Abstract: The coil according to the invention has normal dimensions, but contains a considerable optical fiber length.It is constituted by a main cylindrical support (12) about which is wound a first part (18) of the optical fiber (16), which is to be unwound by pulling. It is constituted by a first concentric, supplementary cylindrical support (14) placed within the main cylindrical support (12), a second part (20) of the optical fiber (16) being wound around said first supplementary support (14), the inner layer of the first part (18) of the optical fiber (16) being directly connected to an outer layer of the second part (20) of the optical fiber (16).

Abstract: The present invention relates to castings constituted by a metal matrix reinforced by fibers and having outgrowths.Firstly a reinforcing framework is produced, which is incorporated into the fibrous strengthening member, the complete entity being placed in a mould and the metal matrix is cast. The latter penetrates the fibrous strengthening member and the reinforcing framework. The latter is positioned at the location of an outgrowth which, after solidification of the metal matrix, is consequently reinforced.Application to the production of castings having fixing tabs or lobes.

Abstract: The present invention relates to castings constituted by a metal matrix reinforced by fibres and having outgrowths.Firstly, a reinforcing framework is produced, which is incorporated into the fibrous strengthening member, the complete entity being placed in a mould and the metal matrix is cast. The latter penetrates the fibrous strengthening member and the reinforcing framework. The latter is positioned at the location of an outgrowth which, after solidification of the metal matrix, is consequently reinforced.Application to the production of castings having fixing tabs or lobes.

Abstract: A procedure for steering a missile launched at low speed from a tube, with the missile being equipped with a propulsion unit system of the type with a propellant fuel charge. The procedure is characterized by the fact that the above-mentioned propulsion unit system is determined and arranged in such a way that it can simultaneously impart to the missile axial propulsive thrust and maneuver forces for steering by force and that the variation of the position of the center of gravity of the missile on its axis as a function of the burn-up of the propellant charge is such that, when the missile leaves the tube, the center of gravity passes through the line of action of the above-mentioned maneuver forces and that, during its flight, makes it possible for torques to develop which generate aerodynamic angles of attack and which produce maneuver forces which are added to those of steering by force.