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: An end plate for clamping one or more fuel cells in a fuel cell arrangement, the end plate including one or more integrated storage devices for storing electrical energy. A fuel cell arrangement includes one or more fuel cells and a clamp device for clamping the one or more fuel cells, the clamp device having an end plate including one or more integrated storage device for storing electrical energy, the end plate clamping the one or more fuel cells in the fuel cell arrangement.

Abstract: Methods for fastening two fiber composite parts to each other with a fastener that includes electroactive polymer material. The parts have an opening within an inner circumferential surface. Fibers protrude from the inner circumferential surface into the opening and interlock with chains of micrograins of the electroactive polymer material. The fastener may switch between an activated state and a deactivated state and in the deactivated state, the fastener engages the exposed fibers.

Abstract: A bipolar plate for use in a fuel cell device, the bipolar plate including an integrated ply, the ply including one or more electrically conductive fibers and being configured and electrically connectable to a power supply such that the one or more fibers are heated when power is supplied to the ply.

Abstract: Leakage detection for pressurized fuel tanks. To provide facilitated leakage detection, a leakage detection device for pressurized fuel tanks for storing a pressurized fuel includes a fuel-sensing tracer and a light-wave conducting component. The fuel sensing tracer is configured to alter its optical properties in the presence of a predetermined fuel. The light-wave conducting component is in optical contact with the fuel sensing tracer. Light travelling within the light-wave conducting component is modifiable by altered optical properties of the fuel sensing tracer such that modified light is indicative of the presence of fuel at the location of the fuel sensing tracer.

Abstract: A pipe for heating a cryogenic liquefied gas, the pipe having a peripheral wall including a ply of one or more electrically conductive carbon fibers, the ply being configured and electrically connectable to a power supply such that the one or more carbon fibers are heated when power is supplied to the ply.

Abstract: A component for an aircraft includes at least one connection interface, wherein the connection interface is configured to simultaneously establish an electrical connection and a mechanical connection. An electrical system for an aircraft and a method for connecting components for an aircraft are disclosed.

Abstract: A bipolar plate for a fuel cell stack comprises a first main boundary surface and a second main boundary surface, arranged parallel and at a distance to each other and define an interior space. A plurality of lateral delimiting surfaces extend between outer edges of the first and second main boundary surfaces to enclose the interior space. At least one of the lateral delimiting surfaces comprises a plurality of lateral openings and at least one of the main boundary surfaces comprises a plurality of axial openings. Internal distribution channels are arranged inside the interior space in a distance to the first main boundary surface and the second main boundary surface, and lateral openings are in fluid connection with the axial openings through at least a part of the internal distribution channels.

Abstract: An arrangement includes a fiber-reinforced composite component or assembly and a monitoring device. The composite component or assembly includes at least first and second reinforcing fiber formation sections stitched to each other using a yarn to connect the fiber formation sections along a seam, the yarn being electrically conductive along a length thereof. The monitoring device is configured and coupled to the yarn so as to be capable of sending an electrical input signal along at least a section of the yarn that forms the seam or part thereof and receiving a response signal on the yarn. Furthermore, an aircraft or spacecraft is provided including at least one arrangement of this type, as well as a method of producing an arrangement including a fiber-reinforced composite component or composite assembly, and a method of monitoring the structural integrity of a fiber-reinforced composite component or assembly.

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 structural component of a primary structure for a vehicle, the structural component including a fiber composite laminate with a plurality of fiber composite sublayers. The plurality of fiber composite sublayers includes an electric energy store which is configured as a multilayer electrochemical fiber composite battery to store electric energy in a rechargeable manner; and an electrothermal temperature regulation sublayer which is configured to supply thermal energy to the electric energy store and conducting thermal energy away from the electric energy store as required to regulate a temperature. A control device, which is connected to the electric energy store and the electrothermal temperature regulation sublayer, is configured to control a 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: A method for bonding two fiber composite components with each other to form a fiber composite structure includes integrating conductive fibers underneath a bonding surface of at least one of the two fiber composite components, each conductive fiber comprising a carbon fiber coated with an electrically insulating coating, the conductive fibers running along the bonding surface and protruding at least at their ends from the respective fiber composite component; arranging the two fiber composite components against each other at their respective bonding surfaces; passing an electric current through the conductive fibers by electrically contacting the conductive fibers at their protruding ends so that the respective fiber composite component is heated at the bonding surface to a curing temperature; and joining the two fiber composite components with each other at their bonding surfaces via secondary bonding, co-bonding and/or co-curing at the curing temperature, thereby forming the fiber composite structure.

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 interconnecting device for compact solid oxide fuel cells includes a body having first and second interface surfaces on distinct body sides. The first interface surface includes spaced apart anode and cathode exhaust inputs. The second interface surface includes spaced apart fuel and air supply ports. The anode exhaust input fluidly communicates with the fuel supply port and/or anode exhaust outlet arranged at a distance to the first and second interface surfaces. The cathode exhaust input fluidly communicates with the air supply port and/or cathode exhaust outlet arranged at a distance to the first and second interface surfaces. The first electrical port is arranged at or in the cathode exhaust input and is connectable from the first interface surface. The second electrical port is arranged at or in the fuel supply port and is connectable from the second interface surface, and is electrically connected to the second electrical port.

Abstract: In some aspects, the disclosure relates to compositions and methods comprising ActRII polypeptides to treat, prevent, or reduce the progression rate and/or severity of pulmonary arterial hypertension, particularly treating, preventing or reducing the progression rate and/or severity of one or more pulmonary arterial hypertension associated complications.

Abstract: A cryogenic storage tank including a first metallic end piece having a first structured connection area on its outer surface, a second metallic end piece having a second structured connection area on its outer surface, a hollow body extending between the first structured connection area and the second structured area. The hollow body is formed of a fiber reinforced polymer-based composite, a first metallic clamp having a third structured connection area and a second metallic clamp having a fourth structured connection area. The hollow body is arranged between and in intimate contact with the first structured connection area of the first metallic end piece and with the third structured connection area of the first metallic clamp and is arranged between and in intimate contact with the second structured connection area of the second metallic end piece and with the fourth structured connection area of the second metallic clamp.

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 bipolar plate for a fuel cell for generation of electrical power has a bipolar plate body having a first surface. The bipolar plate body has at least one gas flow channel on the first surface, the gas flow channel defining a first gas flow channel side wall and an opposite second gas flow channel side wall, and the gas flow channel running in a first direction to expose the electrode to the reactant. The bipolar plate also has at least one electrical conductor to run at least partly parallel to the first direction within the bipolar plate body behind the first gas flow channel side wall and/or the second gas flow channel side wall, such that, when a voltage is applied to the electrical conductor, the electrical conductor forms an electromagnetic field, the electromagnetic field to accelerate the reactant at least partly in the direction of the electrode.

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.