Abstract: The invention relates to a flight management assembly (1) comprising two guidance chains (2A, 2B), each one provided with a flight management system (3A, 3B), each of said flight management systems (3A, 3B) carrying out at least one calculation of guidance instructions for the aircraft, the flight management assembly (1) also comprising at least one monitoring unit (4A, 4B) designed to monitor the guidance instructions calculated by the two flight management systems (3A, 3B) in such a way as to be able to detect and identify a defective flight management system, the monitoring unit (4A, 4B) comprising a monitoring device (5) which verifies particularly whether the following three conditions are met: a first derivative of extrapolated cross tracks is positive; a second derivative of extrapolated cross tracks is positive; and extrapolated positions of the aircraft are on the same side of an active segment of the flight plan followed by the aircraft as the current position of the aircraft.

Abstract: Systems and methods are disclosed allowing a passenger of a vehicle to use a personal electronic device to control a saving, on a storage device, of image data of video streams arising from cameras of the vehicle. The system includes at least one client/server module configured to receive and retransmit image data of a video stream received from one of the cameras to the storage device. The client/server module includes a processor configured to connect the personal electronic device to the client/server module, a receiver for receiving a request, originating from the personal electronic device, including an item representative of a set of images of the video stream to be saved and a transmitter for transmitting to the storage device image data of the video stream corresponding to the item, with a view to their saving.

Abstract: In order to reduce the width of the attachment between the rear portion of an aircraft engine and its attachment pylon, an engine assembly attachment include an assembly of rear engine attachments comprising a first connecting rod laid out in a longitudinal and median vertical plane, a second connecting rod substantially laid out tangentially to the inter-turbine case, and a rear engine attachment for transversely spreading the loads, axially shifted rearwards relatively to the first and second connecting rods, and comprising a shear pin oriented along a vertical direction of the engine assembly.

Abstract: The disclosure herein updates distant equipment while avoiding protocols and connections and concerns a deported downloading system of data on distant equipment, and includes a gateway adapted to receive a set of data comprising operational data addressed to the distant equipment as well as a temporary downloading engine, the gateway being also adapted to download the operational data into the distant equipment by starting the execution of the downloading engine.

Abstract: In order to reduce the risks of movable nacelle cowlings opening, the invention provides a nacelle for an aircraft engine assembly comprising a fixed nacelle structure as well as at least one jointed movable cowling on the fixed structure, the cowling being jointed at its front end on the fixed structure so that, upon closing the movable cowling, a rear end of this cowling moves towards the rear and radially towards the inside.

Abstract: A method for manufacturing an aircraft leading edge panel, includes a step of overmoulding a coating onto a sheet positioned in a cavity of a mould, which cavity is delimited by a shaping surface which exhibits an optimized surface finish. The coating includes, after the overmoulding step, an exterior face which corresponds to the exterior face of the panel that is to be obtained and which exhibits an optimized surface finish conferred by the shaping surface of the mould. A panel may be obtained using this method and a leading edge includes at least one such panel. Because of the optimized surface finish of the exterior surface thereof, the panel contributes to extending the regions of laminar flow.

Abstract: A flight management system architecture with separate core and supplementary modules. In the core module, generic functionalties relative to the flight management of the aircraft are implemented. In the supplementary module, supplementary functions are implemented. The supplementary functionalities include functionalties specific to an entity to which the aircraft belongs such as the specific aircraft model, a family of aircraft, a company, an alliance, and so on. The flight management system also includes a message exchange interface in which enables the core and supplementary modules to exchanges messages with each other. The core and supplementary modules includes corresponding core module and supplementary module interfacing functionaltities that respectively interface with generic and specific man-machine interfaces.

Abstract: The detecting means (1) comprise measuring means (2) adapted to measure and provide at least one raw data corresponding to an aircraft parameter, computing means (3) adapted to estimate at least one derivative of said raw data, and detecting means (4) adapted to detect a failure with the aid of said derivative, said computing means (3) being adapted to estimate said derivative by differentiation.

Abstract: A tool for applying a corrosion-protection substance to a rail for securing seats in an aircraft. The tool includes a component of elongate overall shape, with a base configured to slide along the rail, and a rollers support connected to the base. The tool also has an axle incorporated in the rollers support, which extends transversally with respect to the longitudinal direction of the component on each side of the rollers support, and rollers for applying the substance mounted on the transverse axle, one on each side of the component. The tool allows the substance to be applied effectively to the flange parts of the rail that is to be protected.

Abstract: A system for emitting and/or receiving electromagnetic waves embedded in an aircraft, the aircraft including an emitting and/or receiving device for emitting and/or receiving electrical signals, a radome having an electrically insulating protective envelope (12), on which at least one lightning arrester strip (21) is arranged, the radome being attached to a metal frame of the aircraft (30), a first part of the at least one lightning arrester strip is electrically connected to the metal frame of the aircraft, a second part of the at least one lightning arrester strip is connected to the emitting and/or receiving device via a metal element (35) of a predetermined shape, the at least one lightning arrester strip forming an antenna and a part of the metal element (35) is placed at a predetermined distance (d) from a part of the metal frame of the aircraft (30) for forming a capacitive link between the metal element and the metal frame of the aircraft.

Abstract: In operating an aircraft, a situation is displayed at each instant representing a spatio-temporal overview of risk zones around the aircraft. Each direction in space around the aircraft is scanned, and a simulated displacement of the aircraft in each direction is analyzed so as to identify potential zones of interference with the aircraft's path. Anticipated movement of risk zones over a planned time duration of a flight is determined. Such anticipated movement is correlated with an anticipation position of the aircraft over the planned time duration. Accordingly, risk zones initially appearing as a potential hazard may be determined to be safe by the time the aircraft reaches them, and vice versa. Such information is presented to pilots at an outset of the flight and continuously updated throughout the flight, enabling accurate and safe evaluation and strategy decisions.

Abstract: An interface manager device interconnects peripheral devices to a network of ACD type or of AISD type of an aircraft, and includes: a first data interface for connecting it to the network; a first electrical power supply interface for connecting it to a general electrical power source; second data interfaces and second electrical power supply interfaces, for connecting it to the peripheral devices, which are deactivated by default. The interface manager device is configurable via a configuration interface so as to selectively authorize connections between the second data interfaces and the first data interface, and to selectively authorize connections between the second electrical power supply interfaces which are associated with them and the first electrical power supply interface, and to activate the second interfaces concerned. The interface manager device propagates a received data packet when said data packet relate to an authorized connection and deletes said data packet otherwise.

Abstract: A tool-support system for working on holes of a surface. The tool-support system includes two rails fixed to the surface and having imprints regularly distributed over their length, and a mobile tool-support including a mobile optical system capturing an image of the surface. For each rail, at least one wheel is adapted to be moved on the rail, and includes on its rolling strip counter-imprints complementary to the imprints. A mobile tool carries a working tip, and a control unit is configured to control the movement of the mobile tool-support, of the tool and of the optical system to analyze an image captured by the optical system and to detect the presence of a hole. A tool-support system of this kind can therefore move along the rails without slipping while detecting the holes to work on them.

Abstract: A device for conducting accelerated aging tests of a coating, notably an outer coating for an aircraft, in particular allowing the testing of the durability of the coating after having been subject to all kinds of stresses, is desired. An object of the disclosure thus relates to such a device including test chambers subject to different and/or independently controllable test parameters, and including light for generating photo-oxidation, the device including a support for a sample of the coating, displaceable between the chambers for generating mechanical stresses by thermal shocks. The disclosure herein finds applications in many fields of industry, and preferentially in the field of aeronautics.

Abstract: A thrust reverser system includes a thrust reversal cascade and a reverser door which are accommodated in a housing situated outside a secondary flow duct. The system also includes connection parts the presence of which combined with the action of the actuator gives rise simultaneously to: displacement rearwards of the cascade in the direction of a nacelle opening, cleared by a nacelle cowling entrained rearwards together with the cascade; and a combined movement of the reverser door relative to the cascade, leading to displacement of the front end of the door rearwards along the cascade, and to pivoting of this door, such as to give rise to plunging of its rear end into the secondary flow duct.

Abstract: A method for transmitting flight parameters of a lead aircraft to an intruder aircraft. Transmission includes a collision avoidance system connected to which is a flight parameter transmission authorization system having a database including coordinates defining a volume of confidence smaller than the monitoring volume. The flight parameter transmission authorization system of the lead aircraft authorizes, only for an intruder aircraft identified as flying within the volume of confidence, transmission of at least one flight parameter of the lead aircraft, such that this intruder aircraft is able to calculate the position of centers of wake vortices generated by the lead aircraft or the flow strength of the wake vortices. Exchanging flight parameters of the lead aircraft only with intruder aircraft flying within the volume of confidence with limited dimensions makes it possible not to exceed the maximum capacity of the bandwidth of the automated communication.

Abstract: A thrust reverser system includes two thrust reversal cascades, of which the first cascade is entrained by an actuator, and which are configured to adopt a retracted position in which they are housed in a space located outside the duct. The action of the actuator brings about: rearward displacement of the first cascade in the direction of a nacelle opening; and during part of the rearward displacement of the second cascade, simultaneous pivoting of this second cascade under the action of a control lever, the interaction of which with a fixed guide rail forces the front end of the lever to move radially inwards while the lever is entrained rearwards by the second cascade.

Abstract: The device for automatic management of an actuator controlled by a servo-valve, includes a sensor for measuring the actual value of a parameter at the output of the actuator for a given control command, a computation unit for computing a theoretical value of said parameter, by applying the control command to a nominal performance model which models the operation of the actuator exhibiting nominal performance, a computation unit for computing the difference between the measured actual value of the parameter and the computed theoretical value of said parameter, a control unit for computing an adapted gain as a function of this difference, and a link for applying the adapted gain to the servo-valve for it to use it as gain value, so as to allow the actuator to restore nominal performance.

Abstract: The communication system of an aircraft includes a set of communication channels, a communication computer, an audio device and a control device connected to the communication computer. It also includes a wireless communication unit interfaced to the communication computer and configured for simultaneously implementing: a two-way wireless audio link between the wireless communication unit and the audio device, so as to allow an audio communication on one of the communication channels by the audio device, and a two-way wireless data link between the wireless communication unit and the control device, allowing the control device to control the communication computer.

Abstract: A non-destructive inspection device includes: a probe, a camera configured to film an area of the part inspected by the probe, a first display and a second display system configured to allow a display of at least one image filmed by the camera. This configuration makes it possible to remotely display the area of the part inspected by the probe.