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Altitude control of a satellite using a feedback linearization

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Résumé

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.
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Dates et versions

hal-01422733 , version 1 (26-12-2016)

Identifiants

Citer

M Benenia, Hadj Batatia, Felix Mora-Camino, Malek Benslama. Altitude control of a satellite using a feedback linearization. Control and Automation Conference 2013: Uniting Problems and Solutions, Jun 2013, Glasgow, United Kingdom. pp.ISBN: 978-1-84919-710-6, ⟨10.1049/cp.2013.0018⟩. ⟨hal-01422733⟩
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