Spacecraft with anti nadir battery radiator

1. A battery system for a satellite, the system comprising:

an anti-nadir panel for the satellite having a nadir-facing first side and an anti-nadir facing second side,

wherein the nadir-facing first side of the anti-nadir panel is mounted to an anti-nadir side of a main body of the satellite such that the nadir-facing first side of the anti-nadir panel is always facing the anti-nadir side of the main body of the satellite;

at least one battery pack mounted to the anti-nadir facing second side of the anti-nadir panel, wherein the at least one battery pack comprises at least one battery cell; and

at least one radiator, wherein the at least one radiator is mounted to the at least one battery pack,

wherein the at least one radiator comprises a top side, a bottom side, and four edge sides, wherein each of the top side and the bottom side has a larger surface area than each of the four edge sides, and

wherein the at least one radiator is disposed on a side of the at least one battery pack that is opposite the anti-nadir panel such that the top side of the at least one radiator is anti-nadir facing when the satellite is in a deployed position and the bottom side of the at least one radiator always faces the anti-nadir side of the main body of the satellite.

2. The system of claim 1 , wherein the anti-nadir panel is substantially rectangular in shape.

3. The system of claim 2 , wherein when two of the battery packs are mounted to the anti-nadir facing second side of the anti-nadir panel, the two battery packs are disposed diagonally from each other in opposite corners of the anti-nadir panel.

4. The system of claim 2 , wherein when four of the battery packs are mounted to the anti-nadir facing second side of the anti-nadir panel, each of the four battery packs are disposed in a different corner of the anti-nadir panel.

5. The system of claim 1 , wherein when there is two or more of the battery packs, all of the battery packs have substantially the same thermal environment where all of the battery packs have substantially the same sun exposure.

6. The system of claim 1 , wherein when there is two or more of the battery packs, all of the battery packs have substantially the same differential cell charge balancing.

7. The system of claim 1 , wherein at least one external side of at least one of the at least one battery pack is covered with a thermal blanket.

8. The system of claim 7 , wherein the thermal blanket is a multi-layer insulation (MLI) thermal blanket.

9. The system of claim 1 , wherein at least one of the at least one battery cell is a lithium (Li) ion battery cell.

10. The system of claim 1 , wherein each of the at least one battery pack is mounted to the anti-nadir facing second side of the anti-nadir panel via a chassis.

11. The system of claim 1 , wherein each of the at least one battery pack is mounted to the anti-nadir facing second side of the anti-nadir panel via a thermal isolator.

12. The system of claim 1 , wherein the at least one battery pack is mounted to the anti-nadir facing second side of the anti-nadir panel via bonding.

13. The system of claim 1 , wherein at least one of the at least one battery cell is mounted to at least one of the at least one radiator via a bolted interface through a thermal gasket.

14. The system of claim 1 , wherein each of the at least one battery cell is fitted into a chassis via a respective opening formed within the chassis.

15. A method for manufacturing a battery system for a satellite, the method comprising:

providing an anti-nadir panel for the satellite having a nadir-facing first side and an anti-nadir facing second side;

mounting the nadir-facing first side of the anti-nadir panel to an anti-nadir side of a main body of the satellite such that the nadir-facing first side of the anti-nadir panel is always facing the anti-nadir side of the main body of the satellite;

mounting at least one battery pack to the anti-nadir facing second side of the anti-nadir panel,

wherein the at least one battery pack comprises at least one battery cell; and

mounting at least one radiator to the at least one battery pack,

wherein the at least one radiator comprises a top side, a bottom side, and four edge sides, wherein each of the top side and the bottom side has a larger surface area than each of the four edge sides, and

wherein the at least one radiator is disposed on a side of the at least one battery pack that is opposite the anti-nadir panel such that the top side of the at least one radiator is anti-nadir facing when the satellite is in a deployed position and the bottom side of the at least one radiator always faces the anti-nadir side of the main body of the satellite.

16. The method of claim 15 , wherein the anti-nadir panel is substantially rectangular in shape.

17. The method of claim 16 , wherein when two of the battery packs are mounted to the anti-nadir facing second side of the anti-nadir panel, the two battery packs are disposed diagonally from each other in opposite corners of the anti-nadir panel.

18. The method of claim 16 , wherein when four of the battery packs are mounted to the anti-nadir facing second side of the anti-nadir panel, each of the four battery packs are disposed in a different corner of the anti-nadir panel.

19. The method of claim 15 , wherein when there is two or more of the battery packs, all of the battery packs have substantially the same thermal environment where all of the battery packs have substantially the same sun exposure.

20. The method of claim 15 , wherein when there is two or more of the battery packs, all of the battery packs have substantially the same differential cell charge balancing.

21. The method of claim 15 , wherein the method further comprises covering at least one external side of at least one of the at least one battery pack with a thermal blanket.

22. The method of claim 15 , wherein at least one of the at least one battery cell is a lithium (Li) ion battery cell.

23. A satellite, comprising:

an anti-nadir panel having a nadir-facing first side and an anti-nadir facing second side,

wherein the nadir-facing first side of the anti-nadir panel is mounted to an anti-nadir side of a main body of the satellite such that the nadir-facing first side of the anti-nadir panel is always facing the anti-nadir side of the main body of the satellite;

at least one battery pack mounted to the anti-nadir facing second side of the anti-nadir panel, wherein the at least one battery pack comprises at least one battery cell; and

at least one radiator, wherein the at least one radiator is mounted to the at least one battery pack,

wherein the at least one radiator comprises a top side, a bottom side, and four edge sides, wherein each of the top side and the bottom side has a larger surface area than each of the four edge sides, and

wherein the at least one radiator is disposed on a side of the at least one battery pack that is opposite the anti-nadir panel such that the top side of the at least one radiator is anti-nadir facing when the satellite is in a deployed position and the bottom side of the at least one radiator always faces the anti-nadir side of the main body of the satellite.

24. The satellite of claim 23 , wherein the anti-nadir panel is substantially rectangular in shape.

25. The satellite of claim 24 , wherein when two of the battery packs are mounted to the anti-nadir facing second side of the anti-nadir panel, the two battery packs are disposed diagonally from each other in opposite corners of the anti-nadir panel.

26. The satellite of claim 24 , wherein when four of the battery packs are mounted to the anti-nadir facing second side of the anti-nadir panel, each of the four battery packs are disposed in a different corner of the anti-nadir panel.

27. The satellite of claim 23 , wherein when there is two or more of the battery packs, all of the battery packs have substantially the same thermal environment where all of the battery packs have substantially the same sun exposure.

28. The satellite of claim 23 , wherein at least one of the at least one battery cell is a lithium (Li) ion battery cell.