Abstract: An induction heated tool system for receiving and heating polymer-fiber components from a starting temperature to a target temperature includes a tool part having a receiving cutout, the tool part formed from a thermally dimensionally stable material so it has a coefficient of thermal longitudinal expansion less than 10×10?6 K?1, or less than 5×10?6 K?1, or less than 4×10?6 K?1 in the plane of the largest dimension of the receiving cutout, at temperatures between the starting and target temperatures. A receiving cutout for receiving a polymer-fiber component is in the tool part, the receiving cutout delimited by a receiving surface portion so a polymer-fiber component received in the receiving cutout can lie against the receiving surface portion. A susceptor element includes a ferromagnetic material with a first Curie temperature. The susceptor element is on a surface portion of the tool part outside the receiving cutout and the receiving surface portion.

Abstract: A method for manufacturing a structural assembly comprising at least two assembly components interconnected by means of a thermoplastic plastics material, and useful in the field of aviation or space travel. First, a first assembly component and a second assembly component are provided and arranged so as to form an arrangement. Second, the arrangement is subjected to creep forming at a temperature which is selected in such a way that the thermoplastic plastics material melts at least in part during the creep forming so as to connect the first assembly component and the second assembly component. The invention further relates to structural assemblies, in particular for an aircraft or spacecraft, and to an aircraft or spacecraft comprising a structural assembly of this type.

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 method for producing a fiber composite component assembly having at least first and second plate-shaped composite structures made from synthetic resin embedded fibers, the at least first and second fiber composite components having a plurality of partial regions not containing synthetic resin is described. The method includes positioning the at least first and second fiber composite components, the partial regions having been brought to flush conformity with each other, bonding the at least first and second positioned fiber composite components by the adhesive layer arranged in between, placing mechanical reinforcement means through the partial regions, infusing the dry partial regions with synthetic resin, and curing the synthetic resin placed in the partial regions.

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: 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: Disclosed is a laying down device and method for the automated laying down of fiber 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 induction heating system and a method for controlling a process temperature for induction heating of a workpiece. The induction heating system comprises an inductor configured to generate an alternating magnetic field in response to an alternating current supplied thereto, a magnetic load comprising a magnetic material, the magnetic material having a Curie temperature and being configured to generate heat in response to the alternating magnetic field being applied thereto, the magnetic load being connectable to the workpiece in a heat-conducting manner so as to transfer the generated heat to the workpiece, and a control unit configured to control the process temperature for manufacturing the workpiece by adjusting the alternating magnetic field when the temperature of the magnetic material is in a temperature control range around or below the Curie temperature of the magnetic material, the temperature control range being dependent on the magnetic material of the magnetic load.

Abstract: A material for use in vacuum bagging a component. The material includes a compound sensitive to moisture, such that an exposure of the compound to moisture or wetting causes a physical and/or chemical change in the compound that is visually detectable in the cover material. A method of leak detection during vacuum bagging involves the steps of: arranging a component in a vacuum bagging assembly, such as to form a fiber-reinforced plastic component; arranging a material according to the invention in the vacuum bagging assembly such that the compound sensitive to wetting or moisture is under, or on an inner side of, a sealing film or vacuum bag of the assembly; applying a vacuum to the vacuum bagging assembly to evacuate a space containing the component and sealed by the sealing film or vacuum bag; and wetting an outer surface of the sealing film or vacuum bag.

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 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 producing a fiber composite component assembly having at least first and second plate-shaped composite structures made from synthetic resin embedded fibers, the at least first and second fiber composite components having a plurality of partial regions not containing synthetic resin is described. The method includes positioning the at least first and second fiber composite components, the partial regions having been brought to flush conformity with each other, bonding the at least first and second positioned fiber composite components by the adhesive layer arranged in between, placing mechanical reinforcement means through the partial regions, infusing the dry partial regions with synthetic resin, and curing the synthetic resin placed in the partial regions.

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: 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.