Trajectory estimation system for an orbiting satellite

• US 7,725,259 B2
• Filed: 05/03/2007
• Issued: 05/25/2010
• Est. Priority Date: 05/03/2007
• Status: Active Grant

• Current Assignee: Raytheon Company (Rtx Corporation)
• Original Assignee: Raytheon Company (Rtx Corporation)
• Inventors: Schwartz, Lawrence
• Primary Examiner(s): Tran; Khoi
• Assistant Examiner(s): MOYER, DALE S
• Application Number:
  US11/744,059
• Publication Number:
  US 20080275598A1
• Time in Patent Office: 1,118 Days
• Field of Search: 244/158.4, 244/158.8, 244/164, 244/171, 244/195, 342/357.02, 342/357.06, 342/355, 342/357.09, 342/357.14, 455/427, 700/56, 701/13, 701/214, 701/222, 701/226, 701/116, 701/223, 701/219, 703/2, 703/6, 703/8
• US Class Current: 701/214
• CPC Class Codes: B64G 1/242 Orbits and trajectories
• CPC Class Codes: B64G 1/26 using jets

Abstract

A method for calculating a trajectory of a satellite following a maneuver includes determining a first estimated trajectory of a satellite using a first sequential mode of operation; performing a thruster burn as a correction maneuver for the satellite; and providing a real-time assessment of the correction maneuver by utilizing a second sequential mode of operation. The second sequential mode of operation includes receiving a data point from an uplink/downlink facility, determining a second estimated trajectory and an estimated thruster performance of the satellite based upon the received data point, and determining a trajectory error of the satellite based upon the received data point. The method further includes repeating the second sequential mode of operation if the trajectory error is above a specified threshold level, and repeating the first sequential mode of operation if the trajectory error is below the specified threshold level.

Claims

1. A system for determining a trajectory of a satellite comprising:

a processor; and

a computer program stored in a computer-readable medium, and executable on the processor, the computer program operable, when executed on the processor to;

determine a first estimated trajectory of a satellite using a first sequential mode of operation;

perform a thruster burn as a correction maneuver for the satellite;

provide a real-time assessment of the correction maneuver by utilizing a second sequential mode of operation, the second sequential mode of operation comprising;

receiving a data point from an uplink/downlink facility;

determining, using a least squares algorithm, a second estimated trajectory and an estimated thruster performance of the satellite based upon the received data point; and

determining, using the least squares algorithm, a trajectory error of the satellite based upon the received data point, the trajectory error including a vector quantity indicating position error in space and a scalar error value; and

repeat the second sequential mode of operation if the trajectory error is above a specified threshold level; and

repeat the first sequential mode of operation if the trajectory error is below the specified threshold level.

2. The system of claim 1, wherein the computer program is further operable to determine the data point using ranging information from the uplink/downlink facility.

3. The system of claim 1, wherein the computer program is further operable to determine the data point using telemetry information from the uplink/downlink facility.

4. A system comprising:

a processor; and

a computer program stored in a computer-readable medium and executable on the processor, the computer program operable, when executed on the processor to;

determine a first estimated trajectory of a satellite using a first sequential mode of operation;

perform a thruster burn as a correction maneuver for the satellite;

provide a real-time assessment of the correction maneuver by utilizing a second sequential mode of operation, the second sequential mode of operation comprising;

receiving a data point from an uplink/downlink facility;

determining, using a least squares algorithm, a second estimated trajectory and an estimated thruster performance of the satellite based upon the received data point; and

determining, using the least squares algorithm, a trajectory error of the satellite based upon the received data point, the trajectory error including a vector quantity indicating position error in space and a scalar error value; and

repeat the second sequential mode of operation if the trajectory error is above a specified threshold level; and

repeat the first sequential mode of operation if the trajectory error is below the specified threshold level.

5. The system of claim 4, wherein the first sequential mode of operation comprises determining the estimated trajectory of the satellite by calculating a plurality of data points from the uplink/downlink facility over a corresponding plurality of elapsed periods of time.

6. The system of claim 4, wherein the computer program is further operable to determine if the trajectory error is less than a specified threshold level, and if the trajectory error is less than the specified threshold level, determine the estimated trajectory of the satellite using the first sequential mode of operation.

7. The system of claim 4, wherein the satellite includes a microwave transponder circuit.

8. The system of claim 4, wherein the data point is referenced to three dimensional Cartesian space.

9. The system of claim 4, wherein the computer program is further operable to determine the data point using ranging information from the uplink/downlink facility.

10. The system of claim 4, wherein the computer program is further operable to determine the data point using telemetry information from the uplink/downlink facility.

11. A method for calculating a trajectory of a satellite following a maneuver comprising:

determining a first estimated trajectory of a satellite using a first sequential mode of operation;

performing a thruster bum as a correction maneuver for the satellite;

providing a real-time assessment of the correction maneuver by utilizing a second sequential mode of operation, the second sequential mode of operation comprising;

receiving a data point from an uplink/downlink facility;

determining, using a least squares algorithm, a second estimated trajectory and an estimated thruster performance of the satellite based upon the received data point;

determining, using the least squares algorithm, a trajectory error of the satellite based upon the received data point, the trajectory error including a vector quantity indicating position error in space and a scalar error value; and

repeating the second sequential mode of operation if the trajectory error is above a specified threshold level; and

repeating the first sequential mode of operation if the trajectory error is below the specified threshold level.

12. The method of claim 11, wherein the satellite includes a microwave transponder circuit.

13. The method of claim 11, further comprising determining the data point using ranging information from the uplink/downlink facility.

14. The method of claim 11, further comprising determining the data point using telemetry information from the uplink/downlink facility.

15. The method of claim 11, wherein determining an estimated trajectory using a sequential mode of operation further comprises determining an estimated trajectory by calculating a plurality of data points from the uplink/downlink facility over a corresponding plurality of elapsed periods of time.

16. The method of claim 11, further comprising if the trajectory error is less than the specified threshold level, determining the estimated trajectory of the satellite using the sequential mode of operation.