Abstract: The invention relates to a method for producing single- or multi-layered fibre preforms 1,17 by the TFP process with fibre strands 2-8, 18 which are aligned in particular such that they are oriented with the flux of force, wherein the fibre preforms 1, 17 have virtually any desired material thickness without troublesome backing layers and have virtually any desired surface geometry, comprising the steps of: laying and attaching the fibre strands 2 to 8, 18 on a flexible and elastic base 9, 19, in particular a base 9, 19 formed by an elastomer, with a fixing thread 10, 11 led through a sewing head to form the fibre preform 1, 17 and lifting the fibre preform 1, 17 off the elastic and flexible base 9, 19.

Abstract: The present invention provides a shell arrangement as well as an aircraft or spacecraft comprising such a shell arrangement. The shell arrangement comprises a first lightning conductor layer for conducting lightning energy and a fibre composite layer supporting the first lightning conductor layer. Furthermore, the shell arrangement comprises a first electrical connection for connecting a first electrical component with the first lightning conductor layer. The advantage resulting according to the invention is that the lightning conductor layer fulfils a double function: on the one hand it serves to conduct lightning energy and on the other hand it forms a portion of a circuit for operating the first electrical component. For this reason, the need for electrical wiring in the airplane is reduced, in turn resulting in a weight reduction for the aircraft or spacecraft.

Abstract: Disclosed is a device for producing a fiber preform with virtually any desired surface geometry by the TFP process, wherein a fiber strand can be laid by a guiding device in virtually any desired path curve on a backing layer and the fiber strand can be attached on the backing layer by at least one fixing thread by means of a sewing head. The backing layer can be positioned in an xy direction in relation to the guiding device and the sewing head, wherein the sewing head and/or the guiding device can be positioned in a z direction. As a result of the separation of the positioning capabilities of the backing layer (xy direction) and the guiding device, the sewing head and the lower thread guide (z direction), a relatively simple construction of the device is obtained. By means of the device according to the invention, it is possible, for example, to produce fiber preforms for dome-shaped composite components that are used inter alia as pressure bulkheads for cabins in aircraft with virtually optimum properties.

Abstract: The invention relates to a guiding device 1 for a device for producing fibre preforms by the TFP process for composite components by laying and attaching a fibre strand 3 on a backing layer with virtually any desired path curve, the guiding device 1 serving substantially for guiding the fibre strand 3. According to the invention, the guiding device 1 has a through-opening 2 with a variable cross-sectional geometry for leading through the fibre strand 3, wherein the guiding device 1 can be fitted in the region of a sewing head of the device for carrying out the TFP process. As a result of the variable cross-sectional geometry of the through-opening 2, the width of the fibre strands 3 to be laid and attached can be increased, for example in portions of the path curve with small radii of curvature, so that undesired local thickenings are avoided in these portions of the path curve.

Abstract: Disclosed is a method for producing single- or multi-layered fiber performs by the TFP process with fiber strands which are aligned substantially such that they are oriented with the flux of force, are laid on at least one backing layer and are attached by at least one fixing thread. After completion of the TFT process, at least one fiber preform is introduced into a fixing device to secure the position of the fiber strands and the fixing threads and/or the backing layers are at least partially removed. As a result of the preferably complete removal of the fixing threads and/or the backing layer from the fiber preform, the latter has virtually ideal mechanical, quasi isotropic properties. In a preferred variant, the fixing threads and/or the backing layers are formed by a water-soluble material, so that they can be completely dissolved by water as the solvent and flushed out.

Abstract: Disclosed is a method for producing single- or multi-layered fiber preforms by the TFP process with fiber strands, which are aligned substantially such that they are oriented with the flux of force, are laid on a backing layer and are attached by fixing threads, in order to form a fiber preform with virtually any desired material thickness and without a troublesome backing layer. A release layer is applied at least in certain regions to the backing layer and, after completion of the TFP process, the fiber preform is introduced into a fixing device, in which at least some of the fixing threads are melted by heat being supplied, and subsequently the backing layer, separated from the fiber preform by the release layer, is detached from the fiber preform.

Abstract: A supply system that encompasses a vapor generator, may be used to generate water. The vapor generator is supplied with hydrogen and oxygen, and generates hot water vapor, which may be used for supplying energy and water. For example, using the supply system reduces a take off weight for an aircraft and supply redundancy.

Abstract: A fiber textile semi-finished material is fed directly and reformed onto a carrier and reforming tool, where it is fixed with a binder. The carrier has a contour matching the negative or positive shape of the final required geometry of a preform that is to be fabricated. The reformed semi-finished article fixed with the binder is removed from the carrier to provide the preform. Several preforms of different cross-sectional shapes are joined together, compacted to form a dense component having nearly the required finished contour, impregnated with a matrix system including a curable adhesive resin, and then cured under an elevated temperature and/or pressure. The result is a finished fiber reinforced composite structural element such as an aircraft window frame. This method is carried out on an apparatus including the rotating carrier and reforming tool, which may have a cylindrical and/or annular surface for receiving and reforming the material.

Abstract: This invention relates to a method for the production of a producing a three-dimensional preform from textile starting materials such as fibers, fiber bundles or tapes. The textile starting materials are laid in a plane in a two-dimensional manner, whereby the orientation of the fibers and the geometry of the two-dimensional bonded fabric have been determined from the three-dimensional target form by means of back-calculation. The three-dimensional target form is produced by shaping/draping the two-dimensional bonded fabric.

Abstract: A method of producing a textile preform to be used for making a fiber reinforced plastic composite product involves the following steps. A two- or three-dimensional semi-finished textile material or article is produced by essentially any textile production process, such as weaving, knitting or braiding. A binder is applied to the textile material, which is then subjected to a reforming and/or draping process by being applied onto a carrier and reforming tool having a contour or geometry adapted to that of the desired preform that is to be produced. Thereby, the previously unfixed fibers of the textile material are brought into the desired finished orientation and are then fixed, and the cross-sectional shape of the material is changed. This produces the preform having the desired contour, geometry and fiber orientation. The preform may then be subjected to further processing steps to form the finished composite product.

Abstract: Fabric reinforced structural components having a predetermined configuration are produced by first assembling a plurality of preforms prepared as semifinished fabric products. Each preform has a configuration that approximates a portion or section of the predetermined configuration of the finished product so that an assembly of the several preforms resembles approximately the predetermined configuration. The assembly is then compacted between two tool sections. The compacted assembly is then impregnated with a matrix forming resin which is then cured. The compacting is performed in a molding tool that includes the two tool sections placed in a flexible vacuum bag that is evacuable. When the compaction is completed the plurality of preforms together have the predetermined configuration of the structural component within a permissible configuration tolerance range.

Abstract: A method of producing a textile preform to be used for making a fiber reinforced plastic composite product involves the following steps. A two- or three-dimensional semi-finished textile material or article is produced by essentially any textile production process, such as weaving, knitting or braiding. A binder is applied to the textile material, which is then subjected to a reforming and/or draping process by being applied onto a carrier and reforming tool having a contour or geometry adapted to that of the desired preform that is to be produced. Thereby, the previously unfixed fibers of the textile material are brought into the desired finished orientation and are then fixed, and the cross-sectional shape of the material is changed. This produces the preform having the desired contour, geometry and fiber orientation. The preform may then be subjected to further processing steps to form the finished composite product.

Abstract: A fiber textile semi-finished material is fed directly and reformed onto a carrier and reforming tool, where it is fixed with a binder. The carrier has a contour matching the negative or positive shape of the final required geometry of a preform that is to be fabricated. The reformed semi-finished article fixed with the binder is removed from the carrier to provide the preform. Several preforms of different cross-sectional shapes are joined together, compacted to form a dense component having nearly the required finished contour, impregnated with a matrix system including a curable adhesive resin, and then cured under an elevated temperature and/or pressure. The result is a finished fiber reinforced composite structural element such as an aircraft window frame. This method is carried out on an apparatus including the rotating carrier and reforming tool, which may have a cylindrical and/or annular surface for receiving and reforming the material.