Altitude control of a satellite using a feedback linearization
- Benenia, M
- Batatia, Hadj
- Mora-Camino, Felix
- Benslama, Malek
Publication date
June 2013
DOI Publisher
Institution of Engineering and Technology (IET)Abstract
International audienceThis study is dedicated to the problem of non linear attitude control for a rigid large angle maneuver satellite. The non linear control method is based upon the linearization of the input-output of the system, also called feedback linearization, via state feedback. The output function is chosen amongst the attitude quaternion parameters
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