Attitude control of satellites with de-orbiting solar sails

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.