公开(公告)号：US10071507B2

公开(公告)日：2018-09-11

申请号：US14700677

申请日：2015-04-30

Applicant: Airbus Operations S.L.

Inventor： Diego Garcia Martin ,  Pablo Cebolla Garrofe ,  Francisco Javier Chamorro Alonso ,  Felix Dominguez Escauriaza

IPC: B29C33/20 ,  B29C70/34 ,  B29C70/46 ,  B29K105/08 ,  B29K63/00 ,  B29L31/30

CPC classification number: B29C33/202 ,  B29C70/345 ,  B29C70/46 ,  B29K2063/00 ,  B29K2105/0872 ,  B29L2031/3076 ,  Y02T50/43 ,  Y10T428/2419

Abstract: 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.

公开(公告)号：US20180022438A1

公开(公告)日：2018-01-25

申请号：US15645332

申请日：2017-07-10

Applicant: Airbus Operations, S.L.

Inventor： Soledad Crespo Peña ,  Francisco Javier Honorato Ruiz ,  Iker Vélez De Mendizabal Alonso ,  Carlos García Nieto ,  Enrique Guinaldo Fernández ,  Álvaro Torres Salas ,  Pablo Cebolla Garrofe ,  Álvaro Calero Casanova

IPC: B64C3/24 ,  B64C3/18 ,  B64C3/58 ,  B29C45/00 ,  B29D99/00

CPC classification number: B64C3/24 ,  B29C45/0001 ,  B29C45/0005 ,  B29D99/0014 ,  B29K2071/00 ,  B29K2081/04 ,  B29K2307/04 ,  B29K2309/08 ,  B29L2031/3085 ,  B64C3/00 ,  B64C3/18 ,  B64C3/58 ,  B64D37/32 ,  Y02T50/44

Abstract: A tip structure for an aircraft airfoil, such as a control surface (ailerons, flaps, elevators, rudders, etc) and/or a lifting surface (wings, HTP's, VTP's) is a unitary body and includes a tip shell and a metallic material on the outer surface of the tip shell suitable to withstand a lighting strike. The tip shell has been obtained by a single-stage injection molding process using a thermoplastic composite material having fibers dispersed therein, and the metallic material has been integrally formed with the tip shell.

公开(公告)号：US20150314487A1

公开(公告)日：2015-11-05

申请号：US14700677

申请日：2015-04-30

Applicant: Airbus Operations S.L.

Inventor： Diego Garcia Martin ,  Pablo Cebolla Garrofe ,  Francisco Javier Chamorro Alonso ,  Felix DOMINGUEZ ESCAURIAZA

IPC: B29C33/20 ,  B29C70/34

CPC classification number: B29C33/202 ,  B29C70/345 ,  B29C70/46 ,  B29K2063/00 ,  B29K2105/0872 ,  B29L2031/3076 ,  Y02T50/43 ,  Y10T428/2419

Abstract: 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.

Abstract translation: 一种制造飞机复合材料部件的方法，包括以下步骤：在至少模压基座部分和成形模具上部之间放置预成型模具到成型模具中，减少捕获在预浸料坯中的空气，使成型模具上部 部分在垂直于预浸料坯预成型件的平面的方向上抵靠成型模具基座部分，使得成型模具上部部分按压层压表面，直到达到限定上部相对于基部的位置的阻挡装置， 预浸料坯预成型固化部件的标称厚度，其中通过将成型模具的不同部分螺栓连接来实现所述位移，从而为预成型件提供升高的温度以使其固化。