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 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: Disclosed is a reinforcement blank, in particular a curved ring frame segment for fuselage cells of aircraft, comprising a synthetic material that is reinforced by at least one fiber laminate. The fiber laminate includes at least one full-area layer with a first fiber direction and at least one full-area layer with a second fiber direction, wherein at least one further layer with a third fiber direction is arranged in a peripheral area of the fiber laminate. This results in an orientation of the fibers in the individual layers of the fiber laminate used to reinforce the reinforcement beam that is overall suitable for the applied load, so that the reinforcement beam withstands high mechanical loads at a minimum weight.

Abstract: Disclosed is a reinforcement blank, in particular a curved ring frame segment for fuselage cells of aircraft, comprising a synthetic material that is reinforced by at least one fiber laminate. The fiber laminate includes at least one full-area layer with a first fiber direction and at least one full-area layer with a second fiber direction, wherein at least one further layer with a third fiber direction is arranged in a peripheral area of the fiber laminate. This results in an orientation of the fibers in the individual layers of the fiber laminate used to reinforce the reinforcement beam that is overall suitable for the applied load, so that the reinforcement beam withstands high mechanical loads at a minimum weight.

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 moulding tool; forming the fiber-reinforced component by applying pressure on the blank using the moulding tool; and injecting a further thermoplastic plastic material into at least one edge region of the moulding tool so as to form an edge seal.

Abstract: The invention relates to a method for producing a component for connecting a fuselage cell skin to an annular rib of an aircraft, wherein the component is formed by bending of a flat blank along at last two edge lines and wherein the blank is formed by a CFRP. According to the invention the interlaminar sliding of the fiber layers is largely completed in a first forming step, while in a second forming step a consolidation of the component takes place by the use of pressure from the press on all sides by means of an upper tool and a lower tool. This enables complex components with at least two edge lines to be produced, which edge lines run at angles of approximately, preferably at angles of 309° to 90°, to each other, and which edge lines also lie in at least two different planes.

Abstract: The invention relates to a vehicle window consisting of a transparent composite material, wherein the composite material comprises fibres 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 fibres 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.

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: The invention relates to a method for producing a component for connecting a fuselage cell skin to an annular rib of an aircraft, wherein the component is formed by bending of a flat blank along at last two edge lines and wherein the blank is formed by a CFRP. According to the invention the interlaminar sliding of the fibre layers is largely completed in a first forming step, whilst in a second forming step a consolidation of the component takes place by the use of pressure from the press on all sides by means of an upper tool and a lower tool. This enables complex components with at least two edge lines to be produced, which edge lines run at angles of approximately, preferably at angles of 309° to 90°, to each other, and which edge lines also lie in at least two different planes.

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.

Abstract: Disclosed is a reinforcement blank, in particular a curved ring frame segment for fuselage cells of aircraft, comprising a synthetic material that is reinforced by at least one fiber laminate. The fiber laminate includes at least one full-area layer with a first fiber direction and at least one full-area layer with a second fiber direction, wherein at least one further layer with a third fiber direction is arranged in a peripheral area of the fiber laminate. This results in an orientation of the fibers in the individual layers of the fiber laminate used to reinforce the reinforcement beam that is overall suitable for the applied load, so that the reinforcement beam withstands high mechanical loads at a minimum weight.

Abstract: A closed ring fiber reinforced frame structure is produced by first preparing a prepreg. A section of the prepreg is formed into a flange preferably after impregnation by folding the flange section along a folding line. The folding line is formed by securing a deformable or drapable fiber ribbon material, for example by sewing or stitching to a carrier substrate which is preferably also a fiber material. The sewing seam or stitching line becomes the folding line. The ribbon material is so secured to the carrier substrate that the fiber orientation of the ribbon material is uniformly distributed all around a ring component that is formed of the ribbon material on the substrate. The impregnated ring component with its substrate is then cured after the folding of the flange to complete the ring frame structure.

Abstract: A closed ring fiber reinforced frame structure is produced by first preparing a prepreg. A section of the prepreg is formed into a flange preferably after impregnation by folding the flange section along a folding line. The folding line is formed by securing a deformable or drapable fiber ribbon material, for example by sewing or stitching to a carrier substrate which is preferably also a fiber material. The sewing seam or stitching line becomes the folding line. The ribbon material is so secured to the carrier substrate that the fiber orientation of the ribbon material is uniformly distributed all around a ring component that is formed of the ribbon material on the substrate. The impregnated ring component with its substrate is then cured after the folding of the flange to complete the ring frame structure.

Abstract: The invention relates to a belt conveyor comprising a revolving conveyor belt (1, 1′), carrying rollers (2, 2′) which are positioned between the upper strand (3) and the lower strand (4, 4′) of the conveyor belt (1), a drive device and a power-transmitting unit (5, 5′) for moving the conveyor belt (1). Damage to the surface of the conveyor belt of the belt conveyor by the power transmitting device is largely excluded by the fact that for power transmission a pair of elements (6, 6′, 7) is provided for which cooperate in a positive-fit and in that the one element (6, 6′) is assigned to the power-transmitting device (5, 5′) and the other element (7) to the conveyor belt (1).

Abstract: For securing the position of the conveyor belt when starting the belt under load, a belt tensioning device, has a circulating conveyor belt, carrying idlers arranged between the carrying run and the return run of the conveyor belt, a drive mechanism, a power transmission device for moving the conveyor belt, a gear ring and a toothed belt for power transmission, the gear ring being allocated to the power transmission device and the toothed belt being allocated to the conveyor belt, wherein a guiding component part adapted to the edge area of the circulating conveyor belt and a contacting component part for direct contact with the surface of the conveyor belt are provided, and wherein the contacting component part is arranged inside the guiding component part.