| Patent application number | Description | Published |
|---|
| 20090050259 | Method for producing single- or multi-layer fiber preforms by the tfp process as well as a backing layer - 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. The fiber preforms formed by this method have a virtually optimum fiber structure without flaws along with virtually any desired material thickness and are predestined for the production of composite components for load-bearing components that have to withstand high mechanical loads. A backing layer for the production of a fiber preform as well as a fiber preform that is formed in accordance with this method are also disclosed. | 02-26-2009 |
| 20090096119 | Method for Producing Single- or Multi-Layered Fiber Preforms by the TFP Process as Well as a Fixing Thread and Backing Layer - 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. | 04-16-2009 |
| 20090229761 | Device for producing a fiber preform with virtually any desired surface geometry by the tfp process - 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. | 09-17-2009 |
| 20090266935 | SHELL ARRANGEMENT AS WELL AS AIRCRAFT OR SPACECRAFT - 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. | 10-29-2009 |
| 20100126652 | METHOD FOR PRODUCING SINGLE-OR MULTI-LAYERED FIBER PREFORMS BY THE TFP PROCESS - The invention relates to a method for producing single- or multi-layered fibre preforms | 05-27-2010 |
| 20100143716 | Fixing thread for sewing together reinforcing fibers - The invention relates to a fixing thread | 06-10-2010 |
| 20110006159 | FUSELAGE OF AN AIRCRAFT OR SPACECRAFT AND CORRESPONDING AIRCRAFT OR SPACECRAFT - The invention relates to a fuselage of an air- or spacecraft. The fuselage comprises at least one shell element and one insulation element. The insulation element is configured as a passive, watertight insulation element and can be mounted on an inner side of the at least one shell element in a completely air- and watertight manner. The invention furthermore relates to a respective aircraft or spacecraft. | 01-13-2011 |
| 20110009042 | FUSELAGE OF AN AIRCRAFT OR SPACECRAFT AND METHOD OF ACTIVELY INSULATING SUCH A FUSELAGE - The present invention relates to a fuselage of an aircraft or spacecraft, with at least one shell element and a structural element. An interspace to which air can be admitted by an air stream is provided between the at least one shell element and the structural element. The fuselage is distinguished by the fact that, to form the air-admitting air stream as an outgoing/incoming air stream of a pressurized interior space of the fuselage, the interspace is connected to a corresponding outgoing/incoming air connection of the interior space. The invention also relates to a corresponding aircraft or spacecraft and to a method of actively insulating such a fuselage. | 01-13-2011 |
| 20110042516 | WINDOW ELEMENT FOR A DOUBLE-SHELL SKIN FIELD OF AN AIRCRAFT FUSELAGE CELL - A window element for a double-shell skin field of an aircraft fuselage cell includes a window frame having a window module disposed in the frame, wherein the frame is disposed in an opening of the double-shell skin field, and wherein the frame is connected to the double-shell skin field by a surrounding embrasure profile positioned against a core structure of the skin field at least in some regions, wherein the core structure includes an inner and an outer covering layer. | 02-24-2011 |
