Abstract: A fuel cell system includes a first fuel cell unit having a first fuel cell and a second fuel cell, a second fuel cell unit having a third fuel cell and a fourth fuel cell, a hydrogen tank coupled to all fuel cells, an oxygen supply unit and an air inlet. Oxidant inlets of the first fuel cell and the fourth fuel cell are couplable with the air inlet. Oxidant inlets of the second fuel cell and the third fuel cell are couplable with the oxidant supply unit couplable with at least one of the oxygen supply unit and the air inlet. Exhaust outlets of the first and fourth fuel cells are couplable with an inert gas outlet. Exhaust outlets of the second and third fuel cells are coupled with an exhaust switching unit couplable with the inert gas outlet and a water outlet.

Abstract: The present invention provides a method for producing a fibre composite component, comprising: arranging a first and a second mould in relation to one another in such a way that these together form a first cavity; laying a fibre material on the first and/or second mould; filling the formed first cavity with a casting material and solidifying said casting material in order to seal the first and the second mould to one another and/or interconnect them; and infiltrating the fibre material with a matrix and curing said matrix to form the fibre composite component.

Abstract: A method for detecting a device that generates spurious signals in an electrical network, to which several devices and at least one fault detection device are connected, includes the steps of monitoring the electrical network for electrical spurious signals, sequentially deactivating each device for a predetermined time T when an electrical spurious signal has been detected, and checking the electrical network for the disappearance of the respective spurious signal, and signaling as soon as the respective spurious signal has disappeared upon deactivating a respective device. This makes it possible to especially reliably detect a device in an electrical network that couples an undesired spurious signal into the network.

Abstract: According to an exemplary embodiment of the invention, a digital data stream is divided into at least two complementary digital substreams and delayed in time. The first digital substream and the second digital substream are transmitted by the broadcasting systems with a time offset in accordance with the broadcasting principle such that any receiver can use the respectively intact part of the other complementary digital substream in order to ensure a seamless media reception when a break in the transmission or reception occurs.

Abstract: A device for acquiring mechanical loads on mechanically loaded bodies is provided. The device exhibits a resonance-capable micro-bridge structure, an alternating voltage source with a variable frequency, an impedance measuring device for acquiring the impedance of the micro-bridge structure and an electronic unit for receiving determined impedance values and changing the frequency of the alternating voltage source. By exciting the micro-bridge structure and measuring its impedance, a conclusion can be drawn as to the expansion-dependent resonance frequency, which in return makes it possible to determine the expansion, and hence the mechanical load. Such a device is sufficiently accurate, and largely independent of outside influences.

Abstract: An adhesive holder for holding objects comprises an adhesive layer, an object holder, an adapter with a contact surface and a counter element with a counter surface. The counter surface of the counter element is positionable at a distance from the contact surface of the adapter in order to enclose a section of a structural element. The adhesive layer can be applied onto the contact surface of the adapter or onto the counter surface of the counter element. The adhesive holder according to the invention makes it possible to introduce a force into a structural element by exerting compressive stress and shearing stress only such that the adhesive connection is much more durable and the adhesive holder can be subjected to higher loads than in the state of the art.

Abstract: A process for management of thermal effluents of an aircraft that includes an airframe (110) and at least one propulsion system (112), whereby the at least one propulsion system (112) includes a gas turbine engine (116) that is supplied with fuel via a fuel supply circuit (122) that extends from a reservoir (124) that is arranged at the airframe (110), whereby the airframe (110) includes at least one source of thermal effluents (134), wherein the process includes at least partially dissipating—at the level of at least one propulsion system (112)—the thermal effluents that are generated at the airframe (110) by using as coolant the fuel that is used for supplying the gas turbine engine (116).

Abstract: Disclosed are a method and system for improving real-time determination of flight parameters of an aircraft during flight. A selection module selects and delivers measured values of input parameters to an estimation unit, and the estimation unit uses the input parameters to estimate at least two selected flight parameters. The input parameters are received by the estimation unit on the basis of identified flight mechanics equations associated with the selected flight parameters. The estimation unit includes an extended Kalman filter, which is configured to receive the values of the input parameters and to output joint estimations of the selected flight parameters based on the flight mechanics equations, during the flight of the aircraft.

Abstract: An aircraft propulsion unit includes a nacelle in which a power plant is arranged. The nacelle includes an inside wall that delimits a pipe with an air intake at the front. The propulsion unit includes a frost treatment system having at least one first pipe equipped with elements for regulating the passing air, for directing the hot air from the power plant to the air intake, and, an exhaust system having at least one second pipe equipped with elements for regulating the passing air, for directing air from the power plant to a delivery zone. The at least one second pipe is connected to the at least one first pipe, and the elements for regulating the air that passes into the at least one first pipe are separate from the elements for regulating the air that passes into the at least one second pipe.

Abstract: A fastening assembly for the fastening of systems in an aircraft comprising frames, a skin, and clips between the skin and the frames. The fastening assembly includes: ramps, that extend between two consecutive frames of the aircraft; brackets for fastening the ramps to two of the clips situated respectively on two consecutive frames of the aircraft; system supports, fastened to the ramps, each system support being able to receive at least one system.

Abstract: An insulation arrangement with a holding device that comprises a collar forms an overlapping region between a second insulating package and the collar such that incidental condensation water on a first insulation package drains to the second insulating package along the collar under the influence of the gravitational force and from there into a bilge of the aircraft equipped with the insulation arrangement on a waterproof cover film of the second insulating package. This prevents condensation water from dripping into a passenger cabin.

Abstract: The invention relates to a strut system for the stabilization of the shell (2) of an aerodynamic aircraft component in a commercial aircraft, comprising a pair of connection supports (4a, 4b) connected on the inside to the shell (2) and opposing each other, between which connection supports (4a, 4b) several struts (5) extend to form a latticework structure (3), which struts (5) in nodal points (6a, 6b) arranged on the ends are non-detachably connected to the connection supports (4a, 4b), wherein the area extension of the latticework structure (3) is aligned in such a manner relative to a middle plane of symmetry (11) that the struts (5), formed with an open symmetrical cross section, as well as the cross section of the connection supports (4a, 4b), are arranged so as to be symmetrical to the aforesaid.

Abstract: The object of the invention is in particular the validation of configuration of a system comprising a plurality of elements, at least one reference being associated with each element of the said plurality of elements. After at least one reference key has been calculated (410) according to at least one expected reference of each element of the said plurality of elements, a theoretical configuration report of the said system, comprising the said at least one reference key, is generated (420). Similarly, at least one verification key is calculated (455) according to at least one reference of each element of the said plurality of elements, and a real configuration report of the said system, comprising the said at least one verification key, is generated (460). A configuration error is detected if the values of the said verification key and reference key of the said real and theoretical configuration reports are different.

Abstract: Aircraft fuselage section (32) subjected to impacts of external bodies, the aircraft fuselage having a curved shape with at least a vertical symmetry plane (A-A) and a central longitudinal axis and comprising a skin (35) and a plurality of frames (37) arranged perpendicularly to said longitudinal axis (33), the aircraft fuselage section also comprising at least an inner reticular structure (51, 53) mounted on a supporting structure (41, 43) comprising longitudinal beams (39) attached to the skin (35) and interconnected with said frames (37), said inner reticular structure (51, 53) being arranged for creating at least one closed cell (75) with the skin (35) for improving its resistance and its damage tolerance to said impacts. Said inner reticular structure (51, 53) can be formed by panels (61), rods (65, 65?), cables (67, 67?) or belts (69, 69?).

Abstract: A process for cutting out a damaged area of an aircraft fuselage, in particular so as to repair the damaged area, includes in making at least one cut-out in the fuselage (20) so as to delimit a cut-out area (24) that encompasses the damaged area and that includes at least one flare-out, characterized in that it includes making a hole (34) at the flare-out of the cut-out area (24) with a tool whose diameter corresponds to that of the desired flare-out.

Abstract: The invention relates to a method for simulating the unsteady aerodynamic loads being exerted on the external structure of an aircraft, notably in the context of a simulation of the buffeting of a wing surface in an airflow. The method includes a step of measurement of pressure (410) at different points of a grid, a step of calculation of the spectral density at these points (420) followed by extrapolation/interpolation operations to calculate the missing measurements (430), a step of estimation of the pressure coherence (440) for each pair of points of the grid, a step of estimation of the interspectral pressure density (450) for these same pairs of points, from the coherence thus estimated, and a step of calculation of the aerodynamic loads (460) by summing the real part of the interspectral density for the area of the wing surface having a separation of the boundary layer.

Abstract: The system (1) comprises means for determining the distance at the current time of the target aircraft (B) with respect to the merge waypoint (P0) along its path (TB), this distance being transmitted to calculation means in order to determine the speed control commands which are subsequently applied to the reference aircraft (A) in order for it to carry out the acquisition of the spacing at said merge waypoint (P0).

Abstract: In a method for manufacturing components from composite fiber materials, at least one placeholder is inserted into a recess in a molding tool, wherein the unfinished component is subsequently produced, the placeholder is removed, at least one lifting pad is inserted into the recess and the unfinished component is removed from the molding tool by inflating the lifting pad. In a system for manufacturing components from composite fiber materials, the component removal process is monitored and controlled by a computer unit in order to prevent predetermined maximum component loads from being exceeded. The gentle component removal process makes it possible to avoid consequential costs for repairing or reworking the components.

Abstract: A method and device for displaying trim information on an airplane during a take-off, for determining and displaying a precise trim setpoint which enables the pilot, by following the displayed information, to carry out a manual take-off which is optimized from the performance point of view.

Abstract: A power distribution system for an aircraft having at least one engine includes at least one torque transmission means that is movably held and is connected to at least one shaft of the engine and extends from the shaft of the engine to an interior region of the aircraft fuselage, and at an end pointing away from the engine has at least one interface for introducing a torque. At the interface of the torque transmission means it is possible both to operate mechanical and to start the engine. Consequently in the aircraft it is possible to essentially do without converting mechanical energy to electrical energy and the subsequent use of electrical energy for generating mechanical power. This is particularly favorable in the case of twin-engine commercial aircraft that are used on short hauls.