Heat transfer device and spacecraft comprising such a heat transfer device

Patent metadata

Field	Value
Publication number	US-11067341-B2
Application number	US-201816486853-A
Country	US
Kind code	B2
Filing date	Mar 13, 2018
Priority date	Mar 13, 2017
Publication date	Jul 20, 2021
Grant date	Jul 20, 2021

Abstract

A heat transfer device is disclosed having a housing including a first main wall and a second main wall, the housing having a sealed internal cavity, a liquid contained in the internal cavity, and a mixer able to set the liquid in motion, the heat transfer device being able to be switched between a first state and a second state in which the liquid is in motion and transfers heat by convection between the first main wall and the second main wall, the thermal conductance between the first main wall and the second main wall in the first state being four times less than the thermal conductance between the first main wall and the second main wall in the second state.

First claim

The invention claimed is:

1. A heat transfer device of a spacecraft configured to transfer heat between a first object and a second object, comprising:
a housing having a first main wall and a second main wall, the first main wall is configured to be in direct thermal contact by conduction with said first object, the second main wall is configured to be in direct thermal contact by conduction with said second object, said housing comprising a sealed internal cavity, a dielectric liquid contained in the internal cavity, and a mixer configured to set said dielectric liquid in motion,
the heat transfer device is configured to be switched between a first state in which the dielectric liquid is stagnant and a second state in which the dielectric liquid is in motion and transfers heat by forced convection between the first main wall the second main wall,
the mixer comprising at least two electrodes arranged with a spacing between one another and immersed in the dielectric liquid, wherein the at least two electrodes are each formed by a first grid extending in a first plane and a second grid extending in a second plane, the electrodes and the liquid forming an electrohydrodynamic system, when the heat transfer device is switched into the second state, the dielectric liquid passes across the electrodes during a forced convection movement, wherein the thermal conductance between the first main wall and the second main wall when the heat transfer device is in the first state is four times less than the thermal conductance between the first main wall and the second main wall when the heat transfer device is in the second state.

2. The heat transfer device according to claim 1 , wherein the first object is a heat pipe.

3. The heat transfer device according to claim 1 , wherein the second object is a heat pipe.

4. The transfer device according to claim 1 , wherein at least one wall among the first main wall and the second main wall has a flat outer face.

5. The heat transfer device according to claim 1 , wherein the housing has the shape of a parallelepiped having a length (L), a width (I), and a height (h), the height (h) being the distance between the first main wall and the second main wall, and wherein the height (h) has a dimension two times smaller than said width (I).

6. The heat transfer device according to claim 1 , wherein said electrodes extend in a plane parallel to the central plane of the main walls.

7. The heat transfer device according to claim 1 , wherein the mixer comprises a first holder configured to carry at least two electrodes, and a second holder configured to carry at least two electrodes, the first and second holders being arranged next to one another in a same plane parallel to a main wall, the at least two electrodes carried by the first holder being supplied a first voltage (U 1 ), the at least two electrodes carried by the second holder being supplied a second voltage (U 2 ), said second voltage (U 2 ) being of opposite sign to the first voltage (U 1 ), the circulation of fluid between the electrodes of the first holder and the circulation of fluid between the electrodes of the second holder being in opposite directions.

8. The heat transfer device according to claim 1 , wherein the thermal conductance between the first main wall and the second main wall in the first state is less than 40 W/K/m 2 .

9. The heat transfer device according to claim 1 , wherein the thermal conductance between the first main wall and the second main wall in the second state is greater than 250 W/K/m 2 .

10. A spacecraft, comprising:
a body having a North face, a South face opposite to the North face, an East face, and a West face opposite to the East face;
at least one radiator carried by at least one face among the North face, the South face, the East face, or the West face,
at least one dissipative equipment item connected by a nominal heat transfer device to at least one radiator;

wherein the nominal heat transfer device comprises at least one heat transfer device according to claim 1 , so as to enable switchable thermal conductance between the dissipative equipment item and the radiator, according to the state of the heat transfer device.

11. The spacecraft according to claim 10 , further comprising at least one redundant heat transfer device, a nominal heat pipe, and a redundant heat pipe, and wherein a main wall of the heat transfer device and a main wall of the at least one redundant transfer device is in thermal contact with said nominal heat pipe and said redundant heat pipe.

12. The heat transfer device according to claim 1 , wherein the thermal conductance between the first main wall and the second main wall in the first state is less than 8 W/K/m 2 .

13. The heat transfer device according to claim 1 , wherein the thermal conductance between the first main wall and the second main wall in the second state is greater than 800 W/K/m 2 .

Assignees

• Airbus Defence & Space Sas

Inventors

• Walker Andrew

Classifications

• B01F33/052

  the energy being electric fields for electrostatically charging of the ingredients or compositions for mixing them · CPC title

• F28D2021/0021

  for aircrafts or cosmonautics · CPC title

• F28D15/04 Primary

  with tubes having a capillary structure · CPC title

• B64G1/503

  Radiator panels · CPC title

• B64G1/506

  Heat pipes · CPC title