Transactions of the Korean Society of Mechanical Engineers B (대한기계학회논문집B)

The Korean Society of Mechanical Engineers (대한기계학회)
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Thermal Design for Satellite Propulsion System by Thermal Analysis

열해석에 의한 인공위성 추진시스템 열설계

  • 한조영 (한국항공우주연구원 위성연구부 위성제어 연구그룹 추진계) ;
  • 김정수 (한국항공우주연구원 위성연구부 위성제어 연구그룹 추진계) ;
  • 이승우 (한국항공우주연구원 위성연구부 위성제어 연구그룹)
  • Published : 2003.01.01
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Abstract

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.

Keywords

References

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Cited by

  1. Empirical and Computational Performance Prediction for Monopropellant Hydrazine Thruster Employed for Satellite vol.46, pp.6, 2009, https://doi.org/10.2514/1.43739