GNSS and inertial navigation system utilizing relative yaw as an observable for an ins filter

Patent metadata

Field	Value
Publication number	US-9791575-B2
Application number	US-201615007866-A
Country	US
Kind code	B2
Filing date	Jan 27, 2016
Priority date	Jan 27, 2016
Publication date	Oct 17, 2017
Grant date	Oct 17, 2017

Abstract

A GNSS/INS navigation system includes an INS filter that uses relative yaw values as an observable for attitude updates. The system calculates the relative yaw values based on carrier phase measurements, e.g., phase windup measurements, of GNSS signals received at a system GNSS antenna. The use of the relative yaw values as an observable in the INS filter allows the system to improve estimates of associated biases, and also to continue to estimate the associated biases in low dynamic environments.

First claim

What is claimed is:

1. An inertial navigation system (INS)/global navigation satellite system (GNSS) navigation system comprising
a GNSS subsystem including a GNSS receiver and a GNSS antenna,
an INS subsystem including an inertial measurement unit and an INS filter, and
a relative yaw subsystem configured to calculate relative yaw values based on phase windup measurements of GNSS satellite signals received by the GNSS antenna, the relative yaw subsystem providing the relative yaw values to the INS subsystem
the INS subsystem operating the INS filter to determine an updated attitude based on using inertial measurements of the inertial measurement unit and the relative yaw values as an observable of the updated attitude.

2. The INS/GNSS navigation system of claim 1 , wherein the INS subsystem uses the relative yaw values to aid in estimating biases associated with the inertial measurement unit.

3. The INS/GNSS navigation system of claim 2 , wherein the inertial measurement unit includes gyroscopes and the relative yaw values are utilized to estimate gyroscope biases.

4. The INS/GNSS navigation system of 1 , wherein
the INS/GNSS navigation system time tags the inertial measurements and the relative yaw values, and
the INS subsystem utilizes position and orientation related information associated with corresponding time tags.

5. The INS/GNSS navigation system of claim 4 , wherein the time tags are GNSS time.

6. The INS/GNSS navigation system of claim 1 wherein the INS filter is a Kalman filter and the Kalman filter utilizes update measurements associated with orientation information and the corresponding relative yaw values.

7. The INS/GNSS navigation system of claim 1 wherein the navigation system provides navigation information to a vehicle steering device.

8. The INS/GNSS navigation system of claim 1 wherein the navigation system operates in a steady state navigation mode with or without a GNSS position determined by the GNSS subsystem when the calculated relative yaw values are available.

9. The INS/GNSS navigation system of claim 1 wherein the INS subsystem utilizes attitude updates determined from the relative yaw values to provide an observation of an attitude error state of the INS subsystem.

10. The INS/GNSS navigation system of claim 1 wherein the INS subsystem utilizes attitude updates determined using the relative yaw values over multiple measurement cycles to reduce an associated variance.

11. An inertial navigation system (INS) subsystem of an INS/global navigation satellite system (GNSS) navigation system, the INS comprising:
a relative yaw subsystem configured to calculate relative yaw values based on phase windup measurements of GNSS signals received at an antenna of the INS/GNSS navigation system;
an inertial measurement unit (IMU) configured to read data associated with acceleration and orientation of the INS/GNSS navigation system, wherein the data is utilized to produce measurements that include at least an attitude of the INS/GNSS navigation system; and
an INS filter configured to update the attitude of the INS/GNSS navigation system using the relative yaw values as observables.

12. The INS subsystem of claim 11 , wherein the INS subsystem is configured to receive GNSS position, covariance information, and GNSS observables from a GNSS subsystem of the INS/GNSS navigation system.

13. The INS subsystem of claim 12 , wherein the INS filter is further configured to utilize the measurements, relative yaw values, the GNSS position, the covariance information, and the GNSS observables to determine INS-based position, velocity, and attitude.

14. The INS subsystem of claim 11 , wherein the INS subsystem uses the relative yaw values to aid in estimating biases associated with the measurements produced by the IMU.

15. The INS subsystem of claim 14 , wherein the IMU is further configured to estimate gyroscope biases, associated with one or more gyroscopes of the IMU, utilizing the relative yaw values.

16. The INS subsystem of claim 11 , wherein the measurements and the relative yaw values are time tagged, and wherein the INS subsystem is configured to utilize position and orientation information associated with corresponding time tags.

17. A method, comprising:
calculating, by a relative yaw subsystem of an inertial navigation system (INS) subsystem of an INS/global navigation satellite system (GNSS) navigation system, relative yaw values based on phase windup measurements of GNSS signals received at an antenna of the INS/GNSS navigation system;
reading, by an inertial measurement unit (IMU), data associated with acceleration and orientation of the INS/GNSS navigation system, wherein the data is utilized to produce measurements that include at least an attitude of the INS/GNSS navigation system; and
updating, by an INS filter, the attitude of the INS/GNSS navigation system using the relative yaw values as observables.

18. The method of claim 17 , further comprising receiving, by the INS subsystem, GNSS position, covariance information, and GNSS observables from a GNSS subsystem of the INS/GNSS navigation system.

19. The method of claim 18 , further comprising utilizing, by the INS filter, the measurements, the relative yaw values, the GNSS position, the covariance information, and the GNSS observables to determine INS-based position, velocity, and attitude.

20. The method of claim 17 , further comprising utilizing the relative yaw values to aid in estimating biases associated with the measurements produced by the IMU.

Assignees

• Novatel Inc

Inventors

• Bobye Michael

Classifications

• G01C21/18

  Stabilised platforms, e.g. by gyroscope · CPC title

• B62D6/003

  in order to control vehicle yaw movement, i.e. around a vertical axis (B62D6/007 takes precedence) · CPC title

• G01S19/47 Primary

  the supplementary measurement being an inertial measurement, e.g. tightly coupled inertial · CPC title

• G01S19/53

  Determining attitude · CPC title

• G01C21/165

  combined with non-inertial navigation instruments · CPC title