Health Monitoring of the Aircraft Structure during a Full Scale Fatigue Test with Use of an Active Piezoelectric Sensor Network

Michal Dziendzikowski; Krzysztof Dragan; Artur Kurnyta; Sylwester Klysz; Andrzej Leski

doi:10.4028/www.scientific.net/SSP.220-221.328

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HomeSolid State PhenomenaSolid State Phenomena Vols. 220-221Health Monitoring of the Aircraft Structure during...

Health Monitoring of the Aircraft Structure during a Full Scale Fatigue Test with Use of an Active Piezoelectric Sensor Network

Abstract:

The paper presents an approach to develop a system for fatigue crack growth monitoring and early damage detection in the PZL – 130 ORLIK TC II turbo-prop military trainer aircraft structure. The system functioning is based on elastic waves propagation excited in the structure by piezoelectric PZT transducers. In the paper, a built block approach for the system design, signal processing as well as damage detection is presented. Description of damage detection capabilities are delivered in the paper and some issues concerning the proposed signal processing methods and their application to crack growth estimation models are discussed. Selected preliminary results obtained during the Full Scale Fatigue Test thus far are also presented.

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Periodical:

Solid State Phenomena (Volumes 220-221)

Pages:

328-332

DOI:

https://doi.org/10.4028/www.scientific.net/SSP.220-221.328

Citation:

Cite this paper

Online since:

January 2015

Authors:

Michal Dziendzikowski, Krzysztof Dragan, Artur Kurnyta, Sylwester Klysz, Andrzej Leski

Keywords:

Fatigue Cracks Detection, Piezoelectric Sensors Networks, Structural Health Monitoring (SHM)

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References

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