MATEC Web Conf.
Volume 158, 2018VI International Forum for Young Scientists “Space Engineering 2018”
|Number of page(s)||4|
|Published online||19 March 2018|
Design issues of the piezo motor for the spacecraft reflector control system
National Research Tomsk State University, Research Institute of Applied Mathematics and Mechanics, 634050 Tomsk, Russia
2 Academician M.F. Reshetnev Information Satellite Systems, 662972 Zheleznogorsk, Krasnoyarsk region, Russia
* Corresponding author: firstname.lastname@example.org
Creation of large-size reflectors for spacecrafts is a topical issue for the space industry. The accuracy of the reflecting surface form and the structure weight are the main criteria for the reflector design. The accuracy of the reflecting surface form during a long-term operation is provided by adjustment when using piezoelectric motors in the reflector design. These motors have small weight-size parameters and can reach great torque values. The piezo motor is a distributed mechanical-acoustic oscillation system. Mechanical-acoustic oscillations are generated in the piezo motor by a PZT-stack and transmitted to an oscillator element, and then from the oscillator element to a load action element. At high frequencies, when dimensions of the oscillator are proportionate to the wavelength, the energy is transmitted by means of acoustic waves. In this case, mechanical waves practically are not involved in the energy transmission process. This thesis shows a method for selecting the material of a mechanical-acoustic oscillation system according to the efficiency of the acoustic energy transmission via a piezoelectric layered structure.
© The Authors, published by EDP Sciences, 2018
This is an Open Access article distributed under the terms of the Creative Commons Attribution License 4.0, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. (http://creativecommons.org/licenses/by/4.0/).
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