Abstract: A system for liquid composite molding includes a first rigid tool part onto which a semi-finished fiber material is positioned, a first vacuum foil arrangeable on the first rigid tool part to provide a first gastight chamber therebetween having a first port, a second vacuum foil and the first vacuum foil providing a second gastight chamber, and granulated material arranged in the second gastight chamber. The semi-finished fiber material is infusible with a matrix material via the first port. A second port is provided at the second gastight chamber for applying a negative pressure thereto. Therein, the granulated material is adapted for forming a second rigid tool part when negative pressure is applied to the second port. I.e. the first vacuum foil, the second vacuum foil and the granulated material function similarly to a vacuum mattress and may be stiffened and collapsed.

Abstract: A connecting port arrangement for use in an apparatus for producing a composite material component comprising a base member attached to a surface of a foil adapted to seal a mold of the apparatus for producing a composite material component. The base member is provided with a channel extending therethrough. The connecting port arrangement further comprises a punch member adapted to be inserted into the channel formed in the base member and provided with a cutting device suitable to cut at least one opening into the foil.

Abstract: A flat metallic structure having a multiplicity of openings and having a width between 6 and 1000 mm. The metallic structure is treated with a metallic impregnating material whose melting point is lower than that of the flat metallic structure, and wherein the conductivity of the metal before the impregnation is at least 15 S/m. A use of such a structure as lightning protection for fiber composite components, as well as fiber composite components having such a structure, and a method for the production of such fiber composite components.

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: A method for manufacturing a component includes a) providing a first, plate-shaped semi-finished product and a second semi-finished product, the first semi-finished product including a first thermosetting reactive resin with non-directionally inserted long-stranded fibers, the second semi-finished product including an oriented network of endless fibers, the endless fibers having a mean length l of at least 80 mm, and the long-stranded fibers having a mean length k which is at least 30 mm shorter than that of the endless fibers; b) placing the second semi-finished product on top of the first semi-finished product so as to form a semi-finished product group; c) inserting the semi-finished group into a first molding part of a multi-part mold of a press, the semi-finished group covering between 70% and 95% of the first molding part after the insertion; d) extrusion forming of the semi-finished product group by the mold resulting in the component; and e) removing the component.

Abstract: A vacuum bagging system for vacuum bagging a fiber-reinforced polymer component for an aircraft or spacecraft includes a vacuum bagging film or membrane which is configured to cover and seal the component during molding. The vacuum bagging film or membrane is pre-formed, e.g. thermoformed, to a shape or to an external geometry of the component to be molded. A method of vacuum bagging a fiber-reinforced polymer component of an aircraft or space-craft, includes the steps of: arranging a component to be molded in a vacuum bagging assembly for forming a fiber-reinforced polymer component; pre-forming a vacuum bagging film or membrane to a shape or external geometry of the component; and arranging the vacuum bagging film or membrane on or over the component in the vacuum bagging assembly such that the film or membrane form-fittingly covers the component.

Abstract: In a method for producing a component from a fiber-reinforced composite material, a semifinished product, containing reinforcing fibers, is disposed on a support surface. The semifinished product is covered with a film, draped, in at least one portion, such that at least one fold, extending from the support surface, is produced. A sealing tape is applied along an open edge of the fold, to seal off a space, defined by the support surface and the film, from the ambient atmosphere, in the region of the fold, such that two mutually opposite fold walls are formed partly by the film and partly by the sealing tape. A clip is applied over the fold such that the clip applies a clamping force, which presses the mutually opposite fold walls of the fold against each other. A vacuum is generated in the space defined by the support surface and the film.

Abstract: Disclosed is a laying down device and method for the automated laying down of fibre tapes on a surface, wherein a creel is arranged on an independent positioning device that can be individually traversed in three dimensions, and tracks the movements of a laying head; also disclosed is a laying method.

Abstract: An apparatus for producing a composite material aircraft component comprises a mold having a receiving space adapted to accommodate a plastic material. A heating device is adapted to supply heat to the mold in order to heat the plastic material accommodated within the receiving space of the mold. The apparatus further comprises a plurality of heat pipes, each heat pipe having a first end which is in thermal contact with a heat source and a second end which is in thermal contact with the receiving space of the mold, such that the plastic material accommodated within the receiving space is supplied with heat transferred to the receiving space from the heat source via the plurality of heat pipes.

Abstract: An assembly for producing a fiber composite workpiece having a base tool, including a first tool part and a second tool part, arranged relative to one another either in a closed position in which they enclose an internal space, or in an open position wherein a preform can be mounted in the internal space and maintained there in a predetermined shape. The base tool includes a connection to convey matrix material into the internal space, and has a device for holding the first and second tool parts together in a closed position. A tool insert is provided which is separate from the base tool, the tool insert being mounted in the internal space of the base tool, and the tool insert including a cavity for accommodating a preform and a shaping surface, facing the cavity, for maintaining the preform in a predetermined shape.

Abstract: A flat metallic structure having a multiplicity of openings and having a width between 6 and 1000 mm, characterized in that the metallic structure is treated with a metallic impregnating means whose melting point is lower than that of the flat metallic structure, and in that the conductivity of the metal before the impregnation is at least 15 S/m;, a use of such a structure as lightning protection means for fiber composite components as well as fiber composite components having such a structure, and a method for the production of such fiber composite components.

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: An apparatus for producing a composite material aircraft component comprises a mold having a receiving space adapted to accommodate a plastic material. A heating device is adapted to supply heat to the mold in order to heat the plastic material accommodated within the receiving space of the mold. The apparatus further comprises a plurality of heat pipes, each heat pipe having a first end which is in thermal contact with a heat source and a second end which is in thermal contact with the receiving space of the mold, such that the plastic material accommodated within the receiving space is supplied with heat transferred to the receiving space from the heat source via the plurality of heat pipes.

Abstract: A lighting strike protection device for applying automatically to a fiber composite component. The protection device includes a reinforcement structure having a width that is less than a width of the metal strip. The fiber composite component having an integrated lighting strike protection.

Abstract: A connecting port arrangement for use in an apparatus for producing a composite material component comprising a base member attached to a surface of a foil adapted to seal a mold of the apparatus for producing a composite material component. The base member is provided with a channel extending therethrough. The connecting port arrangement further comprises a punch member adapted to be inserted into the channel formed in the base member and provided with a cutting device suitable to cut at least one opening into the foil.

Abstract: A system and method for producing a composite component, especially for continuous production of such composite components, includes a feeding device for feeding one or more layers of reinforcing material from a material supply along a process path, a resin application device for applying a resin matrix to the reinforcing material fed along the process path, and a forming device configured to shape or mould a profile of the reinforcing material and the resin matrix applied thereto to form a composite component as the reinforcing material is fed or conveyed along the process path.

Abstract: A preform station for forming a flexible semi-finished product and for transforming a flexible semi-finished product into a geometrically stable preform is provided. The preform station comprises a first pin array having a multitude of pins, on which the semi-finished product can be draped. Furthermore, the pins are movable along their longitudinal directions in order to form the flexible semi-finished product. Furthermore, the preform station comprises an activation device for activating a binder of the semi-finished product such that the semi-finished product can be transformed into the geometrically stable preform.

Abstract: A system for liquid composite moulding includes a first rigid tool part onto which a semi-finished fiber material is positioned, a first vacuum foil arrangeable on the first rigid tool part to provide a first gastight chamber therebetween having a first port, a second vacuum foil and the first vacuum foil providing a second gastight chamber, and granulated material arranged in the second gastight chamber. The semi-finished fiber material is infusible with a matrix material via the first port. A second port is provided at the second gastight chamber for applying a negative pressure thereto. Therein, the granulated material is adapted for forming a second rigid tool part when negative pressure is applied to the second port. I.e. the first vacuum foil, the second vacuum foil and the granulated material function similarly to a vacuum mattress and may be stiffened and collapsed.

Abstract: A method for stiffening a skin field of an aircraft fuselage includes providing a skin field for an aircraft fuselage, manufacturing an integral lattice-shaped stiffening structure including a plurality of longitudinal stiffeners and connecting the stiffening structure to the skin field. The manufacturing can include the use of a tool mold having a plurality of longitudinal recesses configured to form longitudinal stiffeners and a plurality of sunken areas disposed between the longitudinal recess. The sunken areas are configured for forming respective mounts that are configured for connection to circumferential stiffeners.

Abstract: A method for manufacturing a fiber composite component having an integral structural design includes positioning a sheet-like fibrous semi-finished product in a mold that defines an outer contour of the fiber composite component. Dimensionally stable fibrous semi-finished products, each having dimensions corresponding to a respective portion of the manufactured fiber composite component, are arranged on the sheet-like fibrous semi-finished product. The dimensionally stable fibrous semi-finished products are stabilized and fixed in place using mold cores. The semi-finished products are resin infiltrated using one of a first or a second gating process so as to form a construct. The first gating process includes gating via the mold cores at a head of each dimensionally stable fibrous semi-finished product and performing extraction in an area of the mold.