METHOD FOR DETECTING WHETHER PERFORMANCE OF AIRCRAFT COMPONENTS IS IN THE DETERIORATION PERIOD

• US 20130179028A1
• Filed: 07/06/2012
• Published: 07/11/2013
• Est. Priority Date: 07/07/2011
• Status: Active Grant

• Current Assignee: Air China Limited
• Original Assignee: Air China Limited
• Inventors: GU, Zhuping, DING, Huifeng, ZHENG, Fengliang, WU, Yubin, WU, Jiaju, ZHU, Yi, WANG, Bingzheng, MA, Hongtao, HUNAG, Lei
• Granted Patent: US 8,798,848 B2
• Time in Patent Office: Days
• US Class Current: 701/29.4
• CPC Class Codes: G05B 23/0275 Fault isolation and identification, e.g. classify fault; estimate cause or root of failure
• CPC Class Codes: G06F 17/00 Digital computing or data processing equipment or methods, specially adapted for specific functions information retrieval, database structures or file system structures therefor G06F16/00

Abstract

The present application discloses a method for detecting whether performance of an aircraft component is in a decline period, comprising: obtaining one or more detection parameters reflecting operation status of the aircraft component; comparing data of the one or more detection parameters with respective desired values; and determining whether the performance of the aircraft component is in the decline period based on a comparison result.

Claims

1. A method for detecting whether performance of an aircraft component is in a decline period, comprising:

obtaining one or more detection parameters reflecting operation status of the aircraft component;

comparing data of the one or more detection parameters with respective predetermined values; and

determining whether the performance of the aircraft component is in the decline period based on the comparison results.

2. A method according to claim 1, wherein, the step of obtaining comprising:

obtaining multiple parameters related to operation status of the aircraft component;

associating data of the multiple parameters with failure events of the aircraft component; and

determining the detection parameters based on the associations between the multiple parameters and the failure events.

3. A method according to claim 2, wherein, the steps of associating data of the multiple parameters with failure events of the aircraft component and determining the detection parameters based on the associations comprising:

calculating correlations between data changes of the multiple parameters and the failure events; and

setting one or more parameters, which have greater correlations than a threshold, of the multiple parameters as the detection parameters.

4. A method according to claim 3, wherein, a range of the threshold is 0.3-0.5.

5. A method according to claim 3, wherein, a range of the threshold is 0.5-0.7.

6. A method according to claim 3, further comprising:

calculating correlations between the multiple detection parameters; and

removing one or more of the multiple detection parameters based on the correlations between the multiple detection parameters.

7. A method according to claim 1, wherein, the step of obtaining comprising:

obtaining multiple parameters related to operation status of the aircraft component; and

determining the detection parameters based on respective physical representations indicated by the multiple parameters.

8. A method according to claim 1, wherein, the predetermined value is an extreme value of the one or more detection parameters;

and

the step of comparing comprising;

calculating differences or ratios between measured values of one or more detection parameters and their respective extreme values.

9. A method according to claim 8, wherein, the measured values of the one or more detection parameters are replaced with converted values under a specific condition.

10. A method according to claim 8, wherein, the step of determining comprising:

determining whether the measured values of the one or more detection parameters are close to or exceed the respective extreme values.

11. A method according to claim 8, further comprising:

assigning a weight to the ratio between the measured value of each of the one or more detection parameter and the respective extreme value.

12. A method according to claim 11, further comprising:

obtaining the weight of each detection parameter based on a correlation between data change of the multiple detection parameters and the failure events of the aircraft component.

13. A method according to claim 11, wherein, the step of determining comprising:

integrating the weighted ratios of the measured values of the multiple detection parameters to the extreme values thereof to obtain performance reference values of the aircraft component.

14. A method according to claim 13, further comprising:

determining the performance of the aircraft component is in the decline period if the reference value of the aircraft component is greater than a threshold value.

15. A method according to claim 1, wherein, the predetermined value is a reference slope of a change trend of one or more detection parameters, and

wherein the step of comparing comprising:

calculating a slope of a change trend of the measured values of the one or more detection parameters in a period.

16. A method according to claim 15, further comprising:

comparing the slope of a change trend of the measured values of the one or more detection parameters in a period with the reference slope to determine whether there is significant difference between them.

17. A method according to claim 16, wherein, the step of determining whether the performance of the aircraft component is in the decline period based on the comparison result comprising:

determining the performance of the aircraft component is in the decline period if there is significant difference between the slope of a change trend of the measured values of the one or more detection parameters in a period and the reference slope.

18. A method according to claim 15, wherein, the reference slope is a slope of change trend in a period after the aircraft component is initially installed.

19. A method according to claim 15, wherein, the reference slope is a slope of change trend in a period of the same aircraft component having good working condition in other identical model of aircraft.

20. A method according to claim 15, further comprising:

replacing the measured values of the one or more of the detection parameters with converted values under a specific condition.

21. A method according to claim 15, further comprising:

performing a smooth processing on the measured values of the one or more of the detection parameters.

22. A method according to claim 21, wherein, the smooth processing adopts multipoint average rolling mean algorithm.

23. A method according to claim 21, wherein, the smooth processing adopts following formula:

X_new=C1X_smooth+C2X_old

wherein, X_old is the measured value, X_new is a value after the smooth processing, X_smooth is a value of adjacent points after the smooth processing or is an average value of several adjacent points, C1 and C2 are the weight values.

24. A method according to claim 1, wherein, the step of comparing:

setting measured values of the one or more detection parameters in a period as a sample;

setting measured values of the one or more detection parameter in a pervious period of the same length as a reference sample; and

determining whether there is significant difference between the sample and the reference sample based on an independent sample test.

25. A method according to claim 24, wherein, the step of determining whether the performance of the aircraft component is in the decline period based on the comparison result comprising:

determining the performance of the aircraft component is in the decline period, if there is significant difference between the sample of the measured values of one or more detection parameters in a period related and the corresponding reference sample.

26. A method according to claim 24, further comprising:

replacing the measured values of the one or more detection parameters with converted values under a specific condition.

27. A method for maintaining an aircraft, comprising:

determining whether the performance of the aircraft component is in the decline period based on the method in claim 1;

arranging a maintenance schedule of the aircraft if the performance of the aircraft component is in the decline period; and

maintaining the aircraft component of the aircraft.

28. A method for obtaining one or more detection parameters reflecting operation status of an aircraft component, comprising:

obtaining multiple parameters related to operation status of the aircraft component;

associating data of the multiple parameters with failure events of the aircraft component; and

determining the detection parameters based on the associations between the multiple parameters and the failure events.

29. A method according to claim 28, wherein, the step of obtaining comprising:

calculating a correlation between a data change of the multiple parameters and the failure events; and

setting one or more parameters, which have greater correlations than a threshold, of the multiple parameters as the detection parameters.

30. A method according to claim 29, wherein, a range of the threshold is 0.3-0.5.

31. A method according to claim 29, wherein, a range of the threshold is 0.5-0.7.

32. A method according to claim 29, further comprising:

calculating correlations between the multiple detection parameters; and

removing one or more of the multiple detection parameters based on the correlations between the multiple detection parameters.

33. A method according to claim 28, wherein, the step of obtaining comprising:

obtaining multiple parameters related to operation status of the aircraft component; and

determining the detection parameters based on respective physical meaning indicated by the multiple parameters.