Abstract: A two-phase type heat transfer device (10) for heat sources operating at a wide temperature range. The heat transfer device (10) includes an evaporator (21) collecting heat from a heat source, a condenser (21) providing heat to a cold sink by a first working fluid passing through liquid and vapor transport lines (25, 27) that connect the evaporator (21) and the condenser (23). The evaporator (21) is arranged inside a saddle (31) configured for avoiding that the temperature of the first working fluid in the evaporator (21) is greater than its critical point. The invention also refers to aircraft ice protection systems using the heat transfer device (10).

Abstract: The advanced control heat transfer loop apparatus (1) for heat transfer and thermal control applications uses a two-phase fluid as a working media and comprises at least one evaporator (2) to be connected with a heat source and comprising primary capillary pump (4), a thermal stabilization-compensation chamber (3) being attached to the at least one evaporator (2), at least one condenser (24) to be connected with a heat sink, liquid lines (22) and vapor lines (23) connecting the at least one evaporator (2) and the at least one condenser (24), a remote compensation chamber (20), temperature sensors (27) for detecting the temperature of the remote compensation chamber (20) and at the thermal stabilization compensation chamber (3) attached to the at least one evaporator (2), at least one heating element (19) for heating the remote compensation chamber (20), and a controller (28).

Abstract: A two-phase type heat transfer device (10) for heat sources operating at a wide temperature range. The heat transfer device (10) includes an evaporator (21) collecting heat from a heat source, a condenser (21) providing heat to a cold sink by a first working fluid passing through liquid and vapor transport lines (25, 27) that connect the evaporator (21) and the condenser (23). The evaporator (21) is arranged inside a saddle (31) configured for avoiding that the temperature of the first working fluid in the evaporator (21) is greater than its critical point. The invention also refers to aircraft ice protection systems using the heat transfer device (10).

Abstract: The advanced control heat transfer loop apparatus (1) for heat transfer and thermal control applications uses a two-phase fluid as a working media and comprises at least one evaporator (2) to be connected with a heat source and comprising primary capillary pump (4), a thermal stabilization-compensation chamber (3) being attached to the at least one evaporator (2), at least one condenser (24) to be connected with a heat sink, liquid lines (22) and vapor lines (23) connecting the at least one evaporator (2) and the at least one condenser (24), a remote compensation chamber (20), temperature sensors (27) for detecting the temperature of the remote compensation chamber (20) and at the thermal stabilization compensation chamber (3) attached to the at least one evaporator (2),at least one heating element (19) for heating the remote compensation chamber (20), and a controller (28).

Abstract: Loop heat pipe apparatus (1) for heat transfer and thermal control, using a two-phase fluid as a working media and comprising: at least one evaporator (2) to be connected with a heat source and comprising a thermal stabilization-compensation chamber (10) attached to the at least one evaporator (2) and a secondary capillary pump (40) located inside the thermal stabilization-compensation chamber (10), at least one condenser (27) to be connected with a heat sink, liquid lines (24) and vapour lines (28) connecting the at least one evaporator (2) and the at least one condenser (27), and a remote compensation chamber (20), wherein the thermal stabilization-compensation chamber (10) comprises a two-phase reservoir (5) and a liquid accumulator reservoir (6) separated by a heat exchange surface (15), such that the remote compensation chamber (20) is hydraulically connected with the two-phase reservoir (5) and the liquid accumulator reservoir (6).

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: The invention refers to a thermal control device for controlling the temperature of a heat source by means of transferring heat from the heat source to the ambient environment, through the circulation of a fluid in the device, said device comprising an evaporator (10) collecting heat from the heat source, a condenser (30) rejecting heat to the ambient environment, a compensation chamber (20), and liquid (50) and vapor (40) transport lines connecting the evaporator (10) and the condenser (30), the fluid flowing through said transport lines (40, 50), the device further comprising a thermal electrical cooler (90), the thermal electrical cooler (90) further comprising a thermal saddle (80) attached to the cold side of the thermal electrical cooler (90), and a thermal radiator (100) attached to the hot side of the thermal electrical cooler (90), such that heat is rejected to the ambient environment directly through the thermal radiator (100), when the thermal control device operates in a hot environment, the ambie

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.