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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
    2.
    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：EP3210884A1

    公开(公告)日：2017-08-30

    申请号：EP17154891.0

    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: B64C3/24

    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 composite skin (199) for a tiltrotor aircraft including 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 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).

    Abstract translation: 在一个方面中，提供了一种用于倾转旋翼飞机的复合蒙皮（199）的制造方法，包括：在模具（220）中提供第一蒙皮（201），所述第一蒙皮（201）具有由 前缘（201a），后缘（201b）和外侧端（201c，201d）; 在第一表皮（201）上提供具有大单元（205）阵列的多个蜂窝板（203），每个单元具有至少1cm的宽度; 沿着第一表皮（201）的纵向轴线组装多个蜂窝板（203），以在第一表皮（201）的周边（201p）内形成具有外周边（207p）的蜂窝芯（207）; 将第二表皮211定位在所述蜂窝芯207上，所述第二表皮211在所述第一表皮201的外围201p内具有外周边211p; 以及固化粘合剂以在第一表皮（201），蜂窝芯（207）和第二表皮（211）之间形成结合以形成复合表层（199）。

    WING-FUSELAGE INTEGRATED AIRFRAME BEAMS FOR TILTROTOR AIRCRAFT
    4.
    发明公开
    WING-FUSELAGE INTEGRATED AIRFRAME BEAMS FOR TILTROTOR AIRCRAFT 审中-公开

    公开(公告)号：EP3461737A1

    公开(公告)日：2019-04-03

    申请号：EP18195577.4

    申请日：2018-09-19

    Applicant: Bell Helicopter Textron Inc.

    Inventor： BRUNKEN, Jr, John Elton ,  BAINES, Andrew G. ,  KOOIMAN, James Everett ,  MCCULLOUGH, John Richard ,  ZIMMERMAN, Brett Rodney

    IPC: B64C1/26 ,  B64C1/06 ,  B64C1/14 ,  B64C3/18 ,  B64C29/00

    Abstract: An airframe for a tiltrotor aircraft (10) includes a wing airframe (24; 106) including a rib (20a, 20b; 124a, 124b), a fuselage airframe (26; 102) including a fore-aft overhead beam (28a, 28b; 126a, 126b) and a cradle support assembly (56a, 56b; 110a, 110b). The cradle support assembly (56a, 56b; 110a, 110b) includes a forward wing support (146a, 146b) coupled to the fore-aft overhead beam (28a, 28b; 126a, 126b) and the wing airframe (24, 106) and an aft wing support (148a, 148b) coupled to the fore-aft overhead beam (28a, 28b; 126a, 126b) and the wing airframe (24, 106). The rib (20a, 20b; 124a, 124b), the fore-aft overhead beam (28a, 28b; 126a, 126b), the forward wing support (146a, 146b) and the aft wing support (148a, 148b) are substantially aligned to form a wing-fuselage integrated airframe beam assembly (32a, 32b; 108a, 108b) to support the wing airframe (24, 106).

    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。

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