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 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 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 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 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.

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: The disclosed embodiments concerns a system for monitoring anemobaroclinometric parameters in an aircraft, including a primary detection circuit having at least one measurement channel. The measurement channel includes a device for measuring static air pressure, a device for measuring a side-slip angle of the aircraft, a device for measuring a dynamic pressure, a total air temperature and a angle of attack of the aircraft, and a data-processing device capable of determining anemobaroclinometric parameters from the measurements of static pressure, side-slip angle, dynamic pressure, total air temperature and angle of attack, a least one laser anemometer to measure at least one true airspeed parameter of the aircraft.

Abstract: A composite panel having a first skin forming the outer wall of the panel, known as the lower face (1), and a second skin forming part of the inner wall of the panel. The second skin is formed hollow such as to produce an inner reinforcing frame (2) in the form of a half-box structure (3) which, together with the first skin, forms box parts. The aforementioned frame is equipped with a rim (4a, 4b) for fixing to the first skin, a face known as the upper face (5) and connecting side walls (6, 6a, 6b, 6c, 6d, 6e, 7) between the rim (4a, 4b) and the upper face (5) the first and second skins forming a monolithic self-stiffened panel. The half-box frame (2) has perforated sections (8) which are defined by hollow beam sections forming the half-box frame (2).

Abstract: The invention concerns a wall (10) of vertical partitioning for a ventral cowling of an aircraft including a plurality of vertical panels (11, 12, 12?, 13, 13?), each panel being linked to an adjacent panel by a vertical post (14, 15, 16). At least one exterior panel (13, 13?) is mounted in a fixed manner on at least one associated vertical post (14, 16). The upper end of said vertical post is fitted with a means of fastening in transverse rotation intended to be fixed to the structure (8) of an aircraft, the means of fastening in transverse rotation being capable of allowing the displacement (Dy) of the structure of the aircraft with respect to the fixed partitioning wall. It is also possible for at least one intermediary panel (12, 12?) to be mounted floating on at least one associated vertical post (15, 16), in such a way as to have a deflection parallel and perpendicular to the adjacent panels.

Abstract: A feed device for a superplastic press-forming press has a slide that moves vertically and a base between which is held a tool having a cover and a bottom die enclosing a forming tool, which includes at least one heating shuttle to transport the bottom die, equipped with the forming tool and a cover, with the heating shuttle adapted to complete the press and constitute the base of the press during a hot-press forming operation.

Abstract: A reduced-volume landing gear casing for the landing gear of an aircraft including a box structure to which the landing gear is fixed and which takes up the loads acting thereon. The box structure can include, in particular, means for receiving the fixing bearings of the landing gear.