Abstract: An assembly of a pylon and of a nacelle of an aircraft, wherein the nacelle has a structure, a visor, two centering systems and two tensioning systems. Each tensioning system comprises a first fitting, which is attached to the structure and has an engagement wall through which an orifice passes, a second fitting, which is attached to the visor, a threaded rod that is articulated on the second fitting and passes through the orifice, a spring element fitted on the threaded rod against the opposite face of the engagement wall from the second fitting, and an arresting means that blocks the spring element. Each centering system comprises a first fitting, which is attached to the structure and has a bore, and a second fitting, which is attached to the visor and bears a shaft that is accommodated in the bore.

Abstract: An acoustic measuring device suitable for performing measurements on a surface in contact with a flow. This acoustic measuring device comprises an acoustic surface delimiting a cavity, which has an axis of revolution, which comprises a recess centered with respect to the axis of revolution, configured to house an acoustic sensor and which, in a longitudinal plane passing through the axis of revolution, follows a logarithmic profile which extends from a first edge separating the recess and the acoustic surface.

Abstract: A method for manufacturing a component by stacking layers of material that are each obtained by depositing and melting, continuously, a material by virtue of an energy beam of which at least one feature is controlled by a control current intensity. The manufacturing method includes a step of monitoring the control current intensity, a step of comparing the monitored control current intensity with a given threshold and a step of stopping the manufacturing method when the control current intensity is above the given threshold. This momentary stopping of the method makes it possible to significantly reduce the risks of energy runaway liable to destroy the deposited material bead and the neighboring structure.

Abstract: A nacelle for an aircraft, including a structure, a cap attached to the structure and a seal system including an arch forming a channel which extends beneath a rear edge of the cap and which has a bottom, the arch being attached to the structure, a seal in the form of a solid block in the channel and beneath the rear edge of the cap, a spring system arranged to move the seal away from the bottom, and a retaining arrangement configured to prevent the seal from leaving the channel under the action of the spring system. With an arrangement of this kind, it is not necessary to oversize the bead, this being replaced with a solid seal mounted on a spring system.

Abstract: A device includes a current difference measurement module for measuring the difference between a current flowing in a positive contact of the electrical installation and a current flowing in a negative contact of the electrical installation, a low-pass filter for filtering the differential current, a full-wave rectifier without threshold module for rectifying the filtered current and a trip module for emitting a trip command when the rectified current is greater than or equal to a predetermined threshold for a predetermined duration. The device thus makes it possible to protect a DC-voltage electrical installation in a noisy environment.

Abstract: A system 100 to detect aircraft ground proximity including: a transmitter 110 for transmitting a radio frequency signal along an extended landing gear 20 of an aircraft 10, a sensor 120 configured to detect a parameter of the radio frequency, and a controller 130 configured to detect a change in the detected parameter on the basis of an output of the sensor 120, and to issue a landing signal when the change in the detected parameter meets a predetermined criterion. The predetermined criterion is indicative of a certain aircraft ground proximity.

Abstract: An aircraft fuselage is configured to receive two tanks designed to contain liquid hydrogen. The fuselage includes a first section for a cockpit, a second section for a passenger cabin and a third section (T3) distinct from the first section (T1) and from the second section (T2). The third section (T3) includes two housings each to house a tank. The two housings are arranged symmetrically with respect to a vertical plane of symmetry (P1). This arrangement of the tanks in a section distinct from the other sections allows them to be located as close as possible to the motors that they have to supply.

Abstract: An aircraft comprising a structure comprising a leakproof tank delimited by walls, of which at least one is in contact with the air outside the aircraft, and filled partly with a two-phase heat-transfer fluid, a fuel cell that is passed through by a heat-transfer fluid, and a line which takes the heat-transfer fluid at an output of the fuel cell and which reintroduces this heat-transfer fluid at an input of the fuel cell. The line passes through the leakproof tank immersed in the heat-transfer fluid in liquid phase.

Abstract: A method and system for determining a position error of an aircraft. The system comprises a set of collection modules implemented in an iterative manner, including an offset collection module, a position vector collection module, a set of sequentially implemented computation modules, including an angular alignment bias computation module, an observable position bias computation module and a position error computation module. The system thus allows a position error to be determined that is used to perform a landing in good conditions.

Abstract: A method for parameterizing a photogrammetric cable robot, having a frame, a mobile platform carrying a camera and cables, each cable extending from a mobile platform attachment point to a position-adjustable exit point, while remaining linked to the frame. The robot's maximum workspace is defined by the ranges of possible positions of the different cable exit points. A set of pairs of setpoint positions and orientations of the platform is determined, for performing the point measurements of a scene by photogrammetry. Then, a genetic algorithm comprising crossing, transformation and selection operations is applied to a population of vectors, each representing respective positions of cable exit points, the selection being made via a fitness function involving a first objective function evaluating a collision percentage and a second objective function evaluating a percentage violation of a mobile platform constraint of equilibrium, when the platform assumes the different setpoint positions and orientations.

Abstract: An engine pylon has a primary structure fastened between an engine and an aircraft wing and a cowling system having a front set of fixed cowls, a rear cowl, a displacement system having a first structure as one with the rear cowl and having a first slide mechanism, and a second structure fastened to a fixed structure of the wing and having second slide mechanism. The slide mechanisms cooperate so as to realize a sliding connection and to move the rear cowl in translation from an advanced position to a retracted position. An immobilizing system locks the rear cowl in the advanced position.

Abstract: An enhanced flight vision system for an aircraft includes an image acquisition system configured to acquire images of the surroundings outside the aircraft and a display system configured to receive images produced by the image acquisition system and to display these images on a display in the cockpit of the aircraft. The display system is configured to acquire information about the flight path angle of the aircraft when approaching a runway, to calculate a difference between the flight path angle of the aircraft and a nominal angle and to deactivate the display of the images received from the image acquisition system on the display when the absolute value of the difference is greater than a first angular value.

Abstract: A switching device including at least one main breaker, an actuator configured to cause a change of state of the main breaker, from a first to a second state, counter to a spring generated force, the actuator being powered by a control signal equal to a first level to cause the change of state of the main breaker then to a second, lower level, to hold the main breaker in the second state. The switching device comprises a current sensor configured to control the control signal to increase it to a third level higher than the second level if the current flowing in the main breaker is higher than or equal to a given operating threshold, to avoid a spurious change of state of the main breaker. The switching device comprises a re-armable protection system for controlling the time for which the control signal is held at the third level.

Abstract: An aircraft including two main landing gears and also a main landing gear bay configured to house, on either side of a vertical median plane, the two main landing gears in a retracted position, the main landing gear bay including a rear transverse wall, a front transverse wall and also an end wall that is approximately perpendicular to the rear and front transverse walls. The main landing gear bay includes at least one strut connecting the rear or front transverse wall and the end wall, approximately positioned in the vertical median plane.

Abstract: A hydrogen storage system comprises a hydrogen tank and a system for controlling hydrogen evaporation in the hydrogen tank. This control system comprises a hydrogen discharge pipe connected to the hydrogen tank, on the one hand, and to a controllable valve, on the other hand, as well as a processing unit configured to control the valve as a function of the pressure in the tank. The hydrogen storage system further comprises a fuel cell permanently connected to the hydrogen tank and the processing unit being electrically powered by the fuel cell.

Abstract: An assembly having a pylon with an upper spar and two lateral scoops, a wing with a skin and a front spar, port-side/starboard-side front/rear brackets, each with a recess for a nut. The front spar has front/intermediate/rear pleats. Each front bracket is positioned against the front pleat and the intermediate pleat. Each rear bracket is positioned against the intermediate pleat and the skin. For each recess, the associated bracket has an open bore passing through it that opens into the recess. For each recess, the assembly has a fastening bolt having the nut and a screw of which the threaded shank passes through coaxial bores in the front pleat, in the skin, in the upper spar and in the associated lateral scoop, and the open bore, and is screwed into the nut, and of which the head bears against the lateral scoop.

Abstract: An aircraft fuselage portion extending in a general longitudinal direction and comprising a fuselage structure comprising annular frames and a flat floor. The fuselage portion also comprises struts perpendicular to the floor in a nominal position and extending from the floor to a frame. Each strut comprises, in the vicinity of at least one of the ends thereof, a detachable link so that the strut can be moved relative to the fuselage structure or separated from the fuselage structure to temporarily grant access to a triangle area located between the frames, the floor and the struts in the nominal position. This allows access to be granted to the area in which the ducts must be installed in the aircraft, in particular, in the form of sets of ducts assembled prior to their installation in the fuselage.

Abstract: A mixing device for mixing a first video signal and a second video signal to form a third video signal, the device comprising electronic circuits configured such that the third video signal is representative of the first video signal when the amplitude of a control signal is lower than a first predetermined threshold, such that the third video signal is representative of the second video signal when the amplitude of the control signal is greater than a second predetermined threshold, or else such that the third video signal is representative of a combination of the first and second video signals when the amplitude of the control signal lies between the two predetermined thresholds or is equal to one of them. A mixing method is performed by the abovementioned mixing device.

Abstract: A method and system for estimating an angular deviation from a reference guidance axis, a position and a velocity of an aircraft. The system includes an offset collection module for collecting an offset measured by a measurement module, a position vector collection module for collecting a position vector measured by a position vector measurement module, a velocity vector collection module, a module for estimating the angular deviation of a reference guidance axis with respect to the approach axis towards the runway, for estimating the position of the aircraft with respect to the runway and for estimating the velocity of the aircraft with respect to the runway.

Abstract: An electrical connector provided with at least one male or female plug configured to be connected to a socket. The electrical connector includes at least one locking system provided with a polarized ferromagnetic locking element and with a return element, which are configured to have a first shape corresponding to a locking configuration of the electrical connector that is at least partially complementary to a shape of the connection plug or of the socket when an intensity of a current flowing through the connection plug is higher than or equal to a predetermined value, and a second shape corresponding to a non-locking configuration of the electrical connector when the intensity of the current flowing through the connection plug is lower than the predetermined value, so as to electromechanically lock the connection plug in the socket of the connector.