Conventional magnetic attitude control methodologies require several orbital periods to accomplish the required attitude maneuvers due to the existence of an uncontrollable axis, namely the local Earth’s magnetic field vector. Since in some attitude maneuver missions the elapsed time is of critical importance, those time-consuming controllers are not satisfactory and we need a much faster controller to achieve the maneuver in a fraction of an orbit. In this research the attitude slew maneuver using magnetic torquers is formulated as a time optimal problem and solved through the calculus of variations. The resulted controller is shown to be very fast in forcing the attitude to converge to the desired condition.
Heydari,A. and Dr. Pourtakdoust,S. H. (2008). TIME OPTIMAL SLEW MANEUVER OF MAGNETICALLY ACTUATED LEO SATELLITES. Journal of Aerospace Science and Technology, 5(2), 51-56.
MLA
Heydari,A. , and Dr. Pourtakdoust,S. H. . "TIME OPTIMAL SLEW MANEUVER OF MAGNETICALLY ACTUATED LEO SATELLITES", Journal of Aerospace Science and Technology, 5, 2, 2008, 51-56.
HARVARD
Heydari A., Dr. Pourtakdoust S. H. (2008). 'TIME OPTIMAL SLEW MANEUVER OF MAGNETICALLY ACTUATED LEO SATELLITES', Journal of Aerospace Science and Technology, 5(2), pp. 51-56.
CHICAGO
A. Heydari and S. H. Dr. Pourtakdoust, "TIME OPTIMAL SLEW MANEUVER OF MAGNETICALLY ACTUATED LEO SATELLITES," Journal of Aerospace Science and Technology, 5 2 (2008): 51-56,
VANCOUVER
Heydari A., Dr. Pourtakdoust S. H. TIME OPTIMAL SLEW MANEUVER OF MAGNETICALLY ACTUATED LEO SATELLITES. Journal of Aerospace Science and Technology, 2008; 5(2): 51-56.
