Transducer Placement Option of Lamb Wave SHM System for Hotspot Damage Monitoring
AbstractIn this paper, we investigated transducer placement strategies for detecting cracks in primary aircraft structures using ultrasonic Structural Health Monitoring (SHM). The approach developed is for an expected damage location based on fracture mechanics, for example fatigue crack growth in a high stress location. To assess the performance of the developed approach, finite-element (FE) modelling of a damage-tolerant aluminum fuselage has been performed by introducing an artificial crack at a rivet hole into the structural FE model and assessing its influence on the Lamb wave propagation, compared to a baseline measurement simulation. The efficient practical sensor position was determined from the largest change in area that is covered by reflected and missing wave scatter using an additive color model. Blob detection algorithms were employed to determine the boundaries of this area and to calculate the blob centroid. To demonstrate that the technique can be generalized, the results from different crack lengths and from tilted crack are also presented. View Full-Text
Share & Cite This Article
Ewald, V.; Groves, R.M.; Benedictus, R. Transducer Placement Option of Lamb Wave SHM System for Hotspot Damage Monitoring. Aerospace 2018, 5, 39.
Ewald V, Groves RM, Benedictus R. Transducer Placement Option of Lamb Wave SHM System for Hotspot Damage Monitoring. Aerospace. 2018; 5(2):39.Chicago/Turabian Style
Ewald, Vincentius; Groves, Roger M.; Benedictus, Rinze. 2018. "Transducer Placement Option of Lamb Wave SHM System for Hotspot Damage Monitoring." Aerospace 5, no. 2: 39.
Note that from the first issue of 2016, MDPI journals use article numbers instead of page numbers. See further details here.