Title :
Attitude control of satellites with de-orbiting solar sails
Author :
Tekinalp, Ozan ; Atas, Omer
Author_Institution :
Aerosp. Eng. Dept., Middle East Tech. Univ., Ankara, Turkey
Abstract :
Utilization of solar sails for the de-orbiting of satellites is investigated. The satellite orbit is assumed to be equatorial. Proper attitude maneuver is prescribed to utilize highest solar drag from the sun. The maneuver is realized using a quaternion feedback algorithm. The success of the attitude control during the continuous and abrupt maneuvers is shown through simulations. The reduction in semi major axis due to solar drag is also demonstrated.
Keywords :
Sun; artificial satellites; attitude control; feedback; motion control; abrupt maneuvers; attitude control; attitude maneuver; continuous maneuvers; equatorial satellites deorbiting; quaternion feedback algorithm; solar drag; solar sails utilization; sun; Attitude control; Drag; Equations; Force; Mathematical model; Orbits; Satellites; locally optimal steering law; orbit decay; solar sail;
Conference_Titel :
Recent Advances in Space Technologies (RAST), 2013 6th International Conference on
Conference_Location :
Istanbul
Print_ISBN :
978-1-4673-6395-2
DOI :
10.1109/RAST.2013.6581230
