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양수석,송태호,Yang, Soo-Seok,Song, Tae-Ho 대한기계학회 2000 大韓機械學會論文集B Vol.24 No.4
Analytical experiments to determine the line-of-sight temperature distribution is conducted by using spectral radiation intensities. For this study, fourteen narrow bands of $25cm^{-1}$ interval in $CO_2\;4.3{\mu}m$ band ($2,050cm^{-1}$ to $2375cm^{-1}$) are selected. The applied system is a one-dimensional gas slab filled with 100% $CO_2$ gas at 1 atm. Two types of temperature profile are tested; parabolic and boundary layer types. Three kinds of radiation calculation are used in the iteration procedure for the temperature inversion; LBL(Line by Line), SNB(Statistical Narrow Band) and WNB(WSGGM. based Narrow Band) models. The LBL solution shows perfect agreement while some error of temperature prediction is caused by radiation modeling error when using SNB and WNB models. The inversion result shows that the WNB model may be used more accurately in spectral remote sensing techniques than the traditional SNB model.
양수석(Soo-Seok Yang),이대성(Dae-Sung Lee),김승우(Seung-Woo Kim) 한국유체기계학회 1999 유체기계 연구개발 발표회 논문집 Vol.- No.-
Currently under development is an airborne auxiliary power unit with 100 Kw equivalent power, which is composed of a centrifugal compressor, a reverse annular combustor, and a radial turbine. Air-foil bearings are used in this power unit to eliminate the oil supplying system, which can reduce the system complexity and weight. The high speed generator is adopted as an electric power generation and engine starting system, which can also eliminate the reduction gear system. Not only electric power but also pneumatic power is provided by bleeding the compressed air. This power unit is aimed for the multi-purpose use such as a primary power unit in the army weapon system, an auxiliary power and environmental control unit in a next-generation tank, and a smoke generating unit.
양수석(Soo Seok Yang) 한국추진공학회 2019 한국추진공학회 학술대회논문집 Vol.2019 No.11
아폴로 11호의 달 착륙으로 우주여행에 대한 꿈이 현실로 실현될 것만 같았으나, 50년이 지난 지금도 우주는 인류의 자유로운 접근을 쉽게 허용하지는 않고 있다. 다만, 최근 들어서 ‘New Space’라는 기치 아래 민간 주도로 우주에 대한 상업적 활용의 폭이 점차 커지고 있고, 이에 따라 우주여행과 이를 실현 할 수 있는 우주비행기의 개발도 상당한 진척을 보이고 있다. 본 연구에서는 우주비행기의 형태 중에서 현실적으로 가장 실현 시기가 빠를 것으로 예측되는, 로켓엔진을 이용한 TSTO (Two Stage To Orbit)형 우주비행기로서, SpaxeX가 현재 개발을 진행하고 있는 BFR 비행체를 대상으로 하여 발사비용을 분석한다. 발사비용은 6가지의 세부비용으로 나누어 계산하며 각각의 비용은 TRANSCOST의 비용 추정식 등을 이용하여 계산한다. The historic moon landing of Apollo 11 made mankind to fall into illusion that the space journey would be realized in an instant. Fifty years after, however, the unconstrained and non-specific space access of mankind has not been still allowed. Fortunately, as many commercial parties are recently taking the initiative in enlarging the economic utilization of space under the flag of ‘New Space’, the new business of space, for example such as global satellite service, space resource mining, space tourism and son on, comes into the spotlight. Therefore, the space plane to realize the space journey is being also focused, and significant progress has been made in its development. In this research, the launch cost analysis of space plane is conducted for the BFR vehicle, TSTO space plane using rocket engines, that is under development by SpaceX because its successful commercialization is generally forecast to come true in nearest future. The total launch cost is divided into 6 subsections costs which are calculated by using the cost estimation relationships of TRANSCOST and others.
이양지(Yang Ji Lee),강상훈(Sang Hun Kang),양수석(Soo Seok) 한국추진공학회 2011 한국추진공학회 학술대회논문집 Vol.2011 No.11
한국항공우주연구원은 비행시험용 스크램제트 엔진의 최적 형상을 도출을 목표로 추력 노즐 변화에 따른 스크램제트 엔진의 특성을 파악하고자 여러 가지 형상의 추력 노즐을 설계 및 제작하였다. 성능시험은 호주 University of Queensland의 T4 충격파 터널에서 수행되었으며, 총 8종의 노즐과 2종의 측벽이 시험되었다. 본 논문에는 스크램제트 엔진의 추력 노즐과 측벽의 설계 및 사양을 정리하였다. 또한 스크램제트 엔진 Baseline의 정압력과 노즐 출구 피토 압력 분포를 계산한 결과 양의 비추력을 얻었음을 확인하였다. Korea Aerospace Research Institute has been designed and manufactured various thurst nozzles of the scramjet engine for optimized configuration. The test campaign for thurst nozzle characteristics was performed at T4 free-piston shock tunnel in University of Queensland, Australia. Total 8 kinds of thrust nozzles and 2 kinds of side walls were manufactured for this campaign. In this paper, the design and specification of thrust nozzles was reported. Based on the static pressure distribution of the engine and pitot pressure distributions at nozzle exit, The positive net thurst was observed with baseline case of the test campaign.