1 April 2016 Finite element modeling of guided wave scattering at delaminations in composite panels
Author Affiliations +
Abstract
Carbon fiber laminate composites, consisting of layers of polymer matrix reinforced with high strength carbon fibers, are increasingly employed for aerospace structures. They offer advantages for aerospace applications, e.g., good strength to weight ratio. However, impact during the operation and servicing of the aircraft can lead to barely visible and difficult to detect damage. Depending on the severity of the impact, delaminations can occur, reducing the load carrying capacity of the structure. Efficient structural health monitoring of composite panels can be achieved using guided ultrasonic waves propagating along the structure. The guided ultrasonic wave (A0 Lamb wave mode) scattering at delaminations was modelled using full three-dimensional Finite Element (FE) simulations. The influence of the delamination size was systematically investigated from a parameter study. The angular dependency of the scattered guided wave amplitude was calculated using a baseline subtraction method. A significant influence of the delamination width on the guided wave scattering was found. The sensitivity of guided waves for the detection of barely visible impact damage in composite panels has been predicted.
© (2016) COPYRIGHT Society of Photo-Optical Instrumentation Engineers (SPIE). Downloading of the abstract is permitted for personal use only.
B. I. S. Murat, B. I. S. Murat, P. Fromme, P. Fromme, "Finite element modeling of guided wave scattering at delaminations in composite panels", Proc. SPIE 9805, Health Monitoring of Structural and Biological Systems 2016, 98050S (1 April 2016); doi: 10.1117/12.2220409; https://doi.org/10.1117/12.2220409
PROCEEDINGS
6 PAGES


SHARE
Back to Top