Abstract: A fibrous preform (1) is produced, provided with a sandwich structure comprising an intermediate flexible core (4) and two outer fibrous frames (2, 3), respectively arranged on opposing outer faces of said flexible core (4) and assembled by sections of wire (8, 9) passing through said fibrous frames (2, 3), said preform (1) being impregnated with resin. Said preform is then hardened and the core (4) is removed, preferably by pre-densification with chemical vapour infiltration, and the structure produced is then densified with liquid-phase infiltration.

Abstract: A machining device has a machine head capable of displacement along at least three translation axes X, Y, Z for machining an immobile part fixed above the machining head. The machining head is maintained in a constant orientation by at least three articulated connecting rods. Two connecting rods define together with the machining head and with a first Y carriage, on which they are articulated, an deformable articulated parallelogram in the XZ plane. Another connecting rod is articulated on the machining head and on a second Y carriage and the second Y carriage is capable of displacement along Y on a second X carriage capable of displacement along X. The relative movement along X of the Y carriages results in a displacement in the Z direction. Several devices can be positioned in a plurality of tunnels, these tunnels being arranged so as to share several means.

Abstract: A rear tail assembly for an aircraft, including a fuselage, a wing and at least one propulsion engine attached in the rear portion of the fuselage located behind the wing along the X longitudinal axis of the aircraft, wherein the aforementioned assembly includes aerodynamic surfaces connected in the rear portion of the fuselage. The tail assembly essentially includes horizontal aerodynamic surfaces and essentially vertical aerodynamic surface arranged so as to form an annular structure including at least one ring attached to the fuselage. At lease one engine is held in the ring formed by the tail assembly. In one embodiment, a central fin is used for defining two rings in the annular structure. In particular embodiments of an aircraft including such a tail assembly, one or two engines can be fitted in the ring area.

Abstract: To analyze an electronic component, this component is exposed to a focused laser beam. The information provided by the laser mapping relating to the position and to the depth of the sensitivity zones of the component is used as input parameter in prediction codes for quantifying the sensitivity of the mapped component to ionizing particles in the natural radioactive environment. The prediction codes are used to determine the occurrence of malfunctions in the electronic component. Determination of the risks associated with the radiative environment imposes two aspects: one, probabilistic, takes into account the particle/matter interaction and the other, electrical, takes into account the charge collection inside the electronic component.

Abstract: An avionic system for an aircraft including at least two pieces of equipment (10a, 10b) which can exchange information by means of at least one electrical bus for simultaneous bidirectional communication, in which the information can be exchanged between pieces of equipment (10a, 10b) via an optical bus (20) that can be connected to the electrical interfaces (11a, 11b) of the equipment. The optical bus (20) of the avionic system includes at least one optical cable (21) having at least one optical fibre (22) and, at each end, a connector (30) having means (41, 42, 45, 46) for converting electrical signals into optical signals and means for converting optical signals into electrical signals. The optical bus (20) is connected to the electrical outlets of existing equipment.

Abstract: A device for non-destructive testing of a structure likely to contain a defect, including microsensors for measuring vibratory waves emitted by the structure at different points of a surface of the structure, the aforementioned microsensors being integrated in a flexible housing capable of adhering on the surface of the structure to be tested. The disclosed embodiments are applicable to all industrial sectors where testing of the integrity of structures is important, in particular in areonautics.

Abstract: An aircraft, the propulsive units of which include engines, and which is distinguished by reduced noise emissions, includes a wing structure fixed to an upper region of the fuselage, and a vertical tail system having at least two vertical stabilizers which are generally vertically fixed to the fuselage aftwardly of the wing structure. The engines are disposed side by side in a propulsive package disposed above the fuselage, which propulsive package includes the following: air inlet openings for the propulsive package, which openings are disposed above the fuselage between a point at the leading edge and a point at the trailing edge of an aerodynamic root chord of the wing structure; and exhaust nozzle conduit outlets associated with exhaust nozzle conduits, which outlets are formed by the structure (cowling structure) of the propulsive package, and are disposed above the fuselage forwardly of an aft terminus of the fuselage and between the vertical stabilizers.

Abstract: An electrical cable (1) provided with a sheath (2) having external marking. The marking is formed from a block (3) of two patterns (4, 5), the two patterns being consecutive along a length of the cable, said block being repeated at least twice along the length of the cable starting from the free end (12) of the cable. The disclosed embodiments also relates to a method of crimping a contact (7) onto such a cable, the external marking of the cable making it possible to know the position of the cable in the barrel and thus guarantee that the crimping that takes place will be of good quality.

Abstract: The invention concerns a doorway in an aircraft fuselage comprising a door frame in which a door is mounted, this frame comprising an outer framework, an inner framework and a core placed between the inner framework and the outer framework, capable of absorbing energy from an impact, the core being a stiffener made of composite material having an accordion shape.

Abstract: A pitch-oscillation limitation system, applied to an aircraft having main landing gear located toward the center of the aircraft and forward landing gear located under the nose of the aircraft, wherein the system includes means for automatically applying, in the event of sudden braking, time-deferred braking between the wheels of the landing gear under the wings and the wheels of the landing gear under the fuselage, so as to reduce the amplitude of the aircraft's pitching motion.

Abstract: A method for the determining, on board an aircraft, of an identifier of a communications center with which an aircraft crew wishes to enter into contact, includes the following operations: a) the writing, by the crew, of a radio-communications frequency to a display unit of the cockpit of the aircraft, b) the determining of surroundings of the aircraft, c) the determining of the communications centers situated in these surroundings, d) the comparing of the frequencies of these communications centers with the frequency displayed on the display unit of the cockpit, and f) when the frequency of a communications center is identical to the displayed frequency, the display on the aircraft display unit of the identifier of said communications center having a frequency identical to the displayed frequency.

Abstract: A process for transmitting data between at least one display screen in a cockpit and at least one remote client system includes at least one computer, in which the display screen displays a first request to send a message in a first communication protocol; this message is sent to the remote client system over a first link using a second communication protocol. A request to confirm a message is generated and displayed on the display screen via a communication interface designed to receive and generate messages in this first communication protocol and to receive and generate messages that can be received by the remote client system.

Abstract: The disclosed embodiments relate essentially to a primary structure of an aircraft fuselage that has at least a first strut linked at one end to a crossbeam and at the other end to a reinforcing frame. A second strut has one end fastened to the structure below the end of the first strut, and another end linked to the first strut through an intermediate sliding linkage. A deformable member is linked to the struts so that in case of a crash, the compressive forces press against the second strut, so that the end of the second strut slides along the first strut so as to stretch the deformable member longitudinally to absorb the shock.

Abstract: A device for fixing a seat rail, designed to maintain passenger seats on a floor, wherein it includes a connecting bracket, secured to the floor and to the seat rail, the bracket being adapted to support the stresses perpendicular to the plane of the floor, and the stresses parallel to the plane of the floor. The bracket extends obliquely between the floor and the rail seat, a lower end of the bracket being secured to the floor and an upper end of the bracket being secured to the seat rail.

Abstract: To be able to transport and replace in an autonomous manner one of its failing propulsion engines, a plane includes: a fuselage; propulsion engines maintained above the fuselage; maintenance wells traversing the fuselage substantially vertically with respect to the engines in which the engines can be lifted or lowered; a cargo compartment including a floor arranged in the fuselage, where the height, length and width dimensions of the cargo compartment are compatible with the transport of an engine; the cargo compartment and the wells have a common separation wall including an exit whose dimensions allow the passage of an engine; and a lower hatch or ramp for closing the lower opening of the well includes a position in which the upper surface of the ramp is substantially horizontal and substantially in the extension of the floor of the cargo compartment.

Abstract: A cockpit and an aircraft including such cockpit. The cockpit includes a front section of an aircraft. Such cockpit includes a pressure bulkhead sealing the section and a pressurization system for pressurizing such section.

Abstract: The present invention provides a method of reducing the compressibility drag of wing, and it also provides a container implementing the method. The container (10, 10?, 10?) is provided successively with a front portion (11) in the vicinity of its leading edge (14), then with an intermediate portion (12), and then with a rear portion (13) in the vicinity of its trailing edge (15), said rear portion (13) tapering progressively in a direction going from the leading edge (14) of the container towards its trailing edge (15). Furthermore, said rear portion (13) is extended by connection means (17) enabling the container (10, 10?, 10?) to be connected under the wing (1) in such a manner that said tapering rear portion (13) is partially upstream from the leading edge (2) of the wing (1).

Abstract: In order to conduct tests designed to determine the adherence properties of a coating on a substrate, a pull plate of a hardenable material is molded directly to the surface of a coating applied to a substrate. The pull plate geometry is determined by the mold cavity and is made of a material that adheres to the coating surface during the molding process. The pull plate therefore, is only used once, while the mold may be reused.

Abstract: A nacelle cowling for a turbojet, characterized in that it is provided with a fixed part and a mobile part, the mobile part being adapted to slide along the fixed part, from a closed position wherein the mobile part extends in the extension of the fixed part, up to an open position wherein the mobile part is at least partly superimposed to the fixed part. For example, the fixed part is located in the upper part of the cowling, the mobile part being located in the lower part of the cowling.

Abstract: A device and a method for assembling oriented objects, such as parts of a pipeline. The device includes means for rotational displacement about a rotational axis of a first and second base. The first base has a first main axis which is perpendicular to the rotational axis and includes first means for supporting objects that can be displaced in translation along the first main axis. The second base has a second main axis which is perpendicular to the rotational axis and includes second means for supporting objects and a revolving plate device for supporting and orienting one of the objects in an angular manner. The revolving plate device can be displaced in translation in relation to the second supporting means along the second main axis. Visualization means enable at least the rotational angle of the plate and the position of the second base to be visualised.