Abstract: To improve the complicated painting process of large three-dimensionally shaped components, preferably aircraft components, the masking step is automated. This is achieved by printing a masking medium onto the component with an inkjet method, the masking medium forming a masking film. The masking film masks the desired surface area and can be pulled off following the end of the painting. Preferably, spray films, functional printing inks or mold release agents are used as the masking medium.

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: A turbofan with a nacelle having a fixed structure, a mobile assembly bearing second blocking element and able to move between an advanced position and a withdrawn position, a set of deflectors able to move in translation between an advanced position and a withdrawn position, and an actuation system having a carriage, a blocking lever bearing first attachment element and able to move between a blocking position and a free position, and a transmission system configured to move the blocking lever from the blocking position to the free position when the mobile assembly reaches a tilting position between the advanced position and the withdrawn position.

Abstract: In an aircraft, latches are used to secure cargo within the cargo hold of the aircraft. Such latches include a base plate configured for rigid attachment to a surface of the cargo hold, a latch head attached to the base plate and configured to prevent a movement of at least one cargo unit in a Y-direction and a Z-direction and to allow a movement of the at least one cargo unit in an X-direction, and a roller assembly attached to the base plate, opposite the latch head, and comprising at least one roller, the roller being configured to provide a vertical support to the at least one cargo unit in the Z-direction while allowing the movement of the at least one cargo unit in the X-direction.

Abstract: A linking member between a first and a second structural member of a fuselage of an aircraft allowing improved dissipation of stresses. The linking member has a first part made of a solid structure and at least one second part made of a lattice structure. The first part made of the solid structure is configured to dissipate static stresses and to withstand fatigue up to a predetermined maximum stress and fatigue threshold. This configuration allows improved dissipation of the stresses exerted on the linking member.

Abstract: A measurement device includes a substrate having accommodations with an emerging opening in which sensors are provided, the substrate including a cavity with a flexible printed circuit. The device is installed on a surface to characterize a fluid flow at this surface. The circuit uses hierarchized buses comprising two data communication buses emerging at the two longitudinal ends of the substrate and an internal data acquisition bus, the bus linking control circuits, each control circuit being connected to one of the communication buses, the sensors being connected to the bus in a distributed fashion on either side of each control circuit. The data from the sensors can be transmitted to the two surrounding circuits and may be acquired if one of them is faulty.

Abstract: A seal includes a barrel extending between a base and a top, in which the barrel has a cylindrical cavity passing through it between its base and its top, and a skirt indissociable from the barrel and extending around said barrel, in which the skirt adopts the shape of a dome of which the exterior edges extend out beyond the base starting from the top. The seal is able to divert the fluid and keep the space under the skirt fluid tight.

Abstract: An information processing architecture for implementation in a vehicle includes a software segregation unit which is configured to provide a first security domain and a second security domain which are assigned in each case to different operational areas of the vehicle and have their own data processing environments which are segregated from one another to run a multiplicity of computer applications. The software segregation unit is further configured to provide a synchronization instance, wherein the synchronization instance has a central dataset which is synchronized with data generated in the respective security domains independently from one another via data exchange and is selectively readable by both security domains.

Abstract: A method for resistance welding of two fiber-composite components to give a fiber-composite structure includes arranging conductive fibers within a jointing region of the two fiber-composite components, where each conductive fiber includes a carbon fiber with an electrically insulating coating. An electric current is passed through the conductive fibers to heat the jointing region to a welding temperature and melt the fiber-composite components in the jointing region. The jointing region is hardened in a manner that bonds the two fiber-composite components by way of the jointing region to give the fiber-composite structure.

Abstract: Systems and methods for detecting and locating a signal source. The system contains an antenna array with antennas, a control unit that is connected to the antenna array, and an evaluation unit to receive data from the control unit. The antennas are designed to acquire a signal emitted by the signal source. The control unit is designed to ascertain a cross-correlation or covariance matrix of a signal received from the antenna array, and to transmit the cross-correlation or covariance matrix to the evaluation unit. The evaluation unit is designed to ascertain a position of the signal source on the basis of the cross-correlation or covariance matrix received from the control unit.

Abstract: A hinge assembly 8a for an aircraft component comprises first and second hinge plates 9, 10, each hinge plate including a plurality of fingers 13 to 17. The fingers of the first and second hinge plates are interleaved. A seal assembly 28 to 32 is provided between at least some of the fingers. The provision of a hinge including interposed fingers allows for a hinge assembly having a complex aerodynamic profile to be made, while the sealing function is performed by the seals filling the gaps between the fingers.

Abstract: An object identification unit contains an artificial neural network and is designed to identify human faces. For this purpose, a face is divided into a number of triangles. The relative component of the area of each triangle in the total of the areas of all triangles is ascertained to ascertain a rotational angle of the face. The relative component of the area of each triangle in the total of the area of all triangles is then scaled to a rotation-invariant dimension of the face. The scaled area of the triangles is supplied to the artificial neural network in order to identify a person.

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: An anterior part of a nacelle of an aircraft propulsion assembly, which comprises an air intake lip, an outer panel extending an outer part of the air intake lip, an inner structure extending an inner part of the air intake lip, a front frame connecting the outer wall to the air intake lip or to the inner structure. The outer panel and the outer part of the air intake lip together form an outer wall of the anterior part. The front frame and the outer wall are connected to one another by assembly means located inside the anterior part. The anterior part constituted in this manner ensures laminar flow of the air on an outer surface of the anterior part and reduces drag. A nacelle of a propulsion unit, comprising an anterior part of this kind is also provided.

Abstract: An apparatus for threading a tool unit onto an elongate structural element. The apparatus has a holding arrangement for holding it on a feed device, a tool unit to be threaded onto the elongate structural element. The tool unit has a tool axis and a vibration unit connected to the tool unit and configured to generate a periodic force in at least one first spatial direction that runs transversely with respect to the tool axis. First and second coupling components, held elastically on one another, are provided. The first coupling component is connected to the holding arrangement, the second coupling component is connected to the tool unit. The vibration unit is operated, during a feed movement of the holding arrangement for threading the tool unit onto the elongate structural element, to add an additional, periodically varying transverse component to a feed force acting on the tool unit.

Abstract: A device for electrically connecting cables where a change of direction occurs. The device includes at least two busbars as well as a plate having independent internal ducts in which the busbars are located, each duct being electrically insulated from the other ducts, the busbars ensuring electrical conduction from one open end of a duct to the other end. The cables are fastened at these open ends and thus do not undergo any deformation, the change of direction taking place inside the plate with the aid of the busbars.

Abstract: An electric power supply system for an aircraft includes: a first electric source and a second electric source coupled together to supply electric power to a set of electrical loads, and a controller configured to acquire a piece of information on the current electric consumption consumed by the set of electrical loads; acquire a piece of information corresponding to a target ratio of the distribution, between the first and second electric sources, of the current electric consumption consumed by the set of electrical loads; perform frequency filtering of the current electric consumption to determine a transient consumption portion of the current electric consumption; determine control setpoints for the first electric source and for the second electric source in accordance with the target distribution ratio and with the transient consumption portion; and apply the control setpoints to the first and second electric sources.

Abstract: A photovoltaic assembly dual junction solar cell for space use including a solar cell stack including first and second subcells stacked on each other and each including an epitaxially grown light absorbing layer. The first subcell is adjacent to a solar cell stack front, light-receiving surface and the second subcell is adjacent to a solar cell stack rear surface. The first subcell light absorbing layer has a larger bandgap than the second subcell light absorbing layer. A light reflecting element positioned adjacent to a second subcell light absorbing layer rear side is configured to reflect photons having an energy smaller than the bandgap energy of the second subcell light absorbing layer and/or photons having an energy larger than the bandgap energy of the second subcell light absorbing layer and smaller than the bandgap energy of the first subcell light absorbing layer with a reflectivity of at least 90%.

Abstract: A busbar for an aircraft with at least two conductive layers and at least three insulating layers. The conductive layers and the insulating layers are stacked together alternatingly and extend in a longitudinal direction. The conductive layers and the insulating layers include different coefficients of thermal expansion. Each of the conductive layers includes spatial structures. Each spatial structure is connected to an adjacent one by an interconnecting segment. Each conductive layer is embedded between two insulating layers, resulting in a deforming of the side walls of the spatial structures under heat, thereby compensating a longitudinal expansion of the conductive layers. Further, an aircraft with a disclosed busbar and a method of producing such busbar is provided.

Abstract: Devices and methods for producing a T-shaped semifinished product from a multiply non-crimp fabric with reinforcing fibers for a composite material. The product has a web and a flange. The device includes a web forming tool, with which a web portion of the non-crimp fabric is clamped in place, a forming tool, with which plies of a flange portion of the non-crimp fabric are split into two parts, a depositing device, with which a tube body is deposited on the flange portion formed into the flange, a holding tool, with which a clearance between the holding tool and the flange is formed, and a filling device, with which the tube body is filled with a gas such that the tube body fills the clearance and firmly holds the flange portion formed into the flange, and alternatively, a magnetic force can be generated between a sheet and the web forming tool.