3D AIME™ aircraft navigation

• US RE42,891 E1
• Filed: 10/09/2001
• Issued: 11/01/2011
• Est. Priority Date: 12/04/1997
• Status: Expired due to Term

• Current Assignee: Northrop Grumman Systems Corporation (Northrop Grumman Corporation)
• Original Assignee: Northrop Grumman Guidance & Electronics Co., Inc. (Northrop Grumman Corporation)
• Inventors: Diesel, John W.
• Primary Examiner(s): Beaulieu; Yonel
• Application Number:
  US09/974,088
• Time in Patent Office: 3,675 Days
• Field of Search: 701/4, 701/1, 701/3, 701 15- 18, 342/33, 342/34, 342/36, 342/38, 342/120, 342/355, 342/357.06, 342/357.09
• US Class Current: 701/4
• CPC Class Codes: G01C 21/165 combined with non-inertial navigation instruments
• CPC Class Codes: G01S 13/882 for altimeters measuring height using barometric means G01C5/06
• CPC Class Codes: G01S 19/15 Aircraft landing systems
• CPC Class Codes: G01S 19/49 whereby the further system is an inertial position system, e.g. loosely-coupled

Abstract

The apparatus of the present invention uses radar altimeter measurements and stored terrain altitude profiles to provide pre-filtered observations to a Kalman filter for estimating barometric offset at the airport runway, and barometric scale factor for offsets above the runway. These offsets are used with the smoothed baro-inertial output from an inertial reference system to provide 3 dimensional constant rate of descent approach procedures to replace non-precision approach procedures based on constant barometric altitude step approaches. The horizontal positions used as reference for the stored terrain altitude profiles are obtained from a prior art navigation apparatus. The integrity of all measurements is assured by using long term averages of the Kalman filter residuals to detect failures. In addition, the estimated baro offset at the runway is compared for consistency with the baro offset obtained by the pilot from the airport by radio.

Claims

1. A method for determining a vehicle'"'"'s altitude above a predetermined reference level utilizing values of navigation quantities from one or more external sources, an altitude being referenced to the predetermined reference level unless otherwise noted, the method comprising the steps:

(a) obtaining values of a plurality of external-source navigation quantities at periodic input intervals, the external-source navigation quantities including a first external-source vehicle altitude, the external source for the first external-source vehicle altitude being an inertial reference system;

(b) obtaining observations at periodic observation intervals of one or more observation quantities, at least one of the observation quantities being a function of a second external-source vehicle altitude, the second external-source vehicle altitude being referenced to the portion of the terrain beneath the vehicle, an observation interval containing one or more of the periodic input intervals;

(c) deriving correction data at the periodic input intervals from the observations of step (b);

(d) obtaining values of one or more corrected or computed navigation quantities at the periodic input intervals using the correction data of step (c), the one or more corrected or computed navigation quantities including a corrected first external-source vehicle attitude.

2. The method of claim 1 wherein the source for the first external-source vehicle altitude in step (a) is a barometric altimeter.

3. The method of claim 1 wherein the source for the first external-source vehicle altitude in step (a) is an inertial reference system that includes a barometric altimeter.

4. The method of claim 1 wherein the navigation quantities of step (a) include an external-source two-coordinate vehicle position, the two coordinates defining a position in the horizontal plane.

5. The method of claim 4 wherein the source for the external-source two-coordinate vehicle position in step (a) is an inertial reference system.

6. The method of claim 1 wherein the navigation quantities of step (a) include a plurality of external-source three-coordinate GPS satellite positions.

7. The method of claim 6 wherein the source for the external-source three-coordinate GPS satellite positions in step (a) is a GPS receiver.

8. The method of claim 1 wherein the navigation quantities of step (a) include a plurality of external-source pseudoranges to GPS satellites.

9. The method of claim 8 wherein the source for the external-source pseudoranges in step (a) is a GPS receiver.

10. The method of claim 1 wherein the navigation quantities of step (a) include a plurality of external-source error-model coefficients.

11. The method of claim 10 wherein the source for the external-source error-model coefficients in step (a) is an inertial reference system.

12. The method of claim 1 wherein the navigation quantities of step (a) include an external-source vehicle altitude referenced to the terrain altitude beneath the vehicle.

13. The method of claim 12 wherein the source for the external-source vehicle altitude referenced to the terrain altitude beneath the vehicle is a radar altimeter.

14. The method of claim 1 wherein the navigation quantities of step (a) include an external-source terrain altitude of the portion of the terrain beneath the vehicle.

15. The method of claim 14 wherein the source for the external-source terrain altitude is a memory in which terrain altitude is stored as a function of two-coordinate vehicle position in the horizontal plane.

16. The method of claim 1 wherein the observations of step (b) include an observation which is derived from the sums of an external-source vehicle altitude referenced to the portion of the terrain beneath the vehicle and an external-source terrain altitude of the portion of the terrain beneath the vehicle for a plurality of present and past input intervals.

17. The method of claim 1 wherein the observations of step (b) include an observation which is derived from the differences of a first external-source vehicle altitude and a second external-source vehicle altitude for a plurality of present and past input intervals.

18. The method of claim 17 wherein step (c) comprises the step:

(c1) determining a polynomial as a function of time or a function of a parameter that is a function of time that approximates the differences for a plurality of present and past input intervals, the polynomial coefficients constituting the correction data for the present input interval.

19. The method of claim 18 wherein the polynomial provides closer approximations to differences that are of a higher quality.

20. The method of claim 18 wherein a difference is ignored in the determination of the polynomial if the quality of the difference is less than a specified quality level.

21. The method of claim 17 wherein in step (d) the corrected first external-source vehicle altitude is the sum of the first external-source vehicle altitude and the polynomial value.

22. The method of claim 1 wherein the observations of step (b) include an observation which is derived from the differences of the corrected first external-source vehicle altitude and a second external-source vehicle altitude for a plurality of present and past input intervals.

23. The method of claim 22 wherein the observations of step (b) include an observation which is the sum of the weighted differences of the corrected first external-source vehicle altitude and a second external-source vehicle altitude for a plurality of present and past input intervals.

24. The method of claim 1 wherein the external-source navigation quantities of step (a) include an external-source three-coordinate vehicle position, the observations of step (b) including a plurality of observations derived from values of the external-source three-coordinate vehicle position for a plurality of input intervals.

25. The method of claim 1 wherein the external-source navigation quantities of step (a) include external-source satellite positions of a plurality of GPS satellites, the observations of step (b) including a plurality of observations derived from values of external-source satellite positions of a plurality of GPS satellites for a plurality of input intervals.

26. The method of claim 1 wherein the external-source navigation quantities of step (a) include external-source pseudoranges to a plurality of GPS satellites, the observations of step (b) including a plurality of observations derived from the values of external-source pseudoranges to a plurality of GPS satellites for a plurality of input intervals.

27. The method of claim 1 wherein the corrected or computed navigation quantities of step (d) include a corrected external-source three-coordinate vehicle position, the observations of step (b) including a plurality of observations derived from values of the corrected external-source three-coordinate vehicle position obtained for a plurality of input intervals.

28. The method of claim 1 wherein the corrected or computed navigation quantities of step (d) include computed pseudoranges to a plurality of GPS satellites, the observations of step (b) including a plurality of observations derived from values of the computed pseudoranges for a plurality of input intervals.

29. The method of claim 1 wherein the external-source navigation quantities of step (a) include external-source pseudonanges to a plurality of GPS satellites and the corrected or computed navigation quantities include computed pseudoranges to a plurality of GPS satellites, the observations of step (b) including a plurality of observations derived from the differences of the external-source pseudoranges and the computed pseudoranges obtained for a plurality of input intervals.

30. The method of claim 29 wherein the derivation of a plurality of observations is accomplished by summing the weighted differences of the external-source pseudoranges and the computed pseudoranges for a plurality of present and past input intervals.

31. The method of claim 1 wherein step (c) comprises the step:

(c1) obtaining component values for an error-state vector at observation intervals by using the observations of step (b) in a Kalman filter process, the error-state vector constituting the correction data.

32. The method of claim 31 wherein the components of the error-state vector include errors in vehicle position in a horizontal plane, errors in vehicle velocity in a horizontal plane, GPS vehicle clock bias and clock rate bias, GPS satellite clock biases for a plurality of satellites, barometric altitude bias at a first reference altitude, and the offset of the barometric altitude bias at a second reference altitude.

33. The method of claim 1 wherein the correction data of step (c) is a Kalman filter error-state vector, step (d) comprising the steps:

(d1) determining the time rate-of-change of the error-state vector by applying a dynamics matrix to the error-state vector;

(d2) obtaining corrections to a plurality of external-source navigation quantities by adding the integral of the time rate-of-change of the error-state vector to the error-state vector.

34. The method of claim 1 wherein the external-source navigation quantities of step (a) includes terrain altitude stored in an external memory as a function of vehicle position in the horizontal plane and external-source vehicle position in the horizontal plane, a value of terrain altitude being obtained by addressing the external memory with the external-source vehicle-position coordinates.

35. The method of claim 1 wherein the external-source navigation quantities of step (a) includes terrain altitude stored in an external memory as a function of vehicle position in the horizontal plane and the corrected or computed navigation quasntities of step (d) includes corrected external-source three-coordinate vehicle position, a value of terrain altitude being obtained in step (a) by addressing the external memory with the horizontal-plane coordinates of the corrected external-source three-coordinate vehicle-position.

36. The method of claim 1 wherein an observation of step (b) is ignored in performing step (c) if the quality of the observation is less than a specified quality level.