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    HEATING OPERATION PROCESS CONTROL
    1.
    发明申请
    HEATING OPERATION PROCESS CONTROL 有权

    公开(公告)号：US20220219411A1

    公开(公告)日：2022-07-14

    申请号：US17505875

    申请日：2021-10-20

    Applicant: THE BOEING COMPANY

    Inventor： Keith D. Humfeld ,  Geoffrey A. Butler ,  Karl M. Nelson

    IPC: B29C70/44 ,  B29C70/54 ,  G06N3/08

    Abstract: Heating operation control includes obtaining sensor data indicating measured temperatures within a heating vessel during a heating operation; determining sets of thermal stack parameters. Each set of candidate thermal stack parameters is descriptive of a respective configuration of a thermal stack modeled by a first machine learning model to generate one or more estimated tool temperature values. The thermal stack includes the tool and a part coupled to the tool. Heating operation control also includes determining a temperature profile for the heating operation. The temperature profile is determined, via a second machine learning model, based on the plurality of sets of thermal stack parameters and one or more process specifications of the thermal stack.

    Forming of staged thermoset composite materials
    2.
    发明授权
    Forming of staged thermoset composite materials 有权
    形成分级热固性复合材料

    公开(公告)号：US09539767B2

    公开(公告)日：2017-01-10

    申请号：US14561900

    申请日：2014-12-05

    Applicant: The Boeing Company

    Inventor： Geoffrey A. Butler

    IPC: B29C35/02 ,  B29C70/30 ,  B29C70/44 ,  B29C73/10 ,  B29C73/12 ,  B29C65/00 ,  B29K105/24

    CPC classification number: B29C70/30 ,  B29C35/02 ,  B29C35/0222 ,  B29C35/0288 ,  B29C66/73754 ,  B29C70/44 ,  B29C73/10 ,  B29C73/12 ,  B29C2793/0009 ,  B29C2795/002 ,  B29K2105/243

    Abstract: A method of forming a composite article may include initially curing a composite laminate at an initial temperature to an initial cure stage of 30-50 percent of full cure and beyond a gel point to form an initially-cured composite laminate. The method may initially include heating the initially-cured composite laminate to an intermediate temperature higher than the initial temperature and above a resin glass transition temperature. In addition, the method may include intermediately curing the composite laminate to an intermediate cure stage of 50-70 percent of full cure while on a final forming tool to form an intermediately-cured composite laminate. Furthermore, the method may include removing the intermediately-cured composite laminate from the final forming tool, and finally curing the intermediately-cured composite laminate at a final temperature higher than the intermediate temperature to a final cure stage.

    Abstract translation: 形成复合制品的方法可以包括在初始温度下将复合层压材料初始固化至完全固化的30-50％的初始固化阶段并超过凝胶点以形成初始固化的复合层压材料。 该方法可以最初包括将初始固化的复合层压体加热至高于初始温度并高于树脂玻璃化转变温度的中间温度。 此外，该方法可以包括将复合层压板固化到中间固化阶段，在最终成型工具上形成中间固化复合层压材料的50-70％的完全固化。 此外，该方法可以包括从最终成型工具中去除固化后的复合层压材料，最后在高于中间温度的最终温度下固化到最终固化阶段的中间固化的复合层压材料。

    METHOD FOR ACHIEVING LOW POROSITY IN COMPOSITE LAMINATES
    4.
    发明申请
    METHOD FOR ACHIEVING LOW POROSITY IN COMPOSITE LAMINATES 有权
    在复合层压板中实现低孔隙度的方法

    公开(公告)号：US20160257102A1

    公开(公告)日：2016-09-08

    申请号：US14636012

    申请日：2015-03-02

    Applicant: The Boeing Company

    Inventor： Geoffrey A. Butler

    IPC: B32B37/14 ,  B32B37/06 ,  B32B37/10

    CPC classification number: B32B37/1009 ,  B29C70/00 ,  B29C70/202 ,  B29C70/30 ,  B29C70/547 ,  B32B37/0076 ,  B32B37/02 ,  B32B37/1045 ,  B32B37/18 ,  B32B38/0004 ,  B32B2038/0076 ,  B32B2038/1891

    Abstract: A method of manufacturing a composite laminate may include laying up bands of composite material in layers to form a composite layup. At least one layer may have at least one gap between an adjacent pair of bands. The gap may extend continuously along a lengthwise direction of the band. The gap in two or more of the layers may be fluidly interconnected and may form at least one breather path that opens to an exterior of the composite layup.

    Abstract translation: 制造复合层压材料的方法可以包括层叠复合材料带，以形成复合叠层。 至少一个层可以在相邻的一对带之间具有至少一个间隙。 间隙可以沿带的长度方向连续延伸。 两个或更多个层中的间隙可以是流体互连的并且​​可以形成至少一个通向复合叠层外部的通气路径。

    System and method for a heating operation process control
    5.
    发明授权
    System and method for a heating operation process control 有权

    公开(公告)号：US12138867B2

    公开(公告)日：2024-11-12

    申请号：US17505875

    申请日：2021-10-20

    Applicant: THE BOEING COMPANY

    Inventor： Keith D. Humfeld ,  Geoffrey A. Butler ,  Karl M. Nelson

    IPC: G05B13/02 ,  B29C70/44 ,  B29C70/54 ,  G06N3/08

    Abstract: Heating operation control includes obtaining sensor data indicating measured temperatures within a heating vessel during a heating operation; determining sets of thermal stack parameters. Each set of candidate thermal stack parameters is descriptive of a respective configuration of a thermal stack modeled by a first machine learning model to generate one or more estimated tool temperature values. The thermal stack includes the tool and a part coupled to the tool. Heating operation control also includes determining a temperature profile for the heating operation. The temperature profile is determined, via a second machine learning model, based on the plurality of sets of thermal stack parameters and one or more process specifications of the thermal stack.

    Methods for Making Composite Parts from Stacked Partially Cured Sublaminate Units
    6.
    发明申请
    Methods for Making Composite Parts from Stacked Partially Cured Sublaminate Units 审中-公开

    公开(公告)号：US20190168481A1

    公开(公告)日：2019-06-06

    申请号：US15829780

    申请日：2017-12-01

    Applicant: The Boeing Company

    Inventor： Geoffrey A. Butler

    IPC: B32B3/26 ,  B32B7/12 ,  B32B37/12 ,  B32B37/06

    Abstract: A method of forming a composite article. One step involves applying adhesive on surfaces of a plurality of sublaminate units, each ply of each sublaminate unit comprising fibers impregnated with resin which has been initially cured to 30% to 50% of full cure. The initially cured sublaminate units are then arranged in a stack, which stack is pressed against a surface of a forming tool. While pressure is being applied, the stack is heated to an intermediate temperature above a glass transition temperature of the resin for a time interval sufficient to intermediately cure the resin to 50% to 70% of full cure to form a composite laminate having a contour defined by the surface of the forming tool. Then the resin is finally cured at a final temperature higher than the intermediate temperature.

    FORMING OF STAGED THERMOSET COMPOSITE MATERIALS
    7.
    发明申请
    FORMING OF STAGED THERMOSET COMPOSITE MATERIALS 有权
    标准热固性复合材料的成型

    公开(公告)号：US20160159057A1

    公开(公告)日：2016-06-09

    申请号：US14561900

    申请日：2014-12-05

    Applicant: The Boeing Company

    Inventor： Geoffrey A. Butler

    IPC: B32B37/06 ,  B32B37/10

    CPC classification number: B29C70/30 ,  B29C35/02 ,  B29C35/0222 ,  B29C35/0288 ,  B29C66/73754 ,  B29C70/44 ,  B29C73/10 ,  B29C73/12 ,  B29C2793/0009 ,  B29C2795/002 ,  B29K2105/243

    Abstract: A method of forming a composite article may include initially curing a composite laminate at an initial temperature to an initial cure stage of 30-50 percent of full cure and beyond a gel point to form an initially-cured composite laminate. The method may initially include heating the initially-cured composite laminate to an intermediate temperature higher than the initial temperature and above a resin glass transition temperature. In addition, the method may include intermediately curing the composite laminate to an intermediate cure stage of 50-70 percent of full cure while on a final forming tool to form an intermediately-cured composite laminate. Furthermore, the method may include removing the intermediately-cured composite laminate from the final forming tool, and finally curing the intermediately-cured composite laminate at a final temperature higher than the intermediate temperature to a final cure stage.

    Abstract translation: 形成复合制品的方法可以包括在初始温度下将复合层压材料初始固化至完全固化的30-50％的初始固化阶段并且超过凝胶点以形成初始固化的复合层压材料。 该方法可以最初包括将初始固化的复合层压体加热至高于初始温度并高于树脂玻璃化转变温度的中间温度。 此外，该方法可以包括将复合层压板固化到中间固化阶段，在最终成型工具上形成中间固化复合层压材料的50-70％的完全固化。 此外，该方法可以包括从最终成型工具中去除固化后的复合层压材料，最后在高于中间温度的最终温度下固化到最终固化阶段的中间固化的复合层压材料。

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