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21.发明申请公开(公告)号：US20180065165A1
公开(公告)日：2018-03-08
申请号：US15256958
申请日：2016-09-06
Applicant: The Boeing Company
Inventor： Marc R. Matsen , David S. Nansen , Lee C. Firth , Gregory A. Foltz
IPC: B21D26/053 , B23K20/12 , B21D26/021
CPC classification number: B21D26/053 , B21D26/021 , B21D31/04 , B23K20/127 , B23K26/22 , B23K26/32 , B23K26/38 , B23K26/40 , B23K2101/006 , B23K2103/10 , B23K2103/14 , B23K2103/166 , B23K2103/26
Abstract: A method for forming a multilayer structure from a precursor panel having an edge, the method including steps of connecting an attachment member to the precursor panel such that an edge of the attachment member is in alignment with the edge of the precursor panel and applying heat and gas pressure to expand the precursor panel.
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公开(公告)号：US20170050229A1
公开(公告)日：2017-02-23
申请号：US14827711
申请日：2015-08-17
Applicant: The Boeing Company
Inventor： Marc R. Matsen , David S. Nansen , Lee C. Firth , Gregory A. Foltz
IPC: B21D26/031 , B21D37/16 , H05B6/10 , B21D26/029
CPC classification number: B21D26/031 , B21D26/029 , B21D26/055 , B21D26/059 , B21D37/16 , B21D47/02 , B21D47/04 , B32B15/01 , B32B15/011 , H05B6/105
Abstract: An apparatus for forming a panel, including a first face sheet, a second face sheet and a core sheet between the first face sheet and the second face sheet, may include a molding tool defining a forming cavity shaped to correspond to the panel, a heating system positioned adjacent to the forming cavity and configured to heat the forming cavity, and a pressurization system configured to pressurize a cavity volume between the tool and the panel and pressurize a panel volume between the first face sheet and the second face sheet.
Abstract translation: 一种用于形成面板的装置，包括在第一面板和第二面板之间的第一面板，第二面板和芯板，可以包括限定成形为对应于面板的成形腔的模制工具，加热 系统定位成邻近成形腔并被配置为加热成形腔;以及加压系统，其构造成对工具和面板之间的空腔体积加压并对第一面板和第二面板之间的面板容积加压。
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23.发明申请公开(公告)号：US20170036310A1
公开(公告)日：2017-02-09
申请号：US14818997
申请日：2015-08-05
Applicant: The Boeing Company
Inventor： Marc R. Matsen , Gregory J.S. Hickman , William C. Dykstra
CPC classification number: B29C33/06 , B29C70/44 , B29K2105/12 , B29K2105/256 , B29K2905/00 , B29K2905/12
Abstract: Described herein is a method of forming tooling used to form a material. The method includes positioning a first susceptor made from a first susceptor material between first and second dies. At least one of the first and second dies includes a forming surface having a desired shape. The method further includes positioning a second susceptor made from a second susceptor material between the first and second dies such that the first susceptor is interposed between the second susceptor and the forming surface. Additionally, the method includes positioning a first bladder between the first and second dies such that the second susceptor is interposed between the first bladder and the first susceptor. Also, the method includes inflating the first bladder to concurrently deform the first susceptor and second susceptor into the desired shape.
Abstract translation: 这里描述的是形成用于形成材料的模具的方法。 该方法包括将由第一基座材料制成的第一基座定位在第一和第二管芯之间。 第一和第二模具中的至少一个包括具有期望形状的成形表面。 该方法还包括将由第二基座材料制成的第二基座定位在第一和第二模具之间，使得第一基座插入在第二基座和成形表面之间。 此外，该方法包括将第一气囊定位在第一和第二模具之间，使得第二感受器插入在第一气囊和第一感受器之间。 而且，该方法还包括使第一气囊膨胀以使第一感受器和第二感受器同时变形成所需形状。
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24.发明授权Method of consolidating/molding near net-shaped components made from powders 有权由粉末制成的网状部件附近的固结/成型方法公开(公告)号：US09457404B2
公开(公告)日：2016-10-04
申请号：US13758609
申请日：2013-02-04
Applicant: The Boeing Company
Inventor： Marc R. Matsen , Mark Alan Negley , Robert James Miller
CPC classification number: H05B6/101 , B21D21/00 , B22F3/03 , B22F3/087 , B22F3/105 , B22F3/14 , B22F3/16 , B22F2003/1053 , B22F2202/05 , B22F2202/07 , B22F2203/00 , C21D1/18 , C21D1/42 , C21D6/00 , C21D9/42 , H05B6/06 , H05B6/08 , H05B6/105 , H05B2206/023 , Y02P10/253
Abstract: A method for consolidating a pre-form made of powder, comprising: (a) placing the pre-form between smart susceptors; (b) heating the smart susceptors to a leveling temperature by applying a varying low-strength magnetic field having a magnetic flux that passes through surfaces of the smart susceptors; (c) applying consolidation pressure to the pre-form at least during a time period subsequent to the temperature of the smart susceptors reaching the leveling temperature; and (d) while consolidation pressure is being applied, applying a pulsed high-strength magnetic field having a magnetic flux that passes through a surface of the pre-form. The strength and pulse rate of the high-strength magnetic field are selected so that the crystallographic phase of the pre-form will rapidly oscillate at a substantially constant temperature. The pulsed high-strength magnetic field is applied sufficiently long that superplasticity of the pre-form is attained during phase oscillation.
Abstract translation: 一种用于固结由粉末制成的预制件的方法，包括：（a）将所述预成型件置于智能基座之间; （b）通过施加具有穿过所述智能基座的表面的磁通量的变化的低强度磁场，将所述智能感受器加热到平整温度; （c）至少在智能感受器的温度达到调平温度之后的一段时间内对固化压力施加固化压力; 和（d）在施加固结压力的同时，施加具有穿过预成型件表面的磁通量的脉冲高强度磁场。 选择高强度磁场的强度和脉冲速率，使得预成型体的结晶相在基本恒定的温度下快速振荡。 脉冲高强度磁场施加足够长，使得在相位振荡期间获得预制件的超塑性。
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公开(公告)号：US09314975B1
公开(公告)日：2016-04-19
申请号：US13870111
申请日：2013-04-25
Applicant: The Boeing Company
Inventor： Marc R. Matsen , Mark A. Negley , William C. Dykstra , Glen L. Smith , Robert J. Miller
CPC classification number: B29C70/345 , B29C33/06 , B29C35/0805 , B29C43/18 , B29C43/52 , B29C51/082 , B29C51/421 , B29C70/42 , B29C70/46 , B29C70/54 , B29C2035/0811 , B29C2043/568 , B29C2043/5816 , B29K2105/06 , B29K2105/0872
Abstract: A method for fabricating a thermoplastic composite component comprises inductively heating a thermoplastic pre-form with a first induction coil by inducing current to flow in susceptor wires disposed throughout the pre-form, inductively heating smart susceptors in a molding tool to a leveling temperature with a second induction coil by applying a high-strength magnetic field having a magnetic flux that passes through surfaces of the smart susceptors, shaping the magnetic flux that passes through surfaces of the smart susceptors to flow substantially parallel to a molding surface of the smart susceptors, placing the heated pre-form between the heated smart susceptors; and applying molding pressure to the pre-form to form the composite component.
Abstract translation: 一种制造热塑性复合材料组件的方法包括：通过将设置在整个预成型件中的基座导线中的电流感应电流流动到具有第一感应线圈的热塑性预成型件，将模制工具中的智能感应器感应加热至具有调平温度的 通过施加具有穿过所述智能基座的表面的磁通量的高强度磁场，使穿过所述智能基座的表面的磁通量成形为基本上平行于所述智能基座的模制表面流动的第二感应线圈，放置 加热的智能感受器之间的加热预成型件; 并将成型压力施加到预成型件以形成复合部件。
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Patent Agency Ranking
公开(公告)号：US08708691B2
公开(公告)日：2014-04-29
申请号：US13722670
申请日：2012-12-20
Applicant: The Boeing Company
Inventor： Marc R. Matsen , Kim E. Peterson , William Dykstra
CPC classification number: B29C45/78 , B29C33/06 , B29C33/302 , B29C35/0805 , B29C35/16 , B29C70/48 , B29C70/54 , B29C2035/0811 , B29C2035/1616 , B29C2035/1658 , B29C2035/1691 , D06N3/00 , Y10T442/20
Abstract: A composite fabrication apparatus which may include a first tooling die and a second tooling die movable with respect to each other; a temperature control system having induction coils disposed in thermal contact with the first tooling die and the second tooling die; a first die susceptor provided on the first tooling die and a second die susceptor provided on the second tooling die and connected to the induction coils; and a cooling system disposed in thermal contact with the first tooling die and the second tooling die. A resin transfer system delivers resin from a resin source to the tooling dies to allow resin transfer molding. A composite fabrication method is also disclosed.
Abstract translation: 一种复合制造装置，其可以包括可相对于彼此移动的第一工具模具和第二模具模具; 温度控制系统，其具有与所述第一模具模具和所述第二模具模具热接触地设置的感应线圈; 设置在第一模具上的第一模具基座和设置在第二模具上并连接到感应线圈的第二模具基座; 以及与所述第一工具模具和所述第二工具模具热接触地设置的冷却系统。 树脂转移系统将树脂从树脂源输送到模具以允许树脂传递模塑。 还公开了复合制造方法。
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公开(公告)号：US20250100205A1
公开(公告)日：2025-03-27
申请号：US18474073
申请日：2023-09-25
Applicant: The Boeing Company
Inventor： Marc R. Matsen , Randall D. Wilkerson , Gwendolyn M. Janda
Abstract: A tool for stamp-forming thermoplastic components may include a frame reinforced by an infill material. The infill material (e.g., cast ceramic) is configured to provide compression resistance to the frame and to insulate the frame from heat. A forming plate is coupled to the frame, and the plate has a front face defining a forming surface of the tool. One or more inductive heating elements are configured to heat the plate, wherein each of the one or more inductive heating elements comprises a conductor (e.g., Litz wire) coupled to a susceptor material (e.g., Invar®), and the one or more inductive heating elements are configured to be self-regulating with respect to temperature.
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公开(公告)号：US11987353B2
公开(公告)日：2024-05-21
申请号：US17659671
申请日：2022-04-19
Applicant: The Boeing Company
Inventor： Jeffery Lee Marcoe , Marc R. Matsen , Waeil M. Ashmawi , Sahrudine Apdalhaliem
IPC: B64C3/26 , B29C35/08 , B29C70/68 , B29K101/12 , B29K105/08 , B29L31/30
CPC classification number: B64C3/26 , B29C35/0805 , B29C70/685 , B29C2035/0811 , B29K2101/12 , B29K2105/0809 , B29L2031/3085
Abstract: Stiffened skin panels comprise alternating truss core portions and solid laminate portions sandwiched between inner and outer facesheets, all formed from a fiber reinforced thermoplastic. The components of the panels are co-consolidated using induction heating. The panels are stiffened with spars fastened to the solid laminate portions.
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公开(公告)号：US11724420B2
公开(公告)日：2023-08-15
申请号：US16204260
申请日：2018-11-29
Applicant: The Boeing Company
Inventor： Marc R. Matsen , Lee Charles Firth , Randall D. Wilkerson , Julie F. Murphy , Ravi Verma
IPC: B29C33/38 , B21D26/031 , B33Y10/00 , B33Y80/00 , B29C70/42
CPC classification number: B29C33/3842 , B21D26/031 , B29C70/42 , B29K2905/00 , B33Y10/00 , B33Y80/00
Abstract: Systems and methods are provided for creating precursors for consolidating composite parts. One embodiment is a method for forming a metallic structure. The method includes forming a precursor for a pressure membrane that includes a contour having a linearized length corresponding with a linearized length of a surface of a forming tool. The method also includes affixing a perimeter of the precursor to a perimeter of a base member, leaving a volume between the base member and the precursor, altering a shape of the precursor at a superplastic temperature by forcing the precursor into complementary contact with the surface of the forming tool, and setting the shape of the precursor while the precursor is held in complementary contact.
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公开(公告)号：US20230060515A1
公开(公告)日：2023-03-02
申请号：US17460835
申请日：2021-08-30
Applicant: The Boeing Company
Inventor： Kurtis S. Willden , Marc R. Matsen
Abstract: A composite forming apparatus includes an end effector, a forming feature that is coupled to the end effector, and a heating element that is coupled to the forming feature to heat the forming feature. The end effector moves the forming feature relative to a composite ply to form the composite ply over a forming tool or over a prior formed composite ply. The forming feature heats the composite ply via conduction.
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