Satellite Attitude Control with Desaturated Rotors

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


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.


Pitch Angle Roll Angle Roll Axis Uncontrolled System Equilibrium Posi 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.


Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.


  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

Personalised recommendations