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.
Attitude control of satellites with de-orbiting solar sails
01.06.2013
676130 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
DEORBITSAIL: De-orbiting of satellites using solar sails
IEEE | 2011
|Attitude control of orbiting satellites at high eccentricity
Engineering Index Backfile | 1962
|Attitude Control Methodology for Large Solar Sails
Online Contents | 2015
|Attitude Dynamics of Satellites Orbiting an Asteroid
Online Contents | 2006
|Attitude Dynamics of Satellites Orbiting an Asteroid
British Library Conference Proceedings | 2006
|