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公开(公告)号：US11806954B2
公开(公告)日：2023-11-07
申请号：US17644285
申请日：2021-12-14
Applicant: The Boeing Company
Inventor： Gagandeep Saini , Ian Edward Schroeder , Kurtis Shuldberg Willden , Lisa Christina Carlson
CPC classification number: B29C70/549 , B29C70/462 , B29D99/0003 , B29L2009/00 , B29L2031/001
Abstract: 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.
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公开(公告)号：US11806947B2
公开(公告)日：2023-11-07
申请号：US17583165
申请日：2022-01-24
Applicant: The Boeing Company
CPC classification number: B29C70/38 , B29C70/446 , B29C70/541 , B29D99/0003 , B29L2031/3076
Abstract: There is provided a forming system for forming a contoured composite structure having a complex curved configuration. The forming system includes a receiving station having a receiving assembly to receive a composite charge to be formed. The forming system includes a forming station having a forming assembly. The forming assembly includes a gantry assembly, an upper die assembly movably coupled to the gantry assembly, a lower die assembly coupled to a floor support beam positioned between the gantry assembly, and one or more pick-and-place devices movably coupled to the gantry assembly. The upper die assembly is separate from, and independently movable with respect to, the lower die assembly. The pick-and-place device(s) are designed to move the composite charge, and the contoured composite structure. The forming system includes a tray station having a tray assembly designed to receive the contoured composite structure from the forming station.
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公开(公告)号：US11795705B1
公开(公告)日：2023-10-24
申请号：US17816683
申请日：2022-08-01
Applicant: Amundson Technology, LLC
Inventor： Gregory A. Amundson
IPC: B29C48/21 , B29C48/22 , E04F19/06 , B29C48/12 , E04F19/04 , A47K3/00 , E04B1/68 , B29L31/00 , B29C48/20 , B29L31/26 , B29C48/16 , B29L9/00 , B32B27/06 , B29C48/03 , B32B7/04 , B29D99/00 , B32B1/04 , B32B27/04
CPC classification number: E04F19/064 , B29C48/12 , B29C48/21 , B29C48/22 , A47K3/008 , B29C48/03 , B29C48/16 , B29C48/20 , B29D99/0003 , B29D99/0053 , B29L2009/00 , B29L2031/003 , B29L2031/26 , B32B1/04 , B32B7/04 , B32B27/04 , B32B27/06 , E04B1/6803 , E04F19/04 , E04F19/045 , E04F19/0477 , E04F2019/0404 , E04F2019/0422 , E04F2019/0431 , E04F2019/0454 , Y10T428/139 , Y10T428/24479 , Y10T428/24488 , Y10T428/24777 , Y10T428/28 , Y10T428/2852
Abstract: A trim piece for sealing a work surface including a body having a first side, a second side, and a span disposed between the first side and the second side, wherein the first side and the second side are joined at a junction defining an angle between the first side and the second side of between 80 degrees and 100 degrees, a topcap is affixed to the span of the body, wherein the topcap includes a left side having a first wing and a right side having a second wing, an adhesive is bonded to the first side of the body and an aperture is disposed within the body.
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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.
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公开(公告)号：US20230182417A1
公开(公告)日：2023-06-15
申请号：US17644285
申请日：2021-12-14
Applicant: The Boeing Company
Inventor： Gagandeep Saini , Ian Edward Schroeder , Kurtis Shuldberg Willden , Lisa Christina Carlson
CPC classification number: B29C70/549 , B29C70/462 , B29D99/0003 , B29L2031/001
Abstract: 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.
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Patent Agency Ranking
6.发明申请公开(公告)号：US20190232576A1
公开(公告)日：2019-08-01
申请号：US16382288
申请日：2019-04-12
Applicant: BOMBARDIER INC.
Inventor： Louis FERNANDES , Thomas RIGUIDEL
CPC classification number: B29C70/446 , B29C35/0805 , B29C43/3642 , B29C70/548 , B29C2035/0822 , B29C2043/3644 , B29D99/0003 , B29K2307/04 , B29K2313/00 , B29K2823/06 , B29K2995/0027 , B29K2995/0077 , B29K2995/0081 , B29L2031/3076
Abstract: A method for forming a shaped composite structure. The method includes laying a composite laminate stack onto a mold, where the composite laminate stack comprises fabric laminate and resin and wherein the mold presents a predetermined shape, draping a vacuum film comprising polyethylene onto the composite laminate stack, thereby establishing an evacuatable volume between the vacuum film and the mold, applying suction to the evacuatable volume between the mold and the vacuum film to establish at least a partial vacuum within the evacuatable volume, thereby compressing the composite laminate stack via pressure applied to the vacuum film responsive to the at least partial vacuum within the evacuatable volume, and heating the composite laminate stack while applying suction to the evacuatable volume, thereby at least partially consolidating the laminate stack.
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公开(公告)号：US20180319051A1
公开(公告)日：2018-11-08
申请号：US15649162
申请日：2017-07-13
Applicant: The Boeing Company
Inventor： Richard E. Heath , Andrew Elmer Modin , Richard Alexander Prause
CPC classification number: B29D99/0003 , B29C33/505 , B29C70/342 , B29D99/0014
Abstract: An illustrative embodiment of the present disclosure provides a method of manufacturing a composite structure. A composite material having a closed cross-section or a partially closed cross-section is cured to form the composite structure, wherein the composite material is in contact with a foam mandrel assembly when curing begins. A supportive foam mandrel in the foam mandrel assembly is collapsed during curing.
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公开(公告)号：US10016934B2
公开(公告)日：2018-07-10
申请号：US15225823
申请日：2016-08-01
Applicant: The Boeing Company
Inventor： Donald J. Sutkus , Sandie H. Cheung Hallman , Courtney M. Fix , Douglas A. McCarville
CPC classification number: B29C65/70 , B29C70/52 , B29C70/526 , B29D99/0003 , B29D99/0007 , B32B38/0004 , B32B38/0012 , B32B38/10 , B32B2305/076 , B32B2605/18 , Y10T156/1008
Abstract: A composite radius filler having a varying cross-sectional shape is pre-conditioned before being pultruded through forming dies. The composite filler radius filler includes a tab ply having a varying width that is laminated onto a supporting, full width base ply.
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公开(公告)号：US09944025B2
公开(公告)日：2018-04-17
申请号：US14982039
申请日：2015-12-29
Applicant: AIRBUS OPERATIONS, S.L.
Inventor： Gabriel Cruzado Parla , Pablo Lopez Fernandez , Aitor Echevarria Hernandez , Alberto Martinez Cerezo , Alberto Mulas De Lamo , Maria Mora Medias
CPC classification number: B29C70/382 , B29C70/345 , B29C70/386 , B29C70/545 , B29D99/0003 , B29L2031/06
Abstract: The disclosure refers to a method for manufacturing rod-shaped components of composite material, for example rowings or fillers, wherein a laminate is layered by automatically laying up a plurality of plies of composite material, which is then cut in an automated machine to obtain a plurality of rods having substantially the same cross-sectional shape. The obtained rods are then simultaneously conformed by applying heat and pressure to obtain rods with the desired cross-sectional shape. With the method of the disclosure, a large number of these types of components are produced with improved quality and in a very simple manner, using the machinery and equipment already commonly existing in a factory of aeronautic components.
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10.发明申请公开(公告)号：US20180029313A1
公开(公告)日：2018-02-01
申请号：US15127097
申请日：2015-03-18
Applicant: Bombardier Inc.
Inventor： Louis LABERGE LEBEL , Matei DRAGUTESCU , Paul TRUDEAU , Gaetan NORMANDIN , Mouhcine RIFAY
CPC classification number: B29C70/30 , B29C70/205 , B29C70/226 , B29C70/541 , B29C70/543 , B29C70/56 , B29D99/0003 , Y10T156/1028 , Y10T156/103
Abstract: A method and device of positioning a ply of material for a composite component along an arcuate surface are presented. The ply comprises two end portions and a plurality of fiber tows extending longitudinally between the two end portions. The arcuate surface has a curved edge and a planar surface extending from the curved edge. The method comprises placing a first longitudinal edge portion of the ply along the curved edge; and rotating at least one of the two end portions away from the arcuate surface about a pivot axis normal to the ply, so as to cause sliding of at least some of the plurality of fiber tows relative to each other, and substantial aligning of the plurality of fiber tows in a curved direction along the arcuate surface. A method of positioning a ply of material for a composite component onto a curved mandrel is also presented.
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