Three axis attitude control system

• US 4,732,353 A
• Filed: 11/07/1985
• Issued: 03/22/1988
• Est. Priority Date: 11/07/1985
• Status: Expired due to Fees

• Current Assignee: The United States of America As Represented By The Secretary of Agriculture
• Original Assignee: United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration
• Inventors: Studer, Philip A.
• Primary Examiner(s): Barefoot, Galen
• Application Number:
  US06/795,805
• Time in Patent Office: 866 Days
• Field of Search: 244/158 R, 244/164, 244/165, 244/166, 310/90.5, 364/459, 74/5.46
• US Class Current: 244/165
• CPC Class Codes: B64G 1/28 using inertia or gyro effect
• CPC Class Codes: B64G 1/283 using reaction wheels
• CPC Class Codes: B64G 1/285 using momentum wheels
• CPC Class Codes: B64G 1/32 using earth's magnetic field
• CPC Class Codes: B64G 1/36 using sensors, e.g. sun-sensors, horizon sensors
• CPC Class Codes: F16C 2326/47 Cosmonautic vehicles, i.e. bearings adapted for use in outer-space in general B64G
• CPC Class Codes: F16C 32/044 Active magnetic bearings
• CPC Class Codes: H02K 7/09 with magnetic bearings

Abstract

A three axis attitude control system for an orbiting body, such as a spacecraft, comprises a motor driven flywheel supported by a torque producing active magnetic bearing. Free rotation of the flywheel is provided about its central axis and together with limited angular torsional deflections of the flywheel about two orthogonal axes which are perpendicular to the central axis. The motor comprises an electronically commutated DC motor, while the magnetic bearing comprises a radially servoed permanent magnet biased magnetic bearing capable of producing cross-axis torques on the flywheel. Three body attitude sensors for pitch, yaw and roll generate respective command signals along three mutually orthogonal axes (x, y, z) which are coupled to circuit means for energizing a set of control coils for producing torques about two of the axes (x and y) and speed control of the flywheel about the third (z) axis. An energy recovery system, which is operative during motor deceleration, is also included which permits the use of a high speed motor to perform effectively as a reaction wheel suspended in the magnetic bearing.

Claims

1. An attitude control system for a body stabilized vehicle such as a spacecraft, comprising:

a motor driven flywheel centered about one of three mutually perpendicular axes and being coupled to a relatively high speed electrical motor whose rotary speed and acceleration is controlled to produce a bi-directional controllable torque about said one axis;

motor control circuit means coupled between a power source and said motor and being operable to accelerate or decelerate said flywheel to produce a reaction torque about one of said axes;

circuit means coupled to said motor for feeding power back to said power source during motor deceleration; and

an active magnetic bearing, centered about said one axis, radially suspending said flywheel orthogonally along the other two of said three mutually perpendicular axes, said bearing further including electromagnetic circuit means for producing bi-directional controlled cross-axis torques of said flywheel about said two other axes, whereby a stabilized attitude of said vehicle in space is provided.

2. The attitude control system of claim 1 wherein said three mutually perpendicular axes of said vehicle include a roll axis, a pitch axis, and a yaw axis, and wherein said one axis comprises the roll axis, and the two other axes comprise the pitch and yaw axes, respectively.

3. The attitude control system of claim 1 and additionally including a plurality of vehicle attitude sensors carried by the vehicle for sensing deviations of said vehicle about said three mutually perpendicular axes and being operable to generate respective vehicle attitude command signals in response to a change in vehicle attitude about said three axes, and wherein said motor control circuit means is responsive to one of said attitude command signals for controlling motor speed and acceleration.

4. The attitude control system of claim 3 wherein said electromagnetic circuit means of said magnetic bearing are responsive to the other two of said attitude command signals for producing said cross-axis torques.

5. The attitude control system of claim 4 wherein said electromagnetic circuit means further comprises feedback control circuit means and additionally including feedback sensor means located adjacent said flywheel and being operable to sense any angular deviation of said flywheel from a commanded orientation relative to said two other axes and to generate error signals for both said two other axes, said error signals being applied to said control circuit means for reorienting said flywheel to said commanded orientation.

6. The attitude control system of claim 3 wherein said motor comprises an electronically commutated direct current motor.

7. The attitude control system of claim 6 wherein said motor control circuit means includes means coupled to said motor for providing a signal indicative of the direction of rotation of said motor, and a pulsewidth modulated motor controller coupled to said source and being responsive to said direction of rotation signal and said one attitude command signal to provide pulsewidth modulated power signals to an electronic commutator, said electronic commutator being coupled between said pulsewidth modulated motor controller and said direct current motor for driving said motor in a predetermined direction and rotational speed in response to said one attitude command signal and the pre-existing operating condition of said motor.

8. The attitude control system of claim 7 wherein said direction of rotation signal comprises a digital signal and said means for providing said direction of rotation signal comprises a multiphase digital encoder.

9. The attitude control system of claim 1 wherein said means for feeding power back to said power source further comprises rectifier means coupled to said motor whereby energy is extracted from said motor during deceleration, and power conversion means coupled between said rectifier means and said power source.

10. The attitude control system of claim 1 wherein said active magnetic bearing further includes a plurality of circumferential air gaps between said flywheel and said electromagnetic circuit means and additionally including permanent magnet means for providing passive stabilization of said flywheel axially along said one axis.

11. The attitude control system of claim 10 wherein said electromagnetic circuit means of said active magnetic bearing includes flux coil means for said two other axes and being selectively energized whereby magnetic flux provided by said flux coil means and said permanent magnet means reinforce and oppose each other along said two other axes on either side of said one axis to produce said controlled cross-axis torques.

12. The attitude control system of claim 10 wherein said electromagnetic circuit means of said active magnetic bearing includes flux coil means for said two other axes and being selectively energized whereby flux provided by said flux coil means and said permanent magnet means combine to provide active radial stabilization of said flywheel about said one axis along said two other axes.

13. The attitude control system of claim 1 and wherein said magnetic bearing comprises inner generally circular stator member having a plurality of peripheral outer surfaces defining a set of curvilinear interior pole faces, and wherein said flywheel comprises an outer annular magnetically permeable ring member having a like plurality of inwardly projecting rims including surfaces defining a set of curvilinear interior pole faces disposed opposite said set of exterior pole faces of the stator member and being separated therefrom by respective circumferential air gaps;

said stator member being further comprised of a central magnetically permeable member having a pair of opposing faces lying in a plane perpendicular to said one axis, a pair of magnetically opposed permanent magnets located on said pair of opposing faces and providing a substantially uniform radial DC flux across said circumferential air gaps for providing, per se, passive axial stabilization of said flywheel along said one axis, a first and second set of segmented magnetically permeable members respectively located on said pair of opposing faces and including flux bridge means for being magnetically coupled diametrically to direct flux across said air gaps along said two other axes, first flux coil winding means selectively located on said stator member and being selectively energized to produce flux which combines with said DC flux to produce differential radial forces across said circumferential air gaps to generate said cross-axis torques about said two other axes, and second flux coil winding means selectively located on said stator member and being selectively energized to produce flux which combines with said DC flux to provide active radial stabilization of said flywheel about said one axis.

14. The attitude control system of claim 13 wherein said first flux coil winding means are located on said first and second set of segmented magnetically permeable members.

15. The attitude control system of claim 13 wherein said second flux coil winding means are located on said central magnetically permeable member.

16. The attitude control system of claim 13 wherein said central magnetically permeable member comprises a generally flat circular plate having a peripheral outer surface defining one of said plurality of exterior pole faces and wherein said first and second set of segmented magnetically permeable members comprise quadrants of respective generally circular magnetically permeable discs and wherein the vertices of said quadrants intersect at said one axis.

17. The attitude control system of claim 13 and additionally including a plurality of vehicle attitude sensors carried by the vehicle for sensing deviations of said vehicle about said three mutually perpendicular axes and being operable to generate respective vehicle attitude command signals in response to a change in vehicle attitude about said three axes, and wherein said motor control circuit means is responsive to one of said attitude command signals for controlling motor speed and acceleration.

18. The attitude control system of claim 17 wherein said first flux coil winding means are responsive to the other two of said attitude command signals to produce said flux which combines with said DC flux to generate said cross-axis torques.

19. The attitude control system of claim 13 wherein electromagnetic circuit means further comprises feedback control circuit means and additionally including first feedback sensor means located adjacent said flywheel and being operable to sense any angular deviation of said flywheel from a commanded orientation about said two other axes and generate angular error signals for both said two other axes, and second feedback sensor means located adjacent said flywheel and being operable to sense any radial displacement of said flywheel from said one axis along said two other axes and generate radial error signals for both said two other axes, and wherein said angular error signals are applied to said first flux coil winding means and said radial error signals are applied to second flux coil winding means.

20. The attitude control system of claim 19 wherein said vehicle includes three mutually perpendicular axes defined as the roll, pitch and yaw axes and wherein said one axis comprises the roll axis, and said other two axes comprise the pitch and yaw axes.