Method and apparatus for determining positions on the earth corresponding to an observed rate of change of satellite range

• US 5,488,378 A
• Filed: 12/28/1993
• Issued: 01/30/1996
• Est. Priority Date: 12/28/1993
• Status: Expired due to Term

• Current Assignee: CSR Technology Incorporated (Qualcomm, Inc.)
• Original Assignee: Rockwell International Corporation
• Inventors: Colley, Jaime B.
• Primary Examiner(s): Issing, Gregory C.
• Application Number:
  US08/174,085
• Time in Patent Office: 763 Days
• Field of Search: 342/357
• US Class Current: 342/357.25
• CPC Class Codes: G01S 19/42 Determining position

Abstract

A method for using a value of range rate observed by a receiver, such as a GPS receiver, at a particular location, along with other satellite information, to determine the coordinates of points on the surface of the earth from which this value of range rate would be observed. These coordinates are given in an earth-centered, earth-fixed (ECEF) coordinate system, and they form a locus of points of equal range rate. The coordinates of these points provide estimates of the location of the GPS receiver.

Claims

1. A method of determining, for a particular position, location coordinates for the particular position, the method comprising the steps of:

receiving, at a receiver located at the particular position, signals from at least one earth-orbiting satellite, the signals including orbital information indicating the general location of the at least one satellite with respect to an earth-centered, earth-fixed (ECEF) coordinate system;

measuring the rate of change of the range from the satellite to the receiver; and

calculating, based upon the satellite orbital information and measured rate of change of the range from the satellite to the receiver, a first plurality of points representing a first line on the earth'"'"'s surface along which the rate of change of range of the satellite is constant, such that the location of the receiver at the particular position is near the first line.

2. The method of claim 1, further comprising the steps of:

receiving, at the receiver, signals from a second earth-orbiting satellite;

measuring the rate of change of the range from the second satellite to the receiver; and

calculating a second plurality of points representing a second line on the earth'"'"'s surface which intersects the first line, wherein the receiver is approximately located near the intersection of the first and second lines.

3. The method of claim 2, further comprising the step of calculating additional pluralities of points to determine additional corresponding lines which intersect the first and second lines, wherein the particular position is approximately located near the intersection of the lines.

4. An apparatus for estimating a location of a particular position on the earth according to signals transmitted by at least one satellite orbiting the earth, comprising:

a receiver for receiving the transmitted signals, the receiver being located at the particular position, wherein the signals indicate an associated satellite from which they are transmitted;

means for determining the location of the satellite and the speed of the satellite as it orbits the earth, relative to the particular position;

means for measuring a rate of change of the range from the receiver to the satellite, as the satellite orbits the earth; and

means for determining a first plurality of points representing a first line on the earth'"'"'s surface along which the rate of change of the range of the satellite is constant, wherein the receiver, located at the particular position, is located near the first line.

5. The apparatus of claim 4, wherein the receiver receives signals from additional earth-orbiting satellites such that the ranges from the additional satellites to the receiver are measured, and further wherein corresponding pluralities of points representing corresponding lines n the earth'"'"'s surface which intersect the first line are determined, such that the intersection of the pluralities of points defines the location of the receiver at the particular position.

6. A method of estimating the position of a particular location on the surface of the earth, with respect to an earth-centered, earth-fixed (ECEF) x, y, z coordinate system, from signals transmitted by a plurality of earth-orbiting satellites, each satellite having an associated position (X_S, Y_S, Z_S), a distance d_S to the center of the earth, a velocity vector V_S having vector components (V_Sx, V_Sy, V_Sz) and magnitude |V_S |, the earth having a radius R_e and a gravitational vector g_S relative to the satellite, the method comprising the steps of:

receiving, at a receiver located at the particular location on the surface of the earth, signals from at least one of the earth-orbiting satellites, wherein the signals include orbital information describing the rate of change of the range I between the receiver and the at least one satellite;

measuring the rate of change of the range I between the receiver and the at least one satellite according to the satellite orbital information; and

determining coordinates (P_lx, P_ly, P_lz) of multiple points P_I on the earth based upon the measured rate of change of the range I to the satellite, wherein the coordinates (P_lx, P_ly, P_lz) describe a locus of points which provide estimates of the particular location of the receiver.

7. A method of estimating the position of a particular location on the surface of the earth using information received from a plurality of earth-orbiting satellites, by determining location coordinates (P_lx, P_ly, P_lz) with respect to an earth-centered, earth-fixed (ECEF) x, y, z coordinate system of multiple points P_I on the surface of the earth, from which points may be observed a rate of change of the range I to the satellite, with the method using satellite information received at a receiver, the satellite information including the values of the position (X_S, Y_S, Z_S) of the satellite with respect to said coordinate system, the distance d_S of the satellite from the center of the earth, the velocity vector V_S of the satellite with respect to said coordinate system, V_S having vector components (V_Sx, V_Sy, V_Sz) and magnitude |V_S |, and an earth gravitational vector g_S at the satellite, the method comprising the steps of:

establishing in the receiver a satellite frame of reference having axes aligned, respectively, with the velocity vector V_S and the gravitational vector g_S ;

deriving the vector orientation of the satellite frame of reference with respect to the ECEF coordinate system according to |V_S |, (V_Sx, V_Sy, V_Sz), d_S, (X_S, Y_S, Z_S);

using I to determine a function of an angle φ

which is formed by the line of the velocity vector V_S and each of multiple lines of-of-sight from the satellite to the points P_I ;

making the following determinations for each of multiple values of a variable, which values correspond to locations of the points P_I in the satellite frame of reference;

selecting one of the multiple values of the variable;

determining, for the selected value of the variable, the length L of a specific line-of-sight between the satellite and that point P_I which corresponds to the selected value;

deriving, for the selected value of the variable using the function of angle φ

, the orientation of the specific line-of-sight with respect to the satellite frame of reference;

using said derived orientation of the specific line-of-sight with respect to the satellite frame of reference, along with the length L, and said derived orientation of the satellite frame of reference with respect to the ECEF coordinate system, to derive vector components of the specific line-of-sight with respect to said ECEF coordinate system; and

determining the location coordinates (P_lx, P_ly, P_lz) using the derived components of the specific line-of-sight with respect to the ECEF coordinate system, and the position.

8. A method of estimating the position of a particular location on the surface of the earth using information received by a receiver from a plurality of earth-orbiting satellites and determining location coordinates (P_lx, P_ly, P_lz), with respect to an earth-centered, earth-fixed (ECEF) x, y, z coordinate system, of multiple points P_I on a spherical model of the earth, from which points the receiver may observe a rate of change of the range I to the satellite, the information transmitted from a satellite indicating the values of the position (X_S, Y_S, Z_S) of the satellite with respect to the ECEF coordinate system, the distance d_S of the satellite from the center of the earth, the velocity vector V_S having vector components (V_Sx, V_Sy, V_Sz) and magnitude |V_S |, the radius R_e of the spherical model, and an earth gravitational vector g_S at the satellite, the method comprising the steps of:

determining the cosine of an angle φ

formed by the velocity vector V_S and multiple lines-of-sight between the satellite and the points P_I, according to the relationship ##EQU15## determining the components (e_gx, e_gy, e_gz) of the unit vector of V_S, with respect to the ECEF coordinate system;

determining the components (e_vx, e_vy, e_vz), with respect to the ECEF coordinate system, of a unit vector V_gs of the earth gravitational vector g_S ;

determining, for each of multiple values of a variable a, where a and b are the values of the A and B coordinates, respectively, P_I in another coordinate system which is earth-centered with the A axis being collinear with and opposite in direction to the gravitational vector gs, and the B axis being parallel with the vector V_gs, according to the following steps;

selecting one of the multiple values of a;

determining the length L of a specific line-of-sight from the satellite to a point P_I which corresponds to the selected value of a;

computing, according to L, a function of an angle ψ

formed by said specific line-of-sight and the gravitational vector g_S ;

determining the b coordinate of P_I ;

computing, according to b, a function of an angle λ

formed by said specific line-of-sight and the vector V_gs ;

determining the components (e_Lx, e_Ly, e_Lz) of a unit vector of said specific line-of-sight using cos φ and

said computed functions ψ and

λ and

the unit vectors of V_S, G_S, and V_gs, with respect to said ECEF coordinate system; and

determining the location coordinates (P_lx, P_ly, P_lz) according to the relationships

space="preserve" listing-type="equation">P.sub.lx =X.sub.S +Le.sub.Lx

space="preserve" listing-type="equation">P.sub.ly =Y.sub.S +Le.sub.Ly

space="preserve" listing-type="equation">P.sub.lz =Z.sub.S +Le.sub.Lz.

9. The method of claim 8, wherein the vector V_g.sbsb.s is the vector product of the velocity vector V_S and the gravitational vector g_S.

10. The method of claim 8, wherein the components (e_Vx, e_Vy, e_Vz) are determined, with respect to the ECEF coordinate system, according to ##EQU16##

11. The method of claim 8, wherein the components (e_gx, e_gy, e_gz) are determined, with respect to the ECEF coordinate system, according to the relationships ##EQU17##

12. The method of claim 8, further comprising the step of determining the unit vector components (e_Vgx, e_Vgy, e_Vgz), with respect to the ECEF coordinate system, of a vector which is the vector product of V_S and the earth gravitational vector g_S, according to the relationships

13. The method of claim 8, wherein the length L of a specific line-of-sight from the satellite to that point P_I which corresponds to the selected value of a is determined according to the relationship ##EQU18##

14. The method of claim 8, wherein the function of angle ψ

formed by said specific line-of-sight is determined according to ##EQU19##

15. The method of claim 8, wherein the distance b is determined according to ##EQU20##

16. The method of claim 8, wherein the angle λ

formed by said specific line-of-sight is determined according to ##EQU21##

17. The method of claim 8, wherein the components (e_Lx, e_Ly, e_Lz) are determined, with respect to the ECEF coordinate system, according to the relationships