Abstract: An aircraft high-lift device comprising a kinematic chain connected to flaps, the kinematic chain comprising a plurality of shafts connected by coupling systems. This high-lift device comprises at least one differentiated coupling system different from the non-differentiated coupling systems, the differentiated coupling system being configured to be coupled to an adapter and comprising at least one poka-yoke feature. Another subject of the disclosure is an aircraft which comprises at least one high-lift device.

Abstract: A structure ensuring acoustic attenuation of a flow of a first fluid and heat exchange between a first fluid and a second fluid. The structure includes a first wall which is perforated, a second wall, and a plurality of intermediate walls extending between the first wall and the second wall. For each intermediate wall, there is a pipe intended to receive the second fluid and inscribed within the intermediate wall. Such a structure makes it possible to optimally integrate the acoustic wave attenuation function and the heat exchange function.

Abstract: A process for manufacturing an acoustic panel including at least one acoustically resistive layer, at least one cellular structure and a reflective wall. The process includes steps of depositing the parts of the acoustic panel made of thermosetting composite, depositing a film made of thermoplastic resin that is miscible with the thermosetting composite at the polymerization temperature of the thermosetting composite, polymerizing the parts of the acoustic panel made of thermosetting composite, and depositing and consolidating at least one layer made of thermoplastic composite against the film made of thermoplastic resin in order to form the reflective wall.

Abstract: A length-adjustable control rod includes a first part including a cylindrical peripheral face which has a succession of peripheral grooves separated from one another and positioned in transverse planes. A second part includes a barrel configured to at least partially receive the first part and which has several cutouts configured to divide up the barrel into several cylinder sectors and at least one inner rib, protruding from the inner lateral face of the barrel, which has a section configured to be housed in one of the peripheral grooves.

Abstract: A device includes a database including data related to obstacles, a first determination module for determining at least one obstacle intercepted by a direct flight path connecting an initial point to the target point, a second determination module for determining at least one lateral extreme apex of at least one intercepted obstacle, an evaluation module for assigning a rating to each section corresponding to a segment between a lateral extreme apex and the initial point, a storage module for storing in a memory the section corresponding to the optimum extreme apex having the best rating, the optimum flight path corresponding to all of the sections stored in the memory, the preceding modules being used iteratively, the device further including a transmission module for transmitting the optimum flight path to a user device.

Abstract: To reduce flexural deformations of an engine, an engine assembly comprises a device for attaching the engine onto a structure of an aircraft, the attachment device including a primary structure, an attachment device for attaching the engine onto the primary structure of the attachment pylon, and a nacelle including thrust reversal cowls, each equipped with an inner structure arranged around a case portion of the engine. The assembly includes flexible devices for transmitting forces, arranged between the case portion and the inner structures of the cowls, each device including an elastically deformable device configured so that in the closed position of the cowl, with the engine at a standstill, it adopts a partial elastic deformation state allowing the device to apply a prestress force on the case portion.

Abstract: A device for separating waste includes a tank having a closed internal chamber, the device being provided with an inlet opening and an outlet opening that can be connected to a suction system. The internal chamber of the tank is provided with a magnetic filter making it possible to attract and retain ferromagnetic waste likely to be entrained by the suction system into the tank, with a grating placed between the filter and the base of the tank, with a fluid discharge system at the level of its base. The device which is intended to be connected to a suction system makes it possible to retain and recover, sorted, the waste sucked in by said system and prevent the latter from polluting the pipelines thereof until they are blocked.

Abstract: A self-perforating spacer has a first part and a second part, the first part including a through-seat, the first and second parts being designed to be assembled together and the self-perforating spacer including a cutting system that cuts when the self-perforating spacer is assembled. A method for assembling a self-perforating spacer on an insulation blanket and an insulation blanket fitted with at least one self-perforating spacer is also described.

Abstract: Method and system of simple, precise, rapid and automatic control to verify fit between a manufactured device and its digital mock-up modelling it beforehand. The system includes a scanner configured to produce a three-dimensional cloud of points representative of the device, as well as a processor and a memory configured to superpose the cloud of points on the digital mock-up, coordinate the cloud of points with polychrome images captured during the scanning of the device and stored in a memory, disperse the cloud of points into several sets of points, each set of points corresponding to an object identified in the polychrome images, establish a correspondence between the sets of points and nodes of a treelike structure identifying the digital mock-up, and evaluate a fit between the cloud of points and the digital mock-up by analyzing the correspondence between the sets of points and the nodes of the treelike structure.

Abstract: In order to allow an aircraft fuselage structure to provide optimum resistance to pressurization loads in a fuselage region with a double curvature, the fuselage structure includes a circumferential frame oriented so that the web of the circumferential frame has an orientation close to the local normal to the skin of the fuselage.

Abstract: A front fairing of a pylon of an aircraft includes a shroud, produced in a single piece, which extends over almost all the surface area of the front fairing and which is configured to occupy a closed position in which a peripheral edge of the shroud and a peripheral edge of the front fairing and/or of the nacelle are contiguous, and an open position in which the peripheral edge of the shroud is, at least partially, separated from the peripheral edge of the front fairing and/or of the nacelle. The front fairing includes at least one locking system to hold the shroud in closed position.

Abstract: An aircraft propulsion assembly includes a first engine and a second engine that are adjacent and a nacelle in which the engines are installed. The nacelle includes a common air inlet lip for the first engine and the second engine, the air flow being divided between the first engine and the second engine by a median lip which extends, at least partly, set back from said common air inlet lip. The common are inlet lip includes, directly in line with the median lip, a bottom lobe and a top lobe extending forward of the nacelle. Such a configuration makes it possible to be able to provide a high aerodynamic form between the fairings of the engines, without the risk of generating overspeeds in the air flow.

Abstract: System and method to generate automatically a compact application code suitable for taking advantage of the intrinsic power of processors. The system can generate the application code executable by a processor from a formal specification associated with an application, the formal specification including operators, and the system including an analyzer to code each operator of the formal specification by a corresponding operation code followed by a minimum number of input code(s) and output code identifying input and output parameters associated with the operator, thus automatically generating a compact application code suitable for being stored in a memory associated with the processor and for being executed by an interpreter of the processor.

Abstract: A central wing box for an aircraft, including a top panel, a bottom panel, a front spar, a rear spar, and at least one secondary rib. A secondary rib includes two stiffeners, a first stiffener extending adjacent to the top panel and to one of the front spar and the rear spar, and a second stiffener extending adjacent to the bottom panel and to the other of the front spar and the rear spar. A reduced number of components can be employed, thereby simplifying the construction of the central wing box of an aircraft, particularly the installation of the secondary ribs.

Abstract: An access device enables controlled or secure communication between different areas of an enclosure, and in the example illustrated in the present application of an aircraft, while providing reduced size. The access device includes a folding door which, when in folded position, allows at least one of said openings to be closed and, when in deployed position, forms a security vestibule with at least one movable shutter allowing said opening created by the deployment of said folding door to be closed. By superimposing the main components of the security vestibule that said components allow to close, the device frees up the adjoining cabin space when the security vestibule is not in use.

Abstract: An aircraft includes first and second zones, and a sealing system, interposed between a doorframe and a door providing access to the second zone, including: a peripheral seal secured to the door, a stop secured to the doorframe, and including a body in the form of at least one plate which extends around the perimeter of the doorframe, parallel to the door when the door is in the closed position, a peripheral groove positioned on the stop in such a way that the peripheral seal closes off the peripheral groove around the perimeter of the opening when the door is in the closed position, and at least one passage configured to cause the peripheral groove and the first zone to communicate.

Abstract: A turbojet engine including an engine, a fan casing and a nacelle including a fixed structure and a thrust-reversing system having a mobile assembly with a mobile cowl and a frame, in which the mobile assembly is translationally mobile on the fixed structure between an advanced position and a retracted position to define a window between the secondary jet and the outside of the nacelle, inner doors and outer doors, a runner translationally mobile between a first position and a second position, in which each door is mounted articulated by a rear edge on the runner between a stowed position and a deployed position, an actuator for ensuring the translational displacement of the runner from the first position to the second position and an actuator for ensuring the displacement of the frame from the advanced position to the retracted position.

Abstract: System for friction stir welding of two parts which includes a welding unit which includes at least one welding head fitted with a rotating pin and a counter-bearing unit which has a support surface to support the parts against a pressure exerted by the welding head, and wherein each welding head can be moved relative to the support surface in a first direction parallel to an axis of rotation of the rotating pin and in a second direction orthogonal to the axis of rotation, and wherein the support surface can be moved in the second direction and is formed of two coaxial clamp rollers which are set apart from each other.

Abstract: A decision aid system includes an acquiring module for acquiring at least one current flight parameter of the aircraft, a reception module for receiving a set of information comprising runway characteristic data concerning at least the landing runway on which the aircraft is likely to land, an estimation module for estimating at least one likelihood of at least one state in which the aircraft can be upon the landing, an estimation module for estimating at least one probability of transition between the state or states estimated by the estimation module, an assessment computation module for in-flight assessment of at least one landing distance likely to be travelled by the aircraft on the landing runway, a determination module for determining at least one landing recommendation, a sending module for sending a signal representative of the landing recommendation or recommendations to a user device.

Abstract: An aircraft having a hatch and a fall-protection device includes a structure comprising a roof pierced with an opening, a cover plate, and a lock provided to adopt a locking position, in which the lock holds the cover plate in the closed position in the opening, or, alternatively, an unlocked position, in which the lock does not hold the cover plate. The aircraft further comprises at least one fall-protection device provided so that, when the lock moves into the unlocked position, it is in a first position to allow movement of the cover plate under the influence of gravity from its closed position to an intermediate position, in which the cover plate is suspended from the structure and then moves from the first position into a second position, during which movement the cover plate moves from the intermediate position into an open position, no longer attached to the structure.