| 摘要 |
PROBLEM TO BE SOLVED: To provide a thermal control device mounted on board a spacecraft and located in a condensation zone comprising a means for varying the area of the heat exchange surface according to the thermal energy to be dissipated into space. SOLUTION: The invention relates to a thermal control device intended to dissipate the heat generated by a payload on a spacecraft, comprising a number of surfaces and including means for circulating a refrigerant, an evaporation zone (Z<SB>1</SB>) comprising means for circulating the refrigerant, a compression zone (Z<SB>2</SB>), a condensation zone (Z<SB>3</SB>) comprising at least one radiating panel, linked to a part of the means for circulating the refrigerant, including several branches and comprising means to allow or inhibit the circulation of the refrigerant within these branches so as to vary the area of the heat exchange surface in the condensation zone, and a pressure reduction zone (Z<SB>4</SB>) comprising means for circulating the refrigerant. Such a device is particularly well adapted to thermal problems encountered in telecommunications satellites. COPYRIGHT: (C)2008,JPO&INPIT |
