Abstract: A brake temperature sensing system for an aircraft including a sensor apparatus and an interrogation apparatus. The sensor apparatus includes a temperature sensor for attachment to a brake disc of an aircraft brake, and a relay for attachment to the brake. The temperature sensor is configured to wirelessly transmit a measurement signal containing information relating to a temperature of the brake disc, responsive to receiving a wireless interrogation signal. The relay is configured to receive an interrogation signal from the interrogation apparatus; wirelessly transmit the interrogation signal to the temperature sensor; receive the wireless measurement signal from the temperature sensor; and transmit the received measurement signal. The interrogation apparatus comprises a controller configured to generate an interrogation signal; and a transceiver configured to transmit the generated interrogation signal to the sensor apparatus; and receive the measurement signal transmitted by the sensor apparatus.

Abstract: A thrust reverser system with a thrust reverser cascade and a reverser door with door segments laid out in a folded condition relatively to each other in an inactive configuration of the reverser system, and accommodated in an accommodation space located outside the secondary channel. Upon passing from the inactive configuration to the active configuration a rearward displacement of the cascade towards a nacelle aperture, released by an external movable nacelle cowl driven rearwards by the cascade, and a deployment of segments until they attain a deployed closing position within the secondary channel occurs simultaneously.

Abstract: A crocodile-type flight control surface comprising an upper foil flap, a lower foil flap, an actuating mechanism which guarantees the rotational displacement of each foil flap about a joint axis, either in the same direction or in different directions, and a locking mechanism alternatively adopting a locking position in which the upper foil flap and the lower foil flap are fixed with respect to each other and an unlocking position in which the upper foil flap and the lower foil flap are free with respect to the other. A crocodile-type flight control surface of this kind is therefore stiffened by the locking mechanism that joins the two foil flaps.

Abstract: An aircraft turbomachine comprising a fan conduit with a wall, a flow of air passing through the turbomachine via the fan conduit. An air passage comprising an air opening is arranged in the wall, the air passage configured to receive a portion of the flow of the air through the fan conduit. A deflector is fixed to the wall upstream of the air opening, the deflector comprising at least one cross-section extending in the fan conduit to capture the flow of air. The at least one cross-section is porous. The deflector protects the air passage structure and is easy to produce and to fix to the wall of the fan conduit when it is screwed or riveted directly thereto. The deflector, as a result of its location in the fan conduit, is easy to access and thus allows rapid maintenance operations without having to disassemble the air passage.

Abstract: A rudder bar includes a main module provided at least with pedals and with all the elements subject to maintenance, the main module being one-piece and detachable relative to a support frame integrated into the floor of the cockpit of the aircraft, so as to exhibit significant flexibility with respect to its maintainability, particularly in the event of the failure of a component, by allowing quick intervention both on a local level and an overall level.

Abstract: A method for aiding the landing of an aircraft on a landing runway comprises the following steps implemented automatically by a processing unit: a) acquiring information relating to the runway; b) acquiring information relating to a current situation of the aircraft; i) determining a landing position of the aircraft on a central longitudinal axis of the runway, as a function of a trajectory determined between a current position of the aircraft and this landing position to comply with at least one constraint relating to a roll angle of the aircraft; j) determining a parameter relating to the landing position; k) determining a deviation between this parameter and a reference value; l) comparing this deviation with a predetermined threshold; and m) as a function of the result of the comparison carried out in step l), commanding, if appropriate, the signaling of an alert via the signaling system of the aircraft.

Abstract: A method and tool for repairing a damaged zone of an aircraft radome, using the actual radome itself as a heating chamber to avoid resorting to an autoclave and the removal of certain parts of the radome which cannot withstand the curing temperature needed for the repair. The method for repairing a radome, wherein the radome comprises a composite panel exhibiting a double curvature forming a dome, the panel comprising at least one damaged zone, comprises the steps of closing an interior space of the panel using a cap to form a repair chamber. The surface of the panel forms the repair chamber containing the damaged zone. Another step is heating the space inside the repair chamber to form a heating chamber allowing the curing expected for repairing the damaged zone.

Abstract: A device for visually scaring animal species, in particular bird species includes means for generating at least one visual signal including at least one image, varying in size over time, which simulates approach via an increase in the size of the image. For example, the visual signal includes one of the following images: eyes, a disc, and a spiral.

Abstract: The rudder bar includes two actuation arrangements, each provided with two pedals, each actuation arrangement having a frame provided with two rails arranged on either side of said frame and being in the form of a concave curve, and, associated with each one of said rails, a movable carriage, each one of said movable carriages bearing one of said pedals, each one of said movable carriages being configured such that it can be moved on the associated rail, for a direction command, under an action exerted by at least one foot of a pilot on at least one of said pedals.

Abstract: A landing gear box of an aircraft comprising a front door with independent opening and a rear door with opening mechanically connected to the landing gear, including an orifice in the rear door provided with a closure member and a drive mechanism allowing movement of this closure member independently of any movement of the rear door.

Abstract: An engine assembly comprising an engine and a pod surrounding the engine that is equipped, upstream according to the direction of entry of air into the engine, with a fan provided with blades, the pod having an upstream air intake. The engine assembly also comprises a display unit including at least one light ring arranged in the air intake upstream of the fan, the light ring including at least one row of light-emitting diodes and being configured to emit at least one light beam and to project it on the blades of the fan.

Abstract: An on-board system for evaluating the severity of a lightning strike, intended to be installed in the interior of an airplane and connected to an avionic system of the airplane. The system comprises four devices, a master device and three slave devices, each device comprising a magnetic-field sensor. The devices are placed pairwise symmetrically about a plane of symmetry of the airplane, vertically in line with the leading edge of the wing of the airplane and vertically in line with the trailing edge of the wing, respectively. The system allows an evaluation of the severity of a lightning strike to be obtained depending on the measured magnetic fields.

Abstract: An aircraft wing, including a main part and a wing tip mounted mobile in attack relative to the main part.

Abstract: A clip for fastening a pipe to a support, comprising a fixed part, a mobile part, a first joint connecting a first edge of the fixed part and a first end of the mobile part, and a system for holding the mobile part a closed state. The system comprises a lever and a second joint connecting the lever to a second end of the mobile part, and an angled U-shape connected to the second edge of the fixed part, configured to permit the lever and the second joint to pass through the angled U-shape and to permit the lever to be positioned in a folded position against an external face of the mobile part to hold the mobile part in the closed state.

Abstract: A pipe assembly includes two pipes connected together by a joining device and a drainage system, the drainage system includes a drainage slot created in the joining device, two annular seals arranged on either side of the drainage slot over the entire periphery around a pipe, and a drainage element configured to send fluid present in the drainage slot from a first end entering the drainage slot to the other end of said drainage element.

Abstract: A fuel system which includes a fuel return system. The fuel return system includes a fuel return valve arranged on a return line, and the return line is intended to be mounted between an engine of an aircraft and a fuel tank of the aircraft. The return valve is configured to allow a return of fuel from the engine to the fuel tank when the engine is in operation. The fuel return system also includes a bypass valve assembly mounted in parallel to the return valve, and is configured to allow a return of fuel from the engine to the fuel tank when the engine is not in operation.

Abstract: The transmission of flight instructions from a ground unit to an aircraft comprising an onboard system. The ground unit is configured to generate, on the basis of flight data intended for the aircraft, at least one optical symbol containing a flight instruction. The onboard system comprises an optical reader and a flight management system. The optical reader is configured to read the optical symbol and to transfer the flight instruction contained in the symbol to the flight management system to prepare the flight of the aircraft.

Abstract: An aircraft engine unit comprising an engine, a mast and an engine connection connecting the engine and the mast. The aircraft engine unit includes a front engine attachment of the engine connection which comprises at least one front rod connecting the primary structure of the mast and the core of the engine and which assures the take-up of vertical forces, and at least one connection connecting the primary structure of the mast and the fan casing of the engine and which assures the take-up of forces that are horizontal and perpendicular to the axis of rotation of the engine and/or a torque about the axis of rotation of the engine.

Abstract: A method for optimizing the take-off parameters of an aircraft. The aircraft comprises a system for automatically controlling the high lift devices at the moment when the wheels of the aircraft leave the ground. The method comprises a step of selecting a first configuration of the high lift devices at the start of the take-off phase and a selection of an acceleration speed of the aircraft. The method is advantageous in that, on reception of an actual aircraft take-off detection signal, a control unit is configured to transmit a control command making it possible to bring the high lift devices into a second configuration, in which they are retracted relative to the first position, and consecutively accelerate the speed of the aircraft automatically to an acceleration speed entered by the pilot.

Abstract: In an aircraft comprising a cockpit comprising a display screen, a camera configured to acquire images of the environment of the aircraft, as well as a display management system, a ground rolling aid system configured so as to a) acquire several successive images of the environment of the aircraft via the camera, corresponding to various ground positions of the aircraft, b) modify these images by removing at least zones corresponding to the aircraft, so as to produce modified images, c) combine several of the modified images to produce a recomposed image, d) superpose an image characteristic of the aircraft on the recomposed image so as to produce a reference image, and e) display, on the cockpit display screen, an image corresponding to the reference image.