Abstract: A device for processing items, in particular items in a production sequence, in different processing steps, has at least one sensor arrangement having a plurality of sensors, wherein at least one item is measured in a detection mode by at least a partial quantity of the sensors as the detection means, wherein an impacting of the at least one item with an irradiation means is determined by a control means while considering a result of the measuring procedure of the at least one item; and wherein the at least one item is irradiated in an irradiation mode by at least a further partial quantity of the plurality of sensors as the irradiation means. If appropriate, at least part of the method is repeated with a renewed measuring, determination and/or irradiation.

Abstract: An airfoil portion includes an outer skin member and an inner stiffening member. Either the outer skin member or the inner stiffening member or both are arranged to delimit a chamber. The chamber is configured to contain an inner pressure, wherein the inner pressure differs from a pressure external to the chamber. In an embodiment, an aircraft includes such an airfoil portion. A method for providing such an airfoil portion with a chamber is also described.

Abstract: An aircraft includes a fuel cell device which can be operated with hydrogen from a hydrogen tank and with oxygen drawn from the surrounding air, and further includes a superconducting magnetic energy storage unit (SMES unit) which is disposed, together with the hydrogen tank, in a cryogenic container, wherein the cryogenic container does not have an active cooling system or a liquid hydrogen generating device, and has a volume for holding a maximum of 40 kg liquid hydrogen.

Abstract: A cabin structural component for a transport vehicle, in particular for an aircraft or spacecraft, has a sandwich structure that has a core and a first cover layer, the first cover layer being provided with a heat conductor that is arranged and designed for heating a cabin wall that can be produced using the cabin structural component.

Abstract: An effector for an aircraft has an effector body and a stealth sheath enclosing the effector body at least in part. The stealth shell is attached to the effector body and embodied so as to be separated from the aircraft and from the effector body during flight of the aircraft carrying the effector.

Abstract: A cooling system for an interior space of a vehicle comprises a main cooling system coupled with an air inlet for receiving air and coupled with the interior space for providing cooled air to the interior space, at least one air duct arranged between the air inlet and the interior space, a reservoir for liquid nitrogen having a nitrogen outlet and a valve arranged between the outlet and an injection port of the at least one air duct. The reservoir is couplable with the injection port of the at least one air duct via the valve on demand for evaporating nitrogen in the at least one air duct. With the injection of liquid nitrogen the main cooling system is supported in case it is not able to provide a sufficient cooling power.

Abstract: A method for the additive manufacturing of a receptacle for storing and/or transporting a product includes three-dimensionally capturing the external form of the product, compiling a computer-readable data set with information about the captured external form of the product, and additively manufacturing the receptacle. In a computer-controlled manner on the basis of the compiled data set, a modelling material is deposited in layers, liquefied and cured. The receptacle is formed having an internal structure which surrounds a receiving chamber that is adapted to the external form of the product.

Abstract: A method for the manufacture of reinforced core composites, comprises: inserting of a pin into a foamed core material or a filled honeycomb-shaped core material, wherein the pin and the core material contain a thermoplastic polymer, or a mixture of thermoplastic polymers; the pin is heated such that as the pin is inserted the core material softens or melts at the point of insertion; and/or the core material is heated at the point of insertion such that the core material softens or melts.

Abstract: This relates to a sinterable composite electrolyte compound, a sintered composite electrolyte, a method for manufacturing a sintered composite electrolyte and the use of the sintered composite electrolyte in a fuel cell, preferably a solid oxide fuel cell, an exhaust gas probe or a high-temperature gas sensor, and a fuel cell, preferably a solid oxide fuel cell, exhaust gas probe or high-temperature gas sensor containing the sintered composite electrolyte.

Abstract: A gas inlet suitable in particular for use in an ion thruster includes a housing which is made of a gas-tight ceramics material, and an insert which is arranged in the housing and is made of a porous ceramics material. The geometry and pore structure of the insert are such that the insert forms a desired flow resistance for a gas stream flowing through the insert.

Abstract: A method for effecting the airborne determination of geographic coordinates of corresponding pixels from digital synthetic aperture radar images, where the SAR images are available in the form of slant range images and the recording position of the respective SAR image is known. The coordinates of the corresponding pixels in the SAR images and the corresponding range gates are used in each case to determine the distance between a corresponding resolution cell on the ground and the respective recording position of the respective SAR image. The determined distances and associated recording positions of the SAR images are used to determine the geographic coordinates of the corresponding pixels in the SAR images by employing a WGS84 ellipsoid.

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 arrangement for visual fault inspection of at least one component includes a fault identification unit for identifying a structural fault of the component and for determining at least one piece of fault information, and an overlay device connected to the fault identification unit, configured for context-dependent overlay of the fault information in a component image in real-time.

Abstract: This relates to changes in wing profiles. In order to provide an aerodynamic structure that can be variably adjusted and changed with respect to the wing profile, it is provided that an aerodynamic structure for a wing or rudder arrangement of an aircraft comprises a support structure and an outer skin. The support structure comprises an adaptive surface support structure in a longitudinal direction, which extends in a longitudinal direction from a root area to an outer end area, and is formed by a support surface, which comprises an adjustable periodic profiling that runs in the transverse direction, in which first flange areas and second flange areas are alternatingly formed, and joined together by web areas running in the direction of a profile height. Alternatingly aligned open profile segments running in the longitudinal direction are here formed.

Abstract: Coating a metallic surface with at least one of a pretreatment composition prior to organic coating, with a passivation composition without intent for subsequent organic coating, with a pretreatment primer composition, with a primer composition, with a paint composition and with an electrocoating composition, wherein the coating composition includes particles on a base of at least one layered double hydroxide (LDH) phase characterized by the general formula [M2+(1±0.5)?x(M3+, M4+)x(OH)2±0.75]An?x/n.mH2O.

Abstract: An engine for propelling an aircraft includes an annular fuel cell arrangement having at least one fuel cell, at least one electric motor couplable to the fuel cell arrangement, at least one fan couplable to the electric motor and a cowling having an inlet and an outlet nozzle. The fuel cell arrangement is arranged inside the cowling, the at least one fan is arranged between the inlet and the fuel cell arrangement inside the cowling, the electric motor is operable under consumption of electric power delivered by the fuel cell arrangement and the at least one fan is designed to produce a thrust force by creating an accelerated airflow at the outlet nozzle. The engine is extremely efficient and comprises a distinct low noise.

Abstract: An intake for feeding air to an engine of an aircraft includes an opening for sucking in air, which opening faces in the direction of movement of the aircraft; and an air duct between the opening and the engine, which air duct is curved such that an impact region is arranged in the air duct after the opening in relation to the direction of movement of the aircraft. An object flying into the opening contacts the impact region. The impact region has a penetration region, which is designed to be penetrated by the impinging object.

Abstract: An aircraft (1), in particular a passenger or cargo aircraft, with a fuselage (2), has a tandem wing arrangement and has at least two aero engines (5, 6) disposed on the upper surface of the rear wing (4). In this way the disadvantages of the known solutions of the prior art are avoided and an improved aircraft configuration with improved aerodynamics, namely clearly reduced induced drag, is provided. Moreover, the invention creates an environmentally friendly aircraft design which conserves resources, increasing the acceptance of such aircraft among the population.

Abstract: A coating method for producing a function layer on mechanically loaded components or surfaces includes providing or applying a first material layer of a first material or substrate matrix having a mechanical flexibility higher than that of a second material on a substrate constituting the component or the surface, respectively, structuring the first material layer such that the material layer surface of the first material layer, which is opposite to the substrate, obtains a three-dimensionally molded basic structure with projections and recesses, and coating the material layer surface of the first material layer with a second material layer of the second material in such a way that the second material layer adopts substantially the basic structure of the material layer surface with the projections and recesses. Also, surface layer structures can be produced by this method.

Abstract: A positioning system for detecting a spatial position of a laying head of a device for automatically laying reinforcing fiber strips in relation to a base on which the reinforcing fiber strips can be laid by the laying head includes at least two laser lines which extend substantially in parallel at a spacing A from one another and substantially transversely to a laying direction can be projected on the laid reinforcing fiber strips by at least one laser source. The elevation profiles of the projected laser lines which occur on account of an irregular surface of the laid reinforcing fiber strips are able to be recorded by a camera and supplied to an evaluation unit.