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    Composite structure having a stabilizing element
    104.
    发明授权
    Composite structure having a stabilizing element 有权
    具有稳定元件的复合结构

    公开(公告)号：US09517594B2

    公开(公告)日：2016-12-13

    申请号：US13644628

    申请日：2012-10-04

    Applicant: The Boeing Company

    Inventor： Marc R. Matsen ,  Mark A. Negley

    IPC: B29C70/34 ,  B29C70/54

    CPC classification number: B29C70/34 ,  B29C70/543 ,  Y02T50/43 ,  Y10T156/10 ,  Y10T428/24562

    Abstract: A composite structure may include a laminate and a stabilizing element. The laminate may have a plurality of composite plies. The composite structure may include a geometric discontinuity that may be associated with the laminate. The stabilizing element may be included with the composite plies and may be located proximate the geometric discontinuity.

    Abstract translation: 复合结构可以包括层压板和稳定元件。 层压板可以具有多个复合层。 复合结构可以包括可以与层压板相关联的几何不连续性。 稳定元件可以包括在复合层中，并且可以位于几何不连续处附近。

    Double Vacuum Debulk Processing
    105.
    发明公开
    Double Vacuum Debulk Processing 审中-公开

    公开(公告)号：US20240140053A1

    公开(公告)日：2024-05-02

    申请号：US18491222

    申请日：2023-10-20

    Applicant: The Boeing Company

    Inventor： John F. Spalding ,  Marc R. Matsen ,  Gwendolyn Marie Janda ,  Karl Marius Nelson ,  Bret Alan Mcginness Voss

    IPC: B29C70/44

    CPC classification number: B29C70/44 ,  B29K2105/0872

    Abstract: Methods and a double vacuum processing system are presented. A method of performing a double vacuum debulk and cure on a composite laminate is presented. A composite laminate is heated to begin a double vacuum debulk of the composite laminate while vacuum is pulled in a first vacuum zone containing the composite laminate and a second vacuum zone containing the first vacuum zone. Pressure within the second vacuum zone is increased to above atmospheric pressure. Heating the composite laminate is continued to complete a cure cycle for the composite laminate while the second vacuum zone is above atmospheric pressure.

    Induction cookware with bi-metallic smart susceptor
    106.
    发明授权
    Induction cookware with bi-metallic smart susceptor 有权

    公开(公告)号：US11576235B2

    公开(公告)日：2023-02-07

    申请号：US16442415

    申请日：2019-06-14

    Applicant: The Boeing Company

    Inventor： Marc R. Matsen ,  Landon K. Henson

    IPC: H05B6/12 ,  H05B6/06 ,  A47J27/00 ,  A47J36/02

    Abstract: Cookware, and an induction cooking system including the cookware, include a container, a base layer, and a susceptor layer. The container and the base layer are non-magnetic at room temperature, while the susceptor layer is magnetic at room temperature and has a Curie temperature at which the susceptor layer becomes non-magnetic. During heating of a material within the container, the base layer functions as a passive heat exchange to transfer heat across the susceptor layer. Further, during the heating, the base layer conducts an electric current when the susceptor layer approaches a leveling temperature and/or the Curie temperature of the susceptor layer, thereby decreasing an amount of heat produced and resulting in a more even heating of the material.

    Induction forming and curing of thermoset composite charges
    107.
    发明授权
    Induction forming and curing of thermoset composite charges 有权

    公开(公告)号：US11541575B2

    公开(公告)日：2023-01-03

    申请号：US17026066

    申请日：2020-09-18

    Applicant: The Boeing Company

    Inventor： Marc R. Matsen ,  Timothy J. Luchini ,  Bret A. Voss ,  Christopher J. Hottes

    IPC: B29C33/06 ,  B29C35/08 ,  B29C70/44 ,  B30B5/02 ,  B29K101/10

    Abstract: A first tooling die and a second tooling die are movable with respect to each other. The first tooling die and the second tooling die form a die cavity. The first tooling die and the second tooling die comprise a plurality of stacked metal sheets. A plurality of air gaps is defined between adjacent stacked metal sheets. A first smart susceptor material is within the die cavity and connected to the first tooling die. The first smart susceptor material has a first Curie temperature. A second smart susceptor material is within the die cavity and associated with the second tooling die. The second smart susceptor material has a second Curie temperature lower than the first Curie temperature. A flexible membrane is between the second tooling die and the first smart susceptor material. The flexible membrane is configured to receive pressure.

    Smart susceptor induction heating apparatus and methods having improved temperature control
    108.
    发明授权
    Smart susceptor induction heating apparatus and methods having improved temperature control 有权

    公开(公告)号：US11485053B2

    公开(公告)日：2022-11-01

    申请号：US16201612

    申请日：2018-11-27

    Applicant: The Boeing Company

    Inventor： Bret A. Voss ,  Marc R. Matsen ,  Jeffrey H. Olberg ,  James R. Jones

    IPC: B29C35/08 ,  H05B6/06 ,  H05B6/10 ,  H05B6/44 ,  B29K101/12

    Abstract: Heating apparatus and methods for thermally processing a part including improved control of temperature. A thermal management system is coupled to a back surface of a table thermally coupled to an inductive heating circuit. The thermal management system includes a chamber defining an interior space, at least one cooling fin disposed within the chamber, an inlet extending through the chamber and fluidly communicating with the interior space, and an outlet extending through the chamber and fluidly communicating with the interior space. In some applications, an air source fluidly communicates with the inlet and is selectively operable to generate an air flow through the chamber, so that the thermal management system may be selectively operated in an insulator mode and a cooling mode.

    METHOD AND APPARATUS FOR FORMING A COMPOSITE FUSELAGE STRUCTURE
    110.
    发明申请
    METHOD AND APPARATUS FOR FORMING A COMPOSITE FUSELAGE STRUCTURE 有权

    公开(公告)号：US20210187874A1

    公开(公告)日：2021-06-24

    申请号：US16718709

    申请日：2019-12-18

    Applicant: The Boeing Company

    Inventor： Jeffery Lee Marcoe ,  Marc R. Matsen

    IPC: B29C70/34 ,  B29C70/54

    Abstract: A method and apparatus for forming a composite structure. A stackup comprising a plurality of overbraided thermoplastic members and an overbraided thermoplastic skin is built. The stackup is placed between an inner tooling and an outer tooling. The inner tooling, the stackup, and the outer tooling are held in place together using a load constraint. The inner tooling, the stackup, the outer tooling, and the load constraint form a consolidation setup. The consolidation setup is heated to form the composite structure.

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