Abstract: A bipolar plate for a proton exchange membrane fuel cell includes a laminate of carbon fiber reinforced plastic (CFRP) with a first outer ply. The CFRP includes a resin and carbon fibers. The first outer ply is arranged at a first lateral surface of the laminate, wherein the laminate includes a first plurality of carbon nanotubes (CNTs). The first outer ply includes a first groove, wherein the first groove is configured to define a first gas diffusion channel. At least some of the first plurality of CNTs extend through the first outer ply in a direction transversely to the first lateral surface of the laminate.

Abstract: A propulsive assembly comprising a nacelle delimiting an internal volume, a T-shaped frame comprising a first wall fixed to the wing and a second wall that is vertical and that divides the internal volume into two sub-volumes, a dihydrogen consumer device, for each sub-volume, a dihydrogen processing system, a supply line connected between the processing system and the consumer device, and an input line connected between the processing system and a dihydrogen tank. Also an aircraft with a wing and such a propulsive assembly.

Abstract: A wing assembly (5) including: a fixed wing portion (7), a first high-lift device (9), a first connecting assembly (19) which allows the first high-lift device (9) to move between a retracted position and an extended position, a second high-lift device (11), a second connecting assembly (21) which allows the second high-lift device (11) to move between a retracted position and an extended position, a drive unit (23) attached to the fixed wing portion (7), and a drive assembly (25) having a first portion (27) is attached to the drive unit (23) and a second portion (29) attached to the second high-lift device (11), wherein the drive unit (23) moves the second high-lift device (11) via the drive assembly (25) between the retracted position and the extended position.

Abstract: An extinguishing device for an electrical unit on an aircraft cabin monument or in an aircraft structure cavity, a combination of a holder and an extinguishing device and systems formed by extinguishing devices and a control unit and by combinations of an extinguishing device and a holder and a control unit. The extinguishing device has a base element for a holder. An extinguishing agent container has a casing and holds an extinguishing agent. A triggering device is connected to the extinguishing agent container to act in response to receiving a triggering signal wherein an extinguishing agent is released into the extinguishing device surrounding area. A data transmission device has a data store with an identifier unique to the extinguishing device and connected to the triggering device, the data transmission device for sending a warning signal via a network to a control unit in response to the triggering device receiving the triggering signal.

Abstract: A method for manufacturing an aerodynamic structure including a first panel having an aerodynamic face, as well as a second reinforced panel. The method includes a step of stamping the second panel to obtain at least one raised shape which is recessed on the second face, and a step of joining the first and second panels by pressing them against each other outside the at least one raised shape. An aerodynamic shape is obtained using this method.

Abstract: A method for securing a geographical area encompassing a route. A map of the area is obtained. A weapon is associated with a firing modeling consisting of a probability model of hitting its target when shooting, as a function of the firing distance. Positions of potential shelters of threats on the map are determined by using a trained artificial intelligence device. The modeling is applied for each weapon and potential shelter while relating the shots to the route and summing all the probabilities of hitting its target on each portion of the route. The potential shelters most likely to constitute attack threats along the route are determined. A path is defined in order to address these potential shelters most likely to constitute attack threats.

Abstract: A method for installing a screw in at least one through-orifice of a box-type structure, including inserting a body of a first tool into the through-orifice from an external region of the box-type structure, moving the body in an internal region of the box-type structure, towards an end of the box-type structure, securing the screw to the body, the first tool comprising a link connected to the body which remains accessible from the external region during the inserting, moving and securing steps, pulling on the link from the external region until the shank of the screw is positioned in the through-orifice, and separating the body from the screw.

Abstract: An aircraft nacelle equipped with a thrust reversal device which comprises: at least one deflection system configured to deflect an air stream channeled in the nacelle toward a lateral opening of the nacelle, in the activated state; at least one orientation system having: at least one transverse deflector configured to orient the air stream deflected by the deflection system toward the upstream end of the nacelle, at least one downstream deflector positioned at the downstream edge of the lateral opening and configured to deflect the air stream deflected by the deflection system toward the upstream end of the nacelle.

Abstract: A measuring rake, configured to be arranged on a link rod, includes a sheath including a front face and two side walls delimiting between them a recess configured to receive the link rod, an electronic circuit arranged on the front face of the sheath and including at least one sensor, a patched leading edge fixed removably to the sheath, and a seal arranged between the patched leading edge and the electronic circuit, the patched leading edge including a plurality of air intakes, each forming a fluidic passage between an outer face and an inner face of the patched leading edge opening out facing at least one sensor of the electronic circuit, the measuring rake making it possible to obtain a measuring tool which can be assembled simply and quickly, with easy access to the electronic circuit, and making it possible to avoid problems of orifice blockages or air leaks.

Abstract: A propulsive assembly for an aircraft with an engine system with a core in a casing and having a combustion chamber and a turbine with blades, a supply line supplying dihydrogen, an injector manifold equipped with injectors which dip into the combustion chamber, and a distribution network with several bypass lines distributed around the casing, a rear manifold connected to the supply line and to the bypass lines and a front manifold connected to the bypass lines and to the injector manifold, in which the rear manifold is at the rear of the turbine and the front manifold is at the front of the turbine.

Abstract: A propulsion system comprising a chassis, a fan cowl, an articulation system fixed between the chassis and the fan cowl and comprising a shaft with two offset cylinders in which a central cylinder is movably mounted in rotation on the chassis and wherein a lateral cylinder is movably mounted in rotation on the fan cowl, a blocking device limits the rotation of the central cylinder relative to the chassis between a closed position and an intermediate position, and a stopping device allows rotation of the fan cowl between the intermediate position and the open position and preventing rotation of the fan cowl beyond the intermediate position.

Abstract: A device for cooling an aircraft propulsion system, including at least one cooling circuit with at least one air inlet equipped with an intake flap mobile between closed and open positions and at least one air outlet equipped with an exhaust flap mobile between closed and open positions, and at least one actuator coupled by at least one kinematic system to the pair of intake and exhaust flaps in such a manner that the intake and exhaust flaps are driven in synchronized movements and simultaneously occupy the closed position or the open position. This solution enables reduction of the number of actuators and, finally, the all-up weight of the aircraft.

Abstract: A propulsion system for an aircraft comprises a closed cooling circuit which has at least one main segment and at least two secondary segments, in which a heat-transfer fluid circulates. Each secondary segment has: a leak detection device, a shut-off valve, and a non-return valve. The cooling circuit also has electronic circuitry configured to close the shut-off valve of a secondary segment when a leak is detected by the leak detection device of said secondary segment.

Abstract: An electrical propulsion assembly that includes: a propeller that has a rotation axis, at least two electric motors offset relative to one another in a longitudinal direction parallel to the rotation axis of the propeller, a main drive shaft parallel to the rotation axis of the propeller to which the electric motor are coupled, a transmission system including an output shaft connected to the propeller and an input shaft connected to the main drive shaft. Also an aircraft including at least one such electrical propulsion assembly.

Abstract: An aircraft propulsion unit with an engine mount connecting a rigid casing, supporting a propeller, and a structure. First and second transverse link rods connect the casing and the structure with first and second joints each having an axis of pivoting substantially parallel to an axis of rotation of the propeller. First and second thrust rods connect the casing and the structure by first and second thrust rod connections. The first and second thrust rod connections separated from one another in the longitudinal direction. A longitudinal end stop is configured to limit the movement of the casing with respect to the structure in at least the longitudinal direction. An aircraft with at least one such propulsion unit.

Abstract: A powerplant for an aircraft, comprising a frame, a propulsion system comprising a core enclosed in a casing and comprising a combustion chamber and a turbine, a supply pipe for conveying dihydrogen to the combustion chamber and that snakes outside the casing running along the turbine before dropping down into the combustion chamber through the casing, and a protective plate fastened to the frame and positioned between the casing and the supply pipe. With such an arrangement, if a blade of the turbine became detached it would meet the protective plate blocking its path to the dihydrogen pipe and would thus be diverted or stopped.

Abstract: A supply system for an aircraft, wherein the supply system has a supply module with outlet pipes, feed pipes connected to dihydrogen tanks, and means for channeling the dihydrogen in the feed pipes towards the outlet pipes, a distribution module having introduction pipes connected to the outlet pipes via heaters, distribution pipes connected to an engine, and means for channeling the dihydrogen in the introduction pipes towards the distribution pipes, and a control unit which commands the means of the supply module and of the distribution module depending on the information provided by the detection means. Also an aircraft with such a supply system.

Abstract: An aircraft pairing system and method are provided to arrange for scheduling flights of two or more aircraft. The system and method allow to identify pairs of aircraft flights, wherein the aircraft can be brought together into a formation with a follower aircraft flying in the wake upwash of a leader aircraft to generate fuel savings. The system and method utilize historical flight data to generate a list of possible flight pairings and anticipated fuel savings, and live data to update the possible flight pairings and anticipated fuel savings. A display of the possible flight pairings and anticipated fuel savings is provided on a user interface. The user may accept flight pairings and extract data to modify flight plans.

Abstract: A drainage valve comprising a through hole, a seat around the through hole, a shutter comprising an end face and movable in a longitudinal direction between a first position in which the end face of the shutter is away from the seat and a second position in which the end face of the shutter is pressed against the seat and blocks the through hole, and an elastic element configured to keep the shutter in the first position. The shutter has a recess, emerging at its end face, configured to introduce therein a part of a tool in order to temporarily secure the part of the tool and the shutter in order to displace it in two directions longitudinally.

Abstract: An aircraft floor including a structure, a deck attached to the structure, and first and second sealing barriers superposed at least in line with a protection zone, the deck being configured to form the first sealing barrier at least in line with the protection zone. The second sealing barrier includes a sealing tarpaulin interposed between the deck and the structure and having several reinforcing strips fixed against a face of the sealing tarpaulin oriented toward the structure, at least some of the reinforcing strips being interposed between the sealing tarpaulin and longitudinal reinforcements of the structure of the floor.