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http://dx.doi.org/10.3795/KSME-B.2003.27.10.1377

Faultproof Design in Space for Monopropellant Rocket Engine Assembly  

Han, Cho-Young (한국항공우주연구원)
Kim, Jeong-Soo (한국항공우주연구원 위성기초기술그룹)
Publication Information
Transactions of the Korean Society of Mechanical Engineers B / v.27, no.10, 2003 , pp. 1377-1384 More about this Journal
Abstract
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.
Keywords
Satellite Propulsion System; Rocket Engine; DTM; Worst Cold Condition; Thermal Analysis;
Citations & Related Records
Times Cited By KSCI : 2  (Citation Analysis)
연도 인용수 순위
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