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3 Fatigue of Aircraft Structures

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Composite Aerospace Structure Monitoring with use of Integrated Sensors

Dragan K., Dziendzikowski M., Kurnyta A., Salacinski M., Klysz S., Leski A.

Fatigue of Aircraft Structures

2015

Iss. 7

12--17

One major challenge confronting the aerospace industry today is to develop a reliable and universal Structural Health Monitoring (SHM) system allowing for direct aircraft inspections and maintenance costs reduction. SHM based on guided Lamb waves is an approach capable of addressing this issue and satisfying all the associated requirements. This paper presents an approach to monitoring damage growth in composite aerospace structures and early damage detection. The main component of the system is a piezoelectric transducers (PZT) network integrated with composites. This work describes sensors’ integration with the structure. In particular, some issues concerning the mathematical algorithms giving information about damage from the impact damage presence and its growth are discussed.

An Approach to Structural Health Monitoring of Composite Structures Based on Embedded PZT Transducers

Dziendzikowski M., Dragan K., Kurnyta A., Kornas Ł., Latoszek A., Zabłocka M., Kłysz S., Leski A., Chalimoniuk M., Giewoń J.

Fatigue of Aircraft Structures

2014

Iss. 6

113--118

One approach to developing a system of continues automated monitoring of structural health is to use elastic waves excited in a given medium by a piezoelectric transducers network. Depending on their source and the geometry of the structure under consideration elastic waves can propagate over a significant distance. They are also sensitive to local structure discontinuities and deformations providing a tool for detecting local damage in large aerospace structures. This paper investigates the issue of Barely Visible Impact Damages (BVIDs) detection in composite materials. The model description and the results of impact tests verifying damage detection capabilities of the proposed signal characteristics are presented in the paper.

An On-Line Multiway Approach to In-Situ NDI Looking at the PZL-130TCII

Dragan K., Dziendzikowski M., Kurnyta A., Latoszek A., Leski A., Kłysz A.

Fatigue of Aircraft Structures

2013

Iss. 5

5--11

Providing a reliable and universal Structural Health Monitoring (SHM) system allowing for remote aircraft inspections and a reduction of maintenance costs is a major challenge confronting the aerospace industry today. SHM based on guided Lamb waves is one of the approaches capable of addressing the issue while satisfying all the associated requirements. This paper presents a holistic approach to the continuous real time damage growth monitoring and early damage detection in aircraft structure. The main component of the system is a piezoelectric transducers (PZT) network. It is complemented by other SHM methods: Comparative Vacuum Monitoring (CVMTM) and Resistance Gauges at selected aircraft hot spots. The paper offers the description of damage detection capabilities including the analysis of data collected from the PZL-130 Orlik aircraft full-scale fatigue test.