GPS/IRS global position determination method and apparatus with integrity loss provisions

• US 5,923,286 A
• Filed: 10/23/1996
• Issued: 07/13/1999
• Est. Priority Date: 10/23/1996
• Status: Expired due to Term

• Current Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Original Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Inventors: Divakaruni, Sudhakar P.
• Primary Examiner(s): Tarcza, Thomas
• Assistant Examiner(s): PHAN, DAO LINDA
• Application Number:
  US08/735,764
• Time in Patent Office: 993 Days
• Field of Search: 342/357, 342/450, 342/457, 701/213, 701/214
• US Class Current: 342/357.44
• CPC Class Codes: G01C 21/165 combined with non-inertial navigation instruments
• CPC Class Codes: G01S 19/20 Integrity monitoring, fault detection or fault isolation of space segment
• CPC Class Codes: G01S 19/49 whereby the further system is an inertial position system, e.g. loosely-coupled

Abstract

A system for use with an inertial reference system and a global position receiver for calculating a position error after a loss of integrity by utilizing the global position system values for position and velocity at a time just before the loss of integrity and by utilizing the inertial reference system position modified by the known error in inertial reference system position as it varies with time and the position error as calculated by the global position system velocity extrapolated over the time since integrity loss.

Claims

1. A combined inertial reference system and a satellite positioning system for determining user position comprising:

an inertial reference system employing inertial sensors for providing IRS position and inertial reference information, including IRS velocity information, derived from output information from said inertial sensors;

a satellite positioning system receiver for providing a GPS position solution including a resultant GPS position and resultant GPS velocity information derived form satellite information from signals transmitted from a plurality of satellites;

validation means responsive to at least the number of said plurality of satellites transmitting said satellite information signals for indicating a non-availability time period when said number is below that which is required to provide at least one integrity limit value associated with the accuracy of said GPS solution, as opposed to an integrity time period when said number is sufficient to provide said at least one integrity limit value;

error estimator means for determining velocity and acceleration error estimates associated with said IRS inertial information as a function of said IRS velocity information and said resultant GPS velocity information;

coast position estimator means for determining a first estimated position of the user'"'"'s position during said non-availability time period as function of said velocity and acceleration error estimates occurring at the beginning of said non-availability time period, the elapsed time accumulated since the beginning of said non-availability time period, and the IRS position.

2. The combined inertial reference system and a satellite positioning system of claim 1 further comprising:

IRS/GPS position solution determining means for determining a second estimated position of the user'"'"'s position as a function of a t least said IRS position and inertial information and said resultant GPS position and resultant GPS velocity information;

position selector means for providing as an output thereof said second estimated position for time during an integrity time period, and said first estimated position for time during a non-availability time period.

3. The combined inertial reference system and a satellite positioning system of claim 1 wherein said error estimator means provides a second order filter having as it input the difference between corresponding components of said resultant GPS velocity and said IRS velocity.

4. The combined inertial reference system and a satellite positioning system of claim 3 wherein said error estimator means includes (i) a second order filter having as its input the difference between north direction components of said resultant GPS velocity and said IRS velocity, and as outputs corresponding north direction velocity and acceleration bias values, and (ii) a second order filter having as it input the difference between east direction components of said resultant GPS velocity and said IRS velocity, and as outputs the corresponding east direction velocity and acceleration bias values.

5. An apparatus for determining the position of a vehicle, the apparatus comprising:

a global positioning system (GPS) communicating with a plurality of satellites and providing a GPS position signal;

an inertial reference system (IRS) providing an IRS position signal;

a position estimator providing a hybrid position signal based upon th eGPS position signal and the IRS position signal;

an IRS position estimator providing an estimated IRS position signal based upon the IRS position signal, the velocity of the vehicle, and the acceleration of the vehicle; and

a position selector providing a vehicle position signal, wherein the vehicle position signal corresponds to the hybrid position signal when the GPS position signal is reliable, and wherein the vehicle position signal corresponds to the estimated IRS position signal when the GPS position signal is unreliable.

6. The apparatus of claim 5 wherein the GPS position signal is unreliable when receiver autonomous integrity module (RAIM) information is unavailable from the global positioning system.

7. The apparatus of claim 5 wherein the GPS position signal is unreliable when the global positioning system communicates with fewer than five satellites.

8. The apparatus of claim 5 further comprising a RAIM availability module that receives the GPS position signal and provides a RAIM availability signal to the position selector.

9. The apparatus of claim 5 further comprising a RAIM availability module that receives the GPS position signal and provides a RAIM availability signal to the IRS position estimator.

10. The apparatus of claim 5 further comprising a velocity/acceleration error estimator that receives a GPS velocity based upon the velocity of the vehicle from the global positioning system and provides a data error signal to the IRS position estimator.

11. The apparatus of claim 5 further comprising a velocity/acceleration error estimator that receives an IRS velocity based upon the velocity of the vehicle from the inertial reference system and provides a data error signal to the IRS position estimator.

12. The apparatus of claim 10 further comprising a velocity/acceleration error estimator that receives an IRS velocity based upon the velocity of the vehicle from the inertial reference system.

13. The apparatus of claim 11 wherein the velocity/acceleration error estimator comprises a second order filter.

14. The apparatus of claim 12 wherein the velocity/acceleration error estimator comprises a second order filter.

15. A method of determining the position of a vehicle having a velocity and an acceleration, the method comprising the steps of:

providing a GPS position signal from a global positioning system;

providing an IRS position signal from an inertial navigation system;

determining if the GPS position signal is reliable;

providing a hybrid position signal to a flight control when the GPS position signal is reliable, the hybrid position signal being based upon the GPS position signal and the IRS position signal; and

providing an estimated IRS position signal to a flight control when the GPS position signal is unreliable, the estimated IRS position signal being based upon the velocity of the vehicle, the acceleration of the vehicle and the IRS position signal.

16. The method of claim 15 wherein the velocity of the vehicle and the acceleration of the vehicle are monitored by the global positioning system.

17. The method of claim 15 wherein the velocity of the vehicle and the acceleration of the vehicle are monitored by the inertial reference system.

18. The method of claim 16 wherein the velocity of the vehicle and the acceleration of the vehicle are monitored by the inertial reference system.

19. The method of claim 15 further comprising the steps of:

determining if the estimated IRS position signal is reliable; and

providing an indication to a pilot of the vehicle if the estimated IRS position signal is not reliable.