• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.399-402
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• 2008

It is well known that helium saturated propellants significantly effects the dynamics of propulsion system, thruster cross coupling, water hammer and thruster performance. Especially for the propulsion systems, which have multiple high thrust engines, such as HTV(H-II transfer vehicle), the effect is more important. Therefore full-saturated propellants should be used at ground tests of HTV propulsion system and evaluate its effects. HTV is an advanced space vehicle being developed by Japan Aerospace Exploration Agency(JAXA) to enhance cargo delivery capabilities of the fleet of vehicles visiting the International Space Station(ISS). This paper presents an overview of the successful effort of the testing with saturated propellants(MMH/MON3) for HTV propulsion system during the ground firing tests.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.480-485
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• 2008

In this study, two types of ramjet intake were designed for the flight condition of Mach number 2 and 5 and numerical analysis was performed. In order to widen the flight envelope range(Mach number $2{\sim}6$), movable intake concept was applied. The central body was designed so that the capture area ratio which is one of most important factors of ramjet intake design could be adjusted. And various types of cowl and movable insert part of shell were designed in order to control throat area which could increase total pressure recovery. The numerical results showed that the designed ramjet intake could be applied in various flights Mach number.

• 한국가스학회지
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• 제10권4호
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• pp.41-46
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• 2006

본 연구를 통해 액체로켓 추진기관의 운용 및 시험을 수행하는데 있어 LOX 시스템 내의 불순물로 인해 발생할 수 있는 문제점들에 대한 연구를 수행하였다. 특히 LOX 시스템 내부에 축적되는 오염물질과 그것들의 시스템 내부이동 및 이에 따른 사고발생 확률에 관하여 심도 있는 연구를 하였다. 추진기관의 산화제 누출로 일어날 수 있는 사고의 확률을 감소시키기 위한 시스템 운영에 대한 몇 가지 방법들을 연구하였고, LOX 시스템 내 오염물질 축적으로 인한 사고발생 저감방법에 대한 연구를 수행하였다. 본 연구를 통해 얻은 실험식의 일반적인 원리는 액체 추진기관의 LOX 시스템에 적용할 수 있을 뿐 아니라, 기타 추진제에도 적용할 수 있다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2003년도 The Fifth Asian Computational Fluid Dynamics Conference
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• pp.248-250
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• 2003

Thermal analysis is performed to protect the propulsion system of low-earth-orbit earth observation satellite from unwanted thermal disaster like propellant freezing. To implement thermal design adequately, heater powers for the propulsion system estimated through the thermal analysis are decided. Based on those values anticipated herein, the average power for propulsion system becomes 22.02 watts when the only one redundant catalyst bed heater is turned on. When for the preparation of thruster firing, 25.93 watts of the average power is required. All heaters selected for propulsion components operate to prevent propellant freezing meeting the thermal requirements for the propulsion system with the worst-case average voltage, i.e. 25 volts.

• 시스템엔지니어링학술지
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• 제1권1호
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• pp.61-66
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• 2005

In executing the large scale national project, such as development of space launch vehicle, it is most important to guarantee the technological reliability. However the reliability analysis of launch vehicle is different from other mass product goods because of the limitation of budget and number of tests. In this study, the reliability analysis technique of the propulsion system, which is one of the major sub-systems of launch vehicle is illustrated and applied to the liquid rocket engine of KSR-III.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2004년도 한국우주과학회보 제13권2호
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• pp.341-343
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• 2004

In executing the large scale national project, such as development of space launch vehicle, it is most important to guarantee the technological reliability. However the reliability analysis of launch vehicle is different from other mass product goods because of the limitation of budget and number of tests. In this study, the reliability analysis technique of the propulsion system, which is one of the major sub-systems of launch vehicle is illustrated and applied to the liquid rocket engine of KSR-III.

• 항공우주시스템공학회지
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• 제2권1호
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• pp.28-36
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• 2008

The technology relevant to a bipropellant propulsion system is quite new one in Korea, which is being transferred for the first time, with development of COMS propulsion system. It hasn't ever attempted before, and hasn't got any general idea itself as well, in Korea. The technical heritage of UK bipropellant propulsion pertinent to COMS propulsion system is scrutinised mainly. Furthermore the strong possibility of COMS CPS for the moon explorer mission is rationalised on the basis of the history of successful predecessors.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.307-310
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• 2008

In the framework of COMS(Communication, Ocean and Meteorological Satellite) programme, the first bipropellant propulsion system for GEO satellite has been developed successfully. So far Korea has its own experience of development of a monopropellant propulsion system for LEO satellites, i.e., KOMPSAT's. Other types of propulsion systems for a satellite, such as cold gas and electric propulsion etc., are being developed somewhere in Korea, however they are not commercialised yet, apart from those two systems aforementioned. This paper mainly focused on the design of the Chemical Propulsion System(CPS) for the COMS, joint scientific and communications satellite. It includes descriptions of the general system design and a summary of the supporting analysis performed to verify suitability for space flight. Essentially it provides an overview and guide to the various engineering rationale generated in support of the COMS CPS design activities. The manufacture and subsequent testing of COMS CPS are briefly discussed. Feasibility of COMS CPS to an interplanetary mission is proposed as well.

• 항공우주시스템공학회지
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• 제2권1호
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• pp.37-45
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• 2008

KARI has jointly developed COMS bipropellant propulsion system with EADS Astrium, UK. It is well known at the moment about American or even German efforts for space development and space propulsion activities. On the contrary UK's capability for space development hasn't been recognised well in Korea. The major space activities relevant to the development of chemical and electric propulsion systems in UK, in reference to our space propulsion programme are addressed in detail. In addition the collaboration in prospect between two countries is proposed.

• 한국추진공학회지
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• 제26권3호
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• pp.1-9
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• 2022

본 연구에서 대상으로 삼은 비행체는 4~5인승급 수직이착륙기이며, 해당 비행체용 추진시스템은 가스터빈엔진과 배터리팩을 주 전력원으로 사용하여 다수의 모터가 필요로 하는 요구전력을 공급하는 분산 하이브리드 추진시스템이다. 본 연구에서는 기본설계 결과를 바탕으로 MATLAB/Simulink 프로그램을 사용하여 하이브리드 추진시스템용 설계/해석 플랫폼을 개발하였다. 시뮬레이션 해석을 통해 비행 시나리오에 따른 각 전력원별 출력 거동 및 운용 범위를 확인하였고, 이를 통해 기본설계 결과의 실현가능성을 확인하였다.