Momentum tube for distributed actuation

• US 20060086865A1
• Filed: 10/22/2004
• Published: 04/27/2006
• Est. Priority Date: 10/22/2004
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Peck, Mason A., Jacobs, Jack H.
• Granted Patent: US 7,367,529 B2
• Time in Patent Office: Days
• US Class Current: 244/165
• CPC Class Codes: B64G 1/283 using reaction wheels
• CPC Class Codes: B64G 1/285 using momentum wheels
• CPC Class Codes: B64G 1/286 using control momentum gyroscopes (CMGs)

Abstract

An spacecraft control system is provided that includes a tube and a plurality of microwheels. The plurality of microwheels is disposed within the tube. Each microwheel has a first stator wafer, a second stator wafer, and a rotor wafer disposed therebetween. The first and second stator wafers are configured to spin the rotor wafer.

Claims

1. An spacecraft control system, comprising:

a tube; and

a plurality of microwheels disposed within the tube, each microwheel having a first stator wafer, a second stator wafer, and a rotor wafer disposed therebetween, the first and second stator wafers configured to spin the rotor wafer.

2. The spacecraft control system of claim 1, wherein the first and second stator wafers and rotor wafer comprise silicon disks.

3. The spacecraft control system of claim 1, wherein the first and second stator wafers are configured to magnetically levitate and spin the rotor wafer.

4. The spacecraft control system of claim 3, wherein the first and second stator wafers each include electromagnetic coils coupled thereto and the first stator wafer electromagnetic coil is configured to have polarity that is opposite of the polarity of the second stator wafer electromagnetic coil.

5. The spacecraft control system of claim 4, wherein the first and second stator wafers have electrical circuitry embedded therein.

6. The spacecraft control system of claim 5, wherein each of the electromagnetic coils further comprises a magnet coupled to one of the first and second stator wafers and in communication with the electrical circuitry.

7. The spacecraft control system of claim 5, wherein the tube has electrical connections and the tube electrical connections are in electrical communication with the stator wafer electrical circuitry.

8. The spacecraft control system of claim 3, wherein the rotor wafer has a first side, a second side, and magnets coupled to the first and second sides, wherein the magnets have opposite magnetic polarities.

9. The spacecraft control system of claim 1, wherein the first and second stator wafers are configured to electrostatically spin the rotor wafer.

10. The spacecraft control system of claim 1, wherein the first and second stator wafers each have an outer peripheral surface, and a magnet is coupled to each outer peripheral surface.

11. The spacecraft control system of claim 10, wherein the tube has an inner surface and first and second magnets are coupled to the tube inner surface, the first and second stator wafers disposed proximate the first and second magnets respectively, the first stator magnet having a magnetic polarity opposite of the magnetic polarity of the inner surface first magnet and the second stator magnet having a magnetic polarity opposite of the magnetic polarity of the inner surface second magnet.

12. The spacecraft control system of claim 1, wherein the plurality of microwheels comprises a first microwheel and a second microwheel, each disposed within the tube, the first microwheel disposed below the second microwheel, the first stator wafer of the first microwheel having a magnetic polarity and the second stator wafer of the second microwheel having an opposite magnetic polarity.

13. The spacecraft control system of claim 1, wherein each rotor wafer is configured to spin in the same direction.

14. The spacecraft control system of claim 1, wherein each rotor wafer is capable of spinning at different speeds.

15. A spacecraft control system comprising:

a plurality of tubes, wherein each tube is coupled to and in parallel with at least one other tube; and

a plurality of microwheels disposed within each tube, each microwheel having a first stator wafer, a second stator wafer, and a rotor wafer disposed therebetween, the first and second stator wafers configured to spin the rotor wafer.

16. The spacecraft control system of claim 15, wherein each microwheel is configured to spin in the same direction.

17. The spacecraft control system of claim 15, wherein the first and second stator wafers are configured to magnetically levitate and spin the rotor wafer.

18. The spacecraft control system of claim 15, wherein the first and second stator wafers are configured to electrostatically spin the rotor wafer.

19. The spacecraft control system of claim 15, wherein the plurality of tubes is configured to be disposed within a microsatellite.

20. The spacecraft control system of claim 15, wherein at least three of the plurality of tubes form a curved wall.

21. A satellite, comprising:

a housing;

a plurality of tubes disposed within the housing, wherein each tube is coupled to and in parallel with at least one other tube; and

a plurality of microwheels disposed within each tube, each microwheel having a first stator wafer, a second stator wafer, and a rotor wafer disposed therebetween, the first and second stator wafers configured to spin the rotor wafer.

22. The satellite of claim 21 wherein at least three of the plurality of tubes form a curved wall.

23. The satellite of claim 21, wherein the housing further comprises a sidewall and the plurality of tubes is coupled to the sidewall.

24. The satellite of claim 21, wherein the first and second stator wafers are configured to magnetically levitate and spin the rotor wafer.

25. The satellite of claim 21, wherein the first and second stator wafers are configured to electrostatically levitate and spin the rotor wafer.