Method and apparatus for monitoring a structure

• US 7,983,854 B2
• Filed: 03/11/2009
• Issued: 07/19/2011
• Est. Priority Date: 04/16/2008
• Status: Active Grant

• Current Assignee: Airbus Operations Limited (Airbus SE)
• Original Assignee: Airbus Operations Limited (Airbus SE)
• Inventors: O'Brien, Edwin William
• Primary Examiner(s): Le; John H
• Application Number:
  US12/401,915
• Publication Number:
  US 20090265120A1
• Time in Patent Office: 860 Days
• Field of Search: 702/42, 702/101, 702/104, 702/173, 702/174, 737/27, 737/80, 738/626.27, 738/626.29, 738/49, 335/33, 335/443, 335/44, 166/250.01, 384/448, 356/33
• US Class Current: 702/42
• CPC Class Codes: B64C 25/00 Alighting gear air-cushion alighting gear B60V3/08
• CPC Class Codes: G01L 1/2225 the direction being perpendicular to the central axis
• CPC Class Codes: G01M 5/0041 by determining deflection or stress
• CPC Class Codes: G01M 5/0083 by measuring variation of impedance, e.g. resistance, capacitance, induction

Abstract

The present disclosure discloses a method of monitoring a structure by a monitoring system including at least one strain gauge positioned on the structure and a computer processor coupled to the at least one strain gauge. According to at least one embodiment, strain data are acquired using the at least one strain gauge, and it is determined, by the computer processor, whether the structure has undergone plastic deformation according to the strain data. Further, a result is outputted according to the determination of plastic deformation.

Claims

1. A method of monitoring a structure by a monitoring system comprising at least one strain gauge positioned on the structure and a computer processor coupled to the at least one strain gauge, the method comprising:

acquiring strain data using the at least one strain gauge;

determining, by the computer processor, whether the structure has undergone plastic deformation according to the strain data; and

outputting a result according to the determination of plastic deformation.

2. The method of claim 1, wherein the at least one strain gauge is positioned in a region of substantially constant shear.

3. The method of claim 1, wherein the determination of plastic deformation comprises comparing the strain data with a threshold.

4. The method of claim 1, wherein the acquiring strain data is performed during a transient loading event, and the determination of plastic deformation is performed based on the strain data acquired during the transient loading event.

5. The method of claim 1 wherein the acquiring strain data is performed after a transient loading event, and the determination of plastic deformation comprises determining whether a residual strain due to plastic deformation is retained in the structure after the transient loading event based on the strain data acquired after the transient loading event.

6. The method of claim 5 further comprising:

supplying substantially no power to the at least one gauge during the transient loading event; and

supplying power to the at least one gauge after the transient loading event in order to acquire the strain data.

7. The method of claim 5, further comprising lifting the structure to at least partially remove a gravitational load in the structure caused by at least a gravitational force, wherein the acquiring strain data is performed after the structure has been lifted.

8. The method of claim 1, further comprising estimating a gravitational load in the structure caused by at least a gravitational force, wherein the determination of plastic deformation is performed further according to the estimated gravitational load.

9. A method of determining an abnormal landing of an aircraft, the method comprising monitoring a structure of the aircraft by the method of claim 1.

10. An apparatus for monitoring a structure, comprising:

one or more strain gauges positioned on the structure; and

a processor coupled to the one or more gauges and configured to receive strain data from the one or more gauges, to analyse the strain data to determine whether the structure has undergone plastic deformation, and to output a result according to the determination of plastic deformation.

11. The apparatus of claim 10 wherein the structure comprises a pin with an annular groove.

12. The apparatus of claim 11 wherein at least one of the one or more strain gauges is positioned in the annular groove.

13. The apparatus of claim 11 wherein the structure comprises a pin with an internal annular groove and an external annular groove located at substantially the same axial position along the pin.

14. The apparatus of claim 13 wherein at least one of the one or more strain gauges is positioned in the internal annular groove.

15. The apparatus of claim 13 wherein the internal annular groove is deeper than the external annular groove.

16. The apparatus of claim 10, wherein the structure comprises:

a pin bearing comprising at least two elements defining adjacent axially separated bearing surfaces which bear on a pin; and

at least one of the strain gauges is positioned on the pin and axially aligned with an interface between the axially separated bearing surfaces.

17. The apparatus of claim 10, further comprising a memory coupled to the processor, the memory is arranged for storing the strain data received from the one or more gauges.

18. The apparatus of claim 10, further comprising an output device coupled to the processor, the output device is arranged for indicating a result outputted from the processor.

19. The apparatus of claim 18, wherein the output device is a warning light.

20. The apparatus of claim 10, further comprising a battery selectively coupled to the one or more gauges.