Abstract: The invention relates to a detection device (10) for detecting the emotional state of a user. The detection device (10) comprises a processing unit (1) for processing data, in particular input data, a main data storage unit (2) for storing data, in particular input data and/or data processed by said processing unit and a connecting element (3a, 3b) for connecting the detection device (10) to an interface device (50), in particular a mobile phone or a tablet, and/or a recording device (7a, 7b). The detection device (10) is adapted to be calibrated to said user by use of the processing unit (1) and calibration data. In particular, the calibration data is at least one set, preferably five sets, of audio and video data of said user. The processing unit (1) is adapted to analyse input data based on said calibration. In particular, the processing unit (1) is adapted to compare input data to calibration data and to calculate the nearest approximation of the input data and the calibration data.

Abstract: A microplastic filter (also referred herein as fluid filter) for a washing machine has a filter housing, a first filter screen, a second filter screen, an inlet opening 16, and an outlet opening. The inlet and outlet openings communicate with each other through the first filter screen to define a direction of fluid flow. The first filter chamber has a retentate outlet, is particularly easy to handle if the second filter screen is arranged in a cavity of the filter housing, the inlet and outlet openings communicate with each other through the second filter screen, and the retentate outlet is arranged on a side of the second filter screen that faces the fluid flow.

Abstract: A microplastic filter (also referred herein as fluid filter) for a washing machine has a filter housing, a first filter screen, a second filter screen, an inlet opening 16, and an outlet opening. The inlet and outlet openings communicate with each other through the first filter screen to define a direction of fluid flow. The first filter chamber has a retentate outlet, is particularly easy to handle if the second filter screen is arranged in a cavity of the filter housing, the inlet and outlet openings communicate with each other through the second filter screen, and the retentate outlet is arranged on a side of the second filter screen that faces the fluid flow.

Abstract: A composite skin for the aeronautics and astronautics industries, and also a method for producing a composite skin of this type is provided. The method comprises the following method steps: removing excess material from a butt plate to form a butt strap at one end thereof, subsequently connecting the other end of the butt plate to a skin plate with a substance-to-substance bond, and then fastening a further skin plate to the butt strap to form the composite skin. The idea behind the invention involves replacing a rivet connection with a substance-to-substance bond. This provides the advantage that the weight of the composite skin and the production costs for the composite skin are reduced.

Abstract: A transverse splicing plate for producing a fuselage of an aircraft by connecting several CFP fuselage sections that have in particular been produced in the winding method, in each case by forming a transverse seam, wherein the flexible transverse splicing plate is of a multilayer construction, in other words it comprises a multitude of plate segments arranged one above the other, wherein each of the plate segments comprises a multitude of longitudinal slits, each being able independently of each other to make small radial bending movements in order to cause tolerance compensation in radial direction between the fuselage sections to be joined, in which tolerance compensation a sliding movement between the sub-plates of the plate segments arranged one above the other takes place in axial direction of the barrel-shaped fuselage sections, and wherein on the inside the ends of the fuselage sections comprise chamfers; as well as a method for producing a connection between two CFP fuselage sections, which have pref

Abstract: A sealing arrangement is provided in which a seal flange includes a seal flange body having an integrated electrically conductive seal integrated onto an outer circumferential edge of the seal flange body. The seal flange with integrated seal is installable to seal between two confronting mounting flange faces. The seal is operative to conduct electric charge between said seal flange body and said mounting flanges.

Abstract: The present invention provides a structural component for an aircraft or a space craft having an outer skin and a first reinforcing element which runs on the outer skin along a first spatial direction. A second reinforcing element runs over the first reinforcing element in a second spatial direction. A foot element supports the second reinforcing element on the outer skin, the foot element having a feed-through opening in which the first reinforcing element is held in a positive manner. From another point of view, a method is provided for reinforcing an outer skin of an aircraft or space craft, in which a first reinforcing element is attached to the outer skin along a first spatial direction. A foot element having a feed-through opening is attached over the first reinforcing element such that the first reinforcing element is held positively in the feed-through opening. A second reinforcing element is attached to the foot element in a second spatial direction over the first reinforcing element.

Abstract: The present invention provides a pressure bulkhead for subdivision of an aircraft or spacecraft into an internal and an external pressure region. The pressure bulkhead comprises a pressure plate having an edge shaped so as to correspond to an inner contour of the aircraft or spacecraft, a supporting means which tiltably supports the edge on the inner contour, and a seal which seals the edge with the inner contour. A further aspect of the invention provides a method for subdivision of an aircraft or spacecraft into an internal and an external pressure region. Firstly, a pressure plate is provided that has an edge shaped so as to correspond to an inner contour of the aircraft or spacecraft. In further steps, the edge is tiltably supported on the inner contour and sealed with the inner contour.

Abstract: The invention relates to a fuselage cell structure of an aircraft for the simplified installation and attachment of at least one fastener for at least one conduit, the fuselage cell structure having a large number of reinforcing elements formed in particular using an aluminum alloy material. According to the invention, the reinforcing elements within the fuselage cell structure are provided with at least one groove in which the fasteners can be secured by producing a combined pressing and clamping fit creating a positive fit at least in certain regions. For this purpose, the fasteners can have at the lower face thereof, for example, two retaining feet which can be spread apart and attached by driving a fixing element into the groove. The reinforcing elements are continuous stringers preferably produced by extrusion and cross-bars, the required grooves being simultaneously extruded during the production process.

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: Disclosed is a method for producing a fuselage of an aircraft, wherein several fuselage sections that are arranged one behind another are joined together, comprises the following steps: a) production of an outer skin segment, the outer skin segment having on the underside a continuous longitudinal opening, b) widening the outer skin segment in order to introduce at least one floor frame, c) joining the outer skin segments to a rigid fuselage section which is already present, with the formation of a partial transverse seam, d) positioning a prefabricated lower shell in the longitudinal opening, in order to close the outer skin segment on the peripheral side, e) completing the partial transverse seam to form a transverse seam and joining the lower shell together with the outer skin segment with the formation of at least two longitudinal seams, and f) joining the floor frame together with the outer skin segment.

Abstract: Disclosed is a device for separating liquids from gases comprising a preseparator that separates an untreated gas region from a preseparator gas region, a main separator comprising a coalescing element for increasing the size of liquid droplets and a post-separator.

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 sealing arrangement is provided in which a seal flange includes a seal flange body having an integrated electrically conductive seal integrated onto an outer circumferential edge of the seal flange body. The seal flange with integrated seal is installable to seal between two confronting mounting flange faces. The seal is operative to conduct electric charge between said seal flange body and said mounting flanges.

Abstract: A laminate sheet, in particular for use as a fuselage skin includes thin aluminium alloy sheets layered on top of one another with each two aluminium alloy sheets being adhesively bonded to one another at least in regions by an adhesive layer which includes at least one unidirectional fibreglass insert impregnated with a curable synthetic resin.

Abstract: An air dryer desiccant cartridge, the cartridge comprising a base having an inlet and an outlet, and a casing connected to the base to define a cavity there between, wherein the cavity contains a filter and a desiccant, the filter being arranged upstream of the desiccant such that during normal operation fluid flow entering the cartridge through the inlet passes through the filter and then on to the desiccant before reaching the outlet, and during purging of the cartridge purge flow entering the outlet passes through the desiccant before reaching the filter, wherein further the cartridge includes a valve operable to permit a portion of the purge flow to bypass the filter.

Abstract: The invention relates to a fuselage cell structure of an aircraft for the simplified installation and attachment of at least one fastener for at least one conduit, the fuselage cell structure having a large number of reinforcing elements formed in particular using an aluminium alloy material. According to the invention, the reinforcing elements within the fuselage cell structure are provided with at least one groove in which the fasteners can be secured by producing a combined pressing and clamping fit creating a positive fit at least in certain regions. For this purpose, the fasteners can have at the lower face thereof, for example, two retaining feet which can be spread apart and attached by driving a fixing element into the groove. The reinforcing elements are continuous stringers preferably produced by extrusion and cross-bars, the required grooves being simultaneously extruded during the production process.

Abstract: The present invention provides a structural component for an aircraft or a space craft having an outer skin and a first reinforcing element which runs on the outer skin along a first spatial direction. A second reinforcing element runs over the first reinforcing element in a second spatial direction. A foot element supports the second reinforcing element on the outer skin, the foot element having a feed-through opening in which the first reinforcing element is held in a positive manner. From another point of view, a method is provided for reinforcing an outer skin of an aircraft or space craft, in which a first reinforcing element is attached to the outer skin along a first spatial direction. A foot element having a feed-through opening is attached over the first reinforcing element such that the first reinforcing element is held positively in the feed-through opening. A second reinforcing element is attached to the foot element in a second spatial direction over the first reinforcing element.

Abstract: A transverse splicing plate for producing a fuselage of an aircraft by connecting several CFP fuselage sections that have in particular been produced in the winding method, in each case by forming a transverse seam, wherein the flexible transverse splicing plate is of a multilayer construction, in other words it comprises a multitude of plate segments arranged one above the other, wherein each of the plate segments comprises a multitude of longitudinal slits, each being able independently of each other to make small radial bending movements in order to cause tolerance compensation in radial direction between the fuselage sections to be joined, in which tolerance compensation a sliding movement between the sub-plates of the plate segments arranged one above the other takes place in axial direction of the barrel-shaped fuselage sections, and wherein on the inside the ends of the fuselage sections comprise chamfers; as well as a method for producing a connection between two CFP fuselage sections, which have pref

Abstract: The present invention provides a pressure bulkhead for subdivision of an aircraft or spacecraft into an internal and an external pressure region. The pressure bulkhead comprises a pressure plate having an edge shaped so as to correspond to an inner contour of the aircraft or spacecraft, a supporting means which tiltably supports the edge on the inner contour, and a seal which seals the edge with the inner contour. A further aspect of the invention provides a method for subdivision of an aircraft or spacecraft into an internal and an external pressure region. Firstly, a pressure plate is provided that has an edge shaped so as to correspond to an inner contour of the aircraft or spacecraft. In further steps, the edge is tiltably supported on the inner contour and sealed with the inner contour.