Methods for approximate inertial sensor bias self-calibration

Patent metadata

Field	Value
Publication number	US-12031841-B2
Application number	US-202217732187-A
Country	US
Kind code	B2
Filing date	Apr 28, 2022
Priority date	Apr 28, 2022
Publication date	Jul 9, 2024
Grant date	Jul 9, 2024

Abstract

A method and system for providing gyroscope bias self-calibration are described herein. The method comprises powering on one or more gyroscopes; after a predetermined first period of time, and upon determining that the one or more gyroscopes is stationary, measuring input rates of rotation during a predetermined second period of time; and determining an average rate of rotation for each gyroscope channel based upon the measured input rates of rotation during the predetermined second period of time. After determining the average rate of rotation and after the predetermined second period of time, the method further comprises commencing additional measurements by the one or more gyroscopes; determining calibrated gyroscope measurements by subtracting the average rate of rotation from each of the additional measurements; and providing, at the output of the one or more gyroscopes, the calibrated gyroscope measurements.

First claim

What is claimed is:

1. A method comprising:
powering on one or more gyroscopes;
after a predetermined first period of time, and upon determining that the one or more gyroscopes is stationary, measuring input rates of rotation during a predetermined one or more additional periods of time;
determining an average rate of rotation for each gyroscope channel based upon the measured input rates of rotation during the predetermined one or more additional periods of time, wherein a value of the average rate of rotation corresponds to an average gyroscope bias shift and is saved as a zero-order offset;
adjusting the zero-order offset based on one or more temperature variations, wherein the zero-order offset is adjusted using a polynomial model of gyroscope bias as a function of temperature (gyro bias (T)) expressed as:
gyro bias ( T )= Wo+W 1* T+W 2* T 2 +W 3* T 3
where Wo is the zero-order offset,
W1, W2, and W3 are coefficients of a 3 rd order polynomial that represent temperature dependent gyroscope bias terms, and
T is a temperature having a value that is measured at each of the predetermined periods of time;

after determining the average rate of rotation and after the predetermined one or more additional periods of time, commencing additional measurements by the one or more gyroscopes;
determining calibrated gyroscope measurements by subtracting the average rate of rotation, as a function of temperature, from each of the additional measurements; and
providing, at the output of the one or more gyroscopes, the calibrated gyroscope measurements.

2. The method of claim 1 , wherein determining that the one or more gyroscopes is stationary comprises determining that the input rate of each gyroscope is less than or equal to Earth's spin-rate.

3. The method of claim 1 , further comprising:
determining whether the average rate of rotation exceeds a threshold rotation rate level; and
if the average rate of rotation exceeds the threshold rotation rate level, then determining the calibrated gyroscope measurements by subtracting the average rate of rotation from each of the additional measurements.

4. The method of claim 3 , wherein a value of the average rate of rotation that exceeds the threshold rotation rate level corresponds to an average bias shift and is saved as a zero-order offset.

5. The method of claim 1 , wherein the one or more gyroscopes is implemented in an inertial measurement unit (IMU) onboard a vehicle.

6. The method of claim 5 , wherein the one or more gyroscopes in the IMU includes a set of three gyroscopes having three mutually orthogonal gyroscope axes.

7. A method for calibrating at least one gyroscope in an inertial measurement unit (IMU), the method comprising:
powering on the IMU;
after a predetermined first period of time, and upon determining that the IMU is stationary, measuring input rates of rotation during a predetermined second period of time;
determining an average rate of rotation for each gyroscope in the IMU based upon the measured input rates of rotation during the predetermined second period of time, wherein a value of the average rate of rotation corresponds to an average gyroscope bias shift and is saved as a zero-order offset;
after determining the average rate of rotation and after the predetermined second period of time, commencing additional measurements by the IMU;
determining whether the average rate of rotation exceeds a minimum desired adjustment threshold rotation rate level;
if the average rate of rotation exceeds the minimum desired adjustment threshold rotation rate level:
computing calibrated gyroscope measurements by subtracting the average rate of rotation from each of real time IMU measurements; and
providing at the output of the at least one gyroscope, the calibrated gyroscope measurements;

if the average rate of rotation does not exceed the minimum desired adjustment threshold rotation rate level:
providing at the output of the at least one gyroscope, only the real time IMU measurements.

8. The method of claim 7 , wherein determining that the IMU is stationary comprises determining that the input rate of each gyroscope is less than or equal to about 15 degrees per hour.

9. The method of claim 7 , wherein the zero-order offset is saved in a status word of the IMU.

10. The method of claim 7 , wherein the IMU is onboard a vehicle.

11. The method of claim 10 , wherein the vehicle comprises an aircraft, or a dynamic object using the IMU for attitude determination.

12. A system comprising:
an inertial measurement unit (IMU) including at least one gyroscope and at least one accelerometer, the IMU operative to generate attitude and inertial data;
at least one processor operatively coupled to the IMU; and
a processor readable medium including instructions to cause the at least one processor to perform a method for providing calibrated measurements at an output of the at least one gyroscope;
wherein during a calibration event, with the IMU assumed to be static, the method comprises:
powering on the IMU and starting a calibration timer;
determining an average rate of rotation for each gyroscope in the IMU based upon measured input rates of rotation, wherein a value of the average rate of rotation corresponds to an average gyroscope bias shift; and
powering off the IMU, stopping the calibration timer, and saving a calibration time value;
wherein the average gyroscope bias shift is saved as a zero-order offset;

wherein during a mission event, with the IMU assumed to be dynamic, the method comprises:
powering on the IMU, and reading a mission timer to determine a mission time value;
determining whether the mission time value substantially corresponds to the calibration time value; and
applying the zero-order offset to gyroscope measurements from the IMU when the mission time value substantially corresponds to the calibration time value.

13. The system of claim 12 , wherein the IMU is onboard a vehicle.

14. The system of claim 13 , wherein the inertial data generated by the IMU includes acceleration data and attitude data for the vehicle.

15. The system of claim 13 , wherein the vehicle is an aircraft.

16. The system of claim 12 , wherein the zero-order offset is adjusted based on one or more temperature variations.

17. The system of claim 12 , wherein the IMU is a micro-electro-mechanical systems (MEMS) based IMU.

18. The method of claim 7 , further comprising:
adjusting the zero-order offset based on one or more temperature variations, wherein the zero-order offset is adjusted using a look up table of gyroscope bias as a function of temperature.

19. The method of claim 7 , further comprising:
adjusting the zero-order offset based on one or more temperature variations, wherein the zero-order offset is adjusted using a polynomial model of gyroscope bias as a function of temperature.

20. The method of claim 7 , wherein the calibrated gyroscope measurements are limited by a maximum correction amount per unit time.

Assignees

• Honeywell Int Inc

Inventors

• Hanson Timothy J
• Winegar Keith F

Classifications

• G01C23/00

  Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration · CPC title

• G01C21/16 Primary

  by integrating acceleration or speed, i.e. inertial navigation · CPC title

• G01C19/42

  for indicating rate of turn; for integrating rate of turn · CPC title

• G01C25/005 Primary

  initial alignment, calibration or starting-up of inertial devices · CPC title

• G01C21/183

  Compensation of inertial measurements, e.g. for temperature effects · CPC title