Affiliation:
1. National Key Laboratory of Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics, Nanjing, China
2. Shanghai Institute of Spaceflight Control Technology, Shanghai, China
Abstract
The housing and pre-compressed spring of the integrated piezo longitudinal actuator can protect the piezoelectric stack from shear stress and tensile stress. In this paper, the limitations of this actuator model in existing vibration control projects are pointed out. An electromechanical coupling dynamic model in the transfer matrix form is established for the longitudinal vibration of the integrated piezo longitudinal actuator. The model includes all parameters of the integrated piezo longitudinal actuator: force and velocity at both ends, material and structural parameters, voltage and current, which is suitable for any mechanical and electrical boundary conditions; The transfer matrix method has a simple structure and clear physical definition, which is convenient to be applied to the vibration control system. This model is verified by the finite element software and experiments. In the experimental verification, an electromechanical coupling dynamic experiment system of the integrated piezo longitudinal actuator is established. The accuracy of this model is verified by comparing the frequency domain dynamic response of various parameters in the simulation and experiments. The integrated piezo longitudinal actuator model provides a wide range of possibilities for model-based controller design, active and semi-active control, electric power estimation, and optimal vibration isolation performance estimation.
Funder
National Key LaboratoryFoundation of China
Project Funded by the Priority Academic Program Development of Jiangsu Higher Education Institutions
National Key Laboratory of Rotorcraft Aeromechanic
Subject
Mechanical Engineering,General Materials Science
Cited by
3 articles.
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