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    COMPOSITE WING STRUCTURE AND METHODS OF MANUFACTURE
    1.
    发明公开
    COMPOSITE WING STRUCTURE AND METHODS OF MANUFACTURE 审中-公开

    公开(公告)号：EP3616892A1

    公开(公告)日：2020-03-04

    申请号：EP19196833.8

    申请日：2017-02-06

    Applicant: Bell Helicopter Textron Inc.

    Inventor： CARLSON, David G. ,  McCULLOUGH, John R. ,  DECKER, George R. ,  WOLFE, Douglas K. ,  BAINES, Andrew G.

    IPC: B29C70/88 ,  B29D99/00 ,  B29C70/30 ,  B64C3/18 ,  B64C3/26 ,  B64C29/00 ,  B29C70/54

    Abstract: A method of making a composite skin (199) for a tiltrotor aircraft includes providing a first skin (201) in a mold (220), the first skin (201) having a periphery (201p) defined by a forward edge (201a), an aft edge (201b), and outboard ends (201c, 201d); providing a plurality of honeycomb panels (203) having an array of large cells (205) onto the first skin (201), each cell having a width of at least 1 cm; assembling the plurality of honeycomb panels (203) along the longitudinal axis of the first skin (201) to form a honeycomb core (207) having an outer perimeter (207p) within the periphery (201p) of the first skin (201); positioning a plurality of filler members (209) between the plurality of honeycomb panels and positioning a plurality of filler members on outboard ends of the honeycomb core, wherein each of the filler members is butt jointed to the respective adjacent honeycomb panel; positioning a second skin (211) onto the honeycomb core (207), the second skin (211) having an outer perimeter (211p) within the periphery (201p) of the first skin (201); and curing an adhesive to create a bond between the first skin (201), the honeycomb core (207), and the second skin (211) to form a composite skin (199).

    COMPOSITE WING STRUCTURE AND METHODS OF MANUFACTURE
    3.
    发明公开
    COMPOSITE WING STRUCTURE AND METHODS OF MANUFACTURE 审中-公开

    公开(公告)号：EP3584067A2

    公开(公告)日：2019-12-25

    申请号：EP19189692.7

    申请日：2017-02-06

    Applicant: Bell Helicopter Textron Inc.

    Inventor： CARLSON, David G. ,  McCULLOUGH, John R. ,  DECKER, George R. ,  WOLFE, Douglas K. ,  STANNEY, Keith A.

    IPC: B29C70/54

    Abstract: A method of manufacturing a tiltrotor wing structure (109) including providing a spar mold (402) having a plurality of bores (410) extending from an exterior surface (402e) of the mold (402) to an interior surface (402i) of the mold (402), the plurality of bores (410) corresponding to a plurality of primary coordination holes (422) in a spar member (418), the spar mold (402) having a periphery (406p) defined by a top edge (406t), a bottom edge (406b) and outboard ends (406c, 406d); selecting a plurality of resin impregnated plies (412) to ensure that the plies (412) continuously extend beyond the periphery (406p) of the spar mold (402); laying the plies (412) in the spar mold (402); curing the plies (412) in the mold (402) to form a cured spar member (418) that extends beyond the periphery (406p) of the spar mold (402); and accurately drilling a plurality of primary coordination holes (422) in the cured spar member (418) in the spar mold (402) using a tool (417) positioned in the plurality of bores (410).

    METHOD OF MAKING A LAMINATE
    4.
    发明公开
    METHOD OF MAKING A LAMINATE 审中-公开

    公开(公告)号：EP3584066A1

    公开(公告)日：2019-12-25

    申请号：EP19189691.9

    申请日：2017-02-06

    Applicant: Bell Helicopter Textron Inc.

    Inventor： CARLSON, David G. ,  McCULLOUGH, John R. ,  OLDROYD, Paul K. ,  MAY, Carl A. ,  KOOIMAN, James E.

    IPC: B29C70/30

    Abstract: In one aspect, there is a method of making a pre-cured laminate having a total number of plies in a mold (190), the mold (190) having a periphery (198) defined by a forward edge (198a), an aft edge (198b), and outboard ends (198c, 198d). The method includes selecting a first plurality of resin impregnated plies (173) that continuously extend beyond the periphery (189) of the mold (190), the first plurality of resin impregnated plies (173) includes at least 50 percent of the total number of plies; laying the plies in a mold (190); compacting the plies in a mold (190); and pre-curing the plies to form a pre-cured laminate, which can extend beyond the periphery (198) of the mold (190). In an embodiment, a pre-cured laminate includes a first plurality of resin impregnated plies (173) that continuously extend beyond the periphery (198) of the mold (190), the first plurality of resin impregnated plies (173) includes at least 50 percent of the total number of plies.

    COMPOSITE WING STRUCTURE AND METHODS OF MANUFACTURE
    5.
    发明公开
    COMPOSITE WING STRUCTURE AND METHODS OF MANUFACTURE 审中-公开
    复合翼结构和制造方法

    公开(公告)号：EP3208187A1

    公开(公告)日：2017-08-23

    申请号：EP17155027.0

    申请日：2017-02-07

    Applicant: Bell Helicopter Textron Inc.

    Inventor： CARLSON, David G. ,  McCULLOUGH, John R. ,  DECKER, George R. ,  WOLFE, Douglas K. ,  BAINES, Andrew G.

    IPC: B64C3/24 ,  B29C70/30 ,  B61C1/12 ,  B64F5/10 ,  B64C1/12

    CPC classification number: B29C70/34 ,  B29C35/02 ,  B29C65/48 ,  B29C70/06 ,  B29C70/30 ,  B29C70/545 ,  B29C2793/009 ,  B29D99/001 ,  B29D99/0089 ,  B29L2031/3076 ,  B29L2031/3085 ,  B32B3/12 ,  B32B7/12 ,  B32B2250/05 ,  B32B2305/024 ,  B32B2605/18 ,  B64C1/12 ,  B64C3/24 ,  B64C3/26 ,  B64C29/0033 ,  B64F5/10 ,  Y02T50/43

    Abstract: In one aspect, there is a method of making a pre-cured laminate having a total number of plies in a mold (190), the mold (190) having a periphery (198) defined by a forward edge (198a), an aft edge (198b), and outboard ends (198c, 198d). The method includes selecting a first plurality of resin impregnated plies (173) that continuously extend beyond the periphery (189) of the mold (190), the first plurality of resin impregnated plies (173) includes at least 50 percent of the total number of plies; laying the plies in a mold (190); compacting the plies in a mold (190); and pre-curing the plies to form a pre-cured laminate, which can extend beyond the periphery (198) of the mold (190). In an embodiment, a pre-cured laminate includes a first plurality of resin impregnated plies (173) that continuously extend beyond the periphery (198) of the mold (190), the first plurality of resin impregnated plies (173) includes at least 50 percent of the total number of plies.

    Abstract translation: 在一个方面中，存在一种制造在模具（190）中具有总数量的层的预固化层压体的方法，所述模具（190）具有由前边缘（198a）限定的周边（198），尾部 边缘（198b）和外侧端（198c，198d）。 该方法包括选择连续延伸超过模具（190）的周边（189）的第一多个树脂浸渍帘布层（173），第一多个树脂浸渍帘布层（173）包括总数量的至少50％ 帘布层; 将所述层放置在模具（190）中; 在模具（190）中压实层片; 并预固化这些层以形成可以延伸超过模具（190）的周边（198）的预固化层压材料。 在一个实施例中，预固化的层压件包括连续延伸超过模具（190）的周边（198）的第一多个树脂浸渍层（173），第一多个树脂浸渍层（173）包括至少50 层数总数的百分比。

    MOLD TOOL WITH ANISOTROPIC THERMAL PROPERTIES
    6.
    发明公开
    MOLD TOOL WITH ANISOTROPIC THERMAL PROPERTIES 审中-公开

    公开(公告)号：EP3459702A1

    公开(公告)日：2019-03-27

    申请号：EP17198419.8

    申请日：2017-10-25

    Applicant: Bell Helicopter Textron Inc.

    Inventor： CARLSON, David G.

    IPC: B29C33/40 ,  B29C64/118 ,  B29C70/30

    Abstract: The method comprises heating a composite material into a viscous form, wherein the composite material comprises a thermoplastic (216) and a plurality of reinforcement fibers (217), wherein the plurality of reinforcement fibers (217) is randomly arranged within the thermoplastic (216). The method further comprises extruding a plurality of strands (215) of the composite material, wherein extruding the plurality of strands (215) causes the plurality of reinforcement fibers (217) within each strand (215) to align. The method further comprises arranging the plurality of strands (215) of the composite material to form a mold tool (300), wherein the mold tool (300) is configured to mold a composite structure at a heated temperature, and wherein the mold tool (300) comprises an anisotropic thermal expansion property, wherein the anisotropic thermal expansion property is based on an orientation of the plurality of reinforcement fibers (217) within the mold tool (300).

    COMPOSITE WING STRUCTURE AND METHODS OF MANUFACTURE
    7.
    发明公开
    COMPOSITE WING STRUCTURE AND METHODS OF MANUFACTURE 审中-公开
    复合翼结构和制造方法

    公开(公告)号：EP3210882A1

    公开(公告)日：2017-08-30

    申请号：EP17155085.8

    申请日：2017-02-07

    Applicant: Bell Helicopter Textron Inc.

    Inventor： CARLSON, David G. ,  McCULLOUGH, John R. ,  DECKER, George R. ,  WOLFE, Douglas K. ,  STANNEY, Keith A.

    IPC: B64C3/18 ,  B29C45/37 ,  B64C3/24 ,  B64F5/10

    CPC classification number: B64C3/185 ,  B29C70/34 ,  B29C70/545 ,  B29L2031/3076 ,  B64C3/24 ,  B64F5/10 ,  Y02T50/43

    Abstract: A method of manufacturing a tiltrotor wing structure (109) including providing a spar mold (402) having a plurality of bores (410) extending from an exterior surface (402e) of the mold (402) to an interior surface (402i) of the mold (402), the plurality of bores (410) corresponding to a plurality of primary coordination holes (422) in a spar member (418), the spar mold (402) having a periphery (406p) defined by a top edge (406t), a bottom edge (406b) and outboard ends (406c, 406d); selecting a plurality of resin impregnated plies (412) to ensure that the plies (412) continuously extend beyond the periphery (406p) of the spar mold (402); laying the plies (412) in the spar mold (402); curing the plies (412) in the mold (402) to form a cured spar member (418) that extends beyond the periphery (406p) of the spar mold (402); and accurately drilling a plurality of primary coordination holes (422) in the cured spar member (418) in the spar mold (402) using a tool (417) positioned in the plurality of bores (410).

    Abstract translation: 一种制造倾旋转子机翼结构（109）的方法，所述方法包括提供具有多个从所述模具（402）的外表面（402e）延伸到所述模具（402）的内表面（402i）的孔（410） （402），所述多个孔（410）对应于翼梁构件（418）中的多个主要协调孔（422），所述翼梁模具（402）具有由顶部边缘（406t） ），底部边缘（406b）和外侧端部（406c，406d）; 选择多个树脂浸渍层（412）以确保层（412）连续延伸超过翼梁模具（402）的外围（406p）; 将帘布层（412）铺设在翼梁模具（402）中; 固化模具（402）中的帘布层（412）以形成延伸超过翼梁模具（402）的周边（406p）的固化翼梁构件（418）; 以及使用定位在所述多个孔（410）中的工具（417）在所述翼梁模具（402）中的所述固化翼梁构件（418）中准确地钻出多个主要协调孔（422）。

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