Attitude Control of an Earth Orbiting Solar Sail Satellite to Progressively Change the Selected Orbital Elements

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2015-01-12

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Tekinalp, Ozan

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http://www.space-flight.org/
https://hdl.handle.net/11511/76167

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Attitude control of an earth orbiting solar sail satellite to progressively change the selected orbital element Ataş, Ömer; Tekinalp, Ozan; Department of Aerospace Engineering (2014) Solar sailing is currently under investigation for space propulsion. Radiation pressure from the Sun is utilized to propel the spacecraft. This thesis examines locally optimal steering law to progressively change the selected orbital elements, without considering others, of an Earth centered Keplerian orbit of a cube satellite with solar sail. The proper attitude maneuver mechanization is proposed to harvest highest solar radiation force in the desired direction for such Earth orbiting satellites. The satel...
ATTITUDE CONTROL OF AN EARTH ORBITING SOLAR SAIL SATELLITE TO PROGRESSIVELY CHANGE THE SELECTED ORBITAL ELEMENT Atas, Omer; Tekinalp, Ozan (2015-01-15) Solar sailing where the radiation pressure from Sun is utilized to propel the spacecraft is examined in the context of orbital maneuvers. In this vein a locally optimal steering law to progressively change the selected orbital elements, without considering others, of an Earth centered Keplerian orbit of a cubesat satellite with solar sail is addressed. The proper attitude maneuver mechanization is proposed to harvest highest solar radiation force in the desired direction for such Earth orbiting satellites. ...
ATTITUDE CONTROL OF MULTIPLE RIGID BODY SPACECRAFT WITH FLEXIBLE HINGE JOINTS Akbulut, Burak; Özgören, Mustafa Kemal; Tekinalp, Ozan (2010-02-18) Control algorithm is developed for a satellite with flexible appendages to achieve a good pointing performance. Detailed modeling activity was carried out that consists of sensor and actuator models, disturbances and system dynamics. Common hardware found in the spacecraft such as reaction wheels, gyroscopes, star trackers etc. were included in the model. Furthermore, the Newton-Euler method is employed for the derivation of multi-body equations of motion. Proper metrics such as accuracy, jitter and stabili...
Attitude control of multiple rigid body spacecraft with flexible hinge joints Akbulut, Burak; Özgören, Mustafa Kemal; Department of Mechanical Engineering (2009) Control algorithm is developed for a satellite with flexible appendages to achieve a good pointing performance. Detailed modeling activity was carried out that consists of sensor and actuator models, disturbances and system dynamics. Common hardware found in the spacecraft such as reaction wheels, gyroscopes, star trackers etc. were included in the model. Furthermore, the Newton-Euler method is employed for the derivation of multi-body equations of motion. Evaluation of the pointing accuracy with proper poi...
Attitude Control of Satellites with De-Orbiting Solar Sails Tekinalp, Ozan (2013-06-14) 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.

Citation Formats

O. Tekinalp, “Attitude Control of an Earth Orbiting Solar Sail Satellite to Progressively Change the Selected Orbital Elements,” 2015, Accessed: 00, 2021. [Online]. Available: http://www.space-flight.org/.