Patent application number | Description | Published |
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 |
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 |
20130224443 | REINFORCEMENT DEVICE FOR THE PURPOSE OF REINFORCING A MAIN LOAD-BEARING COVERING PANEL AND MAIN LOAD-BEARING COVERING PANEL - The invention concerns a reinforcement device for the purpose of reinforcing a main load-bearing covering panel, also a corresponding main load-bearing covering panel, a structural component of a flow body, and also a corresponding flow body. Here the reinforcement device serves the purpose of accommodating and transferring forces and/or stresses in the interior of the covering panel. In accordance with the present invention, in addition to forces and/or stress in the normal direction, forces and/or stresses in a crosswise direction, that is to say, for example, transverse stresses and/or shear stresses, can also be accommodated and transferred. | 08-29-2013 |
20130266756 | MAIN-LOAD-BEARING PLANKING SHELL AND STRUCTURAL COMPONENT AND FLOW BODY COMPRISING SUCH A MAIN-LOAD-BEARING PLANKING SHELL - According to the invention a main-load bearing skin shell for a structural component is provided, wherein the skin shell for being affixed to a support component comprises an outer edge section with an outer edge and comprises: a connection region that does not comprise a core layer, which connection region extends along the edge with the inner skin section and the outer skin section, wherein in an end region of the core layer along the outer edge section of the skin shell reinforcement devices are integrated that project through the shear-force-absorbing core layer. | 10-10-2013 |
20130273301 | LINING SHELL CARRYING A MAIN LOAD AND STRUCTURAL COMPONENT HAVING AT LEAST ONE LINING SHELL CARRYING A MAIN LOAD - The invention relates to a structural component ( | 10-17-2013 |
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 |
20140000381 | PLANKING PANEL FOR A STRUCTURAL COMPONENT, FLOW BODY COMPRISING SUCH A PLANKING PANEL AND DEVICE FOR MONITORING MATERIAL DAMAGE ON SUCH A PLANKING PANEL | 01-02-2014 |
20140050884 | STRUCTURAL COMPONENT COMPRISING AT LEAST ONE MAIN-LOAD-BEARING COVERING SHELL AND A CARRIER STRUCTURE FOR FIXING THE MAIN-LOAD-BEARING COVERING SHELL, AND FLOW BODY COMPRISING SUCH A STRUCTURAL COMPONENT - Structural component including at least one covering shell and a carrier structure, the covering shell designed in the form of a sandwich and formed by an inner skin section, an outer skin section and a shear-load absorbing core layer disposed between the two sections and connecting the inner and the outer skin sections to one another in a planar manner. The carrier structure is formed by at least one panel-shaped connecting part extending between and transversely to the inner and outer skin sections and connected along a reference longitudinal direction to the covering shell. The connecting part is located outside the carrier structure and fastened to the inner skin section resting thereon in a planar manner, wherein at least one profiled support extending along the reference longitudinal direction is provided in the covering shell in order to form a reinforcing section in the connecting region of the panel-shaped connecting part. | 02-20-2014 |
20140054419 | PRESSURIZED AIRPLANE FUSELAGE, COMPRISING A PRESSURE BULKHEAD - A pressurized aircraft fuselage includes a pressure bulkhead installed on a fuselage structure, which forms a barrier between an internal pressurized cabin area and an outside area, wherein the edge of the pressure bulkhead is circumferentially attached to the fuselage structure by fastening means, wherein the fastening means include a pair of ring-shaped attachment frames made of an open or hollow profile, which are disposed at each side of the pressure bulkhead respectively, in order to form a clamping connection for the pressure bulkhead towards the fuselage structure. | 02-27-2014 |
20150080499 | Method and system for producing a panel member for an airframe - A method of producing a composite panel member, especially a composite panel member having a foam core sandwich structure for an airframe of an aircraft or spacecraft, including: providing at least one fiber reinforcement layer in a panel molding tool; moving or transferring the molding tool to an infusion station that is pre-heated to an infusion temperature and infusing the fiber reinforcement layer in the molding tool with a polymer resin; moving or transferring the molding tool to a curing station that is pre-heated to a curing temperature and curing the at least one resin-infused fiber reinforcement layer in the molding tool to form a composite panel member; and moving or transferring the molding tool to a cooling station that is provided at a cooling temperature and cooling the composite panel member in the molding tool. | 03-19-2015 |