Airbus Operations Gmbh

Airbus Deutschland Gmbh

Deutsches Zentrum Fur Luft-Und Raumfahrt E.v.

Fraunhofer-Gesellschaft Zur Foerderung Der Angewandten Forschung E.v.

Deutsches Zentrum Fuer Luft-Und Raumfahrt E.v

Ulrich Eberth

Paul Joern

Paul Jörn

Martin Friedrich

Hans-Martin Krafft

Mario Koeber

The invention relates to a fixing threadfor sewing together reinforcing fibers, in particular to form a fiber preform, for the production of a fiber-reinforced composite component by means of impregnation with a curable polymer material. According to the invention, the fixing threadhas an interfacefor locally increasing the ductility of a matrix formed by the curable polymer material and has at least one core thread, so as in particular to reduce the tendency for microcracks to form in the matrix of the finished composite component in the regions where the fixing threadspenetrate. The interfacemay be formed, for example, by an enclosure of the core threadby a thermoplastic polymer material, for example by polyethylene, polypropylene or the like.

Fixing thread for sewing together reinforcing fibers

This application describes a tool, an arrangement, and a method of manufacturing a component. The manufacturing of the component is achieved by a resin transfer from a storage chamber via a transfer line into a working chamber. Before the resin transfer, taking place, for example by a compressed air charging of the storage chamber, the storage chamber is filled with an amount of resin adjusted to the size of the component. Furthermore, a semi-finished product, consisting of cut-to-size reinforcement fibers, is inserted into the working chamber that is adjusted to the form of the component to be produced. Storage chamber, transfer line, and working chamber are configured in a one-piece mould casing of the tool. The application further describes a component manufactured by the above-mentioned tool or by the above-mentioned method respectively.

Resin-transfer-moulding method

A tool for a resin transfer molding method comprises a cavity, a resin trap and a transition region, wherein the cavity is designed such that a component can be accommodated in it. Furthermore, the resin trap is integrated in the tool, and the transition region is designed such that with it a connection between the cavity and the resin trap can be established.

Tool for a resin transfer moulding method

Disclosed is a method for producing single- or multi-layered fiber preforms by the TFP process with fiber strands which are aligned in particular such that they are oriented with the flux of force, wherein the fiber preforms 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 fiber strands on a flexible and elastic base, in particular a base formed by an elastomer, with a fixing thread led through a sewing head to form the fiber perform; and lifting the fiber preform off the elastic and flexible base. The fiber preforms produced by means of this method have a virtually optimum fiber alignment, that is to say substantially oriented with the flux of force, and no appreciable flaws in the arrangement of fibers, and consequently make it possible to create composite components that can withstand extreme mechanical stress and are at the same time lightweight, for example by subsequent processing in the RTM process.

Method for producing single-or multi-layered fiber preforms by the TFP process

A window replacement for filling a window frame in an aircraft is provided, in particular a passenger aircraft, the window replacement being fixable by a retainer in the window frame in place of the window assembly when the window assembly is removed. The window replacement includes a panel-shaped element with at least a single curvature, the panel-shaped element being made of a synthetic material. The window replacement is formed by a monolithic panel-shaped element. The panel-shaped element of the window replacement may also be formed by a sandwich panel. This allows a weight reduction in comparison with a window replacement of a metallic material.

Window replacement for filling a window frame

A window replacement for filling a window frame in an aircraft is provided, in particular a passenger aircraft, the window replacement being fixable by a retainer in the window frame in place of the window assembly when the window assembly is removed. The window replacement comprises a panel-shaped element with at least a single curvature, the panel-shaped element being made of a synthetic material. The window replacement is formed by a monolithic panel-shaped element. The panel-shaped element of the window replacement may also be formed by a sandwich panel. This allows a weight reduction in comparison with a window replacement of a metallic material.

The present invention relates to a method and a device for placing at least one material layer onto a relief mold for producing a composite material. Thereby, an elastically-reversibly deformable body with a surface relief that is designed to correspond to the relief mold is pressed against the material layer, as a result of which the surface of said body is deformed, and the material layer can be picked up. As a result of its elastically-reversible characteristics the body subsequently deforms back to its initial state so that the material layer can easily be placed onto the relief mold.

Method and device for placing thin material layers onto a relief mould

A method for producing single- or multi-layered fiber preforms by the TFP process with fiber strands, aligned substantially to be oriented with the flux of force, laid on a backing layer and attached by fixing threads, to form a fiber preform with a desired material thickness and without a 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. Subsequently the backing layer, separated from the fiber preform by the release layer, is detached from the fiber preform. The fiber preforms have a virtually optimum fiber structure without flaws along with a desired material thickness and are predestined for the production of composite components for load-bearing components that must withstand high mechanical loads.

Method for producing single- or multi-layered fiber preforms by the TFP process

A docking system for docking a liquid stream carrying line to a docking body, includes a line end having a first form that is conically tapered in the direction of flow and a docking interface which is situated on the docking body and has a second form that is conically tapered in the direction of flow. The first conically tapered form and the second conically tapered form are adapted to one another in such a way that, in the docked state, they are mutually set apart in one coupling region by an interspace defined by a sealing ring, concentrically opposing one another. The first conically tapered form is equipped on its periphery with at least one cleaning element, which extends from the first conically tapered form toward the second conically tapered form in order to capture liquid that may accumulate in the interspace.

Docking and undocking of liquid carrying lines to and from a docking body

A guiding device for a device for producing fibre preforms by the TFP process, the guiding device guiding the fibre strand. The guiding device has an opening with a variable cross-section for leading through the fibre strand, wherein the guiding device is fitted in the region of a sewing head of the TFP process device. The width of the fibre strands 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. An open-loop and closed-loop control device undertakes the path control of the sewing head and the control of the variation of the cross-sectional geometry of the guiding device. Existing devices for producing fibre preforms for composite components by the TFP process can be retrofitted with the guiding device.

Guiding device for a device for producing fiber preforms by the TFP process for composite components

The present invention relates to a connecting structure for an aircraft or spacecraft, with a structural component and a stringer. The stringer is connected to the structural component by means of connecting regions. In order to reduce stress peaks that result for example from impact in the structural component, a high impact material is introduced into at least one of the connecting regions to provide a local increase in the energy absorbing capacity of the at least one connecting region.

Connecting structure for an aircraft or spacecraft and method for producing the same

Device for producing a fiber preform with virtually any desired surface geometry by a TFP process. A guiding device lays a fiber strand along virtually any desired path curve on a backing layer and a sewing head attaches the fiber strand on the backing layer by at least one fixing thread. 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. 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) provides a relatively simple device construction. Example devices can produce fiber preforms for dome-shaped composite components for use inter alia as pressure bulkheads for cabins in aircraft with virtually optimum properties.

Device for producing a fiber preform with virtually any desired surface geometry by the TFP process

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 TFP 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.

Method for producing single- or multi-layered fiber preforms by the TFP Process as well as a fixing thread and backing layer

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.

Growing community of inventors

Rain, Germany

Ulrich Eberth