• Title/Summary/Keyword: Satellite Propulsion

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Thermal Analysis for Design of Propulsion System Employed in LEO Earth Observation Satellite

  • Han C.Y.;Kim J.S.;Lee K.H.;Rhee S.W.
    • 한국전산유체공학회:학술대회논문집
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    • 2003.10a
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    • pp.248-250
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    • 2003

  • 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.

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Development of Monopropellant Propulsion System for Low Earth Orbit Observation Satellite

  • Lee, Kyun-Ho;Yu, Myoung-Jong;Choi, Joon-Min
    • International Journal of Aeronautical and Space Sciences
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    • v.6 no.1
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    • pp.61-70
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    • 2005

  • The currently developed propulsion system(PS) is composed of propellant tank, valves, thrusters, interconnecting line assembly and thermal hardwares to prevent propellant freezing in the space environment. Comprehensive engineering analyses in the structure, thermal, flow and plume fields are performed to evaluate main design parameters and to verify their suitabilities concurrently at the design phase. The integrated PS has undergone a series of acceptance tests to verify workmanship, performance, and functionality prior to spacecraft level integration. After all the processes of assembly, integration and test are completed, the PS is integrated with the satellite bus system successfully. At present, the severe environmental tests have been carried out to evaluate functionality performances of satellite bus system. This paper summarizes an overall development process of monopropellant propulsion system for the attitude and orbit control of LEO(Low Earth Orbit) observation satellite from the design engineering up to the integration and test.

  • https://doi.org/10.5139/IJASS.2005.6.1.061 인용 PDF KSCI