This contribution presents a study for the monitoring of fatigue crack growth at fastener holes in multi-layered aircraft structures using low frequency guided ultrasonic waves. The investigated model multi-layered structure consists of two adhesively bonded aluminum alloy tensile specimens. Guided ultrasonic waves were excited using multiple piezoelectric discs bonded to the surface of the multi-layered structure. The wave propagation in the tensile specimen was measured using a laser interferometer and compared to numerical simulations. Experiments and 3D Finite Element (FE) simulations show a change in the scattered field around fastener holes caused by a defect in the 2nd layer. During fatigue crack growth, changes in the amplitude of the ultrasonic signal at a single point were monitored and correlated to the optically measured crack length.
Monitoring fatigue crack growth in multi-layered tensile specimens using guided ultrasonic waves
Überwachung des Ermüdungsrisswachstums in Mehrschicht-Zugproben mittels geführter Ultraschallwellen
2009
8 Seiten, 5 Bilder, 12 Quellen
Conference paper
Storage medium
English
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