Methods and systems for fault determination for aircraft

• US 8,521,341 B2
• Filed: 06/26/2009
• Issued: 08/27/2013
• Est. Priority Date: 06/26/2009
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Brotherton, Tom
• Primary Examiner(s): Nguyen, Kim T
• Application Number:
  US12/492,944
• Publication Number:
  US 20100332053A1
• Time in Patent Office: 1,523 Days
• Field of Search: 701 3- 4, 701 10- 11, 701/14, 701/29.1, 701/29.2, 701/29.9, 701/30, 701/2, 701/31, 701/5, 701/7, 701/31.9, 701/32.4, 701/32, 701/32.9, 701/33.4, 701/415, 701/424, 701/439, 701/528
• US Class Current: 701/3
• CPC Class Codes: G05B 23/0254 based on a quantitative model, e.g. mathematical relationships between inputs and outputs; functions: observer, Kalman filter, residual calculation, Neural Networks
• CPC Class Codes: G05D 1/0055 with safety arrangements

Abstract

A method for fault determination for an aircraft includes the steps of generating a predicted maneuver of the aircraft using an aircraft operating input and a model of aircraft performance, determining an actual maneuver of the aircraft using information obtained from an inertial measurement system, comparing the predicted maneuver and the actual maneuver, and determining a fault of the aircraft based on the comparison of the predicted maneuver and the actual maneuver.

Claims

1. A method for fault determination for an aircraft, the method comprising the steps of:

generating a predicted maneuver for a non-landing component of flight of the aircraft using an aircraft operating input and a model of aircraft performance;

determining an actual maneuver of the aircraft using information obtained from an inertial measurement system;

comparing the predicted maneuver and the actual maneuver; and

determining a fault of the aircraft based on the comparison of the predicted maneuver and the actual maneuver.

2. The method of claim 1, wherein the input is selecting from the group consisting of:

a control input based on an action of a pilot of the aircraft, a control system input from a flight control system of the aircraft, or both during an aircraft maneuver during flight.

3. The method of claim 2, wherein the input further comprises environmental data pertaining to environmental conditions surrounding the aircraft during flight.

4. The method of claim 3, wherein the input further comprises performance data pertaining to aircraft performance values of the aircraft during flight.

5. The method of claim 1, wherein the step of determining the fault comprises the step of determining the fault of the aircraft based on the comparison of the predicted maneuver and the actual maneuver and historical data.

6. The method of claim 1, wherein the step of determining the fault comprises the step of determining the fault of the aircraft based on one or more of the following:

a predicted maneuver used classification, the comparison of the predicted maneuver and a Bayesian network, a neural network, a case based approach;

a knowledge based approach, a classification tool, or any combination thereof.

7. A program product for fault determination for an aircraft, the program product comprising:

a program configured to at least facilitate;

generating a predicted maneuver of the aircraft using an aircraft operating input and a model of aircraft performance;

determining an actual maneuver of the aircraft using information provided by an inertial measurement system;

comparing the predicted maneuver and the actual maneuver; and

determining a fault of the aircraft based on the comparison of the predicted maneuver and the actual maneuver; and

a non-transitory, wholly contained, computer-readable medium bearing the program and disposed onboard the aircraft.

8. The program product of claim 7, wherein the input comprises a control input based on an action of a pilot of the aircraft, a control system input from a flight control system of the aircraft, or both, during a non-landing component of flight of the aircraft.

9. The program product of claim 8, wherein the input further comprises environmental data pertaining to environmental conditions surrounding the aircraft during flight.

10. The program product of claim 9, wherein the input further comprises performance data pertaining to aircraft performance values of the aircraft during flight.

11. The program product of claim 9, wherein the program is further configured to at least facilitate:

determining the fault of the aircraft based on the comparison of the predicted maneuver and the actual maneuver and historical data.

12. A system for determination for an aircraft, the system comprising:

an inertial measurement system disposed within a housing and configured to at least facilitate obtaining information pertaining to an actual maneuver of the aircraft; and

a processor disposed within the housing, the processor coupled to the inertial measurement system and configured to at least facilitate;

generating a predicted maneuver of the aircraft using an aircraft operating input and a model of aircraft performance;

determining the actual maneuver of the aircraft using the information obtained by the inertial measurement system;

comparing the predicted maneuver and the actual maneuver; and

determining a fault of the aircraft based on the comparison of the predicted maneuver and the actual maneuver.

13. The system of claim 12, further comprising:

a plurality of sensors disposed within the housing and configured to obtain the aircraft operating input.

14. The system of claim 13, wherein the processor is further configured to at least facilitate:

determining the fault of the aircraft based on the comparison of the predicted maneuver and the actual maneuver and historical data.

15. The system of claim 13, wherein the inertial measurement system comprises a global positioning system disposed within the housing.

16. The system of claim 15, wherein the inertial measurement system further comprises a plurality of accelerometers disposed within the housing.

17. The system of claim 13, wherein the housing, the inertial measurement system and the processor are each disposed onboard the aircraft.

18. The system of claim 12, wherein the input comprises a control input based on an action of a pilot of the aircraft, a control system input from a flight control system of the aircraft, or both during a non-landing component of flight of the aircraft.

19. The system of claim 18, wherein the input further comprises environmental data pertaining to environmental conditions surrounding the aircraft during flight and performance data pertaining to aircraft performance values of the aircraft during flight.

20. The system of claim 18, wherein the input further comprises data based on a turn of the aircraft during flight.