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http://dx.doi.org/10.3795/KSME-B.2003.27.1.117

Thermal Design for Satellite Propulsion System by Thermal Analysis  

Han, Cho-Young (한국항공우주연구원 위성연구부 위성제어 연구그룹 추진계)
Kim, Jeong-Soo (한국항공우주연구원 위성연구부 위성제어 연구그룹 추진계)
Rhee, Seung-Wu (한국항공우주연구원 위성연구부 위성제어 연구그룹)
Publication Information
Transactions of the Korean Society of Mechanical Engineers B / v.27, no.1, 2003 , pp. 117-124 More about this Journal
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
Satellite; Propulsion System; Thermal Design; Constant Worst Cold Case Condition; Active Thermal Control;
Citations & Related Records
Times Cited By KSCI : 2  (Citation Analysis)
연도 인용수 순위
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