Abstract: A casing for connecting electrical lines printed on a foil to a voltage supply. The casing comprises a space, terminal pads and a block. The casing has an opening between a first wall of the space and a first outer side of the casing. The terminal pads are at least partially arranged on a second outer side of the casing. The block is configured to move between a first position and a second position, both within the space. The block is configured to press the foil against a second wall of the space when the block is in the first position. The block is configured to establish an electrical connection between the electrical lines printed on the foil and the terminal pads when the block is in the first position. The space is configured to receive the foil through the opening when the block is in the second position.

Abstract: An aircraft air conditioning system includes an ambient air line which is configured have ambient air flow therethrough and is connected to a mixer of the aircraft air conditioning system to supply ambient air to the mixer, and a refrigerating machine which includes a refrigerant circuit configured to have a refrigerant flow therethrough, the refrigerant circuit being thermally coupled to the ambient air line to transfer heat, from the ambient air flowing through the ambient air line, to the refrigerant circulating in the refrigerant circuit, before the ambient air is supplied into the mixer. A control device is configured to control the ambient air flow through the ambient air line such that the ambient air is selectively conducted through different sections of the ambient air line or different bypass lines running parallel to the sections of the ambient air line.

Abstract: An aircraft ceiling liner element comprises a load-bearing carrier platform, configured to form a part of an aircraft ceiling liner, and a mounting mounted on the carrier platform, connectable to a primary structure of the aircraft. An electrical connection mounted on the carrier platform is connectable to an electrical supply network of the aircraft. Furthermore, the aircraft ceiling liner element comprises a mechanical interface mounted on the carrier platform, configured to attach various interchangeable modular units detachably and in a load-transferring manner to the carrier platform, and an electrical interface mounted on the carrier platform, which interface is configured to create an electrical connection between the modular unit and the carrier platform.

Abstract: A fiber composite component having a first and a second fiber composite element each bent along a transverse axis opf the fiber composite component to have, respectively, in succession, a first and second base flange, a first and second web section, a first and second top flange and a first and second stiffening web. Respectively, the first and second base flanges are parallel to the first and second top flanges, the first and second web sections are angled with respect to each of the first and second base flanges and the first and second top flanges, the first and second stiffening webs are at right angles with respect to the first and second top flanges, and the first stiffening web and the second stiffening web are congruent with respect to one another, and are connected to one another, along a longitudinal axis of the fiber composite component.

Abstract: A trolley handling device for guiding a trolley into and out of a trolley stowage, comprising a trolley holder adapted to interact with and secure the trolley against displacement relative to the trolley holder in at least a first direction, and a guiding device comprising a first guiding element attached to the trolley holder and a second guiding element adapted to be provided on a structural part arranged near the stowage. The first and second guiding elements are configured to engage with each other and to guide the trolley between a first position, in which the trolley is essentially arranged inside of the stowage, and a second position, in which the trolley is at least partially arranged outside the stowage. The trolley, in its second position, is arranged offset relative to its first position in the first direction and in a second direction perpendicular to the first direction.

Abstract: An ice-protection system for an aerodynamic structure for an aircraft comprising: an outer skin defined by a leading edge point and a trailing edge point that are interconnected by an upper skin and a lower skin, an internal chamber defined within the outer skin configured to be in fluid communication with the atmosphere external to the outer skin via an inlet and an outlet, and at least one air heater provided within the chamber in proximity to the inlet, wherein during use, a pressure differential exists between the inlet and the outlet that causes external air to flow through the chamber from the inlet to the outlet, and wherein the heater is configured to heat the air passing through the inlet such that the temperature of the air in the chamber is sufficiently increased so as to prevent ice accretion on the outer skin.

Abstract: A tooling device for producing a planar structural component for an aircraft has a moulding tool part with a contour surface for receiving a planar semi-finished product, a heating device for heating the semi-finished product, a film produced from an elastically deformable material and a clamping system with a first clamping device arranged on a first longitudinal side of the contour surface, and a second clamping device arranged on a second longitudinal side of the contour surface located opposite the first longitudinal side. The film is couplable to the clamping devices by the edge regions thereof and, when it is coupled to the clamping devices, covers the contour surface of the moulding tool part. The film is elastically deformable relative to the contour surface by the first and/or the second clamping device to press the semi-finished product in a planar manner against the contour surface for deforming purposes.

Abstract: An insulation component to be attached to a fuselage structure of an aircraft. The insulation component extends in a planar manner, and at least one peripheral recess, running transversely to the at least one longitudinal recess, is formed in a first surface of the insulation component configured to receive a respective associated peripheral support of the fuselage structure.

Abstract: The invention relates to a braiding bobbin for a braiding device. The braiding bobbin includes a cylindrical braiding spool, from which a previously wound, multilayer ribbon can be unwound, wherein a first layer of the ribbon consists of a pre-impregnated fiber film, and a second layer of the ribbon consists of a protective film. In addition, the braiding bobbin includes a bracket to which the braiding spool is frontally and rotatably fastened. Additionally provided for the braiding bobbin is a cylindrical additional spool for winding the protective film of the unwound ribbon and a deflection element. The deflection element is fastened to the bracket, wherein the deflection element is secured spaced apart in the radial direction R to the braiding spool and designed for deflecting the protective film from the braiding spool to the additional spool.

Abstract: A vehicle cabin arrangement includes first and second intersecting aisles, a first walling of a cabin monument bordering the first aisle, and a second walling bordering the second aisle. The wallings extend from the floor region of the cabin to a ceiling region of the cabin, and form an angle less than 180°. A first access opening is arranged in the first walling and is closable through a first door, and a second access opening is arranged in the second walling and is closable with a second door. A door blocking unit has blocking means designed for preventing an access to the first access opening and the second access opening. The door blocking unit is switchable between at least two operating modes. In a first operating mode, only the first access opening is accessible. In a second operating mode, only the second access opening is accessible.

Abstract: An aircraft comprises a landing gear assembly on a part of which is mounted a motor for driving a wheel of the landing gear assembly, for example to enable the aircraft to perform taxiing manoeuvres. The motor is a liquid-cooled motor and the liquid that is used to cool the motor is hydraulic fluid, preferably hydraulic fluid taken from a hydraulic system that already exists on the aircraft to supply other consumers of hydraulic fluid pressure on the aircraft. The hydraulic fluid thus has other utility (i.e. other than cooling the motor) on the aircraft and therefore has a significant volume (and therefore a significant heat capacity). There may be a need to convert from high pressure hydraulic fluid to a lower pressure supply.

Abstract: A vehicle cabin seat rail system includes a seat rail having a top side having a plurality of raster openings and mechanically couplable with a cabin floor, a plurality of holding devices positionable on the top side, each being selectively engageable with at least one first raster opening or at least one second raster opening for arresting the holding device and configured for holding an object on the seat rail, and a plurality of marking devices couplable with the seat rail, and configured for optically or mechanically indicating approaching of a first position on the seat rail corresponding to the first raster opening of a respective holding device and of a second position of the same holding device corresponding to the second raster opening, in relation to another object arrested on the seat rail, to prevent an arresting of the holding device on the seat rail on other positions.

Abstract: A cabin monument for an aircraft. The cabin monument has a framework with a base frame and a frame structure connected to the base frame, and side walls fastened to the frame structure. By fastening the side walls to the structural struts of the frame structure, a mechanical load acting on the cabin monument is distributed between the framework and the side walls.

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 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 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 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.