The heat rejection of the space platform of the Columbus Space Station program is analyzed in order to establish guidelines for further studies. A preliminary heat rejection capability of 125 W/sq m is determined. It is found that the integration of feeder lines in the radiator panels leads to a high reliability against meteoroid impact. Investigation of potential heat pipe layouts results in a preference for using low to moderate transport capacity heat pipes (10 to 100 Wm). A preliminary comparison of three types of coating shows that white silicate paint results in highest radiation efficiency, even when degrading is taken into account.
Space Station Study: Thermal Control
1985
99 pages
Report
No indication
English
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