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황창환(Chang Hwan Hwang),백승욱(Seung Wook Baek),한조영(Cho Young Han),김수겸(Su Kyum Kim),전형열(Hyung Yeol Jeon) 한국연소학회 2012 KOSCOSYMPOSIUM논문집 Vol.- No.45
The droplet behavior of 83.9 wt.% HAN water solution was investigated experimentally with various ambient temperature and nitrogen environment. At the initial stage of evaporation under thermal decomposition temperature of HAN, gradual decreasing of droplet diameter was observed. After that, the droplet started to expand due to the internal pressure build up by water nucleation inside the droplet. The micro explosion was observed at higher temperature than the decomposition temperature of HAN and the remaining droplet showed similar behavior of single composition droplet. The decreasing rate was augmented as the ambient temperature increasing.
단일추진제 로켓 엔진 어셈블리를 위한 우주 공간에서의 과실 방지 설계
한조영,김정수,Han, Cho-Young,Kim, Jeong-Soo 대한기계학회 2003 大韓機械學會論文集B Vol.27 No.10
An analysis has been performed for active thermal control of the KOMPSAT monopropellant rocket engine assembly, i.e., dual thruster module(DTM). The main efforts of this work have been directed at determining proper heater sizes for propellant valves and catalyst beds necessary to maintain their temperatures within specified temperature ranges under KOMPSAT environment and operational conditions. The TAS incorporated with TRASYS thermal radiation analyzer was used to establish a complete heat transfer model which allows to predict the DTM temperature as a function of time. The thermal analysis has been performed in transient mode to verify the appropriate power for catalyst bed heaters necessary to increase catalyst bed temperature to the required value within a specified period of time. Similar analysis has been executed to validate the heater power for the thermostatically controlled primary and redundant heater circuits used to prevent hydrazine freezing, i.e., single fault. Moreover the effect of the radiative property of thermal control coating of heat shield was examined. Thruster firing condition was also simulated for the heat soakback condition. As a consequence, all thermal analysis results for DTM satisfactorily met the thermal requirements for the KOMPSAT DTM under the worst case average voltage, i.e. 25 volt.
동섬 및 편섬된 두 수형원판 사이의 환상유로에서의 복사와 자연대류간의 상호작용
한조영,백승욱,Han, Cho Young,Baek, Seung Wook 대한기계학회 1998 大韓機械學會論文集B Vol.22 No.12
A numerical investigation has been performed to discuss the radiation-affected steady-laminar natural convection induced by a hot inner cylinder under a large temperature difference in the annuli filled with a gray gas. To examine the effects of thermal radiation on thermo-fluid dynamic behaviors in the eccentric geometry, the generalized body-fitted coordinate system is introduced while the finite volume method (FVM) is used for solving the radiative transport equation. After validating the numerical results for the case without radiation, the detailed radiation effect has been discussed. Based on the results of this study, when there exists a large temperature difference between two cylinders, the existence of radiatively participating medium is found to incur a distinct difference in fluid dynamic as well as thermal behavior.
영국산 화학추진시스템의 기술이력과 통신해양기상위성 이원추진제 추진시스템
한조영,HAN, Cho Young 항공우주시스템공학회 2008 항공우주시스템공학회지 Vol.2 No.1
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.
한조영,김정수,이승우,Han, Cho-Young,Kim, Jeong-Soo,Rhee, Seung-Wu 대한기계학회 2003 大韓機械學會論文集B Vol.27 No.1
Thermal design fur satellite propulsion system has been performed. Overall design requirements and the constitution for propulsion system is described. To meet the thermal design requirements, both a primary and a redundant heater circuit, each with two thermostats placed in series, will protect each hydrazine-wetted components, even if one heater circuit fails to operate. Heater power is turned off if any one of these thermostats is opened at its higher setpoint. Thus, even if one thermostat is failed closed, the second thermostat will turn off the heater. All such components shall be insulated with MLI. Propulsion heater sizing based on the constant worst cold case condition is conducted through thermal analysis. All heaters selected fur propulsion components operate to prevent propellant freezing satisfying the thermal requirements for the propulsion subsystem over the worst case average voltage, i.e. 25 volts.
한조영,HAN, Cho Young 항공우주시스템공학회 2008 항공우주시스템공학회지 Vol.2 No.1
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.
한조영(Cho Young Han),김정수(Jeong Soo Kim),이균호(Kyun Ho Lee),김병교(Byung Kyo Kim) 대한기계학회 2003 대한기계학회 춘추학술대회 Vol.2003 No.11
Flame onset and propagation within hydrogen premixed gas mixture are numerically investigated in an<br/> rectangular enclosure. A detailed chemistry for hydrogen reaction is applied to anticipate the thermochemical<br/> behavior of intermediate species appropriately. To facilitate computation, 10 species and 16 elementary<br/> reaction steps for hydrogen combustion are taken into account. On the basis of 30 % of hydrogen<br/> concentration in hydrogen-air mixture, the effects of position and quantity of ignition sources on the flame<br/> evolution are analyzed. From the simulation results, the means that can lessen the possible hazard caused by<br/> flame propagation are suggested.
한조영(Cho Young HAN),채종원(Jong Won CHAE) 한국추진공학회 2011 한국추진공학회 학술대회논문집 Vol.2011 No.5
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. Chollian bipropellant propulsion system is composed of one main engine for orbit transfer and fourteen thrusters for on-station operations. The design and analyses of the propulsion system were carried out in the framework of international collaboration. Following the system integration and testings required, the Chollian was transported to Kourou Space Center in French Guiana and launched successfully. 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.