This paper presents the results of a spacecraft attitude control system based on magnetic actuators designed for low Earth orbits. The control system is designed by using a nonlinear control technique based on the approximating sequence of Riccati equations. The behavior of the satellite is discussed under perturbations and model uncertainties. Simulation results are presented when the control system is able to guide the spacecraft to the desired attitude in a variety of different conditions.
Spacecraft magnetic attitude control using approximating sequence Riccati equations
IEEE Transactions on Aerospace and Electronic Systems ; 51 , 4 ; 3374-3385
01.10.2015
3800933 byte
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Optimized State-Dependent Riccati Equation Method for Spacecraft Attitude Estimation and Control
British Library Conference Proceedings | 2012
|Optimized State-Dependent Riccati Equation Method for Spacecraft Attitude Estimation and Control
British Library Conference Proceedings | 2012
|On Spacecraft Magnetic Attitude Control
AIAA | 2018
|