公开(公告)号：US20160167318A1

公开(公告)日：2016-06-16

申请号：US14970130

申请日：2015-12-15

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Pablo CEBOLLA GARROFE

IPC: B29C70/54 ,  B29C70/30 ,  B29C70/06

CPC classification number: B29C70/545 ,  B25J11/006 ,  B29C37/02 ,  B29C70/06 ,  B29C70/30 ,  B29C2793/009 ,  B29K2307/04 ,  B29L2031/3076

Abstract: A Method for manufacturing of a CFRP part includes laying out one or more pre-preg or composite plies, on a mould comprising a marking tool, forming an uncured laminate with a guiding mark on the uncured laminate using curing the laminate giving the part the final shape with the guiding mark and trimming and/or drilling the CFRP part taking as reference the guiding mark. There are also provided a mould for moulding and curing a CFRP part comprising a marking tool adapted to perform a guiding mark on a fresh CFRP part, and a system for manufacturing of a moulded CFRP part.

Abstract translation: 一种用于制造CFRP部件的方法包括在包括标记工具的模具上布置一个或多个预浸料或复合层，在未固化的层压板上形成具有引导标记的未固化层压板，其中使用该层压板，使部件成为最终 形状具有引导标记，并修剪和/或钻孔CFRP部件作为参考标记。 还提供了一种用于模制和固化CFRP部件的模具，其包括适于在新鲜CFRP部件上执行引导标记的标记工具，以及用于制造模制CFRP部件的系统。

公开(公告)号：US20150343702A1

公开(公告)日：2015-12-03

申请号：US14494012

申请日：2014-09-23

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Diego GARCÍA MARTÍN ,  Carlos ROMÓN BANOGON ,  Pablo CEBOLLA GARROFE ,  Francisco Javier HONORATO RUIZ ,  Aquilino GARCíA GARCíA ,  Francisco Javier CHAMORRO ALONSO ,  Julio NÚÑEZ DELGADO

IPC: B29C65/48 ,  B64C3/18

CPC classification number: B29C65/4805 ,  B29C33/30 ,  B29C33/485 ,  B29D99/0014 ,  B29L2031/3076 ,  B64C3/00 ,  B64C3/18 ,  B64C3/24 ,  B64C5/00 ,  B64F5/10

Abstract: Method for manufacturing a base structure (8) of an aeronautical torsion box (1) for an aircraft (11) characterized in that it comprises the steps of: a.—providing at least a fresh skin (3), at least one fresh stringer (4), at least a fresh front spar (5) and fresh rear spar (6), b.—positioning the fresh skin (3), the at least one fresh stringer, the fresh spars (5, 6) in a curing tool in a configuration corresponding to that of a base structure (8), c.—subjecting the structure (8) to a single curing cycle, obtaining a cured base structure (8).

Abstract translation: 一种用于制造用于飞行器（11）的航空扭转箱（1）的基座结构（8）的方法，其特征在于，其包括以下步骤：a。至少提供一个新鲜的皮肤（3），至少一个新的纵梁 （4），至少一个新鲜的前翼梁（5）和新鲜的后翼梁（6），b。将新鲜的皮肤（3），至少一个新的纵梁，新鲜的翼梁（5,6）定位在固化 工具具有对应于基部结构（8）的构造，c。使结构（8）进行单个固化循环，获得固化的基础结构（8）。

公开(公告)号：US20150064393A1

公开(公告)日：2015-03-05

申请号：US14470555

申请日：2014-08-27

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Pablo CEBOLLA GARROFE ,  Carlos ROMÓN BANOGON

IPC: B32B37/18 ,  B32B38/18 ,  B32B37/10 ,  B32B5/22 ,  B32B5/12

CPC classification number: B32B5/12 ,  B29C65/18 ,  B29C65/4835 ,  B29C65/5014 ,  B29C65/5021 ,  B29C65/5057 ,  B29C66/1122 ,  B29C66/12821 ,  B29C66/1286 ,  B29C66/301 ,  B29C66/43441 ,  B29C66/45 ,  B29C66/474 ,  B29C66/7212 ,  B29C66/73756 ,  B29C66/73941 ,  B29C66/8322 ,  B32B5/24 ,  B32B7/12 ,  B32B27/12 ,  B32B2250/03 ,  B32B2250/40 ,  B32B2260/021 ,  B32B2260/046 ,  B32B2305/076 ,  B32B2405/00 ,  B32B2605/18 ,  B64C1/00 ,  B64C1/12 ,  B64C3/26 ,  C09J5/06 ,  C09J7/205 ,  C09J7/21 ,  C09J2201/128 ,  C09J2201/61 ,  C09J2400/263 ,  Y10T156/1744 ,  Y10T428/24124 ,  Y10T428/24132 ,  Y10T428/2848 ,  Y10T428/31504 ,  B29K2307/04

Abstract: 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.

Abstract translation: 用于接合复合材料部件的层压材料包括与第二层相邻的第一粘合材料层，与第一层相邻的预浸渍复合材料的第二层和第三层粘合剂材料。 将复合材料的至少两部分与层压体接合的方法包括以下步骤：提供已经固化的复合材料部件，将层压体定位在两个固化部分之间，并将压力和温度施加到包括至少两个部分的整个结构 和层压体，使得层压体固化，并且至少两个部分以所得结构连接在一起。

公开(公告)号：US20210187787A1

公开(公告)日：2021-06-24

申请号：US17129057

申请日：2020-12-21

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Pablo CEBOLLA GARROFE

IPC: B29B11/06

Abstract: A method for forming fiber composite preforms, the preform (1) include a web (2), a flange (3) and a bent part (2.1), and the method includes: laying-up a laminate (4) onto a tooling (5), the laminate (4) comprising lateral and transverse edges (4.1, 4.2) and the tooling (5) comprising a male part (7) comprising a surface (7.1) and a lateral wall (7.2), the web (2) being configured to be located over the surface (7.1) of the male part (7) and the flange (3) being configured to be located over the lateral wall (7.2) of the male part (7); forming the preform (1) over the male part (7); clamping the lateral edges (4.2) of the laminate (4) to the tooling (5) such that the web (2) and the flange (3) of the laid-up laminate (4) are kept under tensional loads, and bending a longitudinal portion of the male part (7).

公开(公告)号：US20150183506A1

公开(公告)日：2015-07-02

申请号：US14587647

申请日：2014-12-31

Applicant: Airbus Operations S.L.

Inventor： Diego GARCÍA MARTÍN ,  Lara BARROSO FERNÁNDEZ ,  Pablo CEBOLLA GARROFE ,  David Alfonso CEREZO ARCE ,  Ignacio José MÁRQUEZ LÓPEZ

IPC: B64C3/18 ,  B32B41/00 ,  B32B37/16 ,  B64D27/26 ,  B32B37/06 ,  B32B37/10 ,  B32B37/02 ,  B64C5/02

CPC classification number: B64C3/18 ,  B29C70/443 ,  B29D99/0014 ,  B32B37/02 ,  B32B37/06 ,  B32B37/1018 ,  B32B37/16 ,  B32B41/00 ,  B32B2038/0076 ,  B32B2038/0096 ,  B32B2309/68 ,  B32B2309/70 ,  B32B2605/18 ,  B64C3/20 ,  B64C3/26 ,  B64C5/02 ,  B64D27/26 ,  B64D2027/264 ,  B64F5/10 ,  Y02T50/43

Abstract: Highly integrated infused box made of composite material with two skins (3), several ribs (4), several stringers (5), a front spar and a rear spar, comprising a first semibox (1) and a second semibox (2) joined by connecting means, in which the first semibox (1) comprises one skin (3) and the ribs (4), and the second semibox (2) comprises one skin (3), the front spar, the rear spar and the stringers (5). A manufacturing method is also provided, which comprises forming processes for the first semibox (1), the second semibox (2) and an assembly process of the first semibox (1) with the second semibox (2).

Abstract translation: 由具有两个表皮（3），多个肋（4），多个桁条（5），前翼梁和后翼梁的复合材料制成的高度集成的输入盒，包括第一半箱（1）和第二半箱（2） 通过连接装置，其中第一半箱（1）包括一个皮肤（3）和肋（4），并且第二半箱（2）包括一个皮肤（3），前翼梁，后翼梁和纵梁 5）。 还提供了一种制造方法，其包括用于第一半盒（1），第二半盒（2）和第一半盒（1）与第二半盒（2）的组装过程的形成工艺。

公开(公告)号：US20180155006A1

公开(公告)日：2018-06-07

申请号：US15801669

申请日：2017-11-02

Applicant: AIRBUS OPERATIONS, S.L.

Inventor： Alberto ARANA HIDALGO ,  Esteban MARTINO GONZÁLEZ ,  Jesús Javier VÁZQUEZ CASTRO ,  Pablo CEBOLLA GARROFE

IPC: B64C5/02 ,  B64C1/26 ,  B64C3/28

CPC classification number: B64C5/02 ,  B64C1/065 ,  B64C1/26 ,  B64C3/28

Abstract: An aircraft stabilizer (15, 17) with an enlarged area of laminar flow. The lateral skins (45a, 45b; 65a, 65b) of its torsion box (43; 63) include joggled areas (53a, 53b; 73a, 73b) as attachment areas of its leading edge (41; 61) which are arranged in a rearward position with respect to the forward most spar of the stabilizer (15, 17).

公开(公告)号：US20170259903A1

公开(公告)日：2017-09-14

申请号：US15457499

申请日：2017-03-13

Applicant: AIRBUS OPERATIONS, S.L.

Inventor： Pablo CEBOLLA GARROFE ,  Álvaro CALERO CASANOVA ,  Soledad CRESPO PEÑA ,  Carlos GARCÍA NIETO ,  Iker VÉLEZ DE MENDIZÁBAL ALONSO ,  Enrique GUINALDO FERNANDEZ ,  Francisco Javier HONORATO RUIZ ,  Alvaro TORRES SALAS

IPC: B64C3/26 ,  B29C69/00 ,  B29C45/40 ,  B29C45/00 ,  B29C45/14

CPC classification number: B64C3/26 ,  B29C33/30 ,  B29C33/48 ,  B29C45/0005 ,  B29C45/0055 ,  B29C45/14475 ,  B29C45/40 ,  B29C69/001 ,  B29K2105/06 ,  B29K2105/12 ,  B29L2031/3076 ,  B29L2031/3085 ,  B64C21/06 ,  B64C2230/22

Abstract: This disclosure relates to the manufacturing of a leading edge section with hybrid laminar flow control for an aircraft. A manufacturing method involves: providing an outer hood, a plurality of elongated modules, first and second C-shaped profiles having comprising cavities, and an inner mandrel; assembling an injection moulding tool by placing each profile on each end of the inner mandrel, arranging a first extreme of each elongated module in one cavity of the first profile and a second extreme of the module in another cavity of the second profile, both cavities positioned in the same radial direction; and placing the hood on first and second profiles to close the tool. Further, the injection moulding tool is closed and filled with an injection compound comprising thermoplastic and short-fiber. Finally, the compound is hardened and demoulded.