Abstract: A component for an aircraft and an aircraft with such component. The component includes a heat source enclosed by a housing, heat exchanger, heat sink, at least one structural suspension element, and an air duct. Each structural suspension element is attached to an inner surface of the housing and supports one or more of the heat source within the housing. The heat sink is part of the housing and configured to guide air from an inside of the housing an outside of the housing. Each heat exchanger is thermally coupled to the heat source. Each heat exchanger is fluidly connected to the heat sink via an inlet line and a return line for a coolant. The air duct is configured to guide ambient air from the outside through the housing, past each of the at least one structural suspension element, and through the heat sink out of the housing.

Abstract: A process is proposed for producing a bipolar plate for an electrochemical device, said process comprising providing a first main plate body and a second main plate body as fibrous shaped bodies including carbon fibers and each having a joining face and an opposing useful face, infiltrating the main plate bodies with at least one carbon allotrope, locally applying silicon to respective joining sites in the joining faces, placing the joining faces against one another, such that the joining sites rest against one another and the useful faces of the two main plate bodies face away from one another, and at least locally heating the joining sites, such that the silicon melts and reacts with adjoining carbon to form a silicon-carbon bond.

Abstract: An aircraft, including a hydrogen consumer and a hydrogen supply device for supplying the hydrogen consumer with hydrogen, the hydrogen supply device having a cryogenic hydrogen tank for storing liquid hydrogen. In order to lower the weight while improving performance of the hydrogen tank during different flight conditions, embodiments of the aircraft further include a suspension arrangement with suspension elements for suspending the hydrogen tank on a structure of the aircraft, wherein the hydrogen tank includes a tank wall made from fiber reinforced composite material, and wherein the suspension arrangement includes a plurality of first tensile loaded dry fiber suspension elements fixed to load introduction areas on the hydrogen tank such that the suspension elements extend essentially tangential to a surface of the hydrogen tank at the associated load introduction area.

Abstract: In order to improve usability of hybrid or fully electric aircraft, a fuel cell having improved efficiency and increased volume/weight specific energy density is provided. The fuel cell has a self-supporting membrane structure that is formed as a triply periodic level surface, which separates a first cavity supplied with gaseous fuel from a second cavity supplied with gaseous oxidizer in a gas-sealed manner while connecting the cavities in an ion-conductive manner.

Abstract: A joining method and assembly for an aircraft. To improve the characteristics or permit hitherto impossible connections between thermoplastic and thermoset components, a multi-material joining method is disclosed in which a thermoplastic connecting region is formed on the thermoplastic component. The connecting region is connected to the thermoset component by interdiffusion. For this purpose, the uncured second component is brought into contact with the connecting region and heat is supplied. An interdiffusion layer is formed which fixedly connects the second component and the connecting region to one another and thus joins the first component to the second component.

Abstract: A method for producing a layer of a device for electromagnetic radiation absorption, includes: providing a ply of powder material in the layer to be produced of the device; providing a predefined concentration distribution of particles for electromagnetic radiation absorption in the layer; providing a first binder and a second binder for the powder materials, wherein the first binder includes particles for the absorption of electromagnetic radiation, wherein the second binder includes a lower concentration of identical and/or different particles than the first binder; determining a mixing ratio between the first binder and the second binder for every position in the layer; selecting a position of the layer; mixing the first and second binder according to the mixing ratio for the selected position; wetting the powder material at the selected position using the mixed first and second binders; and repeating selecting, mixing, and wetting to produce the layer.

Abstract: A joining method and assembly for an aircraft. To improve the characteristics or permit hitherto impossible connections between thermoplastic and thermoset components, a multi-material joining method is disclosed in which a thermoplastic connecting region is formed on the thermoplastic component. The connecting region is connected to the thermoset component by interdiffusion. For this purpose, the uncured second component is brought into contact with the connecting region and heat is supplied. An interdiffusion layer is formed which fixedly connects the second component and the connecting region to one another and thus joins the first component to the second component.

Abstract: To improve the range of application of manufacturing methods for fiber-reinforced polymer or metal hybrid composite components, and preferably to enable the introduction of fiber bundles into a larger number of geometries, such as branches, merging points and intersections, a production method for producing a component including a composite material with a fiber reinforcement which is formed from fiber bundles and resin is disclosed. A component body with tube-like cavities is initially provided. Curable resin is introduced into the cavities. A pulling apparatus for the fiber bundles is also inserted into at least one of the cavities. The pulling apparatus includes at least one pulling member suitable for pulling the fiber bundles and transmitting compressive force. As a result of pulling of the pulling member, the fiber bundles are pulled into the cavities.

Abstract: For improving storage of hydrogen in a vehicle, a hydrogen tank assembly is provided for a vehicle. The hydrogen tank assembly includes an inner tank wall defining a hydrogen tank volume configured for storing liquid hydrogen; and an outer hydrogen collector defining, together with the inner tank wall, at least one cavity outside of the hydrogen tank volume and including at least one hydrogen outlet for leading gaseous hydrogen which leaks from the hydrogen tank through the inner tank wall into the at least one cavity to a hydrogen storage or a hydrogen consumer.

Abstract: A hydrogen tank assembly is provided for use in vehicles, such as aircraft. The hydrogen tank assembly has an inner tank wall, an outer tank wall, and an inert gas source. The inner tank wall defines a hydrogen tank volume that is surrounded by a shroud volume which is defined by the outer tank wall. The hydrogen tank volume is filled with cryogenic hydrogen and has a higher pressure than the shroud volume that is filled with an inert gas, such as helium. The counter-pressure of the inert gas prevents micro-cracks in the inner tank wall and increases the in-service life.

Abstract: To achieve a composite material part with a fully load adapted 3D fiber reinforcement with low costs for tools and process, a method is provided for manufacturing a part made of composite material with a continuous fiber reinforcement. The method comprises the steps of providing a body with tubular cavities and having at least one first portion made from a first polymer material and at least one second portion made from a second polymer material, introducing resin and continuous fibers into the tubular cavities, and removing at least a part of the second polymer material.

Abstract: In order to improve usability of hybrid or fully electric aircraft, a fuel cell having improved efficiency and increased volume/weight specific energy density is provided. The fuel cell has a self-supporting membrane structure that is formed as a triply periodic level surface, which separates a first cavity supplied with gaseous fuel from a second cavity supplied with gaseous oxidizer in a gas-sealed manner while connecting the cavities in an ion-conductive manner.

Abstract: A joining method and assembly for an aircraft. To improve the characteristics or permit hitherto impossible connections between thermoplastic and thermoset components, a multi-material joining method is disclosed in which a thermoplastic connecting region is formed on the thermoplastic component. The connecting region is connected to the thermoset component by interdiffusion. For this purpose, the uncured second component is brought into contact with the connecting region and heat is supplied. An interdiffusion layer is formed which fixedly connects the second component and the connecting region to one another and thus joins the first component to the second component.

Abstract: To improve the range of application of manufacturing methods for fiber-reinforced polymer or metal hybrid composite components, and preferably to enable the introduction of fiber bundles into a larger number of geometries, such as branches, merging points and intersections, a production method for producing a component including a composite material with a fiber reinforcement which is formed from fiber bundles and resin is disclosed. A component body with tube-like cavities is initially provided. Curable resin is introduced into the cavities. A pulling apparatus for the fiber bundles is also inserted into at least one of the cavities. The pulling apparatus includes at least one pulling member suitable for pulling the fiber bundles and transmitting compressive force. As a result of pulling of the pulling member, the fiber bundles are pulled into the cavities.

Abstract: A method for producing a layer of a device for electromagnetic radiation absorption, includes: providing a ply of powder material in the layer to be produced of the device; providing a predefined concentration distribution of particles for electromagnetic radiation absorption in the layer; providing a first binder and a second binder for the powder materials, wherein the first binder includes particles for the absorption of electromagnetic radiation, wherein the second binder includes a lower concentration of identical and/or different particles than the first binder; determining a mixing ratio between the first binder and the second binder for every position in the layer; selecting a position of the layer; mixing the first and second binder according to the mixing ratio for the selected position; wetting the powder material at the selected position using the mixed first and second binders; and repeating selecting, mixing, and wetting to produce the layer.

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 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: An aircraft wing has an upper surface element and a first actuator powered mechanism for varying the shape of the surface element which includes: an upstream segment SEG1, a downstream segment SEG2, an interconnecting segment SEG3 interconnecting a downstream edge of SEG1 with an upstream edge of SEG2, wherein the interconnecting segment SEG3 extends along the whole or at least a major part of the downstream edge of SEG1 and the whole or at least a major part of the upstream edge of SEG2, and a link element LNK interconnecting an upstream edge of SEG1 with an upper surface of the aircraft wing, and the first mechanism interconnecting a contact C1 on a lower side of the upper surface element with a contact C2 on an inner structure of the airfoil. The first mechanism controls the shape of the upper surface element by controlling the distance between C1 and C2.

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 module element for driving and retaining braiding bobbin carriers on a predetermined bobbin path has at least one base element that can rotate about an axis of rotation, and at least one retaining element that is formed integrally with the base element. The retaining element is configured to releasably hold at least one braiding bobbin carrier offset from the rotary axis.