Terrain referenced navigation-Schuler cycle error reduction method and apparatus

• US 5,450,345 A
• Filed: 06/15/1992
• Issued: 09/12/1995
• Est. Priority Date: 06/15/1992
• Status: Expired due to Term

• Current Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Original Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Inventors: McGuffin, John T., Raymer, Kris A.
• Primary Examiner(s): ZANELLI, MICHAEL J
• Application Number:
  US07/898,260
• Time in Patent Office: 1,184 Days
• Field of Search: 364/487, 364/578, 364/572, 364/571.01, 364/581, 364/453, 324/76.77, 342/64, 73/178 R, 244/175
• US Class Current: 701/220
• CPC Class Codes: G01C 21/005 with correlation of navigation data from several sources, e.g. map or contour matching G01C21/30 takes precedence
• CPC Class Codes: G01C 21/188 for accumulated errors, e.g. by coupling inertial systems with absolute positioning systems
• CPC Class Codes: G05D 1/0646 to follow the profile of undulating ground

Abstract

A method for Schuler cycle error reduction is provided for use in a terrain referenced navigation system. Terrain Reference Navigation filter coefficients are analytically determined using a terrain reference navigation database and a hypothetical Schuler cycle. The optimum filter coefficients are determined assuming that there will be three parallel filters being executed during flight. The first filter is a nominal filter which represents a compromise between sensing zero crossing of a Schuler cycle error and peak changes of a Schuler cycle. The other filters are chosen to be perpendicular to the instantaneous line of flight. One is a peak filter, the other is a zero crossing filter. The peak filter is set to capture the inertial navigation unit when the Schuler cycle is changing rapidly. The zero crossing detector is set to capture the inertial navigation unit when it is zero crossing. The Schuler cycle is detected by algebraically noting similar features of each filter. INS measurements are then dynamically compensated for the now known Schuler cycle.

Claims

1. A Schuler cycle phase detection method, wherein the Schuler cycle has at least one Schuler cycle precision point, the Schuler cycle phase detection method comprising the steps of:

(a) determining a location of the at least one Schuler cycle precision point at at least one predetermined point in the Schuler cycle by relating the Schuler cycle to a predetermined cyclic measurement that varies with the Schuler cycle, and relating the Schuler cycle precision point to the predetermined cyclic measurement; and

(b) estimating a current Schuler cycle phase from the at least one Schuler cycle precision point.

2. A Schuler cycle error reduction method for a terrain referenced navigation system, wherein the terrain referenced navigation system contains navigation errors according to the Schuler cycle and wherein the Schuler cycle has at least one Schuler cycle precision point, the Schuler cycle error reduction method comprising the steps of:

(a) determining a location of the at least one Schuler cycle precision point at at least one predetermined point in the Schuler cycle by relating the Schuler cycle to a predetermined cyclic measurement that varies with the Schuler cycle, and relating the Schuler cycle precision point to the predetermined cyclic measurement;

(b) estimating a Schuler cycle phase from the at least one Schuler cycle precision point; and

(c) compensating the terrain referenced navigation system for the navigation errors according to the Schuler cycle.

3. The Schuler cycle error reduction method for a terrain referenced navigation system of claim 2 further comprising the step of compensating the terrain referenced navigation system for a 24 hour error bias.

4. The Schuler cycle error reduction method for a terrain referenced navigation system of claim 2 further comprising the step of selecting a predetermined inertial system error model to match the Schuler cycle phase, wherein the predetermined inertial system error model is utilized in compensating the terrain referenced navigation system to correct for the navigation errors according to the Schuler cycle.

5. The Schuler cycle error reduction method for a terrain referenced navigation system of claim 4 wherein the predetermined inertial system error model provides a short memory.

6. The Schuler cycle error reduction method for a terrain referenced navigation system of claim 4 wherein the predetermined inertial system error model provides a long memory.

7. The Schuler cycle error reduction method for a terrain referenced navigation system of claim 4 wherein the predetermined inertial system error model comprises a vector Q whose value is set in the range of 0.7-3.0.

8. The Schuler cycle error reduction method for a terrain referenced navigation system of claim 4 wherein the predetermined inertial system error model comprises a vector Q whose value is set in the range of 0.001-0.015.

9. A Schuler cycle phase detection method for a Schuler cycle, wherein the method comprises the steps of:

(a) determining a cyclic function having a cyclic phase, wherein the cyclic function phase relates to the Schuler cycle phase;

(b) determining at least one point of the Schuler cycle that corresponds to at least one point of the cyclic function; and

(c) determining the Schuler cycle phase from the cyclic function phase.

10. A Schuler cycle error reduction method for a terrain referenced navigation system wherein the terrain referenced navigation system contains navigation errors according to the Schuler cycle, wherein the Schuler cycle has at least one Schuler cycle precision point, the Schuler cycle error reduction method comprising the steps of:

(a) determining a cyclic function having a cyclic phase, wherein the cyclic function phase relates to the Schuler cycle phase;

(b) determining at least one point of the Schuler cycle that corresponds to at least one point of the cyclic function;

(c) determining the Schuler cycle phase from the cyclic function phase; and

(d) compensating the terrain referenced navigation system for the navigation errors according to the Schuler cycle.

11. The Schuler cycle error reduction method for a terrain referenced navigation system of claim 10 further comprising the step of compensating the terrain referenced navigation system for a 24 hour error bias.

12. The Schuler cycle error reduction method for a terrain referenced navigation system of claim 10 further comprising the step of selecting a predetermined inertial system error model to match the Schuler cycle phase, wherein the predetermined inertial system error model is utilized in compensating the terrain referenced navigation system to correct for the navigation errors according to the Schuler cycle.

13. The Schuler cycle error reduction method for a terrain referenced navigation system of claim 12 wherein the predetermined inertial system error model provides a short memory model.

14. The Schuler cycle error reduction method for a terrain referenced navigation system of claim 13 wherein the predetermined inertial system error model provides a long memory model.

15. The Schuler cycle error reduction method of claim 14 wherein system error models are chosen for a nominal value at the location of the aircraft and a first long memory model is taken in a direction perpendicular to the line of flight of the aircraft and a short memory model is taken in a direction perpendicular to the flight of the aircraft but opposite in direction from the first long memory model.

16. The Schuler cycle error reduction method for a terrain referenced navigation system of claim 12 wherein the predetermined inertial system error model comprises a vector Q whose value is set in the range of 0.7-3.0.

17. The Schuler cycle error reduction method for a terrain referenced navigation system of claim 12 wherein the predetermined inertial system error model comprises a vector Q whose value is set in the range of 0.001-0.015.

18. The Schuler cycle error reduction method of claim 10 wherein the step of determining the cyclic function comprises the steps of:

(a) setting a terrain referenced navigation filter coefficient to a nominal model filter;

(b) analyzing an existing predetermined terrain referenced navigation data base from a simulated terrain referenced navigation flight;

(c) running a predetermined number of test cases on a flight path of a hypothetical aircraft running through the predetermined terrain referenced navigation data base;

(d) storing flight profiles;

(e) analyzing different Q values ranging from a very small predetermined value to a very large predetermined value;

(f) imposing an artificial Schuler cycle on the flight path during each run;

(g) determining the Schuler cycle error based on prior knowledge of the location of the Schuler cycle; and

(h) determining values of Q for any predetermined rate of change based on known error models for a multitude of cases.

19. An analytical method performed on a computer for determining the value of a predetermined error model for a terrain reference navigation system comprising the steps of:

(a) setting a terrain reference navigation filter coefficient to a nominal model filter;

(b) analyzing an existing predetermined terrain reference navigation data base from a simulated terrain reference navigation flight;

(c) running a predetermined number of test cases on a flight path of a hypothetical aircraft running through the predetermined terrain referenced navigation data base;

(d) storing flight profiles;

(e) analyzing different Q values ranging from a very small predetermined value to a very large predetermined value;

(f) imposing an artificial Schuler cycle on the flight path during each run;

(g) determining the Schuler cycle error based on prior knowledge of the location of the Schuler cycle; and

(h) determining the values of Q for any predetermined rate of change based on the known error models for the multitude of cases.

20. The analytical method of claim 19 wherein the very small predetermined values of Q range from 0.001-0.015.

21. The analytical method of claim 19 wherein the very large predetermined values Q range from a value of 0.7-3.0.

22. The analytical method of claim 19 wherein the nominal model filter includes a Q value in the range of 0.2-0.6.