| 摘要 |
The deployment mechanism acts on each of the panels 14, 15 of the appendage 12, in such a way that the distance separating the centre of gravity of this appendage from the axis of rotation O of the space vehicle 10 is permanently increasing, from the initial position in which the panels are folded up to the final complete deployment position of these panels. To this end, cables 24, 26 are used which wind round pulleys 20a, 22a; 20b, 22b in such a way that their winding radius around the articulation axis 16 of the intermediate panel 14 is permanently increasing and that their winding radius around the articulation axis of the outer panel 15 is permanently decreasing from the said initial position out to the said final position, according to an analytically-defined geometric law. <IMAGE>
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