Triple flywheel assembly with attitude jitter minimization

Patent metadata

Field	Value
Publication number	US-10005569-B2
Application number	US-201414900893-A
Country	US
Kind code	B2
Filing date	Jul 2, 2014
Priority date	Jul 2, 2013
Publication date	Jun 26, 2018
Grant date	Jun 26, 2018

Abstract

Various embodiments of the present invention include assemblies and methods for minimizing the amplitude of attitude jitter. In one embodiment, a flywheel assembly for reducing the amplitude of attitude jitter is provided. The flywheel assembly includes a first flywheel, a second flywheel, and a third flywheel. The first flywheel, second flywheel, and third flywheel are axially aligned and in operable engagement with one another. Each flywheel is configured to be independently controlled in order to manipulate the phase difference therebetween.

First claim

The invention claimed is:

1. A flywheel assembly for reducing the amplitude of attitude jitter, the flywheel assembly comprising:
a first flywheel;
a second flywheel; and
a third flywheel,
wherein:
the first flywheel, the second flywheel, and the third flywheel are axially aligned and in operable engagement with one another;
each of the first, second, and third flywheels is configured to be independently controlled in order to manipulate the phase difference therebetween; and
an imbalance due to eccentricity in the first flywheel and an imbalance due to eccentricity in the third flywheel are approximately the same.

2. The flywheel assembly according to claim 1 , wherein the first flywheel, second flywheel, and third flywheel are each configured to rotate about the same axis.

3. The flywheel assembly according to claim 1 , wherein:
the second flywheel is positioned axially between the first flywheel and the third flywheel; and
the first flywheel has a first eccentric center of mass, the second flywheel has a second eccentric center of mass, and the third flywheel has a third eccentric center of mass.

4. The flywheel assembly according to claim 1 , wherein the imbalance due to eccentricity in the second flywheel is approximately double that of each of the first flywheel and third flywheel.

5. The flywheel assembly according to claim 4 , wherein the variation of static and dynamic imbalance between the flywheels is less than 2.5%.

6. The flywheel assembly according to claim 1 , further comprising a controller, the controller configured to independently control the rotation of each flywheel to obtain a desired phase difference.

7. The flywheel assembly according to claim 6 , wherein:
the second flywheel is positioned axially between the first flywheel and the third flywheel; and
the controller is configured to cause rotation of the first flywheel to increase with respect to rotation of the second flywheel and cause rotation of the third flywheel to decrease with respect to rotation of the second flywheel for a predetermined period of time to reduce the amplitude of attitude jitter.

8. The flywheel assembly according to claim 7 , wherein:
the controller is configured to cause rotation of the first flywheel to increase using a trapezoidal angular velocity pulse; and
the controller is further configured to cause rotation of the third flywheel to decrease using an opposing trapezoidal angular velocity pulse.

9. The flywheel assembly according to claim 5 , wherein the controller is configured to control the rotation and relative phase of each flywheel to achieve static and dynamic imbalance.

10. The flywheel assembly according to claim 1 , further comprising:
a first motor configured to rotate the first flywheel;
a second motor configured to rotate the second flywheel; and
a third motor configured to rotate the third flywheel.

11. The flywheel assembly according to claim 10 , wherein the first, second, and third motors are each a frameless brushless DC motor.

12. The flywheel assembly according to claim 1 , wherein the flywheel assembly is mounted in a common housing.

13. The flywheel assembly according to claim 1 , wherein the overall mass and axial inertia of the flywheel assembly is substantially the same as the overall mass and inertia of a single flywheel assembly capable of being used in an identical spacecraft.

14. The flywheel assembly according to claim 1 , wherein the flywheel assembly is configured to be mounted within a spacecraft such that the spacecraft jitter can be stabilized by independently controlling the speed of rotation of at least one of the flywheels to adjust the phase difference therebetween.

15. The flywheel assembly according to claim 1 , wherein the flywheel assembly is configured to provide at least two layers of redundancy with a reduced capacity relative to a conventional flywheel assembly.

16. The flywheel assembly according to claim 15 , wherein reduced capacity is realized via a total combined mass of the first, second, and third flywheels of the assembly being substantially equal to a total mass of a conventional single flywheel assembly.

17. The flywheel assembly according to claim 1 , wherein a total combined mass of the first, second, and third flywheels of the assembly is substantially equal to a total mass of a conventional single flywheel assembly.

18. A spacecraft comprising:
a flywheel assembly for reducing the amplitude of attitude jitter in the spacecraft, the flywheel assembly comprising:
a first flywheel;
a second flywheel; and
a third flywheel,
wherein:
the first flywheel, second flywheel, and third flywheel are axially aligned and in operable engagement with one another;
each of the first, second, and third flywheels is configured to be independently controlled in order to manipulate the phase difference therebetween; and
an imbalance due to eccentricity in the first flywheel and an imbalance due to eccentricity in the third flywheel are approximately the same.

19. The spacecraft according to claim 18 , further comprising a controller configured to independently control the rotation of each flywheel to obtain a desired phase difference to rebalance the spacecraft.

20. The spacecraft according to claim 18 , wherein:
the second flywheel is positioned axially between the first flywheel and the third flywheel; and
the controller is configured to cause rotation of the first flywheel to increase with respect to rotation of the second flywheel and cause rotation of the third flywheel to decrease with respect to rotation of the second flywheel for a predetermined period of time to reduce the amplitude of attitude jitter of the spacecraft.

21. The spacecraft according to claim 18 , wherein:
the flywheel assembly is configured to provide at least two layers of redundancy with a reduced capacity relative to a conventional flywheel assembly; and
the reduced capacity is realized via a total combined mass of the first, second, and third flywheels of the assembly being substantially equal to a total mass of the conventional single flywheel assembly.

22. A method for reducing the amplitude of attitude jitter, the method comprising:
providing a flywheel assembly comprising:
a first flywheel;
a second flywheel; and
a third flywheel, wherein the first flywheel, second flywheel, and third flywheel are axially aligned and in operable engagement with one another; and

independently controlling each flywheel so as to manipulate the phase difference therebetween, wherein said independent controlling of each flywheel comprises rotating the first flywheel to increase with respect to rotation of the second flywheel and rotating the third flywheel to decrease with respect to rotation of the second flywheel for a predetermined period of time to reduce the amplitude of attitude litter.

23. The method according to claim 22 , wherein:
the second flywheel is positioned axially between the first flywheel and the third flywheel.

24. The method according to claim 22 , wherein:
the first flywheel has a first eccentric center of mass, the second flywheel has a second eccentric center of mass, and the third flywheel has a third eccentric center of mass.

25. The method according to claim 22 , wherein:
the flywheel assembly is configured to provide at least two layers of redundancy with a reduced capacity relative to a conventional flywheel assembly; and
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Assignees

• Univ Florida

Inventors

• Fitz-Coy Norman G
• Nagabhushan Vivek

Classifications

• B64G2001/228

  Operations & Transport · mapped topic

• B64G1/286

  using control momentum gyroscopes (CMGs) · CPC title

• B64G1/283 Primary

  using reaction wheels · CPC title

• B64G1/285 Primary

  using momentum wheels · CPC title

• F16F15/30

  Flywheels (F16F15/16, F16F15/28 take precedence; suppression of vibrations in rotating systems using elastic members or friction-damping members moving with the system, {i.e. split flywheels or single masses connected to a hub by elastic members or friction-damping members} F16F15/12; rotary-body aspects in general F16C13/00, F16C15/00) · CPC title