Damage Detection in Thin Plates and Aerospace Structures with the                 Electro-Mechanical Impedance Method

Giurgiutiu, Victor; Zagrai, Andrei

doi:10.1177/1475921705049752

Cited by 202 publications

(137 citation statements)

References 15 publications

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“…Recent research has shown that the utilization of electro-mechanical (E/M) impedance methods allow for the direct identification of structural dynamics [9][10][11] . The mechanism is to couple small-size piezoelectric active sensors, like lead zirconate titanate, with the material structure.…”

Section: Introductionmentioning

confidence: 99%

Early damage detection in epoxy matrix using cyclobutane-based polymers

Zou

Liu

Shan

et al. 2014

Smart Mater. Struct.

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Identification of early damage in polymer composites is of great importance. We have incorporated cyclobutane-containing crosslinked polymers into an epoxy matrix, studied the effect on thermal and mechanical properties and more importantly, demonstrated early damage detection through mechanically induced fluorescence generation. Two cinnamate derivatives, 1,1,1-tris(cinnamoyloxymethyl) ethane (TCE) and poly(vinyl cinnamate) (PVCi), were photoirradiated to produce cyclobutane-containing polymer, respectively. The effects on the thermal properties and mechanical properties with the addition of cyclobutane-containing polymer into epoxy matrix were investigated. The emergence of cracks was detected by fluorescence at a strain level right beyond the yield point of the polymer blends and the fluorescence intensified with accumulation of strain. Overall, the results show that the damages can be detected through fluorescence generation along the crack propagation.

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Section: Introductionmentioning

confidence: 99%

Early damage detection in epoxy matrix using cyclobutane-based polymers

Zou

Liu

Shan

et al. 2014

Smart Mater. Struct.

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“…The most common metrics for damage detection using the EM signature are based on the analysis of the resistance R( f ) [1,3,27,28]. Let R ref ( f ) be the resistance in the reference healthy case and R unk ( f ) the resistance in the current unknown state.…”

Section: Electromechanical (Em) Signatures and Associated Metricsmentioning

confidence: 99%

Simultaneous Influence of Static Load and Temperature on the Electromechanical Signature of Piezoelectric Elements Bonded to Composite Aeronautic Structures

Rébillat

Guskov

Balmès

et al. 2016

Journal of Vibration and Acoustics

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Electromechanical (EM) signature techniques have raised a huge interest in the structural health monitoring community. These methods aim at assessing structural damages and sensors degradation by analyzing the EM responses of piezoelectric components bonded to aeronautic structures. These structures are subjected simultaneously to static loads and temperature variations that affect the metrics commonly used for damage detection and sensor diagnostics. However, the effects of load and temperature on these metrics have mostly been addressed separately. This paper presents experimentations conducted to investigate the simultaneous influence of static load and temperature on these metrics for two kinds of piezoelectric elements (PZT: lead zirconate titanate, and MFC: macro fiber composite) bonded on sandwich composite materials, for the full range of real-life conditions encountered in aeronautics. Results obtained indicate that both factors affect the metrics in a coupled manner in particular due to the variations of the mechanical properties of the bonding layer when crossing its glass transition temperature. Furthermore, both piezoelectric elements globally behave similarly when subjected to temperature variations and static loads. Simultaneous accounting of both temperature and static load is thus needed in practice in order to design reliable structural health monitoring systems based on these metrics. IntroductionIn the past decades, electromechanical (EM) signature techniques have gained importance in the structural health monitoring community [1][2][3][4]. The EM signature technique consists of measuring the EM signature (real or imaginary part of the impedance or admittance as a function of frequency) of a piezoelectric sensor which is mounted on a host structure in order to pinpoint incipient damages that may appear on the structure (damage detection) or to detect any defect on the sensor itself (sensor diagnostics). In an aeronautic context, temperature variations as well as static loads induced on the structure during a flight can both be very important. Experiments have been carried out that focused on temperature [5][6][7][8][9][10][11][12][13][14][15][16][17] or static loads [18][19][20][21][22], but rarely simultaneously [23][24][25][26]. Regarding temperature effects, it has been observed that the effect of temperature changes consists of a shift of the piezoelectric resonance frequencies. It has also been shown that higher temperature increases the apparent capacitive value of the bonded piezoelectric patch. Regarding the effect of static loads, it has been shown that the magnitude of the peaks and valleys of the EM signature decreases with an increase of applied loads and that natural frequencies shift proportionally with the applied load. Regarding the influence of both temperature and static loads, a strategy has been designed by Lim et al. [23] to compensate for their effects and Zhu et al. [24,25] and Xu et al. [26] analyzed experimentally both effects, but in a separate manner.This...

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“…In the case of stack transducers, normal stress is applied to the structure while the patch-type transducers apply shear stress [2]. A successful method for the analysis and detection of mechanical damages using piezotransducers is the electromechanical impedance method (EMI) [14]. The EMI method analyzes and compares the mechanical impedance value of the structure to establish if damages are present or not [15].…”

Section: Introductionmentioning

confidence: 99%

Development of a Flexible Lead-Free Piezoelectric Transducer for Health Monitoring in the Space Environment

et al. 2015

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Abstract:In this work we report on the fabrication process for the development of a flexible piezopolymeric transducer for health monitoring applications, based on lead-free, piezoelectric zinc oxide (ZnO) thin films. All the selected materials are compatible with the space environment and were deposited by the RF magnetron sputtering technique at room temperature, in view of preserving the total flexibility of the structures, which is an important requirement to guarantee coupling with cylindrical fuel tanks whose integrity we want to monitor. The overall transducer architecture was made of a c-axis-oriented ZnO thin film coupled to a pair of flexible Polyimide foils coated with gold (Au) electrodes. The fabrication process started with the deposition of the bottom electrode on Polyimide foils. The ZnO thin film and the top electrode were then deposited onto the Au/Polyimide substrates. Both the electrodes and ZnO layer were properly patterned by wet-chemical etching and optical lithography. The assembly of the final structure was then obtained by gluing the upper and lower Polyimide foils with an epoxy resin capable of guaranteeing low outgassing levels, as well as adequate thermal and electrical insulation of the transducers. The piezoelectric behavior of the prototypes was confirmed and evaluated by measuring the mechanical displacement induced from the application of an external voltage.

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Damage Detection in Thin Plates and Aerospace Structures with the Electro-Mechanical Impedance Method

Cited by 202 publications

References 15 publications

Early damage detection in epoxy matrix using cyclobutane-based polymers

Early damage detection in epoxy matrix using cyclobutane-based polymers

Simultaneous Influence of Static Load and Temperature on the Electromechanical Signature of Piezoelectric Elements Bonded to Composite Aeronautic Structures

Development of a Flexible Lead-Free Piezoelectric Transducer for Health Monitoring in the Space Environment

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