公开(公告)号：US12208890B2

公开(公告)日：2025-01-28

申请号：US16460104

申请日：2019-07-02

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： Paul Douglas ,  Anthony John Bryant ,  Daniel Peachey

IPC: B64C3/18 ,  B64C3/34 ,  B64C3/38 ,  B64D37/00 ,  B64C3/20 ,  B64C3/26 ,  B64C23/00

Abstract: A connector, a connector assembly, an aircraft fuel breather system and an aircraft wing are disclosed. The connector connects a breather pipe or float valve to a hat section stringer duct attached to an aircraft panel. The connecter has a bridge to bridge over the duct and to cover an aperture in a wall of the duct. The bridge has a flange on either side for attachment of the connector to the panel. The connector has a seal to seal the bridge to the duct, an aperture defined in the bridge and a flow controller connector to connect and provide fluid connection between the connector and pipe or float valve. The assembly comprises the connector, the duct and aircraft panel and the fuel breather system includes one or more fuel tanks, a breather pipe and a vent to atmosphere.

公开(公告)号：US12077287B2

公开(公告)日：2024-09-03

申请号：US18162303

申请日：2023-01-31

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： William Tulloch ,  Javier Ruiz De Pablo ,  Paul Dean ,  James Bird

IPC: B64C3/18 ,  B64C3/34

CPC classification number: B64C3/185 ,  B64C3/34

Abstract: An aircraft wing structure (100) including a spar (101) and a systems module (200) that is releasably secured to brackets (300) on a first side of the spar (101) and the second, opposite side of the spar is configured to define a wall of a fuel tank of an aircraft wing.

公开(公告)号：US20240166331A1

公开(公告)日：2024-05-23

申请号：US18547661

申请日：2022-02-08

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： William TULLOCH

IPC: B64C3/34 ,  B64D27/31 ,  B64D27/355 ,  B64D37/04 ,  B64D37/30

CPC classification number: B64C3/34 ,  B64D27/31 ,  B64D27/355 ,  B64D37/04 ,  B64D37/30 ,  B64D2221/00

Abstract: An aircraft wing including: a wingbox; a fuel tank; a fuel cell system with a fuel cell; a fuel line configured to deliver fuel from the fuel tank to the fuel cell system; a propulsion system carried by the wingbox; and an electrical power line configured to deliver electrical power from the fuel cell system to the propulsion system. The fuel tank and the fuel cell system are located inside the wingbox, and the propulsion system is located outside the wingbox.

公开(公告)号：US11794874B2

公开(公告)日：2023-10-24

申请号：US16661514

申请日：2019-10-23

Applicant: The Boeing Company

Inventor： Garrett C. Hanson

IPC: B64C3/18 ,  B64C3/34

CPC classification number: B64C3/182 ,  B64C3/34

Abstract: Examples for low impact hat stringer fluid dams are presented herein. An aircraft structure may include a wing with a vent stringer coupled to the wing. The vent stringer may include a center portion positioned between a first section and a second section. The center portion of the vent stringer includes a slot. A vent dam may be coupled within the vent stringer proximate the slot in the center portion. The vent dam can include a sealant coupled between an integrated pair of baffles such that a combination of the sealant and the integrated pair of baffles prevents fluid communication between the first section and the second section of the vent stringer.

公开(公告)号：US20230257101A1

公开(公告)日：2023-08-17

申请号：US18109672

申请日：2023-02-14

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： John Martin GAITONDE ,  Chris HEAYSMAN

IPC: B64C3/34

CPC classification number: B64C3/34

Abstract: A fuel tank is disclosed including a lower cover and an upper cover. The lower cover or the upper cover includes a panel assembly. The panel assembly includes a panel and a stringer attached to the panel. The stringer includes a pair of portions which are spaced apart in a lengthwise direction of the stringer and connected to each other by a bridge. Each portion is connected to a respective end of the bridge, and each end of the bridge deviates away from the panel. The stringer includes reinforcement fibres which extend between the portions via the bridge. Each reinforcement fibre deviates away from the panel at each end of the bridge. The stringer includes a stringer recess between the bridge and the panel, and a flow passage in the stringer recess through which fluid can flow across the stringer.

公开(公告)号：US11613376B2

公开(公告)日：2023-03-28

申请号：US17217564

申请日：2021-03-30

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： Antony Charles Peacock ,  Ross Salisbury ,  Jonathan Paisley ,  Phillip Scott

IPC: B64D37/04 ,  B64C3/18 ,  B64D37/08 ,  B64C3/34

Abstract: An aircraft wing box is disclosed having a fuel tank with a fuel-tight boundary, upper and lower covers, forward and aft spars, and a partition including an inboard portion, an outboard portion, and a third portion between the inboard and outboard portions. Each cover is attached to each spar, the inboard portion of the partition is joined to each cover and joined to one of the spars, the outboard portion of the partition is joined to each cover and joined to one of the spars, each cover is joined to the partition. The inboard part, outboard part and third part of the partition are integrally formed as a single-piece; and the single-piece provides part of the fuel-tight boundary of the fuel tank.

公开(公告)号：US11597498B2

公开(公告)日：2023-03-07

申请号：US17812947

申请日：2022-07-15

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： Paul Edwards ,  Antony Peacock ,  Timothy Sanderson

IPC: B64C3/34 ,  B64C3/18 ,  B64C7/00 ,  F16J15/06 ,  F16J15/10

Abstract: A seal for sealing an aircraft fuel tank, an aircraft wing rib and stringer sealing assembly, an aircraft wing fuel tank, an aircraft structural wing box, an aircraft wing, and a method of sealing an aperture are disclosed. The seal is for sealing a wing rib to a stringer passing through an aperture in the rib at a variable position in the aperture. The seal includes self-adjustment means to absorb any tolerance when forming the seal, upon the stringer being assembled into the aperture in the rib.

公开(公告)号：US11560213B2

公开(公告)日：2023-01-24

申请号：US16821204

申请日：2020-03-17

Applicant: EMBRAER S.A.

Inventor： Alberto Vilar Vilas Boas ,  Daniel Gonçalves Da Silva ,  Gustavo Dedding Martins ,  Juliano De Oliveira ,  Luciano Alves Martins ,  Luiz Gustavo Suzuki ,  Robson Garcia Correa ,  Vitor Juliano Sampaio Soares ,  Wagner Garcez Verri

IPC: B64C7/00 ,  B64C3/34

Abstract: Closure devices and methods are provided for closing a stringer penetration space defined between a stringer and a wing rib of an aircraft wing section. According to certain embodiments, the closure devices will integrally include a forward face plate positioned in covering relationship to at least a portion of the stringer penetration space, and a rearwardly projecting attachment arm rigidly adapted for rigid attachment to the stringer so as to positionally fix the forward face plate relative to the stringer penetration space.

公开(公告)号：US20220340281A1

公开(公告)日：2022-10-27

申请号：US17862317

申请日：2022-07-11

Applicant: ZSM HOLDINGS LLC

Inventor： Etan D. KARNI ,  Scott David REWERTS ,  Mark Emil LUNDSTROM

IPC: B64D9/00 ,  B64C1/14 ,  B64C1/22 ,  B64C1/20 ,  B64C3/32 ,  B64C3/34 ,  B64C17/08 ,  B64D37/04 ,  F03D13/40 ,  B64C1/06 ,  B64F1/32

Abstract: Systems, methods, and aircraft for managing center of gravity (CG) while transporting large cargo are described. Management of CG is achieved in many ways. In some instances, the aircraft itself is designed to assist in managing CG by providing fuel tanks that minimize the impact of fuel on the net CG of the aircraft. The fuel tanks utilize only a small amount of available volume in the wings for fuel. Disclosures related to properly managing CG while loading wind turbines onto cargo aircraft are also provided. The CG management techniques provided for herein allow for the transportation of wind turbine blades via aircraft, running counter to the typical rail or truck transportation of the same. One such management technique includes accounting for how a rotation of the blades when loading impacts the CG of the blades, and thus taking this into account when placing the blades in the aircraft.

公开(公告)号：US11465731B2

公开(公告)日：2022-10-11

申请号：US16451337

申请日：2019-06-25

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： Paul Douglas

IPC: B64C3/18 ,  B64F5/10 ,  B29C70/30 ,  B29C70/86 ,  B64C3/34 ,  B29K307/04 ,  B29K701/12 ,  B29L31/30 ,  F16L9/06

Abstract: A duct stringer has duct walls providing a duct with a closed cross-section; and a bulkhead in the duct. The duct is adapted to transport fluid, and the bulkhead is adapted to block the flow of fluid along the duct. The bulkhead is adhered to the duct walls by one or more co-cured or co-bonded joints. The bulkhead includes a pair of bulkhead parts, each with a web and one or more flanges. The duct stringer is manufactured by positioning the mandrels end-to-end with the bulkhead parts back-to-back between them; wrapping or laying-up the duct walls around the bulkhead parts and the mandrels; co-curing or co-bonding the flanges of the bulkhead parts to the duct walls; and after the bulkhead has been adhered to the duct walls, removing the mandrels from opposite ends of the duct.