Inertial navigation system including self-contained performance validating arrangement

• US 5,301,114 A
• Filed: 06/11/1992
• Issued: 04/05/1994
• Est. Priority Date: 06/11/1992
• Status: Expired due to Fees

• Current Assignee: Alliedsignal Inc. (Honeywell International Inc.)
• Original Assignee: Alliedsignal Inc. (Honeywell International Inc.)
• Inventors: Mitchell, William J.
• Primary Examiner(s): Black, Thomas G.
• Assistant Examiner(s): Walker, Tyrone V.
• Application Number:
  US07/897,137
• Time in Patent Office: 663 Days
• Field of Search: 364/453, 364/459, 364/443, 364/449, 73/178 R, 33/324
• US Class Current: 701/220
• CPC Class Codes: G01C 21/188 for accumulated errors, e.g. by coupling inertial systems with absolute positioning systems

Abstract

The accuracy of the performance of an inertial navigation system is validated by comparing data measured by a fourth gyro and accelerometer to an analytic equivalent constructed from measurements made by a primary gyro/accelerometer orthogonal triad.

Claims

1. An inertial navigation system including a self-contained performance validating arrangement, comprising:

an inertial sensor assembly including a substantially orthogonal triad having three gyros and three accelerometers;

said inertial sensor assembly including a fourth gyro and a fourth accelerometer having input axes which symmetrically bisect the input axes of the orthogonal triad;

means for establishing an analytical equivalent to data from the fourth gyro and the fourth accelerometer from measurements made by the orthogonal triad including means for providing compensated incremental angle vectors, means for providing compensated incremental velocity vectors, and means for transforming the incremental angle vectors and the incremental velocity vectors to an analytical equivalent measurement along the axes of the fourth gyro and the fourth accelerometer, respectively; and

means for comparing data from the fourth gyro and the fourth accelerometer to said analytical equivalent for validating the performance of the inertial navigation system.

2. A system as described by claim 1, wherein:

the means for providing a compensated incremental angle vector includes means for compensating for instrumentation and dynamic errors; and

the means for providing a compensated incremental velocity vector includes means for compensating for instrumentation and dynamic errors.

3. An inertial navigation system including a self-contained performance validating arrangement, comprising:

an inertial sensor assembly including a substantially orthogonal triad having three gyros and three accelerometers;

said inertial sensor assembly including a fourth gyro and a fourth accelerometer having input axes which symmetrically bisect the input axes of the orthogonal triad;

means for establishing an analytical equivalent to data from the fourth gyro and the fourth accelerometer from measurements made by the orthogonal triad;

means for comparing data from the fourth gyro and the fourth accelerometer to said analytical equivalent for validating the performance of the inertial navigation system;

means for summing the transformed incremental angle vectors and for providing a first summation output;

means for summing the transformed incremental velocity vectors and for providing a second summation output;

means for summing the incremental bisector angles from the fourth bisector gyro and for providing a third summation output;

means for summing the incremental bisector velocities from the fourth bisector accelerometer and for providing a fourth summation output;

means for taking the differences between the first and third summation outputs, said differences corresponding to an angle error criteria; and

means for taking the differences between the second and fourth summation outputs, said differences corresponding to a velocity error criteria.

4. A system as described in claim 3, wherein:

the differences between the first and third summation outputs correspond to the net angle rotated about the input axis of the fourth gyro.

5. A system as described by claim 3, wherein:

the differences between the second and fourth summation outputs are the double integral of acceleration and correspond to position.

6. A self-contained method for validating the performance of an inertial navigation system, comprising:

providing an inertial sensor assembly with a substantially orthogonal triad having three gyros and three accelerometers;

providing a fourth gyro and a fourth accelerometer having input axes which symmetrically bisect the input axes of the orthogonal triad;

establishing an analytical equivalent to data from the fourth gyro and the fourth accelerometer from measurements made by the orthogonal triad including establishing compensating incremental angle vectors, establishing compensated incremental velocity vectors, and transforming the incremental angle vectors and the incremental velocity vectors to an analytical equivalent measurement along the axes of the fourth gyro and the fourth accelerometer, respectively; and

comparing data from the fourth gyro and the fourth accelerometer to said analytical equivalent for validating the performance of the inertial navigation system.

7. A system as described by claim 6, including:

compensating the incremental angle and velocity vectors for instrumentation and dynamic errors.

8. A method as described by claim 6, including:

summing the transformed incremental angle vectors and providing a first summation output;

summing the transformed incremental velocity vectors and providing a second summation output;

summing the incremental bisector angles from the fourth bisector gyro and providing a third summation output;

summing the incremental bisector velocities from the fourth bisector accelerometer and providing a fourth summation output;

taking the differences between the first and third summation outputs, said differences corresponding to an angle error criteria; and

taking the differences between the second and fourth summation outputs, said differences corresponding to a velocity error criteria.

9. A method as described by claim 8, wherein:

the differences between the first and third summation outputs correspond to the net angle rotated about the input axis of the fourth gyro.

10. A method as described by claim 8, wherein:

the differences between the second and fourth summation outputs are the double integral of acceleration and correspond to position.