Sliding mode attitude control for flexible spacecraft

DOI

10.2991/mce-14.2014.122How to use a DOI?

Keywords

flexible spacecraft; error quaternion; sliding mode control; Chattering reduction

Abstract

Aiming at the attitude control problem of flexible spacecraft, an improved sliding mode controller is presented. First of all, the dynamics equation and the kinematics equation described by error quaternion and error angular velocity are studied, which avoid the non-single question of the end attitude. What’s more, according to the mathematical model of flexible spacecraft attitude system, the sliding mode controller is designed by the Lyapunov approach. Finally, in order to reduce the chattering of variable structure control for flexible spacecraft attitude, the smoother “arc tan function” is used to replace the sign function to reduce the chattering. And optimization to reduce the maximum control torque required by the system, which can avoid the vibration of flexible appendages. Simulation results show that the proposed control scheme can effectively achieve the spacecraft attitude control. Besides, On account of this, we can find that it can eliminate the chattering of traditional sliding mode control and keep good robustness.

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  - Qi Wang
AU  - Qin Wei
PY  - 2014/03
DA  - 2014/03
TI  - Sliding mode attitude control for flexible spacecraft
BT  - Proceedings of the 2014 International Conference on Mechatronics, Control and Electronic Engineering
PB  - Atlantis Press
SP  - 545
EP  - 549
SN  - 1951-6851
UR  - https://doi.org/10.2991/mce-14.2014.122
DO  - 10.2991/mce-14.2014.122
ID  - Wang2014/03
ER  -