Altitude control of a satellite using a feedback linearization

M. Benenia, H. Batatia, F. Mora Camino, M. Benslama

Research output: Chapter in Book/Report/Conference proceedingConference contribution

2 Citations (Scopus)

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.

Original languageEnglish
Title of host publicationIET Conference on Control and Automation 2013
Subtitle of host publicationUniting Problems and Solutions
PublisherInstitution of Engineering and Technology
ISBN (Electronic)9781849197106
DOIs
Publication statusPublished - 2013
Event2013 IET Conference on Control and Automation: Uniting Problems and Solutions - Birmingham, United Kingdom
Duration: 4 Jun 20135 Jun 2013

Conference

Conference2013 IET Conference on Control and Automation: Uniting Problems and Solutions
CountryUnited Kingdom
CityBirmingham
Period4/06/135/06/13

Keywords

  • Feedback linearization
  • Quaternion
  • Sliding mode control
  • Spacecraft attitude control

ASJC Scopus subject areas

  • Control and Optimization
  • Modelling and Simulation

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