This Article Full Text (PDF) References Alert me when this article is cited Alert me if a correction is posted Services Email this article to a friend Similar articles in this journal Alert me to new issues of the journal Add to Saved Citations Download to citation manager Request Permissions Request Reprints Add to My Marked Citations Citing Articles Citing Articles via Google Scholar Citing Articles via Scopus Google Scholar Articles by Monnier, T. Search for Related Content Social Bookmarking                         What's this?

Lamb Waves-based Impact Damage Monitoring of a Stiffened Aircraft Panel using Piezoelectric Transducers

Group of Metallurgy and Materials Science (CNRS 5510), National Institute of Applied Sciences in Lyon, 69621 Villeurbanne Cedex, Francethomas.monnier{at}insa-lyon.fr

The growth of the use of composite materials to replace traditional materials as primary structures remains limited by the significant inspection costs that are required to detect the appearance of internal defects. Indeed, many different damage processes can be observed in such kinds of heterogeneous media. The present article defines an in situ and nondestructive method for the impact damage monitoring of carbon/epoxy laminated composites. This structural health monitoring (SHM) method aims to improve the operational safety of the structure using integrated piezoelectric sensors. We describe the propagation of Lamb waves inside a stiffened aeronautical structure, and the definition of associated data processing systems. The detection of realistic defects thanks to the definition of a damaging parameter, based on the real time analysis of the ultrasonic signatures transmitted inside the structure is outlined.

Key Words: composite material • monitoring • delamination • piezoelectric

Journal of Intelligent Material Systems and Structures, Vol. 17, No. 5, 411-421 (2006)
DOI: 10.1177/1045389X06058630


CiteULike    Complore    Connotea    Del.icio.us    Digg    Reddit    Technorati    Twitter    What's this?