公开(公告)号：US11440634B2

公开(公告)日：2022-09-13

申请号：US16521057

申请日：2019-07-24

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Elena Arevalo Rodriguez ,  Antonio Torres Esteban

IPC: B64C1/12 ,  B64C1/06 ,  B64F5/10 ,  B29L31/30 ,  B64C1/00

Abstract: A frame (1) for fuselage shells of an aircraft, the fuselage comprising a skin (3) and stringers (4), the frame (1) including: a plurality of sections (5), the sections (5) being separated by intermediate gaps corresponding to the position of the stringers (4) in the fuselage, each section (5) having a multi-cell configuration constituted by several modular elements (6) of composite material arranged in longitudinal direction, and a continuous inner cap (7) on top of the sections (5) and the intermediate gaps.

公开(公告)号：US11752704B2

公开(公告)日：2023-09-12

申请号：US17075211

申请日：2020-10-20

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Antonio Torres Esteban ,  Jose-Maria Blanco-Saiz ,  Manuel Recio Melero ,  Pedro Nogueroles Viñes

IPC: B29C70/20 ,  B29C65/48 ,  B29C65/00 ,  B29C70/30 ,  B64C1/00 ,  B32B5/12 ,  B32B5/26 ,  B29L31/30

CPC classification number: B29C70/202 ,  B29C65/48 ,  B29C66/721 ,  B29C70/30 ,  B32B5/12 ,  B32B5/26 ,  B64C1/00 ,  B29L2031/3076 ,  B64C2001/0072

Abstract: A composite laminate (2) for an airframe lifting surface comprising a set of stacked plies (10) of pre-preg material, the composite laminate (2) being surrounded by at least an edge (3) following an edge direction E along the composite laminate (2), the set of stacked plies (10) including: a first plurality (4) of plies (4.1) formed by tapes arranged parallel to the edge direction E, and a second plurality (5) of plies (5.1, 5.2, 5.3) formed by tapes arranged in a direction different to the edge direction E, wherein the thickness of at least one ply of the second plurality (5) of plies is lower than the thickness of each ply of the first plurality (4) of plies.

公开(公告)号：US09440725B2

公开(公告)日：2016-09-13

申请号：US14139147

申请日：2013-12-23

Applicant: AIRBUS OPERATIONS, S.L.

Inventor： Ignacio Outon Hernández ,  Yolanda Miguez Charines ,  Oscar Miguel Macías Jareño ,  Juan José Pastrana Bermejo ,  Antonio Torres Esteban

IPC: B64C1/06 ,  B29C70/34 ,  B29D99/00

CPC classification number: B64C1/064 ,  B29C70/34 ,  B29D99/0003 ,  Y02T50/43 ,  Y10T156/1043 ,  Y10T428/24174

Abstract: The present invention relates to a stringer, particularly to a stiffening and structural longitudinal element for skin of aircraft airfoil surfaces, characterized in that it incorporates two separate and independent reinforcement areas, one in the foot and the other at the end of the web (head) of the stringer, where the reinforcement areas are obtained by a widening of the section of the stringer, the widening being formed by a localized stack of reinforcing plies of composite material which are embedded within the stringer. The invention also relates to the method of manufacture and is particularly applicable to stringers having an L-shaped or T-shaped section.

Abstract translation: 技术领域本发明涉及一种纵梁，特别涉及一种用于飞机机翼表面的皮肤的加强和结构纵向元件，其特征在于，其包括两个独立且独立的加强区域，一个在脚部中，另一个位于腹板末端（头部 ），其中通过桁条的部分的加宽获得加强区域，该扩宽由嵌入在桁条内的复合材料的增强层的局部叠层形成。 本发明还涉及制造方法，特别适用于具有L形或T形截面的桁条。