A Nonlinear Feedback Control Law for Attitude Control

  • S. Monaco
  • S. Stornelli
Part of the Mathematics and Its Applications book series (MAIA, volume 29)


Nonlinear feedback control laws are proposed for large angle attitude maneuvers of a rigid satellite by using pulsed thrusters and reaction wheels. The kinematic equations in the quaternions parametrization together with the Euler dynamical equations constitute the mathematical model of the system under study. The design of the control law is based on the nonlinear input-output decoupling input-output linearization and linear pole placement theories. Simulation results are discussed.


Large angle attitude control nonlinear attitude control linearization stabilization 


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Copyright information

© D. Reidel Publishing Company 1986

Authors and Affiliations

  • S. Monaco
    • 1
  • S. Stornelli
    • 2
  1. 1.Dipartimento di Informatica e SistemisticaUniversità di Roma “La Sapienza”RomeItaly
  2. 2.Telespazio S.p.A. per le Comunicazioni SpazialiRomeItaly

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