As heat generation in satellites increases, ensuring that they are provided with sufficient radiator panel area is an important problem. Deployable radiators, with radiator panels that are deployed post-launch in space to increase the satellite's effective radiator panel area of the satellite, are becoming an important thermal control technology. A reservoir embedded loop heat pipe (RELHP) is used in deployable radiators as a heat transport device. A deployable radiator of this type was mounted on the ETS-VIII satellite, which was launched on December 18, 2006 and injected into a geostationary orbit. The satellite is still operating without any significant issues over two years later. This paper investigates the heat transport characteristics of an RELHP system used in a deployable radiator in a geostationary orbital environment. This system can be successfully started up in a micro gravity environment. We also found that the sub-cooling region is shorter in a micro gravity environment than in a terrestrial gravity environment, because there is less heat leakage into the reservoir in a micro gravity environment.
Heat transfer characteristics of a reservoir embedded loop heat pipe (heat transfer characteristics of a deployable radiator for use on the ETS-VIII satellite while in orbit)
Wärmeübertragungsdaten eines in ein Reservoir eingebetteten Loop-Wärmerohres (Wärmeübertragungsdaten eines entfaltbaren Radiators für den Einsatz an einem ETS-VIII Satellit während des Orbits)
Heat Transfer Asian Research ; 40 , 3 ; 269-285
2011
17 Seiten, 15 Bilder, 14 Quellen
Aufsatz (Zeitschrift)
Englisch
SAE Technical Papers | 2001
|NTRS | 1978
|1500 W Deployable Radiator with Loop Heat Pipe
SAE Technical Papers | 2001
|British Library Conference Proceedings | 2000
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