INTEGRITY OF DIFFERENTIAL GPS CORRECTIONS IN NAVIGATION DEVICES USING MILITARY TYPE GPS RECEIVERS

• US 20090322598A1
• Filed: 06/26/2008
• Published: 12/31/2009
• Est. Priority Date: 06/26/2008
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Morgan, Kenneth S., Fly, Brian E., Ignac, Martin P., Waid, James D.
• Granted Patent: US 7,940,210 B2
• Time in Patent Office: Days
• US Class Current: 342/357.48
• CPC Class Codes: G01S 19/20 Integrity monitoring, fault detection or fault isolation of space segment
• CPC Class Codes: G01S 19/215 issues related to spoofing
• CPC Class Codes: G01S 19/23 Testing, monitoring, correcting or calibrating of receiver elements
• CPC Class Codes: G01S 19/41 Differential correction, e.g. DGPS [differential GPS]

Abstract

A method and apparatus for calculating corrections to a navigation solution based on differential GPS data includes receiving GPS ephemeris from at least three GPS satellites. A PVT solution is resolved from the GPS ephemeris. The PVT solution includes a Circular Error Probable (CEP). Differential GPS data for calculating the corrections to the PVT solution is received. A corrected PVT solution is then based upon the differential GPS data. The corrected PVT solution is compared to an area defined by the CEP. Where the corrected PVT solution is not within the area, the corrected PVT solution is rejected in favor of the PVT solution for determining an accurate navigational solution.

Claims

1. A system processor for a navigation system, comprising:

a GPS ranging system operable to receive GPS ephemeris from at least three GPS satellites;

a DGPS data receiver operable to receive differential GPS data for correction of the GPS ephemeris;

at least one Kalman filter operating alone or in combination, the at least one Kalman filter operable to calculate a navigation solution based on the GPS ephemeris received the GPS ranging system and to calculate a corrected navigation solution based upon the differential GPS data, wherein the Kalman filter uses the differential GPS data;

a mode logic operable to calculate the navigation solution operable to determine whether to select the navigation solution based upon the GPS ephemeris or the corrected navigation solution.

2. The system of claim 1, wherein the mode logic includes activation of an alert signal.

3. The system of claim 2, wherein the alert signal includes modifying an icon on a display.

4. The system of claim 2, wherein the alert signal includes a light.

5. The system of claim 1, wherein the navigation solution includes a three-dimensional position, three-dimensional velocity, and three-dimensional attitude solution.

6. A method of calculating corrections to a navigation solution based on accurate data, comprising:

receiving GPS ephemeris from at least three GPS satellites;

resolving a PVT solution from the GPS ephemeris, the PVT solution including a CEP;

receiving differential GPS data for calculating the corrections to the PVT solution calculating a corrected PVT solution based upon the differential GPS data;

comparing the corrected PVT solution to an area defined by the CEP; and

rejecting the corrected PVT solution where the corrected PVT solution is not within the area.

7. The method of claim 6, wherein the rejecting of the corrected PVT solution includes activating an alert.

8. The method of claim 7, wherein the activating of an alert includes modifying an icon in a display.

9. The method of claim 7, wherein the activating of an alert includes generation of a display including words and figures indicative of rejection of the differential GPS data.

10. The method of claim 7, wherein the activation of an alert includes an aural alert.