Direct torque control moment gyroscope

• US 5,386,738 A
• Filed: 12/22/1992
• Issued: 02/07/1995
• Est. Priority Date: 12/22/1992
• Status: Expired due to Fees

• Current Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Original Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Inventors: Havenhill, Douglas D.
• Primary Examiner(s): Bonck, Rodney H.
• Application Number:
  US07/995,477
• Time in Patent Office: 777 Days
• Field of Search: 74/5.22, 74/5.46, 74/5.4
• US Class Current: 74/5.22
• CPC Class Codes: B64G 1/286 using control momentum gyroscopes (CMGs)
• CPC Class Codes: F16C 2326/47 Cosmonautic vehicles, i.e. bearings adapted for use in outer-space
• CPC Class Codes: F16C 2370/00 Apparatus relating to physics, e.g. instruments
• CPC Class Codes: F16C 32/04 using magnetic or electric supporting means
• CPC Class Codes: F16C 39/06 using magnetic means
• CPC Class Codes: G01C 19/30 Erection devices, i.e. devices for restoring rotor axis to a desired position for instrument indicating the vertical G01C19/46
• CPC Class Codes: H02K 7/09 with magnetic bearings
• CPC Class Codes: Y10T 74/1218 Combined
• CPC Class Codes: Y10T 74/125 by magnetic field

Abstract

A control moment gyroscope for providing directional control in a spacecraft. The control moment gyroscope has a rotor which is electrostatically or magnetically supported within a gimbal housing so as not to touch any of the interior surfaces of the housing. The housing is mounted on a gimbal support which in turn is mounted on the spacecraft. Connected to the gimbal housing is a torque motor which rotates the housing around a gimbal axis. In order to induce a direction changing torque on the spacecraft, the rotor is first spun about its rotor axis. A torque is then induced on the rotor about the output axis. This induced torque will cause the rotor to precess about the gimbal axis which the torque motor follow. The torque induced around the output axis is transferred directly to the spacecraft.

Claims

1. A control moment gyroscope which applies directional torque to a vehicle comprising:

a gimbal;

gimbal support means mechanically attached to the vehicle which allows rotation of said gimbal about a gimbal axis;

a rotor;

means to magnetically levitate said rotor within said gimbal;

means for inducing angular rotation of said rotor about a rotor axis which is normal to the gimbal axis;

means for generating a magnetic field which induces torque on said rotor about an output axis normal to both the rotor axis and the gimbal axis, the torque on said rotor is transferred to the vehicle through said gimbal support means;

sensing means to detect the proximity of said rotor to said gimbal; and

rotation means connected to said sensing means for rotating said gimbal so as to follow precession of the rotor about the gimbal axis and avoid contact between the gimbal and said rotor.

2. The control moment gyroscope of claim 1 wherein the vehicle is a spacecraft.

3. The control moment gyroscope of claim 1 wherein said rotor is levitated within said gimbal by an electrostatic or electromagnetic field.

4. The control moment gyroscope of claim 3 wherein said means for inducing angular rotation on said rotor is a DC brushless motor.

5. The control moment gyroscope of claim 4 wherein said sensing means is a magnetic flux detector.

6. The control moment gyroscope of claim 5 wherein said sensing means is a hall element.

7. The control moment gyroscope of claim 4 wherein said sensing means is a gap sensor.

8. The control moment gyroscope of claim 7 wherein said sensing means is an eddy current sensor.

9. The control moment gyroscope of claim 3 wherein said means for generating a magnetic field is a plurality of magnetic actuators which create an electromagnetic or electrostatic field.

10. The control moment gyroscope of claim 1 wherein said gimbal torque means is an electromechanical motor.

11. A vehicle mounted control moment gyroscope comprising:

a rotor;

a gimbal;

means for magnetically levitating said rotor within said gimbal;

means for rotating said rotor about a rotor axis;

means for generating a magnetic field which induces a torque on said rotor about an output axis which is normal to the rotor axis;

gimbal support means mounted on the vehicle and mechanically connected to said gimbal so that said gimbal may rotate about a gimbal axis which is normal to both the rotor axis and the output axis;

a plurality of sensors for sensing the proximity of said rotor to said gimbal;

a gimbal torque motor for rotating said gimbal about the gimbal axis; and

a control circuit electrically connected to said plurality of sensors and said torque motor for rotating said gimbal about the gimbal axis so as to follow precession of said rotor.

12. The control moment gyroscope of claim 11 wherein the vehicle is a spacecraft.

13. The control moment gyroscope of claim 11 wherein said means for magnetically levitating said rotor are a plurality of actuators which generate an electrostatic or electromagnetic field around said rotor.

14. The control moment gyroscope of claim 13 wherein said means for rotating said rotor is a DC brushless motor.

15. The control moment gyroscope of claim 14 wherein said sensors are magnetic flux detectors.

16. The control moment gyroscope of claim 15 wherein said sensors are hall elements.

17. The control moment gyroscope of claim 14 wherein said sensors are gap sensors.

18. The control moment gyroscope of claim 16 wherein said sensors are eddy current elements.

19. The control moment gyroscope of claim 11 wherein said means for generating a magnetic field is a plurality of magnetic actuators which create a electromagnetic or electrostatic field around said rotor.

20. The control moment gyroscope of claim 11 wherein said gimbal torque motor is an electromechanical motor.