Abstract: A supply system for providing at least oxygen depleted air and water in a vehicle includes at least one hydrogen supply means, an air channel having an inlet and an outlet, an air cooled fuel cell unit couplable with the hydrogen supply means and arranged inside the air channel and at least one catalytic converter couplable with the hydrogen supply means and arranged between the fuel cell unit and the outlet of the air channel inside the air channel. The air cooled fuel cell unit is adapted for conducting a fuel cell process under consumption of air flowing from the inlet of the air channel through the air cooled fuel cell unit and hydrogen from the hydrogen supply means. At least one catalytic converter is adapted for producing water and oxygen depleted air under consumption of hydrogen from the at least one hydrogen supply means and air.

Abstract: A system for suctioning fluid is disclosed. In a cabin monument, a vacuum source and a vacuum interface unit is provided. At least one flexible hose provides a connection to the vacuum interface unit, having at least one first fluid line having a connection element. The end connection element connects to a unit to be evacuated. The vacuum interface unit includes an adapter for connection to the at least one fluid line, and a trigger unit. At least one valve unit and a control unit for controlling the at least one valve unit reside in the cabin monument. The control unit controls the valve unit at least indirectly based on a trigger signal generated by the trigger unit. Thus, a flexible positioning of a unit to be evacuated for waste compaction is possible. The disclosure also relates to a vehicle, in particular an aircraft, having such a suctioning system.

Abstract: A rotational joint (101) that rotatably couples a wing tip device (4) to a fixed wing (3), and includes an outer race (8) and an inner race (9), a rotational drive member (70) and the race that is rotationally fixed relative to the wing tip device (4) each being provided with a coupling section (110, 111, 114), the coupling sections coupled to each other by a coupling member (119), that is received in a bore (112, 113) in one of the coupling sections, such that rotation of the drive member (70) rotates the race that is rotationally fixed relative to the wing tip device, to rotate the wing tip device (4) from one configuration to the other, wherein the coupling member (119) is mounted in the bore such that it is movable radially within the bore.

Abstract: An aircraft monument comprising a desk and a movable part that is mounted to the aircraft monument by means of an attachment device. The movable part is pivotable about an axis between a first position in which the movable part covers a first area of the desk and is essentially arranged inside of the aircraft monument such that its front faces in a first direction towards the back of the aircraft monument, and a second position in which the movable part is at least partially arranged outside of the aircraft monument and its front faces in a second direction that crosses the first direction. The movable part, in its second position, covers a second area of the desk that is less than the first area.

Abstract: A virtual window device, particularly for use in an airplane, includes a bezel, or a frame, with a display arranged within the bezel, or within the frame; a distance sensor unit configured to produce at least one first distance signal indicating a first distance to an object; a first camera unit configured to capture a live video of a real scene; and a computing unit configured to select, based at least on the at least one first distance signal, a section of the live video of the real scene captured by the first camera unit; wherein the computing unit is further configured to control the display to display the selected section.

Abstract: A cable harness test system includes a cable tester that has a microcomputer and a multiplicity of first test point connections for connecting first ends of a multiplicity of electrical lines of a cable harness and is designed to feed line test signals into the multiplicity of electrical lines of the cable harness at the first test point connections, and also a multiplicity of interface simulation devices that each have a multiplicity of second test point connections for connecting second ends of the multiplicity of electrical lines of the cable harness and are each designed to return line test signals received from the cable tester at the second test point connections to the cable tester by the multiplicity of electrical lines of the cable harness.

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: An arrangement for selectively arresting a serving trolley in a cabin includes a walling extending perpendicularly to a cabin floor. The walling has a height at least equal to the height of a serving trolley. The arrangement has an upper arresting unit positioned at an upper fastening section of the walling and a lower arresting unit positioned at a lower fastening section of the walling. The upper arresting unit has a first engagement element and a second engagement element, wherein at least one of the engagement elements is movable relative to the other engagement element. The upper arresting unit releasably engages two distanced recesses at an upper end of the serving trolley by way of the engagement elements. The lower arresting unit includes at least one third engagement element and is designed for engaging a bottom side component of the serving trolley by way of the third engagement element.

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 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: 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 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: 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: 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 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.