• Title/Summary/Keyword: 화학추진시스템

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Types and Characteristics of Chemical Propulsion Systems for Repersentative Korean Satellites (국내의 대표적 인공위성 화학추진시스템의 형식 및 특성)

  • Han, Cho-Young
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.35 no.8
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    • pp.747-752
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    • 2007
  • Domestic satellite development programme is generally classified into two categories: COMS as GEO satellite and KOMPSAT as LEO one. Each satellite has the on-board propulsion system fulfilling its own mission requirements. The COMS propulsion system provides the thrust and torque required for the insertion into GEO, attitude and orbit control/adjustment of spacecraft. It is the well-known Chemical Propulsion System(CPS) using bipropellants. On the other hand, the monopropellant propulsion system is employed in KOMPSAT, and its main role is on-station attitude control excluding the orbit transfer function. In this study, these two representative propulsion systems are compared and analysed as well, in terms of essential differences and important characteristics.

Feasibility Study of Chemical Propulsion System for Moon Explorer (화학추진시스템의 달탐사위성 적용 가능성 연구)

  • Han, Cho-Young;Kim, Bang-Yeop
    • Journal of the Korean Society of Propulsion Engineers
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    • v.13 no.4
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    • pp.22-29
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    • 2009
  • Development of Moon Explorer-1 (orbiter) is supposed to be commenced in 2017 and launched in 2020. In case of Moon Explorer-2 (lander), it would be slated to start in 2021 and launch in 2025. In this paper conceptual feasibility studies are conducted for the propulsion system applicable to a Moon Explorer. In the first place the availability of monopropellant/bipropellant/electric propulsion system is examined with domestic as well as overseas precedents. Secondly ${\Delta}V$ is estimated by the mission analysis and the propellant budget is calculated accordingly. Subsequently feasibility of a chemical propulsion system for a Moon Explorer is evaluated.

A Survey of the Current Components of Bipropellant Propulsion System for Geosynchronous Satellites (정지궤도 인공위성용 이원추진시스템 부품 조사)

  • Chae, Jong-Won
    • Current Industrial and Technological Trends in Aerospace
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    • v.6 no.1
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    • pp.82-89
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    • 2008
  • In this paper a survey was conducted to find out the current components of bipropellant propulsion system for geosynchronous satellites. The purpose of the survey is to list up the alternative components corresponding to the components of chemical propulsion system (CPS) of the communication, ocean, and meteorological satellite (COMS), so that the criterion of survey is whether the alternative components can be applicable to COMS CPS or not. The survey results are described in component-by-component way and the short descriptions of each component and its companies are added. This paper can be useful for beginning a market survey and have a good understanding of the components of bipropellant propulsion system.

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Technical Heritage of UK Chemical Propulsion Systems and COMS Bipropellant Propulsion System (영국산 화학추진시스템의 기술이력과 통신해양기상위성 이원추진제 추진시스템)

  • HAN, Cho Young
    • Journal of Aerospace System Engineering
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    • v.2 no.1
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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.

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Development of Chollian Bipropellant Propulsion System (천리안위성 이원추진시스템 개발)

  • Han, Cho-Young;Lim, Cheol-Ho
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.19 no.1
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    • pp.94-100
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    • 2011
  • This paper gives a brief overview of the COMS CPS development process from start to finish. The manufacturing techniques used for CPS were founded on established generic processes that have been developed and proven on previous satellite programs, and have used the expertise and facilities in the framework of international collaboration. Manufacture and testing of the CPS were successfully accomplished, and COMS CPS demonstrated good performance in the launch phase.

A Study on the Application of a Fully Electric Propulsion System for Geostationary Missions (정지궤도위성의 완전 전기추진시스템 적용방안 연구)

  • Choi, Jaedong;Park, Bongkyu
    • Journal of Aerospace System Engineering
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    • v.16 no.5
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    • pp.26-34
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    • 2022
  • The propulsion system of geostationary orbiting satellites is typically used to raise the orbit into a transfer orbit, maintain the orbital position in the south/north, east/west direction in regular operation, and accumulate momentum in the south/north and east/west direction. Recently, when an electric propulsion system is used in a geostationary orbit satellite, the payload capacity can be increased by about 40% compared to a chemical propulsion system. However, despite these advantages, using an electric propulsion system has several limitations that should apply to all geostationary orbiting satellites. This paper discusses the operational constraints to consider when developing an indigenous geostationary satellite using a fully electric propulsion, radiation exposure, and control mechanism design due to unit displacement and floating ground-design. A high-voltage control unit for electric drives were analyzed.

Geostationary Satellite Launch and Early Operations (정지궤도위성 발사 및 발사후 초기운용)

  • Han, Cho-Young;Chae, Jong-Won;Kim, Su-Kyum;Won, Su-Hee
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.66-68
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    • 2011
  • Chollian is a geostationary satellite, and its bipropellant propulsion system is mainly composed of one main engine for orbit transfer and fourteen thrusters for on-station operations. The Chollian was launched successfully at Kourou Space Center in French Guiana. After it separated from the launcher, the propulsion system was initialised automatically. Then three times of main engine firing were successfully performed, and the target obit insertion was accomplished. This paper details the major CPS events during LEOP phase for the Chollian satellite.

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진보형 우주 추진시스템 개발 현황

  • Hong, Yong-Sik
    • Defense and Technology
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    • no.1 s.131
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    • pp.6-13
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    • 1990
  • 지상 수백km정도의 고도밖에는 왕복할수 없는 현재의 제한된 우주수송능력은 비교적 가까운 우주공간에서 화물을 운반하고 작업을 하는 궤도기동체(OMV)와 우주공간의 어느 곳, 어떤 궤도에도 왕래하는 우주전이비행체(STV)를 필요로 하고 있다. 이들은 재래식 화학로켓을 개량한 진보형 추진시스템을 1차적으로 활용하는 방향으로 개발이 진행되고 있다. 우주와 지구사이를 비교적 경제적으로 용이하게 왕래하고 우주공간에서 자유로이 기동작동하는 추진시스템이 완성되면, 인류의 우주개척은 본궤도에 오르게 되며, 생활권을 우주로 옮기는 날도 가까워질 것이다

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Numerical Study of Chemical Reaction for Liquid Rocket Propellant Using Equilibrium Constant (평형상수를 이용한 액체로켓 추진제의 화학반응 수치연구)

  • Jang, Yo Han;Lee, Kyun Ho
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.44 no.4
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    • pp.333-342
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    • 2016
  • Liquid rocket propulsion is a system that produces required thrust for satellites and space launch vehicles by using chemical reactions of a liquid fuel and a liquid oxidizer. Monomethylhydrazine/dinitrogen tetroxide, liquid hydrogen/liquid oxygen and RP-1/liquid oxygen are typical combinations of liquid propellants commonly used for the liquid rocket propulsion system. The objective of the present study is to investigate useful design and performance data of liquid rocket engine by conducting a numerical analysis of thermochemical reactions of liquid rocket propellants. For this, final products and chemical compositions of three liquid propellant combinations are calculated using equilibrium constants of major elementary equilibrium reactions when reactants remain in chemical equilibrium state after combustion process. In addition, flame temperature and specific impulse are estimated.