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    MOLD TOOL WITH ANISOTROPIC THERMAL PROPERTIES
    11.
    发明申请
    MOLD TOOL WITH ANISOTROPIC THERMAL PROPERTIES 审中-公开

    公开(公告)号：US20190084192A1

    公开(公告)日：2019-03-21

    申请号：US15710811

    申请日：2017-09-20

    Applicant: Bell Helicopter Textron Inc.

    Inventor： David G. Carlson

    IPC: B29C33/38

    Abstract: In one embodiment, a method may comprise heating a composite material into a viscous form, wherein the composite material comprises a thermoplastic and a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is randomly arranged within the thermoplastic. The method may further comprise extruding a plurality of strands of the composite material, wherein extruding the plurality of strands causes the plurality of reinforcement fibers within each strand to align. The method may further comprise arranging the plurality of strands of the composite material to form a mold tool, wherein the mold tool is configured to mold a composite structure at a heated temperature, and wherein the mold tool comprises an anisotropic thermal expansion property, wherein the anisotropic thermal expansion property is based on an orientation of the plurality of reinforcement fibers within the mold tool.

    SPAR FOR A COMPOSITE WING STRUCTURE
    13.
    发明申请
    SPAR FOR A COMPOSITE WING STRUCTURE 审中-公开

    公开(公告)号：US20170225765A1

    公开(公告)日：2017-08-10

    申请号：US15424588

    申请日：2017-02-03

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Douglas K. Wolfe ,  David G. Carlson ,  John R. McCullough ,  George R. Decker

    IPC: B64C3/18

    Abstract: In one aspect, there is provided a spar member for an aircraft wing including a support beam having an interior surface, an exterior surface, and opposing ends configured for an aircraft wing, the interior surface and exterior surface disposed between the opposing ends; and a first spar flange extending generally laterally from the exterior surface, the first spar flange configured for attachment with a first wing skin. The first spar flange can be an upper or lower spar flange. In some embodiments, the first spar flange is at an acute angle relative to the exterior surface of the support beam. In certain embodiments, the first spar flange is at an angle of from about 50 degrees to about 85 degrees relative to the exterior surface of the support beam.

    MOLD TOOL WITH ANISOTROPIC THERMAL PROPERTIES
    14.
    发明申请
    MOLD TOOL WITH ANISOTROPIC THERMAL PROPERTIES 有权

    公开(公告)号：US20210339431A1

    公开(公告)日：2021-11-04

    申请号：US17378232

    申请日：2021-07-16

    Applicant: Bell Helicopter Textron Inc.

    Inventor： David G. Carlson

    IPC: B29C33/38 ,  B29C33/40 ,  B29C70/46 ,  B29C70/20

    Abstract: One embodiment is an apparatus including a mold configured to manufacture a composite structure at a heated temperature. The mold includes a first mold tool configured to mold a first portion of the composite structure, wherein the first mold tool comprises a plurality of strands of a fiber-reinforced thermoplastic material, wherein the fiber-reinforced thermoplastic material comprises a thermoplastic embedded with a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is aligned within each strand of the plurality of strands; and an anisotropic thermal expansion property, wherein the anisotropic thermal expansion property is based on an orientation of the plurality of reinforcement fibers within the first mold tool; and a second mold tool configured to mold a second portion of the composite structure.

    Material dispensing systems
    15.
    发明授权
    Material dispensing systems 有权

    公开(公告)号：US11155048B2

    公开(公告)日：2021-10-26

    申请号：US16031452

    申请日：2018-07-10

    Applicant: Bell Helicopter Textron Inc.

    Inventor： David G. Carlson ,  Paul K. Oldroyd ,  George R. Decker ,  Doug K. Wolfe

    IPC: B29C70/38 ,  B29C70/34 ,  B64F5/10 ,  B65H16/00 ,  B65H16/02 ,  B29L31/30

    Abstract: A material dispensing system including a first frame and a first application head. The first application head supported by the first frame including a first bias ply assembly comprising a bias ply roll supported on a bias ply dispenser unit, the first bias ply assembly configured to pass bias ply material along a bias path; and a first non-bias ply assembly comprising a non-bias ply roll supported by a non-bias ply dispenser unit, the non-bias ply assembly configured to pass non-bias ply material along a non-bias path; wherein the bias path and the non-bias path are substantially parallel. Another aspect provides a material dispensing system including a first frame and a first application head supported thereby; and a second frame and a second application head supported thereby; wherein the first frame and the second frame move in an X direction during operation. Another aspect includes preparing a composite article.

    COMPOSITE WING STRUCTURE AND METHODS OF MANUFACTURE
    17.
    发明申请
    COMPOSITE WING STRUCTURE AND METHODS OF MANUFACTURE 审中-公开

    公开(公告)号：US20190143613A1

    公开(公告)日：2019-05-16

    申请号：US16244295

    申请日：2019-01-10

    Applicant: Bell Helicopter Textron Inc.

    Inventor： David G. Carlson ,  John R. McCullough ,  Douglas K. Wolfe ,  Andrew G. Baines ,  George R. Decker

    IPC: B29C70/34 ,  B29C70/54 ,  B29C70/06 ,  B29D99/00 ,  B29C35/02

    Abstract: In one aspect, there is a method of making a pre-cured laminate having a total number of plies in a mold, the mold having a cavity with a periphery defined by a forward edge, an aft edge, and outboard ends. The method includes selecting a first plurality of resin impregnated plies that continuously extend beyond the periphery of the cavity, the first plurality of resin impregnated plies includes at least 50 percent of the total number of plies; laying the plies in a mold; compacting the plies in a mold; and pre-curing the plies to form a pre-cured laminate, which can extend beyond the periphery of the cavity. In an embodiment, a pre-cured laminate includes a first plurality of resin impregnated plies that continuously extend beyond the periphery of the cavity.

    FIXED ENGINE AND ROTATING PROPROTOR ARRANGEMENT FOR A TILTROTOR AIRCRAFT
    19.
    发明申请
    FIXED ENGINE AND ROTATING PROPROTOR ARRANGEMENT FOR A TILTROTOR AIRCRAFT 有权
    固定发动机和转向架飞机的旋转安装机构

    公开(公告)号：US20150048213A1

    公开(公告)日：2015-02-19

    申请号：US13966678

    申请日：2013-08-14

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Brent C. Ross ,  David R. Bockmiller ,  John R. McCullough ,  David G. Carlson

    IPC: B64C27/26 ,  B64C27/28

    CPC classification number: B64C29/0033

    Abstract: A tiltrotor aircraft includes a fuselage; a wing member having a first rib, a second rib, a first spar, second spar; and an upper wing skin; an engine disposed at a fixed location relative to the wing member; and a proprotor having a spindle gearbox, rotor mast, and a plurality of rotor blades drivable in rotation about the rotor mast, the spindle gearbox being rotatable about a conversion axis. The spindle gearbox is located above the upper wing skin of the wing member.

    Abstract translation: 一架俯仰式飞机包括机身; 翼构件，具有第一肋，第二肋，第一翼梁，第二翼梁; 和上翼皮; 设置在相对于翼构件的固定位置的发动机; 以及具有主轴齿轮箱，转子桅杆和可围绕转子桅杆旋转驱动的多个转子叶片的推进器，所述主轴齿轮箱可围绕转换轴线旋转。 主轴齿轮箱位于机翼构件的上翼面上方。

    Mold tool with anisotropic thermal properties
    20.
    发明授权
    Mold tool with anisotropic thermal properties 有权

    公开(公告)号：US11123900B2

    公开(公告)日：2021-09-21

    申请号：US15710811

    申请日：2017-09-20

    Applicant: Bell Helicopter Textron Inc.

    Inventor： David G. Carlson

    IPC: B29C33/38 ,  B29C33/40 ,  B29C70/46 ,  B29C70/20 ,  B29C70/88 ,  B29C48/18

    Abstract: In one embodiment, a method may comprise heating a composite material into a viscous form, wherein the composite material comprises a thermoplastic and a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is randomly arranged within the thermoplastic. The method may further comprise extruding a plurality of strands of the composite material, wherein extruding the plurality of strands causes the plurality of reinforcement fibers within each strand to align. The method may further comprise arranging the plurality of strands of the composite material to form a mold tool, wherein the mold tool is configured to mold a composite structure at a heated temperature, and wherein the mold tool comprises an anisotropic thermal expansion property, wherein the anisotropic thermal expansion property is based on an orientation of the plurality of reinforcement fibers within the mold tool.

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