Abstract: A ram jet engine including a combustion chamber ending in a gas injection nozzle, a cruising propulsion unit fee ding liquid propellant into the combustion chamber, and at least one air duct for feeding air intended for combustion of the fuel in the combustion chamber. A rigid tubular element is incorporated into the ramjet engine, with an interior volume of the rigid tubular element being divided into two spaces by an intermediate transverse partition. One of the spaces houses the cruising propulsion unit while the other space houses the combustion chamber. Passages are cut into the intermediate transverse partition to allow feeding of liquid fuel into the combustion chamber, and the air duct is mounted on the tubular element to feed the combustion air through the tubular wall of the tubular element.

Abstract: A machine, for the construction of a braid (11), that includes a set of identical multiindented wheels (2), which are mounted on a fixed support (1) and driven in rotation to cause the circulation of spindles (6) carrying spools (7) of braiding threads (8). The multiindented wheels are disposed in parallel and equidistant lines (L—L). In the set of multiindented wheels: the multindented wheels (2) belonging to a line are spaced from one another, so that two consecutive multiindented wheels belonging to one and the same line cannot cooperate directly with one another; and a multiindented wheel (2) belonging to one line is disposed between two multiindented wheels belonging to an adjacent line and cooperates with the two multiindented wheels, In the spaces between the consecutive multiindented wheels of a line, there are provided passages (3) for the longitudinal elongate elements (9) of the braided tubular structure.

Abstract: A process is proposed for the fabrication of parts with large dimensions formed of a skin (10) and stiffeners (12, 16) such as aircraft fuselage segments made of a composite material with a thermoplastic matrix. After stiffeners have been made separately by lay-up, consolidation and shaping, these stiffeners are placed on a tooling (23) and the skin (10) is simultaneously fabricated and assembled to the stiffeners (12, 16) by diffusion welding. More precisely, the skin (10) is laid up and continuously consolidated by the lay-up head (36) such that the required part is obtained directly.

Abstract: A device for depositing in contact roving of pre-impregnated fibers in which at least one roving (F) is, in the course of a deposition sequence, unrolled from a spool (19) or the like, pressed and deposited on the surface (9) to be covered with the help of a deposition roller (11) or the like, then cut when the desired length of roving is deposited. Substantially from beginning to end of each deposition sequence the roving (F) is maintained in contact with the roller (11), the roving being unrolled substantially under only the tension of the roller and deposited and held, at least at the beginning and at the end of the deposition path, pressed against the surface to be covered, and, at the end of the deposition sequence, spacing the deposition roller (11) from the surface (9), then cutting the roving in its portion between the roller and the surface. Useful in the production of structures of composite material.

Abstract: The present invention relates to a vitrification process for a pulverulent material and an apparatus for implementing said process. The process consists in introducing the pulverulent material into the fusion area of a furnace via injection means, where it is melted by means of at least one plasma torch to obtain a melt, and where the melt is removed from the furnace via a casting zone, the material being introduced laterally into the fusion zone in a direction comprising a horizontal component, and the melt being removed from the furnace by overflowing via the said casting zone, more or less along said horizontal component and away from the means for injecting the material into the furnace, in relation to the fusion zone.

Abstract: The present invention relates to a connecting rod made of composite material, especially for internal-combustion engines, the composite material being formed by a reinforcement embedded in a cured material, and the connecting rod (A) comprising, along the longitudinal extension (X—X) of the connecting rod, a central shank (B) extended respectively, at its two ends, by a connecting-rod big end (C) and a connecting-rod small end (D). According to the invention, the connecting rod (A) is produced entirely as a single component made of composite material and the reinforcement of the composite material comprises superposed plies of crossed straight filling yarns, the filling yarns, which extend parallel to the longitudinal extension (X—X) of the connecting rod (A), constituting at least twice the volume percentage of the filling yarns which extend in each of the directions other than the longitudinal extension (X—X) of the connecting rod (A), and binding yarns pass through the superposed plies.

Abstract: Braided tubular structure (11) including longitudinal elongate elements (9) distributed on a plurality of collars coaxial with the structure and braiding threads (8) forming two grids of directions oblique in relation to the longitudinal elongate elements and interlaced with the longitudinal elongate elements. The braiding threads following paths which cause them pass between the longitudinal elongate elements. In the tubular structure, the braiding threads (8) of each one of the grids form an assembly of superposed layers in which the braiding threads (8) are parallel from one layer to the next.

Abstract: A panel of composite material, in particular with a thermosetting or thermoplastic matrix, with edges and/or external surface protected from shocks and erosion, for any streamlining element for housings or nacelles of aeronautical motors, comprises, over all or a portion of its edges, a cladding which forms a border overlapping the two opposite surfaces of the panel. The border comprises a metallic cloth connected to the structure of the panel by an adhesive agent, diffused through the cloth. The panel is particularly applicable to aircraft.

Abstract: A thermal protection device adapted to extend along a surface to be protected from a thermally and mechanically severe external environment, having an inside face adapted to face the surface to be protected and an outside face adapted to be exposed to the external environment, includes a composite layer containing a refractory armature buried in a thermally insulative material matrix, the device further including a ceramic, metal or metalloid external layer of which the outside face is part and which is attached to the composite layer.

Abstract: The present invention relates to on-site repairs of a composite structure (10) such as an aircraft structure in which a concave recess (14) is machined in the damaged zone, a non-polymerized composite part (16) is set into said recess and part (16) is polymerized under pressure using tooling (18) comprising a stack of plates (32) that increase the pressure applied to the composite part. The present invention thus obtains invisible repairs with mechanical characteristics that are similar to those of the initial structure.

Abstract: A process and apparatus for depositing simultaneously by winding on a support, several rovings of pre-impregnated fibers. The rovings are deposited simultaneously by winding on a rotating support. At least two rovings are brought into superposition near where they will be applied to the support, and the various rovings are subjected to different tensions depending on their position relative to the support. Specifically, the roving nearest the support is subjected to a greater tension than a roving farther from the support. Composite structures are thus produced.

Abstract: The object of the invention is a process for the production of a monolithic composite panel provided to be articulated on a support, particularly a panel articulated by hinges (36) for the production of a fan hatch of a turbo reactor or of a landing gear door in an aircraft, the panel comprising openings for the emplacement of elements (24, 26, 28) of service such as access doors, ports and/or ventilating grilles, characterized in that it consists in providing a network of beams (54, 56) as a function of the openings, avoiding the emplacements of the service elements, shaped and positioned for taking up the transmission of forces particularly between the articulation device and the panel. The invention also covers the panel obtained and the hatch particularly for use in an aircraft.

Abstract: A device for starting a gas turbine in an aircraft includes an electrical power supply delivering a direct current and a drive electric motor connected to the power supply, independent of the turbine to be started and having an output shaft mechanically coupled to an input shaft of the turbine to rotate with it. The drive electric motor is a three-phase alternating current synchronous motor and is controlled by an inverter connected to the power supply. Applications include situations in which the turbine to be driven is a high-power turbine.

Abstract: Input peripheral for a computer with automatic switching between 3D and 2D operating modes, and its interaction process with a display screen. A casing (10) containing a tracking type electromagnetic sensor (16) is fitted with a contactor (22) on one face (12) designed to be placed on a flat support. The contactor (22) makes the device automatically change from a 3D operating mode to a 2D operating mode when it is placed on a flat support, and vice versa when it is lifted off this support.

Abstract: A bar (25) for holding open a cover (4) hinged on the nacelle enclosing an aircraft engine (7) comprises two sections (26 and 28) of unequal length, one of which is hinged (27) on the cover (4) and the other (30) on the engine (7). The mechanism for locking or unlocking the sections (26 and 28) is controlled by a handle adjacent to the cover hinge (27). The bar can therefore be controlled by the very operator who is responsible for raising the cover (4).

Abstract: In an aircraft propulsion system, such as a jet engine, the fan cowls (22) are articulated to the support strut or pylon (12) by which the centre or core engine (14) is connected to a wing element (10). The cowls (22) are kept closed by hooked locks (32a, 32b), which connect their lower edges. To eliminate any risk of accidental opening, guide devices (36, 38) are placed between the lower edges of the cowls (22) and structures (20; 24, 26) connected to the centre engine (14), at least at the front of the cowls. The front structure (20) opposes any axial and radial displacement of the cowls.

Abstract: A simulator for simulating the firing of weapons the simulator including a firing station, and a missile weapon simulator. The missile weapon simulator able to simulate imaginary firings, an image display device, an image processing device, and an instructor station. The instructor station includes a video screen associated with a decision device by which an instructor chooses a virtual scenario relating to a firing field, the type of the missile and firing conditions. The image display device displays virtual images in actual size representing a field of vision of a firer in the virtual scenario chosen by the instructor, a micromonitor placed upon the missile weapon simulator displays the same images as those of the display device. The image processing device generates images within the instructor station, the images displayed on the micromonitor, and the images displayed on the display device.

Abstract: A pyrotechnic cutting device (14) is designed for directly cutting one or two parts (10) made form a nonmetallic material, such as a composite material. The device (14) comprises a pyrotechnic expansion tube (16), which acts on the part or parts (10) to be cut by means of a cutting member (32). This member can act in the manner of a punch or single or double shears. It can also be deformable or non-deformable. In the former case, the cutting member (32) can be integrated into the part (10) during its manufacture, particularly when said part is made from a composite material.

Abstract: The blocking system comprises a first interface element adapted to cooperate with a first of two bodies; a second interface element adapted to cooperate with the second of the two bodies; blocking element adapted to cooperate with the interface elements to ensure temporary blocking and comprising a frangible zone; a rupture device consisting of a shape memory alloy adapted to be deformed by elongation through heating to break the frangible zone, by which the second body becomes free to move relative to the first body; and heating element adapted to heat the rupture device beyond the critical temperature to cause the shape memory alloy to be deformed. A redundancy of heating element may be provided, as well as a retraction of at least part of the blocking element in a housing defined by one of the interface elements. The invention is useful for blocking the displacement of a tilting platform with respect to a fixed platform in the field of space applications.

Abstract: A device for protecting an optical system against the excess luminosity of an incident light beam. The device forms first and second light beams from an incident light beam. A mirror reflects the first beam which is then guided toward the optical system. The mirror includes a reflecting layer capable of being ablated, at least locally, when it is subjected to high luminous intensity. The second beam initiates the ablation process of the reflecting layer, which is continued and completed by the joint action of the first and second light beams.