Abstract: A simple and lightweight system for discharging water that can flow out through an orifice in an insulation blanket lining the walls of a fuselage of a transport vehicle such as an aircraft. The blanket has an impermeable collection plate having at least partially the shape of a channel, container or the like for collecting and discharging condensation water under the effect of gravity through an orifice.

Abstract: Method and device for manufacturing a component from a plate made of deformable material, in particular for an edge of an element of an aircraft. The device includes a tool with two tool parts configured to be able to move closer to one another and are able to round a plate made of deformable material fixed to the two tool parts, a mold at the periphery of the tool and including a molding cavity of a shape corresponding to the shape of the component that is to be manufactured, and a displacement system configured to press the rounded plate firmly against the molding cavity of the mold, the mold being able to shape the rounded plate when it is pressed firmly against the molding cavity to give it its definitive shape, the device allowing the manufacture of single-piece components of varying sizes and notably large-sized components and/or deep components.

Abstract: A braking system and a method for applying one or more aircraft wheel brakes according to at least one of a plurality of wheel brake control functions are disclosed. The method includes receiving an indication of an aircraft speed from an aircraft speed indicator, controlling a wheel braking operation of the aircraft according to at least a first wheel brake control function if the aircraft speed indicated by the aircraft speed indicator exceeds a speed threshold, and controlling the wheel braking operation of the aircraft according to at least a second wheel brake control function if the aircraft speed does not exceed the speed threshold. Also disclosed is an aircraft including one or more aircraft wheel brakes and the disclosed braking system.

Abstract: A propulsion assembly includes an engine below a pylon by engine attachments, including a thrust force uptake device, the engine having a longitudinal axis and a vertical median plane parallel to the longitudinal axis, the thrust force uptake device having a main fitting fixed below the pylon and two links disposed on either side of the vertical median plane and which each have a rear end articulated to the main fitting by a spreader mounted to pivot on the main fitting about an axis of rotation which, on the one hand, is orthogonal to a mean plane for transmitting thrust forces parallel to the longitudinal axis of each of the links, and which is disposed in the vertical median plane, each link being articulated to the spreader by a connecting pin extending parallel to the mean plane for transmitting thrust forces and perpendicular to the longitudinal axis of the link.

Abstract: A method for detecting potential dents in a surface includes providing a flying drone with an image acquisition device and a light source, the shape of which is elongate, and a data processing device. At least one series of images is acquired of portions of the surface by the image acquisition device by moving the flying drone past the surface along a trajectory so that, for each image of the series, the light source is illuminating the corresponding portion of the surface. The data processing device is operated to analyze the shape of a specular reflection of the light source in images of the series of images to estimate the position of any dents in the surface.

Abstract: A turbofan with a sliding element, rotary blades that can rotate between stowed and deployed positions, and a maneuvering system which moves each blade when the sliding element moves and which includes, for each blade, a rotary main shaft, for each main shaft, a transmission lever rigidly secured to the main shaft, at least two connecting strips articulated to one another, wherein each connecting strip is associated with at least three main shafts, the transmission levers of which are articulated to the connecting strip, and a drive system which rotates the first connecting strip when the sliding element moves. The use of rotary blades on the sliding element and the simplified maneuvering system makes the assembly more lightweight compared to the use of conventional reverser doors.

Abstract: A flying drone for inspecting surfaces able to reflect light has a lighting device formed of two light sources each having a shape that is elongate in a longitudinal direction of each of the light sources, two first image acquisition devices, and a second image acquisition device between the two first image acquisition devices. The two light sources are respectively between the second image acquisition device and each of the first image acquisition devices. The flying drone allows effective detection of dents in surfaces by analyzing specular reflections, by the lighting device and of the first image acquisition devices, and effective detection of superficial defects on surfaces by the second image acquisition device, with the lighting device switched off.

Abstract: To simplify architecture of a measurement device for affixing to a wall of a moving object or stationary object located in a flow, a device includes a support having compartments with an opening that opens to the exterior of the support at the free face in which sensors are housed, the support having a free face and a face to come into contact with the wall, the free face being opposite the face. The device includes a cavity with a printed circuit board, the compartments including an opening that opens to the exterior of the support in the cavity. The cavity is made in the free face opening into it. The circuit board is upside down in the cavity with the printed face towards the interior of the support. The sensors attached to the circuit board are suspended in the compartments. The unprinted face affords an aerodynamic smooth and planar surface.

Abstract: An assembly includes a structure with 6 o'clock and 12 o'clock beams and front and rear curved beams, in which the 12 o'clock beam is mounted to be able to rotate on a pylon of an aircraft between a closed position and a raised position, a fan cowl fixed to the structure, a thrust reverser with a rear cowl and that is able to move in translation along the 6 o'clock and 12 o'clock beams between a forward position and a backward position, cascades fixed to the thrust reverser, and a mover for moving the thrust reverser. With such an arrangement, the fan cowl and the thrust reverser are fixed to the same structure, and it is this structure that is hinged to the pylon.

Abstract: A forward secondary structure for a mounting pylon for a turbomachine, the forward secondary structure extending from upstream to downstream along a longitudinal axis and having a chassis clad with an aerodynamic fairing. The aerodynamic fairing includes two adjacent cowls each having an upstream portion, where each of the cowls extends lengthwise along the longitudinal direction and includes in its upstream portion a system for articulating the cowl to the chassis, by which system the cowl can pivot with respect to the chassis about an axis of rotation normal to the longitudinal axis, between a closed position in which all of an inner face of the cowl is pressed against the chassis and an open position in which the cowl frees up an opening in the forward secondary structure.

Abstract: An acoustic panel for an aircraft nacelle includes, from a central axis of the nacelle to the exterior thereof, a resistive skin perforated with sound-absorbing micro-perforations, a first attenuation stage, a septum perforated with holes, a second attenuation stage, and a back skin configured to provide the mechanical strength of the acoustic panel. The septum is a planar wall having a thickness greater than that of the resistive skin, preferably greater than 4 mm. Such a panel is configured to attenuate several frequency ranges one of which being a low-frequency range, while optimizing the weight, the cost and the air intake functions. The thickness of the septum, the dimensions of the holes in the septum, the OAR of the septum and the height of the second attenuation stage are adjusted to match the mean attenuated low frequency to the vibration frequency of the aircraft engine.

Abstract: Use of a hydrogen tank of a vehicle such as an aircraft for protecting at least one electrical connection device linked to at least one electrical device. At least one connection device is placed in a tank or in a sealed enclosure supplied with hydrogen by a tank or by any other source of hydrogen supply of the vehicle. The use of a tank that already exists in the vehicle makes it possible to avoid having to use specific chambers incorporated in a complex manner with the connection device.

Abstract: A control system for an aircraft includes a hydraulic pump, first hydraulic line, second hydraulic line, a first actuator coupled with a first control surface, a second actuator coupled with a second control surface, and a third actuator coupled with a third control surface. The first control surface and the second control surface are at a distance to each other and symmetrically relative to a symmetry axis. The third control surface is substantially on the symmetry axis, and the first hydraulic line and the second hydraulic line are connected to the hydraulic pump. The first actuator is connected to the first hydraulic line, and the second actuator is connected to the second hydraulic line. The third actuator is connected to the first hydraulic line downstream of the first actuator at a junction point, and the first hydraulic line at least partially includes a larger diameter than the second hydraulic line.

Abstract: A main electrical cabling is subject to variations in ambient temperature over its length. A detection system for detecting a fault in the main electrical cabling able to cause a serial arc, or heating within a connection, includes a monitor electrical cabling placed alongside the main electrical cabling and a controllable current generator injecting, at the input of the monitor electrical cable, a current proportional to the current flowing through the main electrical cabling. The main and monitor sets of electrical cabling being joined at the output, an electronic circuitry measures the difference between the electrical potential at the input of the main electrical cabling and that at the input of the monitor electrical cabling and detects a fault in the main electrical cabling when the difference of the electrical potentials exceeds a predefined threshold. A fault in the main electrical cabling is detected despite the variations in temperature.

Abstract: A gripping device for a panel of a section of a fuselage of an aircraft, the panel including a skin and having an arcuate shape about a longitudinal axis X. The gripping device includes two gripping subsystems arranged at a distance from one another parallel to the longitudinal axis X, and each gripping subsystem includes a central element fastened to the panel, and two lateral elements fastened on either side of the central element by fasteners, and each lateral element includes pressurizers which come against the skin to apply a tension thereto in the opening direction of the arcuate shape. Such a gripping device makes it possible to ensure the shape of the panel when it is transported and until it is fastened to other panels in order to produce the section of the fuselage.

Abstract: A hinge assembly 8a for an aircraft component including first and second hinge plates 9, 10, having an aerodynamic surface. A first seal assembly 28 to 32 is provided and arranged to seal between the aerodynamic surfaces of the hinge plates. A second seal assembly 38 to 42 is arranged to seal between the undersides of the hinge plates in order to reduce pressure leakage between voids under the hinge. The provision of two seal assemblies, each having a dedicated function, addresses the competing demands made on the sealing arrangement of an aircraft hinge assembly in use.

Abstract: An aircraft propulsion unit includes a drive unit with a static part and a rotary part which rotates a fan situated downstream from the drive unit, an assembly of fixed blades situated downstream from the fan, and a nacelle in which the fan and the assembly of fixed blades are accommodated. The propulsion unit also includes an assembly of at least two coaxial shafts, wherein a fan shaft connects the fan to the rotary part, and a stator blading shaft connecting the assembly of fixed blades to the static part extends concentrically, and for at least part of its length in the interior of the fan shaft. This rigid and compact configuration limits the variations of distance between the end of the fan blades and a fan housing situated in the inner duct of the nacelle.

Abstract: A module includes two main landing gears and a landing gear bay containing the landing gears. The bay has two lateral walls, a roof wall, a front wall and a rear wall. The roof wall, the front wall and the rear wall together form a pressurization barrier between the bay and a pressurized compartment. By virtue of the landing gear module, it is now possible to assemble and test the main landing gears and the one or more doors and the fairing before they are installed on the aircraft.

Abstract: An aircraft with at least one propulsion assembly and its fire-fighting system, which includes two reservoirs of extinguishing agent, and, associated with each reservoir, a control that can be actuated by a pilot to open the reservoir, a detection assembly to detect a fire and emit, if appropriate, a fire alert signal, the propulsion assembly including a first and a second compartment each including at least one fire zone, the fire-fighting system including a bypass valve controlled by a localization unit, a set of pipes connecting each reservoir to each of the fire zones through the bypass valve, the localization unit configured to detect a fire in a fire zone in the first compartment, and, if appropriate, control the bypass valve so it adopts a first state where the extinguishing agent in a reservoir is expelled towards the one or more fire zones in the first compartment after activation of the control associated with a reservoir, the bypass valve otherwise being controlled to adopt a second state, in which

Abstract: A method and system allowing fully autonomous automatic take-off using only images captured by cameras on the aircraft and avionics data. The system includes an image capture device on the aircraft to take a stream of images of the runway, image processing modules to estimate, on the basis of the streams of images, a preliminary current position of the aircraft on the runway and to assign a preliminary confidence index to the estimate. A data consolidation module can determine a relevant current position of the aircraft on the runway by consolidating data originating from the image processing modules with inertial data to correct the estimate of the preliminary current position and determine a relevant confidence index using a current speed of the wheels of the aircraft to refine the preliminary confidence index. A flight control computer can control and guide aircraft take-off.