Patent application number | Description | Published |
20110115124 | Method For Manufacturing A FRC/FRP- Component From Rovings With A Moulding Tool And Moulding Tool For Implementing The Method - The invention pertains to a method for manufacturing a FRC/FRP-component component from rovings by means of a moulding tool with a mould surface, featuring the steps of: applying rovings formed of dry fibers onto the mould surface by depositing the rovings under tension with predetermined orientations between deflection devices by means of an application device, applying binder material onto the tensioned rovings; consolidating the arrangement of fiber strands and binder material by applying heat and pressure in order to produce a preform for the component to be manufactured; separating the preform from the deflection devices and removing the preform from the moulding tool; and carrying out an injection process or infusion process in order to manufacture the component after separating the preform from the deflection devices; as well as to a moulding tool and a device for implementing the method. | 05-19-2011 |
20110133358 | METHOD AND DEVICE FOR TREATING A SURFACE OF A FIBRE COMPOSITE MATERIAL - The present invention provides a method and a device for treating a surface of a fibre composite material which contains fibres of a specific hardness, the surface of the fibre composite material being removed abrasively by an abrasion means, the hardness of which is less than the hardness of the fibres contained in the fibre composite material and is greater than the hardness of a plastics material in which the fibres of the fibre composite material are embedded. | 06-09-2011 |
20110148007 | PROCESS FOR PRODUCING FIBRE PREFORMS - A process for producing fibre preforms for composite material components makes it possible to directly produce complex geometries in a flexible and low-cost manner by applying a plurality of dry fibre rovings independently of one another even in spatially uneven contours. It is no longer necessary to use cut fabric strips since fibre preforms are produced straight from the dry fibre rovings. This obviates the need to carry out production, transport and order picking processes. It is not necessary to cut fibre strips to size, and therefore a saving may be made on material. In addition, it is possible to increase the mechanical characteristic values in the composite material because it is not necessary to sew fibre webs. The described process can also readily be scaled since the number of dry fibre rovings arranged next to one another make it possible to vary the area which can be covered. | 06-23-2011 |
20110240213 | METHOD AND DEVICE FOR LAYING AND DRAPING PORTIONS OF A REINFORCING FIBER STRUCTURE TO PRODUCE A PROFILED PREFORM - A device for automatically laying and draping a plurality of web-form portions of a dry sheet-like formation, in particular of a multiaxial laid fiber fabric and/or a woven reinforcing fabric to create a profiled preform on a core by repeated laying and draping of the portions in order to produce a reinforcing profile with a composite material. Accordingly at least one portion, is kept in at least one cassette between two roller conveyors ready for laying on the core. As a result of the preferably simultaneous laying of preferably more than one prefabricated portion of the sheet-like formation on the core by means of at least one cassette of the cassette arrangement a profiled preform can be fully automatically laid and draped quickly and with great dimensional accuracy and at the same time with good reproducibility for the production of CRP profiles. | 10-06-2011 |
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 |
20120279662 | APPARATUS FOR THE PRODUCTION OF AN AIRCRAFT FUSELAGE SHELL CONSISTING OF A FIBRE COMPOSITE - An apparatus for the production of a fuselage shell for an aircraft made of fibre composite, which is to be equipped with a plurality of stringers disposed spaced apart for reinforcement, comprising a main frame to form a supporting substructure having an outwardly curved mounting surface for positive mounting, having longitudinal mounting grooves for receiving of formed parts for deformably positioning the stringers relative to the mounting surface, wherein a plurality of short formed parts spaced apart from each other are disposed in each mounting groove, and which are adjustable relative to the corresponding mounting groove in the transverse direction (Y) by means of adjusters, and which can be raised in the vertical direction (Z) by means of lifters for guiding the stringers in the direction of a laminating adhesive bonding unit brought over the mounting surface. | 11-08-2012 |
20130000815 | DEVICE AND METHOD FOR MANUFACTURING A FIBER-REINFORCED COMPOSITE FUSELAGE SHELL FOR AN AIRCRAFT - A device and a method for manufacturing a fiber-reinforced fuselage shell for an aircraft, which fuselage shell for the purpose of reinforcement comprises several stringers that are spaced apart from each other, wherein the device includes a base frame comprising several supporting walls of different lengths for forming a curved mounting surface for the fuselage shell to be manufactured, wherein several actuators that extend radially outwards and that are longitudinally adjustable are affixed to the mounting surface, at the distal ends of which actuators in each case mold channels for receiving the stringers are attached, which mold channels are interconnected by means of flexible intermediate elements and/or further mold channels for forming a vacuum-tight closed mold surface. | 01-03-2013 |
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 |