Satellite Attitude Control with Actuator Failure

DOI

10.2991/emim-17.2017.67How to use a DOI?

Keywords

Observer; Backstepping; Actuator fault; Attitude stabilization control

Abstract

A method of attitude stabilization control, based on observer design is proposed for an on-orbiting spacecraft in the presence of partial loss of actuator effectiveness, external disturbance and actuator control input saturation problem. In this approach, observer is employed to estimate the value of actuator fault, and a Backstepping attitude controller is then designed to achieve fault tolerant control and external disturbance rejection. The Lyapunov stability analysis shows that the closed-loop attitude system is guaranteed to be almost asymptotically stable. The simulation results show the effectiveness of the derived control law.

Copyright

© 2017, 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  - Haitao Meng
AU  - Aihua Zhang
AU  - Xing Huo
AU  - Zhiyong She
PY  - 2017/04
DA  - 2017/04
TI  - Satellite Attitude Control with Actuator Failure
BT  - Proceedings of the 7th International Conference on Education, Management, Information and Mechanical Engineering (EMIM 2017)
PB  - Atlantis Press
SP  - 323
EP  - 329
SN  - 2352-538X
UR  - https://doi.org/10.2991/emim-17.2017.67
DO  - 10.2991/emim-17.2017.67
ID  - Meng2017/04
ER  -