Abstract: An aircraft bipolar high-voltage network includes a DC voltage converter comprising two unipolar input connections, two bipolar output connections and a reference potential connection, and at least one unipolar device having two electrical connections which are each coupled to one of the two unipolar input connections. The DC voltage converter has a first DC voltage converter module coupled to a first of the unipolar input connections via a module input connection, to the reference potential connection via a module reference potential connection and to a first of the bipolar output connections via a module output connection, and a second DC voltage converter module coupled to a second of the unipolar input connections via a module input connection, to the reference potential connection via a module reference potential connection and to a second of the bipolar output connections via a module output connection.

Abstract: A method for producing a connecting device for connecting films with conductor tracks includes the steps of laying a first film with conductor tracks onto a forming die, applying a first lower shell of a plastic material onto a first end portion of the forming die, producing a cut-out and shifting the first film so that the cut-out lies completely on the first lower shell, applying upper conductor tracks of a conductive material onto the first lower shell so that the upper conductor tracks overlap with the conductor tracks of the first film, and applying a first upper shell of a plastic material onto the first lower shell so that the first film, the first lower shell and the first upper shell connect together by substance bonding to form a first connector. In this way, an integral connector can be provided on each film.

Abstract: A fuel cell system includes a first fuel cell unit having a first fuel cell and a second fuel cell, a second fuel cell unit having a third fuel cell and a fourth fuel cell, a hydrogen tank coupled to all fuel cells, an oxygen supply unit and an air inlet. Oxidant inlets of the first fuel cell and the fourth fuel cell are couplable with the air inlet. Oxidant inlets of the second fuel cell and the third fuel cell are couplable with the oxidant supply unit couplable with at least one of the oxygen supply unit and the air inlet. Exhaust outlets of the first and fourth fuel cells are couplable with an inert gas outlet. Exhaust outlets of the second and third fuel cells are coupled with an exhaust switching unit couplable with the inert gas outlet and a water outlet.

Abstract: A high voltage conductor for transmitting high voltage is provided. The high voltage conductor includes a power wire, a fault detection unit, and a monitoring unit. The power wire is configured for transmission of electrical energy. The fault detection unit is configured for detecting an electromagnetic field emanated by the power wire, and the monitoring unit is configured for detection of degradation in an isolation of the high voltage conductor. The monitoring unit is connected to the fault detection unit and is configured to receive an electrical signal induced in the fault detection unit, which electrical signal is induced as a result of a degradation of the isolation of the high voltage conductor. Thus, degradation of the isolation of the high voltage conductor may be recognized at an early stage.

Abstract: A window frame system, comprising a window frame having an aperture there-through and circumferentially arranged window frame through-holes in a first window frame portion and a second window frame portion, and a stringer coupling with stringer coupling through-holes in a first stringer coupling portion and a second stringer coupling portion. In an overlapping arrangement, the first window frame portion and the first stringer coupling portion are adapted to overlap with their through-holes coaxially, wherein the respective through-holes of the two first portions have different diameters.

Abstract: A wing (5) having a base section (5) and a tip section (13), the base section (7) having a first end portion (9) and a second end portion (11), the tip section (13) having a third end portion (15) and a fourth end portion (17), wherein the second end portion (11) and the third end portion (15) are coupled so that the tip section (13) is pivotable with respect to the base section (7) about a pivot axis (19, 19?), and an actuating arrangement having an actuator (21) which is coupled to the base section (7) and the tip section (13) and which is operable to effect a pivotal movement of the tip section (13) relative to the base section (7) between a stowed position and a deployed position.

Abstract: A flow body of an aircraft includes: a flow surface exposed to an airstream during flight of the aircraft, the flow surface generating at least one region of turbulent airflow during flight of the aircraft, at least one perforated area including a plurality of openings extending through the flow surface, a manifold positioned interior to the flow surface in fluid communication with the openings, and at least one suction duct having a first end and a second end, the first end being in fluid communication with the manifold, the second end including a suction opening and being arranged in the at least one region of turbulent airflow, wherein the suction opening is adapted for inducing a suction force in the at least one suction duct when the flow surface is exposed to an airstream during flight, thereby inducing a flow of air from through the plurality of openings.

Abstract: A fastening system for passenger seats in a vehicle cabin has two or more guide rails to be integrated into or onto a cabin floor, and a plurality of slides, to be brought into engagement with the guide rails and having a flange for connection to a passenger seat in order to retain the passenger seat on a guide rail. Each guide rail has a profile cross section, perpendicularly to a main axis of extent, having a base region and a supporting region. Each slide has a cavity of complementary design with the profile cross section. The guide rails have a plurality of transverse openings spaced apart from one another between the base region and the supporting region. At least one slide has a displaceably mounted retaining body which, when the slide is in engagement with the guide rail, can be brought into engagement with one of the transverse openings.

Abstract: A network for an aircraft including a data line and network access devices, a first interface and at least one second interface and connected to the data line via the first interface. Identifiers are assigned to the second interfaces in pairs. The access devices receive and/or transmit data in first data frames having a fixed format and first portion and second portions. The network access devices transmit second data frames and, for each second interface, a sequence of third data frames received on the second interfaces, the network access device including a first processing unit to insert the second data frames in the first portion of the first data frames, split each third data frame into fragment frames, including a part of the respective third data frame and reassembly information allowing regeneration of the third data frame from the fragment frames, and insert the fragment frames into the second portions.

Abstract: A vortex generator arrangement for an aircraft, a flow control system and an aircraft comprising such vortex generator arrangement. The arrangement includes a surface portion facing a first region of space to constitute a flow surface, a vortex generating element, an element support structure connected to the element, a mounting structure. The element support structure and the element together are rotatable between first and second positions and a biasing device, retainer and release are provided. The rotational axis extends transversely with respect to the surface portion. The projection of the element onto a projection plane is smaller in the first rotational position than in the second rotational position, the projection plane extending perpendicularly to a tangent plane of the surface portion at a reference point of the surface portion and to a predetermined direction parallel to the extension of the tangent plane.

Abstract: A flight attendant seat comprises a carrier having a guide with opposed first and second ends, and a storage compartment receiving the guide first end. The guide provides guidance along its length between its first and second ends. The seat comprises a plurality of segments, each slidingly mounted to the guide to allow a sliding movement of the segments along the guide and relative to the carrier device between a stored position of the segments within the storage compartment, and an exposed position of the segments. A seat element is pivotally mounted to a first of the segments pivotable between an inoperative and operative seat forming position. At least one backrest is mounted to at least a second of the segments. With the segments in their exposed position, the seat element, when pivoted to its operative position, together with the backrest(s), can be used as a flight attendant seat.

Abstract: An adjustable, or all-moving, horizontal stabiliser for an aircraft, the stabiliser having a leading edge, a trailing edge, a root and a tip, and a strake fixed with respect to the stabiliser and attached to, or integrally formed with, the stabiliser leading edge adjacent the root.

Abstract: An aircraft air conditioning system comprising an ambient air line, for ambient air to flow through, connected to supply ambient air to a mixer of the aircraft air conditioning system. An ambient air compressor is arranged in the ambient air line for compressing the ambient air flowing there through. A refrigerating apparatus comprises a refrigerant circuit for a refrigerant to flow through, including a refrigerant compressor arranged in the refrigerant circuit. The refrigerant circuit is coupled thermally to the ambient air line to transfer heat from the ambient air to the refrigerant before the ambient air is supplied to the mixer. A cabin exhaust air turbine is connected to a cabin exhaust air line, is coupled to the ambient air compressor arranged in the ambient air line, and is configured to expand the cabin exhaust air flowing through the cabin exhaust air line and to drive the ambient air compressor.

Abstract: A separating film with an anti-adhesion layer for preventing an adhesive connection between a thermally curable levelling compound, applied in the region of a joining zone of a first component, and a joining zone of a second component to be joined to the first component. The anti-adhesion layer is provided, at least in parts, with a heating layer. As a result of the actively electrically heatable heating layer of the separating film, which is an integral part of the separating film, the processing time for joining two components, which are subject to tolerances, using a thermally curable levelling compound (known as liquid shimming), can be reduced by at least 40% compared with the conventional process.

Abstract: An additive layer manufacturing method is disclosed for producing a three-dimensional object and a corresponding object. Layers of powder material are applied to a carrier and each layer is irradiated with a laser beam or a particle beam only in areas of the layer corresponding to the three-dimensional object to be produced. Irradiation occurs so the powder material in the corresponding areas is locally melted or sintered. An elongate portion of the object is constructed so longitudinal channels extend at an angle of more than 45° to the direction of the force of gravity, and along its entire length the longitudinal channels are formed so that in cross section perpendicular to the direction of extension of the elongate portion the minimum distance to the outer surface of the elongate portion is not smaller than the minimum distance to the closest neighbouring longitudinal channel or the closest neighbouring longitudinal channels.

Abstract: A method for mending damaged areas in fiber composite components formed from a plurality of unidirectional fiber layers includes the steps of automatically lifting at least one fiber layer of the fiber composite component at a cutting edge of the at least one fiber layer using a delaminating device, removing the at least one fiber layer in the extension direction of the fiber orientation of the at least one fiber layer, and separating off the removed at least one fiber layer in a defined manner at a separating edge defined by a separating device placed on the fiber composite component.

Abstract: A system for driving and guiding a trailing edge control surface arranged on a wing of an aircraft includes a first guide device attachable to the wing and coupled with an inboard section of the control surface for guiding the inboard section along a trajectory relative to the trailing edge region of the wing between a retracted position and an extended position, a second guide device attachable to the wing and holding a connecting means of an outboard section of the control surface, and a drive device attachable to the wing and the control surface for moving the control surface. The trajectory is a spatial path at least along one dimension, wherein a distance between the inboard section of the control surface and a fixed part of the wing changes during a motion of the inboard section on the trajectory.

Abstract: A door assembly, particularly for doors of passenger aircraft, includes a door frame, a door having a door body hingedly installed in the door frame, at least one hooking pintle attached to the door frame or an edge of the door body extending along a pintle axis, and at least one door latch connected to an edge of the door body or the door frame, respectively, the door latch having a substantially C-shaped latch body configured to rotate around an axis parallel to the pintle axis of the hooking pintle. The door assembly further includes a bistable latch and hook mechanism configured to catch the door latch in hooking engagement with the hooking pintle and to retain the door latch in a direction perpendicular to the door body in an overcenter position.

Abstract: A fixation assembly for affixing a first object to and variably spaced from a second object. The assembly comprises a male fastener and a female fastener. The male fastener comprises a bolt-shaped part having a circumferential outer surface. The surface includes alternately on a circumferential path, in a cross-sectional plane of the part, at least one ridged section and at least one plain section. The female fastener comprises a tubular part having a circumferential inner surface. The inner surface includes alternately on a circumferential path, in a cross-sectional plane of the part, at least one ridged section and at least one plain section. The male fastener can be inserted into the female fastener such that its ridged section coincides with the female fastener plain section. Either the male or female fastener is configured to be rotated relative to the other, thereby engaging respective ridges of the two fasteners.

Abstract: An electrical power supply system for an aircraft includes a plurality of generators, each being couplable to and rotatable by an aircraft engine. and a plurality of electrical conversion units, each having a plurality of inputs and at least one output. Each generator includes at least four AC phases. The inputs of each individual electrical conversion unit are connected to a plurality of phases of at least two of the plurality of generators. The electrical conversion units each includes a rectification and conversion device for providing an output voltage having a predeterminable frequency and voltage level at the output.