Real time precision orbit determination system

• US 6,133,872 A
• Filed: 10/17/1997
• Issued: 10/17/2000
• Est. Priority Date: 10/17/1997
• Status: Expired due to Fees

• Current Assignee: Ball Aerospace & Technologies Corporation (Ball Corporation)
• Original Assignee: Ball Aerospace & Technologies Corporation (Ball Corporation)
• Inventors: Mitchell, Scott, Cubbedge, Skip
• Primary Examiner(s): Blum, Theodore M.
• Application Number:
  US08/953,704
• Time in Patent Office: 1,096 Days
• Field of Search: 342/357.1, 342/357.09, 701/226
• US Class Current: 342/357.31
• CPC Class Codes: G01S 19/05 providing aiding data
• CPC Class Codes: G01S 19/27 creating, predicting or correcting ephemeris or almanac data within the receiver
• CPC Class Codes: H04B 7/18519 Operations control, administration or maintenance

Abstract

The present invention relates to a system for providing highly accurate position estimates for a vehicle in space, in substantially real time. The system includes a Mission Control Center (MCC) that calculates precise orbits for GPS satellites that are in view of the vehicle, using GPS tracking data from the worldwide network of tracking sites. Because the tracking data from the tracking sites is not current when received by the MCC, the precise GPS orbits are "propagated forward in time" by the MCC. The propagated orbit information is uploaded to the user satellite where it is processed in an extended Kalman filter, or similar device, along with the real time output of the on-board GPS receiver, to achieve highly accurate satellite location estimates in substantially real time.

Claims

1. A method for estimating orbit information of a space system, comprising:

obtaining first orbit information relating to positions of a plurality of space vehicles at a first time;

predicting, using said first orbit information, second orbit information relating to positions of said plurality of space vehicles at a second time, wherein said second time occurs after said first time;

providing third orbit information relating to positions of said space vehicles at a third time, wherein said third orbit information is different from said first and second orbit information; and

using said second and third orbit information to estimate orbit data for a space system that is not part of said plurality of space vehicles.

2. The method of claim 1, wherein:

said step of using includes estimating orbit data of said space system in substantially real time.

3. The method of claim 1, wherein:

said steps of obtaining and predicting are performed at a first location and said step of using is performed at a second location that is different from said first location.

4. The method of claim 3, wherein:

said step of using includes receiving said second orbit information from said first location at said second location.

5. The method of claim 3, wherein:

said steps of obtaining is performed at a control center and said step of using is performed on said space system.

6. The method of claim 1, wherein:

said plurality of space vehicles include Global Positioning System (GPS) satellites.

7. The method of claim 1, wherein:

said step of obtaining includes collecting information from said plurality of space vehicles via a plurality of ground tracking stations.

8. The method of claim 1, wherein:

said step of predicting includes propagating said first orbit information forward in time.

9. The method of claim 1, wherein:

said step of providing includes receiving information from said plurality of space vehicles in a GPS receiver located on said space system.

10. The method of claim 1, wherein:

said third time is the same as said second time.

11. A system for estimating orbit information for a space system, comprising:

means for obtaining first orbit information relating to a plurality of satellites;

means for propagating said first orbit information forward in time to obtain second orbit information relating to said plurality of satellites;

means for acquiring third orbit information relating to said plurality of satellites, wherein said third orbit information is different from said first orbit information; and

means for processing said second orbit information and said third orbit information to estimate orbit data for a space system that is not part of said plurality of satellites.

12. The system of claim 11, wherein:

said means for processing estimates said orbit data in real time.

13. The system of claim 11, wherein:

said means for processing includes a Kalman filter.

14. The system of claim 11, wherein:

said means for obtaining is located at a ground based control center.

15. The system of claim 11, wherein:

said means for propagating is located at a ground based control center.

16. The system of claim 15, wherein:

said means for processing includes means for receiving said second orbit information from said control center.

17. The system of claim 11, wherein:

said means for acquiring and said means for processing are located at said space system.

18. The system of claim 11, wherein:

said means for acquiring includes at least one GPS receiver.

19. A method for determining realtime orbit information of a space system, comprising:

receiving first position data corresponding to a plurality of external navigation satellites in a first receiver on said space system;

receiving second position data corresponding to said plurality of external navigation satellites in a second receiver on said space system, wherein said second receiver is different from said first receiver; and

determining, onboard the space system, real time orbit information of the space system using both of said first position data and said second position data, wherein the accuracy of said real time orbit information does not depend on the relative location of the space system with respect to a ground based reference location.

20. The method, as claimed in claim 19, wherein:

said first receiver includes an uplink receiver for receiving said first position data from a ground station.

21. The method, as claimed in claim 19, wherein:

said second receiver includes a global positioning system (GPS) receiver for receiving said second position data from a plurality of GPS satellites.

22. The method, as claimed in claim 19, wherein:

said plurality of external navigation satellites includes a plurality of global positioning system (GPS) satellites.

23. The method, as claimed in claim 19, wherein:

said second position data includes global positioning system (GPS) ephemerides.

24. The method, as claimed in claim 19, wherein:

said first position data includes global positioning system (GPS) satellite orbit information that has been propagated forward in time within a ground station.

25. The method, as claimed in claim 24, wherein:

said GPS satellite orbit information has been collected from a plurality of GPS tracking stations.

26. The method, as claimed in claim 19, wherein:

said step of determining includes generating a coarse position estimate for said space system using said second position data.

27. The method, as claimed in claim 19, wherein:

said step of determining includes processing said coarse position estimate and said first position data in a processing unit on-board said space system.

28. The method, as claimed in claim 27, wherein:

said processing unit includes a Kalman filter.

29. An apparatus for determining realtime orbit information of a space system, comprising:

first means for providing first orbit information corresponding to a plurality of navigation satellites, said first means including first processing means for processing first orbit data corresponding to said plurality of navigation satellites to generate said first orbit information;

second means for obtaining second orbit information corresponding to said space system, said second means including second processing means for processing second orbit data corresponding to said plurality of navigation satellites to generate said second orbit information, wherein said second processing means is different from said first processing means and said second orbit data is different from said first orbit data; and

third means for determining realtime orbit information of the space system using both of said first orbit information and said second orbit information, wherein the accuracy of said real time orbit information does not depend on the relative location of the space system with respect to a ground based reference location.

30. The apparatus, as claimed in claim 29, wherein:

said first means is located at a first location and said second means is located at a second location that is remote from said first location.

31. The apparatus, as claimed in claim 29, wherein:

said first orbit information includes global positioning system (GPS) satellite orbit information that is propagated forward in time.

32. The apparatus, as claimed in claim 31, wherein:

said first means includes an uplink transmitter for transmitting said first orbit information to said space system.

33. The apparatus, as claimed in claim 29, wherein:

said first orbit data is received by said first means at a substantially different time from said second orbit data being received by said second means.

34. The apparatus, as claimed in claim 29, wherein:

said first means receives said first orbit data from a network of ground stations.

35. The apparatus, as claimed in claim 29, wherein:

said third means includes a Kalman filter.

36. A method for determining real time orbit information of a space system, comprising:

obtaining, at a control center, first orbit information relating to a plurality of space vehicles;

processing, at said control center, said first orbit information to create second orbit information relating to said plurality of space vehicles;

uploading said second orbit information to said space system;

receiving third orbit information relating to said plurality of space vehicles directly from said plurality of space vehicles at said space system, wherein said third orbit information is different from said second orbit information; and

using said second orbit information and said third orbit information to estimate orbit information of said space system in substantially real time.

37. The method, as claimed in claim 36, wherein:

said step of processing includes propagating said first orbit information forward in time.

38. The method, as claimed in claim 36, wherein:

said step of uploading said second orbit information does not have to be performed in real time.