• Fire Science and Engineering
• /
• v.15 no.4
• /
• pp.49-56
• /
• 2001

There have been the current controversy over effectiveness of the pressurized smoke control systems, which are installed within escape shaft to provide 'smoke-free' access for escaping peoples. Therefore, many effective measures were given in this paper by means of the production of a design guide for various types of escape routes used in domestic buildings. The solutions were established on basis of both an investigating current door closing device application in existing facilities and global standardization for pressurized smoke control system, especially in British Standard. Finally, the design guidance for open door air velocity with introduction to three door protection clauses was presented on the basis of consideration of the safety and economical factor,

• Proceedings of the Korean Geotechical Society Conference
• /
• 2010.09a
• /
• pp.109-116
• /
• 2010

일반적으로 사용되는 비탈면 보강공법은 중력식 혹은 가압식 네일링, 앵커 등이 있다. 이들 공법은 주입재 주입압력이 중력식무압 혹은 낮은 압력의 가압에 의한 것으로서, 실제로 단층파쇄대, 붕적층, 이완 및 절리 등이 발달한 지반에서는 일정압력의 가압주입에 의한 지반보강과 보강재에 의한 네일링 효과를 동시에 기대해야 한다. 본 사례에서는 가압주입의 효과를 높이기 위해 보강구간을 일정한 간격으로 나누고 구간별 별도의 주입펌프를 연결하여 보강길이 전구간을 동시에 주입하는 멀티패커시스템(MPS)공법을 소개하고자 한다.

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

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2004.10a
• /
• pp.79-82
• /
• 2004

Propellant feeding system is the system to satisfy propellant feeding requirements(mass flow rate, pressure, temperature) at engine inlet of launch vehicle. Propellant feeding test facility is being constructed for the development scheme of pressurization system, processing in tank, propellant piping system, and flow control system that are main technologies in order to develope propellant feeding system. This paper introduces the propellant feeding test facility being constructed in KARI.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.38 no.1
• /
• pp.73-79
• /
• 2010

Propellant tank pressurizing gas injector is used in the pressurization system of liquid propellant rocket to reduce incoming gas velocity and distribute the gas in the tank. Temperature distribution in the propellant tank ullage is varied according to the gas injector shape, and it has influence on the required pressurant gas and thermal phenomena in the tank. In this paper, diffuser type gas injector was studied to make the ullage have stratified temperature distribution. Injected gas flow at the outlet of prototype diffuser was visulized using particle image velocimetry method and it was compared with the results of calculation. Calculation was well agreed with measurement and was used as an inlet condition of propellant tank ullage calculation.

• Bulletin of the Korean Space Science Society
• /
• 2003.10a
• /
• pp.90-90
• /
• 2003

한국항공우주연구원은 액체추진기관 시스템을 이용한 3단형과학로켓(이하 KSR-III)을 국내 최초로 개발하여 비행시험을 수행하였다. 액체추진기관 로켓의 비행시험을 위해서는 이전의 고체 추진기관을 이용한 과학로켓 1, 2와는 달리 비행시험 조건에 부합하게 액체추진제 및 가압제 등을 공급하는 지상설비가 필요하다. 이에 한국항공우주연구원은 독자적으로 비행시험에 필요한 제반 설비를 갖춘 발사장을 구축하였다. KSR-III는 압축 헬륨가스(GHe)를 이용하여 연료(Jet A-1)와 산화제(LOx)를 가압하여 추력을 얻는 액체추진기관 시스템이다. 따라서 발사장에서의 지상공급설비는 유공압 설비와 발사시나리오에 따라 해당 부품을 제어하고 자료를 저장하는 제어/계측 설비 및 기타설비들로 구성되어 있다. 지상공급설비 중 유공압 설비는 LOx의 저장 및 기체 내 산화제 탱크의 충전을 위한 산화제 공급설비, Jet A-1의 저장 및 기체 내 연료 탱크의 충전을 위한 연료 공급 설비, 지상설비용 밸브구동 및 기체 내부 퍼지 등에 필요한 질소($N_2$)를 저장/공급하는 설비, 기체내부 밸브 구동 및 가압제로 사용되는 기체헬륨(He)을 저장/공급하는 설비들로 구성되어 있다. 이러한 구축된 공급설비는 기능시험, 연계시험 등의 각종 입증시험을 통해 그 성능을 검증한 후 단인증모델(SQTM)을 이용하여 발사 시나리오에 따른 추진제 공급능력을 입증한 후 KSR-III의 비행시험을 성공적으로 수행하였다. 수행된 연구결과는 향후 건설되어질 우주센터내의 발사장 기반설비 설계의 기초 자료로 활용할 수 있을 것이다.

• Aerospace Engineering and Technology
• /
• v.4 no.2
• /
• pp.94-100
• /
• 2005

The geostationary satellite propulsion system has thermistors which can measure liquid propellant temperature at tanks, pipes and etc. In the satellite propulsion system with several tanks, the propellant in the tanks is moved by temperature change and this temperature pattern is constant. In this paper, the temperature change pattern of KOREASAT 1 propulsion system is compared and the prediction study of pressurant inflow using temperature change of geostationary satellite propulsion system is described.

• Journal of Energy Engineering
• /
• v.12 no.1
• /
• pp.1-10
• /
• 2003

Pressurized fluidized bed combustion unit is operated at pressures of 1~1.5 MPa with combustion temperatures of 850~87$0^{\circ}C$. The pressurized coal combustion system heats steam, in conventional heat transfer tubing, and produces a hot gas supplied to a gas turbine. Gas cleaning is a vital aspect of the system, as is the ability of the turbine to cope with some residual solids. The need to pressurize the feed coal, limestone and combustion air, and to depressurize the flue gases and the ash removal system introduces some significant operating complications. The proportion of power coming from the steam : gas turbines is approximately 80:20%. Pressurized fluidized bed combustion and generation by the combined cycle route involves unique control considerations, as the combustor and gas turbine have to be properly matched through the whole operating range. The gas turbines are rather special, in that the maximum gas temperature available from the FBC is limited by ash fusion characteristics. As no ash softening should take place, the maximum gas temperature is around 90$0^{\circ}C$. As a result a high pressure ratio gas turbine with compression intercooling is used. This is to offset the effects of the relatively low temperature at the turbine inlet.

• Aerospace Engineering and Technology
• /
• v.1 no.1
• /
• pp.55-64
• /
• 2002

A conceptual design of propulsion system for a geosynchronous communication satellite with 12 years design life is presented in this paper. Propellant mass budget for the design life is calculated using total velocity increment (ΔV) flowed-down from mission requirement analysis. Sizes of the fuel and oxidizer tank are derived based on the calculated propellant mass budget, and mass of the pressurant as well as the size and pressure of pressurant tank are calculated too. Thruster positioning, number of rocket engines, and position of tank are determined through Trade-Off Study with Structure & Mechanical Subsystem. Propulsion system configuration and its schematics are presented finally.

• 한국신재생에너지학회:학술대회논문집
• /
• 2006.06a
• /
• pp.73-76
• /
• 2006

본 연구에서는 독일 율리히 연구소에서 도입된 면적 200mm*200mm의 연료극 지지체 평판형 SOFC 셀 및 금속 분리판 40장을 적층하여 5kW급 SOFC 스택을 제작하고 연속운전을 수행하여 운전특성을 분석했다. 본 연구를 통해 도입된 5kW급 SOFC 스택은 외국에서 시도된 적이 없는 평판형 SOFC스택의 가압운전을 시도해 보는 것으로서, 스택의 임계압력 특성을 확인하고, 이를 바탕으로 가스터빈-연료전지 하이브리드 시스템에서의 SOFC 스택 가압 운전기술을 확보하는 것이다 이러한 목적을 위해 본 연구에서는 상압형 5kW급 SOFC 스택 운전시스템에 대한 구성과 설계, 전반적인 운전 특성평가 (40셀 스택 운전 열 사이클 시험 연료 전환 $(H_2{\rightarrow}pre-reformed\;gas)$, 1200시간 연속운전 등)가 이뤄졌다.