Electronic bias compensation for a gyroscope

• US 9,417,066 B2
• Filed: 01/11/2012
• 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:
  US13/348,263
• Publication Number:
  US 20130179105A1
• Time in Patent Office: 1,679 Days
• Field of Search: 702/87, 738/613.56
• US Class Current: 1/1
• 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 compensating for bias of a gyroscope. In one embodiment, bias measurements for a plurality of drive angles are generated using the gyroscope. A set of equations for the bias 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. A set of values for the set of parameters is identified using the bias measurements and the set of equations.

Claims

1. A method for compensating measurements of 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 the bias 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

subtracting, using the computer system, the estimated bias from the measurements to substantially compensate for the bias of the gyroscope.

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

identifying the set of equations for the bias of the gyroscope using the model for the motion of the gyroscope and an assumption that an inertial rate for the gyroscope is substantially zero.

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

identifying the model for the motion of the gyroscope;

modifying the model for the motion of the gyroscope based on the assumption that the inertial rate for the gyroscope is substantially zero to form a modified model; and

identifying the set of equations for the bias of the gyroscope using the modified model for the motion of the gyroscope.

4. The method of claim 2, wherein the step of identifying the set of equations for the bias of the gyroscope using the model for the motion of the gyroscope and the assumption that the inertial rate for the gyroscope is substantially 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 substantially 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 substantially zero.

5. The method of claim 1 further comprising:

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

6. The method of claim 1,

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.

7. The method of claim 1, 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 a drive axis for the gyroscope and a sense axis for the gyroscope, and an azimuth angle of the drive axis with respect to a first axis.

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

9. An apparatus comprising:

a gyroscope; and

a compensation system configured to;

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

identify a set of equations for the bias 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;

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

select a drive angle in the plurality of drive angles that reduce 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

subtract the estimated bias from the measurements to substantially compensate for the bias of the gyroscope.

10. The apparatus of claim 9, wherein in being configured to identify the set of equations for the bias of the gyroscope using the model for the motion of the gyroscope, the compensation system is configured to identify the set of equations for the bias of the gyroscope using the model for the motion of the gyroscope and an assumption that an inertial rate for the gyroscope is substantially zero.

11. The apparatus of claim 10, wherein in being configured to identify the set of equations for the bias of the gyroscope using the model for the motion of the gyroscope and the assumption that the inertial rate for the gyroscope is substantially zero, the compensation system is configured to:

identify the model for the motion of the gyroscope;

modify the model for the motion of the gyroscope based on the assumption that the inertial rate for the gyroscope is substantially zero to form a modified model; and

identify the set of equations for the bias of the gyroscope using the modified model for the motion of the gyroscope.

12. The apparatus of claim 10, wherein in being configured to identify the set of equations for the bias of the gyroscope using the model for the motion of the gyroscope and the assumption that the inertial rate for the gyroscope is substantially zero, 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 the assumption that the inertial rate for the gyroscope is substantially 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 substantially zero.

13. The apparatus of claim 9, wherein the compensation system is further configured to estimate the bias of the gyroscope at a selected drive angle using the set of equations with the set of values for the set of parameters to form the estimated bias.

14. The apparatus of claim 9, 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.