Abstract: A method for masking communication signals, particularly for masking terrestrial RF communication signals on board of an aircraft, includes parallelizing a first information data stream to be transmitted on a first LTE transmission channel, the first LTE transmission channel having a first channel transmission bandwidth and at least one guard band adjacent to the channel transmission bandwidth; spreading the first information data stream over a plurality of mutually orthogonal data subcarriers within the first channel transmission bandwidth; generating a CAZAC sequence; spreading the generated CAZAC sequence over guard band subcarriers within the at least one guard band; and transmitting the first information data stream over the data subcarriers in parallel to the CAZAC sequence over the guard band subcarriers.

Abstract: A system for moving loads including a cargo compartment floor into which there is integrated at least one roller conveyor permitting displacement of a load in a direction parallel to a surface of said cargo compartment floor. The system also comprises a transport vehicle comprising a drive system and a platform movable between a first operating position and a second operating position. In its first operating position, the platform is arranged such that the transport vehicle is positionable under a load which is supported on the roller conveyor integrated into the cargo compartment floor. In its second operating position, the platform is arranged such that the load is entrained when a movement of the transport vehicle occurs in a direction parallel to the surface of the cargo compartment floor, and is displaced on the roller conveyor integrated into said cargo compartment floor.

Abstract: The present invention relates to acoustical panels. As to provide a cabin panel to be made as simple as possible and with optimized acoustical properties, an acoustical cabin panel (10) is provided that comprises a first (12) and a second layer (14) which are spaced apart from each other by an intermediate layer (16) and altogether with a plurality of reinforcement elements (22) form a core composite component (24). Furthermore, the panel comprises at least one intermediate layer (18) made of a core material (20) which is arranged in the intermediate layer. The reinforcement elements extend from the first to the second layer through the at least one intermediate film and are tension and pressure resilient in a finished state of the panel. The reinforcement elements can be at least partially infiltrated with a curable matrix material and at least one prepreg (26) soaked with matrix material is provided in the first and/or second layer.

Abstract: An assembly for guiding a cable between a structural part of an aircraft and a movable aerodynamic body includes a chain of pivotally connected links, a first coil device arranged between each pair of the links for guiding the cable between two angular positions, and a second coil device arranged at the first end of the chain for passing the cable from the chain to the aerodynamic body. The support of the assembly is statically determinate through the use of a bracket pivotally connected to one of the links at the structural part, which bracket does not permit a translative motion relative to the structural part. This is further supported by a bearing located at one of the links which is connected to the second coil device, which bearing permits angular rotation at least in two orthogonal directions, but no translative motion relative to the aerodynamic body.

Abstract: A method for producing a textile preform includes manufacturing a multi-layer fiber fabric, which includes a first flange portion and a web portion connected to the first flange portion, deforming a first fiber layer of the first flange portion with respect to the web portion, such that the first fiber layer is at a first flange portion angle to the web portion, a web height of the web portion being set in a variable manner during the deformation of the first fiber layer, and depositing a unidirectional fiber fabric only on the deformed first fiber layer of the first flange portion.

Abstract: A galley system comprises at least one electrically operated galley device, at least one fuel cell, a plurality of compartments for housing the galley devices, and an air extraction means. At least one of the plurality of compartments comprises at least one air extraction port couplable with the air extraction means. The at least one compartment is adapted for housing at least one of the at least one fuel cell and for removing at least a part of heat emanated from the at least one fuel cell through the air extraction means. At least one of the at least one electrically operated galley device is electrically couplable with the at least one fuel cell unit.

Abstract: A floor panel for an aircraft comprising a panel structure for transmitting forces applied to the floor panel, wherein the panel structure includes an upper cover layer, a lower cover layer, and a core assembly sandwiched between the upper and lower cover layers, and a heater layer for heating the floor panel, wherein the heater layer is provided between the upper and lower cover layers. The object of the present disclosure, to provide a possibly simple heated floor panel for an aircraft, wherein the risk of overheating and at the same time the risk of local hot spots at the heater layer is reduced, is achieved in that the heater layer is formed as a PTC-layer having a plurality of electric conductor paths interconnected to one another by a plurality of PTC-resistor paths comprising a PTC-material, wherein the electric resistance of the PTC-Material increases with increasing temperature.

Abstract: A system for liquid composite molding includes a first rigid tool part onto which a semi-finished fiber material is positioned, a first vacuum foil arrangeable on the first rigid tool part to provide a first gastight chamber therebetween having a first port, a second vacuum foil and the first vacuum foil providing a second gastight chamber, and granulated material arranged in the second gastight chamber. The semi-finished fiber material is infusible with a matrix material via the first port. A second port is provided at the second gastight chamber for applying a negative pressure thereto. Therein, the granulated material is adapted for forming a second rigid tool part when negative pressure is applied to the second port. I.e. the first vacuum foil, the second vacuum foil and the granulated material function similarly to a vacuum mattress and may be stiffened and collapsed.

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 structural member for an aircraft or spacecraft has at least one fiber plastic composite, the fiber plastic composite having at least one or a plurality of plies. The structural member also has at least one pre-stressing means providing internal stresses to the fiber plastic composite. The fiber plastic composite and the pre-stressing means are configured and arranged to form a balanced system the internal stresses of which are essentially balanced to zero in a cured state of the said system. The balanced system of the structural member is able to counteract loading stresses exerted to the airframe in service such, that a damage caused by the loading stress is easily detectable visually.

Abstract: A connecting port arrangement for use in an apparatus for producing a composite material component comprising a base member attached to a surface of a foil adapted to seal a mold of the apparatus for producing a composite material component. The base member is provided with a channel extending therethrough. The connecting port arrangement further comprises a punch member adapted to be inserted into the channel formed in the base member and provided with a cutting device suitable to cut at least one opening into the foil.

Abstract: A sanitary unit for a cabin region on board a vehicle is provided with a first lavatory facility and a second lavatory facility. The first and the second lavatory facilities in each case form a longitudinally-directed interior space comprising two longitudinal sides and two narrow sides. In each case a narrow side comprises an access door. The first and the second lavatory facilities adjoin each other by their longitudinal sides and are separated from each other by a shared middle wall. The shared middle wall extends between lateral connection regions on the narrow sides and comprises at least one offset at least in a middle region between the two lateral connection regions in the horizontal direction.

Abstract: A luggage article is provided. The luggage article includes a shell, an electronic processing module integrated with the shell, and an electronic display coupled to the electronic processing module and arranged on an outer surface of the shell. The processing module is configured to control the display to display information items to a user of the luggage article. The luggage article may be configured to display itinerary or travel related information on the display under the control of a user of the luggage article.

Abstract: A data acquisition system, particularly for use in avionics systems, has a control and monitoring apparatus having a plurality of electronic application components and a multiplexer coupled to the plurality of electronic application components, a domain network interface coupled to the multiplexer, a data collection component having a data flow controller and a data collection memory component coupled to the data flow controller, a plurality of external interfaces, and an interface component implemented in the data collection component and coupled between the data flow controller and the plurality of external interfaces. The interface component is configured to allow bidirectional protocol-based communication between the data flow controller and systems connected to the plurality of external interfaces.

Abstract: A device for the attachment of seats in passenger cabins of aeroplanes, road coaches, ships, railways, and similar, with at least one seat track, which has at least one exterior latching section, and with at least one holding device for purposes of attaching the seat to the at least one seat track. The at least one holding device has two integrated arms to engage around the latching sections and a multiplicity of teeth to fix it in position. The teeth can be moved in the vertical direction of the seat track. A seat track thermally is coated on at least some sections with exterior latching sections. A method is disclosed for the attachment of seats in passenger cabins.

Abstract: The present disclosure pertains to a window panel for a body structure of a vehicle, especially an airframe of an aircraft or spacecraft, including a first skin which extends over a first side of the panel to form an outer skin of the vehicle body structure; a second skin which extends over a second side of the panel to form an inner skin of the vehicle body structure; and a core, especially a foam core, located between and covered by the first and second skins in a sandwich structure. The window panel includes at least one window aperture formed through the first layer, the core, and the second layer. The core may be confined to or extends over a limited extent, region or part of the panel. Thus, the first skin and/or the second skin may extend over or cover a greater area of the panel than the core.

Abstract: An aircraft interior equipment component (10) with a frame (12) which comprises two rigid frame sections (14a-h) and a joint (16a-h) connecting the rigid frame sections (14a-h) to one another, and with a sheetlike section (18) which is supported by the frame (12) and is formed by a flexible and/or foldable membrane (20) connected to the frame (12).

Abstract: In a method for operating an aircraft cooling system a cooling medium is guided through a cooling circuit, which is connected to a refrigerating machine and to at least one cooling station associated with a cooling energy consumer, to supply cooling medium cooled by the refrigerating to the cooling station. A temperature of the cooling medium upstream of the cooling station and a temperature of the cooling medium downstream of the cooling station are detected. The mass flow of cooling medium supplied to the cooling station is controlled in dependence on a thermal output of the cooling energy consumer and in dependence on a difference between the temperature of the cooling medium upstream of the cooling station and the temperature of the cooling medium downstream of the cooling station.

Abstract: An aqueous composition for forming a chemical conversion layer on a metal surface, wherein the composition contains at least one active component for the formation of the chemical conversion layer, as well as at least one thickener, and has a viscosity in the range between 10 mPa*s and 10000 mPa*s.

Abstract: A method for manufacturing a load bearing structure involves providing a panel; providing a first set of split stiffening elements on a surface of the panel, wherein the split stiffening elements of the first set have bottom surfaces and central portions with open top clearances, respectively, spaced apart from each other; providing a second set of stiffening elements having bottom surfaces and top surfaces and central portions, respectively; inserting the stiffening elements of the second set into respective open top clearances of the split stiffening elements of the first set and providing the second set of stiffening elements on the surface of the panel for forming a grate structure; and attaching top surfaces to the split stiffening elements of the first set for forming complete profiles.