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A heat transfer assembly can include an equipment panel having an east end and a west end. East and west radiator panels are coupled to the east and west ends, respectively, of the equipment panel. The assembly also includes a plurality of flexible heat pipes each having a first rigid tube thermally

A heat transfer assembly can include an equipment panel having an east end and a west end. East and west radiator panels are coupled to the east and west ends, respectively, of the equipment panel. The assembly also includes a plurality of flexible heat pipes each having a first rigid tube thermally coupled to the east radiator panel, a second rigid tube coupled to the equipment panel, a third rigid tube thermally coupled to the west radiator panel, a first flexible tube sealingly coupled between the first and second rigid tubes, and a second flexible tube sealingly coupled between the second and third rigid tubes. The equipment panel is configured to retain one or more equipment modules in thermal contact with the second rigid tube of at least one of the plurality of flexible heat pipes.

대표청구항 ▼

1. A heat transfer assembly for a spacecraft, comprising: an equipment panel having an east end and a west end;an east radiator panel coupled to the east end of the equipment panel;a west radiator panel coupled to the west end of the equipment panel; anda plurality of flexible heat pipes each compri

1. A heat transfer assembly for a spacecraft, comprising: an equipment panel having an east end and a west end;an east radiator panel coupled to the east end of the equipment panel;a west radiator panel coupled to the west end of the equipment panel; anda plurality of flexible heat pipes each comprising a first rigid tube thermally coupled to the east radiator panel, a second rigid tube coupled to the equipment panel, a third rigid tube thermally coupled to the west radiator panel, a first flexible tube sealingly coupled between the first and second rigid tubes, and a second flexible tube sealingly coupled between the second and third rigid tubes,wherein the equipment panel is configured to retain one or more equipment modules in thermal contact with the second rigid tube of at least one of the plurality of flexible heat pipes. 2. The heat transfer assembly of claim 1, wherein: each of the plurality of flexible heat pipes comprises: a sealed first internal volume formed by the respective first, second, and third rigid tubes and the first and second flexible tubes; anda first heat transfer fluid disposed within the first internal volume; andthe first and third rigid tubes of each of the plurality of flexible heat pipes are each capable of condensing the first heat transfer fluid from a vapor to a liquid by rejecting heat to the respective east and west radiator panels. 3. The heat transfer assembly of claim 2, wherein the second rigid tube of each of the plurality of flexible heat pipes is capable of evaporating the first heat transfer fluid from a liquid to a vapor by accepting heat from one or more equipment modules thermally coupled to the second rigid tube. 4. The heat transfer assembly of claim 2, wherein the first and third rigid tubes of each of the plurality of flexible heat pipes are each capable of evaporating the first heat transfer fluid from a liquid to a vapor by accepting heat from the respective east and west radiator panels. 5. The heat transfer assembly of claim 1, further comprising a plurality of formed heat pipes each comprising a first portion thermally coupled to the second rigid tube of a first flexible heat pipe, a second portion thermally coupled to the second rigid tube of a second flexible heat pipe and a third portion sealingly coupled between the first and second portions. 6. The heat transfer assembly of claim 5, wherein each of the plurality of formed heat pipes is capable of transferring heat from the hotter of the first and second flexible heat pipes to the colder of the first and second flexible heat pipes. 7. The heat transfer assembly of claim 5, wherein: each of the plurality of formed heat pipes further comprises a sealed second interior volume formed by the first, second, and third portions of the respective formed heat pipe and a second heat transfer fluid disposed within the second internal volume;each of the first and second portions is capable of evaporating the heat transfer fluid from a liquid to a vapor by accepting heat from the respective flexible heat pipe when the respective flexible heat pipe is the hotter of the first and second flexible heat pipes; andeach of the first and second portions is capable of condensing the heat transfer fluid from a vapor to a liquid by rejecting heat to the respective flexible heat pipe when the respective flexible heat pipe is the colder of the first and second flexible heat pipes. 8. The heat transfer assembly of claim 1, wherein at least one of the east and west radiator panels is hingedly coupled to the equipment panel such that the at least one of the east and west radiator panels can be rotated with respect to the equipment panel. 9. The heat transfer assembly of claim 1, wherein the east and west radiator panels are rotatably coupled to the respective east and west ends of the equipment panel. 10. A spacecraft, comprising: a core structure;an east-west equipment panel having an east end and a west end;an east radiator panel rotatably coupled to the east end of the equipment panel;a west radiator panel rotatably coupled to the west end of the equipment panel;a plurality of flexible heat pipes each comprising a first rigid tube thermally coupled to the east radiator panel, a second rigid tube coupled to the equipment panel, a third rigid tube thermally coupled to the west radiator panel, a first flexible tube sealingly coupled between the first and second rigid tubes; and a second flexible tube sealingly coupled between the second and third rigid tubes; andone or more equipment modules thermally coupled to the second rigid tube of at least one of the plurality of flexible heat pipes. 11. The spacecraft of claim 10, wherein: each of the plurality of flexible heat pipes comprises a sealed first internal volume formed by the respective first, second, and third rigid tubes and the first and second flexible tubes and a first heat transfer fluid disposed within the first internal volume; andthe first and third rigid tubes of each of the plurality of flexible heat pipes are each capable of condensing the first heat transfer fluid from a vapor to a liquid by rejecting heat to the respective east and west radiator panels. 12. The spacecraft of claim 11, wherein the second rigid tube of each of the plurality of flexible heat pipes is capable of evaporating the first heat transfer fluid from a liquid to a vapor by accepting heat from one or more equipment modules thermally coupled to the second rigid tube. 13. The spacecraft of claim 11, wherein the first and third rigid tubes of each of the plurality of flexible heat pipes are each capable of evaporating the first heat transfer fluid from a liquid to a vapor by accepting heat from the respective east and west radiator panels. 14. The spacecraft of claim 10, further comprising a plurality of formed heat pipes each comprising a first portion thermally coupled to the second rigid tube of a first flexible heat pipe, a second portion thermally coupled to the second rigid tube of a second flexible heat pipe and a third portion sealingly coupled between the first and second portions. 15. The spacecraft of claim 14, wherein each of the plurality of formed heat pipes are capable of transferring heat from the hotter of the first and second flexible heat pipes to the colder of the first and second flexible heat pipes. 16. The spacecraft of claim 14, wherein: each of the plurality of formed heat pipes further comprises a sealed second interior volume formed by the first, second, and third portions of the respective formed heat pipe and a second heat transfer fluid disposed within the second internal volume;each of the first and second portions is capable of evaporating the heat transfer fluid from a liquid to a vapor by accepting heat from the respective flexible heat pipe when the respective flexible heat pipe is the hotter of the first and second flexible heat pipes; andeach of the first and second portions is capable of condensing the heat transfer fluid from a vapor to a liquid by rejecting heat to the respective flexible heat pipe when the respective flexible heat pipe is the colder of the first and second flexible heat pipes. 17. The spacecraft of claim 10, wherein at least one of the east and west radiator panels is hingedly coupled to the equipment panel such that the at least one of the east and west radiator panels can be rotated to provide access to the one or more equipment modules. 18. A method of controlling the temperature of an equipment module on a spacecraft, the method comprising the step of: thermally coupling the equipment module to a flexible heat pipe that comprises a first rigid tube thermally coupled to an east radiator panel disposed on an external east surface of the spacecraft, a second rigid tube thermally coupled to a west radiator panel disposed on an external west surface of the spacecraft, and a third rigid tube coupled to the first and second rigid tubes by first and second flexible tubes, respectively, wherein the equipment module is thermally coupled to the third rigid tube. 19. The method of claim 18, further comprising the steps of: moving one of the east and west radiator panels from a closed position to an open position such that the respective one of the first and second flexible tubes bends to maintain the integrity of the flexible heat pipe;attaching the equipment module to an equipment panel that is coupled to the third rigid tube; andmoving the one of the east and west radiator panels from the open position to the closed position.