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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.
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.
1 N급 단일추진제 추력기 개발모델의 장기수명 연소시험 PartⅡ: 펄스모드 성능 특성
원수희(Su-Hee Won),김수겸(Su-Kyum Kim),전형열(Hyoung-Yoll Jun),이준희(Jun-Hui Lee),박수향(Su-Hyang Park),이재원(Jae-Won Lee) 한국추진공학회 2014 한국추진공학회지 Vol.18 No.6
During the life firing test of 1 N-class thruster development model, pulse mode performance and performance changes were examined. The deviation of pulse mode response time according to thruster feed pressure was relatively small and the resultant ignition delay, response time, tail-off time were 32-35 ms, 86-91 ms, 89-98 ms, respectively. For the stabilized pulse region the impulse bit revealed the outstanding reproducibility of 1.41, 1.32, 2.10% at 3σ. During the life firing test, the impulse bit was decreased with limited amounts, therefore the pulse mode performance could be considered to be maintained. The thrust centroid was also maintained during the life firing test.
GCI 를 이용한 수직분사제트 수치모사의 검증 및 확인
원수희(Su-Hee Won),정인석(In-Seuck Jeung),최정열(Jeong-Yeol Choi) 한국항공우주학회 2006 韓國航空宇宙學會誌 Vol.34 No.4
초음속 주 유동으로의 수직분사에 의해 생성되는 2차원 정상상태 유동장에 대한 수치모사를 수행하였다. 난류효과를 위해서 무차원 벽면거리(y?)를 고려한 2방정식 k-ω SST 모델을 사용하였다. 또한 격자계에 따른 오차범위를 나타내는 방법으로 GCI(Gird Convergence Index)를 사용하여 해의 수렴성을 측정하였다. 표면 압력분포, 박리거리, 침투높이 등에 대해 실험결과 및 다른 난류모델을 이용한 결과들과 비교하였다 k-ω SST 난류모델은 낮은 압력비에 대해서 표면 압력분포 및 박리거리 등을 정확하게 예측하였다. 그러나 압력비가 증가함에 따라 수치적 예측이 실험결과와 차이를 보이고 있다. 상기한 모든 결과는 격자계에 따른 해의 수렴성의 오차범위 1% 이내에서 측정되었다. Two-dimensional steady flowfields generated by transverse injection jets into a supersonic mainstream are numerically simulated. Fine-scale turbulence effects are represented by a k-ω SST two-equation closure model which includes y? effects on the turbulence model. Solution convergence is evaluated by using Grid Convergence Index(GCI), a measure of uncertainty of the grid convergence. Comparison is made with experimental data and other turbulence models in term of surface static pressure distributions, the length of the upstream separation region, and the penetration height. Results indicate that the k-ω SST model correctly predicts the mean surface pressure distribution and the upstream separation length for low static pressure ratios. However, the numerical predictions become less consistent with experimental results as the static pressure ratio increases. All these results are taken within 1 % error band of grid convergence.
원수희(Su-Hee Won),전형열(Hyoung-Yoll Jun),김성훈(Sung-Hoon Kim),이상률(Sang-Ryool Lee) 한국항공우주학회 2012 韓國航空宇宙學會誌 Vol.40 No.7
본 논문은 우주기술 저변확대를 위한 초소형위성 프로그램 중 하나로 캔위성 경연대회에 대해 살펴보았다. 먼저 캔위성과 인공위성의 차이점을 알아보고 해외 캔위성 경연대회사례 및 국내 캔위성 개발 동향을 정리하였다. 이를 바탕으로 국내 캔위성 경연대회의 운영조직 및 역할을 제시하였으며, 캔위성, 발사체, 지상국 등과 같은 경연대회 소요기술의 요구조건 및 개발방안을 도출하였다. 또한 경연대회 수행임무, 사전교육, 진행일정 등 경연대회 추진방안을 마련하였다. This paper presented the CanSat competition as one of very small satellite programs for expending the space technology base. The CanSat was compared and characterized with a real satellite and the foreign CanSat competition cases and domestic CanSat development trends were summarized. On the basis of the above information, the organizational structure and function were suggested for domestic CanSat competition and the required technologies, such as satellite, launcher and ground station were described. And also, the prior plan for competition, including mission, education and schedule were suggested.
1N 단일추진제 추력기 개발모델의 장기수명 연소시험에 따른 펄스모드 성능추이
원수희(Su-hee Won),김수겸(Su-kyum Kim),전형열(Hyoung-yoll Jun),이준희(Jun-hui Lee),박수향(Su-hyang Park),이재원(Jae-won Lee) 한국추진공학회 2014 한국추진공학회 학술대회논문집 Vol.2014 No.5
1N급 추력기 개발모델의 장기수명 연소시험 동안 펄스모드 추력성능 추이를 살펴보았다. 냉시동에 의한 불안정 효과가 사라진 30 펄스에 대해 임펄스 비트 및 추력 중심 지연의 평균을 측정하였다. 장기수명 연소시험 동안 연료 소모량에 따라 임펄스 비트가 다소 감소하지만 그 감소폭은 제한적이며, 따라서 펄스모드 성능이 유지된다고 볼 수 있다. 또한 일부 예외적인 부분이 존재하지만 추력 중심 지연 또한 장기수명 연소시험 동안 일정한 것을 확인할 수 있었다. Pulse-mode performance changes were examined during life firing test of 1N-class thruster development model. The impulse bit and thrust centroid were averaged over the clear 30 pulses without unstable effects caused by cold start. During life firing test, the impulse bit was decreased with limited amounts according to fuel consumption, therefore the pulse-mode performance could be considered to be maintained. The thrust centroid was also maintained during life firing test, even though there was an exception.