Abstract: A method for manufacturing a lining element is provided. The method comprises laying a textile membrane onto a positive molding tool, applying first fibers and a matrix material onto at least one first region of the textile membrane for creating a semi-finished product of a framework supported textile, providing at least one sealing element along outer edges of the molding tool, covering the textile membrane and the at least one sealing element in an air tight manner by a covering means, evacuating the space between the molding tool and the covering means and curing the matrix material by heating the semi-finished product. Thereby, a lining element with a low weight and at the same time a sufficient directional stability is provided that furthermore allows to easily recycle the components of the lining element.

Abstract: A method for load relieving a test object, wherein a load is applied by a multiplicity of hydraulic devices positioned side by side each introducing a partial load into the test object such that the test object has a minimum deflection in an area close to its fixation and a maximum deflection in an area far away from the fixation, wherein the load is reduced sequentially from the maximum deflection to the minimum deflection. A test rig is provided that enables an autonomous and non-synchronical load relief of a test object based on pressure difference. A test rig is provided that enables an autonomous and non-synchronical load relief of a test object based on a delay time and a control system for such test rigs.

Abstract: A modular cabin segment for a vehicle includes a first lateral segment module accommodating a first toilet arrangement with a toilet compartment, a second lateral segment module, and at least one central module, wherein in each case an outer lateral face of the first segment module and of the second lateral segment module is designed to adapt in each case to an inner wall of a cabin of the vehicle so as to correspond to the aforesaid. At least one of the modules includes a cabin attendant seat that on one side is held on the at least one module so that it can be pivoted on an axis. In this manner very good integration of many different functions in the manner of a construction kit is achieved in order to be able to accommodate a greater number of passenger seats elsewhere within the limited space provided in a cabin.

Abstract: A method for manufacturing a solid oxide fuel cell element by layer-wise buildup wherein at least one section of the element is built up by carrying out a step that at least includes the following at least once: applying a layer section of a particulate ceramic material with predefined dimensions onto a base layer in a predefined area and heating the layer section by means of a heat source such that the particles of the ceramic material connect to one another within the predefined dimensions. The solid oxide fuel cell element manufactured with the method is realized in one piece, as well as highly compact, and has a low weight.

Abstract: A toilet arrangement for a vehicle includes a first toilet compartment, an adjacent second toilet compartment and a partition wall situated between the first toilet compartment and the second toilet compartment, wherein the partition wall is movably supported and designed for being transferred into an open position, in which the partition between the first toilet compartment and the second toilet compartment is removed. This makes it possible to convert two relatively small toilet compartments into a larger toilet compartment that is suitable for use by persons with limited mobility.

Abstract: A method for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft, said method comprising the following method steps: positioning the two components relative to one another in such a way that a connection region is formed between the two components; friction stir welding the two components by means of a friction stir welding tool which penetrates the connection region in order to produce a weld which permeates the connection region with the formation of an unpenetrated weld edge portion of the connection region; and introducing internal compressive stresses, at least in the weld edge portion of the connection region. Further a device for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft is provided.

Abstract: A method of transmitting speech and digital data via an analog speech channel within a single frequency band, wherein an analog speech signal is transmitted via the speech channel and a stream of digital data is encoded by an encoding device to a sequence of blocks of symbols taken from a predetermined set of symbols. The transmission of the analog speech signal is periodically blanked during predetermined spaced time intervals, and the blocks of symbols are transmitted during the time intervals. In each time interval a plurality of signals are transmitted via a corresponding plurality of spaced predetermined carrier frequencies. A receiver receives the analog speech signal and the signals transmitted during the time intervals. The signals are demodulated to recover the individual symbols and the respective block of symbols transmitted during the time interval groups, and the digital data is recovered by decoding recovered blocks of symbols.

Abstract: A lightweight structural panel which comprises a planarly extended outer skin having a thickness and stiffening elements which are connected to the outer skin and arranged at a distance from one another. The outer skin is formed by component layers which are each extended in the planar direction of the lightweight structural panel and complement one another to form the thickness of the outer skin and are interconnected, the stiffening elements being formed in one piece with one of the component layers.

Abstract: An automated transport device for moving a cargo unit within an aircraft cargo compartment is provided. The transport device comprises a base body and shifting means, wherein the base body is to carry the cargo unit. The shifting means is to generate a movement of the base body along a floor of the cargo compartment perpendicular to the longitudinal axis of the aircraft and, after that, along the longitudinal axis of the aircraft without rotation of the base body.

Abstract: The present invention provides a device for connecting a first electric cable to a second electric cable, said device comprising: a first cable lug which comprises a first connection portion for electrically contacting the first electric cable and a socket portion having a conical socket; a second cable lug which comprises a second connection portion for electrically contacting the second electric cable and a plug portion having a conical plug; wherein the plug can be inserted into the socket and conductively contacted therewith in order to connect the first cable to the second cable in an electrically conductive manner.

Abstract: A passenger service system includes an individual ventilation arrangement and/or a lighting arrangement, wherein at least one air nozzle of the individual ventilation arrangement and/or at least one reading lamp of the lighting arrangement is/are disposed in the region of a service surface of the passenger service system. The service surface of the passenger service system includes a substantially flat portion as well as a buckled portion, which is curved convexly relative to the substantially flat portion and extends along a longitudinal axis (LP) of the passenger service system.

Abstract: A system for checking the positioning of components is provided. The system includes a reading device for reading in component identification information, which is provided by an identification device in a spatially limited region about a component to be checked, a locating device with at least one stationary reference device, a movement component which is movable relative thereto and a computing unit. The reading device and the locating device can be connected to the computing unit. The computing unit is set up to detect a relative position of the movement component with respect to the at least one reference device in the spatially limited region about the component to be checked and to form a data pair from the detected relative position with component identification information read in by means of the reading device and to compare it with predefined data pairs.

Abstract: A power drive unit, including a plurality of diagonal rollers arranged at a circumference around a central roller axis and each of the plurality of diagonal rollers having a respective diagonal roller axis, a first drive motor coupled to a roller carrier and configured to rotate the plurality of diagonal rollers around the central roller axis, and a second drive motor coupled to a gear carrier and configured to rotate each of the diagonal rollers around the respective diagonal roller axis. The diagonal roller axes are tilted by a common skew angle with respect to the central roller axis.

Abstract: An aircraft including a primary-structure connection element for attaching the aircraft skin to the primary structure of the aircraft is provided. The primary-structure connection element is designed as a shearweb, a clip and/or as a frame stabilization element or as a rib stabilization element and is manufactured from a fiber-reinforced thermoplastic material with the use of injection molding. Likewise, an injection molding method for the manufacture of such a primary-structure connection element is provided, in which method the fiber-reinforced thermoplastic material is injected in its melted state into an injection molding device. The manufactured shearweb etc. is removed from the injection molding device. In this method, in particular, chopped carbon fibers and/or glass fibers in combination with polyphenylene sulfide (PPS) and/or polyetherether ketone (PEEK) are used, for example also in pellet form.

Abstract: A mobile device and a method for the placement of a group of pin-type fasteners so as to form at least one seam field for purposes of connecting large components in aircraft construction, such as fuselage shells and fuselage sections, for purposes of connecting large components in ship construction, in rail vehicle construction, in building construction, and similar construction environments.

Abstract: The invention relates to a method for application of a multifunctional coating to the surface of a workpiece made from aluminum or an aluminum alloy. The invention further relates to a workpiece, which may be produced by such a method.

Abstract: A wing assembly and method for operating the wing assembly, the assembly having a main wing and high-lift body movably coupled to the leading edge of the main wing, the coupling achieved by a driving device, an adjusting lever arrangement having a first main wing lever coupled to the main wing formed between a first adjusting lever pivot joint and the high-lift body as well as a second main wing lever coupled to the main wing so as to form an effective lever arm between a second adjusting lever pivot joint and a first adjusting lever pivot joint, and at least one adjusting lever non-rotatably coupled to the high-lift body, the high-lift body being movable between an initial position and a maximally adjusted position with respect to the initial position, at least one guide mechanism aiding movement of the high-lift body.

Abstract: A method is provided for producing a bonded joint between fiber-reinforced thermoplastic parts to be joined, in which fiber-containing plastic material is mixed into the joining zone while friction stir welding the parts to be joined in the form of a butt joint. A device for carrying out such a method for a joined component is also provided.

Abstract: A method for generating hydraulic power in an aircraft, the aircraft having a drive system comprising at least one transmission shaft connected to a power control unit, the power control unit having an electric motor and a hydraulic displacement machine connected to a differential gear unit for driving a common output shaft. The method includes switching the hydraulic displacement machine into a pump mode, arresting the output shaft, rotating the electric motor such that the hydraulic displacement machine is driven due to the arrested output shaft and supplying the fluid flow into a hydraulic system. A drive system of an aircraft may thereby be used for either moving control surfaces or for generating hydraulic power in an aircraft. This hydraulic power may be used to cover hydraulic load peaks during aircraft operation or to power hydraulic devices without the need of additional hydraulic power generation components.