Abstract: A fuselage component for an aircraft, including a shell part composed of a fiber composite material and a stiffening structure which is connected to an inner surface of the shell part and has shaped parts composed of a fiber composite material, wherein the shaped parts each have a flat base section which extends along the inner surface of the shell part, and a step-shaped profile edge which extends in an encircling manner around the base section. The shaped parts are arranged in the form of parquetry with overlapping profile edges. As a result, the overlapping profile edges form stiffening profiles intersecting at an intersection. Furthermore, an aircraft which has at least one such fuselage component and a method for producing a fuselage component are described.

Abstract: An apparatus for thermally joining thermoplastic fiber composite components includes a pressurization arrangement for jointly covering, at least in a region of a joining zone, thermoplastic fiber composite components to be joined and applying pressure to the thermoplastic fiber composite components to press the thermoplastic fiber composite components against one another, at least in the joining zone, the pressurization arrangement being flexible, at least in some section or sections. A welding device is configured for welding the fiber composite components in the joining zone during pressurization. The pressurization arrangement and welding device are configured to weld the thermoplastic fiber composite components in a pressurized state in the joining zone. The pressurization arrangement is configured to maintain pressurization independently of the welding device until the joining zone solidifies.

Abstract: A method for thermally joining thermoplastic fiber composite components, including jointly covering thermoplastic fiber composite components to be joined, at least in the region of a joining zone, with a pressurization arrangement, which is flexible, at least in some section or sections, and extensive pressurization of thermoplastic fiber composite components to be joined by the pressurization arrangement, with the result that the fiber composite components are pressed against one another, at least in the joining zone. The fiber composite components are welded in the joining zone during pressurization. The pressurization is maintained by the pressurization arrangement until the joining zone solidifies. A cover is also disclosed, in particular a mold or diaphragm, for a pressurization device for thermally joining thermoplastic fiber composite components, and an apparatus for thermally joining thermoplastic fiber composite components.

Abstract: Methods of manufacturing a structural component each include providing a preformed layered structure including a plurality of layers each having reinforcing fibers embedded in a thermoplastic matrix material, heating the layered structure in a cavity formed between a contour surface and an abutment member to a first temperature, which is greater than a melting point of the thermoplastic matrix material, and cooling the layer structure in the cavity to a solidification temperature which is, e.g., less than the melting point of the thermoplastic matrix material, while applying a compression pressure. According to a method, the compression pressure is generated by using a magnet device to generate a magnetic field directed transversely to the contour surface, which pulls or compresses the abutment member and the contour surface relative to each other. According to a further method, inductive heating of the cavity occurs.

Abstract: A method for producing a fibrous preform includes placing a fibrous mat onto a depositing surface, the depositing surface being formed by a web face of a mold core, a first support surface of a first support installation and a second support surface of a second support installation. The fibrous mat is covered by a film and is pressed in a planar manner onto the depositing surface by generating a vacuum. Bringing to bear the fibrous mat on lateral faces of the mold core that extend transversely to the web face is subsequently performed by moving the support installations and the mold core relative to one another in such a manner that a level differential between the web face of the mold core and the support surfaces of the support installations is enlarged. A device for producing a fibrous preform is furthermore described.

Abstract: A device for producing a curved fiber preform from a bi- or multidirectional fiber semi-finished product, in particular for an aircraft or spacecraft fuselage component has first lamellae and second lamellae formed to be couplable to one another criss-cross such that they are positioned on a shared plane and thus form a grid. The lamellae at least in part are formed resiliently bendable about an axis intersecting the shared plane such that a local orientation of the lamellae in the grid changes. An adhesion device or structure is formed for temporarily adhering the fiber semi-finished product and is configured such that the local fiber orientation of the fiber semi-finished product also changes accordingly when the lamellae bend.

Abstract: A semi-finished product for the manufacture of a structural component has a plurality of prepreg tapes, each having unidirectionally arranged reinforcing fibers embedded in a thermoplastic matrix material, and with a plurality of connecting strands containing a thermoplastic material. The prepreg tapes and the connecting strands are either joined to form a textile sheet structure or the prepreg tapes are arranged to form a multiaxial fabric, individual layers of the fabric being joined by the connecting strands. Further, a method for manufacturing a curved structural component from such a semi-finished product is described.

Abstract: An adhesive film and arrangement and method for verifying an adhesive attachment. A mechanical strength of adhesive film structure is matched to a target binding force of a bond produced using the film where when the film is pulled from the substrate or a material layer with peeling stress on the bond for verification of adhesive attachment, the film fails with exceedance of the mechanical strength of the structure when the strength of the bond attains or exceeds the target binding force, and the adhesive film when pulled apart does not fail when bond strength does not attain target binding force. An arrangement is disclosed for verification of adhesive attachment, having a substrate, a component bonded to the substrate by an adhesive film, and at least one test section. The test section is formed by projection of the film across an edge of the component bonded to the substrate, the projection being bonded to regions of the substrate.

Abstract: A fuselage component for an aircraft, including a shell part composed of a fiber composite material and a stiffening structure which is connected to an inner surface of the shell part and has shaped parts composed of a fiber composite material, wherein the shaped parts each have a flat base section which extends along the inner surface of the shell part, and a step-shaped profile edge which extends in an encircling manner around the base section. The shaped parts are arranged in the form of parquetry with overlapping profile edges. As a result, the overlapping profile edges form stiffening profiles intersecting at an intersection. Furthermore, an aircraft which has at least one such fuselage component and a method for producing a fuselage component are described.

Abstract: A semi-finished textile for producing a fiber composite component part has a textile structure and a fixation structure so as to provide a semi-finished textile that can be easily handled and that is suitable for use in complex component part shapes. The textile structure includes a first multitude of reinforcement-fiber bundles of high-performance fibers. Displacement sections are formed between adjacent reinforcement-fiber bundles and adjacent reinforcement-fiber bundles can be displaced against each other. The fixation structure fixates the reinforcement-fiber bundles, depending on the textile structure, with a fixation pattern in such a way that the reinforcement-fiber bundles are fixated at least partially and the displacement sections remain at least partially free.

Abstract: A method for thermally joining thermoplastic fiber composite components, including jointly covering thermoplastic fiber composite components to be joined, at least in the region of a joining zone, with a pressurization arrangement, which is flexible, at least in some section or sections, and extensive pressurization of thermoplastic fiber composite components to be joined by the pressurization arrangement, with the result that the fiber composite components are pressed against one another, at least in the joining zone. The fiber composite components are welded in the joining zone during pressurization. The pressurization is maintained by the pressurization arrangement until the joining zone solidifies. A cover is also disclosed, in particular a mold or diaphragm, for a pressurization device for thermally joining thermoplastic fiber composite components, and an apparatus for thermally joining thermoplastic fiber composite components.

Abstract: A methods for producing a fibrous preform includes placing a fibrous mat onto a depositing surface, the depositing surface being formed by a web face of a mould core, a first support surface of a first support installation and a second support surface of a second support installation. The fibrous mat is covered by a film and is pressed in a planar manner onto the depositing surface by generating a vacuum. Bringing to bear the fibrous mat on lateral faces of the mould core that extend transversely to the web face is subsequently performed by moving the support installations and the mould core relative to one another in such a manner that a level differential between the web face of the mould core and the support surfaces of the support installations is enlarged. A device for producing a fibrous preform is furthermore described.

Abstract: A semi-finished textile for producing a fiber composite component part has a textile structure and a fixation structure so as to provide a semi-finished textile that can be easily handled and that is suitable for use in complex component part shapes. The textile structure includes a first multitude of reinforcement-fiber bundles of high-performance fibers. Displacement sections are formed between adjacent reinforcement-fiber bundles and adjacent reinforcement-fiber bundles can be displaced against each other. The fixation structure fixates the reinforcement-fiber bundles, depending on the textile structure, with a fixation pattern in such a way that the reinforcement-fiber bundles are fixated at least partially and the displacement sections remain at least partially free.

Abstract: An adhesive film and arrangement and method for verifying an adhesive attachment. A mechanical strength of adhesive film structure is matched to a target binding force of a bond produced using the film where when the film is pulled from the substrate or a material layer with peeling stress on the bond for verification of adhesive attachment, the film fails with exceedance of the mechanical strength of the structure when the strength of the bond attains or exceeds the target binding force, and the adhesive film when pulled apart does not fail when bond strength does not attain target binding force. An arrangement is disclosed for verification of adhesive attachment, having a substrate, a component bonded to the substrate by an adhesive film, and at least one test section. The test section is formed by projection of the film across an edge of the component bonded to the substrate, the projection being bonded to regions of the substrate.

Abstract: A semi-finished textile for producing a fiber composite component part has a textile structure and a fixation structure so as to provide a semi-finished textile that can be easily handled and that is suitable for use in complex component part shapes. The textile structure includes a first multitude of reinforcement-fiber bundles of high-performance fibers. Displacement sections are formed between adjacent reinforcement-fiber bundles and adjacent reinforcement-fiber bundles can be displaced against each other. The fixation structure fixates the reinforcement-fiber bundles, depending on the textile structure, with a fixation pattern in such a way that the reinforcement-fiber bundles are fixated at least partially and the displacement sections remain at least partially free.

Abstract: A device for producing a curved fiber preform from a bi- or multidirectional fiber semi-finished product, in particular for an aircraft or spacecraft fuselage component has first lamellae and second lamellae formed to be couplable to one another criss-cross such that they are positioned on a shared plane and thus form a grid. The lamellae at least in part are formed resiliently bendable about an axis intersecting the shared plane such that a local orientation of the lamellae in the grid changes. An adhesion device or structure is formed for temporarily adhering the fiber semi-finished product and is configured such that the local fiber orientation of the fiber semi-finished product also changes accordingly when the lamellae bend.

Abstract: A device for shaping a workpiece is provided. The device includes at least one first and one second component between which the workpiece to be shaped can be molded under the effect of heat. The design and/or the material properties of the first and/or the second component are selected such that the component's thermal expansion is different in different directions.

Abstract: A method for stabilizing a honeycomb core for a sandwich-type structural component includes configuring the honeycomb core. A hardenable adhesive layer is applied to at least one exterior surface of the honeycomb core. A semi-permeable membrane is positioned on the at least one exterior surface. The membrane is gas-permeable and liquid-impermeable. Air in the honeycomb core is drawn off through the semi-permeable membrane. The adhesive layer is hardened.

Abstract: A method for stabilising a honeycomb core for a sandwich-type structural component includes configuring the honeycomb core. A hardenable adhesive layer is applied to at least one exterior surface of the honeycomb core. A semi-permeable membrane is positioned on the at least one exterior surface. The membrane is gas-permeable and liquid-impermeable. Air in the honeycomb core is drawn off through the semi-permeable membrane. The adhesive layer is hardened.

Abstract: A method for preforming a textile semi-finished product, including arranging a textile having at least two layers of fibers, interwoven fibers and/or fiber bundles that are at least in part arranged on top of each other. The method also includes; fixing-in-position of the fibers of the textile against each other and then cutting-to-size of the textile. The fixing-in-position of the textile involves irradiating via a laser beam in order for the melt-on binder of the textile to be melted on only in a localized fashion and not evaporated. The fixing-in-position occurs along a fix-in-position line, the cutting-to-size occurs along a cut-to-size line, and the fix-in-position line is located at a distance relative to the cut-to-size line that is so small that any fraying of the textile is reduced or suppressed altogether.