Abstract
Structural health monitoring using noninvasive methods is one of the major challenges that aerospace manufacturers face in this decade. Our work in this field focuses on the development and the system integration of millimetric piezoelectric sensors/ actuators to generate and measure specific guided waves. The aim of the application is to detect mechanical flaws on complex composite and alloy structures to quantify efficiently the global structures' reliability. The study begins by a physical and analytical analysis of a piezoelectric patch. To preserve the structure's integrity, the transducers are directly pasted onto the surface which leads to a critical issue concerning the interfacing layer. In order to improve the reliability and mitigate the influence of the interfacing layer, the global equations of piezoelectricity are coupled with a load transfer model. Thus we can determine precisely the shear strain developed on the surface of the structure. To exploit the generated signal, a high precision analog charge amplifier coupled to a double T notch filter were designed and scaled. Finally, a novel joined time-frequency analysis based on a wavelet decomposition algorithm is used to extract relevant structures signatures. Finally, this paper provides examples of application on aircraft structure specimens and the feasibility of the system is thus demonstrated.
Highlights
Over the past twenty years, the aerospace industry has registered a high mutation and evolution due to the use of new composite materials
Typically based on non-intrusive local methods, these tools are unsuitable for the inspection of very large structures. They are generally based on the use of compression ultrasonic waves to probe the structure thickness [3] or eddy currents [4] to probe the structure surface
We present how we can generate and sense Lamb waves and the way to exploit them to identify mechanical damages
Summary
Over the past twenty years, the aerospace industry has registered a high mutation and evolution due to the use of new composite materials This constant integration has led to the development of new hybrid aircrafts, lighter and boasting more autonomy than the previous generation. Typically based on non-intrusive local methods, these tools are unsuitable for the inspection of very large structures. They are generally based on the use of compression ultrasonic waves to probe the structure thickness [3] or eddy currents [4] to probe the structure surface. To make the inspection more autonomous, we developed a new methodology based on a smart sensor capable of covering large areas made from different kind of materials. The sensor integration is presented and feasibility experiments are shown for different aircraft part specimens
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