Numerical and experimental analysis of a piezoelectric flat plate in flapping motion

Harputlu, Özgür
The technology of unmanned aerial vehicles (UAV) has a rapid improvement and their use is increasing day by day for military and civilian missions. Developments in production technology enable the fabrication of micro aerial vehicles. Flapping wing systems have an important place among UAVs. These vehicles are superior to fixed wing aircrafts with their high maneuverability and hover capabilities and they can successfully perform many missions in which the fixed aircrafts are insufficient. Developments in material technology provided the use of smart materials and their integration to the engineering applications. Piezoelectric materials which possess the property of electromechanical coupling can be classified as smart materials and they are widely used in aerial vehicle applications. As an example to this fact, piezoelectric actuators which are exceptional choices to drive flapping wing micro air vehicles may be highlighted. The experiments are performed for different operating signal types and frequencies. The displacement fields obtained from the experimental analysis are used as inputs to the numerical analysis. The numerical simulation is performed using the structural analysis and aerodynamic flow analysis components of ANSYS software. The elastic deformations are inserted into the structural system and linked to the fluid flow system. Flow domain around the beam in flapping is then simulated. An analytical model is established to obtain elastic curve of the bimorph piezoelectric beam under actuation loading. The objective of this study is to analyze piezoelectric flat plate in flapping motion by experimental and numerical methods.


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Citation Formats
Ö. Harputlu, “Numerical and experimental analysis of a piezoelectric flat plate in flapping motion,” M.S. - Master of Science, Middle East Technical University, 2014.