Abstract: A structural component for a vehicle, in particular an aircraft or spacecraft, includes a fiber composite laminate comprising an electric energy store which is configured as a multilayer electrochemical fiber composite battery for storing electric energy in a rechargeable manner; and an electrothermal temperature regulation sublayer which is configured for supplying thermal energy to the electric energy store and conducting thermal energy away from the electric energy store when required in order to regulate the temperature. The structural component further comprises a control device which is configured for controlling the temperature regulation of the electric energy store by means of the electrothermal temperature regulation sublayer.

Abstract: A flow body for an aircraft includes a skin having a first flow surface, having a flow influencing section with at least one first layer, at least one separator layer, at least one third layer, and at least one base layer. The first layer includes lithiated carbon fibers embedded into a matrix to form a negative electrode. The third layer includes carbon fibers with an electrode active material coating to form a positive electrode. The separator layer includes a non-conductive material for electrically isolating the first layer and the third layer from each other. The flow influencing section is configured for selectively raising a region of the arrangement of first layer, separator layer and third layer from the base layer upon application of a voltage between the first and third layers to form a bump on the flow body.

Abstract: With the measures described herein, a structural composite laminate is provided that includes a structural fuel cell, a structural supercondensator and a structural battery. Each of these components is configured in a self-supporting manner, such that aircraft parts, like exterior panels, may be manufactured from the laminate. The aircraft parts are capable of generating electrical energy by means of the structural fuel cell and distribute the electrical energy over the whole aircraft without cabling. Furthermore, short power demand peaks can be absorbed by the structural supercondensator, whereas the basic load is supplied by the structural battery.

Abstract: A battery with a layers including a first layer which is electrically conductive, a second layer consisting essentially of carbon-fiber-reinforced plastic, a third layer of glass-fiber-reinforced plastic, a fourth layer of carbon-fiber-reinforced plastic and LiFePO4, where the ratio by weight of LiFePO4 to carbon fiber is from 2:1 to 2.5:1, and a fifth layer which is electrically conductive, wherein the battery has substantially been jacketed by a layer made of glass-fiber-filled polyester.

Abstract: An arrangement of a structural element for an aerospace vehicle and a battery set. The structural element extends along a longitudinal direction and has a main web, a first flange and a second flange. The flanges extend away from the main web and are defined by flange edges extending along the longitudinal direction. The first flange, the second flange and the main web form a U-shaped profile defining a cavity. The battery set includes a baseplate and at least one battery on the baseplate. The structural element and the battery set are formed such that the baseplate can be releasably attached to the structural element. The baseplate extends between flange edges and the battery is received in the cavity when the battery set is mounted to the structural element. Further, an aerospace vehicle including such an arrangement, a structural element for an aerospace vehicle and a battery set are disclosed.

Abstract: A battery core has a positive electrode layer, a separator layer and a negative electrode layer. The separator layer is arranged between the positive electrode layer and the negative electrode layer. The positive electrode layer, the separator layer and the negative electrode layer have nanocellulose fibres. The battery core is folded and forms a cellular structure as a core for a sandwich component. The sandwich component has an upper covering layer, a lower covering layer and a battery core. The battery core is arranged between the upper covering layer and the lower covering layer. A method for producing such a battery core is also described.

Abstract: An indicator apparatus for guiding interior aircraft occupants has a mounting device fastenable to a wall portion of the interior and having an indicator conveying an item of visual information to occupants. An indicator can be or is operated electrically, and the indicator can be or is connected to a power supply for operation. To create an indicator apparatus which helps improve orientation of cabin passengers, can be produced, installed and serviced easily, and which can be operated in a fail-safe manner in an emergency situation of the aircraft, the indicator has an at least one-piece layer, on which circuitry necessary for operation is provided in an integrated fashion, and the power supply is formed by a composite structure battery built up layer by layer and can be or is connected to the layer. A method for producing an indicator apparatus of this kind is disclosed.

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 railway wagon for semitrailers and the like may include a first bogie, a second bogie, and a carrying section therebetween. An elongated channel configured to receive conduits for air, hydraulics and/or electronics may extend between the two bogies. The media channel may be lowered in a mechanical way when the carrying section is turned out to a loading/unloading position.

Abstract: A structural component for an aircraft including at least one heatable component section having a layer structure including an inner base structure, at least one heating layer having carbon allotropes embedded in a matrix material, at least one first group of consecutive layers including at least one anode layer, at least one first insulating layer, and at least one cathode layer having an electroactive coating. The first group of layers are arranged between the inner base structure and the at least one heating layer, and at least one protective layer is arranged outside the heating layer. The first group of layers constitute a structural battery. The at least one anode layer and the at least one cathode layer are electrically connectable with the heating layer.

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: An electrically heatable layer stack is disclosed. The electrically heatable layer stack includes at least two substrate layers, and at least one carbon nanotubes-, CNT-, layer, which is arranged between the substrate layers and which is configured to conduct an electric current. The substrate layers and the at least one CNT-layer are configured to produce heating of at least one of the substrate layers when an electric current is applied to the at least one CNT-layer. A vehicle assembly group, an aircraft, a method and a system for manufacturing an electrically heatable layer stack are also disclosed.

Abstract: A vortex generator apparatus for an aircraft includes a surface section having a receiving recess, a vortex generator having a first edge, an opposite second edge and a vortex generator surface component extending from the first edge to the second edge, wherein the first edge is fixedly arranged in or adjacent to the receiving recess. The vortex generator surface component includes at least one electroactive polymer assembly, wherein the at least one electroactive polymer is switchable into an extended state by applying an electrical voltage and into a neutral state by removing the electrical voltage. The electroactive polymer assembly and the vortex generator surface component are configured to retract the vortex generator surface component completely into the receiving recess in the neutral state of the electroactive polymer assembly and to extend the vortex generator surface component from the receiving recess in the extended state.

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: The invention relates to a belt deflector (10) having a main element (20) which is fastenable to a vehicle structure, and a belt contact element (30) which is movable in relation to the main element (20) and forms a belt contact face (SA30) or belt contact edge for a seat belt (40) that is to be deflected, wherein the belt deflector (10) has a deformable intermediate element (50) which, during a relative movement of the movable belt contact element (30) relative to the main element (20) in the direction of the intermediate element (50), is deformed and is pressed against the seat belt (40) by this deformation. According to the invention, provision is made that the belt contact element (30) forms a mating clamping face (G30), and a belt strap portion (41) of the seat belt (40) is arranged between the intermediate element (50) and the mating clamping face (G30), and, during said relative movement, the intermediate element (50) presses the belt strap portion (41) onto the mating clamping face (G30).

Abstract: A method for laser shock peening of a component, in particular at points that are difficult to access, includes the steps of: supplying a first end of a flexible optical waveguide, which end is designed in the form of an optical waveguide brush having a plurality of divergent optical waveguide fibres, to a point of the component to be treated by laser shock peening; generating laser shock pulses, which are coupled in at a second end of the optical waveguide, by a laser beam source; and discharging the laser shock pulses by the optical waveguide brush into a process zone at the point of the component to be treated. A use of an optical waveguide brush, a system for laser shock peening of a component, and a mobile laser shock treatment station are also described.

Abstract: A structural component for a vehicle has a battery construction having a solid-electrolyte matrix material, a first layer of carbon fibres having a cathode-active coating, embedded in said solid-electrolyte matrix material, a second layer of carbon fibres without a cathode-active coating, embedded in said solid-electrolyte matrix material, and at least one electrically isolating barrier layer disposed between said first layer and said second layer. The structural component has a first collector layer and a second collector layer disposed on the first layer and the second layer, respectively, on a side that faces away from the barrier layer. The first collector layer and the second collector layer are configured from a flexible, moldable and porous layer of carbon allotropes.

Abstract: A riblet film for reducing the air resistance of aircraft, comprising a suspension with magnetic particles enclosed therein. Depending on the pattern of a magnetic field acting on the riblet film, the magnetic field that is acting can be made visible, at least in certain regions, by changing the orientation of the magnetic particles. The riblet film allows an inspection of the aircraft structure located under the riblet film through the riblet film.

Abstract: A method and an apparatus for welding a first object to a second object, wherein the first object is produced from a thermoset and comprises a thermoplastic material outer layer, wherein the second object comprises at least one thermoplastic material outer layer. In addition, a layer of carbon nanotubes is applied to the thermoplastic material outer layer of the first object, and the second object is placed onto the first object. At least some of the thermoplastic material outer layer of the second object lies atop the applied layer of carbon nanotubes. In addition, a potential is applied to the layer of carbon nanotubes, such that an electrical current flows through the carbon nanotubes, wherein the thermoplastic material outer layer of the first object and the thermoplastic material outer layer of the second object are heated and are welded to one another.

Abstract: A method for producing a vehicle component from a fiber-reinforced plastic including providing a skin panel having an inner side, outer side and mounting portion. The skin panel is a fiber-reinforced thermoplastic material. At least one stiffening component has a connection surface. The stiffening component is a fiber-reinforced thermoplastic material. The stiffening component and skin panel are contacted wherein the connection surface lies on the mounting portion. The method includes areally warming a joining zone so the stiffening component and skin panel are welded together. The joining zone is cooled. A determined geometry of the combination of stiffening component and skin panel is compared with a predefinable geometry. The joining zone is re-warmed, deforming the stiffening component and the skin panel, and the method includes cooling in order to attain the predefinable geometry if the determined geometry deviates from the predefinable geometry.