On the applicability of acoustic emission to identify modes of damage in full-scale composite fuselage structures

The acoustic emission method was applied during the testing of six full-scale sandwich composite aircraft fuselage panels containing through-the-thickness notches. The panels were subjected to different combinations of quasi-static internal pressure, the corresponding hoop loads, and longitudinal lo...

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Bibliographic Details
Published in:Journal of composite materials 2016-02, Vol.50 (4), p.447-469
Main Authors: Awerbuch, Jonathan, Leone, Frank A, Ozevin, Didem, Tan, Tein-Min
Format: Article
Language:English
Subjects:
Acoustic emission
Aircraft components
Airframes
Composite materials
Damage
Emission
Fuselages
Panels
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Summary:The acoustic emission method was applied during the testing of six full-scale sandwich composite aircraft fuselage panels containing through-the-thickness notches. The panels were subjected to different combinations of quasi-static internal pressure, the corresponding hoop loads, and longitudinal loads. The applicability of conventional acoustic emission signal feature analysis to identify the dominant modes of failure and extraneous emission in large composite structures was investigated. It was concluded that no clear distinction could be made among the different failure mechanisms based on the conventional acoustic emission signal features alone. Further, emission generated by fretting, either among fracture surfaces or of loading fixtures, has acoustic emission signal waveform features that are similar to those of damage-generated emission signals.
ISSN:0021-9983
1530-793X
DOI:10.1177/0021998315576379