Abstract: The present invention relates to a release system (1, 2, 3, 4, 5), that includes a segmented structural element (10) comprising: a first segment (10a) designed to be coupled to a first structure, a second segment (10b) designed to be coupled to a second structure, and a solder joint (11) joining respective ends of said first (10a) and second (10b) segments, thus holding down the first and second structures with respect to one another; wherein said solder joint (11) is electromagnetically heatable and includes a solder alloy having a predefined melting temperature.

Abstract: The present invention relates to a release system (1, 2, 3, 4, 5), that includes a segmented structural element (10) comprising: a first segment (10a) designed to be coupled to a first structure, a second segment (10b) designed to be coupled to a second structure, and a solder joint (11) joining respective ends of said first (10a) and second (10b) segments, thus holding down the first and second structures with respect to one another; wherein said solder joint (11) is electromagnetically heatable and includes a solder alloy having a predefined melting temperature.

Abstract: A large deployable reflector for an antenna suitable for being installed on board a satellite and provided with a support structure, a parabolic mirror carried by the support structure and a connection arm for mounting the support structure on the satellite; the support structure being a jointed reticulate structure that is able to assume a compact inoperative stowed configuration and an operative deployed configuration and is composed of ‘n’ elements articulated to form tetrahedrons having respective triangular bases, which are connected to each other at the axial ends of respective first sides and have respective external vertices, which are opposite to said respective first sides and, when the reflector is arranged in the deployed configuration, ideally lie on a cone tangent to the parabolic mirror.

Abstract: A large deployable reflector for an antenna suitable for being installed on board a satellite and provided with a support structure, a parabolic mirror carried by the support structure and a connection arm for mounting the support structure on the satellite; the support structure being a jointed reticulate structure that is able to assume a compact inoperative stowed configuration and an operative deployed configuration and is composed of ‘n’ elements articulated to form tetrahedrons having respective triangular bases, which are connected to each other at the axial ends of respective first sides and have respective external vertices, which are opposite to said respective first sides and, when the reflector is arranged in the deployed configuration, ideally lie on a cone tangent to the parabolic mirror.

Abstract: An actuation system which implements a three-dimensional rectilinear guide with high rectilinear features and it provides stability and stiffness to the moved object by supporting it in a not operating initial phase, particularly suitable to the translation of reflectors for satellite antennas along a predetermined axis in order to obtain the zooming effect thereof on the radiation diagram of the antenna itself.

Abstract: An actuation system which implements a three-dimensional rectilinear guide with high rectilinear features and it provides stability and stiffness to the moved object by supporting it in a not operating initial phase, particularly suitable to the translation of reflectors for satellite antennas along a predetermined axis in order to obtain the zooming effect thereof on the radiation diagram of the antenna itself.

Abstract: A double-reflector microwave antenna of the Gregorian optics family and capable of providing an elliptical beam with a major axis that may be oriented in any desired direction of space by rotation of the sub-reflector about an axis. By adding an additional degree of freedom, that is, an independent translation of the sub-reflector and/or the main reflector along respective axes, a considerable degree of reconfigurability of the shape of the beam may be realized. In particular, the axes of the beam may be widened to vary the ratio between the axes of the elliptical beam for any orientation of the major axis or to obtain a circular beam. The inventive antenna is particularly suitable for use as on board satellites with frequency re-use in an operational environment with one or more simultaneously active beams.