Patent application number | Description | Published |
20110156305 | METHOD AND DEVICE FOR MANUFACTURING A FIBER COMPOSITE COMPONENT WITH AN INTEGRAL STRUCTURAL DESIGN - A method for manufacturing a fiber composite component having an integral structural design includes positioning a sheet-like fibrous semi-finished product in a mold that defines an outer contour of the fiber composite component. Dimensionally stable fibrous semi-finished products, each having dimensions corresponding to a respective portion of the manufactured fiber composite component, are arranged on the sheet-like fibrous semi-finished product. The dimensionally stable fibrous semi-finished products are stabilized and fixed in place using mold cores. The semi-finished products are resin infiltrated using one of a first or a second gating process so as to form a construct. The first gating process includes gating via the mold cores at a head of each dimensionally stable fibrous semi-finished product and performing extraction in an area of the mold. The second gating process including gating in an area of the mold and performing extraction via the mold cores at the head of each dimensionally stable fibrous semi-finished product. The construct is hardened and demolded by removing the mold cores. | 06-30-2011 |
20110156309 | METHOD AND DEVICE FOR THE MANUFACTURE OF A COMPONENT - A method of manufacturing a component from a composite-fiber-material semifinished product includes providing a forming support having a contour including at least one section corresponding to a surface of the manufactured component. The semifinished product is placed onto the forming support and the semifinished product is formed such that the semifinished product contacts the forming support. Further, a device form manufacturing component includes the forming support having the contour including at least one section corresponding to the surface of the manufacture component. | 06-30-2011 |
20110186683 | METHOD AND A DEVICE FOR THE MANUFACTURE OF A STIFFENING STRUCTURE FOR AN AIRCRAFT FUSELAGE SEGMENT, AND ALSO A STIFFENING STRUCTURE - A method for stiffening a skin field of an aircraft fuselage includes providing a skin field for an aircraft fuselage, manufacturing an integral lattice-shaped stiffening structure including a plurality of longitudinal stiffeners and connecting the stiffening structure to the skin field. The manufacturing can include the use of a tool mold having a plurality of longitudinal recesses configured to form longitudinal stiffeners and a plurality of sunken areas disposed between the longitudinal recess. The sunken areas are configured for forming respective mounts that are configured for connection to circumferential stiffeners. | 08-04-2011 |
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 |
20120055617 | Method for Producing Fuselage Cell Sections for Aircraft with Composite Fibre Materials, and a Device - The invention relates to a production method for producing seamless, integral aircraft fuselage sections. The method comprises the following steps:
| 03-08-2012 |
20120267824 | MANUFACTURING A COMPOSITE COMPONENT - Manufacturing of a composite component, such as a composite component of an aircraft, is provided with a molding tool that includes, but is not limited to a first mold, a second mold and a pressure generator. Between the first mold and the second mold, a membrane is arranged so that between the first mold and the membrane a first region is formed, and between the second mold and the membrane a second region is formed. In the first region, a fibrous mat is arranged. In the second region with the use of the pressure generator | 10-25-2012 |
20130020030 | DEVICE AND METHOD FOR THE PRODUCTION OF MULTI-ARCHED STRUCTURAL COMPONENTS FROM A FIBER COMPOSITE - A device for the production of structural components from a fiber composite material, the components being three-dimensionally arched over a large surface, including a jig having a convex mounting surface having receiving channels for the insertion of structural components, wherein the loaded jig interacts with a laminating bonding device having a corresponding shape for forming the structural component under pressure, wherein the mounting surface includes a plurality of individually elastically deformable mounting shell parts arranged adjacent to each other along at least one longitudinally extending pitch line and attached to a plurality of elastically deformable supporting frame elements extending on the interior of the shell at a right angle to the pitch line, and a plurality of actuators for deforming the mounting surface between an extended position (A) and at least one retracted position (B) to move the jig from the bonding device relative to the receiving channels without undercuts. | 01-24-2013 |
20160076179 | HONEYCOMB STRUCTURE MADE OF A NON-WOVEN MADE OF RECYCLED CARBON FIBERS - A honeycomb structure comprising carbon-fiber non-woven, sandwich structure comprising the said honeycomb structure, and process for the production of the said honeycomb structure. | 03-17-2016 |