Abstract: An aircraft fuselage for transporting passengers in a lower deck, the fuselage having a longitudinal axis and interior compartment, having an intermediate floor fastened to the fuselage structure, extending through the interior compartment and dividing the interior compartment into an upper deck and a lower deck, having a support device for supporting the intermediate floor on the fuselage structure. The support device is fastened to the intermediate floor and by an opposite end in the lower deck to the fuselage structure. The support device has a concave form and has an energy absorption element such that in a crash of an underside of the fuselage undergoes a defined plastic deformation and absorbs a defined amount of kinetic energy. In a crash, the fuselage structure is, at the underside of the aircraft fuselage, deformed at most to such an extent that a minimum height between a seat surface of passenger seats in the lower deck and the intermediate floor is not undershot.

Abstract: A fuel cell system includes a fuel cell stack, a housing, a first coolant port, a second coolant port, and a cooling device having a coolant pump and a heat exchanger in fluid communication with the coolant pump. The housing includes an upper side and a bottom side. The fuel cell stack is arranged inside the housing. The first coolant port and the second coolant port each comprise a coolant tube having an inner tube, an outer tube and a gap therebetween. Each of the first coolant port and the second coolant port reach through the housing in a way that an inner end is further to the upper side than an outer end. The first coolant port and the second coolant port are coupled to the cooling device and a first coolant path of the fuel cell stack to form a coolant loop.

Abstract: An aircraft-fuselage structure with an external skin and reinforcement structure, supporting the external skin and includes transverse reinforcement elements and longitudinal reinforcement elements. A door opening is in the external skin, between two transverse reinforcement elements and between two longitudinal reinforcement elements, and a door arrangement is installed therein, the door arrangement having a door frame fastened in the door opening and a door panel fastened on the door frame. The door frame and/or the door panel have/has an outer surface directed towards the surroundings and having a curvature differing from curvature of the external skin adjacent to the door opening, and an adapter arrangement is on the outer surface of the door frame and/or of the door panel and, on a side directed towards the surroundings, has at least one surface element which steadily continues the curvature of the external skin adjacent to the door opening.

Abstract: A method for producing a crossmember for a vehicle prepares a workpiece having different thicknesses and a preliminary contour from a metal sheet of uniform thickness by flat roll forming to achieve different local thicknesses. The method cuts out the workpiece, and bending roll forms the workpiece to form a crossmember with a cross section having at least two flanges opposite one another, and a web situated between said flanges. The distance between the flanges is not constant along a longitudinal extent of the crossmember, and a thickness profile at least of the web is determined by the flat roll forming. The local thicknesses and the preliminary contour are such that a geometrical shape of the crossmember corresponds to a predetermined geometrical shape with different thicknesses and heights of the web and differently shaped regions of the flanges along the longitudinal extent of the crossmember.

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 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: In order to integrate an aerodynamic box without a solid shim, a spar joint is provided. The spar joint comprises a first spar having a first spar contact surface and a second spar having a second spar contact surface. When the first and second spars are fixed to each other, the first and second contact surfaces engage each other in a manner forming a contact plane. The first and second contact surfaces are inclined such that a first imaginary plane that is an extension of the contact plane in a chordwise direction forms at least one intersection with a second imaginary plane that is originating from a chordwise extremal end of an aerodynamic skin. The spar joint is used in aerodynamic boxes, such as flap boxes and TE boxes. The spar joint is also used in airfoil profiles.

Abstract: A method for welding thermoplastic components, in particular, thermoplastic fiber composite structural components for an aircraft or spacecraft, having the following steps. Arranging an insert, which has a conductor structure having a plurality of parallel electrical conductor elements, in a joining zone between a first thermoplastic component and a second thermoplastic component such that at least some portions of the parallel electrical conductor elements are located in the joining zone; locally melting the components in the region of the joining zone by supplying current to the conductor structure; disconnecting the connector elements; and removing the insert from the joining zone by pulling out the disconnected conductor elements. An insert for the resistance welding of thermoplastic components is also provided.

Abstract: A process for producing a polymeric stiffened sheet-like component, for example a panel, for aircraft construction. Production includes integration of hollow stiffening profiles, for example closed omega stringers, onto a sheet-like component, for example an external skin, where the stringers and external skin are produced from thermoplastic composite material. The stringers are integrated onto the external skin by establishing contact between the stringers and the external skin and melting thermoplastic composite material with exposure to heat and pressure at the areas of contact between external skin and stringers. Melting of the other sections of the stringers is avoided with a pressurized cooling fluid with a temperature significantly below the melting point of thermoplastic composite material, the fluid flowing through the airtight enclosed space in the stringers.

Abstract: A method for connecting two components. In this method, a first component and a second component, which are each formed from a thermoplastic material, are first provided. The first component has a first peel-off ply on a first surface of the first component. The first peel-off ply is removed from the first component. Once the first peel-off ply has been removed, the first surface of the first component is brought into contact with a second surface of the second component. The first component and the second component are then welded to one another at the first and second surface by ultrasonic welding.

Abstract: An accommodation system for an accommodation space for storing rollable containers in a vehicle. After a front container, which is arranged at the insertion opening, has been removed in the conventional manner, it is possible, through the use of the accommodation system, to remove the rear container which is arranged considerably spaced apart from the insertion opening in the interior of the accommodation space. For this purpose, a rail system is provided in the floor region of the accommodation space. A transfer plate is movable on the rail system in the floor region of the accommodation space and can assume a storage position and a removal position for the rear container.

Abstract: An aircraft structural joint comprising a first structural component provided with an attachment hole that is configured to receive an corresponding attachment fastener provided by a second structural component; a curable composite bush compressed and cured between an outer diameter of the attachment fastener and the attachment hole when the first component is mounted to the second component, wherein the curable composite bush, when cured, prevents radial displacement of the attachment fastener within the attachment hole.

Abstract: A method for testing an audio signal system having multiple audio component connection sockets, each socket having at least one audio signal interface connected to a ground interface of the socket via a series circuit including a resistor and a capacitor, including feeding, via a signal processing device, a time domain reflectometry test signal into a wired network of the audio signal system, in which the sockets are connected to the signal processing device via differently lengthed electrical lines, detecting in a temporally resolved manner, via the signal processing device, test return signals reflected at the multiple sockets, comparing the detected test return signals with a temporally resolved reference pattern for test return signals, which reference pattern was created under predefined boundary conditions, and determining a faulty connection of a socket if comparing the detected test return signals with the reference pattern reveals a deviation above a predefined threshold value.

Abstract: A leading edge structure for an aerodynamic surface of an aircraft with an outer wall part curved in a streamlined manner around an interior compartment and having an inner surface pointing toward the interior compartment and an outer surface provided for contact with the external surrounding flow. The outer wall part has a first outer wall section extending from a leading edge point in an incident flow direction in a convexly curved manner in the direction of a first side. The outer wall part has a second outer wall section which extends from the leading edge point in the incident flow direction in a convexly curved in the direction of a second side. An inner wall part is arranged in the interior compartment opposite the inner surface of the outer wall part and extends from the first outer wall section to the second outer wall section.

Abstract: A fuel cell power system including at least one fuel cell, a ram air system and a cooling circuit in which coolant is intended to circulate for regulating a temperature of the at least one fuel cell. The cooling circuit comprises a ram air heat exchanger in the ram air system and the ram air system comprises a nozzle. The fuel cell power system further comprises a water tank and the fuel cell power system is arranged to flow water from the water tank to the ram air system so as to spray water in ram air via the nozzle. Thus, dimensioning of the ram air system which includes the ram air heat exchanger is reduced.

Abstract: A test module for functionally testing an audio device of an aircraft passenger service unit (PSU) is configured to allocate a first operating mode to a first individual audio device of one PSU of a set of PSUs during which, a test tone is emitted. The test module allocates a second operating mode to other audio devices different than the first audio device. In the second operating mode, the test tone emitted by the first audio device is intended to be received. The other audio devices each belong to different PSUs within the set of PSUs. The test module emits the test tone via the first audio device. The test module initiates a functional test of the first audio device. The functional test is based on the test tone received by the other audio devices. The test module may be part of a system and an aircraft.

Abstract: A semi-active system for providing a required fluid flow, the system comprising an outlet configured to protrude into the main flow direction of an external fluid flow external to the semi-active system, an exhaust channel provided, in relation to the main flow direction of the external fluid flow, beneath the outlet, the exhaust channel being configured to inject an exhaust fluid flow into the external fluid flow, a device configured to produce a jet fluid flow and a pipe provided within the exhaust channel, the pipe being configured to fluid-communicatively couple to the device, and entrain, by the produced jet fluid flow, the exhaust fluid flow.

Abstract: An airborne communication device installed in a vehicle, wherein the airborne communication device is configured to receive navigation information from a ground-based communication device installed outside the vehicle via a datalink protocol. A ground-based communication device, a communication system, and a method for communication are described.

Abstract: An airfoil for flow control is disclosed having an outer skin in contact with an ambient air flow, wherein the outer skin extends between a leading edge and a trailing edge with two opposite lateral sides, and surrounds an interior space. The outer skin comprises a porous section in the area of the leading edge, a pressure chamber arranged in the interior space and fluidly connected to the porous section, an air inlet fluidly connected to the pressure chamber, and an air outlet fluidly connected to the pressure chamber.

Abstract: A door arrangement for an aircraft segment, which door arrangement comprises a passenger door, a fuselage portion accommodating the passenger door, and a girt bar for arming and disarming an emergency slide. The passenger door is movable relative to the fuselage portion between a raised position and a lowered position. The girt bar is connectable by means of a connecting arrangement to the passenger door and/or to the fuselage portion. The connecting arrangement comprises a mechanism which is configured to, during arming of the emergency slide, actuate a locking mechanism of an engagement device fastened to the fuselage portion, such that the girt bar is fixed in a decouplable manner to the engagement device.