Beacon for satellite registration

• US 6,606,560 B1
• Filed: 03/22/2001
• Issued: 08/12/2003
• Est. Priority Date: 03/22/2001
• Status: Expired due to Fees

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Inventors: Clark, Ronald H.
• Primary Examiner(s): LOUIS JACQUES, JACQUES H
• Application Number:
  US09/813,814
• Time in Patent Office: 873 Days
• Field of Search: 701/213, 701/226, 701/214, 701/223, 701/3, 701/4, 701/13, 701/215, 342/427, 342/352, 342/359, 342/356, 342/358, 342/357.06, 342/357.12, 342/357.02, 455/12.1, 455/13.4, 455/98, 455/427, 455/428
• US Class Current: 701/213
• CPC Class Codes: G01S 19/02 Details of the space or ground control segments

Abstract

The present invention is a system for providing GPS users with a high level of confidence in the integrity and accuracy of received GPS signals. A beacon is located at a fixed point on the earth at a known location. The beacon emits a coded signal pulse having a precise RF waveform that is received by all GPS satellites in view of the beacon'"'"'s location. The RF signal pulse is decoded and processed onboard each GPS satellite. The GPS satellite receives beacon position data from the other in-view GPS satellites via crosslinks. The GPS satellite compares the beacon position data with satellite position data such as Autonav data and thereby verifies the integrity of its own operation. The GPS satellite then sends an integrity message to GPS users to inform the GPS users of the integrity of received GPS signals from that satellite.

Claims

1. A system for verifying the integrity of a signal transmitted from a space vehicle, comprising:

a plurality of space vehicles; and

a beacon simultaneously transmitting a beacon signal to all space vehicles of the plurality of space vehicles in view of a location of the beacon,

wherein each space vehicle

receiving the beacon signal,

calculating its position relative to the beacon,

transmitting its position relative to the beacon to other space vehicles,

receiving calculated position data from the other space vehicles,

comparing the received calculated position data with its calculated space vehicle position data,

determining a position of the beacon based upon the comparison,

calculating its coordinates in space,

transmitting its coordinates to the other space vehicles,

receiving calculated coordinates from other space vehicles,

comparing its calculated coordinates with calculated coordinates received from the other space vehicles, and

verifying its integrity based on the comparison of the coordinates.

2. The system of claim 1, wherein the space vehicles are Global Positioning System (GPS) satellites.

3. The system of claim 2, wherein the space vehicles generate an integrity message that that indicates the accuracy and/or the integrity of the transmitted signal.

4. The system of claim 3, wherein the integrity message is included in a GPS navigation message transmitted from the space vehicles.

5. The system of claim 3, wherein the integrity message is transmitted over a channel separate from a channel transmitting a GPS navigation message.

6. The system of claim 5, wherein the separate channel is the L5 channel.

7. The system of claim 1, wherein the beacon is located at a fixed known location on the Earth.

8. The system of claim 1, wherein the space vehicles each perform the determining of the loss of integrity condition by:

calculating a position of the space vehicle based on the beacon position data received from the other space vehicles, the beacon signal received from the beacon, and the known position of the beacon, and

comparing the calculated position of the space vehicle with space vehicle position data.

9. The system of claim 8, wherein the space vehicle position data includes at least one of:

autonav data, and

ephemeris data received from a ground station.

10. The system of claim 1, wherein the space vehicles verify the loss of integrity condition by:

calculating a position of the beacon based on the beacon position data received from the other space vehicles, the beacon signal received from the beacon, and the space vehicle position data;

comparing the calculated position of the beacon with the known position of the beacon.

11. The system of claim 1, wherein the space vehicles receive beacon position data from the other space vehicles via RF or optical crosslinks.

12. A system for verifying the integrity of a signal transmitted from a space vehicle, comprising:

a plurality of space vehicles, each space vehicle

receiving a signal transmitted from a beacon,

calculating its position relative to the beacon,

transmitting its position relative to the beacon to other space vehicles,

receiving calculated position data from the other space vehicles,

comparing the received calculated position data with its calculated space vehicle position data,

determining a position of the beacon based upon the comparison,

calculating its coordinates in space,

transmitting its coordinates to the other space vehicles,

receiving calculated coordinates from other space vehicles,

comparing its calculated coordinates with calculated coordinates received from the other space vehicles, and

verifying its integrity based on the comparison of the coordinates.

13. The system of claim 12, wherein the beacon is located at a fixed known location on the Earth.

14. The system of claim 12, wherein the space vehicles each perform the determining of the loss of integrity condition by:

calculating a position of the space vehicle based on the beacon position data received from the other space vehicles, the beacon signal received from the beacon, and the known. position of the beacon, and

comparing the calculated position of the space vehicle with space vehicle position data.

15. The system of claim 14, wherein the space vehicle position data includes at least one of:

autonav data, and

ephemeris data received from a ground station.

16. The system of claim 12, wherein the space vehicles verify the loss of integrity condition by:

calculating a position of the beacon based on the beacon position data received from the other space vehicles, the beacon signal received from the beacon, and the space vehicle position data;

comparing the calculated position of the beacon with the known position of the beacon.

17. A method for verifying the integrity of a signal transmitted from a space vehicle, comprising:

a) receiving from a beacon a beacon signal at the space vehicle;

b) calculating a position of the space vehicle relative to the beacon;

c) transmitting the position relative to the beacon to other space vehicles;

d) receiving calculated position data from the other space vehicles;

e) comparing the received calculated position data with the calculated position;

f) determining a position of the beacon based upon the comparison;

g) calculating coordinates of the space vehicle in space;

h) transmitting the calculated coordinates of the space vehicle to the other space vehicles;

i) receiving calculated coordinates from other space vehicles;

j) comparing the calculated coordinates of the space vehicle with calculated coordinates received from the other space vehicles; and

k) verifying integrity of the space vehicle based on the comparison of the coordinates.

18. The method of claim 17, wherein the space vehicle is a Global Positioning System (GPS) satellite.

19. The method of claim 17, further comprising:

generating an integrity message that that indicates the accuracy and/or the integrity of the signal; and

transmitting the integrity message to a user.

20. The method of claim 19, wherein the integrity message is included in a GPS navigation message transmitted from the space vehicle.

21. The method of claim 19, wherein the integrity message is transmitted over a channel separate from a channel transmitting a GPS navigation message.

22. The method of claim 21, wherein the separate channel is the L5 channel.

23. The method of claim 17, wherein the beacon is located at a fixed known location on the Earth.

24. The method of claim 17, wherein the determining of the loss of integrity condition comprises:

calculating a position of the space vehicle based on the beacon position data received from the other space vehicles, the beacon signal received from the beacon, and the known position of the beacon, and

comparing the calculated position of the space vehicle with space vehicle position data.

25. The method of claim 17, wherein the space vehicle position data includes at least one of:

autonav data, and

ephemeris data received from a ground station.

26. The method of claim 17, wherein the determining of the loss of integrity condition comprises:

calculating a position of the beacon based on the beacon position data received from the other space vehicles, the beacon signal received from the beacon, and the space vehicle position data; and

comparing the calculated position of the beacon with the known position of the beacon.

27. The method of claim 17, wherein beacon position data is received from the other space vehicles via RF or optical crosslinks.