Abstract: A method for forming a structural component for an airframe of an aircraft or spacecraft, includes: providing a prefabricated shell element comprising a thermoplastic substrate; and applying a stiffening structure to the shell element by additive manufacturing, wherein a plurality of continuous thermoplastic filaments filled with reinforcing fibers are continuously heated and three dimensionally formed such that the filaments are crossing and bonded to each other at a plurality of crossing points to form a three dimensional grid truss integrally formed on the shell element. A corresponding structural component and an aircraft or spacecraft including such a structural component are also described.

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 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 heatable water pipe for an aircraft, having a heat-generating ply which extends in the pipe circumferential direction and the pipe longitudinal direction, at least in some section or sections. The heat-generating ply comprises a fiber composite layer containing fibers and a matrix surrounding the fibers, wherein at least some of the fibers are formed as conducting fibers. In this context, the conducting fibers are formed as carbon fibers with an electrically insulating coating. By virtue of the electrically insulating coating, leakage currents can be avoided. The carbon fibers serve both as heating elements and as reinforcing fibers in the fiber composite layer.

Abstract: A system for producing a component from a fiber-reinforced plastic material with a multi-axial motion device having a base, and a holding installation movable by the motion device. A material dispensing head is disposed on the holding installation. There is at least one fiber dispensing installation and at least one thermoplastic dispensing roll. At least one first feed line is coupled to the dispensing installation and at least one second feed line is coupled to the thermoplastic dispensing roll. The dispensing installation and the dispensing roll are disposed outside the motion device. The first and second feed lines are connected to the material dispensing head. The material dispensing head is configured to melt plastic material delivered by the dispensing roll and, when dispensing the fibers delivered by the dispensing installation, for coating the fibers with the melted plastic material or embedding the fibers in the plastic material.

Abstract: A battery holding device for an aircraft, having a support formed from a solid foam and a continuous-fiber-reinforced plastic material connected to the foam, a plurality of cavities into which batteries are insertable, and at least one cooling duct for cooling batteries that are insertable into the cavities. The cavities are formed by the support. An aircraft having a battery holding device of this type is also provided.

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 transfer arrangement (13) for transferring a semi-trailer (8) onto an intermodal pocket wagon (1) from a ground location beside the wagon, or vice versa, includes base roller beams (15) of first lifting means (15, 20?) supported by the ground at the ground location and intended for lifting the semi-trailer (8) up from the ground, corresponding wagon roller beams (17) of second lifting means (16-18) to be supported by the rail or the ground under the wagon and intended for being elevated to substantially the same height as the base roller beams (15) or for being lowered towards the ground, and transfer means (19) for transferring the semi-trailer (8) sideways from the first to the second lifting means in the elevated condition thereof.

Abstract: A heatable floor panel for an aircraft, with a supporting level, a heat-generating level and a heat-conducting level. The heat-generating level comprises a fiber composite layer with fibers and with a matrix surrounding the fibers. The fibers are at least partially formed as conducting fiber, and the conducting fibers are formed as carbon fibers with an electrically insulating coating. The conducting fibers integrated in the floor panel in order to conduct a heating current through them. Due to the electrically insulating coating of the conducting fibers, leakage currents are avoided. The carbon fibers serve not only as heating elements, but, at the same time, also as reinforcing fibers of the fiber composite layer or of the floor panel.

Abstract: A magnetically levitated arrangement for contactless movement over a surface comprising a magnetizable reaction surface and a magnetically levitated unit arranged to interact with the reaction surface. The levitated unit has at least one pair of rotatable rotary magnet units, each unit rotatable about a rotation axis and having magnetic elements arranged with alternating poles and respectively substantially parallel to the rotation axis in a pole connection direction. Each rotary unit pair is formed to interact, due to rotation of the two rotary units in opposite directions relative to one another and relative to the reaction surface, in such a way with the reaction surface, that forces are generated holding the levitated unit at a distance from the reaction surface, and due to the opposite rotation directions of the rotary units of each pair, a directed drive force moving the levitated unit relative to the reaction surface is generated.

Abstract: A method for manufacturing a rivet connection of a fiber composite component. The method includes positioning a first component which contains a fiber composite material in an overlap joint with a second component, laser-drilling a shared through-hole at least through the fiber composite material of the first component, inserting a rivet into the through-hole and fixing the rivet to the first and to the second component.

Abstract: Production methods for producing a fiber-reinforced metal component having a metal matrix which is penetrated by a plurality of reinforcing fibers are provided. One method includes depositing in layers reinforcing fibers in fiber layers, depositing in layers and liquefying a metal modelling material in matrix material layers, and consolidating in layers the metal modelling material in adjacently deposited matrix material layers to form the metal matrix of the fiber-reinforced metal component. Here, the metal component is formed integrally from alternately deposited matrix material layers and fiber layers. An alternative method includes introducing an open three-dimensional fiberwoven fabric consisting of reinforcing fibers into a casting mold, pouring a liquid metal modelling material into the casting mold and consolidating the metal modelling material to form the metal matrix of the fiber-reinforced metal component.

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.

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 method for producing a frame component for a door frame structure of an aircraft. A connecting zone is generated on a first and a second assembly surface of a connecting component in each case by generating a surface texture on the assembly surfaces, wherein the connecting component is formed from a metal material. The assembly surfaces of the connecting component are placed against a door frame member and against an attachment member, wherein the door frame member and the attachment member are each formed from a fiber-reinforced thermoplastics material. Furthermore, the connecting component and the door frame member are welded, and the connecting component and the attachment member are welded. A frame component and a door frame structure are also described.

Abstract: A method for producing a structural section of a vehicle comprises the steps of providing multiple separate skin panels of a fiber-reinforced plastic having an inner side, an outer side and a border running peripherally around the respective skin panel; arranging at least one stiffening component of a fiber-reinforced plastic on each skin panel, on the respective inner side; integrally connecting the respective at least one stiffening component to the skin panels concerned to form a structural component; arranging at least two structural components on a carrier, so that at least regions of the borders of the structural components concerned are in surface-area contact; and integrally connecting the regions of the borders that are in surface-area contact to one another.

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: A structural component includes a composite laminate built up of a plurality of layers of carbon fibers, wherein the layers of carbon fibers are oriented in different directions, wherein the carbon fibers are surrounded by a conductive polymer resin, wherein the carbon fibers of at least one of the layers comprise an electrically insulating coating, and wherein at least one of the coated carbon fibers extend through its respective layer to form an electrical connection between ends of the layer spaced apart from one another.

Abstract: A casing for connecting electrical lines printed on a foil to a voltage supply. The casing comprises a space, terminal pads and a block. The casing has an opening between a first wall of the space and a first outer side of the casing. The terminal pads are at least partially arranged on a second outer side of the casing. The block is configured to move between a first position and a second position, both within the space. The block is configured to press the foil against a second wall of the space when the block is in the first position. The block is configured to establish an electrical connection between the electrical lines printed on the foil and the terminal pads when the block is in the first position. The space is configured to receive the foil through the opening when the block is in the second position.

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.