Patent application number | Description | Published |
20130101801 | OPTIMIZED STRINGER RUN-OUT ZONES IN AIRCRAFT COMPONENTS - Aircraft component, such as an aircraft wing, that comprises at least one panel ( | 04-25-2013 |
20140352877 | HYBRID TOOL FOR CURING PIECES OF COMPOSITE MATERIAL - A hybrid tool for curing composite structures for aircrafts, such as stringers, torsion boxes, skin panels, wing surfaces, horizontal tail or vertical stabilizers, etc. The hybrid tool comprises a metallic portion and an elastic portion arranged on a surface of the metallic portion. The elastic portion and the metallic portion are permanently joined to each other so that the metallic portion and the elastic portion together define a surface having a shape which copies at least part of a surface of a piece of composite material to be cured. The tool is capable of satisfactorily curing pieces of composite material which have a minimum thickness and/or a very aggressive change of thickness. | 12-04-2014 |
20150064393 | LAMINATE FOR JOINING PARTS, AND METHOD AND SYSTEM FOR JOINING PARTS - A laminate for joining parts of composite material includes a first layer of adhesive material, a second layer of preimpregnated composite material, adjacent to the first layer, and a third layer of adhesive material, adjacent to the second layer. A method for joining at least two parts of composite material with a laminate includes the steps of providing already cured composite material parts, positioning the laminate for joining between two cured parts, and applying pressure and temperature to the whole structure including the at least two parts and the laminate, in such a way that the laminate is cured and the at least two parts are joined together in a resulting structure. | 03-05-2015 |
20150183506 | HIGHLY INTEGRATED INFUSED BOX MADE OF COMPOSITE MATERIAL AND METHOD OF MANUFACTURING - Highly integrated infused box made of composite material with two skins ( | 07-02-2015 |
20150314487 | METHOD AND DEVICE FOR MANUFACTURING A COMPOSITE PART OF AN AIRCRAFT - A method for manufacturing a composite part of an aircraft comprising the steps of placing a prepreg preform in a molding die between at least a molding die base part and a molding die upper part, debulking the air trapped in the prepreg, displacing the molding die upper part against the molding die base part in a direction perpendicular to the plane of the prepreg preform such that the molding die upper part presses the laminated perform until it reaches a blocking arrangement defining the position of the upper part relative to the base part for giving the prepreg preform the nominal thickness of the cured part, wherein said displacement is achieved by bolting the different parts of the molding die against each other, providing an elevated temperature to the preform such that it is cured. | 11-05-2015 |