http://chineseinput.net/에서 pinyin(병음)방식으로 중국어를 변환할 수 있습니다.
변환된 중국어를 복사하여 사용하시면 됩니다.
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.
양수석(Soo Seok Yang) 한국추진공학회 2019 한국추진공학회지 Vol.23 No.4
Recently, in the space market, there has been a rapid reduction of the launch price. The major reason is that a few commercial companies, especially SpaceX, began to enter into the space market about ten years ago, which has changed the space market from monopolization to competition, and accelerated the adoption of commercial efficiency in the technology and management. Also, the successful landing and recovery of a first stage in 2016 by SpaceX proved to be a prelude to opening a new era of reusable launch vehicles, and SpaceX declared the groundbreaking launch price through using the reusable launch vehicle. This study calculates the total launch cost required to put a certain satellite into the LEO, compares the launch cost in three cases with different payload weights, and reviews the impacts of the payload on the cost effectiveness of a reusable vehicle. The total launch cost is divided into 6 subsections cost, namely development cost, production cost, refurbishment cost, operation cost, fixed-cost of factory and launch site, and insurance cost. The cost estimation relationships used in the calculation are taken from the commonly proven cost models such as TRANSCOST.
재사용발사체의 발사비용에 미치는 가격인자들의 민감도 분석
양수석(Soo Seok Yang) 한국추진공학회 2020 한국추진공학회지 Vol.24 No.2
Recently the reusable launch vehicle is being a major trend in the worldwide space market, because a few commercial companies, especially SpaceX, are trying to cut down the launch price through developing and succeeding the reusable launch vehicles. However, there is still a big controversy about whether in view point of the launch cost which is more favorable between expendable and reusable. Therefore, a study and close examination is required for the launch cost in the early development phase of the reusable launch vehicle. In this study the sensitivity analysis is performed with respect to the major cost parameters which have great effects on the launch cost and price. The standard vehicle of this sensitivity analysis is the expendable vehicle having a payload 20 tons. The cost estimation relationships used in this calculation are referred from the commonly proven cost models such as TRANSCOST. The major cost parameters chosen in this study are as follows: development cost, production cost, refurbishment cost, and maximum reusable number.
이양지(Yang Ji Lee),강상훈(Sang Hun Kang),오중환(Joong Hwan Oh),양수석(Soo Seok Yang) 한국추진공학회 2010 한국추진공학회지 Vol.14 No.3
Korea Aerospace Research Institute started on design and development of a hypersonic air-breathing engine test facility from 2000 and completed the test facility installation in July 2009. This facility, designated as Scramjet engine test facility(SeTF), is a blow-down type high enthalpy wind tunnel which has a pressurized air supply system, air heater system, free-jet test chamber, fuel supply system, facility control/measurement system and exhaust system. In this paper, details of the specifications, and configuration of the SeTF are described. For verifying characteristics of the SeTF, wind tunnel tests are now on progress and some of the data are also described.