Altitude control of a satellite using a feedback linearization
| Autor: | M. Benenia, F. Mora Camino, M. Benslama, H. Batatia |
|---|---|
| Přispěvatelé: | University of Constantine, Traitement et Compréhension d’Images (IRIT-TCI), Institut de recherche en informatique de Toulouse (IRIT), Université Toulouse 1 Capitole (UT1), Université Fédérale Toulouse Midi-Pyrénées-Université Fédérale Toulouse Midi-Pyrénées-Université Toulouse - Jean Jaurès (UT2J)-Université Toulouse III - Paul Sabatier (UT3), Université Fédérale Toulouse Midi-Pyrénées-Centre National de la Recherche Scientifique (CNRS)-Institut National Polytechnique (Toulouse) (Toulouse INP), Université Fédérale Toulouse Midi-Pyrénées-Université Toulouse 1 Capitole (UT1), Université Fédérale Toulouse Midi-Pyrénées, Ecole Nationale de l'Aviation Civile (ENAC), Laboratoire électromagnetisme et télécommunications Université de Constantine Algérie (LET), Université de Constantine |
| Jazyk: | angličtina |
| Rok vydání: | 2013 |
| Předmět: |
feedback linearization
quaternion Computer science sliding mode control Control engineering Function (mathematics) Nonlinear control Sliding mode control [SPI.AUTO]Engineering Sciences [physics]/Automatic Attitude control Nonlinear system spacecraft attitude control Linearization Control theory Feedback linearization Quaternion |
| Zdroj: | Control and Automation Conference 2013: Uniting Problems and Solutions 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⟩ |
| DOI: | 10.1049/cp.2013.0018⟩ |
| Popis: | International audience; 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. |
| Databáze: | OpenAIRE |
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