Abstract: A device and system for transferring information from an avionics system of an aircraft to an independent computer. The device can be embedded onboard an aircraft for transferring information arising from an avionics system from the aircraft to a computer independent of the avionics system. The device includes at least one radiofrequency receiver configured to receive information which arises from the avionics system and is emitted destined for the ground or another aircraft, at least one transmitter, and a processing unit to command the transmission by the transmitter, to the computer, of at least some of the information received by the radiofrequency receiver.

Abstract: Automation of the extraction and the consolidation of maintenance data and relates to a method and a system for automatic integration of data among a plurality of maintenance data, the plurality of maintenance data being diffused through a set of maintenance documentary elements comprising a set of directed links, the system including a processor configured for extracting a subset of pertinent links according to predetermined extraction rules and for integrating into a resultant element pertinent maintenance data sourced from a subset of pertinent maintenance documentary elements associated with the subset of pertinent links.

Abstract: A method for assisting the braking of an aircraft on a runway comprises the steps implemented automatically, including: before the landing of the aircraft on the runway, receiving the input, by a crew member of the aircraft, of a target braking distance by a man-machine interface associated with a processing unit, the target braking distance corresponding to a distance between a threshold of the runway and a selected exit of the runway; engaging an automatic optimized braking mode of the aircraft making it possible for the aircraft to attain the target speed when it reaches the selected runway exit; and—controlling a braking system of the aircraft, while the aircraft is running on the runway, according to this automatic optimized braking mode.

Abstract: The present invention relates to a door for closing an opening in a structure, including: a body arranged to be capable of abutting against a first side of the opening; at least one clamping member configured to be capable of abutting against an opposite second side of the opening; and a fastener arranged to fasten or release the clamping member relative to the body. The clamping member is moveable relative to the body between a first position where the clamping member abuts against the second side of the opening so as to clamp the structure between the body and the clamping member and a second position where the clamping member allows the door to be opened. The present invention further relates to an aircraft including the above door.

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: The disclosure herein relates to ensuring the mutual understanding between a remote maintenance support engineer guiding a maintenance engineer intervening on an aircraft, and concerns a system of prevention comprising first and second communication terminals to enable the maintenance engineer and remote maintenance support engineer to exchange information with each other, the information including oral guidance instructions given by the maintenance support engineer and oral responses given by the maintenance engineer relating to the execution of the instructions, a voice recognition device configured for transforming the oral instructions and responses into textual instructions and responses, a semantic analysis device configured for comparing the textual instructions with the textual responses in order to detect any possible inconsistency between the instructions and the responses, and a warning device configured for generating a warning when an inconsistency is detected between the instructions and the res

Abstract: The disclosure herein proposes identifying precursors to all the phenomena which can have an impact on the service use of an aircraft. It relates to a system for predicting failures in an aircraft, including a processor configured to analyze a current behavior of at least one flight parameter of the aircraft to detect any deviation of the current behavior relative to a predetermined behavior model of the parameter, the behavior model being determined from a plurality of series of learning data relating to the parameter collected during the flights of a set of aircraft.

Abstract: The runway state determined on the ground by an aircraft and provided to the aircraft on approach does not make it possible to account for possible degradation of the runway occurring since the previous determination of that runway state. Updating of this runway state on the basis of a simple comparison between a desired deceleration and an observed deceleration resulting from a degraded runway is not satisfactory either. The disclosure herein thus provides for obtaining a local stopping distance according to a local runway state characterizing a runway zone on which the aircraft is in movement at the time of the landing, this local stopping distance being estimated based on local measurements made in the aircraft; obtaining a reference stopping distance according to a reference runway state; then comparing these two distances with each other to determine whether the local runway state is more degraded than the reference runway state.

Abstract: A method to identify the proximity of a wake turbulence and to generate a report relative to that proximity. A method implemented by an aircraft comprising a processor makes it possible to identify the proximity of a wake turbulence and to generate a report relative to that proximity. The method includes a data acquisition step during which the processor retrieves and records the data relative to each generating aircraft present around the aircraft. In a position estimation step, the processor estimates the position of the wake turbulences generated by each generating aircraft. In a proximity step, the processor determines if the aircraft is close to at least one of the wake turbulences. In a generation step, the processor generates a report containing the data relative to each wake turbulence. The method makes it possible to identify the proximity of a wake turbulence in the vicinity of the aircraft and to automatically record the data relative to that wake turbulence.

Abstract: An aircraft canopy includes a window pane, a frame from a primary structure of the aircraft, and a flange fastened to the frame with fastening screw, characterized in that: the flange is secured to the peripheral edge of the window pane by engaging of at least one plate of the flange between plies of the window pane, so that flange and window pane form an all in one-piece assembly, at each fastening screw, a load-transferring and distributing member is arranged between an outer surface of the flange and the fasting screw, a cavity being provided in the flange for receiving the load-transferring and distributing member, the member having a recess for receiving the screw head.

Abstract: A method and a system for determining the state of a device in an aircraft, this state being specified by a current version of the device as implemented in the aircraft. The method according to the invention comprises: transmitting a request to a database and receiving in response a list of updates previously performed on the device, each update specifying an earlier version and a later version; and from a directed graph, such that each edge corresponds to an update of a set of updates associated with devices of the type of the device of interest, determining a sub-graph corresponding to the list.

Abstract: A subscriber of a deterministic Ethernet communication network using virtual links including a first receiver, a first transmitter, a first memory to record a configuration table relating to a set of virtual links that the subscriber can receive and/or retransmit. A processing unit is configured to implement at least one application, a reception function to receive data frames received by the first receiver, to accept the reception only of the frames corresponding to virtual links belonging to the set of virtual links and to transmit these frames to a sorting function to transmit the data frames received to the application and/or to a transmission function to dispatch the data frames received to the first transmitter while complying with Bandwidth Allocation Gap (BAG) constraints associated with the corresponding virtual links.

Abstract: An emergency beacon is configured to replace of one or more navigation lamps installed on an aircraft, which has a fuselage with an outer face, on which is fixed a second interface, on which such a navigation lamp is typically disposed; the emergency beacon includes a base, which has a first interface configured to cooperate with the second interface of the aircraft to fix the base onto the outer face of the fuselage; a casing with a control unit, a radio transmitter for transmitting a distress signal, and a detector to detect abnormal aircraft behavior; and a fixing structure to take up a fixation position, ensuring the casing is fixed to the base, or a separation position, in which it does not ensure the casing is fixed to the base; the transition from fixation position to separation position is controlled by the control unit when an abnormal behavior is detected.

Abstract: The disclosure herein relates to a method of controlling the thrust of the jets of a multi-jet aircraft, during the aircraft takeoff phase, which successively comprises a first step of controlling the jets to a first thrust level, until the aircraft reaches a first predetermined speed, and a second step of controlling the jets to a second thrust level, less than the first thrust level, when the aircraft exhibits a speed greater than the first predetermined speed, the first predetermined speed being less than the minimum ground control speed of the aircraft when the jets are at the second thrust level.

Abstract: A method and device for assisting initiation of a flare maneuver of an aircraft during a landing. The device includes an acquisition unit for acquiring current values of flight parameters of the aircraft, including the current height of the aircraft with respect to the ground, a computation unit for computing a first reference height and a second reference height, corresponding to a height starting from which the aircraft attains a current start of flare height while maintaining its current descent conditions over a predetermined first duration and over a predetermined second duration respectively, and an acoustic emission unit for emitting at least two sound signals in the cockpit of the aircraft, namely a first sound signal when the current height of the aircraft attains the first reference height during the descent and a second sound signal when the current height of the aircraft attains the second reference height during descent.

Abstract: A ground-based server is configured for identifying encounters of aircraft with wake turbulences generated by at least one other generating aircraft. The ground-based server is configured for: collecting avionics data for an in-flight aircraft and traffic data for one or more other aircraft in flight at a first flight time of the in-flight aircraft; determining that the in-flight aircraft was near a wake turbulence estimated, using the traffic data, to be generated by another aircraft; determining that the in-flight aircraft experienced at the first flight time a severe impact; determining that the in-flight aircraft experienced at the first flight time at least one of: one or more uncommanded forces and moments, and a wind signature indicative of wake turbulence; and in response, generating a report of a wake turbulence encounter for the in-flight aircraft at the first flight time.

Abstract: A method and device for displaying at least one position indicator for an aircraft. The display device includes at least one unit for generating information for determining, during a flight of the aircraft, a control value representative of the movement by a first pilot of his joystick relative to at least one of the roll and pitch axes of the aircraft, at least one computation unit for computing a piloting command representative of the control value determined by the unit for generating information, and one display unit for displaying at least one symbol on at least one screen intended for the second pilot and directly visible by the latter, the symbol representing the position indicator and being displayed on the screen in a position illustrating the piloting command on the screen.

Abstract: A method and device to locate an impact on an outer surface of a body including: locating the impact on the outer surface of a virtual model of the body; selecting a first and a second visual reference element on the virtual model; positioning an acquisition module on the outer surface of the actual body at the impact; measuring, using an acquisition module, measuring distances between the impact and the first visual reference element and between the impact and the second visual reference element; calculating a first arc around the first visual reference element and a second contour around the second visual reference element wherein each arc has a radius equal to one of the measured distances; determining a point of intersection of the first and second contours; and calculating coordinates of the point of intersection on the virtual model to locate the impact on the virtual body.

Abstract: An aircraft fuselage includes at least one space arranged in the aircraft fuselage and at least one wall. The wall resists burnthrough for a period of at least four minutes from outside the aircraft fuselage towards the space, wherein the region of the aircraft fuselage underneath the space does not include burnthrough-resistant insulation. The space may be a cargo compartment of the aircraft or a passenger cabin, while the wall may be designed as a cargo compartment floor, passenger cabin floor or wing/fuselage fairing (belly fairing). The design of the aircraft fuselage results in burnthrough resistance that meets the requirements of FAR §25.856 (b) without any additional burnthrough-resistant insulation in the aircraft fuselage.

Abstract: A method of assistance for troubleshooting is provided. A purpose is to prioritize identifiers each associated with a piece of equipment the failure of which can be the cause of a fault within an aircraft. The method is based on transmitting to an expert system, a list of identifiers, and receiving, for each identifier, a family of pertinent parameters, with each pertinent parameter being associated with at least one sensor of the aircraft and taking measurements of the pertinent parameters. Knowing these measurements, it is possible to deduce therefrom, for each identifier, a priority corresponding to the probability that the associated equipment is effectively defective. A system for implementing this method is also provided.