Method and apparatus for precision attitude determination and kinematic positioning

• US 4,963,889 A
• Filed: 09/26/1989
• Issued: 10/16/1990
• Est. Priority Date: 09/26/1989
• Status: Expired due to Term

• Current Assignee: Hughes Electronics Corporation (Rtx Corporation)
• Original Assignee: Magnavox Government and Industrial Electronics Company
• Inventors: Hatch, Ronald R.
• Primary Examiner(s): Tarcza, Thomas H.
• Assistant Examiner(s): Hellner, Mark
• Application Number:
  US07/413,411
• Time in Patent Office: 385 Days
• Field of Search: 342/357, 342/380, 342/450, 342/453
• US Class Current: 342/357.27
• CPC Class Codes: G01S 19/44 Carrier phase ambiguity resolution; Floating ambiguity; LAMBDA [Least-squares AMBiguity Decorrelation Adjustment] method
• CPC Class Codes: G01S 19/55 Carrier phase ambiguity resolution; Floating ambiguity; LAMBDA [Least-squares AMBiguity Decorrelation Adjustment] method

Abstract

A technique for resolving whole-cycle ambiguity that is inherent in phase-angle measurements of signals received from multiple satellite-based transmitters in a global positioning system. The relative position of a secondary receiving antenna with respect to a reference antenna is approximately known or approximately initially determined and then measurements from a minimum number of satellites are used to determine an initial set of potential solutions to the relative position of the secondary antenna that fall within a region of uncertainty surrounding the approximate position. Redundant measurements are taken from one or more additional satellites and used to progressively reduce the number of potential solutions to close to one. Even if the number of potential solutions is not reduced to one true solution, the number can be further reduced by using additional measurements taken at different time intervals, at which different satellite geometries prevail. The disclosed technique produces rapid elimination of false solutions and permits realtime computation of relative position in kinetic positioning applications, and of angular orientation in attitude determination applications.

Claims

1. A method for determining the relative position of a secondary receiving antenna with respect to a reference receiving antenna in a satellite-based positioning system, the method comprising the steps of:

making carrier phase measurements based on the reception of a carrier signal from each of a plurality N of satellites, where N is the minimum number of satellites needed to compute the relative position of the secondary antenna;

deriving from the carrier phase measurements an initial set of potential solutions for the relative position, wherein the initial set of potential solutions all fall within a region of uncertainty defined by a sphere having a radius equal to the maximum distance between the two antennas, and wherein multiple potential solutions arise because of whole-cycle ambiguity of the carrier signal;

making redundant carrier phase measurements based on the reception of a carrier signal from an additional (N+1)th satellite; and

eliminating false solutions from the initial set of potential solutions, based on a comparison of the redundant carrier phase measurements with the initial set of potential solutions, to reduce number of potential solutions to close to one, whereby the number of potential solutions is not reduced by use of the redundant carrier phase measurements.

2. A method as defined in claim 1, and further comprising the steps of:

making redundant carrier phase measurements based on the reception of a carrier signal from other additional satellites; and

eliminating other false solutions from the set of potential solutions, based on a comparison of the additional redundant carrier phase measurements with the initial set of potential solutions.

3. A method as defined in claim 1, and further comprising the steps of:

comparing items in the set of potential solutions with solutions obtained in a prior time interval, to provide another basis for eliminating false solutions.

4. A method as defined in claim 1, wherein:

the step of deriving an initial set of potential solutions includes locating points of intersection of planar carrier wavefronts defining possible locations of the secondary antenna within the region of uncertainty; and

the step of eliminating false solutions includes, locating a set of planar carrier wavefronts from the additional satellite such that the wavefronts also define possible locations of the secondary antenna within the region of uncertainty, selecting, for each of the initial set of potential solutions, a planar carrier wavefront from the additional satellite such that the selected wavefront is the one closest to the potential solution, and disregarding each potential solution for which the closest wavefront from the additional satellite is spaced from the potential solution by more than a selected threshold.

5. A method as defined in claim 1, wherein:

the initial set of potential solutions is initially stored in a local tangent coordinate system, x, y, z, where z is a vertical axis; and

the method further comprises, after the step of making redundant carrier phase measurements, the additional step of rotating the coordinate system of the set of potential solutions, to point the z axis toward the additional satellite and thereby facilitate the step of eliminating false solutions.

6. A method as defined in claim 4, wherein:

the initial set of potential solutions is initially stored in a local tangent coordinate system, x, y, z, where z is a vertical axis; and

the method further comprises, after the step of making redundant carrier phase measurements, the additional step of rotating the coordinate system of the set of potential solutions, to point the z axis toward the additional satellite and thereby facilitate the step of eliminating false solutions.

7. A method as defined in claim 6, wherein the step of selecting a planar carrier wavefront from the additional satellite is performed by comparing the z-axis component of each potential solution with possible positions of wavefronts in the region of uncertainty.

8. A method as defined in claim 1, wherein:

the secondary antenna is held at a fixed distance from the reference antenna;

the method further comprises the step of determining from the relative position of the secondary antenna the angular attitude of a line between the two antennas, with respect to a selected set of coordinate axes; and

the minimum number or satellites N is two.

9. A method as defined in claim 8, wherein:

the method further comprises the steps of making carrier phase measurements and deriving potential solutions for a third antenna located at a fixed distance from each of the secondary and reference antennas, and the further step of determining the angular position of the third antenna with respect to an axis of rotation through the reference and secondary antennas; and

and wherein the two satellites also function as redundant satellites by providing additional carrier phase information to the third antenna.

10. A method as defined in claim 1, wherein:

the secondary antenna is freely movable with respect to the reference antenna; and

the method further comprises the initial step of determining the approximate initial relative position of the secondary antenna.

11. A method as defined in claim 10, wherein:

the step of determining the approximate position includes making measurements of pseudorandom codes received from the satellites, and computing the approximate position from the code measurements.

12. A method for determining the angular attitude of a line of fixed length between a reference receiving antenna and a secondary receiving antenna, from the relative position of the secondary receiving antenna with respect to the reference receiving antenna as determined in a satellite-based positioning system, the method comprising the steps of:

making carrier phase measurements based on the reception of a carrier signal from each of two satellites, where two is the minimum number of satellites needed to compute the relative position of the secondary antenna;

deriving from the carrier phase measurements an initial set of potential solutions for the relative position, wherein the initial set of potential solutions all fall within a region of uncertainty defined by the surface of a sphere having a radius equal to the fixed distance between the two antennas, and wherein multiple potential solutions arise because of wholecycle ambiguity of the carrier signal;

making redundant carrier phase measurements based on the reception of a carrier signal from a third satellite; and

eliminating false solutions from the initial set of potential solutions, based on a comparison of the redundant carrier phase measurements with the initial set of potential solutions, to reduce number of potential solutions to close to one, whereby the number of potential solutions is not reduced by use of the redundant carrier phase measurements.

13. A method as defined in claim 12, wherein:

the carrier phase measurements are first-difference measurements made measuring the phase difference between signals arriving simultaneously at the two antennas from a single satellite source.

14. A method as defined in claim 13, and further comprising the steps of:

making redundant carrier phase measurements based on the reception of a carrier signal from other additional satellites; and

eliminating other false solutions from the set of potential solutions, based on a comparison of the additional redundant carrier phase measurements with the initial set of potential solutions.

15. A method as defined in claim 13, and further comprising the steps of:

comparing items in the set of potential solutions with solutions obtained in a prior time interval, to provide another basis for eliminating false solutions.

16. A method as defined in claim 13, wherein:

the step of deriving an initial set of potential solutions includes locating points of intersection of planar carrier wavefronts defining possible locations of the secondary antenna within the region of uncertainty; and

the step of eliminating false solutions includes locating a set of planar carrier wavefronts from the additional satellite such that the wavefronts also define possible locations of the secondary antenna within the region of uncertainty, selecting, for each of the initial set of potential solutions, a planar carrier wavefront from the additional satellite such that the selected wavefront is the one closest to the potential solution, and disregarding each potential solution for which the closest wavefront from the additional satellite is spaced from the potential solution by more than a selected threshold.

17. A method as defined in claim 13, wherein:

the initial set of potential solutions is initially stored in a local tangent coordinate system, x, y, z, where z is a vertical axis; and

the method further comprises, after the step of making redundant carrier phase measurements, the additional step of rotating the coordinate system of the set of potential solutions, to point the z axis toward the additional satellite and thereby facilitate the step of eliminating false solutions.

18. A method as defined in claim 16, wherein:

the initial set of potential solutions is initially stored in a local tangent coordinate system, x, y, z, where z is a vertical axis; and

the method further comprises, after the step of making redundant carrier phase measurements, the additional step of rotating the coordinate system of the set of potential solutions, to point the z axis toward the additional satellite and thereby facilitate the step of eliminating false solutions.

19. A method as defined in claim 18, wherein the step of selecting a planar carrier wavefront from the additional satellite is performed by comparing the z-axis component of each potential solution with possible positions of wavefronts in the region of uncertainty.

20. A method as defined in claim 13, wherein:

the method further comprises the steps of making carrier phase measurements and deriving potential solutions for a third antenna located at a fixed distance from each of the secondary and reference antennas, and the further step of determining the angular position of the third antenna with respect to an axis of rotation through the reference and secondary antennas; and

and wherein the first two satellites also function as redundant satellites by providing additional carrier phase information to the third antenna.

21. Apparatus for determining the relative position of a secondary receiving antenna with respect to a reference receiving antenna in a satellite-based positioning system, the apparatus comprising:

means for making carrier phase measurements based on the reception of a carrier signal from each of a plurality N of satellites, where N is the minimum number of satellites needed to compute the relative position of the secondary antenna;

means for deriving from the carrier phase measurements an initial set of potential solutions for the relative position, wherein the initial set of potential solutions all fall within a region of uncertainty defined by a sphere having a radius equal to the maximum distance between the two antennas, and wherein multiple potential solutions arise because of whole-cycle ambiguity of the carrier signal;

means for making redundant carrier phase measurements based on the reception of a carrier signal from an additional (N+1)the satellite; and

means for eliminating false solutions from the initial set of potential solutions, based on a comparison of the redundant carrier phase measurements with the initial set of potential solutions, to reduce number of potential solutions to close to one, whereby the number of potential solutions is not reduced by use of the redundant carrier phase measurements.

22. Apparatus as defined in claim 21, and further comprising:

means for making redundant carrier phase measurements based on the reception of a carrier signal from other additional satellites; and

means for eliminating other false solutions from the set of potential solutions, based on a comparison of the additional redundant carrier phase measurements with the initial set of potential solutions.

23. Apparatus as defined in claim 21, and further comprising:

means for comparing items in the set of potential solutions with solutions obtained in a prior time interval, to provide another basis for eliminating false solutions.

24. Apparatus as defined in claim 21, wherein:

the means for deriving an initial set of potential solutions includes means for locating points of intersection of planar carrier wavefronts defining possible locations of the secondary antenna within the region of uncertainty; and

the means for eliminating false solutions includes means for locating a set of planar carrier wavefronts from the additional satellite such that the wavefronts also define possible locations of the secondary antenna within the region of uncertainty, means for selecting, for each of the initial set of potential solutions, a planar carrier wavefront from the additional satellite such that the selected wavefront is the one closest to the potential solution, and means for disregarding each potential solution for which the closest wavefront from the additional satellite is spaced from the potential solution by more than a selected threshold.

25. Apparatus as defined in claim 21, wherein:

the initial set of potential solutions is initially stored in a local tangent coordinate system, x, y, z, where z is a vertical axis; and

the apparatus further comprises means for rotating the coordinate system of the set of potential solutions, to point the z axis toward the additional satellite and thereby facilitate elimination of false solutions.

26. Apparatus as defined in claim 24, wherein:

the initial set of potential solutions is initially stored in a local tangent coordinate system, x, y, z, where z is a vertical axis; and

the apparatus further comprises means for rotating the coordinate system of the set of potential solutions, to point the z axis toward the additional satellite and thereby facilitate elimination of false solutions.

27. Apparatus as defined in claim 26, wherein the means for selecting a planar carrier wavefront from the additional satellite includes means for comparing the z-axis component of each potential solution with possible positions of wavefronts in the region of uncertainty.

28. Apparatus as defined in claim 21, wherein:

the secondary antenna is held at a fixed distance from the reference antenna;

the apparatus further comprises means for determining from the relative position of the secondary antenna the angular attitude of a line between the two antennas, with respect to a selected set of coordinate axes; and

the minimum number or satellites N is two.

29. A method as defined in claim 28, wherein:

the apparatus further comprises means for making carrier phase measurements and deriving potential solutions for a third antenna located at a fixed distance from each of the secondary and reference antennas, and means for determining the angular position of the third antenna with respect to an axis of rotation through the reference and secondary antennas;

and wherein the two satellites also function as redundant satellites by providing additional carrier phase information to the third antenna.

30. Apparatus as defined in claim 21, wherein:

the secondary antenna is freely movable with respect to the reference antenna; and

the apparatus further comprises means for determining the approximate initial relative position of the secondary antenna.

31. A method as defined in claim 30, wherein:

the means for determining the approximate position includes means for making measurements of pseudorandom codes received from the satellites, and means for computing the approximate position from the code measurements.

32. Apparatus for determining the angular attitude of a line of fixed length between a reference receiving antenna and a secondary receiving antenna, from the relative position of the secondary receiving antenna with respect to the reference receiving antenna as determined in a satellite-based positioning system, the apparatus comprising:

means for making carrier phase measurements based on the reception of a carrier signal from each of two satellites, where two is the minimum number of satellites needed to compute the relative position of the secondary antenna;

means for deriving from the carrier phase measurements an initial set of potential solutions for the relative position, wherein the initial set of potential solutions all fall within a region of uncertainty defined by the surface of a sphere having a radius equal to the fixed distance between the two antennas, and wherein multiple potential solutions arise because of whole-cycle ambiguity of the carrier signal;

means for making redundant carrier phase measurements based on the reception of a carrier signal from a third satellite; and

means for eliminating false solutions from the initial set of potential solutions, based on a comparison of the redundant carrier phase measurements with the initial set of potential solutions, to reduce number of potential solutions to close to one, whereby the number of potential solutions is not reduced by use of the redundant carrier phase measurements.