ATTITUDE CONTROL OF AN EARTH ORBITING SOLAR SAIL SATELLITE TO PROGRESSIVELY CHANGE THE SELECTED ORBITAL ELEMENT

Date

2015-01-15

Author

Atas, Omer
Tekinalp, Ozan

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This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

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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. The satellite attitude control is realized using quaternion error feedback control. The effectiveness of the approach to progressively changing the orbital parameters is demonstrated.

Subject Keywords

Aerospace, Engineering,

URI

https://hdl.handle.net/11511/54433

Conference Name

25th American-Astronautical-Society (AAS)/American-Institute-of-Aeronautics-and-Astronautics (AIAA) Space Flight Mechanics Meeting, (11 - 15 Ocak 2015)

Collections

Department of Aerospace Engineering, Conference / Seminar

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Citation Formats

O. Atas and O. Tekinalp, “ATTITUDE CONTROL OF AN EARTH ORBITING SOLAR SAIL SATELLITE TO PROGRESSIVELY CHANGE THE SELECTED ORBITAL ELEMENT,” Virginia, Amerika Birleşik Devletleri, 2015, vol. 155, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/54433.