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: An energy storage device for storing electrical energy, for example for use in an aircraft, includes a cathode layer with at least one ply of carbon fibers, the carbon fibers being coated with a Li-ion containing coating and embedded in an electrolytic polymer matrix material, an anode layer including at least one ply of carbon fibers, the carbon fibers being embedded in an electrolytic polymer matrix material, a separator layer including at least one ply of fibers, the fibers being embedded in an electrolytic polymer matrix material, wherein the separator layer is sandwiched between the cathode layer and the anode layer, and carbon nanotubes extending between and partly into the separator layer and the cathode layer, or the separator layer and the anode layer, or the separator layer and the cathode layer and the separator layer and the anode layer.

Abstract: A door arrangement for an aircraft comprising a door designed to close an aperture in an outer skin of the aircraft, and a articulated arm which is fixed by a first end to the door and which is designed to move the door in at least two translational directions and at least two rotational directions. An aircraft area with this door arrangement and an aircraft having such an aircraft area are furthermore provided. The aircraft area comprises a door aperture arranged in an outer skin of an aircraft, and a door arrangement. Here the door of the door arrangement may be designed to close the door aperture from an inside of the outer skin, and the articulated arm of the door arrangement may be fixed to the aircraft area.

Abstract: A fiber composite component with integrated active electromagnetic shielding includes a fiber composite layer having reinforcing fibers, and an electric conductor, which extends on the fiber composite layer along the fiber composite layer and produces an electromagnetic field during operation, wherein a proportion of the reinforcing fibers is designed as conduction fibers, which are arranged to follow the electric conductor within the fiber composite layer and are designed to produce an opposing electromagnetic field during operation which attenuates the electromagnetic field of the electric conductor.

Abstract: A system is proposed, using which a material is dispensed in a web shape to additively produce a component. An in situ material check is performed, wherein if a geometric deviation lying outside a tolerance is established, material dispensing is interrupted to carry out finish compacting of a dispensed material web by way of a compacting unit.

Abstract: An autoclave for welding thermoplastic composite parts comprises a sealed process chamber, a pressure source, a microwave source and a workpiece supporting member configured to support at least two thermoplastic composite parts which contact each other in an abutting section within the process chamber. The pressure source is configured to generate positive pressure in the process chamber which is higher than an ambient pressure surrounding the process chamber while the microwave source emits microwaves towards the abutting section in order to locally melt the thermoplastic composite parts and weld them together in the region of the abutting section.

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: A structural composite component, in particular for an aircraft or spacecraft, has a lightning strike protection layer, and a composite battery comprising a cathode layer, wherein the lighting strike protection layer is formed integrated with the cathode layer.

Abstract: A method is proposed for installing system components in a portion of an aircraft fuselage. The method provides at least one planar structural arrangement to be secured on or in the aircraft fuselage, secures system components on the structural arrangement, couples system lines to the system components and arranges the system lines on the structural arrangement. The method includes positioning of the structural arrangement with the system components and system lines arranged thereon at a designated installation location of the structural arrangement, and mechanical coupling of the structural arrangement to the aircraft fuselage.

Abstract: A method for manufacturing a fuselage component for an aircraft includes building up, on a surface of a two-dimensional shell part composed of a fibre composite material, stiffening profiles crossing at an intersection from a plurality of layers, superimposed on one another in a thickness direction, which are each formed by applying filaments, which each comprise a fibre bundle embedded in a thermoplastic material. Stabilising layers, within which the filaments extend beyond the intersection, are formed from the filaments in each of the stiffening profiles. A fuselage component and an aircraft, which comprises at least one such fuselage component, are furthermore described.

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: 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 producing a connecting device for connecting films with conductor tracks includes the steps of laying a first film with conductor tracks onto a forming die, applying a first lower shell of a plastic material onto a first end portion of the forming die, producing a cut-out and shifting the first film so that the cut-out lies completely on the first lower shell, applying upper conductor tracks of a conductive material onto the first lower shell so that the upper conductor tracks overlap with the conductor tracks of the first film, and applying a first upper shell of a plastic material onto the first lower shell so that the first film, the first lower shell and the first upper shell connect together by substance bonding to form a first connector. In this way, an integral connector can be provided on each film.

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: A press for pressing a component, such as a thermoplastic consolidation and/or forming press, has a first fixed part as a first pressing tool, a movable part as a second pressing tool for pressing a component together with the first pressing tool, and a second fixed part for applying a pressing force to the movable part, wherein the second fixed part and the movable part apply the pressing force generated via interaction between a magnetic field of a pressing magnet and a superconductor cooled below its step temperature.

Abstract: A heatable leading-edge apparatus for an aircraft having a main structure and a heating layer. The heating layer comprises a fiber composite layer with fibers and with a matrix which surrounds the fibers. The fibers are at least partially formed as conducting fibers, such as carbon fibers, with an electrically insulating coating. Owing to the conducting fibers, which act as electrical heating elements, a desired surface temperature can be established on an outer side of the leading-edge apparatus.

Abstract: A system for the state monitoring of a fiber composite structure, in particular of an aircraft or spacecraft, include a fiber composite structure; a multiplicity of state sensors which, on and/or in the fiber composite structure, are configured to detect state data of the fiber composite structure an energy store configured to store electrical energy for the supply of the state sensors in a rechargeable manner; an energy generating layer configured, on the fiber composite structure, to generate the electrical energy for the supply of the state sensors; and a data processing unit configured for wireless data communication with the state sensors for the further processing of the detected state data.

Abstract: A fiber composite component with integrated active electromagnetic shielding includes a fiber composite layer having reinforcing fibers, and an electric conductor, which extends on the fiber composite layer along the fiber composite layer and produces an electromagnetic field during operation, wherein a proportion of the reinforcing fibers is designed as conduction fibers, which are arranged to follow the electric conductor within the fiber composite layer and are designed to produce an opposing electromagnetic field during operation which attenuates the electromagnetic field of the electric conductor.

Abstract: A fuselage structure for an aircraft has a frame structure, which extends in a circumferential direction and has a first connecting section and a second connecting section, which is arranged spaced apart from the first connecting section, a reinforcing structure, which extends between the first and the second connecting sections and is connected respectively to the first and the second connecting sections, an outer shell, which is secured on an outer side of the reinforcing structure, and an inner shell, which is secured on an inner side of the reinforcing structure. The reinforcing structure has a profiled cross section when viewed in a longitudinal direction extending transversely to the circumferential direction and, together with the inner shell and the outer shell, forms a plurality of channels, which are adjacent to one another in the circumferential direction and each extend in the longitudinal direction.

Abstract: A structural component for an aircraft includes at least one heatable component portion. The heatable component portion has a layered construction with an inner base structure, a first insulating layer arranged outside the inner base structure, a functional layer of carbon allotropes embedded in a matrix material, which is arranged outside the first insulating layer, and at least one protective layer arranged outside the functional layer. The structural component also includes an electrical connection device connected to the functional layer for selectively applying an electrical current to the functional layer to heat the functional layer.