Electronic bias compensation for a gyroscope

• US 9,417,067 B1
• Filed: 02/28/2013
• Issued: 08/16/2016
• Est. Priority Date: 01/11/2012
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Liu, Yong, Challoner, Anthony Dorian
• Primary Examiner(s): Satanovsky, Alexander
• Application Number:
  US13/780,265
• Time in Patent Office: 1,265 Days
• US Class Current: 1/1
• CPC Class Codes: G01C 19/5684 the devices involving a micromechanical structure
• CPC Class Codes: G01C 19/5776 Signal processing not specific to any of the devices covered by groups G01C19/5607 - G01C19/5719
• CPC Class Codes: G01C 25/005 initial alignment, calibration or starting-up of inertial devices

Abstract

A method for simultaneously identifying an inertial rate of a gyroscope and a bias for a gyroscope. A set of equations for an output of the gyroscope is identified using a model for motion of the gyroscope. The set of equations includes a set of parameters for the bias of the gyroscope. The inertial rate of the gyroscope and a set of values for the set of parameters for the bias of the gyroscope are identified using the set of equations and measurements generated by the gyroscope for a plurality of drive angles.

Claims

1. A method for controlling a gyroscope, the method comprising:

operating the gyroscope at a plurality of drive angles to generate measurements of a force rebalance signal, wherein the measurements include a bias;

using a computer system to perform the steps of;

identifying a set of equations for an output of the gyroscope using a model for motion of the gyroscope in which the set of equations includes a set of parameters for the bias of the gyroscope;

estimating a set of values for the set of parameters using the measurements, the set of equations, and an iterative algorithm; and

selecting a drive angle in the plurality of drive angles that reduces an in-quadrature bias of the gyroscope to substantially zero using the set of equations;

operating the gyroscope at the selected drive angle;

forming, using the computer system, an estimated bias using the set of equations and the measurements for the selected drive angle; and

identifying an inertial rate of the gyroscope using the set of equations and measurements generated for the selected drive angle by subtracting the estimated bias from the measurements.

2. The method of claim 1, wherein identifying the set of equations for the output of the gyroscope using the model for the motion of the gyroscope comprises:

identifying the set of equations for the output of the gyroscope using the model for the motion of the gyroscope and an assumption that the inertial rate for the gyroscope is non-zero.

3. The method of claim 2, wherein identifying the set of equations for the output of the gyroscope using the model for the motion of the gyroscope and the assumption that the inertial rate for the gyroscope is non-zero comprises:

identifying a first equation in the set of equations for an in-phase bias of the gyroscope using the model for the motion of the gyroscope and the assumption that the inertial rate for the gyroscope is non-zero; and

identifying a second equation in the set of equations for the in-quadrature bias of the gyroscope using the model for the motion of the gyroscope and the assumption that the inertial rate for the gyroscope is non-zero.

4. The method of claim 1 further comprising:

identifying the set of values for the set of parameters using the set of equations and the measurements generated for the plurality of drive angles.

5. The method of claim 4, wherein identifying the set of values for the set of parameters using the measurements and the set of equations comprises:

identifying the set of values for the set of parameters using the measurements, the set of equations, and the iterative algorithm, wherein the set of parameters includes at least one of a drive axis misalignment angle, a sense axis misalignment angle, a damping azimuth angle, a damping asymmetry term, a difference between natural frequencies of the gyroscope and an azimuth angle of a drive axis with respect to a first natural frequency of vibration axis.

6. The method of claim 4 further comprising:

estimating the bias of the gyroscope at the selected drive angle using the set of equations with the set of values for the set of parameters to form the estimated bias.

7. The method of claim 1, wherein operating the gyroscope at the plurality of drive angles comprises:

operating the gyroscope at the plurality of drive angles, wherein the plurality of drive angles includes angles selected from a range between about 0 degrees and about 360 degrees with respect to a first axis.

8. The method of claim 1, wherein operating the gyroscope at the plurality of drive angles comprises:

operating the gyroscope at a first drive angle for a first drive period;

switching the first drive angle to a second drive angle; and

operating the gyroscope at the second drive angle for a second drive period.

9. The method of claim 1, wherein the gyroscope is a Coriolis vibratory gyroscope.

10. An apparatus comprising:

a gyroscope configured to be operated at a plurality of drive angles; and

a compensation system configured to;

identify a set of equations for an output of the gyroscope using a model for motion of the gyroscope in which the set of equations includes a set of parameters for a bias of the gyroscope;

receive measurements of a force rebalance signal for the plurality of drive angles from the gyroscope, wherein the measurements include the bias;

estimate a set of values for the parameters using the measurements, the set of equations, and an iterative algorithm;

select a drive angle in the plurality of drive angles that reduces an in-quadrature bias of the gyroscope to substantially zero using the set of equations;

operate the gyroscope at the selected drive angle to form an estimated bias using the set of equations and the measurements for the selected drive angle; and

identify an inertial rate of the gyroscope using the set of equations and the measurements generated for the selected drive angle by subtracting the estimated bias from the measurements.

11. The apparatus of claim 10, wherein the compensation system is configured to identify the set of equations for the output of the gyroscope using the model for the motion of the gyroscope and an assumption that the inertial rate for the gyroscope is non-zero.

12. The apparatus of claim 10, wherein in being configured to identify the set of equations for the output of the gyroscope using the model for the motion of the gyroscope, the compensation system is configured to:

identify a first equation in the set of equations for an in-phase bias of the gyroscope using the model for the motion of the gyroscope and an assumption that the inertial rate for the gyroscope is non-zero; and

identify a second equation in the set of equations for the in-quadrature bias of the gyroscope using the model for the motion of the gyroscope and the assumption that the inertial rate for the gyroscope is non-zero.

13. The apparatus of claim 10, wherein the plurality of drive angles includes angles selected from a range between about 0 degrees and about 360 degrees with respect to a first axis.

14. The apparatus of claim 10, wherein the gyroscope further comprises:

a control unit configured to use the set of values identified for the set of parameters in the set of equations by the compensation system to electronically compensate for the bias of the gyroscope.