Abstract: The invention relates to a device for moving a trailing edge flap of an aircraft wing, in which device the trailing edge flap comprises one or several flap segments, wherein a first flap segment is movably mounted on the wing and is connected to a first toothed movement element that is moved by means of a first pinion.

Abstract: A device for manufacturing an FC component with at least one distributing device for placing at least band-shaped material onto a surface of a tool mold or semi-finished product for manufacturing the FC component, wherein the device has at least one bogie truck that carries the distributing device and a guide way that runs around the surface at least partially in its circumferential direction, on which the bogie truck for traversing the distributing device can be moved relative to the surface, as well as a method for manufacturing a fiber composite component and a component fabricated according to such a method.

Abstract: A galley including a galley body on a cabin floor for accommodating storage boxes, appliances and at least one service cart; storage boxes for storing goods, and a service cart. The galley body has a plurality of vertical levels that are substantially equidistant from each other, each of the vertical levels divided into a plurality of laterally adjacent compartments whose horizontal and vertical dimensions are equal to an integer multiple of the respective dimensions of a single one of the storage boxes. A transfer table is provided in front of the galley body for access to the compartments. A method includes catering for passengers on an aircraft.

Abstract: A surface seal for sealing a riveted and/or screwed joint between a first and a second component of an aircraft. The surface seal is arranged in the region of joining surfaces of the first and the second component. The surface seal is formed with a pressure-resistant plastic film that is provided with a pressure-sensitive adhesive layer on both sides. The surface seal 1 may furthermore comprise elements for detecting cracks. A method for producing a riveted and/or screwed joint between a first and a second component of an aircraft is also provided, with the joint being sealed with the surface seal.

Abstract: An aerodynamic element attachable to a primary wing to extend in a longitudinal direction at an angle to a spanwise direction of the primary wing. The aerodynamic element includes a downstream end having at least two flow flaps arranged next to each other and oriented in the longitudinal direction of the aerodynamic element.

Abstract: The invention relates to a device, in particular a connection rod, for bracing a fuselage structure and/or for fastening components on the fuselage structure. In one embodiment, the joints are integrated into fuselage structure for linking on both sides of connection rod to fuselage structure. As a result of the integration of joints, a reduced number of individual parts is produced in comparison to previously known embodiments, which leads to a reduction in weight, a reduced maintenance and servicing outlay and an improved reliability against failure. Moreover, device according to the invention enables the introduction of forces in the region of neutral fibers of fuselage structure. A further configuration of device provides only a one-sided articulated linking of a component to fuselage structure by means of (first) end portion. Second end portion is screwed to fuselage structure. To this end, both end portions are provided with a thread at least in sections.

Abstract: A system box for accommodating aircraft systems, and for load transmission between an aircraft structure and a crew rest compartment. The system box comprises a first, a second and a third region, wherein the three regions differ from each other. The first region is adapted attachment of the system box to the primary structure of the aircraft, wherein the second region is adapted for mechanical contact with a crew rest compartment for the aircrew. The mechanical contact in turn is adapted for load transmission between the aircraft structure and the crew rest compartment. Necessary aircraft systems are accommodated in the third region of the system box.

Abstract: A high-lift system on the wing of an aircraft and a method for its operation are described. High-lift flaps (2) which are arranged on the wing (1) are extended from a retracted position in order to increase the lift, and a slot (3) through which flow passes from the lower face to the upper face of the wing (1) is opened (advanced slat/flap-gap control). According to the invention, the slot (3) through which flow passes is opened independently of the position of the high-lift flap (2). This makes it possible to selectively achieve a better maximum coefficient of lift (CL) or a better lift-to-drag ratio with less noise being produced.

Abstract: A method for improving the performance in developing an interprocess digital mockup. Product data elements are compiled from a digital mockup, wherein the product data elements contain geometry data elements and meta data elements. The geometry data elements are addressed and assigned to a geometry structure. The meta data elements are addressed and assigned to a meta structure. The geometry structure and the meta structure are subsequently linked by a communication protocol such that bidirectional interaction between the geometry structure and the meta structure is realized.

Abstract: The invention relates to a load introduction structure for an aircraft, comprising two lateral frames which are arranged opposite one another in the two lateral regions of a fuselage airframe structure of the aircraft and adjoin a continuous floor surface which rests on a floor frame. The two lateral frames are connected via the top thereof by a ceiling frame, the ceiling frame being suspended from a ceiling region of the fuselage airframe structure. Each lateral frame is divided into at least two lateral frame segments. At least three track portions which extend parallel to a longitudinal axis of the aircraft are arranged on each lateral frame segment. The lateral frames are connected to the fuselage airframe structure, the ring frames in particular, by a plurality of x-rods, y-rods and y-cardan rods.

Abstract: A system for stockkeeping in an aircraft galley includes a plurality of receiving devices which are provided for reception in a base body of the aircraft galley and are each provided with a transponder which is configured to emit an identification signal characteristic of the content of the corresponding receiving devices. Furthermore, the stockkeeping system includes at least one transmitting/receiving unit which is provided on the aircraft galley and is configured to read in identification signals emitted by the transponders of the receiving devices and transmit these signals to a data processing unit, the data processing unit being configured to determine, on the basis of the identification signals transmitted by the transmitting/receiving unit, the inventory of the aircraft galley. An output unit of the system is configured to output the inventory of the aircraft galley determined by the data processing unit.

Abstract: The invention relates to a conveying device for a trolley, in particular to a refreshments trolley, in an aircraft passenger cabin and consists in the fact that the conveying device comprises an electric drive with two drive wheels 12, 13 for moving the trolley 7 inside the aircraft passenger cabin, a further electric drive for raising and lowering the trolley 7 and a current collector 20 for supplying current to the installed electric motors 36, 37. The service crew is as a result relieved of physically tiring work and the trolley 7 is secured against uncontrolled movements during the service phase.

Abstract: A device for cooling hot gas to be discharged from an aircraft includes a duct for leading the hot gas from a hot gas source which is connectable to the device to an outlet point, and a frame which surrounds the duct and serves for mounting the duct. The duct is formed from one or more pipe sections and has one or more cooling air inlet points which is connectable to one or more cooling air sources in order to mix the hot gas with cooling air. An outlet pipe section of the duct extends outwards beyond the aircraft outer skin to lead hot gas through and out of a flow boundary layer on the outer skin.

Abstract: An equipment holder is provided with an optional grid function for positioning a first cabin component of an aircraft relative to a second cabin component of the aircraft and for attaching the two cabin components to each other. The equipment holder includes, but is not limited to an attachment element, a fixing element, and a position determination device. In this arrangement the attachment element is designed to attach the equipment holder to the first cabin component. The fixing element is designed to fix a position of the equipment holder relative to the second cabin component. Furthermore, the position determination device is designed to discontinuously indicate the position of the equipment holder relative to the second cabin component with a position signal.

Abstract: The invention relates to an interconnection, including: a T-stringer which has a web portion and two foot portions; a ?-stringer which has a comb portion and two foot portions; and a connection arrangement which joins together the foot portions of the T-stringer and of the ?-stringer, wherein the connection arrangement joins together the T-stringer and the ?-stringer, wherein the connection arrangement has a first and a second connection element, the connection elements connecting a first foot portion of the T-stringer to a first foot portion of the ?-stringer, respectively, wherein the connection elements together have a substantially H-shaped outline, and wherein at least one angle bracket, in particular for connecting a former to the ?-stringer and the T-stringer, is connected to the widening foot portions of the first and second connection elements.

Abstract: An avionics equipment carrier system for slide-in modules with data processing, data transmitting, data storage or data displaying devices, such as for example electronics printed circuit boards, network components, storage devices, display devices and the like, or power supply devices, includes a housing, at least one module rack for accommodating the slide-in modules and at least one backplane board with Ethernet connection architecture. When the dimensions of the housing comply with ARINC standards, and the housing is arranged for installation in an avionics module rack as a quick-mount housing, and any desired circuit boards of a specific standard format can be used in the slide-in modules which are designed as quick-mount modules.

Abstract: The present invention provides a fuselage structure (1; 1?) of an aircraft comprising an annular skin segment (2; 2?) which has a cross-sectional opening (3; 3?), a pressure cap (4; 4?) for a pressure-tight closure of the cross-sectional opening (3; 3?), and a plurality of tension struts (7, 8, 9; 7?, 8?, 9?) which in each case connect the pressure cap (4; 4?) to the annular skin segment (2; 2?) and absorb loads acting on the pressure cap (4; 4?), as tensile loads. This advantageously means that the tension struts (7, 8, 9; 7?, 8?, 9?) do not have to absorb substantially any bending moments. Consequently, the tension struts can be produced with a relatively small cross section, which entails a reduction in weight. Furthermore, it is possible to produce and mount tension struts (7, 8, 9; 7?, 8?, 9?) of this type in a simple manner.

Abstract: A leak detector for detecting a leak in a line includes a transmitting device for generating radiation to be coupled into the line. By a receiving device, radiation that has emerged from the line through a leak is received, as a result of which the leak becomes detectable.

Abstract: The present invention relates to a method for producing a core structure. Firstly, a first core structure and a second core structure are fastened. The first core structure and the second core structure are positioned at a defined distance. A reinforcement element is introduced into a cavity between the first core structure layer and the second core structure layer. The reinforcement element, the first core structure layer, and the second core structure layer form a self-supporting core structure.

Abstract: An arrangement for installing electric cables in the floor region of an aircraft includes longitudinal guide elements that form cable channels and essentially extend in the longitudinal direction of the aircraft parallel to seat rails that are arranged in the aircraft floor and serve for the mechanical attachment of seat legs. The longitudinal guide elements, which accommodate the data and supply cables to be installed, are not visible to aircraft passengers, but are still readily and easily accessible to the maintenance personnel. The floor plate features an elongate groove-shaped recess extending parallel to the seat rail in the longitudinal direction of the aircraft in the immediate vicinity of one of the two seat rails, wherein an elongate extruded profile is arranged in said recess. The extruded profile features an elongate drawer for transmitting shearing forces and an elongate cable shaft arranged above the drawer and serves for accommodating electric cables.