Spacecraft magnetic attitude control using approximating sequence Riccati equations

Author

Rodriquez-Vazquez, Antonio L. ; Martin-Prats, Maria A. ; Bernelli-Zazzera, Franco

Author_Institution

Dept. de Ing. Electron., Univ. de Sevilla, Sevilla, Spain

Volume

51

Issue

4

fYear

2015

Firstpage

3374

Lastpage

3385

Abstract

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.

Keywords

Riccati equations; approximation theory; artificial satellites; attitude control; celestial mechanics; control system synthesis; magnetic actuators; nonlinear control systems; space vehicles; Riccati equation; approximating sequence; low Earth orbit; magnetic actuator; nonlinear control technique; perturbation; satellite; spacecraft magnetic attitude control system; Attitude control; Magnetic hysteresis; Magnetic moments; Magnetomechanical effects; Mathematical model; Satellites; Space vehicles;

fLanguage

English

Journal_Title

Aerospace and Electronic Systems, IEEE Transactions on

Publisher

ieee

ISSN

0018-9251

Type

jour

DOI

10.1109/TAES.2015.130478

Filename

7376261