Abstract: A display system of an aircraft, able to display a horizon line able to be deformed and related method are provided. The display system includes a display unit; and an assembly for generating a display on the display unit, able to dynamically display, on the display unit, at least one horizon line and a slope scale relative to the horizon line. Upon approaching a landing strip, the display generator is able to create, on the horizon line, a region that is deformed as a function of the topographical slope of the landing strip approached by the aircraft.

Abstract: A communication system for an aircraft with an external assembly and related method are provided. The system includes a unit for receiving incoming text messages, received from the outside assembly, and sending outgoing text messages, sent to the outside assembly; a display screen and a display management station, the display management station being able to display, on the display screen, a synthesis window showing a series of incoming text messages and/or outgoing text messages, each text message containing operating information about the aircraft. The display management station is able to display, in the synthesis window, an execution status indicator for an action to be performed remaining to be executed, associated with the incoming text message and/or the outgoing text message, in addition to the operating information of the aircraft.

Abstract: A device is provided for assisting in the piloting of a vehicle, in particular an aircraft. The device includes a surface displaying images and a display management unit for images designed to be displayed on the display surface superimposed on a view of the outside landscape. The management unit is capable of commanding the display of piloting information images on the display surface. The management unit is capable of commanding the display, for at least one of the piloting information images, of an animation intended to attract a user's attention to that piloting information image, the animation comprising the display of an alert image and the shrinkage of the alert image.

Abstract: A method for detecting a failure of at least one sensor onboard an aircraft implementing a baro-inertial loop is provided. The method includes implementing a baro-inertial loop including obtaining a computed vertical speed, then a short-term baro-inertial altitude, based on a double integration of the measured vertical acceleration; and developing at least one intermediate loop parameter based on a deviation between the short-term baro-inertial altitude and the pressure altitude. The method also includes observing at least one failure detection parameter obtained from one of the intermediate parameters of the baro-inertial loop; and determining the presence of a failure on one of the sensors of the aircraft based on the value of the observed failure detection parameter.

Abstract: A drain mast or discharging fluids from an aircraft and associated method are provided. This drain mast includes a fairing including a base including an upstream section intended to be attached on an outer surface of the aircraft and a downstream section. The drain mast also includes a discharge nozzle including a discharge end opening onto the outside of the fairing, the discharge nozzle protruding from the downstream section in a first direction with respect to the base, the base and the discharge nozzle defining a tubular through-cavity, extending from the upstream section as far as the discharge end. The fairing also includes a profiled section for guiding air, protruding from the downstream section, in a direction opposite to the first direction, and configured for orienting an incident mass of air on the profiled section towards the discharge end.

Abstract: An automatic speech recognition with detection of at least one contextual element, and application to aircraft flying and maintenance are provided. The automatic speech recognition device comprises a unit for acquiring an audio signal, a device for detecting the state of at least one contextual element, and a language decoder for determining an oral instruction corresponding to the audio signal. The language decoder comprises at least one acoustic model defining an acoustic probability law and at least two syntax models each defining a syntax probability law.

Abstract: A device for displaying flight characteristics of an aircraft is provided. The device includes a display for the selective display of flight characteristics of an aircraft, as a function of a state of credibility assigned to measurements from static pressure, total pressure and angle-of-attack sensors, configured for selectively displaying a primary set of flight characteristics comprising at least one flight characteristic coming from a measurement from one of said sensors, when the measurements from said sensors are deemed reliable, and a secondary set of flight characteristics, distinct from said primary set, comprising at least one secondary flight characteristic designed to replace a counterpart flight characteristic from the primary set, when the measurements from at least one sensor are deemed unreliable, said secondary flight characteristic being independent of any measurement by the or each sensor deemed unreliable done when the measurements from that sensor are deemed unreliable.

Abstract: The system includes additional display means including at least one additional screen and additional graphic interface handling means of the additional screen (able to display on the additional screen, a summary window depending on the operational state of the aircraft. The summary window comprises at least one first pictogram able to be displayed on a first display window of main display means of the aircraft without being displayed on the second window of the main display means, and at least one second pictogram intended to be displayed on the second display window of the main display means without being displayed on the first window of the main display means.

Abstract: A system for controlling the position of a movable object on a viewing device in an aircraft cockpit, which can be actuated by an operator includes means for determining, at least at one given moment, a position of a target zone on said viewing device toward which the operator's gaze is directed, and positioning means adapted for placing the object on the target zone of the viewing device.

Abstract: The system according to the invention comprises: an electrical network, and a regulating assembly. The regulating assembly includes a secondary electric power source, a conversion assembly for an additional electric power injected on the electrical network, the conversion assembly being able, in a first configuration, to consume the additional electric power present on the network to create a supply fluid of the secondary source. The assembly includes a reservoir for each supply fluid, to collect the supply fluid produced by the conversion assembly.

Abstract: A method for detecting a failure of at least one sensor onboard an aircraft implementing wind detection is provided. The method includes measuring an airspeed of the aircraft; measuring a geographical speed of the aircraft; determining an instantaneous wind vector, based on the measured airspeed and geographical speed; establishing an instantaneous wind variation vector, based on the determined instantaneous wind vector; projecting the instantaneous wind variation vector on the direction of the vector of an air or geographical speed of the aircraft; and determining the presence of a failure based on the obtained projection.

Abstract: A protective method is provided against torque peaks between a motor adapted for setting a shaft of the motor into rotation and an electric source adapted for electrically powering an electric assembly and including a fixed section and a rotating adapted for rotating with the shaft. The method includes a step for controlling the operation of the electric source forcing the rotary movement of the rotating section with the shaft to observe an instruction relating to the torque of the rotating section applied to the shaft of the motor, the instruction being adapted depending on at least one element characterizing a current operating state of the motor.

Abstract: The system according to the invention comprises an assembly for managing the graphic interface of a display, capable of controlling the display, on at least a first region of the display, of a peripheral area formed by a synthetic image comprising at least one synthetic surface representation of the terrain, and capable of maintaining at least one area representative of the position of a landing runway, centered on the landing runway, and at least one front area, adjacent to the center area, substantially free of any synthetic surface representation of the terrain. The management assembly includes means for dynamically defining the length (L) of the front area on the display as a function of a vertical decision position (DP) associated with a selected approach for said landing runway.

Abstract: A plugging device for plugging an end of a conduit is provided. The plugging device includes a sealing plug to the end of the conduit, and a pin intended to be axially driven into the bore of the socket for ensuring a sealing contact between the socket and the end, comprises a driver able to drive the pin into the bore of the socket. The plugging device further includes a determiner configured to determine an instantaneous axial position of the pin relatively to the socket as the pin is gradually driven into the bore of the socket by the driver. A method for plugging an end of a conduit is also provided.

Abstract: This antenna unit comprises an antenna having a radiating front surface, a back surface and a lateral outline having at least one electric field reinforcing region. It is characterized in that it further comprises a device protecting the antenna from lightning, having an internal surface at least partially capping the lateral outline of said antenna by being in electrical contact with said lateral outline, said internal surface covering the or each electric field reinforcing region, said protecting device having a curved external surface opposite said internal surface.

Abstract: An aircraft fuel storage device having at least one main reservoir designed to contain a first batch of fuel and at least one feed line for supplying a propulsion engine of the aircraft with the first batch of fuel contained in the main reservoir and having at least one auxiliary reservoir, designed to contain a second batch of fuel separate from the first batch of fuel, and wherein the auxiliary reservoir is connected to the main reservoir. The device also having an intake line for bringing the second batch of fuel contained in the auxiliary reservoir toward a combustion chamber of the aircraft independent of the propulsion engine of the aircraft.

Abstract: The system according to the invention comprises a mobile electronic device, at least one local base, arranged near a predefined location in the cabin, an assembly for pairing the mobile electronic device with the local base, and at least one piece of functional equipment for managing the cabin environment. The memory of the mobile electronic device stores at least one software application for controlling the functional equipment. The pairing system is capable of sending the mobile electronic device at least one location identification data of the local base during pairing between the mobile electronic device and the local base, the mobile electronic device being able to configure the control software application, based on the location identification data.

Abstract: A separating element for a platform cabin is provided. The separating element comprises: at least one stationary partition, delimiting a passage defining a circulation axis inside the cabin; at least one leaf, mounted transversely movable relative to the circulation axis between a closed position, in which it extends through the passage, and an open position, in which it is positioned at least partially spaced away from the passage; and means for moving the or each leaf between the closed position and the open position thereof, the or each leaf being adapted to move along the plane transverse to the circulation axis.

Abstract: This device providing assistance to aircraft crew for a flight level change of the aircraft in air traffic, comprising means for viewing the position of the aircraft in the vertical plane, is wherein the viewing means comprise: display means capable of displaying an image comprising at least one zone corresponding to a target altitude (FL) for the aircraft, and in that it comprises: selection means for selecting said zone in the image.

Abstract: The method according to the invention comprise the following steps, dynamic measurement of the current geographical position of the aircraft, and its current ground speed, calculation of a first length representative of a flight phase of the aircraft, and calculation of a second length representative of a ground phase of the aircraft, calculation of the position of the stop point based on the first length, the second length and the current geographical position. The calculation of the first length comprises a phase for dynamically estimating a distance traveled by the aircraft during at least part of a flare phase of the aircraft.