Autonomous navigation error correction

• US 20040193373A1
• Filed: 03/25/2003
• Published: 09/30/2004
• Est. Priority Date: 03/25/2003
• Status: Abandoned Application

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Beauregard, John G., Levin, David B.
• Application Number:
  US10/397,012
• Publication Number:
  US 20040193373A1
• Time in Patent Office: Days
• US Class Current: 701/213
• CPC Class Codes: G01S 19/02 Details of the space or ground control segments
• CPC Class Codes: G01S 19/20 Integrity monitoring, fault detection or fault isolation of space segment

Abstract

A method and system for continuously monitoring a constellation of Global Positioning System (GPS) satellites from space is disclosed. The system utilizes a plurality of GPS receivers respectivelyinstalled on-board the GPS satellites. The on-board GPS receivers receive the navigation signals transmitted by its host GPS satellite in addition to the navigation signals from all of the GPS satellites in view. The system further utilizes a Kalman filter which can also be installed on-board one or more of the GPS satellites in space to achieve further isolation from the master control station. The method comprises the steps of providing a plurality of GPS receivers on-board the GPS satellites and substantially continuously receiving at the GPS receivers navigation signals from the GPS satellites in view of the GPS receivers, and continuously determining a range from the navigation signal of each GPS satellite in view of the GPS receivers.

Claims

1. An apparatus for continuously monitoring a plurality of Global Positioning System (GPS) satellites in space, comprising:

a plurality of GPS receivers respectively on-board said plurality of GPS satellites for continuously monitoring and receiving navigation signals from said plurality of GPS satellites in view of the plurality of GPS receivers; and

means for determining a range to said each GPS satellite in view of said plurality of GPS receivers.

2. The apparatus of claim 1, wherein said range of said each GPS satellite is transmitted to a master control station via a communication link.

3. The apparatus of claim 1, wherein said navigation signals include ephemeris data and clock error data.

4. The apparatus of claim 3, further comprising at least one Kalman filter on-board at least one of said plurality of GPS satellites for calculating the ephemeris data and the clock error data received from said navigation signals of said each GPS satellite and generating correction error data to transmit back to said each GPS satellite via a communication link.

5. The apparatus of claim 1, wherein said each GPS receiver received its own navigation signal, such that the navigation signal can be cancelled by using the GPS receiver'"'"'s signal processor.

6. The apparatus of claim 1, wherein five or more satellite navigation signals are simultaneously received by at least one GPS receiver, a faulty satellite navigation signal can be isolated using an algorithm, such that the fault information is transmitted to the affected satellite to form an integrity message that can be added to the navigation signal of the affected satellite.

7. An apparatus for continuously monitoring a constellation of Global Positioning System (GPS) satellites in six orbital planes at 55 degrees inclination and 12 sidereal hour periods from space, the apparatus comprising:

a plurality of GPS receivers respectively mounted on-board said GPS satellites for continuously monitoring and receiving navigation signals from said GPS satellites in view of the GPS receivers;

means for determining a range to said each GPS satellite in view of said plurality of GPS receivers; and

means for calculating ephemeris data and clock error data received from said navigation signals of said each GPS satellite and generating correction error data to transmit back to said each GPS satellite via a communication link.

8. The apparatus of claim 7, wherein said means for calculating the ephemeris data and clock error data includes a Kalman filter.

9. The apparatus of claim 7, wherein said each GPS receiver received its own navigation signal, such that the navigation signal can be cancelled by using the GPS receiver'"'"'s signal processor.

10. The apparatus of claim 7, wherein five or more satellite navigation signals are simultaneously received by at least one GPS receiver, a faulty satellite navigation signal can be isolated using an algorithm, such that the fault information is transmitted to the affected satellite to form an integrity message that can be added to the navigation signal of the affected satellite.

11. An apparatus for continuously monitoring a constellation of 24 Global Positioning System (GPS) satellites in six orbital planes at 55 degrees inclination and 12 sidereal hour periods from space, the apparatus comprising:

at least 24 GPS receivers respectively installed on-board said 24 GPS satellites for continuously monitoring and receiving navigation signals from said GPS satellites in view of the at least 24 GPS receivers;

means for determining a range to said each GPS satellite in view of said at least 24 GPS receivers; and

at least one Kalman filter installed on-board one of said 24 GPS satellites for calculating ephemeris data and clock error data received from said navigation signals of said each GPS satellite and generating correction error data to transmit back to said each GPS satellite via a communication link.

12. The apparatus of claim 11, wherein said each GPS receiver received its own navigation signal, such that the navigation signal can be cancelled by using the GPS receiver'"'"'s signal processor.

13. The apparatus of claim 11, wherein five or more satellite navigation signals are simultaneously received by at least one GPS receiver, a faulty satellite navigation signal can be isolated using an algorithm, such that the fault information is transmitted to the affected satellite to form an integrity message that can be added to the navigation signal of the affected satellite.

14. A method of continuously monitoring a plurality of Global Positioning System (GPS) satellites from space, the method comprising the steps of:

respectively providing a plurality GPS receivers on-board said plurality of GPS satellites;

continuously receiving navigation signals from said plurality of GPS satellites in view of said plurality of GPS receivers; and

continuously determining a range from said navigation signals of said each GPS satellite in view of said plurality of GPS receivers.

15. The method of claim 14, further comprising the step of transmitting the range measurement via a communication link to a master control station (MCS) located on the earth'"'"'s surface.

16. The method of claim 14, wherein said navigation signals include ephemeris data and clock error data.

17. The method of claim 16, further comprising the steps of:

providing at least one Kalman filter on-board one of said plurality of GPS satellites;

receiving the ephemeris data and the clock error data from said navigation signals of said each GPS satellite;

calculating the ephemeris data and the clock error data of said each GPS satellite; and

transmitting correction errors back to said each GPS satellite via a communication link.

18. The method of claim 14, wherein the step of isolating a faulty satellite navigation signal using five or more satellite navigation signals received by at least one GPS receiver, such that the faulty satellite navigation signal can be isolated using an algorithm.

19. The method of claim 18, wherein the step of transmitting the fault information to the affected satellite to form an integrity message that can be added to the navigation signal of the affected satellite.

20. The method of claim 14, wherein said each GPS receiver received its own navigation signal, such that the navigation signal can be cancelled by using the GPS receiver'"'"'s signal processor.

21. A method of continuously monitoring a constellation of Global Positioning System (GPS) satellites in six orbital planes at 55 degrees inclination and 12 sidereal hour periods from space, the method comprising the steps of:

respectively providing a plurality of GPS receivers on-board said GPS satellites;

continuously monitoring at said plurality of GPS receivers navigation signals from said GPS satellites;

continuously receiving at said plurality of GPS receivers said navigation signals from said each GPS satellite in view; and

continuously determining a range from said navigation signals to said each GPS satellite in view of said plurality of GPS receivers.

22. The method of claim 21, wherein the step of transmitting the range measurement via a communication link to a master control station (MCS) located on the earth'"'"'s surface.

23. The method of claim 21, wherein said navigation signals include ephemeris data and clock error data of said each GPS satellite.

24. The method of claim 23, further comprising the steps of:

providing at least one Kalman filter on-board one of said GPS satellites;

receiving said navigation signals of said each GPS satellite;

calculating the ephemeris data and the clock error data of said each GPS satellite; and

transmitting correction errors back to said each GPS satellite via a communication link.

25. The method of claim 21, wherein the step of isolating a faulty satellite navigation signal using five or more satellite navigation signals received by at least one GPS receiver, such that the faulty satellite navigation signal can be isolated using an algorithm.

26. The method of claim 21, wherein the step of transmitting the fault information to the affected satellite to form an integrity message that can be added to the navigation signal of the affected satellite.

27. The method of claim 21, wherein said each GPS receiver received its own navigation signal, such that the navigation signal can be cancelled by using the GPS receiver'"'"'s signal processor.

28. A method of continuously monitoring a constellation of 24 Global Positioning System (GPS) satellites in six orbital planes at 55 degrees inclination and 12 sidereal hour periods from space, the method comprising the steps of:

respectively providing at least 24 GPS receivers on-board said 24 GPS satellites;

continuously monitoring at said at least 24 GPS receivers navigation signals from said GPS satellites in view,

continuously receiving at said at least 24 GPS receivers said navigation signals from said GPS satellites in view,

providing at least one Kalman filter on-board at least one of said GPS satellites, the Kalman filter comprises the steps of;

receiving said navigation signals of said GPS satellites;

calculating the ephemeris data and the clock error data of said each GPS satellite; and

transmitting correction errors back to said each GPS satellite via a communication link.

29. The method of claim 28, wherein the step of isolating a faulty satellite navigation signal using five or more satellite navigation signals received by at least one GPS receiver, such that the faulty satellite navigation signal can be isolated using an algorithm.

30. The method of claim 29, wherein the step of transmitting the fault information to the affected satellite to form an integrity message that can be added to the navigation signal of the affected satellite.

31. The method of claim 28, wherein said each GPS receiver received its own navigation signal, such that the navigation signal can be cancelled by using the GPS receiver'"'"'s signal processor.