Thermal Design for KOMPSAT-2 Propulsion System

다목적실용위성 2호 추진계의 열설계

  • 한조영 (한국항공우주연구원 위성사업부 위성제어연구그룹 추진계) ;
  • 김정수 (한국항공우주연구원 위성사업부 위성제어연구그룹 추진계) ;
  • 이균호 (한국항공우주연구원 위성사업부 위성제어연구그룹 추진계)
  • Published : 2001.11.01

Abstract

Thermal design for KOMPSAT-2 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 for 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.

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