Title :
Altitude control of a satellite using a feedback linearization
Author :
Benenia, M. ; Batatia, H. ; Camino, F. Mora ; Benslama, M.
Author_Institution :
Electromagn. & Telecommun. Lab., Constantine Univ., Constantine, Algeria
Abstract :
This 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.
Keywords :
artificial satellites; attitude control; state feedback; altitude control; attitude quaternion parameters; feedback linearization; nonlinear attitude control; rigid large angle maneuver satellite; state feedback; feedback linearization; quaternion; sliding mode control; spacecraft attitude control;
Conference_Titel :
Control and Automation 2013: Uniting Problems and Solutions, IET Conference on
Conference_Location :
Birmingham
Electronic_ISBN :
978-1-84919-710-6
DOI :
10.1049/cp.2013.0018
