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 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 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 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 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 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: 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 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: 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: 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 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 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.