• Aerospace Engineering and Technology
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• v.2 no.2
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• pp.18-24
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• 2003

Center of buoyancy moves along with pitch attitude variation, which causes Helium gas inclination. In this paper, movement of center of buoyancy and corresponding variation of longitudinal static stability were observed. The effect of separating wall, which is placed in the envelop to minimize movement of center of buoyancy was also investigated. Installation of separating wall was proved to be essential for current design, because movement of center of buoyancy aggravates longitudinal static stability. Investigation of longitudinal static stability for various speeds reveals a 50m airship is statically stable only in a low speed regime.

• Transactions of the Korean Society of Pressure Vessels and Piping
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• v.12 no.1
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• pp.85-92
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• 2016

The operating temperature of VHTR components is much higher than that of conventional PWR due to high core outlet temperature of VHTR. Material requirements and technical issues of VHTR reactor components which are mainly dominated by high temperature service condition were discussed. The codification effort for high temperature material and design methodology are explained. The design class for VHTR components are classified as class A or B according to the recent ASME high temperature reactor design code. A separation of thermal boundary and pressure boundary is used for VHTR components as an elevated design solution. Key design characteristics for reactor pressure vessel, control rod, reactor internals, graphite reflector, circulator and intermediate heat exchanger were analysed. Thermo-mechanical analysis of the process heat exchanger, which was manufactured for test, is presented as an analysis example.

• The Bulletin of The Korean Astronomical Society
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• v.42 no.1
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• pp.29.2-29.2
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• 2017

초기 우주의 구상성단과 같은 소규모 은하 빌딩블럭이 은하의 형성에 미치는 영향을 이해하기 위하여 우리는 완전히 새로운 개념의 화학적 진화모형을 구축하였다. 최근의 이론적 진보를 바탕으로 우리의 모델에서는 이전 모델과 달리 초신성의 폭발과 분출물이 원시 구상성단 내 잔존 가스에 아무런 영향을 끼치지 못하고 대부분 빠져나간다. 이 경우 화학적 진화는 질량이 큰 별의 윈드와 점근거성계열성의 분출물에 의해 좌우된다. 놀랍게도 우리의 모델은 오랜 난제인 구상성단 내 Na-Oxygen anticorrelation 및 다중항성종족의 기원을 자연스럽게 설명하면서 동시에 Lee, Joo, & Chung (2015) 이 최근 주장한 것처럼 은하벌지에 헬륨 함량이 매우 높은 항성이 존재할 것으로 예측한다. 이 결과는 은하의 헤일로와 벌지 형성에 매우 중요한 단서를 제공한다.

• Journal of the KSME
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• v.30 no.6
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• pp.548-554
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• 1990

대체에너지 기관으로서 요구되는 조건을 갖춘 스터링엔진의 이해를 돕기 위하여 기본원리, 개 발현황, 개발상 문제점 등의 기본사항을 소개하였다. 내연기관과는 달리 외연기관인 스터링엔 진은 작동유체가 밀폐공간 내에서 고. 저온 양 영역을 이동하면서 압력차를 발생시켜 일을 형성 하는 과정을 밟기 때문에 고온. 고압일수록 높은 출력이 예상되며, 전열성능과 작동저항면에서 수소나 헬륨과 같은 저분자량의 가스가 작동체로 채택되기 때문에 작동유체의 누기(leakage) 및 크랑크실의 냉각 윤활유의 작동공간으로의 누유 등은 스터링엔진의 출력 저하에 가장 큰 요인 으로 작용한다. 마찰 등 기계적 손실의 저감기술, 속도제어기술, 용도에 따른 엔진 형식 설계 기술, 구성부품 성능향상을 위한 요소기술 등의 개발이 중요한 과제가 되고 있으며, 이상 소개한 내용이 관심있는 많은 분들의 스터링엔진 연구나 이해에 도움이 될 수 있기를 바란다.

• Proceedings of the KIEE Conference
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• 2006.10a
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• pp.174-175
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• 2006

본 논문에서는 상압에서 RF파워에 의해 플라즈마 바늘(plasma needle) 에서 발생된 마이크로 플라즈마를 이용한 바이오 실험에 대한 결과를 제시한다. 마이크로 플라즈마는 그 크기가 수 mm에서 수백 마이크로미터 크기의 플라즈마를 지칭하는 단어로써 다양한 전원에 의해 구동된다. 바이오 응용을 위한 저온 플라즈마는 세포 활동을 저해하지 않도록 온도가 적절히 제어되어져야만 한다. 본 논문에서는 플라즈마 온도를 40도 이하로 조절하도록 외부 인가 파워를 조절하였다. 플라즈마의 특성을 알기 위해서 기초적인 가스 스펙트럼에 대한 조사도 수행하여 아르곤 (Ar) 과 헬륨 (He) 의 결과를 저압의 결과와 비교하였다. 또한 작은 크기 때문에 플라즈마의 관찰이 용이하지 않으므로 모델링을 통한 시뮬레이션으로 플라즈마 거동 및 분포를 계산하였다. 시뮬레이션을 통하여 플라즈마에 대한 정보 및 향후 시스템 개선에 사용할 수 있다. 마이크로 플라즈마를 이용하여 수행한 기초적인 바이오 실험의 예로써 흑색종 (피부암세포, meianoma)에 대한 플라즈마 및 전기장의 효과를 제시한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1171-1175
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• 2017

Cryogenic helium gas is used as the pressurant for the oxidizer pressurization of DR(Damper Receiver) sphere in the PSD(Pogo Suppression Device) system and liquid oxygen is used as the oxidizer for the propellant in Korea Space Launch Vehicle-II. The helium gas is stored in pressurant cylinders inside the cryogenic liquid oxygen tank and liquid oxygen is stored in the oxidizer tank. In this study, the performance test of PSD liquid oxygen drain valve for KSLV-II was considered.

• Journal of Navigation and Port Research
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• v.44 no.4
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• pp.283-290
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• 2020

BOG (Boil Off Gas) generation is unavoidable in the liquefied hydrogen carrier, and proper measures are necessary to prevent pressure problems inside the cargo tank. The BOG can be used as propulsion fuel for ships, and the remaining parts used for propulsion must be effectively managed, such as in the form of reliquefying or burning. This study proposes an BOG reliquefaction system optimized for a 160,000 m3 liquefied hydrogen carrier with a hydrogen propulsion system. The system comprises a hydrogen compression and helium refrigerant section, and increases the efficiency by effectively using the cold energy of the BOG discharged from the cargo tank. In this study, the system was evaluated through the exergy efficiency and SEC (Specific Energy Consumption) analysis according to the rate of the reliquefaction of the BOG while the hydrogen BOG with a supply temperature of -220℃ entered the reliquefaction system. As a result, it showed SEC of 4.11 kWh/kgLH2 and exergy efficiency of 60.1% at the rate of reliquefaction of 20%. And the parametric study of the effects of varying the hydrogen compression pressure, inlet temperature of the hydrogen expander, and the feed hydrogen temperature was conducted.

• Journal of Navigation and Port Research
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• v.48 no.4
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• pp.274-283
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• 2024

Climate change is currently one of the most pressing environmental issues, primarily caused by carbon emissions from fossil fuel usage. As a result, alternative fuels that effectively reduce carbon emissions are garnering more attention. Among these alternatives, hydrogen has numerous advantages, such as its ability for large-scale storage and transport. However, it is crucial to prioritize safety measures, particularly in facilities that handle hydrogen, due to its highly flammable and fast-spreading nature. This study aims to compare and analyze the placement of supply and exhaust vents to efficiently release hydrogen in the event of a leak in an enclosed space. The experiments involved six different scenarios, each with various combinations of supply and exhaust vents. To ensure the experimental process's safety, helium, which shares similar physical properties with hydrogen, was used to analyze the internal oxygen concentration during ventilation system operations. The results revealed that among the six scenarios, Case 2, which employed a lower side supply vent and an upper side exhaust vent, exhibited the shortest ventilation time of 4 minutes and 30 seconds. Additionally, the decrease rate in oxygen concentration was examined in the upper, middle, and lower areas. Ventilation utilizing an upper surface supply vent and two exhaust vents on the upper surface and upper side (Case 6), showed lower oxygen concentration values in the upper area, while Case 2 yielded lower values in the middle and lower areas. Therefore, it is crucial to select an appropriate supply and exhaust vent configuration considering the space's characteristics and usage environment.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.58-64
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• 2007

Propellant pressurization system in liquid rocket propulsion system plays a role supplying pressurant gas at a controlled pressure into the ullage space of propellant tanks. The most important design parameter for such propellant pressurization system is the temperature of pressurant gas fed from pressurant tank, which is placed inside of cryogenic propellant tank. Such pressurant is gaseous state, of which density is very sensitive to the temperature of pressurant. Previous investigation dealt with thermal correlation of pressurant and external fluid at room temperature. This study investigates the temperature variation of cryogenic pressurant (GHe) at the time when the pressurant is coming out of pressurant tank, which is submerged in a liquid oxygen, experimentally as well as numerically.

• Journal of the Korean Society of Propulsion Engineers
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• v.11 no.2
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• pp.54-61
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• 2007

Propellant pressurization system in liquid rocket propulsion system plays a role supplying pressurant gas at a controlled pressure into the ullage space of propellant tanks. The most important design parameter for such propellant pressurization system is the temperature of pressurant gas fed from pressurant tank. Such pressurant is gaseous state, of which density is very sensitive to the temperature of pressurant. Generally for the propulsion system, which requires high thrust and is consisted of cryogenic propellant the pressurant is stored at high density and high pressure to reduce the weight of pressurant tanks, which are placed inside of cryogenic propellant tank. That is called cryogenic storage pressurization system. This study investigates the temperature variation of pressurant at the time when the pressurant is coming out of pressurant tank experimentally as well as numerically. Fluids used in this study are air and liquid oxygen as outer fluid and gaseous nitrogen and gaseous helium as pressurant respectively.