Abstract: A thermal module for use on a spacecraft to control thermal loads coming from a heat source is disclosed. The thermal module includes a two-phase loop system and a heat rejection system. The two-phase loop system includes a thermal collector, a heat flow regulator, a by-pass line, and a condenser. The condenser and the heat rejection system are thermally coupled, such that the heat flow regulator redirects part of the thermal loads from the heat source to the condenser, from which the heat rejection system directs said thermal loads to a heat sink. The temperature of the heat source is regulated by bypassing another part of the thermal loads back to the thermal collector through the by-pass line in a proportional manner, to avoid overcooling the heat source. The heat rejection system is designed based on the hottest possible conditions for the spacecraft mission.

Abstract: Thermal module (1) for use on a spacecraft to control thermal loads coming from a heat source (3) comprising a two-phase loop system (5) and a heat rejection system (13), the two-phase loop system (5) comprising a thermal collector (7), a heat flow regulator (10), a by-pass line (6) and a condenser (11), the condenser (11) and the heat rejection system (13) being thermally coupled, such that the heat flow regulator (10) of the two-phase loop system (5) redirects part of the thermal loads from the heat source (3) to the condenser (11), from which the heat rejection system (13) directs said thermal loads to a heat sink (14), the temperature of the heat source (3) being regulated by bypassing another part of the thermal loads back to the thermal collector (7) through the by-pass line (6) in a proportional manner, to avoid the heat source (3) overcooling, being the heat rejection system (13) designed based on the hottest possible conditions for the spacecraft mission.