Multi coriolis structured gyroscope

Patent metadata

Field	Value
Publication number	US-10907965-B2
Application number	US-201916553785-A
Country	US
Kind code	B2
Filing date	Aug 28, 2019
Priority date	Oct 30, 2015
Publication date	Feb 2, 2021
Grant date	Feb 2, 2021

Abstract

A resonator paradigm, where the resonator structure is made up of a very large number of small, coupled Coriolis sensitive units arranged in a periodic 1D or 2D (and, possibly, in the future, 3D) structure to create a Coriolis-sensitive fabric that supports a large number of Coriolis-coupled supermodes. Such a fabric can be shaped into arbitrary waveguides that propagate either pulses of excitation that are Coriolis-coupled, thus enabling an acoustic version of a FOG-type gyroscope (where a pulse of excitation travels along a passive waveguide and it's phase/time delay is measured), or support multiple stationary Coriolis-coupled vibration modes analogous to optical laser modes in an RLG where counter-propagating modes of oscillation are maintained at constant amplitude via a continuous addition of energy.

First claim

What is claimed is:

1. A gyroscope comprising:
a resonator having a sensor area and an array of coupled sensor units arranged in a periodic structure forming a Coriolis-sensitive fabric configured to sense a Coriolis effect associated with movement of the gyroscope and a signal generation unit located at an excitation point within the sensor area and configured to output a first signal and a second signal, the first signal traveling through a first portion of the sensor units along a first travel path from the excitation point to a first measurement location within the sensor area and the second signal traveling through a second portion of the sensor units along a second travel path from the excitation point to a second measurement location within the sensor area;
a first vibration pick-off point located at the first measurement location;
a second vibration pick-off point located at the second measurement location; and
control electronics coupled with the first vibration pick-off point and the second vibration pick-off point, the control electronics configured to:
receive the first signal from the first measurement location,
receive the second signal from the second measurement location, and
determine a comparative signal characteristic based on the received first signal and the second signal;

wherein the first signal propagates along the first travel path in a first direction counter to a second direction in which the second signal propagates along the second travel path; and
wherein the periodic structure comprises a two-dimensional structure.

2. The gyroscope of claim 1 , wherein the first signal and the second signal form counter-propagating mode pairs, and wherein the comparative signal characteristic is a relative phase of the counter-propagating mode pairs.

3. The gyroscope of claim 1 , wherein the comparative signal characteristic is a phase delay between the first signal and the second signal at the first measurement location and the second measurement location, respectively.

4. The gyroscope of claim 1 , wherein the resonator comprises a resonator body, and wherein the resonator body constitutes a proof mass.

5. The gyroscope of claim 1 , wherein the fabric isolates the resonator from external stress and vibration.

6. The gyroscope of claim 1 , wherein the sensor area is 5 millimeters by 5 millimeters, and wherein the array of coupled sensor units is square and comprises 1,000 sensor units×1,000 sensor units.

7. The gyroscope of claim 1 , wherein the comparative signal characteristic is a time delay between the first signal and the second signal at the first measurement location and the second measurement location, respectively.

8. The gyroscope of claim 1 , further comprising at least one amplifying gain region including tuning electrodes configured to increase an amplitude of the counter-propagating first signal and the second signal.

9. The gyroscope of claim 1 , wherein the first signal and the second signal are each pulses of excitation, and wherein the array of coupled sensor units are electromechanically coupled.

10. The gyroscope of claim 9 , wherein the comparative signal characteristic is a phase delay between the first signal and the second signal at the first measurement location and the second measurement location, respectively.

11. A gyroscope comprising:
a resonator body having a sensor area and an array of coupled sensor units comprising a first plurality of sensor units arranged in a periodic structure forming a Coriolis-sensitive fabric configured to sense a Coriolis effect associated with movement of the gyroscope and a second plurality of sensor units located at an excitation point within the sensor area and configured to output a first signal and a second signal, the first signal traveling through a first portion of the first plurality of sensor units along a first travel path from the excitation point to a first measurement location within the sensor area and the second signal traveling through a second portion of the first plurality of sensor units along a second travel path from the excitation point to a second measurement location within the sensor area;
a first vibration pick-off point located at the first measurement location;
a second vibration pick-off point located at the second measurement location; and
control electronics coupled with the first vibration pick-off point and the second vibration pick-off point, the control electronics configured to:
receive the first signal from the first measurement location,
receive the second signal from the second measurement location,
determine a comparative signal characteristic between the first signal and the second signal; and
determine a rotation of the gyroscope based on the determined comparative signal characteristic;

wherein the first signal propagates along the first travel path in a clockwise direction counter to a counter-clockwise direction in which the second signal propagates along the second travel path; and
wherein the periodic structure comprises a two-dimensional structure.

12. The gyroscope of claim 11 , wherein the control electronics are further configured to determine a rotation of the gyroscope based on the determined comparative signal characteristic.

13. The gyroscope of claim 11 , wherein the first signal and second signal form counter-propagating mode pairs, and wherein the comparative signal characteristic is a relative phase of the counter-propagating mode pairs.

14. The gyroscope of claim 11 , further comprising at least one amplifying gain region including tuning electrodes configured to increase an amplitude of the first signal between the excitation point and the first measurement location.

15. The gyroscope of claim 11 , wherein the resonator comprises a resonator body, and wherein the resonator body constitutes a proof mass.

16. The gyroscope of claim 11 , wherein the fabric isolates the resonator from external stress and vibration.

17. The gyroscope of claim 11 , wherein the sensor area is 5 millimeters by 5 millimeters, and wherein the array of coupled sensor units is square and comprises 1,000 sensor units×1,000 sensor units.

18. The gyroscope of claim 11 , wherein the first signal and the second signal are each pulses of excitation, and wherein the array of coupled sensor units are electromechanically coupled.

Assignees

• Garmin Int Inc

Inventors

• Shcheglov Kirill V
• Smukowski David
• Cheng Yingxiang
• Maggipinto Nolan F

Classifications

• G01C19/64

  Gyrometers using the Sagnac effect, i.e. rotation-induced shifts between counter-rotating electromagnetic beams · CPC title

• G01C19/5712

  the devices involving a micromechanical structure · CPC title

• G01C19/66

  Ring laser gyrometers · CPC title

• G01C19/574 Primary

  the devices having two sensing masses in anti-phase motion · CPC title

• G01C19/5684 Primary

  the devices involving a micromechanical structure · CPC title