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Attitude Control of Satellites with De-Orbiting Solar Sails
Date
2013-06-14
Author
Tekinalp, Ozan
Metadata
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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.
Subject Keywords
Solar sail
,
Orbit decay
,
Locally optimal steering law
URI
https://hdl.handle.net/11511/54985
Collections
Department of Aerospace Engineering, Conference / Seminar
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O. Tekinalp, “Attitude Control of Satellites with De-Orbiting Solar Sails,” 2013, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/54985.
