Predictive approach integrity

• US 5,910,788 A
• Filed: 04/17/1997
• Issued: 06/08/1999
• Est. Priority Date: 04/17/1997
• Status: Expired due to Term

• Current Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Original Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Inventors: Class, Kim A.
• Primary Examiner(s): Blum, Theodore M.
• Application Number:
  US08/843,941
• Time in Patent Office: 782 Days
• Field of Search: 342/357, 701/214
• US Class Current: 342/357.31
• CPC Class Codes: G01S 19/08 providing integrity information, e.g. health of satellites or quality of ephemeris data
• CPC Class Codes: G01S 19/15 Aircraft landing systems
• CPC Class Codes: G01S 19/20 Integrity monitoring, fault detection or fault isolation of space segment

Abstract

A method and apparatus are provided for predicting the position error bound in a satellite positioning system at a future time. The future position of each satellite at the future time is calculated from the trajectory data obtained from each satellite. The predicted position for each satellite and the estimated position of the satellite positioning system receiver is then used to generate a line of sight matrix at the future time from which a position error bound is determined.

Claims

1. A satellite positioning system comprising:

a satellite positioning system receiver for receiving satellite information signals from selected ones of a plurality of satellites, and for deriving corresponding satellite data from selected ones of said satellite information signals, where each of said satellites transmits a satellite information signal containing satellite data sufficient to determine the corresponding range between the satellite and said satellite positioning system receiver, and which said satellite data from selected ones of a plurality of satellites is sufficient to determine an estimated geocentric position of said satellite positioning system receiver;

an information signal processor for deriving from said satellite data at least i) information for determining the trajectory of each of said selected ones of said plurality of satellites, and ii) a pseudo range value between said receiver and each of said selected one of said plurality of satellites, where said pseudo range value is an estimate of the true range value between said receiver and said selected ones of said plurality of satellites determined by a measurement of the corresponding satellite signal travel time from the satellite to the receiver;

means for deriving an estimated geocentric position of said receiver, at a particular time, as a function of selected ones of said pseudo range values and corresponding ones of the geocentric positions of said plurality of said satellites derived from said trajectory information;

means for deriving a line of sight vector measurement matrix H in which said line of sight vector measurement matrix is descriptive of the vectors between said estimated geocentric position of the receiver and said geocentric position of said selected satellites at a selected future time;

an integrity processor responsive to said line of sight vector measurement matrix H at said selected future time; and

a ground station providing measurement statistics to the integrity processor for determining an improved accurate reading of a position error bound value at said future time.

2. The global positioning system of claim 1 comprising:

means for determining an error value associated with each of said pseudo range values, where each of said error values relates the difference between said pseudo range value and a corresponding estimated range value, where said estimated range value is substantially the vector magnitude of the vector between said estimated position of said receiver and the corresponding one of said geocentric position of said satellites;

wherein said integrity processor is responsive to said line of sight vector measurement matrix H at said selected future time and said error values for predicting a position error bound having a selected reliability.

3. A method for determining a future time position error bound value in a satellite positioning system receiver comprising the steps of:

(a) receiving, from a satellite position system, satellite trajectory data from one or more tracked satellites, a receiver time, and an estimated position of a satellite position system receiver;

(b) generating a look-ahead time by adding a time increment to said receiver time;

(c) calculating a predicted position for each satellite based on the trajectory data for each satellite and the look-ahead time;

(d) using the predicted position for each satellite and the estimated position of the satellite position system receiver to generate a line of sight matrix;

(e) providing measurement statistics;

(f) producing a predicted position error bound from said line of sight matrix in combination with the measurement statistics.

4. The method in claim 3 wherein said estimated position is the position of the satellite position system receiver at the receiver time.

5. The method in claim 3 wherein said estimated position is a predicted location of the satellite position system receiver at the look-ahead time.

6. The method in claim 3 wherein said time increment is 5 minutes.

7. The method in claim 3 wherein said time increment may be altered.

8. The method in claim 3 wherein said trajectory data is almanac data.

9. The method in claim 3 wherein said trajectory data is ephemeris data.