Abstract: An electrical system, and, more particularly, to an electrical system for an aircraft comprising one or more energy sinks and a hybrid energy storage system. The hybrid energy storage system may comprise one or more primary energy sources, a secondary energy source, and a secondary energy source control unit. The one or more primary energy sources may be coupled to and supply power to the one or more energy sinks. The secondary energy source may be coupled to the one or more primary energy sources and adapted to supply power at a variable output voltage to the one or more primary energy sources.

Abstract: A method for manufacture of a complex component includes construction of the component from a metal material in an additive manufacturing method with at least one cavity segment that has a cavity open on at least one side and defined by an interior surface of the component, formation of an auxiliary electrode during construction of the component, formation of one or a plurality of supporting structures that connect the auxiliary electrode to the interior surface of the component during the construction of the component, electrical insulation of the auxiliary electrode from the interior surface by separating the supporting structures from the interior surface or from the auxiliary electrode, and performance of an electro-polishing of the interior surface in an electrolyte bath by connecting the component and the auxiliary electrode to different poles of an electric voltage source.

Abstract: An aircraft cabin assembly is depicted and described having a cabin wall, which surrounds a cabin interior space and has a wall surface facing the cabin interior space, and having a light source, which is provided in order to emit light onto the wall surface. The problem of providing an aircraft cabin assembly which, irrespective of the light outside of the aircraft cabin assembly, as effectively as possible gives a passenger in the cabin interior space the impression that the cabin interior space is larger than it actually is, is solved in that the wall surface has a holographic image of an object and in that the light source is designed to emit the kind of light onto the wall surface that allows the holographic image to be seen as a three-dimensional image of the object which is the subject of the holographic image.

Abstract: A turbofan having a fixed structure, a fan, a fan casing surrounding the fan, an outer cowl disposed around the fan casing and mounted so as to be articulated on the fixed structure, and a deployment system that moves the outer cowl from a closed position to an open position. The deployment system has a guide rail fastened around the fan casing, a slider that is able to move along the guide rail and has a shoe. An activation system of the deployment system moves the slider and the shoe alternately in one direction or the other along the guide rail. One end of an arm of the deployment system is mounted to be articulated on the shoe and another end is mounted to be articulated on the outer cowl. Such a motorized deployment system makes it possible to save space and mass in the turbofan.

Abstract: A method and system for synchronizing computers includes a bit computing module for computing of a bit by each computer, an exchange module, a bit signal pair determination module for determining a bit signal pair including the computed bit, a bit product pair determination module for determining a bit product pair indicating which bit equal to 1 of the bit signal pair of a computer can be combined with the bit of the bit signal pair determined for the other computer in the iteration n?1, a bit remainder pair determination module for determining a bit remainder pair indicating which bit equal to 1 of the bit signal pair of a computer in the iteration n is different from the bit of the bit signal pair of the other computer in the iteration n?1, a synchronized signal determination module for determining a synchronized signal based on the bit product pair and on the bit remainder pair.

Abstract: A method of identifying an object signature in an environment includes acquiring infrared information from the environment using a detection unit in order to obtain an infrared wavelength spectrum associated with the environment. The method further includes selecting three wavelength bands of the infrared wavelength spectrum using a filtering unit and detecting a presence of the three wavelength bands of the infrared wavelength spectrum in the environment by filtering the selected three wavelength bands using the filtering unit. The method further includes determining an intensity indicator for the three selected wavelength bands using a processing unit and classifying the object signature using the processing unit based on the determined intensity indicator in order to identify the object signature.

Abstract: Method and device for determining trajectory to optimal position of a follower aircraft with respect to vortices generated by a leader aircraft. The method includes controlling trajectory of a follower aircraft to an optimal position where the follower aircraft benefits from effects of at least one of the vortices of a leader aircraft. A first section control step controls flight of the follower aircraft using current measurements of flight parameters, from a safety position to a search position, along an approach section passing through an approach zone. A second section control step controls flight of the follower aircraft using current measurements of flight parameters, from the search position to a precision position, along a search section passing through a search zone, and a third section control step controls flight of the follower aircraft, from the precision position to the optimal position, along an optimization section passing through an optimization zone.

Abstract: A duct stringer has duct walls providing a duct with a closed cross-section; and a bulkhead in the duct. The duct is adapted to transport fluid, and the bulkhead is adapted to block the flow of fluid along the duct. The bulkhead is adhered to the duct walls by one or more co-cured or co-bonded joints. The bulkhead includes a pair of bulkhead parts, each with a web and one or more flanges. The duct stringer is manufactured by positioning the mandrels end-to-end with the bulkhead parts back-to-back between them; wrapping or laying-up the duct walls around the bulkhead parts and the mandrels; co-curing or co-bonding the flanges of the bulkhead parts to the duct walls; and after the bulkhead has been adhered to the duct walls, removing the mandrels from opposite ends of the duct.

Abstract: A method and system for protecting an aircraft against an incoherent command instruction. The system has a generation unit generating a command instruction transmitted to an evaluation unit that evaluates whether or not the command instruction is incoherent and generates and transmits a validation order if the command instruction is coherent or an arbitration request if not, the arbitration request being transmitted by an arbitration unit, where applicable, to an operator who sends a confirmation response or a cancellation response. The arbitration unit generates and transmits a validation order to an execution unit in the event of receiving a confirmation response and a cancellation order in the event of receiving a cancellation response, the system allowing the execution unit to execute only the command instructions evaluated and confirmed as not being incoherent.

Abstract: A temperature monitoring apparatus configured to monitor a temperature of a portion of a vehicle's electrical energy distribution network is disclosed. The apparatus includes a first optical fibre including one or more temperature sensing sections, each temperature sensing section being for thermal contact with a portion of a vehicle's electrical energy distribution network. Each temperature sensing section is arranged to produce, in response to an optical input signal, an optical output signal indicative of the temperature of the temperature sensing section. The apparatus is arranged to determine a temperature of the portion of the vehicle's electrical energy distribution network based on one or more of the output optical signals in use.

Abstract: A communication system for equipment in airborne operations comprising: at least one first double transceiver and at least one second double transceiver, wherein the at least one first double transceiver is configured to send data to the at least one second double transceiver in two redundant main channels and wherein the data to be sent through each redundant main channel is first compared with each other so as to ensure that the data sent through a first main channel is the same data sent through a second main channel.

Abstract: A multifunctional diffusion barrier comprising at least one organic polymer and a 2D graphene or 2D graphene derivative material and a method for preparing the multifunctional barrier. The multifunctional diffusion barrier can be used as a liquid and/or gas barrier, or as structural material, or as sealing material, or as a self-cleaning material or as protective material against UV radiation in aeronautical, automotive, marine or building field. The multifunctional diffusion barrier is suitable in producing parts of aircraft such as a fuel tank, a fuel tank conduit and a gasket.

Abstract: A communication system for an aircraft comprises a communication interface with the outside of the aircraft and an avionics domain of which the security level is the highest of the communication system. It also comprises a communication domain to which is connected the communication interface and of which the security level is lower than the security level of the avionics domain. A barrier of a first type is arranged to filter the information coming from the communication interface so as to allow the information to pass into the communication domain only if the information corresponds to an authenticated communication. A barrier of a second type is arranged to filter information transmitted from the communication domain to the avionics domain, carrying out at least a syntactic filtering of the information.

Abstract: An engine pylon for mounting a jet engine beneath a wing of an aircraft, the engine pylon having a primary structure having two internal lateral fittings that face one another and a rib that is fastened between the two internal lateral fittings and a primary box that at least partially surrounds the primary structure and comprises a first part made from a composite material.

Abstract: A device for determining a temperature in a passenger compartment of a vehicle comprising a sensor unit for detecting infra-red radiation and a temperature determining unit. The temperature determining unit may be configured so as, in dependence upon the measurement data provided by the sensor unit, to determine a surface temperature of a predetermined object located in the vehicle passenger compartment and, from the determined surface temperature of the object using a first functional relationship, to determine an air temperature in the vehicle passenger compartment. The temperature determining unit may be configured as an alternative or in addition thereto so as, in dependence upon the measurement data provided by the sensor unit, to determine a surface temperature for at least one passenger compartment occupant, and from the determined surface temperature using a second functional relationship to determine a measurement for the level of personal comfort.

Abstract: A system of fuel cells for an aircraft including a plurality of fuel cells, a hydrogen circuit, a cooling circuit and a first air circuit configured to supply oxygen to a first subset of fuel cells having at least two cells. The first air circuit includes an air flow restrictor at each fuel cell inlet of the first subset and configured to distribute the air between the fuel cells of the first subset, and an outlet valve connected to the outlet of the fuel cells of the first subset, the opening of the outlet valve being controlled by a computer as a function of an electrical power that is to be produced by the fuel cells of the first subset. The use of the same air circuit to supply oxygen to several fuel circuits makes it possible to limit the bulk of the fuel cells system.

Abstract: Sound attenuation panel for aircraft having a combination of acoustic attenuation properties. The acoustic panel includes an acoustic structure having a cellular structure and a resistive skin and a backing skin, the acoustic panel also including at least one auxiliary acoustic device with cavities that is configured to produce additional acoustic absorption, the auxiliary acoustic device with cavities being attached to the acoustic structure and including adjacent chambers or cavities separated by shared walls, each of the chambers or cavities having perforations and being adapted to produce acoustic absorption. The combination of the acoustic structure and the auxiliary acoustic device with cavities enables combination of the acoustic absorption properties of these two types of element and an increased range of frequencies of the noise that can be attenuated by the acoustic panel without increasing its overall size.

Abstract: The invention relates to a seat assembly for a cabin of a means of transportation, having an aisle which is arranged in the longitudinal direction of the cabin, two mutually spaced cabin walls which are oriented parallel to the aisle at least in some regions and laterally delimit the cabin, two outer passenger seat regions which are separated from one another by the aisle and each of which adjoins one of the two cabin walls, wherein the outer passenger seat regions have at least one row of seats with a respective inner first seat module which faces the aisle, a central second seat module adjoining the first module, and an outer third seat module adjoining the respective cabin wall.

Abstract: An asymmetrically constructed radome for an aircraft and an aircraft having an antenna and a corresponding radome are described. The radome has a first layer with a first dielectric constant and a first layer thickness, and a second layer with a second dielectric constant and a second layer thickness. The first layer thickness and the second layer thickness are different from each other. The first layer includes a thermosetting material and the second layer includes a thermoplastic material. Such an asymmetrical radome structure improves the mechanical stability and electromagnetic transparency of the radome.

Abstract: A scandium-containing aluminium powder alloy, wires and materials including said alloy, and a method for producing the scandium-containing aluminium powder alloy, the wires and materials, the proportion of scandium in the scandium-containing aluminium powder alloy being elevated, are disclosed. At least one element is selected from the group consisting of the lanthanum group except for Ce, Y, Ga, Nb, Ta, W, V, Ni, Co, Mo, Li, Th, Ag.