• Proceedings of the Optical Society of Korea Conference
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• 1991.06a
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• pp.199-202
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• 1991

기체 시로의 정밀한 분석이 가능한 공명이온화 질량분석장치(Resonance lonization Mass Spectrometor)를 설계, 제작하고 그 특성을 분석하였다. 두 개의 터보펌프(turbo-molecular pump)로 차등펌핑하여 1*10-7Torr 의 진공도를 얻었으며, Nd:YAG 레이저로 광펌핑되는 색소레이저를 분자빔에 조사하여 공명다광자 이온화현상에 의해 발생되는 이온들을 가속시켜 질량을 측정하였다. 아닐린을 시료로 사용하여 분석한 결과 최대 분해능 200을 얻었다.

• Proceedings of the Korean Institute of Surface Engineering Conference
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• 2015.05a
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• pp.83-83
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• 2015

터보 분자 펌프는 수 만 rpm의 고속으로 회전하여 분자 유동 영역에서 효율적으로 기체를 배기하는 특성을 가지고 있지만 실제 플라즈마 공정에서는 챔버의 압력이 수 mTorr이상이므로 점성 유동 영역이나 전이 유동 영역에 해당한다. 따라서 터보 분자 펌프의 rotor, blade, stator등의 설계가 점성 유동 영역에서 반응성 가스 및 플라즈마 특성에 의해서 어떤 영향을 받는지 수치 모델을 통하여 해석을 시도하였다.

• Proceedings of the KSME Conference
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• 2007.05b
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• pp.2725-2730
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• 2007

Turbo-type molecular drag pumps ( MDPs ) are used in the liquid crystal display ( LCD ), semiconductor and other thin film industries. Siegbahn ( disk-type ) molecular drag pumps are used as high-pressure stages in the hybrid-type turbomolecular pumps, where they can operate in the viscous, the transition and the free molecular flow regime. In this study is performed to investigate the pumping characteristics of three-stage disk-type molecular drag pump ( DTDP ) in the molecular transition flow region. The experiments are measured using five vacuum pressure gauges in the positions for rotors of DTDP. The test is performed with nitrogen gas ( $N_2$ ).

• Proceedings of the Korean Vacuum Society Conference
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• 2014.02a
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• pp.145.1-145.1
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• 2014

변형된 end-Hall type의 이온 소스를 사용하여 이온 소스의 형태에 따라 달라지는 이온 빔의 변화를 측정하였다. 이온 소스 cathode의 wehnelt mask를 세 가지 종류로 제작하였으며, 생성된 이온 빔을 이용하여 Al이 sputter 방식으로 증착된 유리 기판을 etching 하였다. 실험 결과 wehnelt mask의 모양에 따라 focus, broad, strate의 형태로 이온 빔이 생성되는 것을 확인하였다. Al이 증착된 유리 기판의 제작을 위하여 Al target을 사용하여 RF power로 150 W, 2분간 sputtering을 하였고, 이온 소스와 기판사이의 거리를 1 cm씩 증가시켜가며 이온 빔을 2,500 V로 3분간 유리 기판을 etching한 후, 유리 기판이 etching된 모양을 통해 이온 빔의 형태를 분석하였다. 본 연구를 위하여 sputtering과 이온 빔 처리가 가능한 챔버를 제작하였으며, scroll pump와 turbo molecular pump를 사용하였다. Base pressure $1.5{\times}10^{-6}Torr$에서 실험이 진행되었고, 불활성 기체 Ar을 사용하였다. Ar 기체를 주입시 pressure는 $2.6{\times}10^{-3}Torr$였다.

• Advances in aircraft and spacecraft science
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• v.9 no.5
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• pp.401-414
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• 2022

In the present paper, the optimal selection of batteries for an electric pump-fed hybrid rocket engine is analyzed. A two-stage Mars Ascent Vehicle, suitable for the Mars Sample Return Mission, is considered as test case. A single engine is employed in the second stage, whereas the first stage uses a cluster of two engines. The initial mass of the launcher is equal to 500 kg and the same hybrid rocket engine is considered for both stages. Ragone plot-based correlations are embedded in the optimization process in order to chose the optimal values of specific energy and specific power, which minimize the battery mass ad hoc for the optimized engine design and ascent trajectory. Results show that a payload close to 100 kg is achievable considering the current commercial battery technology.

• Proceedings of the Korean Society of Medical Physics Conference
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• 2002.09a
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• pp.396-399
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• 2002

Intense quasi-monochromatic x-ray irradiation from the linear plasma target is described. The plasma x-ray generator employs a high-voltage power supply, a low-impedance coaxial transmission line, a high-voltage condenser with a capacity of about 200 nF, a turbo-molecular pump, a thyristor pulse generator as a trigger device, and a flash x-ray tube. The high-voltage main condenser is charged up to 55 kV by the power supply, and the electric charges in the condenser are discharged to the tube after triggering the cathode electrode. The x-ray tube is of a demountable triode that is connected to the turbo molecular pump with a pressure of approximately 1 mPa. As electron flows from the cathode electrode are roughly converged to the molybdenum target by the electric field in the tube, the weakly ionized plasma, which consists of metal ions and electrons, forms by the target evaporating. In the present work, the peak tube voltage was almost equal to the initial charging voltage of the main condenser, and the peak current was about 20 kA with a charging voltage of 55 kV. When the charging voltage was increased, the linear plasma x-ray source grew, and the characteristic x-ray intensities of K-series lines increased. The quite sharp lines such as hard x-ray lasers were clearly observed. The quasi-monochromatic radiography was performed by a new film-less computed radiography system.

• Journal of the Korean Society of Propulsion Engineers
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• v.9 no.3
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• pp.74-84
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• 2005

This paper include the investigation of finding the system characteristics of facility by simulating open-type turbo-pump fed system, which has commercial control valves, using AMESIM (Advanced Modeling Environment Simulation) commercial software. After developing a flight-type control valve on the basis of the results, the system characteristics of facility for control and valve tests is estimated. Especially, one of purposes of this paper is to find PID value of each commercial control valve in the facility for system test. To find suitable control logic, PI and PID modes are also compared. This paper also introduces design parameters of valve and equipment for thrust control and TDS simulation, which are using control valves.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.104-107
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• 2017

The power-pack combustion test of technology demonstration model(TDM0) for 9 tonf-class staged combustion cycle engine development was conducted in the Upper-stage Engine Test Facility(UETF) of Naro Space Center. The power-pack model of TDM0 was composed of a pre-burner, a turbo-pump and propellant supply systems without a main combustor. In the power-pack combustion test, we confirmed the linked working condition and verified the main functional variation of the power-pack for the engine system test.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.864-870
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• 2017

The propellants are burned in the pre-burner of the staged combustion cycle engine, and the resulting hot gas drives the turbine, and the turbine operates the turbo pump. The burned gas passing through the turbo pump is supplied to the combustor at high temperature and high pressure, where the gas is supplied in an excess of fuel or an excess of oxidant depending on the amount of fuel or oxidant. When the cycle works at oxidizer-rich staged combustion, its metal pipe can ignite or explode by the impact of even small particles. In this study, we develop the powder combinations for anti-oxidation coating through the analysis of other coating materials and establish the coating process.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.79-87
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• 2017

Korea Aerospace Research Institute has being developed a staged combustion cycle rocket (SCCR) engine with high specific impulse to send a 3-ton class satellite into geostationary orbit while conducted Korean Space Launch Vehicle (KSLV) II project. The SCCR engine is different from the KSLV-II engine, which is open cycle engine using a gas-generator. The SCCR engine with closed cycle is composed of a pre-burner, a turbo pump, and a main combustor. The technology demonstration model (TDM0) was assembled and tested in the 7ton-class engine combustion test facility of Naro Space Center, and the combustion test was successfully conducted. Afterward engine-shaped SCCR engine model (TDM1) is being designed and developed for the next combustion test.