Method for in-field updating of the gyro thermal calibration of an intertial navigation system

• US 5,527,003 A
• Filed: 07/27/1994
• Issued: 06/18/1996
• Est. Priority Date: 07/27/1994
• Status: Expired due to Term

• Current Assignee: Northrop Grumman Systems Corporation (Northrop Grumman Corporation)
• Original Assignee: Litton Systems Incorporated
• Inventors: Diesel, John W., Dunn, Gregory P.
• Primary Examiner(s): Kashnikow, Andres
• Assistant Examiner(s): MARQUIS, LISSI MOJICA
• Application Number:
  US08/281,349
• Time in Patent Office: 692 Days
• Field of Search: 244/75 R, 244/76 R, 244/76 B, 244/175, 244/194, 244/195, 244/79, 364/447, 364/453
• US Class Current: 244/195
• CPC Class Codes: G01C 21/183 Compensation of inertial measurements, e.g. for temperature effects
• CPC Class Codes: G01C 25/005 initial alignment, calibration or starting-up of inertial devices
• CPC Class Codes: G05D 1/101 specially adapted for aircraft

Abstract

An in-field method for correcting the thermal bias error calibration of the gyros of a strapdown inertial navigation system. The method is begun after initial alignment while the aircraft remains parked with the inertial navigation system switched to navigation mode. Measurements are made of navigation system outputs and of gyro temperatures during this data collection period. A Kalman filter processes the navigation system outputs during this time to generate estimates of gyro bias error that are associated with the corresponding gyro temperature measurements. Heading error correcting is performed after the extended alignment data collection period as the aircraft taxis prior to takeoff. The gyro bias error-versus-temperature data acquired, along with the heading error corrections, are employed to recalibrate the existing thermal model of gyro bias error by means of an interpolation process that employs variance estimates as weighting factors.

Claims

1. A method for correcting gyro outputs in a strapdown aircraft inertial navigation system of the type that includes an associated existing thermal gyro bias error model calibration comprising the steps of:

a) orienting said aircraft to an initial alignment heading;

then

b) activating said system to navigation mode;

then

c) receiving measurements of angular rate and linear acceleration relative to said aircraft'"'"'s body axes from said system at regularly-spaced points in time; and

d) detecting the temperatures of the gyros of said strapdown system at said points in time;

then

e) determining aircraft acceleration with respect to a computed platform reference from said angular rate and linear acceleration measurements;

then

f) determining estimated acceleration rate errors in said gyro outputs from said aircraft acceleration with respect to said computed platform reference;

then

g) determining tilt rate errors in said gyro outputs;

then

h) repeating steps c through g throughout and until completion of an extended alignment period to generate a first set of data points, each data point comprising an associated pair of values of gyro tilt rate and gyro temperature;

then

i) converting each of said gyro tilt rates into a gyro bias error; and

j) storing said converted values as a second set of data points;

then

k) taxiing said aircraft; and

l) determining a heading error by estimating cross-track velocity during said taxiing;

then

m) converting each of said second set of data points to an adjusted gyro bias error by subtracting said heading error from each of said second set of data points;

then

n) storing said adjusted gyro bias errors as a third set of data points;

then

o) incorporating said third set of data points into said existing thermal gyro bias error model calibration to form an updated calibration;

then

p) continuously measuring the temperatures of said gyros; and

then

q) repeatedly adjusting the angular rate outputs of said gyros with bias error values selected from said updated calibration in view of said measured gyro temperatures.

2. A method as defined in claim 1 wherein the step of determining aircraft accelerations with respect to a computed platform reference is performed by said inertial navigation system.

3. A method as defined in claim 1 wherein the step of determining estimated acceleration rate errors in said gyro outputs is accomplished by means of a fourth-order filter.

4. A method as defined in claim 1 wherein the step of determining tilt rate is accomplished by means of the error model of said navigation mode.

5. A method as defined in claim 1 wherein the step of converting said gyro tilt rates into gyro bias errors is accomplished by means of a transformation of the relationship between tilt rate and navigation mode error sources.

6. A method as defined in claim 5 wherein said transformation comprises a first adjustment and a second adjustment.

7. A method as defined in claim 6 wherein said first adjustment comprises the steps of:

a) estimating the effect of velocity error upon tilt rate;

then

b) adding said estimate of velocity error to said tilt rate; and

then

c) assuming the effect of tilt misalignment with respect to the other computed platform axis is negligible.

8. A method as defined in claim 7 wherein said second adjustment comprises the steps of:

a) estimating earth rate misalignment due to heading error; and

then

b) adding said estimate of earth rate misalignment to said first adjustment.

9. A method as defined in claim 1 wherein the step of incorporating said third set of data points into said existing thermal gyro bias error model calibration further includes the step of interpolating said third set of data points with respect to the temperature data of said existing thermal gyro bias error model.

10. A method as defined in claim 9 wherein said step of interpolating further includes the step of estimating the variance of each of said interpolated values of gyro bias error.

11. A method as defined in claim 10 wherein the step of interpolating additionally includes the step of weighting said interpolated values in accordance with the estimated variance thereof.

12. A method for in-field updating of the gyro bias error-versus-temperature calibration of an aircraft strapdown inertial navigation system comprising a plurality of gyro bias error values associated with gyro temperature, said method comprising the steps of:

a) performing an initial alignment;

then

b) turning said system to navigation mode;

then

c) measuring the temperatures of the gyros of said inertial navigation system in said initial alignment heading; and

d) making estimates of gyro bias error in said initial alignment heading;

then

e) associating said estimates of gyro bias error with said measurement temperatures;

then

f) changing the heading of said aircraft and taxiing; and

g) estimating aircraft heading error;

then

h) subtracting said aircraft heading error from each of said estimates of gyro bias error to generate a plurality of updated gyro bias error-and-temperature data points;

then

i) interpolating said updated gyro bias error-and-temperature data points to generate updated values of gyro bias error that correspond to the temperature values of an existing gyro bias error-versus-temperature calibration; and

then

j) adjusting said existing calibration by means of said updated values of gyro bias error.

13. A method as defined in claim 12 wherein said gyros are ring laser gyroscopes.

14. A method as defined in claim 13 further comprising the step of determining a variance value associated with each of said updated values of gyro bias error.

15. A method as defined in claim 14 further including the step of weighting each of said updated gyro bias error values in accordance with the associated variance.

16. A method for correcting the gyros of a strapdown inertial system for temperature-induced gyro bias errors comprising the steps of:

a) generating an initial thermal model calibration;

then

b) setting said inertial navigation system to alignment mode;

then

c) performing an initial alignment;

then

d) switching said system to navigation mode;

then

e) measuring outputs of said inertial navigation system while said aircraft is in the initial alignment heading; and

f) measuring the temperatures of said gyros;

then

g) generating a set of values of gyro bias error from said measured outputs;

then

h) associating each of said values with a measured value of gyro temperature;

then

i) changing the heading of said aircraft; and

j) taxiing said aircraft; and

k) measuring the output of said inertial navigation system;

then

l) determining the heading errors of said gyros;

then

m) subtracting said heading errors from the values of gyro bias error to create a set of values of gyro bias errors associated with measured gyro temperatures;

then

n) interpolating said last-named set of values to correspond to the temperatures of said initial thermal model calibration;

then

o) creating an updated thermal model calibration by incorporating said interpolated values into said initial thermal model calibration;

then

p) flying said aircraft; and

q) measuring the temperatures of said gyros; and

then

r) determining gyro bias error corresponding to said gyro temperatures from said updated thermal model calibration; and

then

s) compensating the outputs of said gyros in accordance with said gyro bias errors.

17. A method as defined in claim 16 wherein the step of interpolating further includes the step of associating a variance value with each of said updated values of gyro bias error.

18. A method as defined in claim 17 further including the step of weighting each of said updated gyro bias error values in accordance with the associated variance.