한국전산유체공학회:학술대회논문집
- 2003.10a
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- Pages.248-250
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- 2003
Thermal Analysis for Design of Propulsion System Employed in LEO Earth Observation Satellite
- Han C.Y. (Satellite Core Technology Department, Satellite Technology Division, KOMPSAT Program Office, Korea Aerospace Research Institute) ;
- Kim J.S. (Satellite Core Technology Department, Satellite Technology Division, KOMPSAT Program Office, Korea Aerospace Research Institute) ;
- Lee K.H. (Satellite Core Technology Department, Satellite Technology Division, KOMPSAT Program Office, Korea Aerospace Research Institute) ;
- Rhee S.W. (Satellite Core Technology Department, Satellite Technology Division, KOMPSAT Program Office, Korea Aerospace Research Institute)
- Published : 2003.10.01
Abstract
Thermal analysis is performed to protect the propulsion system of low-earth-orbit earth observation satellite from unwanted thermal disaster like propellant freezing. To implement thermal design adequately, heater powers for the propulsion system estimated through the thermal analysis are decided. Based on those values anticipated herein, the average power for propulsion system becomes 22.02 watts when the only one redundant catalyst bed heater is turned on. When for the preparation of thruster firing, 25.93 watts of the average power is required. All heaters selected for propulsion components operate to prevent propellant freezing meeting the thermal requirements for the propulsion system with the worst-case average voltage, i.e. 25 volts.