Abstract: An apparatus for draping knitted fiber fabrics for curved profiled structural parts of fiber composite material includes a mold having a mold surface that corresponds to a portion of the desired profile geometry and curvature of the profiled structural part, a clamping device for tensioning a layer of a knitted fiber fabric along a tensioning line in a prestressed state, and a movement device for producing a relative movement between the mold and the clamped-in fabric layer such that the mold surface moves close to the fabric layer in a direction perpendicular to the tensioning line and, in the further course of the relative movement, pushes through the tensioning line such that the fabric layer completely covers the mold surface. The clamping device is equipped to load the fabric layer during the entire draping operation with a tensile force acting along the tensioning line.

Abstract: Disclosed is an infusion method for the manufacture of a fiber-reinforced composite component with semi-finished textile products in an open molding tool, in which at least one local gas reception space is designed for the reception of volatile substances, such as resin gases and residual air contained in the matrix material and/or in the system, which gas reception space is blocked off from the matrix material by a local semi-permeable membrane; also disclosed is a system for the execution of such a method.

Abstract: An apparatus for draping knitted fiber fabrics for curved profiled structural parts of fiber composite material includes a mold having a mold surface that corresponds to a portion of the desired profile geometry and curvature of the profiled structural part, a clamping device for tensioning a layer of a knitted fiber fabric along a tensioning line in a prestressed state, and a movement device for producing a relative movement between the mold and the clamped-in fabric layer such that the mold surface moves close to the fabric layer in a direction perpendicular to the tensioning line and, in the further course of the relative movement, pushes through the tensioning line such that the fabric layer completely covers the mold surface. The clamping device is equipped to load the fabric layer during the entire draping operation with a tensile force acting along the tensioning line.

Abstract: The present invention provides a method for producing a fiber composite component, the method comprising arranging a first and a second mold in relation to one another in such a way that these together form a first cavity; laying a fiber material on the first and/or second mold; filling the first cavity with a casting material and solidifying the casting material in order to seal the first and second molds to one another and/or to interconnect them; and infiltrating the fiber material with a matrix and curing the matrix to form the fiber composite component.

Abstract: An additive manufacturing (AM) system including a platform including a mold die mounted on the platform, the mold die having a surface shape corresponding to a mold cavity used for thermoforming a thermoplastic sheet, and an AM assembly configured to perform an AM method on the thermoplastic sheet having been thermoformed with the mold die. A method for performing AM on a thermoplastic sheet comprises the steps of thermoforming a thermoplastic sheet using a mold die, and performing an AM method on the thermoformed thermoplastic sheet in the mold die as a substrate.

Abstract: A compression mold for use in a compression molding tool, is manufactured by an additive manufacturing method, particularly electron beam melting, selective laser melting, or selective laser sintering. A method for manufacturing a compression mold for use in a compression molding tool includes forming a compression mold body of the compression mold with an additive manufacturing (AM) method.

Abstract: An aircraft structural assembly includes an area element which has a core and an outer layer. A first surface of the area element is convexly curved, at least in certain sections, relative to an imaginary central area of the area element extending through the core of the area element. By contrast, a second surface of the area element located opposite the first surface is oriented, at least in certain sections, parallel to the imaginary central area of the area element extending through the core of the area element. The area element is configured in the form of a floor panel of a floor system. The first or the second surface of the area element is designed to form a walkable floor surface of the floor system in the state of the aircraft structural assembly when mounted in an aircraft.

Abstract: Disclosed is an infusion method for the manufacture of a fiber-reinforced composite component with a flow promoter, wherein the flow velocity of the matrix material in a component to be infiltrated is modified by means of the flow promoter. Also disclosed is a flow promoter, which has an integral body section for the modification of the flow velocity.

Abstract: A method of recycling scraps or offcuts of uncured composite material, such as pre-impregnated or “prepreg” scraps or offcuts having reinforcing fibres and uncured polymer matrix material, includes introducing the scraps or offcuts into a mixing device directly; mixing the scraps or offcuts in the mixing device to blend uncured polymer matrix material and reinforcing fibres of the scraps or offcuts into a generally homogenous or consistent mixture; and feeding or conveying the mixture from the mixing device into a shaping mechanism to form a component or semi-finished product and preferably on a continuous basis.

Abstract: The present invention provides a structural element, in particular for an aircraft or spacecraft, comprising a core, the material density of which varies, at least in portions, in order to optimize the natural vibration behavior of the structural element. The present invention further provides a method for producing a structural element, in particular for an aircraft or spacecraft, comprising the following steps: providing a structural element which has a core; determining the natural vibration behavior of the structural element; and varying the material density of the core of the structural element, at least in portions, in such a way that the natural vibration behavior of the structural element is optimized. The present invention provides still further an aircraft or spacecraft and a rotor blade, in particular for a wind turbine, comprising such a structural element.

Abstract: An apparatus for producing a component includes a material storage tank for receiving a liquid material (M), a molding tool in which a filling region to be filled with material (M) from the material storage tank is formed, and a material supply line which connects the material storage tank to the filling region of the molding tool. In the region of the material supply line and/or the filling region of the molding tool an optical fiber has been arranged, into which at least one Fibre Bragg Grating sensor for detecting a parameter that is characteristic of the flow of material through the material supply line and/or the filling region of the molding tool is integrated.

Abstract: Disclosed is a reinforcing material for the local reinforcement of a component formed with a composite material, in particular in areas of force introduction and/or connecting areas. The reinforcing material is formed by a metallic sheet-like formation, the metallic sheet-like formation having a surface with increased roughness to improve adhesion and a coating applied to the surface to provide a seal and improve the bond with the composite material. As a result of the presence of a coating on the metallic sheet-like formation, once it has been rolled up on supply rolls, said sheet-like formation can be drawn off from the supply rolls and at the same time processed in an automated manner by means of known computer-controlled laying devices with CRP prepreg materials in web form by laying layer by layer to produce components, in particular of large format, for aircraft.

Abstract: A connection is between a monolithic metal component and a continuous-fiber reinforced laminate component wherein the metal component and the laminate component are joined at the ends thereof. A method allows for the production of the connection between the monolithic metal component and the continuous-fiber reinforced laminate component.

Abstract: The present invention provides a method for producing a fibre composite component, comprising: arranging a first and a second mould in relation to one another in such a way that these together form a first cavity; laying a fibre material on the first and/or second mould; filling the formed first cavity with a casting material and solidifying said casting material in order to seal the first and the second mould to one another and/or interconnect them; and infiltrating the fibre material with a matrix and curing said matrix to form the fibre composite component.

Abstract: A fiber composite component comprising at least two, first and second partial elements bordering one another, each having a fiber structure and different matrix systems which respectively embed the fiber structure and cure differently from a liquid state is produced by liquifying the matrix system of the first partial element so that it either penetrates irregularly into the region of the bordering second partial element or leaves an unwetted region in the first partial element adjacent the second partial element, and subsequently liquifying the matrix system of the second partial element so that it can be cured abutting the irregular boundary surfaces of the matrix system of the first partial element. The intermeshing or interlocking of the matrix systems with one another and the fibers increase shear strength.

Abstract: Disclosed is an infusion method for the manufacture of a fibre-reinforced composite component with a flow promoter 18, wherein the flow velocity of the matrix material in a component 22 to be infiltrated is modified by means of the flow promoter 18; also disclosed is a flow promoter 18, which has an integral body section 20 for the modification of the flow velocity.

Abstract: The present invention relates to a method for detecting a defective sandwich component, particularly in aircraft construction, the method comprising the following steps: forming at least one measuring chamber in a core arrangement of a sandwich component, said at least one measuring chamber having an outwardly open end; subjecting the at least one measuring chamber to a predetermined pressure; and detecting and evaluating the pressure forming in the at least one measuring chamber.

Abstract: Disclosed is an infusion method for the manufacture of a fibre-reinforced composite component with semi-finished textile products in an open moulding tool, in which at least one local gas reception space is designed for the reception of volatile substances, such as resin gases and residual air contained in the matrix material and/or in the system, which gas reception space is blocked off from the matrix material by a local semi-permeable membrane; also disclosed is a system for the execution of such a method.

Abstract: An apparatus for producing a component includes a material storage tank for receiving a liquid material (M), a moulding tool in which a filling region to be filled with material (M) from the material storage tank is formed, and a material supply line which connects the material storage tank to the filling region of the moulding tool. In the region of the material supply line and/or the filling region of the moulding tool an optical fibre has been arranged, into which at least one Fibre Bragg Grating sensor for detecting a parameter that is characteristic of the flow of material through the material supply line and/or the filling region of the moulding tool is integrated.

Abstract: An apparatus for draping knitted fiber fabrics for curved profiled structural parts of fiber composite material includes a mold having a mold surface that corresponds to a portion of the desired profile geometry and curvature of the profiled structural part, a clamping device for tensioning a layer of a knitted fiber fabric along a tensioning line in a prestressed state, and a movement device for producing a relative movement between the mold and the clamped-in fabric layer such that the mold surface moves close to the fabric layer in a direction perpendicular to the tensioning line and, in the further course of the relative movement, pushes through the tensioning line such that the fabric layer completely covers the mold surface. The clamping device is equipped to load the fabric layer during the entire draping operation with a tensile force acting along the tensioning line.