Method and apparatus for measuring the structural integrity of a safe-life aircraft component

• US 8,826,738 B2
• Filed: 05/20/2011
• Issued: 09/09/2014
• Est. Priority Date: 07/06/2005
• Status: Active Grant

• Current Assignee: Airbus Operations Limited (Airbus SE)
• Original Assignee: Airbus Operations Limited (Airbus SE)
• Inventors: El-Bakry, Murad, Atherton, Kathryn Jane, Paget, Christophe Armand Nicolas
• Primary Examiner(s): SAINT SURIN, JACQUES M
• Application Number:
  US13/112,007
• Publication Number:
  US 20110219878A1
• Time in Patent Office: 1,208 Days
• Field of Search: 735/87, 735/97, 735/98, 736/02, 737/99, 738/01, 738/02, 702/34, 702/39, 702/188, 702/189, 702/196, 702/197
• US Class Current: 73/587
• CPC Class Codes: G01H 1/00 Measuring characteristics of vibrations in solids by using direct conduction to the detector G01H9/00, G01H11/00 take precedence

Abstract

The structural integrity of a safe-life aircraft component on an aircraft is measured and assessed by a processing unit. The component includes a load-bearing metal element that is free from cracks. In the method, acoustic emissions generated in the metal element are converted into electronic signals. The acoustic emissions converted include relevant acoustic emissions resulting from changes in the structure of the element that make the element more susceptible to the formation of cracks. The electronic signals are set to a processing unit. The processing unit processes over time the signals in conjunction with stored reference data that allows a measure of the structural integrity to be made. Information providing a measure of the structural integrity of the aircraft component is outputted. Thus, deterioration of the structure of the component can be detected and monitored before a crack occurs.

Claims

1. A method of measuring the structural integrity of a safe-life aircraft component on an aircraft, the component comprising a load-bearing metal element that is free from cracks, the method including the steps of:

converting acoustic emissions generated in the metal element into electronic signals, the acoustic emissions converted including relevant acoustic emissions resulting from changes in the structure of the element that make the element more susceptible to the formation of cracks,

sending the electronic signals to a processing unit, and

with the processing unit processing over time the signals in conjunction with stored reference data that allows a measure of the structural integrity to be made from the signals sent to the processing unit, and

outputting information providing a measure of the structural integrity of the aircraft component before any cracks occur.

2. A method according to claim 1, wherein the information outputted comprises a prediction concerning the likely occurrence of crack initiation.

3. A method according to claim 2, wherein the prediction comprises an indication of the predicted mean time left before a crack will occur.

4. A method according to claim 1, wherein the step of processing the signals includes calculating the cumulative number of relevant acoustic emissions over a period.

5. A method according to claim 4, wherein the step of processing the signals includes a step of effectively comparing the cumulative number of relevant acoustic emissions with a pre-set threshold.

6. A method according to claim 1, wherein the step of processing the signals includes a step of monitoring the number of relevant acoustic emissions over a pre-set period.

7. A method according to claim 1, wherein the step of processing the signals includes a step of calculating a characteristic relating to the rate of relevant acoustic emissions.

8. A method according to claim 1, wherein the step of processing the signals includes taking into account an indication of the proximity of the sources of the respective relevant acoustic emissions relative to each other.

9. A method according to claim 1, wherein the information providing a measure of the structural integrity of the aircraft component comprises an indication whether or not the aircraft component is deemed to be in need of further action.

10. A method according to claim 9, wherein the further action is further non-destructive testing to obtain an assessment of the structural integrity of the aircraft component, such testing not being dependent on the monitoring of acoustic emissions.

11. A method according to claim 10, wherein the method includes implementing the further action.

12. A method according to claim 9, wherein the further action comprises replacing at least a part of the aircraft component.

13. A method according to claim 12, wherein the method includes implementing the further action.

14. A method according to claim 9, further comprising implementing the further action.

15. A method according to claim 14, wherein the further action is further non-destructive testing to obtain an assessment of the structural integrity of the aircraft component, such testing not being dependent on the monitoring of acoustic emissions.

16. A method according to claim 1 including providing a multiplicity of acoustic emission sensors for effecting the step of converting acoustic emissions generated in the aircraft component into electronic signals.

17. A method according to claim 1, wherein the aircraft component is in the form of a component on an aircraft landing gear.

18. A processing unit programmed to perform the steps performed by the processing unit according to claim 1.

19. A non-transitory computer readable medium containing therein software that is configured to program a processing unit to perform the steps performed by the processing unit in the method according to claim 1.

20. A non-transitory computer reading medium containing therein reference data for use as the stored reference data as required by the method according to claim 1.

21. A kit of parts, comprising a processing unit and a multiplicity of acoustic emission sensors, the kit of parts being configured to implement the method according to claim 1.

22. A kit of parts according to claim 21, further comprising a computer reference data for use as the stored reference data as required by the method.

23. A method according to claim 1, wherein

the information providing a measure of the structural integrity of the aircraft component before any cracks occur comprises an indication that the aircraft component is in need of further action;

and

the method further comprises implementing the further action in response to said indication.

24. A method according to claim 23, wherein the further action is at least one selected from the group consisting of

non-destructive testing to obtain an assessment of the structural integrity of the aircraft component, such testing not being dependent on the monitoring of acoustic emissions;

testing the load-bearing metal element;

performing a routine test on the load-bearing metal element more often;

replacing the aircraft component or the load-bearing metal element; and

repairing the aircraft component or the load-bearing metal element.

30. An aircraft, comprising:

a crack-free safe-life aircraft component forming a load-bearing metal element of the aircraft, and

an apparatus for performing the method of claim 1 on the safe-life component, the apparatus comprising a processing unit, a multiplicity of acoustic emission sensors, and a reference data storage,

wherein

the multiplicity of acoustic emission sensors is arranged to convert acoustic emissions generated in the metal element into electronic signals,

the processing unit is arranged to receive electronic signals derived from the signals sent by the acoustic emission sensors,

the reference data storage includes stored reference data that allows a measure of the structural integrity of the aircraft component to be made from the signals sent to the processing unit, and

the processing unit is arranged to process over time the received electronic signals in conjunction with the stored reference data and to output information providing a measure of the structural integrity of the aircraft component.

25. A method of acquiring data for subsequent processing, the data concerning the structural properties of a safe-life aircraft component on an aircraft, the component comprising a load-bearing metal element that is free from cracks, the method comprising:

converting acoustic emissions generated in the metal element into electronic signals, the acoustic emissions converted including relevant acoustic emissions resulting from changes in the structure of the element that make the element more susceptible to the formation of cracks,

assessing which of the electronic signals correspond to relevant acoustic emissions, and

storing the electronic signals that have been assessed as corresponding to relevant acoustic emissions as measurement data in a data storage.

26. A kit of parts, comprising a multiplicity of acoustic emission sensors and a data storage unit for the storage of measurement data for subsequent processing, the kits of parts being configured to implement the method according to claim 25.

31. An aircraft, comprising:

a crack-free safe-life aircraft component forming a load-bearing metal element of the aircraft, and

an apparatus for performing the method of claim 25 on the safe-life component, the apparatus comprising a multiplicity of acoustic emission sensors, and a measurement data storage,

wherein

the multiplicity of acoustic emission sensors is arranged to convert acoustic emissions generated in the metal element into electronic signals, and

the measurement data storage is arranged to receive data signals derived from the electronic signals from the acoustic emission sensors and to store those signals as measurement data in the measurement data storage.

27. A method of measuring the structural integrity of a safe-life aircraft component on an aircraft, the component comprising a load-bearing metal element, the method comprising the steps of:

arranging at least one acoustic emission sensor on or around the metal element that is free from cracks,

acquiring, by the at least one acoustic emission sensor, measurement data, including data concerning relevant acoustic emissions generated in the metal element as a result of changes in the submicrostructure of the metal element that contribute to the formation of cracks and make the element more susceptible to the formation of cracks,

processing the data so acquired with a processing unit in conjunction with stored reference data that allows a measure of the structural integrity of the aircraft component to be made from the acquired measurement data, and

outputting information providing a measure of the structural integrity of the aircraft component before any cracks occur.

28. A processing unit programmed to perform the steps performed by the processing unit according to claim 27.

29. A non-transitory computer readable medium containing therein software that is configured to program a processing unit to perform the steps performed by the processing unit in the method according to claim 27.