Abstract: An aircraft fuselage for releasing a fuel tank from inside the aircraft fuselage in case of emergency includes an outer structure, a mounting device to releasably secure a sled device for carrying a fuel tank in an inside of the outer structure, and a first openable release door separating the inside from an outside of the outer structure, wherein the first release door is positioned in relation to the mounting device such that the fuel tank is released through the first release door when the mounting device releases the sled device. A method is disclosed for releasing a fuel tank from inside the aircraft fuselage in case of emergency as well as an aircraft including such an aircraft fuselage.

Abstract: An aircraft tank device for increasing a flight range and a wing area of an aircraft includes a fairing which is formed and configured to at least partly cover an aircraft wing-aircraft fuselage intersection, to store a fuel, and to provide a lifting function. An aircraft including such an aircraft tank device is also disclosed.

Abstract: A connecting system for connecting components in a vehicle includes a first elongate element with a first connecting face at a first end, and a second elongate element with a second connecting face at a second end. The first and second elements each comprise holding devices distributed along an annular connecting line. The connecting faces are congruent. The connecting faces and holding devices are configured to be brought into a flush superficial contact when the orientations of the elongate elements coincide, and the mutually opposing holding devices then connect with one another. One of the elements has a length adjustment component configured to change a position of the respective connecting face in a longitudinal direction of the respective element. The connecting faces comprise at least one pair of connectable interfaces which correlate with one another in pairs for transfer of a fluid, electrical or optical signals or electrical current.

Abstract: In order to improve liquid hydrogen storage on aircraft, a liquid hydrogen tank is integrated into the fuselage of the aircraft. At least one portion of the tank wall is formed by specially adapted tank skin panels and/or a pressure bulkhead. The parts forming the tank wall are strengthened to contain a tank pressure of about 3 bar.

Abstract: An apparatus for fastening a component to an aircraft cabin attachment structure, the attachment structure having a fastening tube with a longitudinal axis. The apparatus has an internally bored sleeve rotatably positionable on the fastening tube and an external thread. A holding body connects to the component and has two spaced-apart limbs and a bearing surface enclosed by the limbs, and on which, an internal thread configured to the sleeve external thread, is arranged. A device fixes the holding body to the threaded sleeve and the fastening tube, the external and internal threads being non-self-locking. When the holding body internal thread presses against the threaded sleeve external thread, the threaded sleeve rotates until the external and internal threads align. The fixing device connects the threaded sleeve to the holding body in a rotationally fixed manner and fixes the holding body transversely with respect to the longitudinal axis.

Abstract: An aircraft with a potable water system to feed potable water from a potable water tank to a consumer equipment of a monument in the aircraft cabin, including potable water interfaces, and at least one monument, with at least one opening in the monument to establish a fluid connection to the consumer equipment, wherein at least one potable water interface is accessible through the at least one opening, and an assembly method for installing a potable water system wherein standard parts of the potable water system are preinstalled and customized parts are installed later on.

Abstract: An aircraft with a potable water system enabling the connection of monuments to preinstalled aircraft potable water interfaces by customized piping, which is routed within raceways for example directly along seat rails, and an installation method.

Abstract: A polar plate for use in a fuel cell device, the polar plate including an integrated fiber arrangement of one or more hollow fibers, each hollow fiber being configured for conducting a fluid from one end portion to another end portion of the hollow fiber such that the fluid can be pumped through the one or more hollow fibers. Also a fuel cell device, a method for producing the polar plate, an additive manufacturing device, a computer program.

Abstract: An aircraft cooling device for cooling a fluid in a fluid supply and/or drainage device of an aircraft in flight, the aircraft cooling device being configured as a skin component for the aircraft, the skin component including an integrated ply of one or more hollow fibers, each hollow fiber being configured for conducting the fluid from one end portion to another end portion of the hollow fiber such that the fluid supply and/or drainage device is enabled to pump the fluid through the one or more hollow fibers when in fluid connection with ply.

Abstract: A rod with attachment sockets for a truss structure of a vehicle. The rod comprises an elongated body having a plurality of attachment sockets formed on and distributed over an outer side of the body. The plurality of attachment sockets comprises at least a first number of attachment sockets facing in a first direction and a second number of attachment sockets facing in a second direction different from the first direction. The plurality of attachment sockets each comprises a cavity open to the outer side of the body and comprising at least one bearing surface.

Abstract: A fastening element for fastening a first component to a second component. The fastening element includes an elastically deformable body and an elongated actuating member. The actuating member is movably guided relative to the body to be selectively movable further into or further out of the body. The body is configured to be elongated by moving the actuating member further into the body and applying a corresponding load onto the body and to elastically deform back by moving the actuating member further out of the body and releasing the load applied thereto. Further, the body is configured to have a smaller outer diameter when correspondingly elongated than when non-elongated and/or deformed back.

Abstract: A water supply system for use in an aircraft, and a method for preventing blockages in a water supply system in an aircraft. The system comprises a central water tank comprising a fluid inlet and a fluid outlet, a supply conduit for permitting fluid flow from the outlet of the central water tank to a user equipment. At least a section of the supply conduit is connected and thermally coupled to an aircraft air duct so as to enable a transfer of thermal energy to the supply conduit therefrom to maintain the temperature of the water in the supply conduit above the freezing temperature thereof.

Abstract: A tank comprising one or several anti-sloshing wall arrangements, with a frame portion and a door portion wherein the frame portion is fixed to a tank wall of the tank, and it edges an opening, and wherein the door portion is configured to selectively close or unclose the opening. Also an aircraft comprising such tank and at least one engine, the engine being configured to be fed with fuel, in particular with liquid hydrogen, contained in the tank.

Abstract: A reinforcing element for a structural profile, in particular for a round, oval or elliptical structural tube, includes a composite structure, which has a hollow-cylindrical, helically wound mesh of fiber strands which form an inner shell surface configured to receive the structural profile, wherein the fiber strands are respectively embedded in a matrix material, which has an electroactive polymer which can be stretched along a longitudinal extent of the fiber strands by application of an electrical voltage, such that the composite structure can be expanded by application of the electrical voltage to introduce the structural profile into the composite structure and can be shrunk by switching off the electrical voltage to fix the structural profile on the shell surface in the composite structure.

Abstract: A vehicle with a cabin comprising an adaptive rail system. The cabin includes a connection area adapted to hold the adaptive rail system. The adaptive rail system includes a rail interface, configured to be attachable to the connection area, at least one installation rail, configured to be attachable to the rail interface, and a jig. The jig is connected to the at least one installation rail in a moveable manner, such that a module attached to the jig is movable inside the cabin.

Abstract: A manifold plate for a fuel cell including a plurality of openings for leading reactants towards and/or away from the fuel cell and at least one magnet providing a magnetic field which is oriented in a direction of the stack of the fuel cell. The manifold plate defines a main direction which may be seen as in a direction of a stack including electrodes forming the fuel cell. The openings of the manifold plate may be arranged along the main direction of the manifold plate and the magnet of the manifold plate may be arranged between two of the openings and may be oriented so that the direction between north pole and south pole of the magnet corresponds to the main direction.

Abstract: A method of providing a deformable shim that comprises a main structure of an at least partly cellular region. The main structure is compressible by plastic deformation from an initial volume to a deformed volume, wherein the deformed volume is smaller than the initial volume. In a deformed state, the main structure maintains the deformed volume without further or continuing compression force. Further, the main structure is arrangeable between a first aircraft component and a second aircraft component to create a predefined distance between the first and the second aircraft component.

Abstract: A component system for an aircraft, having at least one furnishing component, a plurality of component rails, a plurality of guide elements engageable with and movable relative to the component rails, a plurality of retaining elements connected to the guide elements and configured to be coupled to a hull structure of the aircraft or the at least one furnishing component, and a plurality of locking units arranged on the component rails and/or on the guide elements and configured to lock the guide elements to a particular rail. At least two component rails are arranged on the at least one furnishing component or the hull structure at a distance and parallel to each other such that the furnishing component is retractable via the component rails on guide elements or component rails that are spatially fixed in the aircraft and can be locked in a retracted position by the locking units.

Abstract: A busbar for an aircraft with at least two conductive layers and at least three insulating layers. The conductive layers and the insulating layers are stacked together alternatingly and extend in a longitudinal direction. The conductive layers and the insulating layers include different coefficients of thermal expansion. Each of the conductive layers includes spatial structures. Each spatial structure is connected to an adjacent one by an interconnecting segment. Each conductive layer is embedded between two insulating layers, resulting in a deforming of the side walls of the spatial structures under heat, thereby compensating a longitudinal expansion of the conductive layers. Further, an aircraft with a disclosed busbar and a method of producing such busbar is provided.

Abstract: A structure system for installation into a fuselage structure in an interior of an aircraft. The system has a first carrier element, a second carrier element, an elongate frame element having a first end and a second end, a first attachment device for attaching the first carrier element to the fuselage structure or to an element coupled with the fuselage structure, a first coupling device mounted to the first end for coupling the first carrier element to the frame element, and a second coupling device mounted to the second end for coupling the second carrier element to the frame element. The frame element holds a component to be installed in the interior. The first carrier element couples with the first coupling device, the second carrier element couples with the second coupling device, and one of the coupling devices snaps into the respective carrier element.