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전형열(Hyoung Yoll Jun),김정훈(Jung Hoon Kim),박종석(Jong Seok Park),박근주(Keun Joo Park) 한국항공우주연구원 2011 항공우주기술 Vol.10 No.2
인공위성의 효율적인 열제어를 위해 알루미늄으로 만들어진 하니콤 패널과 OSR로 구성된 방열판을 사용한다. 또한 추가적으로 발열량이 많은 부품의 경우, 알루미늄으로 만들어진 더블러와 히트파이프 등을 이용하여 열제어를 수행한다. 최근 위성 전장 부품의 발열량의 증가로 정해진 위성의 크기, 발사 중량 및 비용으로 더 많은 열을 외부로 효율적으로 방출할 수 있는 방열 능력향상에 대한 필요성으로 새로운 열제어 물질에 대한 연구가 진행 중이다. 특히, 탄소 복합재는 일반적으로 열전도가 매우 높고, 가볍고, 기계적 강성에 좋은 특성이 있어 차세대 열제어를 위한 물질로 많은 연구가 진행되고 있다. 본 논문에서는 차세대 탄소 복합재인, APG(Annealed Pyrolytic Graphite)와 탄소-탄소 복합재(carbon-carbon composites)를 이용하여 통신패널의 열제어를 수행하는 경우와 기존의 열제어 방식과의 차이를 수치적으로 비교하였다. Thermal control of satellite is mainly based on passive ways, such as the radiator made of aluminum honeycomb core with aluminum skins and OSR (Optical Solar Reflector). Additionally, for the thermal control of high dissipation unit, the aluminum doubler and heat pipe are utilized. Recently, efforts to find advanced thermal materials have been carried out to enhance heat rejection capability without increasing satellite size, weight and cost. This paper handles the carbon composites have high thermal conductivity with light weigh and have been considered as future thermal control materials to replace aluminum based radiator and doubler. Thermal analysis of satellite panel using APG(Annealed Pyrolytic Graphite) and carbon-carbon composites were performed and temperature contours were compared with the conventional thermal control methods.
히트 파이프가 장착된 정지궤도 위성 패널 열해석 프로그램 개발
전형열(Hyoung Yoll Jun),김정훈(Jung-Hoon Kim),한조영(Cho Young Han),채종원(Jong Won Chae) 한국전산유체공학회 2010 한국전산유체공학회 학술대회논문집 Vol.2010 No.5
The north and south panel of a geostationary satellite are used for radiator panels to reject internal heat dissipation of electronics units and utilize several heat pipe networks to control the temperatures of units and the satellite within proper ranges. The design of these panels is very important and essential at the conceptual design and preliminary design stage, so several thousands of nodes or more are utilized in order to perform thermal analysis of panel. Generating a large number of nodes(meshes) of the panel takes time and is tedious work because the mesh can be easily changed and updated by locations of units and heat pipes. Also the detailed panel model can not be integrated into spacecraft thermal model due to its node size and limitation of commercial satellite thermal analysis program. Thus development of a program was required in order to generate detailed panel model, to perform thermal analysis and to make a reduced panel model for the integration to the satellite thermal model. This paper describes the development and the verification of panel thermal analysis program with ist main modules and its main functions.
정지궤도복합위성(GK2A)의 열진공 시험 및 시험 예측에 관한 연구
전형열(Jun, Hyoung Yoll),김정훈(Kim, Jung-Hoon),현범석(Hyun, Bum-Seok),박근주(Park, Keun Joo) 한국항공우주연구원 2018 항공우주산업기술동향 Vol.16 No.1
정지궤도복합위성(GK2A)는 한국항공우주항우연이 독자적으로 개발하는 3.5톤급의 국내 최초의 정지궤도 위성이다. GK2A는 기상관측을 주 임무로 수행하며, 2010년 발사되어 현재 운용중인 천리안 위성을 대체하기 위해 개발 중이다. 2018년 하반기에 Ariane 5호 발사체를 이용하여 발사될 목표로 현재 조립 및 환경시험을 수행 중에 있다. 2018년 5월 8일, 열진공 시험을 완료하였으며, 이 열진공 시험은 열제어 설계 검증, 열제어 하드웨어 작동 검증, 열해석 모델 보정 및 우주궤도환경하에서 위성전반에 대한 기능 시험을 주목적으로 한다. GK2A 위성의 열진공 시험은 한국항공우주연구원에서 자체 개발한 대형 열진공 챔버를 이용하여 수행되었다. 또한 정지궤도에서의 외부 열유입량을 모사하기 위해, 위성의 남쪽과 북쪽 방열판위에 각각 독립된 액화질소 및 질소가스를 이용하는 히팅플레이트를 장착하였다. 본 논문에서는 정지궤도복합위성의 열진공 시험 방법, 열진공 시험 예측을 위한 모델링, 열진공 시험 예측 및 실제 열진공 시험에 관해 다루고자 한다. KARI is developing independently GEO-KOMPSAT-2A(GK2A), which is the first 3.5 ton class geostationary satellite in Korea. The mission of GK2A is the meteorological observation and it will take over the meteorological mission of COMS launched at 2010. GK2A has been performing the environmental tests and will be launched the end of this year by Ariane 5 launcher. The thermal vacuum test was conducted until 8th May 2018 to validate thermal control design, to validate satellite functions under the simulated space environments and to obtain data for thermal model correlation. The thermal vacuum test was carried out by using the large thermal vacuum chamber developed by KARI. Additionally, the radiating(or heating) plates were installed on the front of the north and south panel of GK2A in order to simulate the external solar flux at the geostationary orbit. The temperatures of the plates were controlled by circulating GN2 and LN2. This paper describes the thermal vacuum test method, the thermal modelling, the test prediction and the test results of GK2A.
전형열(Hyoung Yoll Jun),김정훈(Jung-Hoon Kim),김성훈(Sung-Hoon Kim),양군호(Koon Ho Yang) 한국전산유체공학회 2008 한국전산유체공학회지 Vol.13 No.2
COMS (Communication, Ocean and Meteorological Satellite) is a geostationary satellite and has been developing by KARl for communication, ocean and meteorological observations. It will be launched by ARIANE 5. Ka-band components are installed on South panel, where single solar array wing is mounted. Radiators, embedded heat pipes, external heat pipe, insulation blankets and heaters are utilized for the thermal control of the satellite. The Ka-band payload section is divided several areas based on unit operating temperature in order to optimize radiator area and maximize heat rejection capability. Other equipment for sensors and bus are installed on North panel. The ocean and meteorological sensors are installed on optical benches on the top floor to decouple thermally from the satellite. During the transfer orbit operation, satellite will be under severe thermal environments due to low dissipation of components, satellite attitudes and LAE(Liquid Apogee Engine) firing. This paper presents temperature and heater power prediction and validation of thermal control design during transfer orbit operation.
SMA(SHAPE MEMORY ALLOY) ACTUATOR USING FORCED CONVECTION
전형열(Hyoung Yoll Jun),김정훈(Jung-Hoon Kim),박응식(Eung Sik Park) 한국전산유체공학회 2005 한국전산유체공학회지 Vol.10 No.2
This work discusses the numerical analysis, the design and experimental test of the SMA actuator along with its capabilities and limitations. Convective heating and cooling using water actuate the SMA(Shape memory alloy) element of the actuator. The fuel such as propane, having a high energy density, is used as the energy source for the SMA actuator in order to increase power and energy density of the system, and thus in order to obviate the need for electrical power supplies such as batteries. The system is composed of a pump, valves, bellows, a heater(burner), control unit and a displacement amplification device. The experimental test of the SMA actuator system results in 150 MPa stress(force : 1560 N) with 3 % strain and 0.5 Hz actuation frequency. The actuation frequency is compared with the prediction obtained from numerical analysis. For the designed SMA actuator system, the results of numerical analysis were utilized in determining design parameters and operating conditions.