Apparatus and method for autonavigation with one or more orbiting satellites and an anchor station

• US 5,490,076 A
• Filed: 09/12/1994
• Issued: 02/06/1996
• Est. Priority Date: 09/12/1994
• Status: Expired due to Term

• Current Assignee: Exelis Incorporated (L3Harris Technologies, Inc.)
• Original Assignee: ITT Corporation (ITT, Inc.)
• Inventors: Rawicz, Harris C., Brodie, Peter M., Doyle, Laurence J.
• Primary Examiner(s): ZANELLI, MICHAEL J
• Application Number:
  US08/304,360
• Time in Patent Office: 512 Days
• Field of Search: 364/449, 364/459, 364/458, 364/460, 342/357, 342/457, 342/358, 455/98, 244/158 R, 244/165, 244/169
• US Class Current: 455/98
• CPC Class Codes: H04B 10/118 specially adapted for satellite communication

Abstract

A system of making satellite-to-ground range measurements, carrying out communications between a ground station and a constellation of autonavigating satellites, and using these range measurements to improve navigation accuracy is disclosed. The system comprises an anchor that is in a fixed position relative to the earth. The anchor implements a filtering algorithm to arrive at solutions for the satellites'"'"' positions based on measured satellite positions and predicted satellite positions. Each time a new measurement is received by the anchor an update is generated. In this manner the system is capable of updating satellite positions at a greater rate than similar prior art systems, thereby, decreasing the transient response associated with satellite delta-v maneuvers and decreasing the quantity of data that must be exchanged by the anchor and the satellites.

Claims

1. A system for carrying out communications between one or more earth-orbiting satellites and a fixed reference point, and for computing the position of said satellites with respect to said reference point, comprising:

an anchor of fixed position relative to the earth'"'"'s surface having an anchor receiving means for receiving data and autonomous navigation messages transmitted from said satellites, wherein said anchor communicates with at least one of said satellites, said anchor including a time reference clock and including means for computing position determinations for each of said satellites with which communication is established relative to said anchor and for computing a satellite clock time, means for computing a corrected satellite clock value according to said time reference clock, and means for broadcasting said position determinations and said corrected satellite clock value to said satellites, said position determinations being periodically updated;

wherein each of said satellites includes means for receiving said autonomous navigation messages from other of said satellites and means for broadcasting said autonomous navigation messages to said other of said satellites.

2. The system according to claim 1, wherein, said means for computing said position determinations is a Kalman Filter algorithm, said Kalman Filter algorithm using said autonomous navigation messages broadcast by each of said satellites to derive a measured value and an estimated value for the position of each said satellite and operating on said measured values and said estimated values to arrive at said position determinations.

3. The system according to claim 1, wherein, each of said satellites further comprises

means for computing position determinations for each of said satellites relative to one another, said position determinations being updated every time one of said autonomous navigation messages is received.

4. The system according to claim 3, wherein said means for computing position determinations is a Kalman Filter algorithm, said Kalman Filter algorithm using said autonomous navigation messages broadcast by each of said satellites to derive a measured value and an estimated value for the position of each said satellite and operating on said measured values and said estimated values to arrive at said position determinations.

5. The system according to claim 4, further comprising:

a first transmitter on board each of said satellites for transmitting said autonomous navigation messages from said satellites to said anchor, said first transmitter being an L band transmitter;

a first receiver for receiving at said anchor said autonomous navigation messages from said satellites, said first receiver being an L band receiver;

a second transmitter said for transmitting said position determinations from said anchor to said satellites, said second transmitter being an S band transmitter;

a second receiver on board each of said satellites for receiving at said satellites said position determinations transmitted from said anchor, said receiver being an S band receiver; and

wherein;

said means for broadcasting said autonomous navigation messages to other of said satellites is a crosslink transmitter; and

said means for receiving said autonomous navigation messages from other of said satellites is a crosslink receiver.

6. The system according to claim 3, further comprising:

a first transmitter on board each of said satellites for transmitting said autonomous navigation messages from said satellites to said anchor, said first transmitter being an L band transmitter;

a first receiver for receiving at said anchor said autonomous navigation messages from said satellites, said first receiver being an L band receiver;

a second transmitter said for transmitting said position determinations from said anchor to said satellites, said second transmitter being an S band transmitter; and

a second receiver on board each of said satellites for receiving at said satellites said position determinations transmitted from said anchor, said second receiver being an S bend receiver; and

wherein;

said means for broadcasting said autonomous navigation messages to other of said satellites is a crosslink transmitter; and

said means for receiving said autonomous navigation messages from other of said satellites is a crosslink receiver.

7. The system according to claim 1, further comprising:

a first transmitter on board each of said satellites for transmitting said autonomous navigation messages from said satellites to said anchor;

a first receiver for receiving at said anchor said autonomous navigation messages from said satellites;

a second transmitter for transmitting said position determinations from said anchor to said satellites; and

a second receiver on board each of said satellites for receiving at said satellites said position determinations transmitted from said anchor.

8. A method for carrying out communications between one or more earth-orbiting satellites and a point of fixed position relative to the earth'"'"'s surface, and for computing the position of said satellites with respect to the earth, comprising the steps of:

providing an anchor of fixed position relative to the earth'"'"'s surface;

broadcasting from each of said satellites an autonomous navigation message, each said message containing said satellite'"'"'s determination of its own position;

receiving autonomous navigation broadcasts from each of said satellites at said anchor;

implementing a tracking algorithm at said anchor for computing a position determination of said orbiting satellites relative to the earth, wherein, said position determination is based on autonomous satellite navigation data and data available independently to said anchor;

broadcasting said position determinations to said satellites as part of an autonomous navigation message sent from said anchor;

implementing a tracking algorithm at each of said satellites that is substantially similar to the tracking algorithm implemented at said anchor, said tracking algorithm being used at each of said satellites to generate an updated satellite position determination; and

broadcasting said updated satellite position determinations for reception by said anchor and said satellites.

9. The method according to claim 8, wherein, said tracking algorithm is a Kalman Filter algorithm, said Kalman Filtering algorithm deriving measured satellite and anchor positions from said autonomous navigation message, computing predicted satellite and anchor positions, and using said measured and predicted positions to arrive at a solution for satellite and anchor positions.

10. A system for carrying out communications between one or more earth-orbiting satellites and a point of fixed position relative to the earth'"'"'s surface, and for computing the position of said satellites with respect to the earth, comprising:

transmitting means on board each of said satellites for transmitting data to said anchor and for transmitting data to other of said satellites;

an anchor having an anchor receiving means for receiving data from said satellites, a first processing means for computing a position determination for each of said satellites, and for computing a satellite clock time, a means for computing a corrected clock value by comparing said satellite clock time to a time reference, and an anchor transmitting means for transmitting said position determination and said corrected clock value to said satellites, said position determination being updated every time a transmission is received from one of said satellites;

receiving means on board each of said satellites for receiving transmissions from said anchor and for receiving transmissions from other of said satellites; and

means on board each of said satellites for extracting position and time data received from said anchor and from other satellites, and for using said position and time data as input to a second processing means, said second processing means computing an on-board position determination for each of said satellites and for computing an on-board corrected clock value.

11. The system according to claim 10, further comprising:

means on board each of said satellites for using said on-board position determination to decide whether a delta-v manuever is necessary and to issue a delta-v command when said delta-v maneuver is decided to be necessary; and

means on board each of said satellites for implementing said delta-v maneuver responsive to said delta-v command.

12. The system according to claim 11, further including:

means for transmitting said delta-v command to said anchor;

means for approving at said anchor of said delta-v command;

means for disapproving at said anchor of said delta-v command;

means, at said anchor, for modifying said delta-v command;

means, at said anchor, for communicating any of said approving, disapproving or modifying of said delta-v command to said satellite;

wherein said means for implementing said delta-v maneuver is responsive to said means for communicating at said anchor.

13. The system according to claim 12 further including;

means, on board said satellite, for comparing said modified delta-v command from said anchor with said delta-v command issued on board said satellite; and

means on board said satellite for requesting confirmation, from said anchor, of said modified delta-v command if a predetermined difference between said on board issued command and said modified delta-v command is exceeded.

14. The system according to claim 10, further comprising means for encoding satellite to anchor transmissions in a Quadrature Phase Shift Keying format.

15. The system according to claim 10, further comprising means for determining the gravitational effects of celestial bodies on said satellites and incorporating said determination into said on-board position determination.

16. The system according to claim 10, wherein said first processing means is a Kalman Filter.

17. The system according to claim 10, wherein said second processing means is a Kalman Filter.

18. The system according to claim 10, wherein said first processing means and said second processing means are both Kalman Filters.

19. The system according to claim 18 wherein a satellite range error for said Kalman Filters is projected up to a line of sight between said satellite and a computed anchor position at a mean constellation radius;

wherein an error is processed in said Kalman Filters for improving the geometry of a range measurement between said anchor and said satellite.

20. The system according to claim 10, wherein:

said transmitting means on board each of said satellites for transmitting data to said anchor and for transmitting data to other of said satellites comprises an L band transmitter and a crosslink transmitter; and

said receiving means on board each of said satellites for receiving transmissions from said anchor and for receiving transmissions from other of said satellites comprises an S band receiver and a crosslink receiver.

21. The system according to claim 10, wherein:

said anchor receiving means is an L band receiver; and

said anchor transmitting means is an S band transmitter.

22. The system according to claim 10, wherein said time reference is the US Naval Observatory.

23. The system according to claim 10, further comprising:

means on board each of said satellites for using said on-board position determination to decide whether a delta-v maneuver is necessary;

means on board each of said satellites for implementing said delta-v maneuver;

means for encoding satellite to anchor transmissions in a Quadrature Phase Shift Keying format;

means for determining the gravitational effects of celestial bodies on said satellites and incorporating said determination into said on-board position determination;

wherein;

said first processing means and said second processing means are both Kalman Filters;

said transmitting means on board each of said satellites for transmitting data to said anchor and for transmitting data to other of said satellites comprises a first L band transmitter and a crosslink transmitter;

said receiving means on board each of said satellites for receiving transmissions from said anchor and for receiving transmissions from other of said satellites comprises a first S band receiver and a crosslink receiver;

said anchor receiving means is a second L band receiver;

said anchor transmitting means is a second S band transmitter; and

said time reference is the US Naval Observatory.