Patent application number | Description | Published |
20090166921 | Method for Manufacturing a Composite Fiber Component for Aerospace - Method for manufacturing a composite fibre component ( | 07-02-2009 |
20090166935 | Method for Producing a Fiber Composite Component for Aerospace - The invention relates to a method and a moulding core for producing a fibre composite component ( | 07-02-2009 |
20100007044 | METHOD FOR PRODUCING A FIBRE COMPOSITE COMPONENT - Disclosed is a moulding core for producing a fibre composite component, in particular a stringer on a base component in aerospace, of a spiral construction, wherein the moulding core is a hollow profile with an outer geometry adapted to the moulding core and with a slit provided in the wall of the hollow profile and extending spirally around its periphery; and wherein the slit hollow profile is provided with positional fixing, wherein the slit extending spirally around the periphery penetrates the wall of the hollow profile with the exception of at least three locations arranged such that they are distributed around the circumference of the wall of the hollow profile. A method for producing a fibre composite component, such as a fibre composite component for aerospace, is also disclosed. | 01-14-2010 |
20100007056 | Clip Integration of Pressure Tube Mold Cores into Hardened Omega-Stringers for the Production of Stiffened Fiber Composite Skin Shells, in particular for Aeronautics and Astronautics - The invention concerns a device for stiffening a flat component, a process for the production of a flat component, in particular a fiber composite component, and a fiber composite component. The device has a portion for producing a space for receiving a mold core for the transmission of a pressure for pressing the flat component and the device. It is characterised by means for positively lockingly and/or frictionally lockingly positioning the mold core in the space of the device. The process according to the invention includes the following steps: introducing the mold core into the portion of the device, positively lockingly and/or frictionally lockingly positioning the mold core in the portion of the device by means of the means, applying the device including the mold core to the non-hardened material layer or layers, pressing the material layers, and hardening the material layer or layers and joining the device to the material layer or layers. | 01-14-2010 |
20100028480 | Connection Device for a Moulding Core for Producing a Fibre Composite Component, in Particular for Aerospace - The present invention relates to a connection device ( | 02-04-2010 |
20100044912 | Method For Producing a Fiber Composite Component For Aviation and Spaceflight - A method for producing a fiber composite component, in particular for aerospace, includes the following method steps: introducing an elastic core sleeve into a prestressing mechanism; expanding the core sleeve that is introduced, for elastic prestressing of the same, by activating the prestressing mechanism; introducing a core body through an opening of the expanded core sleeve; releasing the core sleeve by deactivating the prestressing mechanism, for the snug enclosing of the core body by the core sleeve and thus for the forming of the molding core ( | 02-25-2010 |
20100092708 | Method For Producing A Fibre Composite Component For Aerospace - Method for producing a fibre composite component, in particular for aerospace, having the following method steps: forming a moulding core from a core material with a predetermined narrow melting range in a moulding tool to establish an outer geometry of the moulding core at least partly laying at least one semifinished fibre product on the moulding core that is formed, for the shaping of at least one moulded portion of the fibre composite component to be produced; and multistage exposure of at least the moulded portion to heat and/or pressure to produce the fibre composite component; a corresponding moulding core for producing such a fibre composite component and a corresponding fibre composite component with at least one stringer. | 04-15-2010 |
20100151162 | METHOD FOR PRODUCING AN INTEGRAL, REINFORCED FIBRE COMPOSITE COMPONENT AS WELL AS A HOLLOW FIBRE COMPOSITE COMPONENT - The invention relates to a method for producing an integral, reinforced fibre composite component comprising at least one hollow reinforcing component made of fibre composite material and shell component, comprising the following method steps: providing a mould core formed of a hose having a target cross-section deviating from a round cross-section and is adapted to an inner cross-section of the hollow reinforcing component to be produced, at least in portions, or substantially corresponds with said inner cross-section, at least in portions; introducing the mould core into a cavity in the at least one hollow reinforcing component; fixing the mould core in the at least one hollow reinforcing component using a fixing agent; applying the at least one hollow reinforcing component with the mould core fixed therein to the shell component; and subjecting the mould core to a pressurised medium and applying heat and/or pressure to this arrangement in order to produce the integral, reinforced fibre composite component comprising the at least one hollow reinforcing component and the shell component. The invention also relates to an integral, reinforced fibre composite component, a method for producing a hollow fibre composite component and a hollow fibre composite component. | 06-17-2010 |
20100151169 | METHOD FOR PRODUCING A PLASTIC FOIL TUBE AND A RELATED PLASTIC FOIL TUBE - The invention relates to a method for producing a plastic foil tube with an intended cross-section that derives from a circular cross-section as a means for the production of fiber compound components for aviation or aerospace. It comprises the following method steps: mounting a semi-finished tube on a core tool; charging the mounted semi-finished tube with a predetermined force to press the semi-finished tube on a core cross section of the core tool, wherein while charging the mounted semi-finished tube with the force crinkles are formed in longitudinal direction of the semi-finished tube; heating the semi-finished tube to a predetermined forming temperature for a predetermined time period for the production of the plastic foil tube with the intended cross-section and stripping the plastic foil tube which is formed in such a manner and cooled down off the core tool. | 06-17-2010 |
20110076461 | Method for producing a fibre composite component for aviation and spaceflight - Method for producing a fibre composite component, in particular for aerospace, having the following method steps: forming a moulding core that comprises a predetermined number of hollow bodies for defining an external geometry of the moulding core, the hollow bodies being designed such that they extend in the longitudinal direction of the moulding core and are expandable elastically at least in their lateral direction, and are fixed to one another, the formed moulding core having a flexible outer layer for smoothing the contour of its outer surfaces, and a core sleeve surrounding the moulding core, for sealing the moulding core from the fibre composite component to be produced; placing at least one fibre semi-finished product, at least in places, on the moulding core that has been formed, in order to shape at least one moulding section of the fibre composite component to be produced; and applying heat and/or pressure to the at least one moulding section in order to produce the fibre composite component. | 03-31-2011 |
20120222800 | METHOD FOR REINFORCING A FIBER COMPOSITE COMONENT AND ARRANGEMENT FOR PRODUCING A REINFORCED FIBER COMPOSITE COMPONENT - A method and an arrangement for reinforcing a fibre composite component for the aviation and aerospace industry, in which a reinforcing element having a receiving region and a pressure element adapted to the receiving region geometry are provided. The pressure element is inserted into the reinforcing element receiving region. The reinforcing element and the inserted pressure element are fastened relative to one another in a reproducible manner by a reversible fastening device. The fastening device includes a first fastening portion mounted on the pressure element and a second fastening portion which can be mounted on the reinforcing element. The reinforcing element, together with the pressure element fastened thereto, is then applied in a reproducible manner to the fibre composite component to be reinforced, to form a moulding portion. The formed moulding portion is cured to connect the reinforcing element to the fibre composite component. The reversible fastening device and the pressure element are then removed from the reinforced fibre composite component. | 09-06-2012 |
20130037215 | DEVICE FOR THE MASTER MOULDING TECHNIQUE PRODUCTION OF AN INTEGRAL STRUCTURAL COMPONENT MADE OF A FIBRE COMPOSITE MATERIAL REINFORCED BY STRINGERS FOR AN AIRCRAFT - A device for the master moulding technique production of an integral structural component made of a fibre composite for an aircraft that is reinforced by stringers includes at least one moulded part forming a mounting surface to create an exterior or interior surface of the structural component, onto which at least one channel for evacuation of the structural component covered by a vacuum film is arranged, with the structural component comprising a skin-like laminate and a plurality of stringers which are disposed spaced apart from one another, wherein at least surface sections between adjacent stringers are covered with an auxiliary stripe, which comprises a textile ventilation fleece which rests on a vacuum film, and a pre-assembled release film firmly connected therewith, the width (B | 02-14-2013 |
20130240126 | METHOD FOR REINFORCING A FIBER COMPOSITE COMPONENT AND ARRANGEMENT FOR PRODUCING A REINFORCED FIBER COMPOSITE COMPONENT - A method and an arrangement for reinforcing a fibre composite component for the aviation and aerospace industry, in which a reinforcing element having a receiving region and a pressure element adapted to the receiving region geometry. The pressure element is inserted into the reinforcing element receiving region. The reinforcing element and the inserted pressure element are fastened relative to one another in a reproducible manner by a reversible fastening device. The fastening device includes a first fastening portion mounted on the pressure element and a second fastening portion which can be mounted on the reinforcing element. The reinforcing element, with the pressure element, is then applied in a reproducible manner to the fibre composite component to be reinforced, to form a moulding portion. The formed moulding portion is cured to connect the reinforcing element to the fibre composite component. The fastening device and the pressure element are then removed from the fibre composite component. | 09-19-2013 |
20140188429 | MEASUREMENT METHOD AND DEVICE FOR DETERMINING THE POSITION OF A PROFILE COMPONENT APPLIED TO A SHELL COMPONENT - A measurement method for determining the position of an omega profile component placed on a shell component of an aircraft, in which the ACTUAL position of the omega profile component relative to the shell component is optically acquired in a contactless manner, so as to subsequently compare the latter with a defined DESIRED position, wherein several adjacently spaced apart measuring points are established at two mutually opposing flank sides of the profile cross section of the omega profile component, through which a regression line is run according to the path measurement principle based on coordinates, whose point of intersection is drawn upon to determine the orthogonal position of the omega profile component relative to the shell component. | 07-03-2014 |