| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 9823235 | Acta Astronautica | 2005 | 5 Pages |
Abstract
The proposed system is implemented on the IRECIN, a modular nano-satellite weighing less than 1.5Â kg, constituted by 16 external sides with surface-mounted solar cells and three internal Al plates, kept together by four steel bars. Lithium-ion batteries are added for eclipse operations. Attitude is determined by two three-axis magnetometers and the solar panel data. Control is provided by an active magnetic control system. The spacecraft will be spin-stabilized with the spin-axis normal to the orbit.
Related Topics
Physical Sciences and Engineering
Engineering
Aerospace Engineering
Authors
M. Ferrante, M. Povia, L. Di Ciolo, A. Ortenzi, M. Petrozzi,