Dynamic Modeling and Vibration Control for Spacecraft’s Solar Array

DOI

10.2991/icmce-14.2014.56How to use a DOI?

Keywords

Active Vibration Control, Solar Array, Piezoelectric Actuators.

Abstract

Dynamic modeling and active vibration control for a typical flexible solar array of spacecraft by using piezoelectric actuators is discussed. It is different from the simplified beam or plate model for the solar array in the literate, a coupled dynamic model of the solar array with piezoelectric actuators is developed firstly. Especially, a four-node rectangular piezoelectric plate element is presented to discretize the smart solar array. Secondly, a LQR controller is designed to control the vibration of the solar array. Numerical simulation shows that the vibration of solar array could be suppressed efficiently by using piezoelectric actuators.

Copyright

© 2014, the Authors. Published by Atlantis Press.

Open Access

This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).

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TY  - CONF
AU  - Jian-Ping JIANG
AU  - Rui XU
PY  - 2014/12
DA  - 2014/12
TI  - Dynamic Modeling and Vibration Control for Spacecraft’s Solar Array
BT  - Proceedings of the 2014 International Conference on Mechanics and Civil Engineering
PB  - Atlantis Press
SP  - 320
EP  - 325
SN  - 2352-5401
UR  - https://doi.org/10.2991/icmce-14.2014.56
DO  - 10.2991/icmce-14.2014.56
ID  - JIANG2014/12
ER  -