Abstract
Energy Harvesting is a pro mising solution for powering Structural Health Monitoring (SHM ) systems since various mechanical energy sources are generated by aircraft. Today, the main technique to harvest energy consists of using a specific conversion device to provide power to the SHM system. In this paper however, a novel technique to obtain a self-powered SHM system for aeronautical structures is proposed. This SHM system aims to have a double functionality: it will carry out classical SHM tasks using piezoelectric transducers bonded onto the aircraft structure and will also be fully autonomous since the same transducers will convert the mechanical v ibrations of the structure into electrical power. Using a bonded piezoelectric t ransducer to harvest energy will also bring wideband frequency energy harvesting capability. Th is autonomous system using a unique transducer being particularly innovative, the objective of this paper is to provide a complete Bond Graph model of the energy harvesting process in order to allow the optimisation of its performances. This approach is well-suited to monitor the power and energy transfer carried out during the process since it takes into account the interaction between mu ltiphysics systems, here the electrical and mechanical domains in terms of power and energy variables. Consequently, each part of the energy harvesting, i.e. the mechanical v ibration of the host structure, the vibration within the SHM energy harvester volume, the piezoelectric electro mechanical conversion and the terminal electric load have been modelled analytically using this Bond Graph approach. Then, each submodel has been verified with a baseline Fin ite Element model. Good agreements have been found and it has been possible to carry out an estimat ion of the power harvested by the SHM energy harvester for a given mechanical excitation using this innovative complete analytical Bond Graph model.
Highlights
Structural Health Monitoring (SHM ) systems have become a part of new avionic systems which will form future aircraft
The Bond Graph submodels presented in the previous parts are computed using the software 20-sim 4.1
No difference in terms of displacement around the SHM energy harvester area has been noticed. This confirms that the presence of the SHM energy harvester does not modify significantly the d isplacement field o f the structure at these low frequencies
Summary
Structural Health Monitoring (SHM ) systems have become a part of new avionic systems which will form future aircraft. Their objectives are to detect and locate damages occurring within the aircraft structure. They have to be able to characterize the nature and the gravity of the damage as well as to estimate the remain ing lifespan of the structure. The place of such systems is rap idly evolv ing. A technological gap must be overtaken as a major objective is to use them on production line and to implement them on-board aircraft
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