Gyroscopic attitude control system

Patent metadata

Field	Value
Publication number	US-11221633-B2
Application number	US-201615156507-A
Country	US
Kind code	B2
Filing date	May 17, 2016
Priority date	May 17, 2016
Publication date	Jan 11, 2022
Grant date	Jan 11, 2022

Abstract

An attitude control system includes one or more control moment gyro pairs, with gyros of individual of the pairs being counter-rotated to rotate the rotation axes of flywheels of the gyros of a gyro pair in opposite direction. The flywheels of a gyro pair may be in paddle configuration, with the rotation axes of the flywheels rotating in the counter-rotation through separate planes as the gyros are rotated. The rotation of the gyros of a gyro pair may be accomplished by coupling both of the gyros to a servo motor with suitable coupling gears, or by using independent servos for each gyro. The counter-rotation of gyros of an individual pair produces a resultant torque about a fixed global axis, such as the axis of a flight vehicle of which the attitude control system is a part. Further control may be accomplished for example by varying rotation speeds of the flywheels.

First claim

What is claimed is:

1. An attitude control system comprising:
a control moment gyro pair that includes:
a first control moment gyro that includes a first flywheel rotatably mounted to a first frame, wherein the first flywheel rotates relative to the first frame about a first flywheel rotation axis that is perpendicular to the first flywheel;
a second control moment gyro that includes a second flywheel rotatably mounted to a second frame, wherein the second flywheel rotates relative to the second frame about a second flywheel rotation axis that is perpendicular to the second flywheel; and
one or more actuators that selectively counter-rotate the first control moment gyro, and the second control moment gyro, so as to rotate the first flywheel rotation axis and the second flywheel rotation axis in opposite directions to cant the first control moment gyro relative to the second control moment gyro;

wherein the one or more actuators rotate the first flywheel and the first frame, and the second flywheel and the second frame, so as to rotate the first flywheel rotation axis and the second flywheel rotation axis within respective offset parallel planes.

2. The device of claim 1 , wherein the first control moment gyro and the second control moment gyro are both rotated by the one or more actuators about a common gyro pair rotation axis.

3. The device of claim 2 , wherein the gyro pair rotation axis is perpendicular to planes in which the flywheel rotation axes rotate when the control moment gyros are rotated.

4. The device of claim 1 ,
wherein the first control moment gyro includes a first spin motor for rotating the first flywheel about the first flywheel rotation axis, relative to the first frame; and
wherein the second control moment gyro includes a second spin motor for rotating the second flywheel about the second flywheel rotation axis, relative to the second frame.

5. The device of claim 4 , wherein the spin motors are servo motors.

6. The device of claim 4 , wherein the spin motors are variable speed motors.

7. The device of claim 1 ,
wherein the control moment gyro pair is a first control moment gyro pair; and
further comprising a second control moment gyro pair and a third control moment gyro pairs; and
wherein the control moment gyro pairs control attitude about respective control moment axes.

8. The device of claim 7 , wherein the control moment axes are all perpendicular to one another.

9. The device of claim 7 , further comprising a controller that is operatively coupled to the control moment gyro pairs, to control the control moment gyro pairs to achieve a desired attitude about the control moment axes.

10. The device of claim 9 , wherein the controller controls counter-rotation of gyros of the control moment gyro pairs.

11. The device of claim 9 , wherein the controller controls spin rate of flywheels of gyros.

12. The device of claim 9 , wherein the controller is an adaptive controller, able to compensate for reductions in functionality of one or more of the gyros.

13. The device of claim 9 , wherein the controller is a machine learning controller.

14. The device of claim 1 , wherein the attitude control system is part of a flight vehicle.

15. An attitude control system comprising:
three control moment gyro pairs for controlling attitude in respective control moment axes, wherein each of the control moment gyro pairs includes:
a first control moment gyro that includes a first flywheel rotatably mounted to a first frame, wherein the first flywheel rotates relative to the first frame about a first flywheel rotation axis that is perpendicular to the first flywheel;
a second control moment gyro that includes a second flywheel rotatably mounted to a second frame, wherein the second flywheel rotates relative to the second frame about a second flywheel rotation axis that is perpendicular to the second flywheel; and
one or more actuators that selectively counter-rotate the first control moment gyro as a unit, with the first flywheel and the first frame rotating together, and the second control moment gyro as a unit, with the second flywheel and the second frame rotating together, so as to rotate the first flywheel rotation axis and the second flywheel rotation axis in opposite directions to cant the first control moment gyro relative to the second control moment gyro;
wherein the one or more actuators rotate the first flywheel and the first frame, and the second flywheel and the second frame, so as to rotate the first flywheel rotation axis and the second flywheel rotation axis within respective offset parallel planes.

16. The attitude control system of claim 1 , wherein the one or more actuators includes a single actuator that counter-rotates both the first control moment gyro and the second control moment gyro.

17. The attitude control system of claim 1 , wherein the one or more actuators includes separate respective actuators to effect the counter-rotation of the first control moment gyro and the second control moment gyro.

18. The attitude control system of claim 15 , wherein for each of the control moment gyro pairs the one or more actuators includes separate respective actuators to effect the counter-rotation of the first control moment gyro and the second control moment gyro.

19. The attitude control system of claim 1 ,
wherein the first flywheel rotation axis is fixed relative to the first frame; and
wherein the second flywheel rotation axis is fixed relative to the second frame.

20. The attitude control system of claim 1 , wherein the one or more actuators selectively counter-rotate the first control moment gyro as a unit, with the first flywheel and the first frame rotating together, and the second control moment gyro as a unit, with the second flywheel and the second frame rotating together.

21. The device of claim 16 , wherein the single actuator includes a motor.

22. The device of claim 21 , wherein a shaft of the motor engages gearing on the frames.

Assignees

• Raytheon Co

Inventors

• Ala Eero H
• Owan Christopher P

Classifications

• B64C19/00 Primary

  Aircraft control not otherwise provided for · CPC title

• G01C19/04

  Details · CPC title

• F42B10/025

  using giratory or oscillating masses for stabilising projectile trajectory · CPC title

• B64G1/286

  using control momentum gyroscopes (CMGs) · CPC title

• G05D1/0808 Primary

  specially adapted for aircraft · CPC title