Control moment gyroscope

Patent metadata

Field	Value
Publication number	US-11021272-B2
Application number	US-201616070086-A
Country	US
Kind code	B2
Filing date	Jul 25, 2016
Priority date	Feb 10, 2016
Publication date	Jun 1, 2021
Grant date	Jun 1, 2021

Abstract

A control moment gyroscope includes: an inner gimbal; a rotor that is held by the inner gimbal to be rotatable around a spin axis; a spin motor that is disposed on the inner gimbal, and that rotates the rotor around the spin axis; a stator that holds the inner gimbal to be rotatable around a gimbal axis that is perpendicular to the spin axis; gimbal bearings that are disposed between the inner gimbal and the stator to face each other from opposite sides of a plane that is perpendicular to the gimbal axis and that includes the spin axis, to be in contact with the plane in question, or to include the plane in question; and a torque module that is disposed on the stator, and that rotates the inner gimbal around the gimbal axis.

First claim

The invention claimed is:

1. A control moment gyroscope to be disposed on a spacecraft, wherein said control moment gyroscope comprises:
an inner gimbal;
a rotor that is held by said inner gimbal so as to be rotatable around a spin axis;
a spin motor that is disposed on said inner gimbal, and that rotates said rotor around said spin axis;
a stator that holds said inner gimbal so as to be rotatable around a gimbal axis that is perpendicular to said spin axis;
gimbal bearings that are disposed between said inner gimbal and said stator so as to face each other from opposite sides of a plane that is perpendicular to said gimbal axis and that includes said spin axis, so as to be in contact with said plane, or so as to include said plane; and
a torque module that is disposed on said stator, and that rotates said inner gimbal around said gimbal axis,
wherein said rotor has a shaft extending along said spin axis, and
wherein said gimbal bearings are disposed outside of opposite ends of said shaft of said rotor when viewed along said gimbal axis.

2. The control moment gyroscope according to claim 1 , wherein said torque module is disposed on said stator so as to be adjacent to said gimbal bearings.

3. The control moment gyroscope according to claim 2 , wherein:
said gimbal bearings are disposed so as to be in contact with said plane; and
said torque module is disposed so as to face said gimbal bearings.

4. The control moment gyroscope according to claim 1 , wherein said gimbal bearings are constituted by two angular contact ball bearings that face each other from the opposite sides of said plane.

5. The control moment gyroscope according to claim 4 , wherein said torque module is disposed between said two angular contact ball bearings.

6. The control moment gyroscope according to claim 1 , further comprising an interface that connects said spacecraft and said stator, said interface being disposed so as to include said plane, so as to be in contact with said plane, or so as to be in proximity to said plane.

7. The control moment gyroscope according to claim 1 , wherein a maximum diameter of said rotor is equal to a length between bearings that rotatably support the ends of said shaft of said rotor.

8. The control moment gyroscope according to claim 1 , wherein a maximum diameter of said rotor is less than or equal to a maximum dimension among said stator and said inner gimbal in an axial direction of said gimbal axis.

Assignees

• Mitsubishi Electric Corp

Inventors

• Kashiwa Munetaka
• Fukushima Kazuhiko

Classifications

• G01C19/18

  providing movement of rotor with respect to its rotational axes (G01C19/20, G01C19/24 take precedence) · CPC title

• G01C19/16

  Suspensions; Bearings · CPC title

• B64G1/28

  using inertia or gyro effect · CPC title

• H02K7/14

  Structural association with mechanical loads, e.g. with hand-held machine tools or fans (with fan or impeller for cooling the machine H02K9/06) · CPC title

• B64G1/286 Primary

  using control momentum gyroscopes (CMGs) · CPC title