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Satellite Attitude Control with Desaturated Rotors

  • H. I. Weber
Conference paper
Part of the COSPAR-IAU-IUTAM book series (IUTAM)

Abstract

An active attitude control system with 3 rotors, for positioning an Earth pointing satellite on a circular orbit is presented. The system is subjected only to the influence of the gravitational moment, and impact disturbances or sinusoidal moment perturbations are considered. A different approach is developed for the control. The desaturation of the rotors is done simultaneously with the control of the whole system. The control law is obtained by means of a suitable optimal linear controller and the result is optimal in the sense of a minimum angle deviation from the equilibrium position.

Keywords

Pitch Angle Roll Angle Roll Axis Uncontrolled System Equilibrium Posi 
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References

  1. 1.
    Weber, H.I.; Shiehlen, W.: Attitude Controllability of a Satellite with Flywheels, J. Spacecraft Rockets 7 n. 4 (1970).Google Scholar
  2. 2.
    Weber, H.I.: Optimale Lageregelung von Satelliten mit Simultan Entdrallten Rotoren. Dr-Ing. thesis, T.U. München, 1971.Google Scholar
  3. 3.
    Weber, H.I.: Otimizaçâo Simultànea do Comportamento Dinàmico Próprio e Perturbado, no Projeto de um Sistema Mecànico Linear Ativo, I Simpósio Brasileiro de Cièncias Mecànicas, Rio de Janeiro, November 1973.Google Scholar
  4. 4.
    Kreindler, E.; Hedrick, J.K.: On Equivalence of Quadratic Loss Functionals. Int. J. Control 11 n. 2 (1970).Google Scholar

Copyright information

© Springer-Verlag, Berlin/Heidelberg 1975

Authors and Affiliations

  • H. I. Weber
    • 1
  1. 1.Departmento de Engenharia MecânicaUniversidade Estadual de CampinasBrazil

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