• JOURNAL OF ELECTRICAL WORLD
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• s.428
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• pp.32-37
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• 2012

• Proceedings of the Korean Vacuum Society Conference
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• 2013.02a
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• pp.532-532
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• 2013

세계의 반도체, 의료, 금속, 섬유 등의 분야에서 기술이 고도화됨에 따라서 나노 입자, High quality 박막 등에 대한 수요는 커져가고 있다. 이를 제조하기 위한 공정은 극 저압 상태에서 이루어진다. 따라서 극 저압 기체 흐름에 대한 이해는 필수적이다. 하지만 일반적으로 수 mTorr 이하의 압력에서는 유체 시뮬레이션으로 해석하는 것이 불가능하다. 그러므로 우리는 DSMC 방법을 이용하여 극 저압 CCP 챔버 내의 기체의 흐름을 해석하고 특성을 살펴보았다.

• Journal of IKEEE
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• v.20 no.1
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• pp.61-67
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• 2016

In this paper, a hardware design method is proposed for high speed high precision neutron radiation measurements. Our system is fabricated to use a high performance A/D Converter for digital data conversion of high precision and high speed analog signals. Using a neutron sensor, incident neutron radiation particles are detected; a precision microcurrent measurement module is also included: this module allows for more precise and rapid neutron radiation measurement design. The high speed high precision neutron measurement hardware system is composed of the neutron sensor, variable high voltage generator, microcurrent precision measurement component, embedded system, and display screen. The neutron sensor detects neutron radiation using high density polyethylene. The variable high voltage generator functions as a 0 ~ 2KV variable high voltage generator that is robust against heat and noise; this generator allows the neutron sensor to perform normally. The microcurrent precision measurement component employs a high performance A/D Converter to precisely and swiftly measure the high precision high speed microcurrent signal from the neutron sensor and to convert this analog signal into a digital one. The embedded system component performs multiple functions including neutron radiation measurement for high speed high precision neutron measurements, variable high voltage generator control, wired and wireless communications control, and data recording. Experiments using the proposed high speed high precision neutron measurement hardware shows that the hardware exhibits superior performance compared to that of conventional equipment with regard to measurement uncertainty, neutron measurement rate, accuracy, and neutron measurement range.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.597-600
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• 2010

Cold flow injection test was conducted to investigate the characteristics of cryogenic liquid nitrogen jet at sub to supercritical condition. Single jet injector element was installed in high pressure chamber to investigate the effect of ambient pressure around the jet, injector geometry and flow conditions. Experimental results showed obvious differences between jet characteristics under subcritical and supercritical condition. Effect of injector inlet shape also was investigated.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.4
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• pp.348-353
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• 2011

Characteristics of cryogenic single jet flow were investigated. Liquid nitrogen was injected into a high-pressure chamber and formed single jet. Ambient condition around jet was changed from subcritical to superctirical condition of nitrogen. Injector geometries also were changed. A shape of the jet and core diameter were measured by flow visualization technique, and core spreading angle was calculated. Flow instability was found at atmospheric pressure condition. As ambient pressure increased, core spreading angle was increased and maintained after certain pressure.

• Journal of Drive and Control
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• v.12 no.4
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• pp.48-53
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• 2015

This paper deals with the flow characteristics of a reed valve analyzed using computational dynamics(CFD) for optimal design. The seat sizes of the valve are modeled asØ6[mm] and Ø8[mm] to compare the flow characteristics. The inlet boundary condition is entered at 10[kPa], 15[kPa], 20[kPa], and 30[kPa] and the outlet boundary condition is set to the atmospheric pressure. The flow coefficient(C) and pressure loss coefficient(K) are calculated from the results of flow analysis. From the analysis results, it was confirmed that the flow coefficient of a reed valve having a seat size of Ø6[mm] is greater than that having a seat size of Ø8[mm], and the coefficient of pressure loss of a valve with a seat size of Ø6[mm] is lower than the Ø8[mm] size valve.

• Journal of Drive and Control
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• v.12 no.4
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• pp.1-7
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• 2015

In this study, a spiral valve which is used with a cryogenic linear expander and composed of plural plate coil shapes was examined. Generally, a spiral valve is well known for having excellent efficiency and low noise characteristics. In order to determine the movement characteristics and to investigate the limit of valve displacement, the stress variations according to the changes of operating pressure, displacement and workable temperature are discussed. From this examination, it is considered that the results of this study will significantly facilitate the design and development of a spiral valve for the cryogenic linear expander.

• Proceedings of the Korean Vacuum Society Conference
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• 2011.02a
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• pp.366-366
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• 2011

냉중성자원은 하나로 반사체탱크에 위치한 수직공에 설치되어 노심에서 발생하는 열중성자를 감속재인 액체수소층을 통과시켜 냉중성자를 생산하는 설비로 수소가를 충전하고 있는 수소계통이 있으며, 21K의 극저온 액체수소/기체수소 2상(ttwo-phase)을 유지하기 위해 외부에서 유입되는 열침입을 최소화하기 위해 진공계통이 설치되어 있다. 진공계통은 수조내기기 집합체(In-Pool Assembly : IPA)의 액체수소 열사이펀, 감속재 용기 등의 냉중성자원 극저온 부풀들의 단열을 위하여 진공용기 내부진공도를 공정진공도 이하로 유지하기 위한 계통으로 고진공펌프, 진공배기탱크 및 저진공펌프의 조합으로 두 개의 진공펌프시스템과 진공박스, 배기수집탱크 및 밸브박스를 포함한 연결배관으로 설계되었다. 저진공펌프를 이용하여 대기압에서 고진공펌프 작동압력까지 도달한 후 고진공펌프를 가동하여 공정진공도 이하의 진공도를 확보하고, 고진공펌프로부터 배기되는 배출가스는 고진공펌프 후단에 설치된 진공배기탱크에 포집되며, 필요 시 저진공펌프레 의하여 배기수집탱크로 배출된다. 진공펌프시스템은 진공용기 내부의 압력이 공정진동고 이하로 유지되도록 연속적으로 가동되어 진공단열이 가능하다. 본 논문은 감속재인 수소를 액화상태로 유지하며, 공정진공도 이하로 충분히 유지되어 운전되는 진공계통의 특성을 원자로 운전 주기별로 소개하고자 한다.

• Journal of the Korean Society of Propulsion Engineers
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• v.11 no.2
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• pp.9-17
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• 2007

The performance test of recirculation line in propellant feeding system was carried out. Liquid oxygen was used as cryogenic propellant and helium was used as recirculation promotion gas. Tests were done in cases at atmospheric pressure and at pressure of 4 barg in the ullage space of propellant tank. Liquid oxygen recirculation flowrate with helium injection flowrate and temperature distribution along the line were measured. There was appropriate helium injection flowrate for gas-lift recirculation system. Test data were used to make calculation program by test data correlation method. In this paper the procedure of calculation was presented and the results were compared to test data.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.178-183
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• 2004

Thermal stratification phenomena in the liquid oxygen tank of launch vehicle is caused by heat influx from ambient and non-equilibrium heat and mass transfer in the cryogenic tank. The thermal stratification study is needed for designing vent system, tank insulation, pump inlet. In this paper by investigating buoyancy driven boundary layer flow by side wall heating, one dimensional analysis of thermal stratification is peformed. thermal gradient is described with time.