Transducer Placement Option of Lamb Wave SHM System for Hotspot Damage Monitoring

Transducer Placement Option of Lamb Wave SHM System for Hotspot Damage Monitoring

Adrianus Ewald, V. (TU Delft Structural Integrity & Composites)
Groves, R.M. (TU Delft Structural Integrity & Composites)
Benedictus, R. (TU Delft Structural Integrity & Composites)

2018

In 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.

sensor placement option
hotspot damage
Lamb wave
Structural Health Monitoring (SHM)
finite element modelling
image processing
additive color model

http://resolver.tudelft.nl/uuid:0289262a-bc71-45ce-8d8d-0a9ead34a410

https://doi.org/10.3390/aerospace5020039

2226-4310

Aerospace — Open Access Aeronautics and Astronautics Journal, 5 (2)

Institutional Repository

journal article

© 2018 V. Adrianus Ewald, R.M. Groves, R. Benedictus