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Development of piezoelectric actuated mechanism for flapping wing micro-aerial vehicle applications

By K. Lal Kummari, Daochun Li, Shijun J. Guo and Zhaorong Huang

Abstract

A piezoelectric actuated two-bar two-flexure motion amplification mechanism for flapping wing micro-aerial vehicle application has been investigated. f(r)*A as an optimisation criterion has been introduced where f(r) is its fundamental resonant frequency of the system and A the vibration amplitude at the wing tip, or the free tip deflection at quasi-static operation. This criterion can be used to obtain the best piezoelectric actuation mechanism with the best energy transmission coefficient for flapping wing micro-aerial vehicle applications, and is a measurable quantity therefore can be compared with experimental results. A simplified beam model has been developed to calculate the fundamental resonant frequency for the full system consisted of piezoelectric actuator, motion amplification mechanism and the attached wing and the calculated values were compared with the measured results. A clear trend of the criteria f(r)*A varying with the two-flexure dimension, stiffness and setting angle have been obtained from the measured data and also the predicted results as a guideline for optimal design of the system

Topics: Piezoelectric materials Actuators Micro-aerial vehicle Flapping wing Motion amplification mechanism Actuator criterion air vehicles bending actuators efficiency design
Publisher: Maney Publishing
Year: 2010
DOI identifier: 10.1179/174367509X12447975734357
OAI identifier: oai:dspace.lib.cranfield.ac.uk:1826/5225
Provided by: Cranfield CERES
Journal:

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