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ORBIT TRANSFER OF AN EARTH ORBITING SOLAR SAIL CUBESAT
Date
2017-02-09
Author
Atas, Omer
Tekinalp, Ozan
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Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License
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Propelling a spacecraft by using solar radiation pressure is examined in the context of orbital maneuvers. A locally optimal steering law to progressively change number of selected orbital elements together is addressed. An Earth centered cubesat satellite with solar sail is used as an example. The proper attitude maneuver mechanization is proposed to harvest highest solar radiation force in the desired direction for Earth orbiting satellites. The satellite attitude control is realized using to-go quaternion feedback control. And the effectiveness of the approach to progressively changing the orbital parameters is demonstrated.
URI
https://hdl.handle.net/11511/53547
Collections
Department of Aerospace Engineering, Conference / Seminar
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O. Atas and O. Tekinalp, “ORBIT TRANSFER OF AN EARTH ORBITING SOLAR SAIL CUBESAT,” 2017, vol. 160, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/53547.