公开(公告)号：US11701801B2

公开(公告)日：2023-07-18

申请号：US16291535

申请日：2019-03-04

申请人： The Boeing Company

发明人： Daniel J. Wade ,  Mathew K. Lathrop

IPC分类号： B64C3/18 ,  B29C37/00 ,  B29C70/44 ,  B29C33/38 ,  B29C70/54 ,  B29C70/68 ,  B29L31/30 ,  B29C43/36

CPC分类号： B29C37/0003 ,  B29C33/3842 ,  B29C70/443 ,  B29C70/541 ,  B29C70/542 ,  B29C70/549 ,  B29C70/681 ,  B29C2043/3655 ,  B29L2031/3076 ,  B64C3/18

摘要： Systems and methods are provided for a caul plate having a feature for removal. One embodiment is a caul plate for forming a composite part. The caul plate includes a body that includes a lower surface which faces the composite part, and an upper surface that is opposite to the lower surface. The caul plate also includes a groove in the upper surface to accept a tool to slide the caul plate laterally from the composite part.

公开(公告)号：US11820081B2

公开(公告)日：2023-11-21

申请号：US17397855

申请日：2021-08-09

申请人： The Boeing Company

发明人： 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分类号： 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分类号： 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

摘要： 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：US20230356485A1

公开(公告)日：2023-11-09

申请号：US17661894

申请日：2022-05-03

申请人： The Boeing Company

发明人： Samuel Shane Brickey ,  Julia Karolina Slusarski

IPC分类号： B29C70/54 ,  B29C70/44

CPC分类号： B29C70/549 ,  B29C70/44

摘要： A method, apparatus, and system for applying a vacuum-based pressure on an uncured composite structure. Membranes are bonded to a boundary of a caul. The membranes include positive features that define vacuum channels. The membranes are spliced to each other. The positive features that define the vacuum channels in the membranes are aligned to each other during splicing of the membranes. The membranes spliced to each other and bonded to the caul to form an integrated caul. The integrated caul applies a pressure on the uncured composite structure during operation of the integrated caul.

公开(公告)号：US11806954B2

公开(公告)日：2023-11-07

申请号：US17644285

申请日：2021-12-14

申请人： The Boeing Company

发明人： Gagandeep Saini ,  Ian Edward Schroeder ,  Kurtis Shuldberg Willden ,  Lisa Christina Carlson

IPC分类号： B29C70/54 ,  B29D99/00 ,  B29C70/46 ,  B29L9/00 ,  B29L31/00

CPC分类号： B29C70/549 ,  B29C70/462 ,  B29D99/0003 ,  B29L2009/00 ,  B29L2031/001

摘要： A composite charge is formed between two compression dies into a composite laminate stiffener. The stiffener is contoured along its length by contouring the dies. Wrinkle diffusers attached to, or embedded or incorporated into the tool surfaces of the dies, diffuse wrinkles formed on the inside radius of the stiffener during the contouring.

公开(公告)号：US11738526B2

公开(公告)日：2023-08-29

申请号：US16588846

申请日：2019-09-30

申请人： The Boeing Company

发明人： Michael J. Fleming

IPC分类号： B29C70/54 ,  B29C65/50 ,  B29C70/44 ,  B29C65/00 ,  B29C65/48 ,  B29L31/30

CPC分类号： B29C70/549 ,  B29C65/4825 ,  B29C65/50 ,  B29C66/721 ,  B29C70/443 ,  B29L2031/3076

摘要： A method and apparatus for manufacturing a composite part is provided. A composite laminate is formed upon a first tool that provides a first mold line for the composite laminate. A second tool is placed against the composite laminate in which a tooling surface of the second tool is used to create a second mold line for the composite laminate. The second tool is formed from a plurality of prefabricated sections joined by a joining material in which the tooling surface is formed by a layer adhered to the plurality of prefabricated sections and the joining material.

公开(公告)号：US11724469B2

公开(公告)日：2023-08-15

申请号：US17706456

申请日：2022-03-28

申请人： Safran Seats GB Limited

发明人： Nicholas Potts ,  Bhaskar Biswas

IPC分类号： B29C70/54 ,  B29C70/44 ,  B29C33/02 ,  B29C70/68 ,  B32B27/08 ,  B32B37/00 ,  B32B37/10 ,  B32B38/18

CPC分类号： B29C70/543 ,  B29C70/44 ,  B29C70/549 ,  B29C33/02 ,  B29C70/68 ,  B29C2033/023 ,  B32B27/08 ,  B32B37/0046 ,  B32B37/1018 ,  B32B38/1808 ,  B32B2605/18

摘要： The present invention provides a tool 1 for curing a composite component, the tool comprising a lay-up surface 8 for laying-up layers of an uncured composite component, a cover assembly 9 for moving in relation to the lay-up surface to cover a layed-up uncured composite component on the lay-up surface, the cover assembly comprising a sealable cover for sealing around the uncured composite component on the lay-up surface to form a sealed zone, and a vacuum port 25 for providing a vacuum to the sealed zone, wherein the tool further comprises at least one heating element 15, 53 within the sealed zone for heating the uncured composite component. The invention also provides a method of manufacturing a composite component and a composite component. The composite component may form at least part of a piece of aircraft furniture, such as an aircraft seat shell.

公开(公告)号：US20230191722A1

公开(公告)日：2023-06-22

申请号：US17554775

申请日：2021-12-17

申请人： ROHR, INC.

发明人： SHAWN TARDY ,  NOUSHIN BAHRAMSHAHI ,  ANDREW ADAN ,  ROBERTO RAMOS ,  NICOLE M. SANNES

IPC分类号： B29C70/44 ,  B29C65/00 ,  B29C70/54

CPC分类号： B29C70/443 ,  B29C66/81455 ,  B29C66/7392 ,  B29C66/0044 ,  B29C66/91411 ,  B29C70/549 ,  B29L2007/002

摘要： A method of manufacturing a thermoplastic panel may comprise: laying up a panel preform within a consolidation assembly, the panel preform comprising a plurality of plies of material comprising thermoplastic resin and fiber; generating, via a hot bond unit, a vacuum environment within the consolidation assembly; and heating, via the hot bond unit and through a heated blanket within the consolidation assembly, the panel preform.

公开(公告)号：US20230182417A1

公开(公告)日：2023-06-15

申请号：US17644285

申请日：2021-12-14

申请人： The Boeing Company

发明人： Gagandeep Saini ,  Ian Edward Schroeder ,  Kurtis Shuldberg Willden ,  Lisa Christina Carlson

IPC分类号： B29C70/54 ,  B29D99/00 ,  B29C70/46

CPC分类号： B29C70/549 ,  B29C70/462 ,  B29D99/0003 ,  B29L2031/001

摘要： A composite charge is formed between two compression dies into a composite laminate stiffener. The stiffener is contoured along its length by contouring the dies. Wrinkle diffusers attached to, or embedded or incorporated into the tool surfaces of the dies, diffuse wrinkles formed on the inside radius of the stiffener during the contouring.