Method and Apparatus for Providing Integrity Information for Users of a Global Navigation System

• US 20080288167A1
• Filed: 09/17/2005
• Published: 11/20/2008
• Est. Priority Date: 09/20/2004
• Status: Active Grant

• Current Assignee: European Space Agency
• Original Assignee: Astrium GmbH (Airbus SE)
• Inventors: Trautenberg, Hans L., Lobert, Bruno, Abele, Marcel, Oehler, Veit
• Granted Patent: US 8,200,430 B2
• Time in Patent Office: Days
• US Class Current: 701/214
• CPC Class Codes: G01S 19/08 providing integrity information, e.g. health of satellites or quality of ephemeris data

Abstract

In a method for providing integrity information for users of a global navigation system, which comprises several space vehicles like satellites transmitting information to a device for position detection, the transmitted information comprises first information from the global navigation system about the accuracy of a signal in space error SISE of a faulty space vehicle, and second information whether or not the global navigation system assesses the faulty space vehicle as faulty. The invention is based on the assumption how exact a fault can be detected, so that performance the global navigation system can be increased; and no unfounded assumption is used which improves the quality of service.

Claims

1-14. -14. (canceled)

15. Method for providing integrity information for users of a global navigation system, said method comprising:

a plurality of space vehicles transmitting information to a device for position detection;

wherein the transmitted information includes,

a first information from the global navigation system about the accuracy of a signal in space error SISE of a faulty space vehicle; and

a second information that specifies whether or not the global navigation system assesses the faulty space vehicle as faulty.

16. The method according to claim 15, wherein the first information comprises:

information about the quality of a signal in space SIS broadcast by the space vehicles, which is called signal in space accuracy SISA; and

information about accuracy of a monitoring of the signal in space SIS broadcast by the space vehicles by a ground segment of the global navigation system, which is called signal in space monitoring accuracy SISMA.

17. The method according to claim 15, wherein the second information comprises information about a signal in space SIS broadcast by space vehicles, which should not be used, which is called integrity flag IF.

18. The method according to claim 16, wherein a navigation message is disseminated to the device for position detection which includes values of the SISA.

19. The method according to claim 16, wherein an integrity message is disseminated to the device for position detection which includes a table containing a value of the SISMA and an integrity flag IF for each SIS.

20. The method according to claim 18, wherein the navigation and the integrity message are updated each 30 seconds.

21. A device for position detection by means of a global navigation system in which a plurality of space vehicles transmit information to the device for determining the position of the device in space;

wherein the device comprises;

receiving means for receiving an integrity information that includes a first information from the global navigation system about the accuracy of a signal in space error SISE of a faulty space vehicle; and

a second information that specifies whether or not the global navigation system assesses the faulty space vehicle as faulty;

processing means for calculating an integrity risk from the received first and second information, and from further information; and

alert means for raising an alert if the calculated integrity risk is larger than an allowed integrity risk.

22. Device according to claim 21, wherein the processing means are adapted for calculating the integrity risk for a given alert limit which is the maximum allowed position deviation for which no alert has to be raised.

23. The device according to claim 22, wherein for calculation of the integrity risk it is assumed that all distribution used for the calculation are Gaussian distributions.

24. The device according to claim 21, wherein said further information comprises relative geometry between the device for position detection and a space vehicle, error budgets for the signal in space SIS including propagation errors, reception errors and errors of the SIS broadcast by the space vehicles, and integrity flags IFs.

25. The device according to claim 24, wherein, for errors of the SIS broadcast by the space vehicles, it is assumed that for a non fault-free space vehicle the distribution of the difference between the error of the SIS broadcast by the space vehicles and an integrity flag threshold is over-bound by a Gaussian distribution with standard deviation signal in space monitoring accuracy SISMA.

26. The device according to claim 21, wherein the device is adapted for calculating the integrity risk as the sum of the horizontal integrity risk P_IntRisk,H and the vertical integrity risk P_IntRisk,V.

27. The method for determining integrity risk of information disseminated from space vehicles in a global navigation system which provides integrity information that includes a first information from the global navigation system about the accuracy of a signal in space error SISE of a faulty space vehicle;

and a second information that specifies whether or not the global navigation system assesses the faulty space vehicle as faulty;

said method comprising;

checking that the integrity information received for every integrity data stream is the integrity information generated by the integrity function of the ground infrastructure;

selecting out of redundant and positively checked integrity data-streams the integrity data stream to be used;

determining from selected and positive checked integrity information and the navigation information which signals are valid;

computing an integrity risk at the alert limit for the critical operation period wherein only valid signals are considered; and

computing a number of critical space vehicles for the critical operation period, considering only space vehicles that provide valid signals; and

generating an alert for the user which indicates whether or not the received information should be used for position detection.

28. The method according to 27, wherein the integrity information generated by the integrity function of the ground infrastructure is signed so that it can be validated by a receiver.