Abstract: A passenger aircraft includes a plurality of passenger seats arranged in seat rows, and a disembarkation guidance system. The disembarkation guidance system includes a plurality of electronically operable visual indicators, each of the plurality of electronically operable visual indicators being assigned to a respective seat row. The disembarkation guidance system further includes an indicator control device coupled to each of the electronically operable visual indicators. The indicator control device is configured to individually control electronically operable visual indicators to indicate passengers in the assigned seat row whether they are permitted to disembark the passenger aircraft.

Abstract: A method of producing an integrated monolithic aluminum structure, the method including the steps of: (a) providing an aluminum alloy plate with a predetermined thickness of at least 3 mm, wherein the aluminum alloy plate is a 2xxx-series alloy provided in an F-temper or an O-temper; (b) optionally pre-machining of the aluminum alloy plate to an intermediate machined structure; (c) high-energy hydroforming of the plate or optional intermediate machined structure against a forming surface of a rigid die having a contour in accordance with a desired curvature of the integrated monolithic aluminum structure, the high-energy hydroforming causing the plate or the intermediate machined structure to conform to the contour of the forming surface to at least one of a uniaxial curvature and a biaxial curvature; (d) solution heat-treating and cooling of the high-energy hydroformed structure; (e) machining and (f) ageing of the final integrated monolithic aluminum structure.

Abstract: A method of producing an integrated monolithic aluminum structure, comprising: providing an aluminum alloy plate with a thickness of at least 38.1 mm, wherein the plate is a 2xxx-series alloy in a T3-temper and has a composition comprising, in wt. %: Cu 3.8-4.5, Mn 0.3-0.8, Mg 1.1-1.6, Si up to 0.15, Fe up to 0.20, Cr up to 0.10, Zn up to 0.25, Ti up to 0.15, Ag up to 0.10, balance aluminum; optionally pre-machining the plate to an intermediate machined structure; high-energy hydroforming the plate or intermediate structure against a rigid die forming surface having a desired curvature contour of the integrated monolithic aluminum structure, causing the plate or the intermediate structure to conform to the forming surface contour; machining or mechanical milling the high-energy formed structure to a near-final or final machined integrated monolithic aluminum structure; ageing the final integrated monolithic aluminum structure to a desired temper.

Abstract: An alloy formed of aluminum, nickel, scandium and optionally one, two or more further metals. The aluminum alloy is suitable for additive manufacturing of lightweight highly thermally conductive components for aircraft, such as heat exchangers. In a first step, a powder of the described aluminum alloy is produced by additive manufacturing, such as laser melting in the L-PBF process. Large grains are able to grow epitaxially along the build direction thereby increasing phonon and electron mobility along the build direction. With this, a higher thermal conductivity can be achieved. In a second step, the preliminary part is hardened by precipitation of secondary phases at 250 to 400 C to form the hardened part. 3D-printed lightweight parts with high thermal conductivity are obtained.

Abstract: An electric propulsion system of an aircraft includes an electrical generator and a cooling device of the electrical generator. It further includes at least one thermoacoustic engine and a heat transfer circuit configured to transport heat dissipated by the electrical generator to the thermoacoustic engine. The cooling device of the electrical generator is at least partially powered by energy from the thermoacoustic engine.

Abstract: To enable early detection of AC insulation faults, or to permit easier, faster and more accurate measurement of small currents in inverters, a current measuring circuit for a converter is provided. The current measuring circuit has a positive supply rail, a negative supply rail, a reference potential rail and a current measuring device that contains a Y-capacitor and a current sensor connected in series therewith. The load current can be decoupled from the measurement current through the at least one Y-capacitor, so that at high load currents even small fault currents can be acquired reliably with the current sensor.

Abstract: A connection assembly between two portions of a line including an inner conduit for transporting a cryogenic fluid, the assembly including two flanges which are respectively arranged at the ends of the line portions and which are configured to be held in contact with one another by virtue of a fixing arrangement. The contact zone between the two flanges includes at least two grooves for positioning seals and at least one conduit opening out, for the one part, between the two seals and, for the other part, into an expansion chamber for the cryogenic fluid. The expansion chamber is arranged in one, or in the vicinity of one, of the first connection flange and the second connection flange. The expansion chamber includes a detector for detecting the presence of the cryogenic fluid in the expansion chamber or a recess configured for the installation of such a detector.

Abstract: An aircraft having at least one transport pipe in which dihydrogen flows and, for each transport pipe, an embedding channel in which the transport pipe is housed. The embedding channel has a gutter that has a bottom and an opening opposite the bottom and a cover that covers the opening of the gutter. The cover constitutes an outer wall of the aircraft in direct contact with external air surrounding the aircraft. The cover has ventilation windows passing through it that allow the passage of the dihydrogen towards the outside. With such an arrangement, even in the event of dihydrogen leaking into the embedding channel, the dihydrogen is automatically evacuated towards the outside of the aircraft.

Abstract: A heat exchanger including a sealed housing and a body positioned inside the housing, the body including a stack of least one first assembly of first and second plates pressed against each other, between which flows a first fluid, and at least one second assembly of third and fourth plates pressed against each other, between which flows a second fluid, the first and second assemblies being arranged so that they transfer heat between the first and second fluids. This configuration limits the risk of leaks and mixing of the two fluids.

Abstract: A system and device for laser shock peening device and components thereof. The system includes umbilical cords with flexible outer sheaths surrounding the fiber optic cable within the umbilical. The umbilical may include two different sections with different outer sheathes. The applicator device may have a laser peeing pen that has a longitudinal axis that is spaced from the longitudinal axis of the applicator device. In a method of operating the device, a first step includes a vertical movement, followed by a second step of rotation movement, and then another step of vertical movement opposite the first step.

Abstract: An aircraft including at least one hydrogen engine, at least one hydrogen supply device including at least one hydrogen tank and at least one item of equipment through which the hydrogen flows and which is positioned between the hydrogen tank and the hydrogen engine. The aircraft includes at least one sealed container sealed from the outside air, in which sealed container the equipment of the hydrogen supply device is positioned. This solution allows a safe hydrogen installation to be obtained using existing equipment.

Abstract: An aircraft comprising a fuselage, first and second wings positioned on either side of the fuselage, wherein each wing includes an inner part connected to the fuselage and an outer part continuing the inner part, the end of each inner part connected to the fuselage having a height greater than half the height of the fuselage and extending over a length greater than or equal to half of a distance separating the nose and the tail of the fuselage.

Abstract: A connection assembly between two portions of a supply line for a cryogenic fluid, the assembly including a male nozzle arranged to be at least partially inserted into a female nozzle together forming a tight mechanical link, over a distance of a few centimeters, a thermal insulation chamber for each of the two line portions and an additional thermal insulation chamber to thermally insulate the connection zone of the two line portions, and an expansion chamber for the cryogenic fluid that is configured to be linked to a cryogenic fluid sensor, arranged about the connection zone of the two line portions. This enables two cryogenic fluid line portions to be connected without requiring one portion to be inserted into the other portion over a significant length, thereby enhancing mechanical flexibility and obviating the need for significant free space about the connection assembly to assemble and disassemble the assembly.

Abstract: An auxiliary power unit for an aircraft. It includes an air compressor coupled to an air-drawing device for drawing in air from outside the aircraft, the compressor supplying compressed air to a manifold. The manifold is configured to supply air to an environmental control system and a start-up module of at least one propulsion system of the aircraft running on hydrogen. The manifold is also configured to supply air to a fuel cell stack arranged to provide an electric generation function configured to power non-propulsive systems of the aircraft, the fuel cell stack also being supplied with hydrogen from a tank supplying hydrogen to the at least one propulsion system of the aircraft.

Abstract: This control system takes into account the thermomechanical aspects of materials to quickly and easily determine optimal cutting conditions and to automatically control machining to preserve the integrity of the workpiece. This system includes an acquisition module configured to acquire values of a set of input parameters relating to cutting conditions and material properties of the piece, and a microprocessor configured for determining at least one operating cutting parameter representative of a cutting signal from the machining apparatus using a set of output parameters of an integrity model previously constructed during a learning phase. The integrity model connects the set of input parameters to the set of output parameters comprising specific cutting coefficients representative of the material integrity of the piece, and establishes at least one fatigue threshold of the at least one cutting operating parameter. The fatigue threshold allows control of the progress of cutting operations.

Abstract: A method for assembling an aircraft pylon including a primary structure and at least one internal system positioned at least partially within the primary structure, wherein the assembly method includes a first step of assembling a part of the primary structure so that the interior of the primary structure remains accessible, a step of mounting an internal systems module including at least one support and at least one internal system connected to the support, a second step of assembling the internal systems module and the partially assembled primary structure, a third step of assembling any element of the primary structure not assembled in the first assembly step, and an aircraft pylon assembled by such a method.

Abstract: A method and a system for detecting leak noise in an aircraft, making it possible to perform ground tests in complete safety and over an entire cabin pressurization range, thus avoiding having to resort to a plurality of in-flight tests. The system includes: at least one acquisition device configured to be installed in at least one area of interest of the aircraft, the acquisition device being configured to acquire data in relation to current noise in the area of interest and data in relation to a current pressure gradient between the cabin of the aircraft and the outside, and a monitoring device configured to control the acquisition of the data by the at least one acquisition device and to receive the acquisition data in order to detect any leak noise in the at least one area of interest.

Abstract: An aircraft is disclosed include wiring configured to carry electrical power; and an electromagnetic shielding arrangement which provides an enclosure around the wiring and is configured to block electromagnetic emissions from the wiring. The electromagnetic shielding arrangement includes a first shield; a second shield which can move relative to the first shield; and a gap between overlapping portions of the shields. The gap is configured to enable air to flow into or out of the enclosure via the gap.

Abstract: A hydrogen tank assembly is provided for use in vehicles, such as aircraft. The hydrogen tank assembly has an inner tank wall, an outer tank wall, and an inert gas source. The inner tank wall defines a hydrogen tank volume that is surrounded by a shroud volume which is defined by the outer tank wall. The hydrogen tank volume is filled with cryogenic hydrogen and has a higher pressure than the shroud volume that is filled with an inert gas, such as helium. The counter-pressure of the inert gas prevents micro-cracks in the inner tank wall and increases the in-service life.

Abstract: A process for pairing two aircraft together to save fuel. After evaluating whether two aircraft may possibly be paired together in a formation for fuel savings, the process determines new flight plans for both aircraft, allowing the second aircraft to save fuel by flying behind the first aircraft so that the second aircraft utilizes the energy of the wake vortices generated by the first aircraft. Based on the new flight plan, the process determines if there is a net trip fuel savings for the pair.