Airplane hot spot monitoring using integrated impedance and guided wave measurements

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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 (C) 2012 John Wiley & Sons, Ltd.
Publisher
WILEY-BLACKWELL
Issue Date
2012-11
Language
English
Article Type
Article
Citation

STRUCTURAL CONTROL & HEALTH MONITORING, v.19, no.7, pp.592 - 604

ISSN
1545-2263
DOI
10.1002/stc.1493
URI
http://hdl.handle.net/10203/102838
Appears in Collection
CE-Journal Papers(저널논문)
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