公开(公告)号：US12097973B2

公开(公告)日：2024-09-24

申请号：US17454267

申请日：2021-11-10

Applicant: The Boeing Company

Inventor： Daniel R. Smith ,  Darrell Darwin Jones

IPC: B64F5/10 ,  B29C70/30 ,  B29L31/30 ,  B64C3/18 ,  B64C3/26

CPC classification number: B64F5/10 ,  B29C70/30 ,  B64C3/182 ,  B64C3/26 ,  B29L2031/3085

Abstract: Wing panels having composite wing skins and stringers are produced on a moving production line. The wing panels are formed on mandrels that move through workstations along the production line where laminators layup the wing skins and pick-and-place machines place stringers on the wing skins that are supplied by stringer feeder lines.

公开(公告)号：US20240198609A1

公开(公告)日：2024-06-20

申请号：US18522445

申请日：2023-11-29

Applicant: AIRBUS OPERATIONS, S.L.U.

Inventor： Diego GARCÍA MARTIN ,  Fernando MUÑOZ AJENJO ,  Georgina GALERA CÓRDOBA ,  Alexander IBISATE GONZALEZ DE MATAUCO ,  Fernando ESQUIVIAS GARCIA

IPC: B29C70/78 ,  B29C70/44

CPC classification number: B29C70/78 ,  B29C70/446 ,  B29L2031/3085

Abstract: A process for manufacturing composite wing covers is provided that includes placing a laminate inside each of a plurality of shaping tools. Shaping the laminates and pressing the laminates against the shaping tools. Retaining the shaped laminates inside the shaping tools and turning over the shaped laminates. Attaching a skin to the shaped laminates and curing the skin and the shaped laminates. Heating the shaping tools and creating a vacuum in the shaping tools.

公开(公告)号：US11878793B2

公开(公告)日：2024-01-23

申请号：US17387193

申请日：2021-07-28

Applicant: The Boeing Company

Inventor： Forouzan Behzadpour ,  Patrick B. Stickler

IPC: B64C3/00 ,  B29C70/00 ,  B29D99/00 ,  B64C3/20 ,  B64C3/26 ,  B29C70/08 ,  B29C70/38 ,  B64C3/18 ,  B29L31/30

CPC classification number: B64C3/20 ,  B29C70/086 ,  B29C70/386 ,  B29D99/0014 ,  B64C3/182 ,  B64C3/26 ,  B29L2031/3085

Abstract: A panel including an outer face sheet; an inner face sheet; a foam disposed between the outer face sheet and the inner face sheet; and a core structure (e.g., a stringer comprising a hat structure) between the foam and the inner face sheet; and between the foam and the outer face sheet. The core structure is protected from impact damage and increases flexural stiffness of the panel on an aircraft wing.

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：US11826965B2

公开(公告)日：2023-11-28

申请号：US17744386

申请日：2022-05-13

Applicant: The Boeing Company

Inventor： Christopher A. Howe ,  Angelo Koucoulis ,  Stuart Bateman

IPC: B33Y10/00 ,  B29C69/02 ,  B33Y80/00 ,  B64C9/24 ,  B29C70/48 ,  B29K307/04 ,  B29K309/08 ,  B29L31/30

CPC classification number: B29C69/02 ,  B33Y10/00 ,  B33Y80/00 ,  B64C9/24 ,  B29C70/48 ,  B29K2307/04 ,  B29K2309/08 ,  B29L2031/3085

Abstract: Disclosed herein are methods for fabricating a composite structure by forming, via additive manufacturing, a solid-phase component; positioning the solid-phase component and a reinforcement into a mold cavity; and consolidating, in the mold cavity, the solid-phase component, the reinforcement, and a liquid-phase component to form the composite structure.

公开(公告)号：US11820081B2

公开(公告)日：2023-11-21

申请号：US17397855

申请日：2021-08-09

Applicant: The Boeing Company

Inventor： Daniel M. Rotter ,  Brad A. Coxon ,  Gabriel Zane Forston ,  Jake Adam Reeves ,  Khanh Mai Pham ,  Stephen Lee Metschan ,  Patrick Shephard ,  John Dempsey Morris ,  Steven Philip Hansen ,  Brian Dodgson

IPC: B29C65/02 ,  B29C70/44 ,  B29C65/00 ,  B29C70/46 ,  B29C70/54 ,  B32B5/10 ,  B32B27/38 ,  B32B37/00 ,  B32B37/06 ,  B32B37/10 ,  B29L31/30 ,  B29K63/00 ,  B29K105/06

CPC classification number: B29C65/02 ,  B29C66/00145 ,  B29C66/721 ,  B29C70/44 ,  B29C70/46 ,  B29C70/549 ,  B32B5/10 ,  B32B27/38 ,  B32B37/0046 ,  B32B37/06 ,  B32B37/1018 ,  B29C66/112 ,  B29C66/1122 ,  B29C66/131 ,  B29C66/41 ,  B29C66/45 ,  B29C66/524 ,  B29C66/636 ,  B29C66/7212 ,  B29C66/73752 ,  B29C66/81455 ,  B29C66/8322 ,  B29K2063/00 ,  B29K2105/06 ,  B29L2031/3076 ,  B29L2031/3085 ,  B32B2305/08 ,  B32B2363/00 ,  B32B2605/18 ,  B29C66/7212 ,  B29K2307/04 ,  B29C66/7212 ,  B29K2309/08 ,  B29C66/7212 ,  B29K2305/00

Abstract: Systems and methods for assembling elongate composite structures are disclosed. The systems include a first rigid elongate cure tool defining a first elongate support surface for supporting a first elongate charge of composite material (FEC), a second rigid elongate cure tool defining a second elongate support surface for supporting a second elongate charge of composite material (SEC), and a flexible elongate caul plate. The systems further include a vacuum compaction film, a translation structure, and a vacuum source. Methods according to the present disclosure include positioning a vacuum compaction film, positioning a flexible elongate caul plate, and positioning an FEC. The methods further include positioning an SEC, contacting a region of the FEC with a region of the SEC, sealing the vacuum compaction film, evacuating the enclosed volume to generate an elongate composite assembly, and heating the elongate composite assembly to define the elongate composite structure.

公开(公告)号：US11767128B2

公开(公告)日：2023-09-26

申请号：US17682141

申请日：2022-02-28

Applicant: The Boeing Company

Inventor： Derek R. Tuck ,  Philipp A. Boettcher ,  Carson Alexander Smith ,  David Thomas Misciagna

IPC: B64D45/02 ,  B29C65/56 ,  B29C65/00 ,  B29C70/02 ,  B29C70/88 ,  B64C3/26 ,  B29K307/04 ,  B29L31/30

CPC classification number: B64D45/02 ,  B29C65/562 ,  B29C66/1122 ,  B29C66/43 ,  B29C66/7212 ,  B29C66/7314 ,  B29C70/028 ,  B29C70/882 ,  B64C3/26 ,  B29K2307/04 ,  B29K2995/0005 ,  B29L2031/3085 ,  Y10T428/19

Abstract: The embodiments described herein provide for lightning protection in aircrafts constructed with Carbon Fiber Reinforced Plastic (CFRP). In one embodiment, the apparatus includes a first Carbon Fiber Reinforced Plastic (CFRP) panel, a second CFRP panel that overlaps with the first CFRP panel in a vertical direction, and a fastener to join the first CFRP panel with the second CFRP panel, the fastener extending in the vertical direction in an area where the first CFRP panel and the second CFRP panel overlap. The apparatus further includes a plurality of electrically conductive pins in each of the first CFRP panel and the second CFRP panel, wherein the pins extend in the vertical direction proximate to the fastener to electrically connect the first CFRP panel and the second CFRP panel in the area where the first CFRP panel and the second CFRP panel overlap.

公开(公告)号：US20230294367A1

公开(公告)日：2023-09-21

申请号：US18321874

申请日：2023-05-23

Applicant: The Boeing Company

Inventor： Joseph L. Hafenrichter ,  Gary E. Georgeson

IPC: B29C65/54 ,  B29C65/14 ,  B29C65/48 ,  B29C65/50

CPC classification number: B29C65/544 ,  B29C65/1448 ,  B29C65/4835 ,  B29C65/5057 ,  B29L2031/3085

Abstract: An example method of joining a first structure and a second structure is described that includes forming a bond cavity between a first structure and a second structure, placing a semi-permeable breather material at one or more exits of the bond cavity, placing a vacuum bag around the bond cavity and the semi-permeable breather material, evacuating the bond cavity via a vacuum port and forcing adhesive into the bond cavity via an adhesive port while the bond cavity is evacuated, and curing the adhesive via one or more heaters to bond the first structure to the second structure.

公开(公告)号：US11707896B2

公开(公告)日：2023-07-25

申请号：US16802321

申请日：2020-02-26

Applicant: The Boeing Company

Inventor： Samuel J. Knutson ,  James R. Kendall ,  Raviendra S. Suriyaarachchi

IPC: B29C70/00 ,  B64C1/00 ,  B64C3/00 ,  B29C70/54 ,  B29C70/44 ,  B64C1/06 ,  B64C1/12 ,  B64C3/18 ,  B64C3/26 ,  B29D99/00 ,  B29L31/30

CPC classification number: B29C70/541 ,  B29C70/44 ,  B29C70/446 ,  B64C1/064 ,  B64C1/12 ,  B64C3/182 ,  B64C3/26 ,  B29D99/0003 ,  B29D99/0014 ,  B29L2031/3082 ,  B29L2031/3085 ,  B64C2001/0072

Abstract: Provided are methods and devices for supporting of variety of different pre-cured composite stringers after forming and prior to curing. A post-forming processing device comprises a base with a channel for receiving hat portions of different stringers. The device also comprises a support structure, at least partially extending within the channel. The support structure is configured to conform to different hat portions and to retain the shape of these hat portions. For example, the support structure is made from a flexible material, which conforms to any shape variations. In some examples, the support structure is made from a jamming material that is reshaped together with each of the pre-cured composite stringers. A post-forming processing device is used for supporting different pre-cured composite stringers while various operations are performed on these stringers, such as stringer trimming, inspection, installation of bladders and noodles, and the like.

公开(公告)号：US11685508B2

公开(公告)日：2023-06-27

申请号：US16843534

申请日：2020-04-08

Applicant: The Boeing Company

Inventor： Joseph L. Hafenrichter ,  Gary E. Georgeson ,  Marc J. Piehl

IPC: B64C3/26 ,  B64C3/24 ,  B29C35/02 ,  B29L31/30 ,  B64F5/10

CPC classification number: B64C3/26 ,  B29C35/0227 ,  B64C3/24 ,  B29L2031/3085 ,  B64F5/10

Abstract: A bonded structure is described. The bonded structure includes an outer structure including a close tolerance hole associated with a first accuracy level. The bonded structure includes an interior structure comprising an oversized hole associated with a second accuracy level that is different from the first accuracy level. The bonded structure includes an elastomeric grommet disposed in the oversized hole. The bonded structure includes one or more spacers between the outer structure and the interior structure providing a space between the outer structure and the interior structure. The bonded structure includes a fastener positioned in the close tolerance hole and in the oversized hole. The bonded structure includes a bonding media disposed in the space between the outer structure and the interior structure via one or more channels of the fastener. The bonding media, elastomeric grommet, and oversized hole collectively position the interior structure relative to the outer structure.