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Airplane hot spot monitoring using integrated impedance and guided wave measurements
Author(s) -
An YunKyu,
Kim Min Koo,
Sohn Hoon
Publication year - 2012
Publication title -
structural control and health monitoring
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 1.587
H-Index - 62
eISSN - 1545-2263
pISSN - 1545-2255
DOI - 10.1002/stc.1493
Subject(s) - airplane , lead zirconate titanate , durability , structural engineering , electrical impedance , structural health monitoring , materials science , hot spot (computer programming) , full scale , finite element method , piezoelectricity , wing , acoustics , engineering , composite material , computer science , electrical engineering , optoelectronics , physics , operating system , dielectric , ferroelectricity
SUMMARY In this paper, an integrated impedance and guided wave (IIG) damage detection technique using permanently embedded lead zirconate titanate (PZT) transducers is advanced specifically for online monitoring of critical hot spots within a composite airplane wing structure. A full‐scale airplane wing segment is designed and manufactured to validate the developed online structural health monitoring system. First, structural hot spots, which are vulnerable to damage due to high stress concentration, are determined through finite element analysis during the design stage of the airplane wing segment. Next, the parameters related to PZT design, size, number, cabling, and location are determined, and the PZTs are embedded near the identified hot spots. Then, the applicability of the IIG technique to detection of debonding on a composite skin and bolt loosening on an aluminum fitting lug is experimentally examined under varying temperature and static loading conditions. Finally, the long‐term durability of the PZTs is experimentally investigated using a PZT self‐diagnosis technique over 2 years. Copyright © 2012 John Wiley & Sons, Ltd.