Abstract: A pressure bulkhead for the pressure-tight axial closure of a pressurized fuselage of an aircraft or spacecraft that is capable of being put under internal pressure includes dome segments, having an integrated reinforcement, in particular a peripheral reinforcement, which are in each case made integrally from a fiber-reinforced thermoplastic plastics material, and are joined to one another so as to form a pressure dome.

Abstract: A pressure bulkhead for the pressure-tight axial closure of a pressurized fuselage of an aircraft or spacecraft that is capable of being put under internal pressure includes dome segments, having an integrated reinforcement, in particular a peripheral reinforcement, which are in each case made integrally from a fiber-reinforced thermoplastic plastics material, and are joined to one another so as to form a pressure dome.

Abstract: A method for producing a thermoplastic fiber composite component, in particular for an aircraft or spacecraft, has the following method steps: material-removing processing of a first face of a first plate, wherein the first plate comprises a thermoplastic fiber composite material and a local reduction in thickness of the first plate is made by the material-removing processing of the first face; positioning a second plate relative to the first plate such that the first face of the first plate is brought into alignment with a third face of the second plate; and joining the first plate to the second plate to form a single component, wherein the surface of the first face of the first plate is integrally bonded to the surface of the third face of the second plate.

Abstract: A method for joining a first and a second component, at least one of which comprises a fiber-reinforced plastics material. The components are arranged in relation to one another in such a way that a gap region remains between the first and the second component. The gap region is filled, at least in portions, with an uncured plastics material filler in which nanoparticles are dispersed. Energy is introduced locally into the nanoparticles in order to cure the plastics material filler. In another aspect, the invention provides a device for joining two components.

Abstract: A semi-finished product arrangement for producing a fiber composite component by molding a planar semi-finished fiber composite product in a molding tool is provided. The arrangement includes the semi-finished fiber composite product and multiple holding elements fixed in place thereon and each extending beyond the edge of the semi-finished fiber composite product. The holding elements are countersunk in recesses of the semi-finished fiber composite product, in order to avoid a projection in terms of height.

Abstract: A method for producing a thermoplastic fiber composite component, in particular for an aircraft or spacecraft, has the following method steps: material-removing processing of a first face of a first plate, wherein the first plate comprises a thermoplastic fiber composite material and a local reduction in thickness of the first plate is made by the material-removing processing of the first face; positioning a second plate relative to the first plate such that the first face of the first plate is brought into alignment with a third face of the second plate; and joining the first plate to the second plate to form a single component, wherein the surface of the first face of the first plate is integrally bonded to the surface of the third face of the second plate.

Abstract: A semi-finished product arrangement for producing a fiber composite component by molding a planar semi-finished fiber composite product in a molding tool is provided. The arrangement includes the semi-finished fiber composite product and multiple holding elements fixed in place thereon and each extending beyond the edge of the semi-finished fiber composite product. The holding elements are countersunk in recesses of the semi-finished fiber composite product, in order to avoid a projection in terms of height.

Abstract: A method for edge sealing a fiber-reinforced component formed from a carbon fiber-reinforced thermoplastic or duroplastic plastic material includes electrostatic coating of at least one section of an edge of the component with a thermoplastic powder so as to form a powder coating; and fusing and cross-linking the powder coating in a furnace so as to create a smooth edge seal.

Abstract: A method for the manufacture of a fiber-reinforced component includes heating a blank of a carbon-fiber-reinforced thermoplastic plastic material to at least a melting temperature of the thermoplastic plastic material; introducing the blank into an at least two-part molding tool; forming the fiber-reinforced component by applying pressure on the blank using the molding tool; and injecting a further thermoplastic plastic material into at least one edge region of the molding tool so as to form an edge seal.

Abstract: The invention pertains to a device for loading goods into and/or unloading goods from a loading space 25, particularly a container, with a conveyor arm 1 that features a transfer station 5, 7, 9 for receiving the goods in the region of its proximal end and a transfer station 21, 23 for delivering the goods in the region of its distal end, wherein the conveyor arm 1 features a transport section 13, 15, 17, 19, 21 for transporting the goods from the transfer station 5, 7, 9 to the transfer station 20, wherein the transfer station 20 is realized in the form of a transfer and/or removal head 21, 23 that automatically deposits the goods at a predefined position in the loading space (25) and/or automatically picks up the goods from a predefined position in the loading space (25), and wherein the conveyor arm 1 is able to continuously transport the stream of successive goods to and/or from the predefined position.

Abstract: A non-destructive determination of material characteristics of an aircraft component is provided. To provide a simple determination of material characteristics, which can be implemented economically, it is provided to make available image data of a layer, which can be detected from outside using electromagnetic radiation, of a workpiece to be examined; to detect first areas having a first pixel characteristic using the image data; and to detect second areas having a second pixel characteristic using the image data; the first pixel characteristic being associated with a fiber inlay of a fiber composite layer; and the second pixel characteristic being associated with an at least part-crystalline thermoplastic polymer of the fiber composite layer, which thermoplastic polymer is in a crystalline state; and to determine a relationship of the first areas to the second areas.

Abstract: The invention concerns a shell segment for the purpose of manufacturing a fuselage cell section for a fuselage cell of an aeroplane, with at least one skin field and with a multiplicity of longitudinal stiffeners arranged thereon, in particular stringers, and also at least one transverse stiffening element running transverse to the longitudinal stiffeners, in particular at least one frame. In that the connection of the at least one transverse stiffening element to the at least one skin field is undertaken with at least one connecting bracket wherein the at least one connecting bracket has at least one corrugation, the supporting brackets for purposes of absorbing tilting moments of the frames, in forms of embodiment of shell segments of prior known art, can be omitted. By this means a considerable weight reduction is possible with, at the same time, a reduced production effort.

Abstract: The invention pertains to a device for loading goods into and/or unloading goods from a loading space 25, particularly a container, with a conveyor arm 1 that features a transfer station 5, 7, 9 for receiving the goods in the region of its proximal end and a transfer station 21, 23 for delivering the goods in the region of its distal end, wherein the conveyor arm 1 features a transport section 13, 15, 17, 19, 21 for transporting the goods from the transfer station 5, 7, 9 to the transfer station 20, wherein the transfer station 20 is realized in the form of a transfer and/or removal head 21, 23 that automatically deposits the goods at a predefined position in the loading space (25) and/or automatically picks up the goods from a predefined position in the loading space (25), and wherein the conveyor arm 1 is able to continuously transport the stream of successive goods to and/or from the predefined position.

Abstract: A method and a device for inspecting the quality of a formed thermoplastic fiber-reinforced plastic component wherein the component is tested by means of a sensor unit with a downstream electronic evaluation unit for analysis of the measuring result acquired by sensor technology by means of sample comparison, wherein by means of the optical sensor unit the surface roughness of the plastic component is measured after forming, which surface roughness is analyzed by means of the evaluation unit by a comparison with a stored reference pattern in such a manner that increased surface roughness is interpreted as increased internal materials porosity.

Abstract: The invention relates to a device for the production of an angle for connecting a fuselage cell skin to an annular former and/or a stringer inside a fuselage cell structure of an aircraft, the angle taking place by the one-step deformation of an initially planar blank along at least three fold lines in a uniaxial compression molding device. A mounting frame with hinges is arranged in the compression molding device, the blank to be deformed being accommodated along the edges preferably by means of a plurality of peripherally arranged springs. A deformation of the blank into an auto-stabilized angle is possible in one step while simultaneously ensuring interlaminar slide. Due to the constructively conditioned auto-stabilization of the angle, additional components which increase the weight and the assembly effort (so-called “stabilos”) in the connection region between fuselage cell skin, stringers and annular formers inside a fuselage structure of an aircraft are unnecessary.

Abstract: A coupling element for connecting stringers in the process of joining two fuselage sections by means of at least one transverse splicing plate, wherein in each case the fuselage sections on the inside comprise a multitude of stringers arranged on fuselage skins, as well as annular frame elements, wherein the coupling element comprises a base flange and a frame element flange, and by way of the coupling element in each case a connection between the opposing stringers, the annular frame element and the fuselage skins or the transverse splicing plate takes place so that the coupling element beyond a connection of the stringer base also supports the connection of stringers on the flank side.

Abstract: A non-destructive determination of material characteristics of an aircraft component is provided. To provide a simple determination of material characteristics, which can be implemented economically, it is provided to make available image data of a layer, which can be detected from outside using electromagnetic radiation, of a workpiece to be examined; to detect first areas having a first pixel characteristic using the image data; and to detect second areas having a second pixel characteristic using the image data; the first pixel characteristic being associated with a fiber inlay of a fiber composite layer; and the second pixel characteristic being associated with an at least part-crystalline thermoplastic polymer of the fiber composite layer, which thermoplastic polymer is in a crystalline state; and to determine a relationship of the first areas to the second areas.

Abstract: An apparatus for distributing goods delivered on one or more feeding conveyor belts onto two or more removal conveyor belts, wherein the feeding conveyor belts as well as the removal conveyor belts are subdivided into a plurality of individual conveyor belts which are arranged in parallel side by side and are driven jointly. A rotary table having an essentially circular contour and also comprising a plurality of parallel individual conveyor belts which are also allocated to a joint drive is positioned between the feeding and the removal conveyor belts, wherein the feeding and the individual removal conveyor belts each closely reach up to the individual conveyor belts of the rotary table and are, in essence, adjusted in their length to the circular contour of the rotary table.

Abstract: A method for joining a first and a second component, at least one of which comprises a fibre-reinforced plastics material. The components are arranged in relation to one another in such a way that a gap region remains between the first and the second component. The gap region is filled, at least in portions, with an uncured plastics material filler in which nanoparticles are dispersed. Energy is introduced locally into the nanoparticles in order to cure the plastics material filler. In another aspect, the invention provides a device for joining two components.

Abstract: The invention relates to a vehicle window consisting of a transparent composite material, wherein the composite material comprises fibers and a matrix material such that the vehicle window is capable of withstanding structural loads occurring in the window region and can substantially provide the window function even in spite of damage to the vehicle window (damage-tolerant), the fibers and the matrix material being transparent and substantially having the same refractive index. The invention proposes vehicle windows which are damage-tolerant, load bearing, cost-saving, easy to handle and require less installation space than conventional vehicle windows.