Abstract: A panelling part for a cabin of a means of transportation is proposed, which includes at least one display unit and at least one control unit, which are produced by printing and equipping at least one film, which is applied to a panelling element. The control unit can communicate wirelessly with an external electronics unit, so that the panelling part only requires a power terminal to implement electronic functions. Functions can be retrofitted easily by replacing the at least one film.

Abstract: For the purpose of simple integration of conductor circuits into composite material components, a method and an apparatus for producing composite material components of this kind are proposed, wherein a conductor circuit is printed onto or applied in some other way to a support, is provided with a thermally activatable adhesive and then the support is applied to a blank of the composite material component for joint curing. The curing at high pressure and high temperature creates a strong connection between the conductor circuit and the composite material component.

Abstract: Validating additively manufactured components is carried out by transmitting to a distributed validation network printing specification data for a component that is to be additively manufactured, validating the printing specification data, and adding the printing specification data, together with a cryptographically encoded checksum, to a print history log, transmitting the printing specification to a 3D printing device, and implementing a generative manufacturing process for the component that is to be additively manufactured in accordance with the transmitted printing specification data. While the generative manufacturing process is being carried out, in each case following specified manufacturing stages, a plurality of manufacturing parameters prevailing in the preceding manufacturing stage are transmitted to the distributed validation network.

Abstract: A power supply unit includes a housing having at least one input terminal and at least one output terminal, an AC-DC converter which is arranged in the housing and which is connected to the input terminal, a DC-DC converter which is arranged in the housing and which is connected to the output terminal; and a capacitor which forms a structural part of the housing. Furthermore, an on-board power supply network of an aircraft or spacecraft is also described.

Abstract: A fiber composite component includes an integrated structural health sensor arrangement, wherein the component includes a plurality of layers of fibers embedded in a matrix material, wherein the layers include at least two strain sensing fibers arranged parallel and at a distance to each other, wherein the strain sensing fibers are lithiated carbon fibers having piezoelectric characteristics.

Abstract: A skin panel with an energy-storing layer for an aircraft or spacecraft comprises structural layers for providing structural stability to the skin panel, at least one of the structural layers forming an exterior supporting layer of the skin panel and at least one of the structural layers forming an interior supporting layer of the skin panel. Primary functional layers are embedded between the exterior supporting layer and the interior supporting layer for providing functional capabilities to the skin panel. The structural layers and the primary functional layers are formed together as a composite laminate and the functional layers comprise an energy-storing layer configured as a structural electro-chemical battery. The present disclosure further pertains to a method for manufacturing such an energy-storing layer for a skin panel of an aircraft or spacecraft.

Abstract: A method for connecting two aircraft components composed of thermoplastic composite material by a rivet. The two aircraft components are arranged, in sections, areally on one another, before bores in the two aircraft components are expanded by a mandrel element such that the bores, after the expansion, form one continuous bore for receiving the rivet. Here, the two aircraft components are locally warmed by the mandrel element such that, during the expansion of the bores, the components are thermoplastically deformed. The mandrel element is inserted through the first bore into the second bore. The rivet is introduced into the continuous bore. A system for carrying out the method is also disclosed.

Abstract: A method for integrating a fuel cell unit into a vehicle structural component, includes determining an available receiving space in an interior structural component of the vehicle, providing two casing parts assembleable to a closed casing, providing a fuel cell having an anode, a cathode and an electrolyte, assembling the casing parts and the fuel cell to form the fuel cell unit, and inserting the fuel cell unit into the receiving space. A casing part is additively manufactured such that the fuel cell unit precisely fits into the receiving space. A casing part includes an exterior fuel inlet and an interior fuel distributor for leading a fuel from the inlet to a fuel outlet couplable with the fuel cell. A casing part includes an exterior oxidant inlet and an interior oxidant distributor for leading an oxidant from the inlet to an oxidant outlet couplable with the fuel cell.

Abstract: A tolerance compensation subassembly in the form of a tolerance compensation element or a tolerance compensation region to improve the production, maintenance and repair of aircraft. The tolerance compensation subassembly contains an actuator which is formed from an electro-active polymer so that the tolerance compensation subassembly is electrically switchable between a fixed state and a non-fixed state. As a result, automation of the assembly of aircraft components on each other can be enabled or facilitated.

Abstract: An aircraft seat fastening assembly, due to the use of electroactive polymers, facilitates the compensation of tolerances and the fastening of aircraft seats in the passenger cabin of the aircraft. A fixing actuator contains the electroactive polymer and can be switched electrically between a fixed state, in which a movement of a fastening region is not possible, and a non-fixed state, in which a movement of the fastening region is possible in a vertical direction. The aircraft seats can thereby be displaced in a continuously variable manner along the aircraft seat fastening rail. The aircraft seats can also be locked in a fully automated manner, and possibly from a central location. It is also conceivable to individually control the aircraft seats and/or the group(s) of seats.

Abstract: A transfer arrangement for transferring a semi-trailer onto an intermodal pocket wagon from a ground location beside the wagon, or vice versa, may include base roller beams of a first lifting mechanism supported by the ground at the ground location and intended for lifting the semi-trailer up from the ground. Corresponding wagon roller beams of a second lifting mechanism may be supported by the rail or the ground under the wagon. The wagon roller beams may be elevated to substantially the same height as the base roller beams or lowered towards the ground. A transfer mechanism may be provided for transferring the semi-trailer sideways from the first lifting mechanism to the second lifting mechanism in the elevated condition thereof.

Abstract: A panel (1000) for a cabin of an aircraft, the panel (1000) including a laminate (150) with a first layer formed of lithiated carbon fibers (100), a second layer form of carbon fibers with a cathode lithium coating (200), and an electrolyte-containing separator (300) interposed between the first and the second layers and a pressure sensor (50a, 50b) on an outer surface of the laminate (150), and a switch (40) to regulate a voltage to the laminate (150) based on an output of the pressure sensor (50a, 50b) so that the panel (1000) expands.

Abstract: A structural component has a plurality of material layers, which are stacked and bonded together in a thickness direction, wherein at least one of the material layers is formed by a fibre composite material, and wherein an outermost material layer in relation to the thickness direction is formed at least in sections by a sensor device, having at least one sensor unit with an electroactive polymer arranged between electrically conductive electrodes. Moreover, a system and a method for the detection of damage and an aircraft are described.

Abstract: A method for repairing a component constructed in multiple layers from a layer composite material comprises a step of removing material of the layer composite material of the component in the region of damage to the component in order to form a scarfed cutout, such that a scarfed peripheral contour formed from a plurality of layers of the component is formed. Furthermore, fiber-reinforced plastic strips, which exhibit a curable plastic material in an uncured state, are applied in layers in the cutout in order to create a replacement-structure semifinished product that is complementary to and butts against the scarfed peripheral contour of the component. In a further step, the curable plastic material contained in the fiber-reinforced plastic strips is cured in order to create a replacement structure and for joining the replacement structure to the component.

Abstract: The invention relates to a belt deflector with a main element (100) that can be attached to the structure of a vehicle, and with a belt support element (200) that is movable relative to the main element (100) and forms a support surface (231) or support edge for a safety belt (20) to be deflected. According to the invention, the belt deflector comprises an intermediate element (300, 400) that is deformed when the movable belt support element (200) is moved relative to the main element (100), in the direction of the intermediate element (300, 400), and because of this deformation is pressed against the safety belt (20).

Abstract: A battery has an integrated flame retardant device, wherein the battery has: a cathode layer, a separating layer, and an anode layer, wherein the separating layer is arranged between the cathode layer and the anode layer, wherein the separating layer is impermeable to electrons and permeable to at least one positive type of ion, wherein the separating layer has a flame retardant device having at least one glass fibre, which includes a closed cavity, and wherein a flame retardant is arranged in the cavity. The battery has increased fire resistance.

Abstract: A method for manufacturing a lining panel with integrated electric lines for a lining of a passenger cabin of an aircraft or spacecraft includes using an additive manufacturing (AM) or 3D printing technique to form the electric lines on or into a panel body of the lining panel. A lining panel with integrated electric lines for a lining of a passenger cabin of an aircraft or spacecraft includes a panel body and electric lines being formed on or into the panel body using an AM or 3D printing technique.

Abstract: A battery cell includes an anode, a cathode, and a separator between the anode and the cathode, wherein at least one of the anode or the cathode includes at least a carbon fiber ply comprising carbon fibers, the carbon fiber ply having a thickness of less than 90 micrometers. Also disclosed are a battery and an aircraft including such battery cell, and a method for manufacturing such battery cell.

Abstract: A three-dimensional printing device includes a movable unit with a superconductor and a printing head arrangement for printing a printing material, a magnetic field generator adapted to generate a magnetic field, and a control device. The magnetic field generator and the movable unit are adapted for coupling in a force-locking manner by means of frozen magnetic flux, and the controlling device is adapted to control a magnetic field strength of the magnetic field generator.

Abstract: A fiber composite component having an integrated structural health sensor arrangement includes a plurality of layers of fibers embedded in a matrix material, at least two rupture sensing fibers arranged on or in at least one of the layers, wherein the rupture sensing fibers are carbon fibers having an electrically insulating coating, and two electrical connection devices, each being accessible from an outer delimiting surface or an outer edge of the component, wherein the electrical connection devices are connected to different ends of the rupture sensing fibers.