The aim is to develop a conceptual satellite that combines the scalability and stability of a spinning sail with the agility of a 3-axis stabilized sail. A tri-spin satellite is proposed making use of a spinning sail and a momentum countering system (MCS) rotating relative to the satellite body. The MCS reduces the angular momentum bias increasing the maneuverability of the satellite. Induced oscillations in the non-rigid elements due to attitude changes are investigated. A complete attitude determination and control system (ADCS) for such a satellite in an earth-centered orbit is proposed and simulated. The simulation reveals that the tri-spin concept is viable.
The Attitude Control of a Tri-Spin Solar Sail Satellite
Springer Praxis Books (formerly: Springer-Praxis Series)
2014-02-04
15 pages
Article/Chapter (Book)
Electronic Resource
English
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