Subterranean target steering strategy

• US 6,135,389 A
• Filed: 03/16/1998
• Issued: 10/24/2000
• Est. Priority Date: 03/16/1998
• Status: Expired due to Term

• Current Assignee: Hughes Electronics Corporation (Rtx Corporation)
• Original Assignee: Hughes Electronics Corporation (Rtx Corporation)
• Inventors: Fowell, Richard A.
• Primary Examiner(s): Poon, Peter M.
• Assistant Examiner(s): DINH, TIEN QUANG
• Application Number:
  US09/039,883
• Time in Patent Office: 953 Days
• Field of Search: 244/158 R, 244/164, 342/22, 342/355
• US Class Current: 244/158.4
• CPC Class Codes: B64G 1/1007 Communications satellites
• CPC Class Codes: B64G 1/1021 Earth observation satellites
• CPC Class Codes: B64G 1/242 Orbits and trajectories
• CPC Class Codes: B64G 1/244 Spacecraft control systems
• CPC Class Codes: B64G 1/365 using horizon or Earth sensors
• CPC Class Codes: B64G 1/66 Arrangements or adaptations of apparatus or instruments, not otherwise provided for

Abstract

A method for steering the payload beam of a satellite in a non-geostationary orbit toward an intended service area having known geographical dimensions in order to obtain improved pointing performance with a corresponding reduction in the demand on onboard hardware and software systems. The method comprises the steps of determining a subterranean target point and a direction fixed in the payload beam, calculating the orientation that points the payload beam direction through the subterranean target point, and maintaining this payload beam orientation using an on-board attitude control system.

Claims

1. A method for targeting the payload beam of a satellite in a geosynchronous earth orbit toward an intended service area having known geographical dimensions, comprising the steps of:

determining a subterranean target point, the target point being at least 100 kilometers below the earth'"'"'s surface and distinct from the earth center;

orienting the satellite payload toward the subterranean target point; and

maintaining the payload beam orientation during orbit using an on board attitude control system.

2. The method of claim 1, wherein the payload beam includes a boresight, and further wherein the orbit inclination angle, the northern and southern region extremes of the intended service area, and the payload beam half-angle are all known, and including the additional steps of:

calculating a northern payload extreme when the satellite is in a first known orbit location;

aligning the northern payload extreme with the northern region extreme; and

calculating a first subterranean point at which the satellite boresight intersects the earth equatorial plane;

calculating a southern payload extreme when the satellite is in a second known orbit location;

aligning the southern payload extreme with the southern region extreme;

calculating a second subterranean point at which the satellite boresight intersects the earth equatorial plane;

comparing the first subterranean point to the second subterranean point; and

choosing the subterranean target point based on the comparison.

3. The method of claim 2, wherein the north orbit location is the northern orbit extreme and wherein the south orbit location is the southern orbit extreme.

4. The method of claim 2 wherein the subterranean target point is obtained by approximating the point of closest approach between the boresight lines extending through the first and second subterranean points.

5. The method of claim 2, including the additional steps of:

positioning the satellite at a third known orbit location;

calculating a northern payload extreme for the third location;

aligning the northern payload extreme with the northern region extreme;

calculating a third subterranean point at which the satellite boresight intersects the earth equatorial plane;

positioning the satellite at a fourth known orbit location symmetrical about an orbital mean relative to the third orbit location;

calculating a southern payload extreme for the fourth location;

aligning the southern payload extreme with the southern region extreme;

calculating a fourth subterranean point at which the satellite boresight intersects the earth equatorial plane;

optimizing the subterranean target point based on a numerical comparison of the subterranean points.

6. A method for steering the payload beam of a satellite in a non-geostationary earth orbit toward an intended service area having known geographical dimensions, comprising the steps of:

determining the position of a subterranean target point, the target point being at least 100 kilometers below the carth'"'"'s surface and distinct from the earth center;

selecting a target vector fixed in the payload pattern;

determining the satellite position;

directing the target vector toward the target point; and

maintaining the target vector pointing toward the target point using an on-board attitude control system.

7. The method of claim 6, wherein the satellite is in a geosynchronous orbit having an inclination angle of ten degrees or less, and wherein the position of the subterranean target point is determined by the step of:

calculating the position of the target vector when the satellite is in its preferred pointing attitude at different satellite locations within the orbit to obtain a set of target vectors; and

choosing the subterranean target point at a point that minimizes a payload pointing metric over the set of target vectors.

8. The method of claim 6, including the additional steps of:

selecting a second vector fixed in the payload beam;

selecting a third vector in a direction fixed relative to the earth; and

directing the target vector so that the second vector is maintained perpendicular relative to the third vector.

9. The method of claim 8, including the step of maintaining the third vector parallel to a spin axis of the earth.

10. A method for targeting the payload beam of a satellite in a geosynchronous earth orbit toward an intended service area having known geographical dimensions, the payload beam includes a boresight, and further wherein an orbit inclination angle, the northern and southern region extremes of the intended service area, and the payload beam half-angle are all known, said method comprising the steps of:

determining a subterranean target point, the target point being distinct from the earth center;

orienting the satellite payload beam toward the subterranean target point;

maintaining the payload beam orientation during orbit using an on board attitude control system;

calculating a northern payload extreme when the satellite is in a first known orbit location;

aligning the northern payload extreme with the northern region extreme;

calculating a first subterranean point at which the satellite boresight intersects the earth equatorial plane;

calculating a southern payload extreme when the satellite is in a second known orbit location;

aligning the southern payload extreme with the southern region extreme;

calculating a second subterranean point at which the satellite boresight intersects the earth equatorial plane;

comparing the first subterranean point to the second subterranean point; and

choosing the subterranean target point based on the comparison.

11. The method of claim 10, wherein the north orbit location is the northern orbit extreme and wherein the south orbit location is the southern orbit extreme.

12. The method of claim 10, wherein the subterranean target point is obtained by approximating the point of closest approach between the boresight lines extending through the first and second subterranean points.

13. The method of claim 10, including the additional steps of:

positioning the satellite at a third known orbit location;

calculating a northern payload extreme for the third location;

aligning the northern payload extreme with the northern region extreme;

calculating a third subterranean point at which the satellite boresight intersects the earth equatorial plane;

positioning the satellite at a fourth known orbit location symmetrical about an orbital mean relative to the third orbit location;

calculating a southern payload extreme for the fourth location;

aligning the southern payload extreme with the southern region extreme;

calculating a fourth subterranean point at which the satellite boresight intersects the earth equatorial plane; and

optimizing the subterranean target point based on a numerical comparison the subterranean points.

14. A method for steering the payload beam of a satellite in a non-geostationary earth orbit toward an intended service area having known geographical dimensions, wherein the satellite is in a geosynchronous orbit having an inclination angle of ten degrees or less, the method comprising the steps of:

determining the position of a subterranean target point, the target point being at least 100 kilometers below the earth'"'"'s surface and distinct from the earth center and wherein said step of determining the position of the subterranean target point further comprises the steps of;

calculating the position of the target vector when the satellite is in its preferred pointing attitude at different satellite locations within the orbit to obtain a set of target vectors; and

choosing the subterranean target point at a point that minimizes a payload pointing metric over the set of target vectors;

selecting a target vector fixed in the payload pattern;

determining the satellite position;

directing the target vector toward the target point; and

maintaining the target vector pointing toward the target point using an on-board attitude control system.

15. The method of claim 14, including the additional steps of:

selecting a second vector fixed in the payload beam;

selecting a third vector in a direction fixed relative to the earth; and

directing the target vector so that the second vector is maintained perpendicular relative to the third vector.

16. The method of claim 15, including the step of maintaining the third vector parallel to a spin axis of the earth.