Low authority GPS aiding of navigation system for anti-spoofing

• US 9,513,129 B2
• Filed: 09/05/2013
• Issued: 12/06/2016
• Est. Priority Date: 04/04/2008
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Wang, Hanching Grant
• Primary Examiner(s): YU, ARIEL J
• Application Number:
  US14/019,004
• Publication Number:
  US 20140005938A1
• Time in Patent Office: 1,188 Days
• Field of Search: None
• US Class Current: 1/1
• CPC Class Codes: G01C 21/165 combined with non-inertial navigation instruments
• CPC Class Codes: G01S 19/215 issues related to spoofing
• CPC Class Codes: G01S 19/47 the supplementary measurement being an inertial measurement, e.g. tightly coupled inertial

Abstract

A method and apparatus for generating navigation solutions. A global positioning system based navigation solution unit; an inertial navigation solution unit; a correction unit, a limiter, and an adding unit. The global positioning system based navigation solution unit is capable of generating a first navigation solution. The inertial navigation solution unit is capable of generating a second navigation solution. The correction unit is capable of generating a raw correction. The limiter is capable of selectively modifying the raw correction to fall within a selected range of corrections to form a correction. The adding unit is capable of adding the correction to the second navigation solution to form a navigation solution.

Claims

1. A method for forming a navigation solution, the method comprising:

generating, by an inertial navigation solution unit, the inertial navigation solution using inertial sensor measurements;

generating, by a blended global positioning system and inertial navigation solution unit, a blended global positioning system and inertial navigation system navigation solution using a set of global positioning system receiver measurements and a set of inertial sensor measurements;

computing, by a processor, a raw global positioning system navigation correction as the difference between inertial navigation solution and blended global positioning system and inertial navigation system navigation solution;

converting the raw global positioning system navigation correction from an earth centered inertial reference frame to a navigation reference frame;

storing the raw global positioning system navigation correction with a time stamp;

retrieving a raw global positioning system navigation correction at a specified past time stamp;

removing the raw global positioning system navigation correction from a correction storage unit;

computing, by the processor, a low authority global positioning system correction by applying a limit upon the retrieved raw global positioning system navigation correction; and

adding, by the processor, the inertial navigation solution and the low authority global positioning system correction to form the navigation solution.

2. The method of claim 1, wherein the storing step comprises:

storing the raw global positioning system navigation correction with the time stamp in earth centered inertial reference frame.

3. The method of claim 1, wherein the retrieving step further comprises:

propagating the retrieved raw global positioning system navigation correction from the specified past time stamp to a current time in earth centered inertial reference frame to form a propagated raw global positioning system navigation correction; and

converting the propagated raw global positioning system navigation correction from the earth centered inertial frame to a navigation reference frame.

4. The method of claim 1, further comprising:

determining, using an integrity monitor, whether one or more of spoofing, meaconing, or corruption has occurred on data generated by the global positioning system receiver; and

in response to the determination, retrieving the raw global positioning system navigation correction at the specified past time stamp.

5. A method for forming a navigation solution, the method comprising:

generating, by an inertial navigation solution unit, an inertial navigation solution using a set of inertial sensor measurements;

generating, by a blended global positioning system and inertial navigation solution unit, a blended global positioning system and inertial navigation system navigation solution using a set of global positioning system receiver measurements and the set of inertial sensor measurements;

computing, by a processor, a raw global positioning system navigation correction as the difference between inertial navigation solution and blended global positioning system and inertial navigation system navigation solution;

converting the raw global positioning system navigation correction from an earth centered inertial reference frame to a navigation reference frame;

storing the raw global positioning system navigation correction with a time stamp;

generating a global positioning system-only navigation solution;

monitoring for global positioning system spoofing;

responsive to detecting the global positioning system spoofing, retrieving a selected raw global positioning system navigation correction at a past time before the global positioning system spoofing was detected;

removing the raw global positioning system navigation correction from a correction storage unit;

computing, by the processor, a low authority global positioning system correction by applying a limit upon the retrieved raw global positioning system navigation correction; and

adding, by the processor, the inertial navigation solution and the low authority global positioning system correction to form the navigation solution.

6. The method of claim 5, wherein the monitoring step comprises:

monitoring for global positioning system spoofing using the global positioning system only navigation solution, the inertial navigation solution, the blended global positioning system and inertial navigation system navigation solution, global positioning system receiver provided health data, and derived global positioning system health data.

7. The method of claim 5, wherein the retrieving step comprises:

retrieving a selected raw global positioning system navigation correction at a past time before the global positioning system spoofing was detected, wherein retrieving the selected raw global positioning system navigation correction at a past time before the global positioning system spoofing was detected allows the low authority global positioning system-aided navigation solution to go back in time to remove the unwanted correction during which the global positioning system is spoofed.

8. The method of claim 5, wherein the step of computing a low authority global positioning system correction by applying a limit upon the retrieved raw global positioning system navigation correction comprises:

computing a low authority global positioning system correction by applying a limit upon the retrieved raw global positioning system navigation correction associated with a past time stamp and apply the limit at a current time.

9. An apparatus comprising:

a global positioning system based navigation solution unit capable of generating a first navigation solution;

a inertial navigation solution unit capable of generating a second navigation solution;

a correction unit capable of generating a raw correction by computing a raw correction as the difference between the global positioning system based navigation solution and the inertial navigation solution;

a correction storage unit capable of converting the raw global positioning system navigation correction from an earth centered inertial reference frame to a navigation reference frame and storing raw corrections in association with a set of time stamps in a manner that allows a selected raw correction to be retrieved from a prior time for use by an adding unit in placed of a current raw correction;

removing the raw global positioning system navigation correction from the correction storage unit;

a limiter capable of selectively modifying the raw correction to fall within a selected range of corrections to form a correction; and

the adding unit capable of adding the correction retrieved from the prior time to the second navigation solution to form a navigation solution.

10. The apparatus of claim 9 further comprising:

a global positioning system receiver; and

an inertial navigation system unit.