• 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.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2007년도 춘계 학술대회논문집
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• pp.163-165
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• 2007

The authors have reviewed many mathematical thermal mode lings of bipropellant propulsion system in literatures to gather basic data for developing a computer program which analyses the performance of bipropellant propulsion system. In this paper COMS and its propulsion system is briefly introduced for understanding. The set of first order nonlinear differential equations is reviewed and considered as candidate equations for the program development.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2007년도 Proceedings of ISRS 2007
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• pp.41-44
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• 2007

Korea Aerospace Research Institute (KARI) has jointly developed a bipropellant propulsion system for Communication, Ocean and Meteorological Satellite (COMS) with EADS Astrium in UK. The technology relevant to a bipropellant propulsion system is quite new one in Korea, which is 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 COMS Chemical Propulsion System (CPS) is designed to perform both the orbital injection function, to take the spacecraft from transfer orbit to Geostationary Earth Orbit (GEO), and all on-station propulsive functions throughout the lifetime of the satellite. All station keeping manoeuvres are performed using the CPS. The design, manufacture and testing of COMS CPS are addressed in this paper. Feasibility of COMS CPS applicable to the other advanced mission is investigated as well.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2010년 춘계학술대회논문집
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• pp.487-490
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• 2010

A fluid transient analysis on the pipe network of bipropellant propulsion system is conducted through numerical parametric studies in which unsteady friction results are compared with quasi-steady friction results and also show the pressure drop results during the liquid apogee engine firing. The fluid transient analysis program has verified through comparing with the original Zielke model, the full and recursive convolution model and quasi-steady model as a reference. And the pressure drop program also has verified through comparing with results of the well-known program, EPANET2. The bipropellant propulsion system has two different fluids as fuel and oxidizer, and mostly they are hypergolic combination so that the valve opening and closing of the thrusters, that cause the pressure waves, shall take place simultaneously to get proper performance. The different physical properties of the fuel and oxidizer result in the different responsive to the same valve opening and closing. The response results may be helpful to know the characteristics of the bipropellant propulsion system and design it.

• 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.

• 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.

• 항공우주산업기술동향
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• 제6권1호
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• pp.82-89
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• 2008

본 논문에서는 정지궤도 인공위성용 이원추진시스템 부품 기술동향 조사 결과를 실었다. 이번 조사의 목적은 통신해양기상위성(COMS)의 화학추진시스템(CPS) 부품의 대체부품 목록을 작성하는 것이며, 따라서 조사기준은 대체부품이 통신해양기상위성 화학추진시스템 부품에 대한 적용 가능성 여부이다. 조사결과를 부품별로 정리하였고 간단한 부품설명과 부품제조회사의 설명도 포함하였다. 본 논문은 시장조사 착수 시 유용하게 사용될 수 있을 것으로 판단되고 이원추진제 추진시스템 부품의 이해도를 높이는데 사용될 수 있다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.243-246
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• 2008

This paper is to consider analytical thermodynamic modeling of bipropellant propulsion system. The objective of thermodynamic modeling is to predict thermodynamic conditions such as pressures, temperatures and densities in the pressurant tank and the propellant tank in which heat and mass transfer occur. In this paper also it shows analytic equations that calculate the evolution of ullage volume and interface areas. Since the ullage interface areas are time-varying,(the liquid propellant volume decreases as the rocket engine is firing; the change of ullage volume correspond to the change of liquid propellant volume) for a numerical convenience non-dimensionalized correlations are commonly used in most literatures with limitations; a few percentages of inherent error. The analytic equations are derived from analytic geometry, subsequently without inherent error. Those equations are important to calculate the heat transfer areas in the heat transfer equations. It presents the comparison result of both analytic equations and correlation method.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2011년도 제36회 춘계학술대회논문집
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• pp.207-210
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• 2011

천리안 이원추진시스템은 궤도전이를 위한 1기의 주엔진과 궤도상 운용에 주로 사용되는 14기의 추력기들로 구성된다. 추진계의 설계 및 해석은 국제협력을 통해 수행되었다. 시스템 조립 및 시험 후, 천리안위성은 프렌치 기아나의 쿠루우주센터로 이송되었으며, 성공적으로 발사되었다. 발사체에서 분리 후 추진시스템은 자동으로 초기화되었다. 이후 3번의 주엔진 분사가 성공적으로 수행되었으며 목표궤도 진입에 성공했다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년도 제30회 춘계학술대회논문집
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• pp.155-158
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• 2008

달탐사위성(궤도선) 1호는 2017년 착수 2020년 발사하고, 달탐사위성(착륙선) 2호는 2021년 착수 2025년 발사를 추진하게 되어 있다. 따라서 성공적인 임무 달성을 위해서는, 달탐사위성 추진시스템에 대한 기초 연구가 매우 중요한 시점이다. 본 연구에서는 달탐사위성에 적용 가능한 추진시스템에 대한 개념적인 타당성 및 비교 연구를 제시한다. 단일/이원/전기 추진시스템의 활용가능성을 외국의 사례와 비교/분석하고, 기술적인 장단점을 검토하여 달탐사위성 추진시스템으로 가능한 후보군을 제시한다.