Method for Increasing the Availability of a Global Navigation System

• US 20100141511A1
• Filed: 02/01/2008
• Published: 06/10/2010
• Est. Priority Date: 02/06/2007
• Status: Active Grant

• Current Assignee: Astrium GmbH (Airbus SE)
• Original Assignee: Astrium GmbH (Airbus SE)
• Inventors: Trautenberg, Hans L., Rang, Tanja
• Granted Patent: US 8,094,069 B2
• Time in Patent Office: Days
• US Class Current: 342/357.310
• CPC Class Codes: G01S 19/20 Integrity monitoring, fault detection or fault isolation of space segment

Abstract

A process for increasing the availability of a global navigation system that includes a plurality of spacecraft, each of which transmits information for determining the position of a terminal. From the plurality of spacecraft, a first subset, with at least one spacecraft, and a second subset are determined. the second subset being constituted by those spacecraft that are not included in the first subset. The integrity risk is determined for the information transmitted only by the second spacecraft. The first and the second subsets of spacecraft are determined such that the integrity risk, for information transmitted by the second subset spacecraft minimized relative to the integrity risk for information of all spacecraft included in the plurality of spacecraft.

Claims

1-12. -12. (canceled)

13. A process for increasing the availability of a global navigation system comprising a plurality of spacecraft, each of which transmits information for determining the position of a terminal, said method comprising:

each of said spacecraft transmitting information to the terminal;

from the plurality of spacecraft, determining a first subset including at least one of said spacecraft, and a second subset, with the second subset being constituted by those spacecraft that are not included in the first subset; and

determining an integrity risk exclusively for the information transmitted by the second subset of spacecraft;

wherein, the first and the second subsets of spacecraft are determined such that the integrity risk determined for the information transmitted by the second subset of spacecraft is optimized relative to the integrity risk that was determined for the information of all spacecraft included in the plurality of spacecraft.

14. The process according to claim 13, wherein only the information of the second subset of spacecraft is used for position determination of the terminal.

15. The process according to claim 13, wherein the information of the first subset of spacecraft is not used for position determination of the terminal.

16. The process according to claim 13, wherein the first and the second subsets of spacecraft are determined iteratively, so that the integrity risk determined for information transmitted by the second spacecraft is minimized relative to the integrity risk determined for the information of all spacecraft of the plurality of spacecraft.

17. The process according to claim 16, wherein, for minimizing the integrity risk:

a) a number of spacecraft from the plurality of spacecraft is allocated to the first subset and the integrity risk of the spacecraft remaining in the second subset is determined;

b) step a) is repeated for possible combinations of a first subset;

c) those spacecraft of the second subset whose integrity risk is minimal form the plurality of spacecraft for a next iteration step,

d) steps a) to c) are repeated until a minimal integrity risk has been reached.

18. The process according to claim 17, wherein it is checked whether the integrity risk is lower than a maximum tolerable integrity risk.

19. The process according to claim 18, wherein it is checked for each of the spacecraft of the second subset, whether it is a critical spacecraft.

20. The process according to claim 19, wherein it is checked whether the number of critical spacecraft is greater than a number of allowed critical spacecraft.

21. The process according to claim 19, wherein, for minimizing the number of critical spacecraft:

a) a non-critical spacecraft from the determined second subset is allocated to the first subset;

b) the number of critical spacecraft within the second subset is determined; and

c) steps a) and b) are repeated iteratively until no non-critical spacecraft can be determined in the second subset.

22. The process according to claim 21, wherein minimizing of the number of critical spacecraft is carried out when the number of critical satellites is greater than a maximum permitted number of critical satellites.

23. A terminal for determining a position using a global navigation system comprising a plurality of spacecraft which, for position determination of the terminal, each transmit information to the terminal, the terminal comprising devices for implementing the process according to claim 13.

24. A computer program product which is loadable into the internal memory of a digital computer and comprises software sections for carrying out the steps according to claim 13, when the product is running on a computer.