GYROSCOPIC FAILURE DETECTION IN A NAVIGATION DEVICE THROUGH SENSOR CORRELATION

• US 20100243791A1
• Filed: 11/30/2006
• Published: 09/30/2010
• Est. Priority Date: 11/30/2006
• Status: Abandoned Application

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Bacon, Robert R., Zubkow, Zygmunt
• Application Number:
  US11/565,173
• Publication Number:
  US 20100243791A1
• Time in Patent Office: Days
• US Class Current: 244/3.150
• CPC Class Codes: F42B 15/01 Arrangements thereon for guidance or control steering arrangements F42B10/60; aircraft flight control B64C; guidance systems other than those installed aboard F41G7/00, F41G9/00; locating by use of radio or other waves G01S; flight control in general G05D1/00; computer aspects G06]
• CPC Class Codes: G01C 21/16 by integrating acceleration or speed, i.e. inertial navigation
• CPC Class Codes: G01C 25/005 initial alignment, calibration or starting-up of inertial devices

Abstract

A method of determining the integrity of a gyro in a navigation system is provided. The method includes detecting a relatively sudden change in one of a pitch, yaw and roll signal from a respective pitch, yaw and roll gyro and reviewing at least one other of the pitch, yaw and roll signals to verify the relatively sudden change.

Claims

1. A method of determining the integrity of a gyro in a navigation system, the method comprising:

detecting a sudden change in one of a pitch, yaw and roll signal from a respective pitch, yaw and roll gyro in the navigation system of a device experiencing coning in an exoatmospheric environment; and

reviewing at least one other of the pitch, yaw and roll signals to verify the sudden change.

2. The method of claim 1, further comprising:

monitoring the pitch signal from the pitch gyro in the navigation system;

monitoring the yaw signal from the yaw gyro in the navigation system; and

monitoring the roll signal from the roll gyro in the navigation system.

3. The method of claim 1, wherein verify the sudden change further comprises:

determining if a corresponding change occurred in the at least one other of the pitch, yaw and roll signals at the same time.

4. The method of claim 3, further comprising:

when a corresponding change is not observed, detecting a faulty gyro signal.

5. The method of claim 4, further comprising:

replacing the faulty gyro.

6. The method of claim 3, further comprising:

when a corresponding change is observed, verifying a valid gyro signal.

7. The method of claim 3, wherein the corresponding change is at least one of magnitude of signal change and frequency of signal change.

8. A method of navigation, the method comprising:

monitoring roll, pitch and yaw of a device experiencing coning in an free coast environment;

generating respective roll, pitch and yaw signals based on the monitoring of the roll, pitch and yaw of the device;

monitoring the roll, pitch and yaw signals for sudden changes; and

when a sudden change in one of the roll, pitch and yaw signals occurs in the monitored roll, pitch and yaw signals, verify if the signal with the sudden change is valid by verifying a corresponding change in at least one other of the roll, pitch and yaw signals.

9. The method of claim 8, further comprising:

when the roll, pitch and yaw signal with the sudden change cannot be verified, ignoring the signal.

10. The method of claim 8, further comprising:

replacing the roll, pitch and yaw signal with a respective backup signal when the respective roll, pitch and yaw signal with the sudden change cannot be verified.

11. The method of claim 8, wherein monitoring roll, pitch and yaw further comprises:

using respective roll, pitch and yaw gyros to monitor the respective roll, pitch and yaw.

12. The method of claim 8, wherein verifying a corresponding change in at least one other of the roll, pitch and yaw signals, further comprises:

detecting relative changes in at least one of magnitude and frequency at the same time as the signal with the sudden change.

13. The method of claim 8, wherein the device is an exoatmospheric device.

14. The method of claim 8, wherein the device is a missile.

15. A device having a navigation system, the device comprising:

a primary roll gyro configured to generate a roll signal based on the roll of the device;

a primary pitch gyro configured to generate a pitch signal based on the pitch of the device;

a primary yaw gyro configured to generate a yaw signal based on the yaw of the device; and

a controller adapted to control the navigation of the device based at least in part on the roll, pitch and yaw signals, the controller further configured to monitor each of the roll, pitch and yaw signals for sudden changes and to verify the accuracy of a roll, pitch and yaw signal with the sudden change by verifying a corresponding change in at least one other roll, pitch and yaw signal when the device is experiencing coning in an exoatmospheric environment.

16. The device of claim 15, further comprising:

a redundant roll gyro configured to generate a roll signal based on the roll of the device;

a redundant pitch gyro configured to generate a pitch signal based on the pitch of the device;

a redundant yaw gyro configured to generate a yaw signal based on the yaw of the device; and

wherein the controller is further configured to use a signal from a respective redundant roll, pitch and yaw gyro when the controller cannot verify the accuracy of the respective roll, pitch and yaw signal with the sudden change.

17. The device of claim 15, wherein verifying the corresponding change further comprises verifying at least one of the magnitude and the frequency of the at least one other roll, pitch and yaw signal.

18. The device of claim 15, wherein the device is a missile.

19. The device of claim 15, wherein the device is an exoatmospheric device.