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 pressure bulkhead for an aircraft fuselage having a skin element, with a first surface and a second surface, a circumferential edge and a center axis, and a reinforcement assembly, which has radially disposed reinforcement elements extending along the first surface radially between an outer end at the edge of the skin element and an inner end, which faces the center axis, wherein, in a cross section, which extends radially along the center axis, each of the radially disposed reinforcement elements defines first and second contour lines, each extending from the outer end of the radially disposed reinforcement elements to the inner end thereof, and the reinforcement assembly resting with the first contour lines thereof on the first surface of the skin element. A pressure bulkhead for an aircraft fuselage can efficiently absorb occurring pressure loads.

Abstract: A system for repairing a component made out of a plastic comprises a frame, a multiaxial guide device coupled with the frame, with a tool holder arranged thereon, an optical acquisition device, a processing device, and a plastic deposition device. The frame comprises a mounting device for retaining the frame on a component surface. The optical acquisition device, the processing device and the plastic deposition device are arranged on the tool holder. The optical acquisition device is set up to optically inspect a surface area of the component lying in proximity to the frame from at least one viewing angle, so as to acquire the spatial structure of the surface area. The processing device is set up to remove material of a damaged area from the component for generating a base surface with a desired structure and boundary edges.

Abstract: A mobile application device for dispensing a formed fibre composite strand has: a coupling unit for detachably fastening the application device to the handling device for moving the application device; a preforming unit for continuously forming an unprocessed fibre strand into a formed fibre strand with a formed fibre cross section settable by the preforming unit; an impregnating unit for continuously developing the formed fibre strand into a fibre composite strand by impregnation with a matrix material; and a postforming unit for continuously pressing the fibre composite strand to and through the dispensing unit and having a drive unit and an adjustable dispensing unit for continuously forming a fibre composite strand into a formed fibre composite strand with a dispensing cross section settable by the dispensing unit and for dispensing the same such that the formed fibre cross section is at least 70% congruent with the dispensing cross section.

Abstract: A pressure bulkhead for an aircraft fuselage having a skin element, with a first surface and a second surface, a circumferential edge and a center axis, and a reinforcement assembly, which has radially disposed reinforcement elements extending along the first surface radially between an outer end at the edge of the skin element and an inner end, which faces the center axis, wherein, in a cross section, which extends radially along the center axis, each of the radially disposed reinforcement elements defines first and second contour lines, each extending from the outer end of the radially disposed reinforcement elements to the inner end thereof, and the reinforcement assembly resting with the first contour lines thereof on the first surface of the skin element. A pressure bulkhead for an aircraft fuselage can efficiently absorb occurring pressure loads.

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: The invention relates to methods and to a manufacturing device for manufacturing a sandwich component. A semifinished product arrangement is soaked with a flowable matrix material, for example a resin, in particular by an infusion method. By using the method of the invention, inherent tensile stresses introduced by the respective method and remaining in the sandwich component to be manufactured are reduced, and moreover the risk of crack formation in the course of the process, afterwards and during operation of the sandwich component is minimized.

Abstract: A system for repairing a component made out of a plastic comprises a frame, a multiaxial guide device coupled with the frame, with a tool holder arranged thereon, an optical acquisition device, a processing device, and a plastic deposition device. The frame comprises a mounting device for retaining the frame on a component surface. The optical acquisition device, the processing device and the plastic deposition device are arranged on the tool holder. The optical acquisition device is set up to optically inspect a surface area of the component lying in proximity to the frame from at least one viewing angle, so as to acquire the spatial structure of the surface area. The processing device is set up to remove material of a damaged area from the component for generating a base surface with a desired structure and boundary edges.

Abstract: Structural component including at least one covering shell and a carrier structure, the covering shell designed in the form of a sandwich and formed by an inner skin section, an outer skin section and a shear-load absorbing core layer disposed between the two sections and connecting the inner and the outer skin sections to one another in a planar manner. The carrier structure is formed by at least one panel-shaped connecting part extending between and transversely to the inner and outer skin sections and connected along a reference longitudinal direction to the covering shell. The connecting part is located outside the carrier structure and fastened to the inner skin section resting thereon in a planar manner, wherein at least one profiled support extending along the reference longitudinal direction is provided in the covering shell in order to form a reinforcing section in the connecting region of the panel-shaped connecting part.

Abstract: According to the invention a main-load bearing skin shell for a structural component is provided, wherein the skin shell for being affixed to a support component comprises an outer edge section with an outer edge and comprises: a connection region that does not comprise a core layer, which connection region extends along the edge with the inner skin section and the outer skin section, wherein in an end region of the core layer along the outer edge section of the skin shell reinforcement devices are integrated that project through the shear-force-absorbing core layer.

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: The invention pertains to a planking panel (B) for a structural component (1) that is realized in the form of a sandwich component in its inner region (BI) that extends in a planar fashion and features a first skin section (11), a second skin section (12) and a core section (13) that is situated between these two skin sections, wherein the core section (13) connects the first and the second skin sections (11, 12) to one another in a planar fashion, with the invention being characterized in that a plurality of monitoring lines (14) is provided that extend over a planar section of the core section (13) to be monitored in order to detect damage in the core section (13) and respectively feature a first connection point (15) on a first end (14a) and a second connection point (16) on a second end (16a) in order to apply a monitoring signal (UK), wherein the monitoring lines (14) have a tear strength that lies in the range between 50% and 100% of the tear strength of the core section (13).

Abstract: According to the invention a main-load bearing skin shell for a structural component is provided, wherein the skin shell for being affixed to a support component comprises an outer edge section with an outer edge and comprises: a connection region that does not comprise a core layer, which connection region extends along the edge with the inner skin section and the outer skin section, wherein in an end region of the core layer along the outer edge section of the skin shell reinforcement devices are integrated that project through the shear-force-absorbing core layer.

Abstract: The invention relates to methods and to a manufacturing device for manufacturing a sandwich component. A semifinished product arrangement is soaked with a flowable matrix material, for example a resin, in particular by an infusion method. By using the method of the invention, inherent tensile stresses introduced by the respective method and remaining in the sandwich component to be manufactured are reduced, and moreover the risk of crack formation in the course of the process, afterwards and during operation of the sandwich component is minimized.

Abstract: The present invention relates to an apparatus and a method to activate a binder on a semi-finished fiber material containing carbon fibers or on a preform. The binder is applied to the semi-finished fiber material or the fiber preform and subsequently activated through increasing the temperature by conducting an electrical current through the carbon fibers of the preform.

Abstract: A forming jig includes a grid pattern of support walls arranged on a support base and having upper free ends located along an imaginary curved surface, and modular sectional profile members arranged on the walls to enclose a vacuum chamber within the jig. Grooves, channels and air passages between neighboring profile members communicate into the vacuum chamber. The outer surface of the profile members matches the intended inner surface of a structural component to be fabricated using the jig. In the fabrication process, a film is applied to the outer surface to pre-establish a vacuum, the film is removed while simultaneously a vacuum skin is applied, stringer members are set into the grooves, fiber skin layers are laid up, a sealant is applied around the perimeter, a structural shell is vacuumed onto the skin layers, and then this preformed component is removed from the jig, injected with resin unless the skin layers were pre-impregnated with resin, and cured.

Abstract: A forming jig includes a grid pattern of support walls arranged on a support base and having upper free ends located along an imaginary curved surface, and modular sectional profile members arranged on the walls to enclose a vacuum chamber within the jig. Grooves, channels and air passages between neighboring profile members communicate into the vacuum chamber. The outer surface of the profile members matches the intended inner surface of a structural component to be fabricated using the jig. In the fabrication process, a film is applied to the outer surface to pre-establish a vacuum, the film is removed while simultaneously a vacuum skin is applied, stringer members are set into the grooves, fiber skin layers are laid up, a sealant is applied around the perimeter, a structural shell is vacuumed onto the skin layers, and then this preformed component is removed from the jig, injected with resin unless the skin layers were pre-impregnated with resin, and cured.