Entropy-based impact load identification

Patent metadata

Field	Value
Publication number	US-9534993-B2
Application number	US-201113882891-A
Country	US
Kind code	B2
Filing date	Nov 1, 2011
Priority date	Nov 1, 2010
Publication date	Jan 3, 2017
Grant date	Jan 3, 2017

Abstract

Methods and apparatus for identifying the location of the load on a structure. Various embodiments include calculating a plurality of potential loading sites, assessing the statistical order of each of those predictions, and selecting regions of the structure where the load most likely occurred based on the orderliness (or randomness) of the assessments.

First claim

What is claimed is:

1. A method for estimating an unknown load acting on an aircraft structure, comprising:
providing an aircraft structure having a plurality of accelerometers mounted thereto, a processor receiving a signal from each of the accelerometers, and a graphical user interface;
measuring with the processor a plurality of accelerometer responses of the aircraft structure to the unknown load;
calculating with the processor a plurality of hypothetical loads each associated with a different one of the plurality of accelerometer responses;
calculating with the processor an entropy associated with each of the hypothetical loads and determining the location on the aircraft structure of the hypothetical load having the lowest entropy; and
identifying the location on the graphical user interface.

2. The method of claim 1 which further comprises identifying the hypothetical loads having an entropy less than a predetermined value; and estimating the unknown load from the range of identified hypothetical loads.

3. The method of claim 1 wherein said calculating hypothetical loads are time domain impact loads.

4. The method of claim 1 wherein said measuring is measuring triaxial accelerometer responses.

5. The method of claim 1 which further comprises calculating the frequency-domain characteristics of each of the plurality of responses.

6. The method of claim 1 which further comprises preparing a structural mathematical model of the aircraft structure wherein the degrees of freedom of said plurality of responses is substantially less than the degrees of freedom of the hypothetical loads, and said calculating with the processor uses the model.

7. The method of claim 1 wherein said calculating the entropy is in the time domain.

8. The method of claim 1 wherein the aircraft structure is a fuselage including a composite panel.

9. A method of estimating an unknown load acting on an aircraft structure, comprising:
providing an aircraft structure having a plurality of accelerometers mounted thereto, a processor receiving a signal from each of the accelerometers, and a graphical user interface;
calculating with the processor a plurality of hypothetical loads associated with the acceleration response of the aircraft structure to the unknown load;
selecting one of the hypothetical loads;
calculating with the processor a first factor corresponding to the energy of the one hypothetical load;
restricting the one hypothetical load;
calculating with the processor a second factor corresponding to the energy of the restricted hypothetical load;
preparing a corrected hypothetical load based on the difference between the first factor and the second factor; and
identifying the location of the selected load on the aircraft structure with the graphical user interface.

10. The method of claim 9 wherein said preparing includes calculating the energy of the restricted hypothetical load and multiplying the energy by the ratio of the first factor to the second factor.

11. The method of claim 9 wherein said restricting is by eliminating some of the frequency content of the one hypothetical load.

12. The method of claim 9 wherein said restricting is by placing a window on the time response of the one hypothetical load.

13. The method of claim 9 wherein said selecting includes quantifying the randomness of the hypothetical loads in one of the time domain or frequency domain.

14. A method for identifying damage to an aircraft structure, comprising:
providing an aircraft structure having a plurality of accelerometers mounted thereto, and a structural health monitoring system including a processor;
providing to the processor a plurality of time-domain data corresponding to responses of the aircraft structure to an event;
quantifying with the processor the randomness associated with each of the plurality of responses;
identifying with the processor regions of the aircraft structure with possible damage based on said quantifying; and
notifying a user of the structural health monitoring system of the identified regions of the aircraft structure.

15. The method of claim 14 which further comprises converting the time domain data to a plurality of hypothetical forcing functions, and the responses are the plurality of hypothetical forcing functions.

16. The method of claim 15 wherein the hypothetical forcing functions are impact loads.

17. The method of claim 14 wherein said quantifying is by calculating an entropy associated with each of the plurality of responses.

18. The method of claim 14 wherein said quantifying includes calculating the statistical likelihood of the responses in the frequency domain.

19. The method of claim 14 wherein said quantifying includes compressing the data into separate data files, and the identified regions have larger data files than the non-identified regions.

20. The method of claim 14 wherein said quantifying includes calculating the energy of the responses.

21. The method of claim 14 wherein said quantifying includes detecting the threshold crossings of the responses and the identified regions have more crossings than the non-identified regions.

22. A method of estimating an unknown load acting on an aircraft structure, comprising:
providing an accelerometer signal corresponding to the acceleration response of the aircraft structure to the unknown load;
determining with a digital processor that the unknown load includes a plurality of separate impact loads to the aircraft structure;
digitally processing the signal and determining with the processor a plurality of time windows, each of the time windows corresponding to a different one of the separate impacts;
applying the plurality of time windows to the time base of the signal to produce a plurality of separated signals, each separated signal corresponding to a different one of the separate loads;
transmitting the separated signals to a structural health monitoring system; and
identifying with the structural health monitoring system from the separated signals at least one of the location or magnitude for one of the separated loads acting on the aircraft structure.

23. The method of claim 22 wherein said determining is by preparing an envelope of the signal.

24. The method of claim 23 wherein said preparing is an envelope of the magnitude of the signal in terms of the time-based spatial response of the aircraft structure.

25. The method of claim 23 wherein said preparing is by calculating a Hilbert transform of the signal.

26. The method of claim 22 wherein said processing includes filtering the signal with a low pass filter.

27. The method of claim 26 which further comprises selecting relative minimums in the filtered signal, and wherein said determining is with the relative minimums.

Assignees

• Bond Ray
• Adams Douglas E
• Purdue Research Foundation

Inventors

• Bond Ray
• Adams Douglas E

Classifications

• G01M5/0033

  by determining damage, crack or wear · CPC title

• G01N3/00 Primary

  Investigating strength properties of solid materials by application of mechanical stress · CPC title

• G01M5/0066

  by exciting or detecting vibration or acceleration (vibration testing of structures G01M7/00) · CPC title

• G01L5/0052 Primary

  measuring forces due to impact (G01L5/0061, G01L5/14 take precedence; impact testing of structures G01M7/08; impact testing of material G01N3/00) · CPC title

• G01M7/08

  Shock-testing · CPC title