REAL-TIME HIGH ACCURACY POSITION AND ORIENTATION SYSTEM

• US 20090093959A1
• Filed: 10/04/2007
• Published: 04/09/2009
• Est. Priority Date: 10/04/2007
• Status: Abandoned Application

• Current Assignee: Trimble Navigation Limited (Trimble Inc.)
• Original Assignee: Trimble Navigation Limited (Trimble Inc.)
• Inventors: Hutton, Joseph J., Vollath, Ulrich, Scherzinger, Bruno M.
• Application Number:
  US11/867,639
• Publication Number:
  US 20090093959A1
• Time in Patent Office: Days
• US Class Current: 701/215
• CPC Class Codes: G01C 21/1652 with ranging devices, e.g. LIDAR or RADAR
• CPC Class Codes: G01C 21/1656 with passive imaging devices, e.g. cameras
• CPC Class Codes: G01C 21/188 for accumulated errors, e.g. by coupling inertial systems with absolute positioning systems
• CPC Class Codes: G01S 19/44 Carrier phase ambiguity resolution; Floating ambiguity; LAMBDA [Least-squares AMBiguity Decorrelation Adjustment] method

Abstract

A real-time high accuracy position and orientation system (RT-HAPOS) system for a vehicle, such as an aircraft, comprises a global navigation satellite system (GNSS) receiver disposed on the vehicle and an integrated inertial navigation (IIN) module disposed on the vehicle. The GNSS receiver generates GNSS position data indicating approximate positions of the vehicle during a data acquisition period in which the vehicle is moving. The IIN module executes a real-time kinematic (RTK) algorithm during the data acquisition period to generate output position data indicating positions of the vehicle at a greater precision than the GNSS position data, based on the GNSS position data, inertial measurement data acquired on the vehicle during the data acquisition period, and a set of virtual reference station (VRS) observables received during the data acquisition period from a remote source external to the vehicle, where the VRS observables are based on the GNSS position data.

Claims

1. A system comprising:

a GNSS receiver, configured for use on a vehicle, to generate GNSS position data indicative of approximate positions of the vehicle during a data acquisition period in which the vehicle is in motion; and

an integrated inertial navigation (IIN) module, configured for use on the vehicle, to execute an RTK algorithm during the data acquisition period to generate output position data indicative of positions of the vehicle at a greater precision than the GNSS position data, based on the GNSS position data, inertial measurement data acquired on the vehicle during the data acquisition period, and a set of VRS observables received during the data acquisition period from a remote source that is external to the vehicle, where the VRS observables are based on the GNSS position data.

2. A system as recited in claim 1, wherein the IIN module is configured to perform integer carrier phase ambiguity resolution and carrier phase measurements.

3. A system as recited in claim 2, wherein the IIN module is configured to acquire differential GNSS observables measurements.

4. A system as recited in claim 3, wherein the vehicle is an aircraft.

5. A system as recited in claim 1, further comprising:

a transmitter, configured for use on the vehicle, to transmit, during the data acquisition period, the GNSS position data to the remote source; and

a receiver, configured for use on the vehicle, to receive the VRS observables during the data acquisition period.

6. A system as recited in claim 1, wherein the vehicle is an aircraft.

7. A system as recited in claim 6, further comprising:

a camera to acquire images for aerial photogrammetry during the data acquisition period; and

a processor to reference the images to the output position data.

8. A system as recited in claim 6, further comprising:

a laser ranging device to acquire altitude data during the data acquisition period; and

a processor to reference the altitude data to the output position data.

9. A positioning system for a vehicle, comprising:

an inertial navigation module to generate an inertial navigation solution for the vehicle based on inertial sensor data;

a filter to input the inertial navigation solution and aiding sensor data including rover GNSS data generated on the vehicle, and further to input VRS GNSS data transmitted to the vehicle from a remote source, the filter further to estimate floated carrier phase ambiguities in combinations of rover carrier phase observables and VRS carrier phase observables from the rover GNSS data and the VRS GNSS data; and

an ambiguity resolution module to determine integer ambiguities from the floated ambiguity data and to output the integer ambiguities to the filter;

the filter further to generate and output a position solution for the vehicle based on the integer ambiguities.

10. A positioning system as recited in claim 9, wherein the vehicle is an aircraft. wherein the filter is to construct carrier phase measurements based on the integer ambiguities, and wherein the position solution for the vehicle is based on the carrier phase measurements.

11. A positioning system as recited in claim 9, wherein the filter comprises a Kalman filter.

12. A positioning system as recited in claim 9, further comprising:

an error controller to translate inertial navigation errors and inertial sensor errors estimated by the filter into corrections and to provide the corrections to the inertial navigation module; and

13. A positioning system as recited in claim 9, further comprising:

an error controller to translate inertial navigation errors and inertial sensor errors estimated by the filter into corrections and to provide the corrections to the inertial navigation module; and

wherein the filter comprises a Kalman filter and is further to construct carrier phase measurements based on the integer ambiguities, and wherein the position solution for the vehicle is based on the carrier phase measurements.

14. A georeferencing system comprising:

a GNSS receiver, disposed on an aircraft, to generate GNSS position data indicative of approximate positions of an aircraft during a data acquisition period;

a transmitter, disposed on the aircraft, to transmit, during the data acquisition period, the GNSS position data to a remote source that is external to the aircraft;

a receiver, disposed on the aircraft, to receive during the data acquisition period a set of VRS observables from the remote source, the VRS observables having been computed based on the GNSS data;

an integrated inertial navigation (IIN) module, disposed on the aircraft, to input the GNSS position data and inertial measurement data acquired on the aircraft during the data acquisition period, and further to input during the data acquisition period the VRS observables, the IIN module further to acquire differential GNSS observables measurements and to perform integer carrier phase ambiguity resolution and carrier phase measurements during the data acquisition period, and to generate output position data indicative of precise positions of the aircraft based on the VRS observables, the GNSS position data and the inertial measurement data;

a data acquisition device, disposed on the aircraft, to acquire data about features that are external to the vehicle, during the data acquisition period; and

a processor, disposed on the aircraft, to georeference the data about features that are external to the vehicle with the output position data.

15. A georeferencing system as recited in claim 14, wherein the data acquisition device is a camera, the data about features that are external to the vehicle includes image data of said features, and the processor is to georeference the image data with the output position data for photogrammetry.

16. A georeferencing system as recited in claim 14, wherein the data acquisition device is a laser ranging device, and the data about features that are external to the vehicle includes altitude data about said features, and the processor is to georeference the altitude data with the output position data for laser altimetry.

17. A system comprising:

means disposed on a vehicle for obtaining differential GNSS observables measurements;

means disposed on the vehicle for obtaining carrier phase measurements and for performing integer carrier phase ambiguity resolution; and

means for integrating observables measurements from a plurality of fixed GNSS reference receivers arranged in a network to correct for atmospheric delays in the differential GNSS observables measurements when a minimum distance between the vehicle and the nearest one of the reference receivers to the vehicle exceeds a predetermined distance.

18. A system as recited in claim 17, wherein the vehicle is an aircraft.

19. A system as recited in claim 18, wherein the predetermined distance is approximately 20 kilometers.

20. A method comprising:

on a vehicle, obtaining differential GNSS observables measurements;

on the vehicle, obtaining carrier phase measurements and for performing integer carrier phase ambiguity resolution; and

on the vehicle, integrating observables measurements from a plurality of fixed GNSS reference receivers arranged in a network around the vehicle to correct for atmospheric delays in the differential GNSS observables measurements when a minimum distance between the vehicle and the nearest one of the reference receivers to the vehicle exceeds a predetermined distance.

21. A method as recited in claim 20, wherein the vehicle is an aircraft.

22. A method as recited in claim 20, wherein the predetermined distance is approximately 20 kilometers.

23. A method of georeferencing data, the method comprising:

obtaining GNSS position data indicative of approximate positions of the aircraft during a data acquisition period;

transmitting, during the data acquisition period, the GNSS position data to a remote source that is external to the aircraft;

receiving, during the data acquisition period, a set of VRS observables from the remote source, the VRS observables having been computed based on the GNSS data;

performing integer carrier phase ambiguity resolution and carrier phase measurements during the data acquisition period to generate output position data indicative of precise positions of the aircraft based on the VRS observables, the GNSS position data and the inertial measurement data;

using a data acquisition device to acquire data about features that are external to the aircraft, during the data acquisition period; and

georeferencing the data about features that are external to the aircraft with the output position data.

24. A method as recited in claim 23, wherein the data acquisition device is a camera, the data about features that are external to the vehicle includes image data of ground-based features, and the processor is to georeference the image data with the output position data for photogrammetry.

25. A method as recited in claim 23, wherein the data acquisition device is a laser ranging device, and the data about features that are external to the vehicle includes altitude data about said features, and the processor is to georeference the altitude data with the output position data for laser altimetry.