By Topic

Robust Magnetic Attitude Control of Satellites

Sign In

Cookies must be enabled to login.After enabling cookies , please use refresh or reload or ctrl+f5 on the browser for the login options.

Formats Non-Member Member
$33 $13
Learn how you can qualify for the best price for this item!
Become an IEEE Member or Subscribe to
IEEE Xplore for exclusive pricing!
close button

puzzle piece

IEEE membership options for an individual and IEEE Xplore subscriptions for an organization offer the most affordable access to essential journal articles, conference papers, standards, eBooks, and eLearning courses.

Learn more about:

IEEE membership

IEEE Xplore subscriptions

3 Author(s)
Andrea Maria Zanchettin ; Dipartimento di Elettronica, Informazione e Bioingegneria, Politecnico di Milano, 20133 Milan, Italy ; Alberto Calloni ; Marco Lovera

Magnetic torquers are frequently adopted as primary actuators for the attitude control of small satellites in low Earth orbit. Such actuators generate a magnetic dipole which, in turn, leads to control torques thanks to the interaction with the magnetic field of the Earth. The design of attitude control laws based on magnetic torquers is a challenging problem as the torques generated by the coils are instantaneously constrained to lie in the plane orthogonal to the local direction of the geomagnetic field vector, which varies according to the current orbital position of the spacecraft. This implies that the attitude regulation problem is formulated over a time-varying model. In this paper, the design of control laws for magnetically actuated spacecraft is considered and an approach guaranteeing robustness to parametric uncertainty and optimal performance in terms of disturbance attenuation is presented. The proposed method is based on linear time-periodic models and H control theory. The results obtained by applying the proposed approach in a simulation study are also presented and discussed.

Published in:

IEEE/ASME Transactions on Mechatronics  (Volume:18 ,  Issue: 4 )