Unambiguous position determination using two low-earth orbit satellites

• US 6,327,534 B1
• Filed: 09/30/1996
• Issued: 12/04/2001
• Est. Priority Date: 09/30/1996
• Status: Expired due to Term

• Current Assignee: Qualcomm, Inc.
• Original Assignee: Qualcomm, Inc.
• Inventors: Victor, Edward B., Vembu, Sridhar, Levanon, Nadav
• Primary Examiner(s): LOUIS JACQUES, JACQUES H
• Application Number:
  US08/723,725
• Time in Patent Office: 1,891 Days
• Field of Search: 701/213, 701/214, 701/215, 701/216, 701/206, 701/207, 701/200, 701/300, 701/225, 701/226, 342/357, 342/356, 342/354, 342/353, 342/358, 342/455, 340/990, 340/995, 340/998, 455/10, 455/15, 455/13.1, 455/12.1, 455/13.2, 455/456, 455/427, 455/13.4, 455/69, 455/426, 455/450, 455/9, 455/67.5, 455/13.3
• US Class Current: 701/215
• CPC Class Codes: G01S 2205/008 using a mobile telephone network
• CPC Class Codes: G01S 5/12 by co-ordinating position lines of different shape, e.g. hyperbolic, circular, elliptical or radial

Abstract

A system and method for unambiguously determining the position of a user terminal (for example, a mobile wireless telephone) in a low-Earth orbit satellite communications system. The system includes a user terminal, at least two satellites with known positions and known velocities, and a gateway (that is, a terrestrial base station) for communicating with the user terminal through the satellites. The method includes the steps of determining a range parameter, a range difference parameter, and either or both of a range-rate parameter and a range-rate difference parameter. A range parameter represents a distance between one of the satellites and the user terminal. A range difference parameter represents the difference between (1) the distance between a first one of the satellites and the user terminal and (2) the distance between a second one of the satellites and the user terminal. A range-rate parameter represents a relative radial velocity between one of the satellites and the user terminal. A range-rate difference parameter represents the difference between (a) a relative radial velocity between a first one of the satellites and the user terminal and (b) a relative radial velocity between a second one of the satellites and the user terminal. The position of the user terminal on the Earth'"'"'s surface is then determined based on the known positions and known velocities of the satellites, the range parameter, the range difference parameter, and either or both of the range-rate parameter and the range-rate difference parameter.

Claims

1. A position determining system for a satellite communications system, comprising:

a user terminal;

at least two satellites with known positions and known velocities;

a gateway for communicating with said user terminal through said satellites;

range parameter determining means for determining a range parameter that represents a distance between one of said satellites and said user terminal;

range difference parameter determining means for determining a range difference parameter that represents a difference between (1) the distance between one of said satellites and said user terminal and (2) the distance between another of said satellites and said user terminal;

at least one of;

range-rate parameter determining means for determining a range-rate parameter that represents a relative radial velocity between one of said satellites and said user terminal; and

range-rate difference parameter determining means for determining a range-rate difference parameter that represents a difference between (1) a relative radial velocity between one of said satellites and said user terminal and (2) a relative radial velocity between another of said satellites and said user terminal; and

position determining means in said gateway for determining a position of said user terminal on the Earth'"'"'s surface based on said known positions and velocities of said satellites, said range parameter, said range difference parameter, and at least one of said range-rate parameter and said range-rate difference parameter.

2. The position determining system of claim 1, wherein said range parameter represents a round-trip delay, further comprising:

round-trip delay measuring means in said gateway for measuring a round-trip delay of a signal, said signal transmitted from said gateway to said user terminal through one of said satellites and retransmitted from said user terminal to said gateway through one of said satellites.

3. The position determining system of claim 1, wherein said range difference parameter represents a delay difference, further comprising:

delay difference measuring means in said user terminal for measuring a delay difference between a first signal received from said gateway through a first one of said satellites and a second signal received from said gateway through a second one of said satellites.

4. The position determining system of claim 3, wherein at least one of said first and second signals is precorrected in time to compensate for delays associated with the difference between (a) the distance between said gateway and said first one of said satellites and (b) the distance between said gateway and said second one of said satellites.

5. The position determining system of claim 3, wherein said gateway adjusts said delay difference to compensate for delays associated with the difference between (a) the distance between said gateway and said first one of said satellites and (b) the distance between said gateway and said second one of said satellites.

6. The position determining system of claim 1, wherein said range-rate parameter represents frequency measurements of a first signal and a second signal, further comprising:

first frequency measuring means in said user terminal for measuring a frequency of the first signal, the first signal received from said gateway through one of said satellites;

sending means in said user terminal for sending said frequency measurement of the first signal to said gateway; and

second frequency measuring means in said gateway for measuring a frequency of the second signal, the second signal received from said user terminal through one of said satellites.

7. The position determining system of claim 1, wherein said range-rate difference parameter represents a frequency difference, further comprising:

frequency difference measuring means in said user terminal for measuring a frequency difference between a frequency of a first signal received from said gateway through a first one of said satellites and a frequency of a second signal received from said gateway through a second one of said satellites.

8. The position determining system of claim 7, wherein at least one of said first and second signals is precorrected in frequency to compensate for Doppler shift caused by the difference between (a) a relative radial velocity between said gateway and said first one of said satellites and (b) a relative radial velocity between said gateway and said second one of said satellites.

9. The position determining system of claim 7, wherein said gateway adjusts said frequency difference to compensate for Doppler shifts caused by (a) a relative radial velocity between said gateway and said first one of said satellites and (b) a relative radial velocity between said gateway and said second one of said satellites.

10. For use in a position determining system including a user terminal, at least two satellites with known positions and known velocities, a gateway for communicating with the user terminal through the satellites, and means for determining parameters describing the position of the user terminal relative to the satellites, a computer program product comprising:

a computer usable medium having computer readable program code means embodied in said medium for causing an application program to execute on the computer system, said computer readable program code means comprising;

a computer readable first program code means for causing the computer system to generate a M×

1 parameter vector z comprising said parameters, wherein M is the number of parameters determined;

a computer readable second program code means for causing the computer system to generate a position vector x representing an initial reference point;

a computer readable third program code means for causing the computer system to generate a partial derivative matrix H containing information regarding the position of the satellites and an Earth model describing the shape of the Earth wherein the relationship between x and H is given by;

$H=H<br><br>\left(x\right)=\frac{\partial <br><br>h}{\partial <br><br>x}<br><br>\left(x\right)$

a computer readable fourth program code means for causing the computer system to generate a M×

M weight matrix W to emphasize the influence of specific parameters; and

a computer readable fifth program code means for causing the computer system to execute the iterative equation;

11. The computer program product of claim 10, wherein said computer readable program code means further comprises:

a computer readable sixth program code means for causing the computer system to use a smooth model of the Earth until the difference between {circumflex over (x)}_i and {circumflex over (x)}_i+1 falls below a second predetermined threshold, and a detailed digital terrain model of the Earth thereafter.

12. The computer program product of claim 10, wherein said weight matrix W is the inverse of the measurement error covariance matrix.

13. The computer program product of claim 10, wherein said computer readable program code means further comprises:

a further computer readable program code means for causing the computer system to use a first weight matrix W₁ for the first n iterations, and a second weight matrix W₂ thereafter, wherein n is a predetermined number, said second weight matrix W₂ is the inverse of the measurement error covariance matrix, and said first weight matrix W₁ gives greater weight to said range-rate parameters and said range-rate difference parameters than to said range parameters and said range difference parameters, beyond the differences in weights in said second weight matrix W₂.

14. The computer program product of claim 10, wherein said computer readable program code means further comprises:

a further computer readable program code means for causing the computer system to use a smooth model of the Earth for the first n iterations, and a detailed digital terrain model of the Earth thereafter, wherein n is a predetermined number.

15. The computer program product of claim 10, wherein said computer readable program code means further comprises:

a further computer readable program code means for causing the computer system to use a first weight matrix W₁ until the difference between {circumflex over (x)}_i and {circumflex over (x)}_i+1 falls below a third predetermined threshold, and a second weight matrix W₂ after the difference between {circumflex over (x)}_i and {circumflex over (x)}_i+1 falls below said third predetermined threshold distance, wherein said second weight matrix W₂ is the inverse of the measurement error covariance matrix, and said first weight matrix W ₁ gives greater weight to said range-rate parameters and said range-rate difference parameters than to said range parameters and said range difference parameters, beyond the differences in weights in said second weight matrix W₂.

16. In a communications system comprising a user terminal, at least two satellites with known positions and known velocities, and a gateway for communicating with the user terminal through the satellites, a method for determining the position of the user terminal, comprising the steps of:

(a) determining a range parameter that represents a distance between one of the satellites and the user terminal;

(b) determining a range difference parameter that represents a difference between (1) the distance between one of the satellites and the user terminal and (2) the distance between another of the satellites and the user terminal;

(c) determining at least one of a range-rate parameter that represents a relative radial velocity between one of the satellites and the user terminal and a range-rate difference parameter that represents a difference between (1) a relative radial velocity between one of the satellites and the user terminal and (2) a relative radial velocity between another of the satellites and the user terminal; and

(d) determining the position of the user terminal on the Earth'"'"'s surface based on the known positions and known velocities of the satellites, said range parameter, said range-rate parameter, and at least one of said range difference parameter and said range-rate difference parameter.

17. The method of claim 16, wherein said range parameter represents a round-trip delay, wherein step (a) further comprises the step of:

(i) measuring, at the gateway, a round-trip delay of a signal, said signal transmitted from the gateway to the user terminal through one of the satellites and retransmitted from the user terminal to the gateway through one of the satellites.

18. The method of claim 16, wherein said range difference parameter represents a delay difference, wherein step (b) further comprises the step of:

(i) measuring, at the user terminal, a delay difference between a first signal received from the gateway through a first one of the satellites and a second signal received from the gateway through a second one of the satellites.

19. The method of claim 18, wherein at least one of said first and second signals is precorrected in time to compensate for delays associated with the difference between (a) the distance between the gateway and said first one of the satellites and (b) the distance between the gateway and said second one of the satellites.

20. The method of claim 18, wherein the gateway adjusts said delay difference to compensate for delays associated with the difference between (a) the distance between the gateway and said first one of the satellites and (b) the distance between the gateway and said second one of the satellites.

21. The method of claim 16, wherein, when said range-rate parameter is to be determined, then step (c) further comprises the steps of:

(i) measuring, at the user terminal, a frequency of a first signal received from the gateway through one of the satellites;

(ii) sending said frequency measurement of said first signal to the gateway;

(iii) transmitting a second signal from the user terminal to the gateway through one of the satellites; and

(iv) measuring, at the gateway, a frequency of a frequency of a second signal received from the user terminal through one of the satellites, wherein said range-rate parameter represents said frequency measurements of said first and second signals.

22. The method of claim 16, wherein, when said:

range-rate difference parameter is to be determined, then step (c) further comprises the steps of;

(i) transmitting a first signal from the gateway to the user terminal through a first one of the satellites and transmitting a second signal from the gateway to the user terminal through a second one of the satellites; and

(ii) measuring, at the user terminal, a frequency difference between a frequency of said first signal and a frequency of said second signal, wherein said range-rate difference parameter represents said frequency difference.

23. The method of claim 22, wherein at least one of said first and second signals is precorrected in frequency to compensate for Doppler shift caused by the difference between (a) a relative radial velocity between the gateway and said first one of the satellites and (b) a relative radial velocity between the gateway and said second one of the satellites.

24. The method of claim 22, wherein the gateway adjusts said frequency difference to compensate for Doppler shift caused by the difference between (a) a relative radial velocity between the gateway and said first one of the satellites and (b) a relative radial velocity between the gateway and said second one of the satellites.

25. In a communications system comprising at least two satellites with known positions and known velocities and a gateway for communicating with a user terminal through the satellites, a user terminal comprising:

means for retransmitting a first signal received from the gateway through one of the satellites;

range difference parameter determining means for determining a range difference parameter that represents a difference between (1) the distance between one of the satellites and the user terminal and (2) the distance between another of the satellites and the user terminal; and

at least one of;

range-rate difference parameter determining means for determining a range-rate difference parameter that represents a difference between (1) a relative radial velocity between one of the satellites and the user terminal and (2) a relative radial velocity between another of the satellites and the user terminal; and

means for measuring a frequency of a second signal transmitted by the gateway through a further one of the satellites, sending said frequency measurement to the gateway, and transmitting a third signal to said gateway through said further one of the satellites;

wherein the position of the user terminal on the Earth'"'"'s surface can be determined based on said retransmitted first signal, said range difference parameter, the known positions and known velocities of the satellites, and at least one of said range-rate difference parameter, said frequency measurement and said third signal.

26. A position determining system for a satellite communications system, comprising:

a user terminal;

at least two satellites with known positions and known velocities;

a gateway for communicating with said user terminal through said satellites;

range parameter determining means for determining a range parameter that represents a distance between one of said satellites and said user terminal;

range difference parameter determining means for determining a range difference parameter that represents a difference between (1) the distance between one of said satellites and said user terminal and (2) the distance between another of said satellites and said user terminal;

range-rate parameter determining means for determining a range-rate parameter that represents a relative radial velocity between one of said satellites and said user terminal;

range-rate difference parameter determining means for determining a range-rate difference parameter that represents a difference between (1) a relative radial velocity between one of said satellites and said user terminal and (2) a relative radial velocity between another of said satellites and said user terminal; and

position determining means in said gateway for determining the position of said user terminal on the Earth'"'"'s surface based on said range parameter, said range-rate parameter, said range difference parameter, said range-rate difference parameter, and said known positions and known velocities of said satellites.

27. A position determining system for a satellite communications system, comprising:

a user terminal;

at least two satellites with known positions and known velocities;

a gateway for communicating with said user terminal through said satellites;

range parameter determining means for determining a range parameter that represents a distance between one of said satellites and said user terminal;

range difference parameter determining means for determining a range difference parameter that represents a difference between (1) the distance between one of said satellites and said user terminal and (2) the distance between another of said satellites and said user terminal;

range-rate difference parameter determining means for determining a range-rate difference parameter that represents a difference between (1) a relative radial velocity between one of said satellites and said user terminal and (2) a relative radial velocity between another of said satellites and said user terminal; and

position determining means in said gateway for determining the position of said user terminal on the Earth'"'"'s surface based on said range parameter, said range difference parameter, said range-rate difference parameter, and said known positions and known velocities of said satellites.

28. A position determining system for a satellite communications system, comprising:

a user terminal;

at least two satellites with known positions and known velocities;

a gateway for communicating with said user terminal through said satellites;

range parameter determining means for determining a range parameter that represents a distance between one of said satellites and said user terminal;

range difference parameter determining means for determining a range difference parameter that represents a difference between (1) the distance between one of said satellites and said user terminal and (2) the distance between another of said satellites and said user terminal;

range-rate parameter determining means for determining a range-rate parameter that represents a relative radial velocity between one of said satellites and said user terminal; and

position determining means in said gateway for determining the position of said user terminal on the Earth'"'"'s surface based on said range parameter, said range-rate parameter, said range difference parameter, and said known positions and known velocities of said satellites.

29. A position determining system for a satellite communications system, comprising:

a user terminal;

at least two satellites with known positions and known velocities;

a gateway for communicating with said user terminal through said satellites;

range parameter determining means for determining a range parameter;

range difference parameter determining means for determining a range difference parameter;

at least one of;

range-rate parameter determining means for determining a range-rate parameter; and

range-rate difference parameter determining means for determining a range-rate difference parameter; and

position determining means in said gateway for determining a position of said user terminal on the Earth'"'"'s surface based on said known positions and velocities of said satellites, said range parameter, said range difference parameter, and at least one of said range-rate parameter and said range-rate difference parameter, said position determining means comprising

means for generating a M×

1 parameter vector z comprising said parameters, wherein M is the number of parameters determined;

means for generating a position vector x representing an initial reference point;

means for generating a partial derivative matrix H containing information regarding said known positions and velocities of said satellites and an Earth model describing the shape of the Earth wherein the relationship between x and H is given by $H=H<br><br>\left(x\right)=\frac{\partial <br><br>h}{\partial <br><br>x}<br><br>\left(x\right)$

means for generating a M×

M weight matrix W to emphasize the influence of specific parameters; and

means for executing the iterative equation

30. The position determining system of claim 29, wherein said position determining means further comprises:

means for using a smooth model of the Earth until the difference between {circumflex over (x)}_i and {circumflex over (x)}_i+1 falls below a second predetermined threshold, and a detailed digital terrain model of the Earth thereafter.

31. The position determining system of claim 29, wherein said weight matrix W is the inverse of the measurement error covariance matrix.

32. The position determining system of claim 29, wherein said position determining means further comprises:

means for using a first weight matrix W₁ for the first n iterations, and a second weight matrix W₂ thereafter, wherein n is a predetermined number, said second weight matrix W₂ is the inverse of the measurement error covariance matrix, and said first weight matrix W₁ gives greater weight to said range-rate parameters and said range-rate difference parameters than to said range parameters and said range difference parameters, beyond the differences in weights in said second weight matrix W₂.

33. The position determining system of claim 29, wherein said position determining means further comprises:

means for using a smooth model of the Earth for the first n iterations, and a detailed digital terrain model of the Earth thereafter, wherein n is a predetermined number.

34. The position determining system of claim 29, wherein said position determining means further comprises:

means for using a first weight matrix W₁ until the difference between {circumflex over (x)}_i and {circumflex over (x)}_i+1 falls below a third predetermined threshold distance, and a second weight matrix W₂ after the difference between {circumflex over (x)}_i and {circumflex over (x)}_i+1 falls below said third predetermined threshold, wherein said second weight matrix W₂ is the inverse of the measurement error covariance matrix, and said first weight matrix W₁ gives greater weight to said range-rate parameters and said range-rate difference parameters than to said range parameters and said range difference parameters, beyond the differences in weights in said second weight matrix W₂.