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).

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）。