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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.
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).
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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).
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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.
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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.
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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公开(公告)号：EP3082055A1
公开(公告)日：2016-10-19
申请号：EP16164943.9
申请日：2016-04-12
Applicant: Bell Helicopter Textron Inc.
Inventor： KNOLL, Jonathan A. , NISSEN, Jeffrey P. , McCULLOUGH, John R.
CPC classification number: G06F17/5018 , G06F17/5086 , Y02T10/82
Abstract: A method of performing structural analysis relating to a component (18) having CAD-based geometry (200), refined CAD-based geometry and CAD-based FEA data (60) associated therewith. The method includes scanning (72) the component to obtain scan-based point cloud geometry of the component, aligning the scan-based point cloud geometry with the CAD-based geometry (200) of the component (18), generating scan-based geometry of the component by refining the scan-based point cloud geometry, comparing the scan-based geometry with the refined CAD-based geometry of the component (18) to quantify geometric differences therebetween, generating scan-based FEA geometry (250) of the component (18) by meshing the scan-based geometry, performing finite element analysis on the scan-based FEA geometry (250) to obtain scan-based FEA data and comparing the scan-based FEA data with the CAD-based FEA data (170) of the component (18) to quantify the effect of geometric difference therebetween.
Abstract translation: 执行与具有基于CAD的几何（200），与CAD相关联的基于CAD的几何和基于CAD的FEA数据（60）的组件（18）相关的结构分析的方法。 该方法包括扫描（72）该组件以获得该组件的基于扫描的点云几何，将基于扫描的点云几何与该组件（18）的基于CAD的几何（200）对准，生成基于扫描的几何 通过精简基于扫描的点云几何，将基于扫描的几何与组件（18）的精细的基于CAD的几何形状进行比较，以量化其间的几何差异，生成组件的基于扫描的FEA几何（250） （18），通过对基于扫描的几何进行啮合，对基于扫描的FEA几何进行有限元分析（250）以获得基于扫描的FEA数据，并将基于扫描的FEA数据与基于CAD的FEA数据进行比较（170） 以量化其间的几何差异的影响。
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Patent Agency Ranking
公开(公告)号：EP3437991B1
公开(公告)日：2020-02-12
申请号：EP17191478.1
申请日：2017-09-15
Applicant: Bell Helicopter Textron Inc.
Inventor： SELF, Robert , GREEN, Nathan P. , McCULLOUGH, John R. , COLE, Russell , SHERRILL, Paul , WARDLAW, Robert
IPC: B64C27/473 , B64C27/82
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公开(公告)号：EP3082055B1
公开(公告)日：2018-07-18
申请号：EP16164943.9
申请日：2016-04-12
Applicant: Bell Helicopter Textron Inc.
Inventor： KNOLL, Jonathan A. , NISSEN, Jeffrey P. , McCULLOUGH, John R.
CPC classification number: G06F17/5018 , G06F17/5086
Abstract: A method of performing structural analysis relating to a component (18) having CAD-based geometry (200), refined CAD-based geometry and CAD-based FEA data (60) associated therewith. The method includes scanning (72) the component to obtain scan-based point cloud geometry of the component, aligning the scan-based point cloud geometry with the CAD-based geometry (200) of the component (18), generating scan-based geometry of the component by refining the scan-based point cloud geometry, comparing the scan-based geometry with the refined CAD-based geometry of the component (18) to quantify geometric differences therebetween, generating scan-based FEA geometry (250) of the component (18) by meshing the scan-based geometry, performing finite element analysis on the scan-based FEA geometry (250) to obtain scan-based FEA data and comparing the scan-based FEA data with the CAD-based FEA data (170) of the component (18) to quantify the effect of geometric difference therebetween.
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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.
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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公开(公告)号：EP3202660B1
公开(公告)日：2020-04-08
申请号：EP17154892.8
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.
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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）。
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