期刊
STRUCTURAL CONTROL & HEALTH MONITORING
卷 19, 期 7, 页码 592-604出版社
JOHN WILEY & SONS LTD
DOI: 10.1002/stc.1493
关键词
structural health monitoring; hot spot monitoring; composite airplane wing; full-scale test; integrated impedance and guided wave (IIG) technique; temperature and loading variations
资金
- Agency for Defense Development [UC080019JD]
- National Research Laboratory Program [2010-0017456]
- Nuclear Research & Development Program of National Research Foundation of Korea [2010-0020423]
- National Research Foundation of Korea [2010-0017456, 2009-0083489] Funding Source: Korea Institute of Science & Technology Information (KISTI), National Science & Technology Information Service (NTIS)
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.
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