Patent application number | Description | Published |
20100252179 | Device And Method For Draping And Pre-Shaping Curved Profiled Structural Components Of Fiber Materials | 10-07-2010 |
20100316857 | Reinforcing Material for the Local Reinforcement of a Component Formed With a Composite Material, and Method - Disclosed is a reinforcing material for the local reinforcement of a component formed with a composite material, in particular in areas of force introduction and/or connecting areas. The reinforcing material is formed by a metallic sheet-like formation, the metallic sheet-like formation having a surface with increased roughness to improve adhesion and a coating applied to the surface to provide a seal and improve the bond with the composite material. As a result of the presence of a coating on the metallic sheet-like formation, once it has been rolled up on supply rolls, said sheet-like formation can be drawn off from the supply rolls and at the same time processed in an automated manner by means of known computer-controlled laying devices with CRP prepreg materials in web form by laying layer by layer to produce components, in particular of large format, for aircraft. The reinforcing material thereby ensures a high embedding strength in the case of introduced boreholes or the like, in particular in areas of force introduction and/or connecting areas. Also disclosed is a method for producing a reinforcing material. In addition, the invention relates to a method for producing components, in particular components of large format for aircraft, with the composite material and with the reinforcing material. | 12-16-2010 |
20110206942 | Connections Between a Monolithic Metal Component and a Continuous-Fiber Reinforced Laminate Component, and Method for Production of the Same - A connection is between a monolithic metal component and a continuous-fiber reinforced laminate component wherein the metal component and the laminate component are joined at the ends thereof. A method allows for the production of the connection between the monolithic metal component and the continuous-fiber reinforced laminate component. | 08-25-2011 |
20120020801 | STRUCTURAL ELEMENT FOR AN AIRCRAFT OR SPACECRAFT AND METHOD FOR PRODUCING SUCH A STRUCTURAL ELEMENT - The present invention provides a structural element, in particular for an aircraft or spacecraft, comprising a core, the material density of which varies, at least in portions, in order to optimise the natural vibration behaviour of the structural element. The present invention further provides a method for producing a structural element, in particular for an aircraft or spacecraft, comprising the following steps: providing a structural element which has a core; determining the natural vibration behaviour of the structural element; and varying the material density of the core of the structural element, at least in portions, in such a way that the natural vibration behaviour of the structural element is optimised. The present invention provides still further an aircraft or spacecraft and a rotor blade, in particular for a wind turbine, comprising such a structural element. | 01-26-2012 |
20120090768 | APPARATUS AND METHOD FOR DRAPING KNITTED FIBER FABRICS FOR CURVED PROFILED STRUCTURAL PARTS OF FIBER COMPOSITE MATERIAL - An apparatus for draping knitted fiber fabrics for curved profiled structural parts of fiber composite material includes a mold having a mold surface that corresponds to a portion of the desired profile geometry and curvature of the profiled structural part, a clamping device for tensioning a layer of a knitted fiber fabric along a tensioning line in a prestressed state, and a movement device for producing a relative movement between the mold and the clamped-in fabric layer such that the mold surface moves close to the fabric layer in a direction perpendicular to the tensioning line and, in the further course of the relative movement, pushes through the tensioning line such that the fabric layer completely covers the mold surface. The clamping device is equipped to load the fabric layer during the entire draping operation with a tensile force acting along the tensioning line. | 04-19-2012 |
20120217382 | APPARATUS AND METHOD FOR PRODUCING A COMPONENT AND AIRCRAFT STRUCTURE COMPONENT - An apparatus for producing a component includes a material storage tank for receiving a liquid material (M), a moulding tool in which a filling region to be filled with material (M) from the material storage tank is formed, and a material supply line which connects the material storage tank to the filling region of the moulding tool. In the region of the material supply line and/or the filling region of the moulding tool an optical fibre has been arranged, into which at least one Fibre Bragg Grating sensor for detecting a parameter that is characteristic of the flow of material through the material supply line and/or the filling region of the moulding tool is integrated. | 08-30-2012 |
20130069286 | INFUSION METHOD AND A SYSTEM FOR AN INFUSION METHOD - Disclosed is an infusion method for the manufacture of a fibre-reinforced composite component with semi-finished textile products in an open moulding tool, in which at least one local gas reception space is designed for the reception of volatile substances, such as resin gases and residual air contained in the matrix material and/or in the system, which gas reception space is blocked off from the matrix material by a local semi-permeable membrane; also disclosed is a system for the execution of such a method. | 03-21-2013 |
20130099426 | INFUSION METHOD AND FLOW AID - Disclosed is an infusion method for the manufacture of a fibre-reinforced composite component with a flow promoter | 04-25-2013 |
20130306794 | AIRCRAFT STRUCTURAL ASSEMBLY - An aircraft structural assembly includes an area element which has a core and an outer layer. A first surface of the area element is convexly curved, at least in certain sections, relative to an imaginary central area of the area element extending through the core of the area element. By contrast, a second surface of the area element located opposite the first surface is oriented, at least in certain sections, parallel to the imaginary central area of the area element extending through the core of the area element. The area element is configured in the form of a floor panel of a floor system. The first or the second surface of the area element is designed to form a walkable floor surface of the floor system in the state of the aircraft structural assembly when mounted in an aircraft. | 11-21-2013 |
20140084508 | METHOD AND DEVICE FOR PRODUCING A FIBRE COMPOSITE COMPONENT - The present invention provides a method for producing a fibre composite component, comprising: arranging a first and a second mould in relation to one another in such a way that these together form a first cavity; laying a fibre material on the first and/or second mould; filling the formed first cavity with a casting material and solidifying said casting material in order to seal the first and the second mould to one another and/or interconnect them; and infiltrating the fibre material with a matrix and curing said matrix to form the fibre composite component. | 03-27-2014 |