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 (Z1) comprises means for circulating the refrigerant, a compression zone (Z2
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 (Z1) comprises means for circulating the refrigerant, a compression zone (Z2), a condensation zone (Z3) 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, a pressure reduction zone (Z4) comprising means for circulating the refrigerant. Such a device is particularly well adapted to thermal problems encountered in telecommunications satellites.
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1. A thermal control device intended to remove the heat generated by heat dissipating equipment on a spacecraft comprising a number of surfaces and including: means for circulating a refrigerant;an evaporation zone comprising means for circulating the refrigerant;a compression zone;a condensation zo
1. A thermal control device intended to remove the heat generated by heat dissipating equipment on a spacecraft comprising a number of surfaces and including: means for circulating a refrigerant;an evaporation zone comprising means for circulating the refrigerant;a compression zone;a condensation zone comprising at least one radiating panel, each radiating panel comprising at least two parts, each part of the radiating panel linked to several parallel U-shaped hydraulic branches of the means for circulating the refrigerant, some of the hydraulic branches within each part of the radiating panels comprising means to allow or inhibit the circulation of said refrigerant within said some of the hydraulic branches so as to vary the area of the heat exchange surface of each panel in the condensation zone; anda pressure reduction zone comprising means for circulating the refrigerant. 2. The thermal control device according to claim 1, wherein the condensation zone comprises at least two radiating panels, each radiating panel composed of several parts, the means for circulating the refrigerant belonging to one part of a first radiating panel being mounted in series with the means for circulating the refrigerant belonging to one part of a second radiating panel or with the pressure reduction zone. 3. Thermal control device according to claim 2, wherein the number n of parts per radiating panel is equal to the number n of radiating panels, the n radiating panels being connected in series by n−1 means of circulation, the n parts being passed through by the refrigerant having an identical discharge area. 4. Thermal control device according to claim 2, wherein the branches are tubes with grooved internal surfaces. 5. The thermal control device according to claim 2, wherein at each radiating panel the condensation zone comprises a system of automatic valves allowing all or part of the surface of the radiating panel to be used to remove heat. 6. The thermal control device according to claim 2, wherein the evaporation zone furthermore comprises centralized means of heating. 7. The thermal control device according to claim 2, wherein the evaporation zone comprises one or more pieces of said heat dissipating equipment controllable at either a single temperature level or at several different temperature levels. 8. Thermal control device according to claim 1, wherein the number of parts n per radiating panel is equal to the number of radiating panels n, the n radiating panels being connected in series by n−1 means of circulation, the n parts being passed through by the refrigerant having an identical discharge area, wherein n is an integer greater than one. 9. Thermal control device according to claim 1, wherein the branches are tubes with grooved internal surfaces. 10. The thermal control device according to claim 1, wherein at each radiating panel the condensation zone comprises a system of automatic valves allowing all or part of the surface of the radiating panel to be used to remove heat. 11. The thermal control device according to claim 1, wherein the evaporation zone furthermore comprises centralized means of heating. 12. The thermal control device according to claim 1, wherein the evaporation zone comprises one or more pieces of said heat dissipating equipment controlled at a single temperature level or at several different temperature levels. 13. The thermal control device according to claim 1, wherein the compression zone comprises several compression stages, the number of stages being equal to the number of temperature levels of the evaporator to be controlled. 14. The thermal control device according to claim 1, wherein the compression zone comprises at least one magnetic-bearing centrifugal compressor. 15. The thermal control device according to claim 1, comprising a bypass system between the compression zone and the condensation zone, allowing the outlet of the compression zone to be linked to the inlet of the compression zone, or to the inlet of the final stage of compression if the compression is multistage, and the temperature of the refrigerant exiting the compression zone to be adjusted. 16. A telecommunications spacecraft including a thermal control device according to claim 1. 17. The telecommunications spacecraft according to claim 16 and with faces commonly called North and South, characterized in that it comprises external radiating panels, fixed to the North and South faces, equipped with the condensation zone of the thermal control device, said radiating panels being conductively and radiatively decoupled from these North and South faces. 18. The telecommunications spacecraft according to claim 17, comprising said evaporation, said compression and said pressure reduction zones inside the spacecraft. 19. The telecommunications spacecraft according to claim 16, comprising a communication module and a service module, the external radiating panels being situated at the communication module. 20. Telecommunications spacecraft according to claim 16, comprising external radiating panels fixed to the panels commonly called the East, West, Earth and anti-Earth panels and parallel to the latter.
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이 특허에 인용된 특허 (14)
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