Share Email Print

Proceedings Paper

Finite element modeling of guided wave scattering at delaminations in composite panels
Format Member Price Non-Member Price
PDF $17.00 $21.00

Paper 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.

Paper Details

Date Published: 1 April 2016
PDF: 6 pages
Proc. SPIE 9805, Health Monitoring of Structural and Biological Systems 2016, 98050S (1 April 2016); doi: 10.1117/12.2220409
Show Author Affiliations
B. I. S. Murat, Univ. College London (United Kingdom)
P. Fromme, Univ. College London (United Kingdom)

Published in SPIE Proceedings Vol. 9805:
Health Monitoring of Structural and Biological Systems 2016
Tribikram Kundu, Editor(s)

© SPIE. Terms of Use
Back to Top
Sign in to read the full article
Create a free SPIE account to get access to
premium articles and original research
Forgot your username?