Abstract: A passenger service module (10) comprises a fitting element (18), an individual ventilation arrangement (26) connected to the fitting element (18) and having at least one air nozzle (24), a lighting arrangement (30) connected to the fitting element (18) and having at least one reading lamp (28), and an operating element (48) connected to the fitting element (18). The operating element (48) comprises a touch panel (58) having at least one input field (68) for individually controlling the operation of the air nozzle (24) and/or of the reading lamp (28).

Abstract: A method and system for displaying information on an electrical display unit in an aircraft cabin including a generating unit for generating at least one signal which clearly identifies the information, a first acquiring unit for wirelessly acquiring the at least one signal and a control unit for controlling the display unit on the basis of the at least one signal. The system may also have a second acquiring unit for acquiring departure and/or arrival location information relating to a flight and a third acquiring unit for acquiring passenger information.

Abstract: A method for manufacturing a fiber composite plastic component with integrated lightning protection. The steps include, for a positive mold, automatically laying down a ribbon-form pre-preg material or dry ribbon-form reinforcing fiber strands onto the mold. Then, automatically laying down a ribbon-form lightning protection material onto the pre-preg material or the reinforcing fiber strands. For a negative mold, the steps include automatically laying down the lightning protection material on the negative mold, then automatically laying down the pre-preg material or the dry reinforcing fiber strands onto the positioned lightning protection material.

Abstract: A lightweight structure at least sectionally composed of a plurality of connected mosaic elements and/or skin mosaic elements. The lightweight structure allows an essentially load-appropriate arrangement of the mosaic elements and/or the skin mosaic elements including the optional skin. The lightweight structure requires a significantly reduced number of connecting elements, such that the assembly effort can be reduced and an additional weight reduction can be achieved. Also, two variations of a method for manufacturing a lightweight structure are provided. Large-format lightweight structures such as, for example, an aircraft fuselage cell or partial shells thereof can also be manufactured in a reliable and dimensionally accurate fashion because only mosaic elements and skin mosaic elements, with relatively small dimensions, need to be handled.

Abstract: A heat exchanger with at least one cooling segment having a first, a second, and a third portion. A first heat carrier flow path, through which a first heat carrier medium flows, extends through the first portion. A second heat carrier flow path, through which a second heat carrier medium flows, extends through the second portion. A first coolant flow path, through which a first coolant medium flows, extends through the third portion. The heat exchanger comprises at least one cooling body, a second coolant medium flowing through a second coolant flow path extending through the cooling body. The first and the second heat carrier flow paths are thermally coupled, respectively, to the first and the second coolant flow path, to discharge heat energy of at least one of the first and the second heat carrier medium to at least one of the first and the second coolant medium.

Abstract: A disposable seating-surface cover (28) for a toilet-seat flap (12) is adapted to cover a seating surface (18) of a toilet-seat flap (12) in order to avoid contact between a user and said toilet-seat flap (12). The disposable seating-surface cover (28) comprises a deformable or foldable base section (30) with an aperture (32). Said disposable seating-surface cover (28) further comprises at least one adhesive section (38a-d) which is arranged on or in the base section (30) and is made of a paramagnetic or ferromagnetic material.

Abstract: A holding device for attaching at least one fixture to a fuselage cell structure of an aircraft, includes a basic element attached to the fuselage cell structure, to which at least one fixture element to accommodate the fixture is fastened, wherein the basic element is embodied as a hook-and-loop element, the hook-and-loop bristles of which co-act with corresponding hook-and-loop bristles of at least one fixture element, which is also embodied as a hook-and-loop element thus forming a hook-and-loop connection, wherein the space between the interengaging hook-and-loop bristles is filled with an adhesive.

Abstract: A supply system for supplying passengers in a passenger compartment of a vehicle, in particular an aircraft, includes a supply line and a number of supply modules which, for supplying the passengers, are connectable to the supply line. The supply modules are displaceable relative to one another along the supply line, the supply line having one or a plurality of supply openings by which the connection between the supply line and the supply modules can be established, each supply module furthermore being assigned at least one screen which is arranged in such a manner on the service supply line that it is displaceable along the supply line and can cover a part of the one supply opening or of the plurality of supply openings which is not used for the connection of a supply module to the supply line.

Abstract: Disclosed is a connecting arrangement for purposes of connecting an electrical line to a component section, with a holding device, which has a holding element for purposes of arranging on the component section and a connecting element for purposes of connecting the line with the holding element, with a breakthrough to be provided on the component section for purposes of guiding through the connecting element, wherein the holding element is embodied in the form of a clamp for purposes of encompassing the component section in at least some sections, and wherein a positioning device is provided for purposes of positioning the holding element in a design position on the component section, which has a holding element-side positioning element and a counter element to be provided on the component section, which interact in a form fit, and also a holding element for such a connecting arrangement with a clamp-type profile and a positioning element for purposes of a form-fit positioning of the holding element on the co

Abstract: A measuring device for an aircraft is provided in order to determine physical properties of aerosol particles in real time. The device includes a heating device that separates volatile and solid aerosol particles, and a particle sensor that measures acquired data. The physical properties of the solid aerosol particles are determined with an analyzer. The determined analytical data is forwarded to other internal aircraft systems via a communication interface. Due to the formation of a measuring data or analytical data network with several airliners equipped with the measuring device, accurate and up-to-date information on the particle pollution, for example, along flight paths, can be obtained and used for defining no-fly zones, if so required.

Abstract: A fuselage cell for an aircraft includes at least two shell segments forming a fuselage cell. The shell segments are provided with a plurality of longitudinal and/or circumferential reinforcements that are integral with a skin panel of the respective shell segment. The reinforcements at least sectionally form a closed cross-sectional geometry together with at least the skin panel of the corresponding shell segment in order to create at least one hollow space, wherein at least one system component at least sectionally extends and/or at least one system medium is at least sectionally routed in the at least one hollow space. The reinforcements also fulfill the function of accommodating at least part of the system components and system mediums of the technical equipment of the aircraft. This results in weight savings and a simplified installation because the number of required mountings and connectors for the system components is reduced.

Abstract: A standardized wall mounting is provided for mounting control units of system components in an aircraft cabin with a fastening unit and at least one plug unit. The fastening unit is designed for guiding the control unit during an installation movement of the control unit on the wall mounting. The plug unit is designed for producing a plug connection between the control unit and the wall mounting during the installation movement of the control unit on the wall mounting.

Abstract: A water system for a vehicle is provided. The water system comprises at least one water supply source, at least one water-conducting device, at least one closing valve and at least one germ reduction connection. The germ reduction connection and the water supply source are connected to the water-conducting device. The germ reduction connection is designed to introduce a germ-reducing fluid into the water-conducting device. The closing valve is arranged between the water supply source and the germ reduction connection and is designed to be fully closed thus preventing the ingress of germ-reducing fluid into the water supply source. By means of such a water system it is possible to carry out sterilization or disinfection very easily and quickly without this requiring any major maintenance work.

Abstract: A device for determining ageing of a hydraulic fluid in a hydraulic system with a multitude of hydraulic components is provided. The device comprises at least one temperature determination device and at least one ageing determination device, wherein the temperature determination device determines the respective temperature of each discrete fluid volume of the hydraulic fluid in the hydraulic system, and from the aforesaid the ageing determination device determines an increase in ageing. Generally, the temperature determination device carries out a numerical thermal simulation of the hydraulic system, component by component, including determining at least one temperature of at least one hydraulic component of the hydraulic system, which simulation is supported by measuring the temperatures of individual hydraulic components by means of temperature sensors.

Abstract: A method and device for measuring the flow speed of a fluid, in one example, of air, is provided.

Abstract: A joining apparatus for joining together structural components of an aircraft, includes positioning means for holding the structural components to be joined in a defined desired position, in which the structural components can be fixedly joined together by means of a joining device that can be moved relative to the structural components by way of guiding means, wherein the positioning means encompass a formative frame structure that is detachably secured to the structural components to be connected along the joining edges outside in the edge area, and serves as a guiding means for the joining device movably secured hereupon.

Abstract: A silencer for an auxiliary power unit of an aircraft includes an inlet, an outlet, a housing, and a flow channel of a porous material, arranged in the housing. Between the housing and the flow channel an intermediate space is created, which space is divided by at least one outer partition into outer cells arranged around the flow channel. A central body includes a casing that is permeable to gas at least in some regions and that is arranged in the interior of the silencer. The central body includes inner partitions dividing the central body into inner cells. The resonance frequency of the inner cells corresponds to the natural frequency of the first radial mode in a channel formed between the central body and the inner surface of the inlet. In this manner particularly good sound attenuation is achieved with a compact installation space of a silencer.

Abstract: An actuation device for opening an emergency exit flap of a cockpit door is provided. The actuation device comprises a support structure, at least two securing elements, an actuation element and a deflection mechanism. The support structure is configured so as to be fastened to the emergency exit flap. The securing elements are integrated into the support structure and are configured so as to fasten the actuation device, and thus the emergency exit flap, to the cockpit door. The actuation element is connected to the support structure. Therein, the deflection mechanism connects the securing elements to the actuation element in such a way that a force which is exerted on the actuation element is diverted in such a way that the securing elements are released from the cockpit door.

Abstract: The invention pertains to a protective device for a pressure line for conveying pressurized fluids, as well as to a pressure line section with a pressure line for conveying pressurized fluids and a corresponding protective device.

Abstract: An aircraft fuselage includes at least one opening that can be closed by a flap or door, which comes to abut against at least one door stopper that is arranged on a fuselage-side door frame bulkhead and transfers the impact forces into an intermediate costal for diversion into an aircraft structure that encompasses bulkheads, wherein the door frame bulkhead exhibits an opening, through which an impact section of the door stopper extends, wherein a fastening plate section adjoining the latter comes to abut the rear side of the door frame bulkhead, which interacts with means for directly introducing the impact forces from the door stopper into the intermediate costal.