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公开(公告)号：US20200331634A1
公开(公告)日：2020-10-22
申请号：US16388791
申请日：2019-04-18
Applicant: The Boeing Company
Inventor： Samuel James Knutson , Brian Timothy Peters , Brian Bentley Reid , Byron James Autry , Raviendra Suriyaarachchi , James R. Kendall
Abstract: A method of fabricating a composite structure is presented. The method comprises laying up a plurality of composite plies over a layup mandrel; positioning a first caul plate and a second caul plate over the plurality of composite plies, leaving composite material exposed; removing at least part of the composite material exposed between the first caul plate and the second caul plate to separate a first composite section from a second composite section; curing the first composite section and the second composite section to form a first composite part and a second composite part; and removing the first composite part and the second composite part from the layup mandrel immediately following curing.
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公开(公告)号：US11872780B2
公开(公告)日：2024-01-16
申请号：US17805060
申请日：2022-06-02
Applicant: The Boeing Company
Inventor： Samuel James Knutson , Raviendra Sidath Suriyaarachchi
CPC classification number: B29C70/545 , B25J11/0055
Abstract: A method of cutting an uncured composite material is presented. The uncured composite material is positioned onto a surface of a tool and over a groove in the surface, the groove having a groove filler and magnetic material within the groove. A cutter having a guide is positioned relative to the uncured composite material, the guide configured to detect the magnetic material. The uncured composite material is cut above the groove using the cutter as the cutter moves along a path defined by the groove, the cutter guided by the guide detecting the magnetic material in the groove.
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公开(公告)号：US10831173B2
公开(公告)日：2020-11-10
申请号：US15675252
申请日：2017-08-11
Applicant: The Boeing Company
IPC: G05B19/19 , G05B19/402
Abstract: A method is presented. A machine head is positioned in a desired location relative to a material on a tool using a sensor connected to the machine head and calibrated to detect magnetic material in the tool. An operation is performed on the material using the machine head starting at the desired location.
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公开(公告)号：US11220353B2
公开(公告)日：2022-01-11
申请号：US16388791
申请日：2019-04-18
Applicant: The Boeing Company
Inventor： Samuel James Knutson , Brian Timothy Peters , Brian Bentley Reid , Byron James Autry , Raviendra Suriyaarachchi , James R. Kendall
Abstract: A method of fabricating a composite structure is presented. The method comprises laying up a plurality of composite plies over a layup mandrel; positioning a first caul plate and a second caul plate over the plurality of composite plies, leaving composite material exposed; removing at least part of the composite material exposed between the first caul plate and the second caul plate to separate a first composite section from a second composite section; curing the first composite section and the second composite section to form a first composite part and a second composite part; and removing the first composite part and the second composite part from the layup mandrel immediately following curing.
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公开(公告)号：US20190049919A1
公开(公告)日：2019-02-14
申请号：US15675252
申请日：2017-08-11
Applicant: The Boeing Company
IPC: G05B19/19 , G05B19/402
Abstract: A method is presented. A machine head is positioned in a desired location relative to a material on a tool using a sensor connected to the machine head and calibrated to detect magnetic material in the tool. An operation is performed on the material using the machine head starting at the desired location.
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Patent Agency Ranking
公开(公告)号：US20170252982A1
公开(公告)日：2017-09-07
申请号：US15060981
申请日：2016-03-04
Applicant: The Boeing Company
Inventor： Samuel James Knutson
CPC classification number: B29C70/021 , B29C33/308 , B29C53/02 , B29C70/342 , B29C70/44 , B29C70/56 , B29K2307/04 , B29L2009/00
Abstract: Systems and methods are provided for dynamically altering the shape of a forming tool for a composite part during forming. An exemplary forming tool includes a main body that holds a first portion of a multi-layer laminate, and a platform that holds a second portion of the laminate aligned with the first portion. The forming tool also includes a biasing device that repositions the second portion with respect to the first portion during forming of the laminate, causing shear stresses between the layers of the laminate.
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公开(公告)号：US11472136B2
公开(公告)日：2022-10-18
申请号：US16415952
申请日：2019-05-17
Applicant: The Boeing Company
Inventor： Samuel James Knutson , Brian Timothy Peters , Raviendra Suriyaarachchi , James R. Kendall , Paul D. Shaw
Abstract: A carrier film set configured to apply a number of stiffener assemblies to a layup mandrel, the carrier film set comprising: a number of alignment features configured to align the carrier film set relative to the layup mandrel; and a number of indexing features configured to index the number of stiffener assemblies onto the carrier film set.
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公开(公告)号：US20220194547A1
公开(公告)日：2022-06-23
申请号：US17480880
申请日：2021-09-21
Applicant: The Boeing Company
Inventor： Patrick J. Macko , Byron James Autry , James R. Kendall , Samuel James Knutson , Brian T. Peters , Michael J. Bailey , Matthew S. Stauffer , Steven Wanthal , Santiago M. Mejia , Sara Murphy
Abstract: Systems and methods are provided for splicing airframe components. One embodiment is a method for assembling an airframe of an aircraft. The method includes forming a first skin of a first circumferential section of fuselage, the first skin including a distal portion comprising a lip and a shoulder, aligning a second skin of a second circumferential section of fuselage with the shoulder such that the lip overlaps the second skin, and affixing the first skin and the second skin together via a circumferential splice.
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公开(公告)号：US10213968B2
公开(公告)日：2019-02-26
申请号：US15060981
申请日：2016-03-04
Applicant: The Boeing Company
Inventor： Samuel James Knutson
Abstract: Systems and methods are provided for dynamically altering the shape of a forming tool for a composite part during forming. An exemplary forming tool includes a main body that holds a first portion of a multi-layer laminate, and a platform that holds a second portion of the laminate aligned with the first portion. The forming tool also includes a biasing device that repositions the second portion with respect to the first portion during forming of the laminate, causing shear stresses between the layers of the laminate.
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公开(公告)号：US11919617B2
公开(公告)日：2024-03-05
申请号：US17480880
申请日：2021-09-21
Applicant: The Boeing Company
Inventor： Patrick J. Macko , Byron James Autry , James R. Kendall , Samuel James Knutson , Brian T. Peters , Michael J. Bailey , Matthew S. Stauffer , Steven Wanthal , Santiago M. Mejia , Sara Murphy
Abstract: Systems and methods are provided for splicing airframe components. One embodiment is a method for assembling an airframe of an aircraft. The method includes forming a first skin of a first circumferential section of fuselage, the first skin including a distal portion comprising a lip and a shoulder, aligning a second skin of a second circumferential section of fuselage with the shoulder such that the lip overlaps the second skin, and affixing the first skin and the second skin together via a circumferential splice.
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