Method and apparatus for spacecraft antenna beam pointing correction

• US 6,504,502 B1
• Filed: 01/07/2000
• Issued: 01/07/2003
• Est. Priority Date: 01/07/2000
• Status: Expired due to Term

• Current Assignee: Hughes Electronics Corporation (AT&T, Inc.)
• Original Assignee: Hughes Electronics Corporation (AT&T, Inc.)
• Inventors: Wu, Yeong-Wei, Li, Rongsheng
• Primary Examiner(s): Blum, Theodore M.
• Application Number:
  US09/479,702
• Time in Patent Office: 1,096 Days
• Field of Search: 342/354, 342/359, 342/352
• US Class Current: 342/354
• CPC Class Codes: B64G 1/244 Spacecraft control systems
• CPC Class Codes: B64G 1/36 using sensors, e.g. sun-sensors, horizon sensors
• CPC Class Codes: B64G 1/361 using star sensors
• CPC Class Codes: B64G 1/363 using sun sensors
• CPC Class Codes: B64G 1/365 using horizon or Earth sensors
• CPC Class Codes: B64G 1/369 using gyroscopes as attitude sensors
• CPC Class Codes: B64G 1/66 Arrangements or adaptations of apparatus or instruments, not otherwise provided for

Abstract

A pointing system and method for directing a first satellite system instrument to a first target is disclosed. The method comprises the steps of computing the orientation of a first satellite system instrument; computing a position of the satellite using measured orbital data; computing a target line of sight (LOS) vector direction from the satellite to the target using the computed orientation and the computed satellite position, and directing the first instrument to the first target according to the computed target LOS vector. The apparatus comprises at least one attitude sensor for the first instrument and a communicatively coupled satellite navigation system. The satellite navigation system determines the satellite position using measured satellite orbital data. The satellite navigation system computes the orientation of the first instrument using the attitude measurements, and computes the satellite position using measured satellite orbital data. The satellite navigation system also computes a target LOS vector direction from the satellite to the target using the computed orientation and the computed satellite position, and generates a first instrument orientation command from the computed target LOS vector direction. The orientation command is used by the first instrument to direct the instrument in the proper direction.

Claims

1. A method of directing first instrument disposed on a satellite to a first target comprising the steps of:

computing an attitude of a first instrument;

computing a position of the satellite using measured satellite orbital data;

computing a target line of sight (LOS) vector direction from the satellite to the first target using the computed attitude and the computed satellite position; and

directing the first instrument to the first target according to the computed target LOS vector direction.

2. The method of claim 1, wherein the step of computing the satellite position using measured satellite orbital data comprises the step of computing an ephemeris for the satellite.

3. The method of claim 2, wherein the ephemeris is computed in the satellite.

4. The method of claim 2, wherein the ephemeris is computed at a ground station and transmitted to the satellite.

5. The method of claim 1, wherein the first instrument is a downlink antenna and he method further comprises the step of directing an uplink antenna at a second target when directing the downlink antenna at the first target.

6. The method of claim 1, wherein the step of computing an orientation of the first instrument comprises the step of:

measuring the attitude of the first instrument using at least one attitude sensor; and

computing the orientation of the first instrument using the attitude sensor measurements.

7. The method of claim 6, wherein the step of computing the orientation of the first instrument using the attitude sensor measurements comprises the step of computing a direction cosine matrix from the attitude sensor measurements.

8. The method of claim 1, wherein the step of computing a target LOS vector direction from the satellite to the target using the computed orientation and the computed satellite position comprises the steps of:

computing a boresight vector using the computed orientation of the first instrument, the computed satellite position, and a location of the first target;

computing a target LOS vector from the satellite to the target using the computed orientation of the first instrument, the computed satellite position, and a location of the first target; and

computing the target LOS vector direction from the computed boresight vector and the computed target LOS vector.

9. An apparatus for directing a first instrument disposed on a satellite to a first location, comprising:

at least one sensor for measuring an attitude of a first instrument on the satellite;

a satellite navigation system for determining the satellite position using measured satellite orbital data, the satellite navigation system comprising a processor communicatively coupled to the sensor, for computing the orientation of the first instrument using the attitude measurements, for computing the satellite position using measured satellite orbital data, and for computing a target line of sight (LOS) vector direction from the satellite to the first location using the computed orientation and the computed satellite position, and for generating a first instrument orientation command from the computed target (LOS) vector direction; and

a first instrument interface, for receiving the first instrument orientation command to direct the first instrument.

10. The apparatus of claim 9, wherein the first instrument is a downlink antenna.

11. The apparatus of claim 9, wherein the satellite navigation system determines the satellite position from the ephemeris of the satellite orbit.

12. The apparatus of claim 9, wherein the satellite navigation system receives the ephemeris of the satellite orbit from a ground station.

13. The apparatus of claim 12, wherein the satellite navigation system receives updates of the ephemeris of the satellite orbit from the ground station.

14. An apparatus for directing a first instrument disposed on a satellite to a first location, comprising:

at least one first instrument attitude sensor;

a first processor, communicatively coupled to the first instrument attitude sensor, for computing an attitude of a line of sight (LOS) of the first instrument, for computing an ephemeris for an orbit of the satellite and for computing a first instrument pointing error estimate and an orbital error estimate using the computed ephemeris and the computed attitude of the first instrument; and

a second processor, coupled to the first processor for computing a first instrument pointing error correction using the computed second instrument pointing error estimate and the computed orbit error estimate.

15. An apparatus for directing a first instrument disposed on a satellite to a first target comprising:

means for computing the orientation of a first instrument in a first reference frame;

means for computing a position of the satellite in the first reference frame using measured satellite orbital data;

means for computing a target line of sight (LOS) vector direction from the satellite to the first target using the computed orientation and the computed satellite position in a second reference frame; and

means for directing the first instrument to the first target according to the computed target LOS vector.

16. The apparatus of claim 15, wherein the means for computing the satellite position using measured satellite orbital data comprises means for computing an ephemeris for the satellite.

17. The apparatus of claim 16, wherein the ephemeris is computed in the satellite.

18. The apparatus of claim 16, wherein the ephemeris is computed at a ground station and transmitted to the satellite.

19. The apparats of claim 15, wherein the first instrument is an uplink antenna, and the apparatus further comprises means for directing an uplink antenna at a second target while directing the downlink antenna at the first target.

20. The apparatus of claim 15, wherein the means for computing an orientation of the second instrument comprises:

means for measuring the attitude of the first instrument using attitude sensors; and

means for computing the orientation of the first instrument using the attitude sensor measurements.

21. The apparatus of claim 20, wherein the means for computing the orientation of the first instrument using the attitude sensor measurements comprises means for computing a direction cosine matrix from the attitude sensor measurements.

22. The apparatus of claim 15, wherein the means for computing a target LOS vector direction from the satellite to the first target using the computed orientation and the computed satellite position comprises:

means for computing a boresight vector in the first reference frame using the computed orientation of the second satellite system instrument, the computed satellite position, and a location of the first target;

means for computing a target LOS vector from the satellite to the target using the computed orientation of the first instrument, the computed satellite position, and location of the first target; and

means for computing the target LOS vector direction from the computed boresight vector and the computed target LOS vector.

23. A program storage device, readable by a computer, tangibly embodying at least one program of instructions executable by the computer to perform method steps of directing a first instrument disposed on a satellite to a first target, the method steps comprising the steps of:

computing the orientation of a first instrument;

computing a position of the satellite using measured satellite orbital data;

computing a target line of sight (LOS) vector direction from the satellite to the first target using the computed orientation and the computed satellite position; and

directing the first instrument to the first target according to the computed target LOS vector direction.