公开(公告)号：US20240286763A1

公开(公告)日：2024-08-29

申请号：US18584496

申请日：2024-02-22

Applicant: Airbus Operations Limited

Inventor： Stuart BRYANT ,  Thomas BARNETT

IPC: B64F5/10 ,  B64C3/18

CPC classification number: B64F5/10 ,  B64C3/182

Abstract: A method of fabricating an aircraft structural component for an aircraft includes providing a component precursor with a web and a flange extending from the web, wherein the web has a length, a height which is shorter than the length, a thickness which is shorter than the height, a first end proximal to the flange and a second end distal from the flange, applying tension to the component precursor in a direction parallel to the length of the web and with a magnitude that varies along the height of the web so as to increase the length of the web to different extents between the first end of the web and the second end of the web, sectioning the component precursor, and releasing the tension to allow shaping of the component precursor into a form required for the aircraft structural component.

公开(公告)号：US20230382061A1

公开(公告)日：2023-11-30

申请号：US18249010

申请日：2021-10-07

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： Thomas BARNETT ,  Lee PROUDLER

IPC: B29C70/30 ,  B64F5/10

CPC classification number: B29C70/302 ,  B64F5/10 ,  B29L2031/3085

Abstract: A method of manufacturing an aircraft aerofoil such as a winglet. The aircraft aerofoil includes: a first cover, a second cover, an aerofoil leading edge, and an aerofoil trailing edge where the first and second cover are joined at a trailing edge interface. The first cover is formed by: a lay-up step in which a plurality of fibre plies are laid up to obtain a preform, wherein the preform has a thickness and a preform trailing edge, and the preform is laid up during the lay-up step with a ramp of decreasing thickness where the thickness of the preform decreases towards the preform trailing edge; and a curing step in which the preform is cured to form the first cover, wherein the ramp of decreasing thickness cures during the curing step to form a contact surface of the first cover.

公开(公告)号：US20200331593A1

公开(公告)日：2020-10-22

申请号：US16851490

申请日：2020-04-17

Applicant: Airbus Operations Limited

Inventor： Thomas BARNETT ,  Andrew SCAIFE ,  Lee PROUDLER

IPC: B64C23/06 ,  B64C3/18

Abstract: A wingtip device to attach to a wing of an aircraft includes an aerofoil portion and a connection spar arranged to be received in a connection spar receiving portion of the wing of an aircraft. The spar includes a first through hole in a first portion of the connection spar and a second through hole in a second rearward portion of the connection spar, the second portion being rearward of the first portion with respect to a direction of flight. The first and second through holes are arranged to receive a retaining pin that is to be inserted through both the first and second through holes.

公开(公告)号：US20190329873A1

公开(公告)日：2019-10-31

申请号：US16391656

申请日：2019-04-23

Applicant: Airbus Operations Limited

Inventor： Lee PROUDLER ,  Andrew SCAIFE ,  Thomas BARNETT

IPC: B64C23/06 ,  B64C3/18

Abstract: A winglet 100 configured for attachment to a wing portion 10 for an aircraft 1000. The winglet 100 includes a first outer wall 101, a second outer wall 102, and one or more spars 114, 116 between the first outer wall 101 and the second outer wall 102. The first outer wall 101 is unitary with the second outer wall 102 and/or with the one or more spars 114, 116.

公开(公告)号：US20230166833A1

公开(公告)日：2023-06-01

申请号：US18102469

申请日：2023-01-27

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： Thomas BARNETT ,  Andrew SCAIFE ,  Lee PROUDLER ,  Richard HEWSON

IPC: B64C23/06 ,  B64C3/18

CPC classification number: B64C23/069 ,  B64C3/185 ,  B64C3/187

Abstract: A winglet is disclosed including first and second covers, a front spar, a rear spar, a rib, and a mid spar between the front spar and the rear spar. The rib and each spar are joined to the first cover and to the second cover. The mid spar has a length and the mid spar curves along all or part of its length. The length of the mid spar extends from an inboard end of the mid spar to an outboard end of the mid spar, and the rib wraps around the inboard or outboard end of the mid spar.

公开(公告)号：US20210114711A1

公开(公告)日：2021-04-22

申请号：US17050585

申请日：2019-04-26

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： Thomas BARNETT ,  Lee PROUDLER ,  Andrew SCAIFE

IPC: B64C3/18 ,  B64C23/06 ,  B29C70/48 ,  B29C70/22

Abstract: A composite spar is disclosed having a main body and a pair of spaced apart legs. The space between the legs permits access to the mandrel assembly within the spar in order to ease its removal. This arrangement permits a spar of any length and contour to be manufactured.

公开(公告)号：US20250135744A1

公开(公告)日：2025-05-01

申请号：US18911377

申请日：2024-10-10

Applicant: Airbus Operations Limited

Inventor： Thomas BARNETT

IPC: B32B3/26 ,  B32B1/00 ,  B32B5/02 ,  B32B5/26 ,  B32B37/16 ,  B32B38/00 ,  B64C3/26

Abstract: A composite structure comprising a body, such as an aircraft wing skin; and an opening in the body, such as a manhole. The body has steered fiber elements and terminated fiber elements. Each steered fiber element has a curved portion with a plurality of steered fibers which follow curved paths around the opening. The terminated fiber elements alternate with the steered fiber elements, and each terminated fiber element comprises a plurality of terminated fibers which terminate next to the curved portion of a respective steered fiber element.

公开(公告)号：US20240286762A1

公开(公告)日：2024-08-29

申请号：US18584454

申请日：2024-02-22

Applicant: Airbus Operations Limited

Inventor： Stuart BRYANT ,  Thomas BARNETT

IPC: B64F5/10 ,  B64C3/18

CPC classification number: B64F5/10 ,  B64C3/182

Abstract: A method of fabricating an aircraft structural component for an aircraft includes providing a component precursor with a web and a flange. The web has a length, height shorter than the length, thickness shorter than the height, first end proximal to the flange and second end distal from the flange. A force is applied to the component precursor with a magnitude varying along the web height from a minimum at one of the first and second ends to a maximum at another of the first and second ends to increase length of the web to different extents. Then shaping the component precursor includes curving the component precursor into a curved shape having a first radius of curvature at the one of the first and second ends and a second radius of curvature at the another of the first and second ends, the second radius of curvature greater than the first.

公开(公告)号：US20230373610A1

公开(公告)日：2023-11-23

申请号：US18029071

申请日：2021-08-11

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： Thomas BARNETT ,  Lee PROUDLER

IPC: B64C3/26 ,  B64C23/06 ,  B64C3/20

CPC classification number: B64C3/26 ,  B64C23/069 ,  B64C3/20

Abstract: A cover panel for an aircraft including: a first region, a second region for forming an overlap with a second panel, and a ramp, wherein at least a portion of the ramp is between the first and second regions, wherein the ramp includes a tapered region such that a width of the ramp tapers towards a free-edge of the first region, and wherein the free-edge is configured to form a butt-joint with the second panel.