Defects detection of the composition caisson of the aircraft wing by the acoustic emission method during static and shock load

Abstract

Acoustic emission (AE) control of defects was performed during testing of the T800 carbon fiber wing caisson. Static and shock loading of the structure was performed, and the location of AE signal sources was performed in real time. Under static loading, the coordinates of the localized sources corresponded to the location of the third rib. Clustering of AE signals based on their digitized form is performed. This allowed the formation of clusters corresponding to structural failure. It is shown that during the loading of the wing caisson, an increase in the structural coefficient of AE signals was observed, corresponding to the stratification of carbon fiber in the location zone. In the process of applying shock damage, AE information corresponding to shock loads was recorded.