Abstract: A system for handling a first component includes: a main-device and a module-device, the module-device having a pressing section arranged to form an outer surface of the module-device, the module-device configured to releasably receive the first component, such that a connection section of the first component is attachable to the pressing section of the module-device. The module-device is releasably connected to a second component, wherein the main-device includes a grabbing unit adapted for releasably connecting the module-device, such that the pressing section is arranged to form a first outer surface section of the main-device, and wherein the main-device includes a connector for connecting to a handling-unit for arranging the main-device at the second component, such that the connection section of the first component, if attached to the pressing section of the module-device, is at least indirectly attachable to a front surface of the second component.

Abstract: A method for producing a smooth aerodynamic surface of an aircraft component is depicted and described. The method includes: provision of an aircraft component with an aerodynamic surface, which has an uneven section, introduction of a liquid or viscous, uncured sealing compound into the uneven section, introduction of a solid, precured sealing body into the uneven section in such a way that the sealing body presses into the sealing compound until the sealing compound at least partially surrounds the sealing body, curing of the sealing compound.

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 smooth aerodynamic surface of an aircraft component is depicted and described. The method includes: provision of an aircraft component with an aerodynamic surface, which has an uneven section, introduction of a liquid or viscous, uncured sealing compound into the uneven section, introduction of a solid, precured sealing body into the uneven section in such a way that the sealing body presses into the sealing compound until the sealing compound at least partially surrounds the sealing body, curing of the sealing compound.

Abstract: A system for handling a first component includes: a main-device and a module-device, the module-device having a pressing section arranged to form an outer surface of the module-device, the module-device configured to releasably receive the first component, such that a connection section of the first component is attachable to the pressing section of the module-device. The module-device is releasably connected to a second component, wherein the main-device includes a grabbing unit adapted for releasably connecting the module-device, such that the pressing section is arranged to form a first outer surface section of the main-device, and wherein the main-device includes a connector for connecting to a handling-unit for arranging the main-device at the second component, such that the connection section of the first component, if attached to the pressing section of the module-device, is at least indirectly attachable to a front surface of the second component.

Abstract: In a device and method for manufacturing preforms of fiber reinforced plastic, in a first step, continuously supplied fiber layers are laterally reshaped in a predetermined manner, and the section that is obtained is curved longitudinally in a specific manner in a second step.

Abstract: An apparatus and method for producing a fiber-reinforced plastics casting (FRP), includes a molding box filled with free flowing molding material, in what a prototype of casting or a textile preform is inserted, forming a mold cavity for infiltration the inserted preform of textile with synthetic resin material in order to form a fiber-reinforced plastics casting (FRP).

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: An apparatus and method for producing a fiber-reinforced plastics casting (FRP), includes a moulding box filled with free flowing moulding material, in what a prototype of casting or a textile preform is inserted, forming a mould cavity for infiltration the inserted preform of textile with synthetic resin material in order to form a fiber-reinforced plastics casting (FRP).

Abstract: A process for producing fiber preforms for composite material components makes it possible to directly produce complex geometries in a flexible and low-cost manner by applying a plurality of dry fiber rovings independently of one another even in spatially uneven contours. It is no longer necessary to use cut fabric strips since fiber preforms are produced straight from the dry fiber rovings. This obviates the need to carry out production, transport and order picking processes. It is not necessary to cut fiber strips to size, and therefore a saving may be made on material. In addition, it is possible to increase the mechanical characteristic values in the composite material because it is not necessary to sew fiber webs. The described process can also readily be scaled since the number of dry fiber rovings arranged next to one another make it possible to vary the area which can be covered.

Abstract: An apparatus for the production of a fuselage shell for an aircraft made of fiber composite, which is to be equipped with a plurality of stringers disposed spaced apart for reinforcement, comprising a main frame to form a supporting substructure having an outwardly curved mounting surface for positive mounting, having longitudinal mounting grooves for receiving of formed parts for deformably positioning the stringers relative to the mounting surface, wherein a plurality of short formed parts spaced apart from each other are disposed in each mounting groove, and which are adjustable relative to the corresponding mounting groove in the transverse direction (Y) by means of adjusters, and which can be raised in the vertical direction (Z) by means of lifters for guiding the stringers in the direction of a laminating adhesive bonding unit brought over the mounting surface.

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: 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: An apparatus for the production of a fuselage shell for an aircraft made of fibre composite, which is to be equipped with a plurality of stringers disposed spaced apart for reinforcement, comprising a main frame to form a supporting substructure having an outwardly curved mounting surface for positive mounting, having longitudinal mounting grooves for receiving of formed parts for deformably positioning the stringers relative to the mounting surface, wherein a plurality of short formed parts spaced apart from each other are disposed in each mounting groove, and which are adjustable relative to the corresponding mounting groove in the transverse direction (Y) by means of adjusters, and which can be raised in the vertical direction (Z) by means of lifters for guiding the stringers in the direction of a laminating adhesive bonding unit brought over the mounting surface.

Abstract: A process for producing fibre preforms for composite material components makes it possible to directly produce complex geometries in a flexible and low-cost manner by applying a plurality of dry fibre rovings independently of one another even in spatially uneven contours. It is no longer necessary to use cut fabric strips since fibre preforms are produced straight from the dry fibre rovings. This obviates the need to carry out production, transport and order picking processes. It is not necessary to cut fibre strips to size, and therefore a saving may be made on material. In addition, it is possible to increase the mechanical characteristic values in the composite material because it is not necessary to sew fibre webs. The described process can also readily be scaled since the number of dry fibre rovings arranged next to one another make it possible to vary the area which can be covered.

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: Method for producing a fibre composite component, in particular for aerospace, having the following method steps: forming a moulding core from a core material with a predetermined narrow melting range in a moulding tool to establish an outer geometry of the moulding core at least partly laying at least one semifinished fibre product on the moulding core that is formed, for the shaping of at least one moulded portion of the fibre composite component to be produced; and multistage exposure of at least the moulded portion to heat and/or pressure to produce the fibre composite component; a corresponding moulding core for producing such a fibre composite component and a corresponding fibre composite component with at least one stringer.

Abstract: The present invention relates to a connection device (1) for a moulding core (10) for producing a fibre composite component (21), in particular for aerospace, comprising: a base element (2) for receiving a coupling portion (26, 26?) of the moulding core (10) for subjecting the moulding core (10) to a medium; a clamping element (3) for fixing and sealing the coupling portion (26, 26?) of the moulding core (10) on the base element (2); and a locking mechanism (5) for locking the clamping element (3) with respect to the base element (2) and the coupling portion (26, 26?) of the moulding core (10).

Abstract: Disclosed is a moulding core for producing a fibre composite component, in particular a stringer on a base component in aerospace, of a spiral construction, wherein the moulding core is a hollow profile with an outer geometry adapted to the moulding core and with a slit provided in the wall of the hollow profile and extending spirally around its periphery; and wherein the slit hollow profile is provided with positional fixing, wherein the slit extending spirally around the periphery penetrates the wall of the hollow profile with the exception of at least three locations arranged such that they are distributed around the circumference of the wall of the hollow profile. A method for producing a fibre composite component, such as a fibre composite component for aerospace, is also disclosed.

Abstract: The invention relates to a method and a moulding core for producing a fibre composite component (34), in particular in aerospace, comprising the following method steps: introducing a core sleeve (9) into a moulding tool (2) for establishing an outer geometry of a moulding 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 moulding core (27); and at least partly laying at least one semifinished fibre product (33a, 33b) on the moulding core (27) that is formed, for the shaping of the fibre composite component (34) to be produced.