion in HyShot scramjet combustor.
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초음속 유동내 수직 연료분사의 난류 반응 유동장에 대한 DES 해석
원수희(Su-Hee Won),노진현(Jinhyeon Noh),정인석(In-Seuck Jeung),최정열(Jeong-Yeol Choi) 한국연소학회 2008 KOSCOSYMPOSIUM논문집 Vol.- No.-
Three-dimensional unsteady reacting flowfield generated by transverse hydrogen injection into a supersonic mainstream are numerically investigated using DES and finite-rate chemistry model. Comparisons are made with experimental results to investigate the turbulent mixing and reacting flow physics. The numerical OH distribution describes well the experimental OH-PLIF result, while the numerical ignition delay time shows some disparity due to the restricted available experimental data. The intermittency phenomena are identified by the comparative analysis between RANS and DES and their effects are Quantified by the temperature distributions along streamlines and superimposed OH mass fraction along with time.
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