Abstract: A device and a system for a lacquer transfer with a frame, transfer roller with a circumferential lateral wall, a drive unit, a slit nozzle, the slit nozzle at least indirectly connected to the frame, an outside contact surface of the lateral wall including depressions, the transfer roller mounted rotatably about an axis of rotation at the frame, the drive unit configured to drive the transfer roller for the transfer roller to rotate about the axis of rotation. The slit nozzle includes a supply connection, nozzle-cavity, slit-shaped nozzle-channel and at least one limiter, the supply connection coupled to the nozzle-cavity for supplying lacquer to the nozzle-cavity, the nozzle-channel extending from the nozzle-cavity to a muzzle end formed by the slit nozzle at the end of the nozzle-channel for dispensing lacquer, the slit nozzle configured by the limiter to adjust a cross-section in a restriction area of the nozzle-channel.

Abstract: In a method for producing a rail-shaped hybrid component, in particular for an aircraft or spacecraft, a second rail component made of a titanium material is positioned on a first bar of a first profile rail that is made of a carbon-fiber reinforced plastic material and moved in an advancing direction, in a fixed position relative to the first profile rail, such that a bar portion of the first bar is arranged between a first connecting portion of the second rail component and a second connecting portion of the second rail component, and the second rail component is cohesively connected to the first profile rail. Furthermore, the hybrid component has a first profile rail made of a carbon-fiber reinforced plastic material and a second rail component made of a titanium material.

Abstract: A method for producing a three-dimensional preform from reinforcing fibers for producing a component from a fiber-reinforced plastic comprises the steps of introducing at least one layer of fibers having a binder into a draping mold, forming the at least one layer of fibers by at least one forming element which is displaceable along the draping mold, applying an airtight film to the at least one layer of fibers during or directly after the forming, creating a negative pressure in the intermediate space between the airtight film and the draping mold, activating the binder and removing the negative pressure after curing of the binder.

Abstract: A seat rail for supporting seats in an aircraft comprises a support portion for connection with the cabin floor and a seat receiving portion having a groove for receiving the end portions of connector elements coupled with the support frame of a seat. The support portion comprises a profile arrangement of a fiber-reinforced polymer, preferably carbon fiber-reinforced polymer, having a central main portion and flanges which extend outwardly from and perpendicular with respect so the main portion to form a support surface for the seat rail. The main portion comprises a slot open at least at its end remote from the flanges. At least one metal element comprising the groove for receiving the end portions of the connector elements has a leg which is inserted into the slot of the main portion and is secured therein. The seat rail may be manufactured in a continuous process.

Abstract: A tool for shaping non-cured reinforcement fibers into a substantially T-shaped profile, comprising a web-shaping tool and a forming tool, wherein the forming comprises an inflatable diaphragm.

Abstract: An apparatus for carrying a fiber composite resin system in a heat transfer device, in particular an autoclave, for transferring heat between the fiber composite resin system and a directed gas flow, to produce a fiber composite aircraft component. The apparatus comprises a carrier structure for carrying the fiber composite resin system, the carrier structure having at least one flow path which, when the apparatus is accommodated in the heat transfer device, extends from an inlet on a side facing the directed gas flow along the fiber composite resin system accommodated by the carrier structure, to allow heat exchange between the gas flow in the flow path and the fiber composite resin system, and a diverting device for diverting at least a part of the directed gas flow when the apparatus is accommodated in the heat transfer device, to feed this part to the carrier structure flow path.

Abstract: A method for producing a textile preform includes manufacturing a multi-layer fiber fabric, which includes a first flange portion and a web portion connected to the first flange portion, deforming a first fiber layer of the first flange portion with respect to the web portion, such that the first fiber layer is at a first flange portion angle to the web portion, a web height of the web portion being set in a variable manner during the deformation of the first fiber layer, and depositing a unidirectional fiber fabric only on the deformed first fiber layer of the first flange portion.

Abstract: In a method for producing a rail-shaped hybrid component, in particular for an aircraft or spacecraft, a second rail component made of a titanium material is positioned on a first bar of a first profile rail that is made of a carbon-fiber reinforced plastic material and moved in an advancing direction, in a fixed position relative to the first profile rail, such that a bar portion of the first bar is arranged between a first connecting portion of the second rail component and a second connecting portion of the second rail component, and the second rail component is cohesively connected to the first profile rail. Furthermore, the hybrid component has a first profile rail made of a carbon-fiber reinforced plastic material and a second rail component made of a titanium material.

Abstract: In a device and method for manufacturing preforms of fiber reinforced plastic, in a first step, continuously supplied fiber layers are laterally reshaped in a predetermined manner, and the section that is obtained is curved longitudinally in a specific manner in a second step.

Abstract: The present invention relates to a method of forming a curved prepreg strip or sheet, especially for use in fabricating a composite component. The method includes providing a strip or sheet of prepreg material having reinforcing fibers and drawing or conveying the prepreg material in a travel direction, wherein the material is drawn or conveyed in the travel direction at a speed which differs across a width of the strip or sheet transverse to the travel direction. Similarly, the invention relates to an apparatus for forming a curved prepreg strip or sheet, having: a mechanism for drawing or conveying a strip or sheet of prepreg material in a travel direction, wherein the mechanism is configured to draw or convey the strip or sheet of prepreg material in the travel direction at a speed which differs across a width of the strip or sheet transverse to the travel direction.

Abstract: An apparatus and method for producing a fiber-reinforced plastics casting (FRP), includes a molding box filled with free flowing molding material, in what a prototype of casting or a textile preform is inserted, forming a mold cavity for infiltration the inserted preform of textile with synthetic resin material in order to form a fiber-reinforced plastics casting (FRP).

Abstract: A seat rail for supporting seats in an aircraft comprises a support portion for connection with the cabin floor and a seat receiving portion having a groove for receiving the end portions of connector elements coupled with the support frame of a seat. The support portion comprises a profile arrangement of a fiber-reinforced polymer, preferably carbon fiber-reinforced polymer, having a central main portion and flanges which extend outwardly from and perpendicular with respect so the main portion to form a support surface for the seat rail. The main portion comprises a slot open at least at its end remote from the flanges. At least one metal element comprising the groove for receiving the end portions of the connector elements has a leg which is inserted into the slot of the main portion and is secured therein. The seat rail may be manufactured in a continuous process.

Abstract: A method for producing a textile preform includes manufacturing a multi-layer fiber fabric, which includes a first flange portion and a web portion connected to the first flange portion, deforming a first fiber layer of the first flange portion with respect to the web portion, such that the first fiber layer is at a first flange portion angle to the web portion, a web height of the web portion being set in a variable manner during the deformation of the first fiber layer, and depositing a unidirectional fiber fabric only on the deformed first fiber layer of the first flange portion.

Abstract: An apparatus and method for producing a fiber-reinforced plastics casting (FRP), includes a moulding box filled with free flowing moulding material, in what a prototype of casting or a textile preform is inserted, forming a mould cavity for infiltration the inserted preform of textile with synthetic resin material in order to form a fiber-reinforced plastics casting (FRP).

Abstract: The present invention relates to a method of forming a curved prepreg strip or sheet, especially for use in fabricating a composite component. The method includes providing a strip or sheet of prepreg material having reinforcing fibres and drawing or conveying the prepreg material in a travel direction, wherein the material is drawn or conveyed in the travel direction at a speed which differs across a width of the strip or sheet transverse to the travel direction. Similarly, the invention relates to an apparatus for forming a curved prepreg strip or sheet, having: a mechanism for drawing or conveying a strip or sheet of prepreg material in a travel direction, wherein the mechanism is configured to draw or convey the strip or sheet of prepreg material in the travel direction at a speed which differs across a width of the strip or sheet transverse to the travel direction.

Abstract: A device for the master moulding technique production of an integral structural component made of a fibre composite for an aircraft that is reinforced by stringers includes at least one moulded part forming a mounting surface to create an exterior or interior surface of the structural component, onto which at least one channel for evacuation of the structural component covered by a vacuum film is arranged, with the structural component comprising a skin-like laminate and a plurality of stringers which are disposed spaced apart from one another, wherein at least surface sections between adjacent stringers are covered with an auxiliary stripe, which comprises a textile ventilation fleece which rests on a vacuum film, and a pre-assembled release film firmly connected therewith, the width (BF) of which is greater than or equal to the width (BV) of the ventilation fleece.