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Output feedback control of satellite attitude using a single vector measurement

Safaei, F ; Sharif University of Technology | 2012

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  1. Type of Document: Article
  2. DOI: 10.1109/CDC.2012.6426764
  3. Publisher: 2012
  4. Abstract:
  5. The existing methods in attitude control of satellites are based on employing the estimate of satellite attitude which is usually generated by using multiple vector measurements. In this paper we propose an output feedback control law that directly uses a single vector measurement and gyro, and without any need for estimating the satellite attitude. The output feedback gain is computed by solving a generalized Riccati time varying differential equation. We assume the moment-of-inertia matrix of satellite is unknown. The controller guarantees asymptotic convergence of the attitude to its desired value. A realistic simulation is presented where a magnetometer is used to provide the single vector measurement
  6. Keywords:
  7. Asymptotic convergence ; Multiple vectors ; Output feedback ; Output feedback controls ; Realistic simulation ; Satellite attitude ; Single vectors ; Time-varying differential equations ; Attitude control ; Differential equations ; Feedback control ; Navigation ; Vectors
  8. Source: Proceedings of the IEEE Conference on Decision and Control, 10 December 2012 through 13 December 2012, Maui, HI ; 2012 , Pages 490-495 ; 01912216 (ISSN)
  9. URL: http://ieeexplore.ieee.org/xpl/articleDetails.jsp?arnumber=6426764