Abstract: An arrangement and method for manufacturing a composite part includes a mold, a composite material including fiber material and matrix material on a forming surface of the mold. To provide a simple and cheap technology for forming and optionally curing the component at the mold, the method includes providing a pressing tool made of semi-crystalline thermoplastic material in an amorphous state on the forming surface of the mold, forming the pressing tool by applying a pressure, that can be by expanding a hollow mandrel, and pressing the pressing tool against the mold, conducting crystallization of the pressing tool material by increasing the temperature of the pressing tool so material of the pressing tool is crystallized. Afterwards, the composite part may be hardened, such as by curing the composite part between the mold and the crystallized tube mandrel.

Abstract: Devices and methods for producing a T-shaped semifinished product from a multiply non-crimp fabric with reinforcing fibers for a composite material. The product has a web and a flange. The device includes a web forming tool, with which a web portion of the non-crimp fabric is clamped in place, a forming tool, with which plies of a flange portion of the non-crimp fabric are split into two parts, a depositing device, with which a tube body is deposited on the flange portion formed into the flange, a holding tool, with which a clearance between the holding tool and the flange is formed, and a filling device, with which the tube body is filled with a gas such that the tube body fills the clearance and firmly holds the flange portion formed into the flange, and alternatively, a magnetic force can be generated between a sheet and the web forming tool.

Abstract: An arrangement for producing a composite material component comprises a bagging configured to seal a receiving space for a semi-finished part against the ambient atmosphere. The bagging is a thermoformed bagging having a shape which, at least in sections, corresponds to a shape of the semi-finished part and which comprises an air-tight outer layer and an inner separation layer. The inner separation layer is configured to allow the bagging to be separated from the composite material component made from the semi-finished part. The arrangement further comprises a vacuum source connected to the receiving space and configured to generate a reduced pressure within the receiving space. The arrangement also comprises a curing apparatus configured to cure a thermoset plastic material either contained in at least one element of the semi-finished part or injected into the receiving space when the semi-finished part is sealed within the receiving space via the bagging.

Abstract: The invention relates to a method and a molding core for producing a fiber composite component (34), in particular in aerospace, comprising the following method steps: introducing a core sleeve (9) into a molding tool (2) for establishing an outer geometry of a molding core (27) to be formed; filling the core sleeve (9) that is introduced with a vacuum-fixable filling material (21); applying a vacuum to the core sleeve (9) and consequently vacuum-fixing the filling material (21) for forming the molding core (27); and at least partly laying at least one semifinished fiber product (33a, 33b) on the molding core (27) that is formed, for the shaping of the fiber composite component (34) to be produced.

Abstract: A method for producing a fiber composite component, in particular for aerospace, includes the following method steps: introducing an elastic core sleeve into a prestressing mechanism; expanding the core sleeve that is introduced, for elastic prestressing of the same, by activating the prestressing mechanism; introducing a core body through an opening of the expanded core sleeve; releasing the core sleeve by deactivating the prestressing mechanism, for the snug enclosing of the core body by the core sleeve and thus for the forming of the molding core (14); and at least partly laying at least one semifinished fiber product on the molding core that is formed, for the shaping of the fiber composite component to be produced.

Abstract: The invention relates to a method for producing a plastic foil tube with an intended cross-section that derives from a circular cross-section as a means for the production of fiber compound components for aviation or aerospace. It comprises the following method steps: mounting a semi-finished tube on a core tool; charging the mounted semi-finished tube with a predetermined force to press the semi-finished tube on a core cross section of the core tool, wherein while charging the mounted semi-finished tube with the force crinkles are formed in longitudinal direction of the semi-finished tube; heating the semi-finished tube to a predetermined forming temperature for a predetermined time period for the production of the plastic foil tube with the intended cross-section and stripping the plastic foil tube which is formed in such a manner and cooled down off the core tool.

Abstract: A measurement method for determining the position of an omega profile component placed on a shell component of an aircraft, in which the ACTUAL position of the omega profile component relative to the shell component is optically acquired in a contactless manner, so as to subsequently compare the latter with a defined DESIRED position, wherein several adjacently spaced apart measuring points are established at two mutually opposing flank sides of the profile cross section of the omega profile component, through which a regression line is run according to the path measurement principle based on coordinates, whose point of intersection is drawn upon to determine the orthogonal position of the omega profile component relative to the shell component.

Abstract: An arrangement for reinforcing a fiber composite component for the aviation and aerospace industry, in which a reinforcing element having a receiving region and a pressure element adapted to the receiving region geometry are provided. The pressure element is inserted into the reinforcing element receiving region. The reinforcing element and the inserted pressure element are fastened relative to one another in a reproducible manner by a reversible fastening device. The fastening device includes a first fastening portion mounted on the pressure element and a second fastening portion which can be mounted on the reinforcing element. The reinforcing element, together with the pressure element fastened thereto, is then applied in a reproducible manner to the fiber composite component cured to connect the reinforcing element to the fiber composite component. The reversible fastening device and the pressure element are then removed from the reinforced fiber composite component.

Abstract: Method for producing a fiber composite component, in particular for aerospace, having the following method steps: forming a moulding core that comprises a predetermined number of hollow bodies for defining an external geometry of the moulding core, the hollow bodies being designed such that they extend in the longitudinal direction of the moulding core and are expandable elastically at least in their lateral direction, and are fixed to one another, the formed moulding core having a flexible outer layer for smoothing the contour of its outer surfaces, and a core sleeve surrounding the moulding core, for sealing the moulding core from the fiber composite component to be produced; placing at least one fiber semi-finished product, at least in places, on the moulding core (that has been formed, in order to shape at least one moulding section of the fiber composite component to be produced; and applying heat and/or pressure to the at least one moulding section in order to produce the fiber composite component.

Abstract: A method for producing an integral reinforced fiber composite component comprising at least one hollow fiber reinforcing component and a shell component is disclosed and can include first providing a mold core having a target cross-section deviating from a round cross-section adaptable to an inner cross-section of the hollow reinforcing component, introducing the mold core into a cavity of the hollow reinforcing component and fixing it thereafter in the cavity with a fixing agent applying the hollow reinforcing component with the mold core fixed therein to the shell component, and subjecting the mold core to a pressurized medium while applying heat and/or pressure to this arrangement to produce the integral reinforced fiber composite component.

Abstract: A measurement method for determining the position of an omega profile component placed on a shell component of an aircraft, in which the ACTUAL position of the omega profile component relative to the shell component is optically acquired in a contactless manner, so as to subsequently compare the latter with a defined DESIRED position, wherein several adjacently spaced apart measuring points are established at two mutually opposing flank sides of the profile cross section of the omega profile component, through which a regression line is run according to the path measurement principle based on coordinates, whose point of intersection is drawn upon to determine the orthogonal position of the omega profile component relative to the shell component.

Abstract: The invention concerns a device for stiffening a flat component, a process for the production of a flat component, in particular a fiber composite component, and a fiber composite component. The device has a portion for producing a space for receiving a mold core for the transmission of a pressure for pressing the flat component and the device. It is characterised by means for positively lockingly and/or frictionally lockingly positioning the mold core in the space of the device. The process according to the invention includes the following steps: introducing the mold core into the portion of the device, positively lockingly and/or frictionally lockingly positioning the mold core in the portion of the device by means of the means, applying the device including the mold core to the non-hardened material layer or layers, pressing the material layers, and hardening the material layer or layers and joining the device to the material layer or layers.

Abstract: Connection devices for a moulding core for producing a fibre composite component are provided. Such a connection device can include a base element for receiving a coupling portion of the moulding core for subjecting the moulding core to a medium, a clamping element for fixing and sealing the coupling portion of the moulding core on the base element, and a locking mechanism for locking the clamping element with respect to the base element and the coupling portion of the moulding core.

Abstract: A method and an arrangement for reinforcing a fibre composite component for the aviation and aerospace industry, in which a reinforcing element having a receiving region and a pressure element adapted to the receiving region geometry. The pressure element is inserted into the reinforcing element receiving region. The reinforcing element and the inserted pressure element are fastened relative to one another in a reproducible manner by a reversible fastening device. The fastening device includes a first fastening portion mounted on the pressure element and a second fastening portion which can be mounted on the reinforcing element. The reinforcing element, with the pressure element, is then applied in a reproducible manner to the fibre composite component to be reinforced, to form a moulding portion. The formed moulding portion is cured to connect the reinforcing element to the fibre composite component. The fastening device and the pressure element are then removed from the fibre composite component.

Abstract: Method for manufacturing a composite fiber component (1) the method comprising the following method steps: forming a moulding core (4) comprising a hollow profile (15) made of segments (16a . . . d) in order to establish an external geometry of the moulding core (4), wherein the segments (16a . . . d) of the moulding core (4) each extend in the direction of the longitudinal axis of the moulding core (4) and are each constructed so as to be pivotable about an axis running in the longitudinal direction of the moulding core (4), between a folded position (A), and an unfolded position (B) of the hollow profile (15) of the moulding core (4), wherein the segments (16a . . . d) are constructed so as to be coupled to one another via connections (18a . . . d, 19a . . .

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.

Abstract: A method and an arrangement for reinforcing a fibre composite component for the aviation and aerospace industry, in which a reinforcing element having a receiving region and a pressure element adapted to the receiving region geometry are provided. The pressure element is inserted into the reinforcing element receiving region. The reinforcing element and the inserted pressure element are fastened relative to one another in a reproducible manner by a reversible fastening device. The fastening device includes a first fastening portion mounted on the pressure element and a second fastening portion which can be mounted on the reinforcing element. The reinforcing element, together with the pressure element fastened thereto, is then applied in a reproducible manner to the fibre composite component to be reinforced, to form a moulding portion. The formed moulding portion is cured to connect the reinforcing element to the fibre composite component.

Abstract: Method for producing a fibre composite component, in particular for aerospace, having the following method steps: forming a moulding core that comprises a predetermined number of hollow bodies for defining an external geometry of the moulding core, the hollow bodies being designed such that they extend in the longitudinal direction of the moulding core and are expandable elastically at least in their lateral direction, and are fixed to one another, the formed moulding core having a flexible outer layer for smoothing the contour of its outer surfaces, and a core sleeve surrounding the moulding core, for sealing the moulding core from the fibre composite component to be produced; placing at least one fibre semi-finished product, at least in places, on the moulding core that has been formed, in order to shape at least one moulding section of the fibre composite component to be produced; and applying heat and/or pressure to the at least one moulding section in order to produce the fibre composite component.

Abstract: The invention relates to a method for producing a plastic foil tube with an intended cross-section that derives from a circular cross-section as a means for the production of fiber compound components for aviation or aerospace. It comprises the following method steps: mounting a semi-finished tube on a core tool; charging the mounted semi-finished tube with a predetermined force to press the semi-finished tube on a core cross section of the core tool, wherein while charging the mounted semi-finished tube with the force crinkles are formed in longitudinal direction of the semi-finished tube; heating the semi-finished tube to a predetermined forming temperature for a predetermined time period for the production of the plastic foil tube with the intended cross-section and stripping the plastic foil tube which is formed in such a manner and cooled down off the core tool.

Abstract: The invention relates to a method for producing an integral, reinforced fibre composite component comprising at least one hollow reinforcing component made of fibre composite material and shell component, comprising the following method steps: providing a mould core formed of a hose having a target cross-section deviating from a round cross-section and is adapted to an inner cross-section of the hollow reinforcing component to be produced, at least in portions, or substantially corresponds with said inner cross-section, at least in portions; introducing the mould core into a cavity in the at least one hollow reinforcing component; fixing the mould core in the at least one hollow reinforcing component using a fixing agent; applying the at least one hollow reinforcing component with the mould core fixed therein to the shell component; and subjecting the mould core to a pressurised medium and applying heat and/or pressure to this arrangement in order to produce the integral, reinforced fibre composite component