Instrument calibration method including compensation of centripetal acceleration effect

• US 5,505,410 A
• Filed: 05/23/1994
• Issued: 04/09/1996
• Est. Priority Date: 05/23/1994
• Status: Expired due to Term

• Current Assignee: Northrop Grumman Systems Corporation (Northrop Grumman Corporation)
• Original Assignee: Litton Systems Incorporated (Northrop Grumman Corporation)
• Inventors: Dunn, Gregory P., Diesel, John W.
• Primary Examiner(s): Kashnikow, Andres
• Assistant Examiner(s): MARQUIS, LISSI MOJICA
• Application Number:
  US08/247,313
• Time in Patent Office: 687 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: G05D 1/0202 specially adapted to aircraft

Abstract

A method and apparatus are provided for addressing the effect of centripetal acceleration upon estimates of cross-track velocity, for determination of east gyro bias error, generated with a taxiing aircraft. After initial estimates of crab angle, ratio of crab angle to centripetal acceleration and lever arm are provided, velocity, heading angle and heading angle rate are observed as the aircraft taxis. An estimated value of centripetal acceleration is taken as the product of heading angle rate and heading velocity. Cross-track velocity is computed from cross-heading velocity and this is integrated to generate cross-track position. A Kalman filter generates various gains, including one associated with the ratio of crab angle to centripetal acceleration, for error allocation. The product of the Kalman gain pertaining to crab angle ratio and the computed cross-track position provides a crab angle ratio error that is integrated and multiplied by the estimated centripetal acceleration to provide an optimum estimate of the portion of crab angle that is associated with centripetal acceleration.

Claims

1. A method for determining the east gyro bias error of the inertial system of an aircraft comprising the steps of:

a) providing initial estimates of crab angle, ratio of crab angle to centripetal acceleration and lever arm;

then

b) taxiing said aircraft; and

c) observing aircraft velocity with respect to an inertial axis system; and

d) observing heading angle and rate of change thereof;

then

e) converting said aircraft velocity to heading and cross-heading velocity components in an aircraft body axis reference system; and

f) estimating centripetal acceleration;

then

g) estimating the cross-track velocity of said taxiing aircraft;

then

h) integrating said cross track velocity to estimate the cross-track position of said taxiing aircraft; and

i) generating Kalman gains for the value of crab angle, ratio of crab angle to centripetal acceleration, lever arm and aircraft velocity with respect to said inertial reference axis;

then

j) obtaining error values by multiplying said cross-track position by said Kalman gains;

then

k) generating optimum estimates of cross-track velocity by combining said error values with said cross-heading velocity; and

then

l) generating east gyro bias error from said optimum estimates of cross-track velocity.

2. A method as defined in claim 1 wherein the step of estimating cross-track velocity further includes the steps of:

a) receiving said cross-heading velocity component; and

then

b) adjusting said cross-heading velocity component for crab angle and lever arm effects.

3. A method as defined in claim 2 wherein thee step of adjusting said cross-heading velocity component for crab angle further includes the steps of:

a) making an optimum estimate of crab angle;

then

b) taking the product of said optimum estimate of crab angle and said heading velocity component; and

then

c) subtracting said product from said cross-heading velocity.

4. A method as defined in claim 3 wherein the step of making an optimum estimate of crab angle further includes the step of adjusting the value of crab angle for centripetal acceleration effects.

5. A method as defined in claim 4 wherein the step of adjusting the value of crab angle for centripetal acceleration effects further includes the steps of:

a) estimating the ratio of crab angle to centripetal acceleration; and

b) estimating centripetal acceleration; and

then

c) multiplying said ratio by said estimated centripetal acceleration.

6. A method as defined in claim 5 wherein the step of estimating centripetal acceleration additionally comprises the steps of:

a) receiving said observed value of heading angle rate of change while taxiing; and

b) receiving said heading velocity component; and

then

c) multiplying said observed value of heading angle rate of change by said heading velocity component.

7. A method as defined in claim 6 wherein the step of estimating said ratio additionally comprises the steps of:

a) receiving said initial estimate of said ratio;

then

b) making observations of said crab angle as said aircraft taxis; and

c) making estimates of centripetal acceleration as said aircraft taxis; and

then

d) applying the data of steps a through c to a statistical filter to generate an updated Kalman gain for said ratio; and

e) deriving a cross-track position of said taxiing aircraft;

then

f) deriving an updated estimate of ratio error as the product of said Kalman gain and said cross-track position; and

then

g) integrating said updated error estimate to provide an optimum estimate of said ratio.

8. A method as defined in claim 4 wherein the step of estimating cross-track velocity further includes the steps of:

a) apportioning said crab angle into a first component and a second component, said first component being a function of centripetal acceleration;

then

b) providing updated optimum estimates of said first and second components;

then

c) multiplying said first and second components by said heading velocity component; and

then

d) subtracting said products from said cross-heading velocity.

9. A method as defined in claim 8 wherein the step of providing updated estimates of said first and second crab angle components includes the step of generating a Kalman gain for each of said first and second components.

10. A method for estimating the cross-track velocity of an aircraft as it taxis comprising the steps of:

a) providing initial estimates of crab angle, ratio of crab angle to centripetal acceleration and lever arm;

then

b) observing aircraft velocity with respect to an inertial axis system; and

c) observing heading angle and rate of change thereof;

then

d) converting said aircraft velocity to heading and cross-heading velocity components in an aircraft body axis reference system; and

e) estimating centripetal acceleration;

then

f) estimating the cross-track velocity of said taxiing aircraft;

then

g) integrating said cross track velocity to estimate the cross-track position of said taxiing aircraft; and

h) generating Kalman gains for the value of crab angle, ratio of crab angle to centripetal acceleration, lever arm and aircraft velocity with respect to said inertial reference axis;

then

i) obtaining error values by multiplying said cross-track position by said Kalman gains; and

then

j) generating optimum estimates of cross-track velocity by combining said error values with said cross-heading velocity.

11. A method as defined in claim 10 wherein the step of estimating cross-track velocity further includes the steps of:

a) receiving said cross-heading velocity component; and

then

b) adjusting said cross-heading velocity component for crab angle and lever arm effects.

12. A method as defined in claim 11 wherein the step of adjusting said cross-heading velocity component for crab angle further includes the steps of:

a) making an optimum estimate of crab angle;

then

b) taking the product of said optimum estimate of crab angle and said heading velocity component; and

then

c) subtracting said product from said cross-heading velocity.

13. A method as defined in claim 12 wherein the step of making an optimum estimate of crab angle further includes the step of adjusting the value of crab angle for centripetal acceleration effects.

14. A method as defined in claim 13 wherein the step of adjusting the value of crab angle for centripetal acceleration effects further includes the steps of:

a) estimating the ratio of crab angle to centripetal acceleration; and

b) estimating centripetal acceleration; and

then

c) multiplying said ratio by said estimated centripetal acceleration.

15. A method as defined in claim 14 wherein the step of estimating centripetal acceleration additionally comprises the steps of:

a) receiving said observed value of heading angle rate of change while taxiing; and

b) receiving said heading velocity component; and

then

c) multiplying said observed value of heading angle rate of change by said heading velocity component.

16. A method as defined in claim 15 wherein the step of estimating said ratio additionally comprises the steps of:

a) receiving said initial estimate of said ratio;

then

b) making observations of said crab angle as said aircraft taxis; and

c) making estimates of centripetal acceleration as said aircraft taxis; and

then

d) applying the data of steps a through c to a statistical filter to generate an updated Kalman gain for said ratio; and

e) deriving a cross-track position of said taxiing aircraft;

then

f) deriving an updated estimate of ratio error as the product of said Kalman gain and said cross-track position; and

then

g) integrating said updated error estimate to provide an optimum estimate of said ratio.

17. A method as defined in claim 16 wherein the step of estimating cross-track velocity further includes the steps of:

a) apportioning said crab angle into a first component and a second component, said first component being a function of centripetal acceleration;

then

b) providing updated optimum estimates of said first and second components;

then

c) multiplying said first and second components by said heading velocity component; and

then

d) subtracting said products from said cross-heading velocity.

18. Apparatus for determining the east gyro bias error of the inertial system of an aircraft comprising, in combination:

a) means for generating initial estimates of crab angle, ratio of crab angle to centripetal acceleration and lever arm;

b) means for measuring the velocity of said aircraft with respect to an inertial axis system as it taxis;

c) means for measuring heading angle and its rate change while said aircraft taxis;

d) means for converting said taxiing velocity to a heading velocity component and a cross-heading velocity component in an aircraft body axis reference system;

e) means for computing centripetal acceleration;

f) an integrator for generating a cross-track position error from said cross-track velocity;

g) a statistical filter, responsive to an error model, for generating Kalman gains with respect to crab angle, ratio of crab angle to centripetal acceleration, lever arm and aircraft taxi velocity with respect to said inertial reference axes;

h) a multiplier for generating error values by multiplying said cross-track position error by said Kalman gains;

i) means for generating optimum estimates of cross-track velocity by combining said error values with taxiing velocity with respect to said body axis system; and

j) means for generating said east gyro bias error from said optimum estimates of cross-track velocity.

19. On-board apparatus for determining the cross-track velocity of a taxiing aircraft comprising, in combination:

a) means for generating initial estimates of crab angle, ratio of crab angle to centripetal acceleration and lever arm;

b) means for measuring the velocity of said aircraft with respect to an inertial axis system as it taxis;

c) means for measuring heading angle and its rate change while said aircraft taxis;

d) means for converting said taxiing velocity to a heading velocity component and a cross-heading velocity component in an aircraft body axis reference system;

e) means for computing centripetal acceleration;

f) an integrator for generating a cross-track position error from said cross-track velocity;

g) a statistical filter, responsive to an error model, for generating Kalman gains with respect to crab angle, ratio of crab angle to centripetal acceleration, lever arm and aircraft taxi velocity with respect to said inertial reference axes;

h) a multiplier for generating error values by multiplying said cross-track position error by said Kalman gains; and

i) means for generating optimum estimates of cross-track velocity by combining said error values with taxiing velocity with respect to said body axis system.