Abstract: The invention relates to a wall made from a composite material comprising at least two layers of fibers (18, 18?) embedded in a resin matrix, a crack being able to spread in said wall in a direction of propagation, characterized in that it comprises at least one longilineal metal reinforcement (20), oriented in a direction secant to the direction of propagation, inserted between two layers of fibers (18, 18?) of the wall.

Abstract: An interface device between an electrical network and energy consumer systems, including an input converter with a first winding connected on one side with a reverse blocking module and on the other with a first semiconductor chopper device, second and third windings having an end connected to output converters via first and second reverse blocking modules, and another end connected to the output converters, via a switching cell, a fourth winding having an end to be connected to the network, via a second semiconductor chopper device; and a control module for the semiconductor chopper devices. The interface device also includes a buffer capacitor having a first end connected to the output converters, and another end, to which a reference voltage is applied, isolated from the network; and a power reserve having an end to be connected to the network and another end connected to the fourth winding.

Abstract: A system for controlling energy of a vehicle, for example an aircraft, characterized in that it comprises: a control interface (10), said control interface comprising a movable element (12) configured to move along a path (13), said path defining at least two path portions (14, 17) respectively associated with at least two combinations of actuators acting on the energy of said vehicle, at least one of said at least two combinations of actuators being associated according to a current phase of movement of the aircraft, and a control unit configured to generate an energy instruction according to a command associated with a current position of said movable element on one of said at least two path portions, and according to said current phase of movement of the vehicle, said instruction being for the associated combination of actuators.

Abstract: The invention relates in particular to a method and a system for monitoring a graphical interface in a computer system of an aircraft cockpit. The method comprises, in addition to the display of a graphical interface of a client application based on a tree structure of graphical interaction objects composing said graphical interface, the following steps: obtaining a plurality of graphical interaction objects having a tree-structure organization; creating and adding, to said obtained tree structure, at least one new graphical interaction object defining a critical graphical display zone; modifying the tree-structure dependency of at least one critical graphical interaction object, of the obtained tree structure to make it dependent from the new graphical interaction object defining the critical zone; and performing critical monitoring only of the critical graphical objects attached to the critical zone.

Abstract: A bleeding system includes an open conduit and, upstream, a control controlling the hydraulic fluid flow, toward the open conduit. The bleeding system includes a dismountable connection device including connection means adapted to be connected to the bleeding system; an outlet adapted to be connected to a pipe; a first central portion including the connection means, a cylindrical bearing, and a conduit extending from the connection means up to the surface of the cylindrical bearing; and an annular second portion including a bore adapted to pivot on the cylindrical bearing, at least one conduit connecting the outlet and the surface of the bore. The first portion and/or the annular portion include a groove ensuring the hydraulic fluid flows between the conduits. The central portion includes a section arranged between the connection means and the cylindrical bearing to ensure the connection of the connection device to the bleeding system.

Abstract: An insulation device for an aircraft, comprising a blanket comprising a layer of insulation filling enclosed in a cover and having provision areas for the passage of aircraft components, these areas being devoid of insulation filling and being formed by a surface junction of two opposite faces of the cover inducing a recess in at least one face. The insulation device comprises an associated detachable complementary assembly to cover at least one of the provision areas, the assembly comprising a portion of insulation filling shaped to fit into the corresponding recess, and a retention arrangement for retaining this portion of filling. The retention arrangement is provided with a detachable arrangement for fixing the detachable complementary assembly on at least one face of the cover.

Abstract: A frame of an aircraft fuselage structure made from composite material, which includes a skin and several stringers fixed on the skin. The frame includes a profile elongated in a longitudinal direction which is hollow over at least a portion of its length. The profile is mounted on two legs. Each leg, intended to be fixed on the skin, includes a first portion extending continuously over the whole length of the profile and a second portion extending from this continuous portion so as to form several openings spaced apart in the longitudinal direction of the profile, in each of which a stringer passes. The presence of the hollow profile in the frame and the structure of the legs makes it possible to dispense with clips and cleats.

Abstract: An arrangement for freeing the structures of fail-safe type from the damage tolerance criterion and to allow a significantly improved fatigue resistance, while producing a weight saving. This is provided by forming a composite hybrid structure in a configuration that makes it possible to combine the advantages of metal and of composite material. In a secure hybrid structure, at least two longitudinal structural spars are joined back to back by fastening means. One of the spars is metal and equipped with stability partitions, whereas another spar is made of a composite material with carbon fibers oriented in the direction of the forces to be predicted such that this spar exhibits a rigidity equivalent to that of the metal spar.

Abstract: A monitoring device is provided. The monitoring device includes means for verifying whether an identifier received from a ground station of a radionavigation system is among the identifiers of the ground stations situated in a monitoring zone around the current horizontal position of the aircraft.

Abstract: A substitution device for replacing a turbojet type of aircraft engine, with a nacelle comprising protective covers, and a support mast having two engine mounts, each of said protective covers being mounted to pivot between an open position and a closed position, said substitution device comprising a body, two anchors attaching to the engine mounts of the engine support mast, and bearing portions adapted to receive support portions belonging to the protective covers. A method for installing such a substitution device in a nacelle, which makes it possible to close the engine covers and authorize the movement of the aircraft.

Abstract: A method for producing an acoustic treatment panel, including: assembling two plates, at least one of which is deformed so as to separate the plates locally in order to form cavities of a cellular structure between the two plates, said cavities being delimited by facets and partitions formed by at least one of the deformed plates, producing at least one opening on the facets of one of the two plates, and pressing an acoustically resistive plate against the surface of the cellular structure including the openings.

Abstract: A device and method for assembling two structural elements made from a composite material is provided. The device includes two cylindrical flanged receptacles, each pierced by an aperture perpendicular to the axis of the cylinder, and a shaft that can be introduced into said apertures. The device also includes bearing means, which bear on the interior surfaces of the cylindrical receptacles and can maintain tension in the shaft when the shaft extends through the apertures in the two receptacles. The device includes means of placing the shaft under tension.

Abstract: The dialog device includes a display screen, on which are displayed three graphic representations, which are respectively associated with the three control axes of the aircraft, each of said graphic representations comprising a plurality of portions, each of which is associated with a guidance mode of the associated control axis, so that all the possible guidance modes of the guidance system are thus represented, this representation highlighting the fact that the guidance modes are active exclusively on a given guidance axis.

Abstract: A front structure of an aircraft fuselage comprising landing gear pivoting about a main shaft and a stay shaft. The front structure also comprises a first reinforcing frame and a second reinforcing frame, the main shaft and the stay shaft being respectively connected to the first and second frames, and a device for the mechanical connection and transfer of forces connecting the stay shaft and the main shaft and transferring to the main shaft a portion of the forces induced by the wheels of the landing gear onto the stay shaft, the second frame and said device being perpendicular to one another.

Abstract: A distribution panel aboard an aircraft includes sites intended for the installation of functional electrical circuit breakers of which at least one of the sites is not occupied by a functional circuit breaker. The functional circuit breakers are wired up to a monitoring system via monitoring cabling so as to monitor a state of the circuit breakers. The at least one site not occupied by a functional circuit breaker is occupied by a nonfunctional circuit breaker, termed a false circuit breaker. The false circuit breaker is able to deliver a state signal and is wired up to the monitoring system by the monitoring cabling in a manner identical to that of a functional circuit breaker.

Abstract: Interactive dialog device between an operator of an aircraft and a guidance system of the aircraft. The dialog device includes an interaction on a screen which represents, on the one hand, a playback element indicating the value of a guidance setpoint of the guidance system of the aircraft, and on the other hand, a control element which can be grasped and moved along a curve by an operator to modify the value of the guidance setpoint.

Abstract: There is provided an aircraft folding seat (12), comprising a frame (14) which pivots about a vertical axis and on which are mounted a seat-rest (20) and a back-rest (18) The flight deck provided comprises control and/or viewing devices, at least one seat (30), an access door (6) and a corridor (10) for access to the seat (30) which is closed at its opposite end to the seats (30) by the access door (6). A folding seat (12) is mounted in the corridor (10) such that it can pivot and adopt a first position in which it is closes the corridor (10) so forming a lock enclosure with the access door (6) and a folded back second position enabling access to said seat (30) from the corridor (10).

Abstract: The object of the invention is an electrical harness having a plurality of electrically conductive elements held one against another in a braided sheath obtained by braiding strands around the electrical conductor elements, the strands being joined and forming a web around the electrical conductor elements when held against each other, wherein it includes a device to space comprising at least one portion with a peripheral surface at the level of which channels are provided wherein an electrical conductor fits, said portion having a section such that it allows to obtain spaced strands at the level of said device to space when the sheath is being braided around the electrical conductor elements.

Abstract: This invention relates to an aft pylon fairing for the suspension system of an aircraft engine, comprising a main structure extending along a longitudinal direction of said fairing and integrating two side panels connected to each other, the fairing also comprising a heat protection deck mounted on said main structure through connection means comprising tabs designed to deform to accompany displacement of the deck relative to the main structure, if there is differential thermal expansion between these two entities.

Abstract: The device (1) comprises means (7) to automatically transmit, on an anticipated way, a runway slope value to an automatic piloting system (6) of the aircraft, and said automatic piloting system (6) uses such slope value so as to automatically manage the flare phase upon landing.