Hybrid power source and control moment gyroscope

Patent metadata

Field	Value
Publication number	US-10228248-B2
Application number	US-201615013947-A
Country	US
Kind code	B2
Filing date	Feb 2, 2016
Priority date	Feb 2, 2016
Publication date	Mar 12, 2019
Grant date	Mar 12, 2019

Abstract

A hybrid power source and control moment gyroscope (“HPCMG”) is disclosed. The HPCMG includes a control moment gyroscope (“CMG”), a first conductive bearing, and a second conductive bearing. The CMG includes a first transverse gimbal assembly, a central mass that produces a voltage potential, and a second gimbal assembly rotationally connected to the first transverse gimbal assembly. The first transverse gimbal assembly is rotationally connected to the central mass along a first axis of rotation and the central mass is configured to spin about the first axis of rotation and the first transverse gimbal assembly is configured to rotate about a second axis of rotation of the second gimbal assembly. The first conductive bearing rotationally connects the central mass with the first position of the first transverse gimbal assembly along the first axis of rotation.

First claim

What is claimed is:

1. A hybrid power source and control moment gyroscope “HPCMG” apparatus, the apparatus comprising:
a control moment gyroscope “CMG” including
a first transverse gimbal assembly,
a central mass that produces a voltage potential, and
a second gimbal assembly rotationally connected to the first transverse gimbal assembly,
wherein the first transverse gimbal assembly is rotationally connected to the central mass at a first position of the first transverse gimbal assembly and a second position of the first transverse gimbal assembly along a first axis of rotation and
wherein the central mass is configured to spin about the first axis of rotation and the first transverse gimbal assembly is configured to rotate about a second axis of rotation at a first position of the second gimbal assembly;

a first conductive bearing at the first position of the first transverse gimbal assembly, wherein the first conductive bearing rotationally connects the central mass with the first position of the first transverse gimbal assembly along the first axis of rotation; and
a second conductive bearing at the second position of the first transverse gimbal assembly, wherein the second conductive bearing rotationally connects the central mass with the second position of the first transverse gimbal assembly along the first axis of rotation,
wherein the first conductive bearing and second conductive bearing are in signal communication with the central mass,
wherein the central mass is a power source that includes a plurality of layers, and
wherein all of the layers of the plurality of layers are in signal communication to each other such that every pair of adjacent layers within the plurality of layers are electrically connected in series.

2. The apparatus of claim 1 , wherein each layer of the plurality of layers is a capacitive disk or a disk having a battery cell.

3. The apparatus of claim 1 , wherein each layer of the plurality of layers may have a layer thickness equal to between approximately 0.05 cm to approximately 2.0 cm.

4. The apparatus of claim 2 , wherein each layer of the plurality of layers is a battery cell chosen from the group consisting of a nickel-metal hydride battery cell “NiMH”, lithium-ion “Li-ion” battery cell, and nickel cadmium “NiCd” battery cell.

5. The apparatus of claim 4 , wherein the central mass is one of
a cylindrical central mass, wherein each layer of the plurality of layers is configured as a constant-diameter disk, and
a spherical central mass, wherein the plurality of layers includes a plurality of variable-diameter disks.

6. The apparatus of claim 1 , wherein a positive terminal is in signal communication with the first conductive bearing and a negative terminal is in signal communication with the second conductive bearing.

7. The apparatus of claim 2 , further including a high-rate motor coupled to the central mass and the first transverse gimbal assembly, wherein the high-rate motor is configured to spin the central mass at a high rate along the first axis of rotation.

8. The apparatus of claim 7 , furthering including a torque motor coupled to the first transverse gimbal assembly and the second gimbal assembly, wherein the torque motor is configured to control the rotation of the first transverse gimbal assembly along the second axis of rotation.

9. The apparatus of claim 8 , further including
a rate sensor attached to the first transverse gimbal assembly, wherein the rate sensor is configured to determine a rotation speed of central mass when the central mass is spinning along the first axis of rotation and
an angular displacement sensor attached to the second gimbal assembly, wherein the angular displacement sensor is configured to determine an angle of deflection of the first transverse gimbal assembly relative to the second gimbal assembly as the first transverse gimbal assembly rotates along the second axis of rotation.

10. The apparatus of claim 9 , wherein the HPCMG is attached to a housing of a vehicle, wherein the vehicle is chosen from the group consisting of a submersible marine vehicle, a surface marine vehicle, an aircraft, and a spacecraft.

Assignees

• Boeing Co

Inventors

• Veto Christopher C

Classifications

• G01C19/10 Primary

  Power supply · CPC title

• B64G1/425

  Power storage · CPC title

• B64G1/421

  Non-solar power generation · CPC title

• B63B39/04 Primary

  to decrease vessel movements by using gyroscopes directly · CPC title

• B64G1/285

  using momentum wheels · CPC title