公开(公告)号：US09796142B2

公开(公告)日：2017-10-24

申请号：US14706660

申请日：2015-05-07

Applicant: Airbus Operations (S.A.S.)

Inventor： Denis Soula ,  Jérome Colmagro ,  Matthieu Plet

IPC: B29C70/52 ,  B29C35/02 ,  B29D99/00 ,  B29C70/44 ,  B29C70/46 ,  B29C70/54 ,  B29C70/68 ,  B29C70/86 ,  B29C65/00 ,  F16C7/02 ,  B29L31/06

CPC classification number: B29C70/523 ,  B29C35/0277 ,  B29C66/5324 ,  B29C66/5344 ,  B29C66/71 ,  B29C66/721 ,  B29C66/7212 ,  B29C66/72141 ,  B29C66/73754 ,  B29C66/73941 ,  B29C70/446 ,  B29C70/462 ,  B29C70/52 ,  B29C70/545 ,  B29C70/68 ,  B29C70/865 ,  B29D99/0003 ,  B29D99/0046 ,  B29L2031/06 ,  B29L2031/3076 ,  F16C7/026 ,  Y02T50/43 ,  B29K2063/00 ,  B29K2307/04

Abstract: The manufacture of structural elements for aircraft requires the use of complex and costly methods, particularly in the case of parts of elongate overall shape and variable thickness or cross section made of composite material. The disclosure herein proposes to overcome this problem by a method that allows the manufacture of a structural part from a preform made of composite material of simple shape obtained by pultrusion and of one or more reinforcing elements made of composite material and secured by cocuring with the preform to a region of this preform which region is to be reinforced.

公开(公告)号：US20150321429A1

公开(公告)日：2015-11-12

申请号：US14706660

申请日：2015-05-07

Applicant: Airbus Operations (S.A.S.)

Inventor： Denis Soula ,  Jérome Colmagro ,  Matthieu Plet

IPC: B29C70/52

CPC classification number: B29C70/523 ,  B29C35/0277 ,  B29C66/5324 ,  B29C66/5344 ,  B29C66/71 ,  B29C66/721 ,  B29C66/7212 ,  B29C66/72141 ,  B29C66/73754 ,  B29C66/73941 ,  B29C70/446 ,  B29C70/462 ,  B29C70/52 ,  B29C70/545 ,  B29C70/68 ,  B29C70/865 ,  B29D99/0003 ,  B29D99/0046 ,  B29L2031/06 ,  B29L2031/3076 ,  F16C7/026 ,  Y02T50/43 ,  B29K2063/00 ,  B29K2307/04

Abstract: The manufacture of structural elements for aircraft requires the use of complex and costly methods, particularly in the case of parts of elongate overall shape and variable thickness or cross section made of composite material. The disclosure herein proposes to overcome this problem by a method that allows the manufacture of a structural part from a preform made of composite material of simple shape obtained by pultrusion and of one or more reinforcing elements made of composite material and secured by cocuring with the preform to a region of this preform which region is to be reinforced.

Abstract translation: 用于飞机的结构元件的制造需要使用复杂和昂贵的方法，特别是在细长整体形状和可变厚度或由复合材料制成的横截面的部分的情况下。 本文的公开内容旨在通过一种方法来克服这个问题，该方法允许从由拉挤成型获得的简单形状的复合材料制成的预成型件和由复合材料制成的一个或多个增强元件制成的结构部件，并通过与预成型件共同固化而固定 到该预制件的该区域要被加强的区域。

公开(公告)号：US10399663B2

公开(公告)日：2019-09-03

申请号：US15255639

申请日：2016-09-02

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： Denis Soula ,  Matthieu Plet ,  Javier Maqueda Lahoz

IPC: B64C3/18 ,  B64C1/06 ,  B64C1/26 ,  B64C3/22

Abstract: A central wing box for an aircraft, including a top panel, a bottom panel, a front spar, a rear spar, and at least one secondary rib. A secondary rib includes two stiffeners, a first stiffener extending adjacent to the top panel and to one of the front spar and the rear spar, and a second stiffener extending adjacent to the bottom panel and to the other of the front spar and the rear spar. A reduced number of components can be employed, thereby simplifying the construction of the central wing box of an aircraft, particularly the installation of the secondary ribs.