Method of using a hybrid power source and control moment gyroscope

Patent metadata

Field	Value
Publication number	US-10837775-B2
Application number	US-201916253550-A
Country	US
Kind code	B2
Filing date	Jan 22, 2019
Priority date	Feb 2, 2016
Publication date	Nov 17, 2020
Grant date	Nov 17, 2020

Abstract

A method, for providing spatial stability and electrical power with a hybrid power source and control moment gyroscope (HPCMG), includes producing spatial stability force for the HPCMG by spinning a central mass within a first transverse gimbal assembly about a first axis of rotation of a control moment gyroscope (CMG). The CMG includes the first transverse gimbal assembly, the central mass, and a second gimbal assembly rotationally connected to the first transverse gimbal assembly. The first transverse gimbal assembly is rotationally connected to the central mass at a first position of the first transverse gimbal assembly and at a second position of the first transverse gimbal assembly along the first axis of rotation. The method includes producing a voltage potential with the central mass. The method includes charging or discharging the central mass through conductive bearings.

First claim

What is claimed is:

1. A method for providing spatial stability and electrical power with a hybrid power source and control moment gyroscope (HPCMG) ( 102 ), the method comprising:
producing spatial stability force ( 122 ) for the HPCMG by spinning a central mass ( 208 , 300 , 400 ) within a first transverse gimbal assembly ( 206 ) about a first axis ( 216 ) of rotation of a control moment gyroscope (CMG) ( 200 ), wherein the CMG ( 200 ) includes the first transverse gimbal assembly, the central mass, and a second gimbal assembly ( 210 ) rotationally connected to the first transverse gimbal assembly, wherein the first transverse gimbal assembly is rotationally connected to the central mass at a first position ( 212 ) of the first transverse gimbal assembly and at a second position ( 214 ) of the first transverse gimbal assembly along the first axis of rotation ( 216 ), wherein the central mass ( 208 , 300 , 400 ) comprises a plurality of layers ( 302 and 402 ), wherein all of the layers of the plurality of layers ( 302 and 402 ) are electrically interconnected to produce the voltage potential, and wherein the first transverse gimbal assembly is configured to rotate about a second axis of rotation ( 218 ) at a first position ( 220 ) of the second gimbal assembly;
producing a voltage potential ( 120 , 234 ) with the central mass; and
discharging the central mass through conductive bearings ( 202 , 204 ), wherein the conductive bearings are in signal communication with the central mass and rotationally connected to both the central mass and the first transverse gimbal assembly.

2. The method of claim 1 , wherein producing the spatial stability force ( 122 ) includes generating a first moment of force along the first axis ( 216 ) of rotation and a second moment of force along the second axis ( 218 ) of rotation.

3. The method of claim 1 , further comprising receiving an attitude control signal ( 118 ), wherein the central mass ( 208 , 300 , 400 ) is spun based on the attitude control signal.

4. The method of claim 3 , wherein the plurality of layers ( 302 and 402 ) includes a capacitive disk or a disk having a battery cell.

5. The method of claim 1 , wherein the HPCMG is coupled to a vehicle.

6. The method of claim 5 , wherein the HPCMG is configured to provide power to the vehicle via the conductive bearings ( 202 , 204 ).

7. The method of claim 5 , wherein the HPCMG is configured to apply the spatial stability force on the vehicle via a third gimbal assembly ( 224 ) coupled to the second gimbal assembly ( 210 ).

8. The method of claim 5 , wherein the vehicle is a submersible marine vehicle, a surface marine vehicle, an aircraft, or a spacecraft.

9. A method for providing spatial stability and electrical power with a hybrid power source and control moment gyroscope (HPCMG) ( 102 ), the method comprising:
producing spatial stability force ( 122 ) for the HPCMG by spinning a central mass ( 208 , 300 , 400 ) within a first transverse gimbal assembly ( 206 ) about a first axis ( 216 ) of rotation of a control moment gyroscope (CMG) ( 200 ), wherein the CMG ( 200 ) includes the first transverse gimbal assembly, the central mass, and a second gimbal assembly ( 210 ) rotationally connected to the first transverse gimbal assembly, wherein the first transverse gimbal assembly is rotationally connected to the central mass at a first position ( 212 ) of the first transverse gimbal assembly and at a second position ( 214 ) of the first transverse gimbal assembly along the first axis of rotation ( 216 ), and wherein the first transverse gimbal assembly is configured to rotate about a second axis of rotation ( 218 ) at a first position ( 220 ) of the second gimbal assembly;
charging the central mass ( 208 , 300 , and 400 ) with a first voltage potential ( 120 and 234 ) through conductive bearings ( 202 and 204 ), wherein the conductive bearings ( 202 and 204 ) are in signal communication with the central mass ( 208 , 300 , and 400 ) and rotationally connected to both the central mass ( 208 , 300 , and 400 ) and the first transverse gimbal assembly ( 206 );
after charging the central mass, producing a second voltage potential ( 120 and 234 ) with the central mass ( 208 , 300 , and 400 ); and
discharging the central mass ( 208 , 300 , and 400 ) through the conductive bearings ( 202 and 204 ).

10. The method of claim 9 , wherein the HPCMG is coupled to a vehicle.

11. The method of claim 9 , wherein producing the spatial stability force ( 122 ) includes generating a first moment of force along the first axis ( 216 ) of rotation and a second moment of force along the second axis ( 218 ) of rotation.

12. The method of claim 9 , wherein the central mass ( 208 , 300 , and 400 ) includes a plurality of layers ( 302 and 402 ), and wherein all of the layers of the plurality of layers ( 302 and 402 ) are electrically interconnected to produce the voltage potential.

13. The method of claim 12 , wherein the plurality of layers ( 302 and 402 ) includes a capacitive disk or a disk having a battery cell.

14. The method of claim 9 , further comprising receiving an attitude control signal ( 118 ), wherein the central mass ( 208 , 300 , 400 ) is spun based on the attitude control signal.

15. The method of claim 9 , wherein the central mass ( 208 , 300 , 400 ) comprises a plurality of layers ( 302 and 402 ).

16. The method of claim 15 , wherein layers of the plurality of layers ( 302 and 402 ) are electrically coupled in series.

17. A method for providing spatial stability and electrical power with a hybrid power source and control moment gyroscope (HPCMG) ( 102 ), the method comprising:
producing spatial stability force ( 122 ) for the HPCMG by spinning a central mass ( 208 , 300 , 400 ) within a first transverse gimbal assembly ( 206 ) about a first axis ( 216 ) of rotation of a control moment gyroscope (CMG) ( 200 ), wherein the CMG ( 200 ) includes the first transverse gimbal assembly, the central mass, and a second gimbal assembly ( 210 ) rotationally connected to the first transverse gimbal assembly, wherein the first transverse gimbal assembly is rotationally connected to the central mass at a first position ( 212 ) of the first transverse gimbal assembly and at a second position ( 214 ) of the first transverse gimbal assembly along the first axis of rotation ( 216 ), and wherein the first transverse gimbal assembly is configured to rotate about a second axis of rotation ( 218 ) at a first position ( 220 ) of the second gimbal assembly;
providing an electrical signal to or from the central mass via conductive bearings ( 202 , 204 ), wherein the conductive bearings are in signal communication with the central mass and rotationally connected to both the central mass and the first transverse gimbal assembly; and
receiving an attitude control signal ( 118 ), wherein the central mass ( 208 , 300 , 400 ) is spun based on the attitude control signal.

18. The method of claim 17 , wherein producing the spatial stability force ( 122 ) includes generating a first moment of force along the first axis ( 216 ) of rotation and a second moment of force along the second axis ( 218 ) of rotation.

19. The method of claim 17 , further comprising charging a capacitor or battery of the central mass responsive to the electrical signal.

20. The method of claim 17 , further comprising discharging a capacitor or battery of the central mass responsive to the electrical signal.

Assignees

• Boeing Co

Inventors

• Veto Christopher C

Classifications

• G01C19/10 Primary

  Power supply · CPC title

• B63B39/04 Primary

  to decrease vessel movements by using gyroscopes directly · CPC title

• B64G1/421

  Non-solar power generation · CPC title

• B64G1/286

  using control momentum gyroscopes (CMGs) · CPC title

• B64G1/425

  Power storage · CPC title