Method and apparatus for generating and distributing satellite tracking information

• US 20070260399A1
• Filed: 01/17/2006
• Published: 11/08/2007
• Est. Priority Date: 06/06/2001
• Status: Active Grant

• Current Assignee: Avago Technologies International Sales Pte Limited (Broadcom, Inc.)
• Original Assignee: Global Locate Incorporated (Broadcom, Inc.)
• Inventors: Abraham, Charles, Riben, Matthew, van Diggelen, Frank
• Granted Patent: US 7,443,340 B2
• Time in Patent Office: Days
• US Class Current: 701/226
• CPC Class Codes: B64G 1/1014 Navigation satellites
• CPC Class Codes: G01S 19/05 providing aiding data
• CPC Class Codes: G01S 19/258 relating to the satellite constellation, e.g. almanac, ephemeris data, lists of satellites in view
• CPC Class Codes: G01S 19/27 creating, predicting or correcting ephemeris or almanac data within the receiver

Abstract

A method and apparatus for generating and distributing satellite tracking data to a remote receiver is disclosed. The method for includes extracting from satellite-tracking data initial model parameters representing a current orbit of at least one satellite-positioning-system satellite, computing an orbit model using the initial model parameters, wherein a duration of the orbit model is longer than a duration of the satellite-tracking data, comparing, for an overlapping period of time, the orbit model to the satellite-tracking data; and adjusting the orbit model to match the satellite tracking data for the overlapping period of time so as to form an adjusted orbit model. The adjusted orbit model comprises the long-term-satellite-tracking data.

Claims

8-1. The apparatus of claim 11, wherein the orbit model comprises at least one of:

square root of a semi-major axis, eccentricity, amplitude of a sine harmonic correction term to an orbit radius, amplitude cosine harmonic correction term to an orbit radius, mean motion difference, mean anomaly at a reference time, amplitude of a cosine harmonic correction to an argument of latitude, amplitude of a sine harmonic correction to the argument of latitude, amplitude of a cosine harmonic correction to an argument of inclination, amplitude of a sine harmonic correction to the argument of inclination, longitudinal of an ascending node of an orbit plane at a weekly epoch, inclination angle at a reference time, rate of inclination angle, and rate of right ascension and argument of perigee.

11. A apparatus for creating long term satellite tracking data, the apparatus comprising:

memory having stored therein executable instructions;

a processor operable to execute the executable instructions to;

a) extract from satellite-tracking data initial model parameters representing a current orbit of at least one satellite-positioning-system satellite;

b) compute an orbit model using the initial model parameters, wherein a duration of the orbit model is longer than a duration of the satellite-tracking data;

c) compare, for an overlapping period of time, the orbit model to the satellite-tracking data; and

d) adjust the orbit model to match the satellite tracking data for the overlapping period of time so as to form an adjusted orbit model, wherein the adjusted orbit model comprises the long term satellite tracking data.

1. A method for creating long-term-satellite-tracking data, the method comprising:

a) extracting from satellite-tracking data initial model parameters representing a current orbit of at least one satellite-positioning-system satellite;

b) computing an orbit model using the initial model parameters, wherein a duration of the orbit model is longer than a duration of the satellite-tracking data;

c) comparing, for an overlapping period of time, the orbit model to the satellite-tracking data; and

d) adjusting the orbit model to match the satellite tracking data for the overlapping period of time so as to form an adjusted orbit model, wherein the adjusted orbit model comprises the long-term-satellite-tracking data.

2. The method of claim 1, further comprising:

iterating c) and d) until an error produced by c) is less than a threshold.

3. The method of claim 1, wherein c) comprises:

determining at least one difference between at least on point in the orbit model and at least one point in the satellite-tracking data;

squaring the at least one difference to form a square of the at least one difference;

summing the square of the at least one difference to form at least one resulting sum; and

comparing the at least one resulting sum to a threshold.

4. The method of claim 3, further comprising:

iterating c) and d) in view of comparing the at least one resulting sum to a threshold.

5. The method of claim 1, wherein the duration the orbit model is four hours, and wherein the duration of the orbit model is more than four hours.

6. The method of claim 5, wherein the duration of the orbit model is six hours.

7. The method of claim 1, wherein d) further comprises:

using a subspace trust region method based on the interior-reflective Newton method.

8. The method of claim 1, wherein the orbit model comprises at least one of:

square root of a semi-major axis, eccentricity, amplitude of a sine harmonic correction term to an orbit radius, amplitude cosine harmonic correction term to an orbit radius, mean motion difference, mean anomaly at a reference time, amplitude of a cosine harmonic correction to an argument of latitude, amplitude of a sine harmonic correction to the argument of latitude, amplitude of a cosine harmonic correction to an argument of inclination, amplitude of a sine harmonic correction to the argument of inclination, longitudinal of an ascending node of an orbit plane at a weekly epoch, inclination angle at a reference time, rate of inclination angle, and rate of right ascension and argument of perigee.

9. The method of claim 1, wherein the orbit model comprises a mathematical representation of a satellite trajectory.

10. The method of claim 1, further comprising:

receiving the satellite-tracking data from a worldwide-reference network, wherein the worldwide-reference network comprises a plurality of satellite-signal receivers.

12. The apparatus of claim 11, wherein the processor is further operable to execute the executable instructions to:

iterate c) and d) until an error produced by c) is less than a threshold.

13. The apparatus of claim 12, wherein the executable instructions to c) comprise executable instructions to:

determine at least one difference between at least on point in the orbit model and at least one point in the satellite-tracking data;

square the at least one difference to form a square of the at least one difference;

sum the square of the at least one difference to form at least one resulting sum; and

compare the at least one resulting sum to a threshold.

14. The apparatus of claim 13, wherein the processor is further operable to execute the executable instructions to:

iterate c) and d) in view of executing the executable instructions to compare the at least one resulting sum to a threshold.

15. The apparatus of claim 11, wherein the duration the orbit model is four hours, and wherein the duration of the orbit model is more than four hours.

16. The apparatus of claim 15, wherein the duration of the orbit model is six hours.

17. The apparatus of claim 11, wherein the executable instructions to d) comprise executable instruction to:

use a subspace trust region method based on the interior-reflective Newton method.

19. The apparatus of claim 11, wherein the orbit model comprises a mathematical representation of a satellite trajectory.

20. The apparatus of claim 11, wherein the processor is further operable to execute executable instructions to:

receive the satellite-tracking data from a worldwide-reference network, wherein the worldwide-reference network comprises a plurality of satellite-signal receivers.