Apparatus and method for determination of a receiver position

• US 6,011,509 A
• Filed: 05/25/1999
• Issued: 01/04/2000
• Est. Priority Date: 05/25/1999
• Status: Expired due to Term

• Current Assignee: Raytheon Company (Rtx Corporation)
• Original Assignee: Raytheon Company (Rtx Corporation)
• Inventors: Dutka, Stephen C.
• Primary Examiner(s): Tarcza, Thomas H.
• Assistant Examiner(s): PHAN, DAO LINDA
• Application Number:
  US09/318,337
• Time in Patent Office: 224 Days
• Field of Search: 342/357.01, 342/357.06, 342/352, 701/213, 701/214, 455/12.1
• US Class Current: 342/357.29
• CPC Class Codes: G01S 19/215 issues related to spoofing
• CPC Class Codes: G01S 19/42 Determining position

Abstract

A method of accurate determination of a fixed position using global positioning system uses pseudo-range output over a predetermined measurement period from a stand-alone GPS receiver located at the fixed position, the pseudo-range output being measured from an ensemble of space vehicles at each time t over the measurement period, and historical ephemerides of the ensemble of space vehicles over the same measurement period to eliminate errors caused by selective availability. The historical ephemerides of the ensemble of space vehicles corresponding to each measurement time t are determined, and using the pseudo-range output and the historical ephemerides, a position solution at each time t is computed. The accurate position in earth-centered earth-fixed coordinates is then the average of all the position solutions at each time t over the measurement period.

Claims

1. A method of determination of a receiver fixed position using global positioning system (GPS), comprising:

obtaining pseudo-range output over a predetermined measurement period from a GPS receiver, the pseudo-range output measured from an ensemble of space vehicles at each of a plurality of times t over the measurement period;

determining the historical ephemerides of the ensemble of space vehicles corresponding to each of the plurality of times t;

determining a position solution for each of the plurality of times t utilizing the pseudo-range output and the ephemerides; and

averaging the position solution for each of the times t over the measurement period.

2. The method, as set forth in claim 1, wherein determining historical ephemerides comprises:

determining an orbit defined by the historical ephemerides; and

determining intermediate historical ephemerides between the historical ephemerides in the orbit.

3. The method, as set forth in claim 2, wherein determining the orbit comprises fitting an orbit to the historical ephemerides.

4. The method, as set forth in claim 1, wherein determining a position solution for each of the plurality of times t comprises;

determining an initial receiver position;

determining, in response to the historical ephemerides and the initial receiver position, a range from each space vehicle to the receiver;

determining a difference between the range of each space vehicle and the receiver pseudo-range output;

determining errors of the initial receiver position in response to the difference between the range of each space vehicle and the receiver pseudo-range output;

correct the initial receiver position with the errors; and

iteratively repeating the above steps until the errors approach zero.

5. The method, as set forth in claim 1, wherein averaging the position solutions comprises:

summing all position solutions of each axis; and

dividing the summed position solution for each axis by the number of position solutions in each axis.

6. A method of determination of a receiver position using a stand-alone global positioning system (GPS) receiver, the receiver generating a plurality of pseudo-range data over a measurement period, comprising:

receiving the plurality of pseudo-range data over the measurement period, the pseudo-range data measured for an ensemble of at least four space vehicles at each of a plurality of times t over the measurement period;

receiving historical ephemerides of the same ensemble of space vehicles over the measurement period;

determining from the received ephemerides an orbit for each space vehicle;

determining intermediate historical ephemerides between the historical ephemerides in each orbit for each of the plurality of times t during the measurement period;

determining a position solution for each of the plurality of times t utilizing the plurality of pseudo-range data and the ephemerides; and

averaging the position solution for each of the times t over the measurement period.

7. The method, as set forth in claim 6, wherein determining the orbit comprises fitting an orbit to the historical ephemerides.

8. The method, as set forth in claim 6, wherein determining a position solution at each time t comprises:

determining an initial receiver position;

determining, in response to the historical ephemerides and the initial receiver position, a range from each space vehicle to the receiver;

determining a difference between the range of each space vehicle and the receiver pseudo-range output;

determining errors of the initial receiver position in response to the difference between the range of each space vehicle and the receiver pseudo-range output;

correct the initial receiver position with the errors; and

iteratively repeating the above steps until the errors approach zero.

9. The method, as set forth in claim 6, wherein averaging the position solutions comprises:

summing all position solutions for each axis; and

dividing the summed position solution for each axis by the number of position solutions in each axis.

10. A stand-alone global positioning system (GPS) receiver having a post-processor for accurate determination of a fixed position, the post-processor programmed to:

receive a plurality of pseudo-range measurements over a predetermined measurement period, the pseudo-range measurements determined from an ensemble of space vehicles at each of a plurality of times t over the measurement period;

obtain historical ephemerides of the ensemble of space vehicles over the measurement period, the historical ephemerides being free of the selective availability broadcast ephemeris error;

determine the historical ephemerides of the ensemble of space vehicles corresponding to each time t in response to the obtained historical ephemerides;

use the plurality of pseudo-range measurements and the historical ephemerides to determine a position solution at each time t; and

average the position solutions over the measurement period.

11. The receiver, as set forth in claim 10, wherein the post-processor being further adapted to:

determine an orbit defined by the obtained historical ephemerides; and

determine intermediate historical ephemerides between the historical ephemerides in the orbit.

12. The receiver, as set forth in claim 10, wherein the post-processor is programmed to determine a position solution at each time t comprises:

determining an initial receiver position;

determining, in response to the historical ephemerides and the initial receiver position, a range from each space vehicle to the receiver;

determining a difference between the range of each space vehicle and the receiver pseudo-range output;

determining errors of the initial receiver position in response to the difference between the range of each space vehicle and the receiver pseudo-range output;

correct the initial receiver position with the errors; and

iteratively repeating the above steps until the errors approach zero.

13. The receiver, as set forth in claim 10, wherein the post-processor is further programmed to average the position solutions by:

summing all position solutions in each axis; and

dividing the summed position solution in each axis by the number of position solutions in each axis.