Abstract: A method for the assembly of an aircraft fuselage, to a fuselage manufacturing station and to a construction kit includes providing a pre-assembled cockpit unit, a pre-assembled wing box, a pre-assembled tail unit and a plurality of pre-fabricated fuselage shell segments. Furthermore, the method involves positioning the cockpit unit, the wing box and the tail unit. Moreover, a first front fuselage shell segment is positioned on a front connecting region of the wing box, and a first rear fuselage shell segment is positioned on a rear connecting region of the wing box. The first front fuselage shell segment is joined to a second front fuselage shell segment, and the first rear fuselage shell segment is joined to a second rear fuselage shell segment. As a result of the above, following the assembly of the aircraft fuselage an aircraft fuselage can be provided that already comprises equipment elements or functional elements.

Abstract: A method for fire prevention and/or fire fighting on board an aircraft comprises the steps detecting a fire event, leading an extinguishant to a fire source through a cooling-system piping system (12) which serves, in the normal operation of the aircraft, to supply a refrigerant to a cooling station (14a, 14b) and/or discharge a refrigerant from a cooling station (14a, 14b), and flooding the fire source with the extinguishant.

Abstract: A system for contactless energy transmission includes a transformer formed by a primary winding and a secondary winding, which transformer is designed so as to be resonant as a result of capacitors. By measuring and comparing electrical state variables on the primary side and on the secondary side the efficiency of the transmission of electrical power from the primary side to the secondary side is determined, and by varying the resonance frequency of the transformer or of the frequency of a primary voltage applied to the primary winding the resonance frequency and the primary voltage frequency are attuned to each other.

Abstract: A toilet module for a vehicle is provided. The toilet module comprises a housing having a front wall, a first functional wall and at least one second functional wall, which enclose a floor surface on the underside of the housing, and a toilet unit. The front wall comprises an access opening. The first functional wall is arranged opposite the front wall and accommodates the toilet unit. The at least one second functional wall extends between the first functional wall and the front wall and is perpendicular to the front wall. The toilet unit has a longitudinal extension axis which forms an angle which is greater than 0° with the at least one second functional wall. In this way, a particularly narrow and compact toilet module can be provided.

Abstract: A process for the recycling of wastes from webs or strands made of prepreg wastes comprising a first reactive resin, having the following steps: homogenization of prepreg wastes, dispersion of fillers and/or additives in a second reactive resin, mixing of the second resin, homogenized prepreg wastes and further processing of the mixture of resin, fillers and/or additives and prepreg wastes to produce molded workpieces.

Abstract: A bipolar high-voltage network for an aircraft or spacecraft. The network includes at least one DC-DC converter having two unipolar input connections and two bipolar output connections as well as a reference potential connection, at least two fuel cell stacks which are coupled in series between the two unipolar input connections, and at least two discharge diodes, each connected in parallel with the output connections of one of the at least two fuel cell stacks. The DC-DC converter is operable selectively in a step-up converter mode of operation or a step-down converter mode of operation, as a function of an input voltage between the unipolar input connections.

Abstract: A method for producing a connector, in particular for repair, in particular in the field of aviation and aerospace, including the steps of: providing a base layer; attaching a first layer of fiber composite material having a first rigidity to the base layer; attaching a second layer of fiber composite material having a second rigidity to the first layer, offset therefrom, the second rigidity being greater than the first rigidity; and riveting the first layer to the base layer and riveting the second layer to the first layer and to the base layer.

Abstract: A divider device for an aircraft cabin including elongate bar elements, each planar and flexible to assume a linear state extending rectilinearly along a longitudinal axis parallel to a plane, each bar element curved in a first stable state, to deform into its first stable state when bent towards the stable state to a predetermined extent, the bar elements arranged side-by-side and adjacent bar elements are pivotably inter-connected with each other.

Abstract: A beam flange clamp includes a clamp body having a first vise jaw portion with a first gripping surface and a second vise jaw portion with a second gripping surface. The first gripping surface and the second gripping surface are oriented parallel to each other and are offset in height by a predetermined clamping distance. The clamp body further including a bolting portion protruding from the second vise jaw portion opposite of the first vise jaw portion, and at least one bolting hole is formed through the bolting portion.

Abstract: A beam flange clamp includes a clamp body having a first vise jaw portion with a first gripping surface and a second vise jaw portion with a second gripping surface. The first gripping surface and the second gripping surface are oriented parallel to each other, are facing the same direction and are offset in height by a predetermined clamping distance. The at least one bolting hole is formed through the first vise jaw portion perpendicularly to the first gripping surface.

Abstract: A data processing device comprises a graphics processing component configured to obtain first graphic data being related to a first graphical human machine interface for control of a first network domain; one or more second graphic data, the one or more second graphic data being related to one or more second graphical human machine interfaces for control of one or more second network domains; and a display unit configured to display a human machine interface, wherein the main human machine interface comprises the first graphical human machine interface and at least one of the one or more second graphical human machine interfaces.

Abstract: A method for joining skin portions of a closed fuselage, in particular for an aircraft or spacecraft, has the following method steps: providing at least a first skin portion and a second skin portion, at least one of the skin portions being fitted with components to remain in the fuselage; positioning at least the first skin portion and the second skin portion relative to one another in a first joint such that the skin portions form a circumferentially closed fuselage arrangement; guiding a first joining head along the first joint on an outer surface of the fuselage arrangement; and guiding a second joining head along the first joint on an inner surface of the fuselage arrangement, the second joining head being guided along longitudinal guide means which are arranged inside the circumferentially closed fuselage arrangement and are formed at least in part by the components to remain in the fuselage.

Abstract: A method for integrating a backing-structure assembly in a structure of an aircraft or spacecraft is described. In this case, a plurality of individual elements is joined to form the backing-structure assembly. The individual elements for the backing-structure assembly and a skin portion for the structure are provided. The elements are arranged on a pre-assembly device which comprises retaining devices, which are each configured to hold one of the elements so as to be adjustable with respect to the position and/or location thereof. Some or all of the elements are connected to the skin portion. In the method, by adjusting the retaining devices for tolerance compensation, gaps between joint regions of the elements and the skin portion are eliminated or adjusted.

Abstract: A reinforcing component for a structure of an aircraft or spacecraft has a first component region for reinforcing at least one other element, and at least one second component region, which is permanently connected to the first component region. The reinforcing component is formed using a thermoplastic plastics material in each of the first component region and the second component region. In the first component region, the thermoplastic plastics material forms a matrix in which continuous reinforcing fibres are embedded. In the second component region, the reinforcing component comprises discontinuous reinforcing fibres or is free of reinforcing fibres.

Abstract: An energy supply system for an electrical seat device in an aircraft or spacecraft comprises a control unit connected to the seat device, an energy supply which is configured to supply the control unit with electrical energy and an energy storage device which is configured to store electrical energy in a rechargeable manner and which is coupled to the control unit such that said energy storage device can be charged by the energy supply and such that the charging and discharging of said energy storage device can be controlled by the control unit, wherein the control unit is configured to use, as required, the electrical energy stored by the energy storage device to operate the seat device.

Abstract: In an aircraft duct formed with pipes connected in pairs via connectors in which the pipes are mounted with the possibility of axial displacement, there exists a risk that a pipe of the duct, with a dimension greater that the dimension of the nominal pipe, is mounted instead and in place of the latter. In this case, the wrongly mounted pipe would risk not having sufficient clearance in axial translation. In order to solve this problem, it is disclosed to equip one of the relevant connectors with an obstacle limiting the travel of the nominal pipe and preventing the mounting of a pipe with a greater dimension belonging to the duct. A method for assembling an aircraft portion is also proposed, in order to benefit from the particularities of the duct.

Abstract: A pressure bulkhead of an aircraft with a fuselage shell and a pressure bulkhead disposed therein preferably in the rear region for forming a fuselage-internal pressure region, which pressure bulkhead is attached on the edge in the interior of the fuselage shell, wherein the pressure bulkhead has a lenticular cross-section and a sandwich construction that comprises a foam core sandwiched between two opposing exterior shells.

Abstract: A rail system, in particular for assembling or fastening seats in an aircraft, includes an assembly rail, in particular a seat rail for assembling or fastening a seat, a first panel, in particular a first floor panel for arrangement next to and substantially in parallel with the assembly rail, at least one cover element which is movable for covering the assembly rail, and a levelling device for levelling the upper surface of the first panel, in particular for levelling a recess or depression in said panel when the at least one cover element covers the assembly rail.

Abstract: An air supply system for passengers includes an air supply line with a plurality of laterally situated air outlets, an individual air panel with at least one air nozzle and an air inlet opening. The individual air panel can be variably positioned along the air supply line in such a way that the air inlet opening faces one of the air outlets. A plurality of magnetic valves is arranged at the air outlets of the air supply line. One of the magnetic valves may be magnetically actuated by the individual air panel, when the air inlet opening of the individual air panel faces said one magnetic valve, so that air can flow out of the air supply line through the air outlet and the air inlet opening to the air nozzle.

Abstract: A hand hygiene on board of a vehicle includes a washing device including a water supply device, a basin device with a hand receiving device and a water collecting region with a discharge opening, and a drying device including an air discharge device for generating an air stream in the hand receiving region The air discharge device is connected to the hand receiving region and a negative pressure device connected to the air discharge device. The stream of air for the hand drying process is generatable by the negative pressure device. The air discharge device is connected to the discharge opening of the basin device such that air and fluids are discharged via the discharge opening, which forms a common disposal opening. The negative pressure device is additionally designed for suctioning solids thrown into the water collecting region, besides fluids, for disposal over the common disposal opening.