Patent ID: 8550407
Filing Date: 2013-10-08
Classification: B64G

Abstract:
1. A deployable structure with which a spacecraft may be equipped, comprising: a set of primary panels, a set of secondary panels, each primary and secondary panel including a substantially plane front surface, primary articulation systems, each primary articulation system enabling a primary panel to be caused to pivot relative to another primary panel about a primary axis, the primary axes being substantially parallel to the front surfaces of the primary panels, and secondary articulation systems, each secondary articulation system being associated with a secondary panel and enabling said secondary panel to be caused to pivot relative to a primary panel or a secondary panel about a secondary axis substantially parallel to the front surfaces of said panels, the deployable structure being configured in such a manner that, in a deployed configuration, the front surfaces of the primary and secondary panels form a substantially continuous overall surface, the deployable structure further including locking devices at the periphery of the overall surface, each locking device being configured to eliminate at least one degree of freedom between two adjacent secondary panels that are not articulated to each other by a secondary articulation system, in such manner as to stiffen the reflector in the deployed configuration.