Attitude control mechanization to de-orbit satellites using solar sails

Date

2015-01-01

Author

Tekinalp, Ozan
Atas, Omer

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Utilization of solar sails for the de-orbiting of satellites is investigated. The proper attitude maneuver mechanization is proposed to harvest highest solar drag for Earth orbiting satellites. The maneuver is realized using a to-go quaternion calculated from body fixed frame measurements. The success of the attitude control during the continuous, as well as abrupt maneuvers is shown through simulations. The reduction in semi major axis due to the solar drag is shown to be similar in orbits with different inclinations.

URI

https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=84968779754&origin=inward
https://hdl.handle.net/11511/107458

Conference Name

2nd International Academy of Astronautics Conference on Dynamics and Control of Space Systems, DyCoSS 2014

Collections

Department of Aerospace Engineering, Conference / Seminar

Citation Formats

O. Tekinalp and O. Atas, “Attitude control mechanization to de-orbit satellites using solar sails,” Rome, İtalya, 2015, vol. 153, Accessed: 00, 2023. [Online]. Available: https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=84968779754&origin=inward.