Abstract: A cover panel for an aircraft including: a first region, a second region for forming an overlap with a second panel, and a ramp, wherein at least a portion of the ramp is between the first and second regions, wherein the ramp includes a tapered region such that a width of the ramp tapers towards a free-edge of the first region, and wherein the free-edge is configured to form a butt-joint with the second panel.

Abstract: A propulsion unit, for an aircraft, comprising a hollow chassis with an opening at the bottom, a propulsion system comprising an electric motor with a propeller, a fuel cell, a tank and a cooling system, and one platform fastened to the chassis through said opening using fasteners and in which at least one element of the propulsion system is fastened to the platform. An aircraft with such a propulsion unit.

Abstract: A wing tip device for a fixed wing aircraft is disclosed having an alular-like projection, a first leading edge region having a first sweep angle, a second leading edge region outboard of the first leading edge region in a spanwise direction and having a second sweep angle greater than the first sweep angle, a third leading edge region outboard of the second leading edge region in the spanwise direction and adjacent a tip end of the wing tip device and having a third sweep angle greater than the first sweep angle. The second leading edge region is adapted to generate a first vortex, and the third leading edge region is adapted to generate a second vortex which builds towards the tip end of the wing tip device.

Abstract: A protective tarpaulin for a propulsion engine of an aircraft is made of a material having an air permeability index that is sufficiently high to prevent the accumulation of moisture inside the engine or a nacelle surrounding the engine.

Abstract: A wing (3) for an aircraft (1) including a main wing (5) and a trailing edge high lift assembly (9) movably arranged at a trailing edge of the main wing (5). The trailing edge high lift assembly (9) includes a flap (11) and a connection assembly (13) movably mounting the flap (11) to the main wing (5). The connection assembly (13) includes an actuator unit (35) moving the flap (11) between a retracted position and at least one extended position. The flap (11) includes a leading edge part (23) and a trailing edge part (27) mounted to the leading edge part (23) pivotable about a pivot axis (31).

Abstract: A device for connection of double-wall pipes including an interior connection system connecting the first and second interior pipes and an exterior connection system including a first part that cooperates with an end section of the first exterior pipe and a second part that cooperates with an end section of the second exterior pipe. The exterior connection system is configured so that at a first temperature at least one of the first and second parts exerts a contact force on the end section of the corresponding first or second exterior pipe greater than at a second temperature higher than the first temperature.

Abstract: A tank system comprising a tank, a drainage line fixed in the bottom part of the tank and having a drainage port at each end and, for each drainage port, a funnel having a wall through which at least one window passes, a body that can move in translation, for each funnel, a plug that is secured to the body and arranged to be able to move inside said funnel between an open position and a closed position, and an arm, a first end of which is mounted in an articulated manner to the top part of the tank and a second end of which is mounted in an articulated manner on the body.

Abstract: In order to improve liquid hydrogen storage on aircraft, a liquid hydrogen tank is integrated into the fuselage of the aircraft. At least one portion of the tank wall is formed by specially adapted tank skin panels and/or a pressure bulkhead. The parts forming the tank wall are strengthened to contain a tank pressure of about 3 bar.

Abstract: A power control unit configured to supply hydraulic pressure and mechanical torque. To this end, the power control unit includes an electric motor coupled to a differential output transmission and a hydraulic pump. A switchable transmission device allows the torque of the motor to be redirected either to the output transmission, e.g., to drive high-lift devices, or to the hydraulic pump, e.g., to extend or retract landing gears.

Abstract: A DC electrical network intended to supply electricity to an electrical load via an electric power source. A first pole of the electric power source is linked to first ends of two first electrical lines, second ends of which are linked to one another, and also to a first pole of the electrical load via two stages of a contactor. A second pole of the electric power source is linked to first ends of two second electrical lines, second ends of which are linked to one another, and also to a second pole of the electrical load via two other stages of the contactor. The electrical network further comprises a processing unit configured to control the contactor to open if current measurements correspond to currents flowing in opposite directions through the two first electrical lines or through the two second electrical lines.

Abstract: A method for ultrasonic inspection of composite parts includes providing a composite part to be inspected with a plurality of layers, determining the runtime and/or attenuation of an ultrasonic signal propagating through the composite part to be inspected, providing the runtime and/or attenuation of the ultrasonic signal propagating through a reference composite part, subtracting the runtime and/or attenuation of the ultrasonic signal in the reference composite part from the runtime and/or attenuation of the ultrasonic signal in the composite part to be inspected, or vice versa, and determining from the result of the subtraction one or more missing and/or additional layers in the inspected composite part. The difference of the runtime and/or attenuation of the ultrasonic signal in the inspected composite part relative to the reference composite part, and/or the difference of the thickness between the composite part and the reference part, is/are visualized.

Abstract: The disclosure concerns a wing for an aircraft including a main wing and a trailing edge high lift assembly movably arranged at a trailing edge of the main wing, the trailing edge high lift assembly having a flap and a connection assembly movably mounting the flap to the main wing, such that the flap is movable between a retracted position and at least one extended position. The connection assembly includes an actuator unit for moving the flap between the retracted position and the at least one extended position. The flap includes a leading edge part and a trailing edge part mounted to the leading edge part in a manner pivotable about a pivot axis.

Abstract: A connector, a connector assembly, an aircraft fuel breather system and an aircraft wing are disclosed. The connector connects a breather pipe or float valve to a hat section stringer duct attached to an aircraft panel. The connecter has a bridge to bridge over the duct and to cover an aperture in a wall of the duct. The bridge has a flange on either side for attachment of the connector to the panel. The connector has a seal to seal the bridge to the duct, an aperture defined in the bridge and a flow controller connector to connect and provide fluid connection between the connector and pipe or float valve. The assembly comprises the connector, the duct and aircraft panel and the fuel breather system includes one or more fuel tanks, a breather pipe and a vent to atmosphere.

Abstract: A method for monitoring an engine of an aircraft supplied with dihydrogen, comprising a safety device including a safety valve that is movable between an open position in which the engine is supplied with dihydrogen and a closed position in which the engine is no longer supplied with dihydrogen, an engine fire detection system, a dihydrogen leak detection system and an engine damage detection system, and comprising electronic circuitry adapted to implement the monitoring method. If a locking authorization is given and if one out of three conditions A, B and C is true, then the safety device closes the safety valve, with: the condition A is true if an engine fire detection system detects a fire, the condition B is true if a dihydrogen leak detection system detects a dihydrogen leak, and the condition C is true if an engine damage detection system detects engine damage.

Abstract: A buffer for storing liquid at a consumer pressure includes a storage volume for holding a liquid and a gas. The storage volume may be separated by a partition element into a liquid compartment for holding the liquid and a gas compartment for holding the gas. A pressurizer is configured for increasing the pressure of gas in the storage volume to an operating pressure when liquid is or has been drained from the storage volume. A ventilator reduces the pressure of gas in the storage volume back to the operating pressure when the storage volume is filled with liquid. A water supply system for an aircraft including the buffer and an aircraft including such a water supply system are disclosed.

Abstract: A method for operating an on-board water supply and distribution system of an aircraft for supplying water includes a central water tank, first consumer assemblies with buffer tanks each including a heater to heat up water in the buffer tank to a disinfection temperature, pump having upstream and downstream sides to operate in supply and reverse modes, and high-pressure conduit system. The central water tank connects to the pump's upstream side. The conduit system connects the downstream side with a first consumer assembly. The method includes operating the pump in supply mode where water from the central tank goes to a first consumer assembly to fill a buffer tank, operating a buffer tank heater so water heats to a predetermined disinfection temperature, and operating the pump in reverse mode so heated water passes through a part of the conduit system and the upstream side of the pump.

Abstract: A system for producing a component or semifinished product with a fibre-reinforced foam core, includes a substrate on which the foam core having a first main surface and an opposite second main surface is to be laid; a sewing device having a needle configured to be moved at least linearly; a fibre supply device for three-dimensional supply of a fibre; and a coating device. The sewing device is configured to position the needle at the first main surface and to pierce the foam core, such that a needle tip penetrates through the first main surface and then through the second main surface. The fibre supply device is configured to position a reinforcing fibre such that the reinforcing fibre is hooked into the needle tip. The coating device is configured to coat a reinforcing fibre hooked into the needle tip with resin immediately before the reinforcing fibre enters the foam core.

Abstract: A method for applying a corrosion protection layer to a surface to be protected of a component including providing the corrosion protection layer having a first surface and a second surface arranged opposite this, laying the first surface of the corrosion protection layer on a bottom face of a mold, laying the surface to be protected of the component on the second surface of the corrosion protection layer so as to enclose a layer of hardenable sealing compound, closing the mold by applying a bend-flexible cover so as to enclose the corrosion protection layer and the component, evacuating the mold so that the cover presses the component in the direction of the corrosion protection layer, and removing the vacuum and the cover after hardening of the sealing compound.

Abstract: An automatic trajectory generation system bringing a flying aircraft from a current position to a destination which: obtains polygons representing obstacles potentially encountered, each polygon associated with an altitude layer; defines two first tangential circles relative to a current direction of the aircraft flight, centered on the right and the left, relative to the aircraft current position; defining two second circles tangential relative to a direction to be followed to destination, centered on the right and the left, relative to the georeferenced destination position; defines a third circle around vertices of the polygons; and searches for a flyable lateral trajectory between the aircraft current position and the destination by bypassing the polygons by the vertices in searching for tangential trajectories between the circles, by observing a pre-established vertical trajectory profile, as well as the lateral margin and a vertical margin with the polygons.

Abstract: A method for removing a two-part connector in a workpiece arrangement includes providing a workpiece arrangement having first and second surfaces and having a hole connecting the first surface to the second surface. A connector is fastened in the hole, which connector has a bolt extending along a central axis and a sleeve fastened on the bolt. The bolt has a head portion and a shank portion with retaining grooves. The sleeve is fastened to the bolt on the side of the second surface such that the inner surface thereof engages with the retaining grooves and prevents a relative movement of bolt and sleeve parallel to the central axis. The sleeve has an outside diameter which is greater than the diameter of the hole in the workpiece arrangement. The sleeve is cut and or the bolt, and the connector is removed from the hole.