Apparatus for controlling temperature in satellites

• US 20070063105A1
• Filed: 02/09/2005
• Published: 03/22/2007
• Est. Priority Date: 02/10/2004
• Status: Abandoned Application

• Current Assignee: Quallion, LLC (EnerSys)
• Original Assignee: Quallion, LLC (EnerSys)
• Inventors: Mann, Alfred
• Application Number:
  US11/055,287
• Publication Number:
  US 20070063105A1
• Time in Patent Office: Days
• US Class Current: 244/171.800
• CPC Class Codes: B64G 1/50 for temperature control

Abstract

Disclosed is a method and apparatus for maintaining the temperature of thermally sensitive components in a satellite within a preferred operating range. The apparatus employs a heat absorber disposed between the outer hull of the satellite and the components. The heat absorber includes heat-absorbing material preferably exhibiting a phase change at a temperature within a preferred operating range of the components.

Claims

1. A satellite, comprising:

a satellite hull defining an outermost skin and defining a satellite interior volume;

at least one component within the satellite interior volume, the component including a battery in a battery housing; and

a heat absorber positioned in the battery housing, the heat absorber having a phase transition that occurs in a range of −

15°

C. to 60°

C.

2. The satellite of claim 1, wherein the heat absorber includes water.

3. The satellite of claim 1, wherein the heat absorber includes paraffin.

4. The satellite of claim 1, wherein the heat absorber includes beeswax.

5. The satellite of claim 1, wherein the range is 5°

C. to 25°

C.

6. The satellite of claim 5, wherein the phase transition is melting.

8. The satellite of claim 1, further comprising:

a second material outside of the battery housing, the second material having a second phase transition that occurs at a temperature higher than 60°

C., but lower than a maximum temperature at which the component can be operated.

9. The satellite of claim 8, wherein the second phase transition is melting.

10. The satellite of claim 9, wherein the second material includes paraffin.

11. The satellite of claim 9, wherein the second material includes beeswax.

12. The satellite of claim 1, wherein the heat absorber completely surrounds the component.

15. The satellite of claim 1, further comprising:

insulation between the hull outermost skin and the heat absorber.

17. The satellite of claim 1, wherein the satellite is in near-earth orbit.

18. The satellite of claim 1, wherein the satellite is in stationary orbit.

20. The satellite of claim 1, wherein the component includes a manned compartment.

27. The satellite of claim 1, wherein the heat absorber surrounds the battery.

7. (canceled)

13-14. -14. (canceled)

16. (canceled)

19. (canceled)

21. A method for controlling temperature of a satellite component comprising:

providing a satellite hull defining an outermost skin and defining a satellite interior volume;

positioning at least one component within the interior volume,

the component including a battery in a battery housing, and

a heat absorber in the battery housing, the heat absorber having a phase transition that occurs in a range of −

15°

C. to 60°

C.

22. The method of claim 21, wherein the range is 5°

C. to 25°

C.

23. The method of claim 22 wherein the phase transition is melting.

24. The method of claim 22 wherein, the heat absorber includes a second material having second phase transition that occurs at a temperature higher than 60°

C., but lower than a maximum temperature at which the component can be operated.

25. The method of claim 24 wherein the second phase transition is melting.

28. The method of claim 21, wherein the heat absorber surrounds the battery.

26. (canceled)