초록 ▼

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. T

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.

대표청구항 ▼

1. A thermal module for use on a spacecraft to control thermal loads coming from a heat source, the thermal module comprising: a two-phase loop system including: a thermal collector;a heat flow regulator;a by-pass line; anda condenser; anda heat rejection system,wherein the condenser and the heat re

1. A thermal module for use on a spacecraft to control thermal loads coming from a heat source, the thermal module comprising: a two-phase loop system including: a thermal collector;a heat flow regulator;a by-pass line; anda condenser; anda heat rejection system,wherein the condenser and the heat rejection system are thermally coupled,wherein the heat flow regulator includes: a main chamber separated from a second chamber by a flexible bellows;a moving element joined to the flexible bellows in the second chamber, the moving element extending into the main chamber; anda gas sealed in a volume between the flexible bellows and internal walls of the second chamber,wherein the heat flow regulator of the two-phase loop system redirects a first part of the thermal loads from the heat source to the condenser, from which the heat rejection system directs said first part of the thermal loads to a heat sink,wherein the temperature of the heat source is regulated by directing a second 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,wherein the flexible bellows expands within the second chamber due to an increase in saturated vapor pressure of a working fluid in the main chamber, the moving element being actuated in the main chamber to increase flow of the working fluid to the condenser and to reduce flow of the working fluid to the by-pass line, andwherein the heat rejection system is designed based on hottest possible conditions for a spacecraft mission. 2. The thermal module according to claim 1, further comprising: a thermal insulation system disposed between the condenser and the thermal collector. 3. The thermal module according to claim 1, further comprising: an isothermalization system including a heat pipe frame network. 4. The thermal module according to claim 1, further comprising: a pump that circulates a two-phase fluid in the two-phase loop system,wherein the pump is one of a mechanical, electro hydrodynamic, jet, piezoelectric bimorph, thermal pulsating, and osmotic pump. 5. The thermal module according to claim 1, wherein the thermal collector is a passive capillary pump. 6. The thermal module according to claim 1, wherein the main chamber is part of the two-phase loop system to control circulation of the thermal loads, and the second chamber is used to regulate a temperature set-up point of the thermal module. 7. The thermal module according to claim 6, wherein a position of said moving element adjusts in response to the thermal loads on the thermal module,wherein the moving element can adopt a position where the thermal collector and the condenser are linked,wherein the moving element can adopt a position where the thermal collector and the by-pass line are linked, andwherein the moving element can adopt an intermediate position where the thermal collector, the condenser, and the by-pass line are all linked. 8. The thermal module according to claim 6, wherein the gas is sealed in the second chamber at a predetermined pressure such that the predetermined pressure of the gas acts as a temperature controlling factor,wherein if the temperature in the thermal module is below a specified value, the corresponding pressure of a two-phase fluid in the two-phase loop system will be less than the pressure of the gas in the second chamber, and a path to the condenser will close to direct all heat flow to the by-pass line, andwherein if the temperature in the thermal module increases, the path to the condenser starts opening as the pressure in the two-phase loop system increases above a pressure in the second chamber. 9. A spacecraft modular thermal platform comprising at least one thermal module according to claim 1, the at least one thermal module being combined or embedded in other thermal architectures, providing optimum heat management of the thermal architecture by reducing power consumption and increasing heat rejection capabilities. 10. The spacecraft modular thermal platform according to claim 9, wherein heat rejection systems of at least two thermal modules are connected by means of heat pipes in order to equalize the working conditions of said heat rejection systems, the heat being bypassed to each of the by-pass lines of the at least two thermal modules. 11. The thermal module according to claim 1, wherein the flexible bellows receives a portion of the working fluid from the main chamber due to an increase in saturated vapor pressure of the working fluid in the main chamber. 12. The thermal module as claimed in claim 1, wherein the moving element is actuated towards a first valve seat in the main chamber to reduce flow of working fluid to the by-pass line when the saturated vapor pressure of the working fluid increases in the main chamber, and wherein the moving element is actuated towards a second valve seat in the main chamber to reduce flow of working fluid to the condenser when the saturated vapor pressure of the working fluid decreases in the main chamber. 13. A thermal module for use on a spacecraft to control thermal loads from a heat source, the thermal module comprising: a thermal collector, a condenser, a first transfer line, a second transfer line, a bypass line anda heat flow regulator, including: a main chamber separated from a second chamber by a flexible bellows a moving element joined to the flexible bellows in the second chamber, the moving element extending into the main chamber; anda gas sealed in a volume between the flexible bellows and internal walls of the second chamber,wherein the moving element is in fluid communication with an exit of the thermal collector through the first transfer line,wherein the moving element is in fluid communication with an inlet of the thermal collector through the bypass line,wherein the moving element is in fluid communication with an inlet of a condenser through the second transfer line, andwherein the flexible bellows expands within the second chamber due to an increase in saturated vapor pressure of the working fluid in the main chamber, the moving element being actuated in the main chamber to increase flow to the second transfer line and to reduce flow to the bypass line. 14. The thermal module as claimed in claim 13, wherein a position of the moving element adjusts in response to a difference between a pressure in the main chamber and a pressure in the second chamber,wherein the first transfer line is isolated from fluid communication with the second transfer line via the heat flow regulator when the moving element is in a first position,wherein the first transfer line is isolated from fluid communication with the bypass line via the heat flow regulator when the moving element is in a second position, andwherein the first transfer line, the second transfer line, and the bypass line are in fluid communication via the heat flow regulator when the moving element is in an intermediate position between the first position and the second position. 15. The thermal module as claimed in claim 13, wherein the gas is argon or nitrogen. 16. The thermal module as claimed in claim 13, wherein the thermal collector is a passive capillary pump. 17. The thermal module as claimed in claim 13, further comprising: a pump for circulating a fluid within the thermal module. 18. The thermal module as claimed in claim 17, wherein the pump is a passive capillary pump. 19. The thermal module as claimed in claim 13, further comprising: a thermal insulation system disposed between the condenser and the thermal collector. 20. The thermal module as claimed in claim 13, further comprising: an isothermalization system including a heat pipe frame network.