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1. 发明申请

WO2015200757A1 FLEX BEAM CLAMP FOR ROTOR ASSEMBLY 审中-公开
标题翻译：用于转子总成的FLEX光束夹
公开(公告)号：WO2015200757A1
公开(公告)日：2015-12-30
申请号：PCT/US2015/037895
申请日：2015-06-26
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： NUSSENBLATT, Eric Lucien , HUNTER, David H. , THOMAS, Justin
IPC分类号： B64C27/473
CPC分类号： B64C27/33 , B64C27/10 , B64C27/14 , B64C27/48
摘要： A rotor assembly for a rotary wing aircraft includes a rotor hub having a central axis, the rotor hub rotatable about the central axis. A plurality of flexible structural members extend radially outwardly from the rotor hub, each flexible structural member substantially U-shaped and having a first arm extending from the hub, a second arm extending from the hub, and an end portion connecting the first arm to the second arm at a radially outboard end of the flexible structural member. A clamp member is positioned between the first arm and the second arm of each structural member and secured thereto to tie deflection of the first arm to deflection of the second arm. A rotor blade is secured to each flexible structural member of the plurality of flexible structural members via the clamp member.
摘要翻译：用于旋转飞行器飞行器的转子组件包括具有中心轴线的转子轮毂，该转子轮毂可围绕中心轴线旋转。多个柔性结构构件从转子毂径向向外延伸，每个柔性结构构件基本上为U形，并具有从毂延伸的第一臂，从轮毂延伸的第二臂和将第一臂连接到第二臂在柔性结构构件的径向外侧端部。夹紧构件定位在每个结构构件的第一臂和第二臂之间并固定到其上以使第一臂的偏转与第二臂的偏转相一致。转子叶片通过夹紧件固定到多个柔性结构件的每个柔性结构件上。

2. 发明申请

WO2017048683A1 STRESS REDUCING HOLES 审中-公开
标题翻译：应力减少
公开(公告)号：WO2017048683A1
公开(公告)日：2017-03-23
申请号：PCT/US2016/051459
申请日：2016-09-13
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： KOPANSKI, Krzystof , THOMAS, Justin
IPC分类号： B63H1/26 , B64C27/473 , F01D5/14
CPC分类号： B64C27/473
摘要： A blade includes a blade body having a surface and a hole extending through the surface of the blade body. The hole defines a hole axis and a plane perpendicular to the hole axis. The hole has an elongated hole perimeter within the plane. The hole perimeter includes a plurality of non-linear perimeter sections to minimize stress concentration around the elongated hole perimeter while maximizing the usable opening area. A rotor system includes a rotor hub and a blade as recited above. The blade extends radially outward from the rotor hub. The blade defines a root end proximate to the rotor hub, a tip end opposite the root end.
摘要翻译：叶片包括具有延伸穿过叶片本体表面的表面和孔的叶片体。孔定义孔轴线和垂直于孔轴线的平面。该孔在平面内具有细长的孔周长。孔周边包括多个非线性周边部分，以最大化可用开口面积来最小化围绕细长孔周边的应力集中。转子系统包括如上所述的转子毂和叶片。叶片从转子毂径向向外延伸。叶片限定靠近转子毂的根部端，与根端相对的尖端。

3. 发明申请

WO2017069840A1 AIRCRAFT ROTOR BLADE INSERT 审中-公开
标题翻译：飞机转子叶片插入
公开(公告)号：WO2017069840A1
公开(公告)日：2017-04-27
申请号：PCT/US2016/047552
申请日：2016-08-18
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： THOMAS, Justin , KOPANSKI, Krzysztof , SCOTT, Mark W.
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , B64C27/467 , F01D5/186 , F05D2230/30 , F05D2230/80 , F05D2260/202 , F05D2260/37 , Y02T50/672 , Y02T50/673 , Y02T50/676
摘要： An inset configured for use in a rotor blade is provided including a body having a shape generally complementary to a hole formed in the rotor blade. An opening extends between a first surface and a second surface of the body. The opening is configured to provide a fluid flow path between an interior and an exterior of the rotor blade.
摘要翻译：提供了一种构造用于转子叶片中的插入物，其包括具有与形成在转子叶片中的孔大致互补的形状的主体。开口在主体的第一表面和第二表面之间延伸。该开口构造成在转子叶片的内部和外部之间提供流体流动路径。

4. 发明申请

WO2016054209A1 DUAL ROTOR, ROTARY WING AIRCRAFT 审中-公开
标题翻译：双转子，旋转翼飞机
公开(公告)号：WO2016054209A1
公开(公告)日：2016-04-07
申请号：PCT/US2015/053223
申请日：2015-09-30
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： HUNTER, David A. , THOMAS, Justin , BEATTY, Robert D. , TUOZZO, Nick , EGOLF, Thomas Alan , LORBER, Peter F. , MOFFITT, Robert C. , WESTFALL, Shawn
IPC分类号： B64C27/00
CPC分类号： B64C27/10 , B64C27/12 , B64C27/14 , B64C27/463 , B64C27/467 , B64C27/473 , B64C2027/8236 , B64C2027/8272 , B64C2027/8281 , G05D1/0858
摘要： A main rotor blade assembly for a rotary wing aircraft is provided including a main rotor blade root region, a main rotor blade inboard region arranged outboard of said main rotor blade root region, a main rotor blade main region arranged outboard of said main rotor blade inboard region, and a main rotor blade tip region arranged outboard of said main rotor blade main region. At least one of chord, twist, sweep, airfoil shape, and thickness/chord of the main rotor blade assembly has been optimized to achieve balanced high speed forward flight and hover relative to both efficiency and high thrust capability.
摘要翻译：本发明提供一种旋转翼飞行器的主转子叶片组件，包括主转子叶片根部区域，布置在所述主转子叶片根部区域外侧的主转子叶片内侧区域，主转子叶片主区域，其布置在所述主转子叶片的外侧以及布置在所述主转子叶片主区域外侧的主转子叶片尖端区域。已经优化了主转子叶片组件的和弦，扭转，扫掠，翼面形状和厚度/弦的至少一个，以实现平衡的高速前进飞行和相对于效率和高推力能力的悬停。

5. 发明申请

WO2017083089A1 ROTOR BLADE STRUCTURES 审中-公开
标题翻译：转子叶片结构
公开(公告)号：WO2017083089A1
公开(公告)日：2017-05-18
申请号：PCT/US2016/058564
申请日：2016-10-25
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： THOMAS, Justin , KOPANSKI, Krzysztof , SCOTT, Mark, W.
IPC分类号： B64C27/72 , B64C27/46 , B64C27/473 , B64C27/54 , B64C27/59 , B64C27/64
CPC分类号： B64C27/72 , B64C27/473 , B64C27/54 , B64C27/64 , B64C2027/7272 , Y02T50/34
摘要： A closeout structure for a rotor blade includes a first fluid channel for supplying a first pressure to a first port of a trailing edge (TE) device, a second fluid channel for supplying a second pressure to a second port of the TE de vice, and a trough disposed between the first fluid channel and the second fluid channel. The closeout structure forms a double- W shape.
摘要翻译：用于转子叶片的封闭结构包括用于向后缘（TE）装置的第一端口提供第一压力的第一流体通道，用于向第二端口提供第二压力的第二流体通道 TE设备的出入口以及设置在第一流体通道和第二流体通道之间的槽。收尾结构形成双W形。

6. 发明申请

WO2016108997A2 AIRCRAFT ROTOR BLADE WITH REDUCED STRESS 审中-公开
标题翻译：减轻压力的飞机转子叶片
公开(公告)号：WO2016108997A2
公开(公告)日：2016-07-07
申请号：PCT/US2015/055719
申请日：2015-10-15
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： KOPANSKI, Krzysztof , THOMAS, Justin
IPC分类号： B64C27/32
CPC分类号： B64C27/473 , B64C27/008 , B64C27/06 , B64C2027/4736 , F01D5/18
摘要： An aircraft rotor blade includes a surface of the rotor blade, at least one main hole that extends through the surface and has a width and a length, and at least one leader hole that extends through the surface and has a length that is less than the length of the main hole and arranged spaced from and adjacent the main hole. The leader hole gradually increases in width from a first end of the leader hole opposite the main hole to an opposed second end of the leader hole proximate the main hole to operatively gradually distribute stress in the leader and main holes and rotor blade and reduce an amount of the stress exerted therein.
摘要翻译：飞行器转子叶片包括转子叶片的表面，延伸穿过表面并且具有宽度和长度的至少一个主孔以及延伸穿过表面的至少一个引导孔以及具有小于主孔的长度的长度并且布置成与主孔间隔开并且与主孔相邻。引导孔的宽度从与主孔相对的引导孔的第一端到邻近主孔的引导孔的相对第二端的宽度逐渐增加，以可操作地逐渐分配引导孔和主孔以及转子叶片中的应力，的压力。

7. 发明申请

WO2016054136A1 TIP CLEARANCE MEASUREMENT OF A ROTARY WING AIRCRAFT 审中-公开
标题翻译：旋转飞机的提升间隙测量
公开(公告)号：WO2016054136A1
公开(公告)日：2016-04-07
申请号：PCT/US2015/053090
申请日：2015-09-30
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： KOESSICK, Maximilian August , KOSTOSS, Michael J. , NUSSENBLATT, Eric Lucien , THOMAS, Justin , BUTLER, Christopher Paul , CERGE, Brandon Michael
IPC分类号： B64C27/10
CPC分类号： B64C27/82 , B64C1/0009 , B64C7/00 , B64C13/04 , B64C13/18 , B64C13/50 , B64C13/503 , B64C19/00 , B64C27/001 , B64C27/006 , B64C27/008 , B64C27/08 , B64C27/10 , B64C27/12 , B64C27/14 , B64C27/16 , B64C27/32 , B64C27/322 , B64C27/33 , B64C27/467 , B64C27/473 , B64C27/48 , B64C27/51 , B64C27/52 , B64C27/54 , B64C27/57 , B64C27/78 , B64C27/80 , B64C2027/004 , B64C2027/8209 , B64C2027/8227 , B64C2027/8236 , B64C2027/8263 , B64C2027/8272 , B64C2027/8281 , B64C2201/024 , B64D35/06 , B64D39/00 , B64D39/06 , B64D45/02 , F02C9/28 , F05D2220/329 , F05D2270/021 , F16D13/52 , F16D13/72 , F16D13/74 , F16H37/02 , G05D1/0077 , G05D1/0202 , G05D1/0204 , G05D1/08 , G05D1/0816 , G05D1/0858 , G06F19/00
摘要： An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly with an upper blade and a lower rotor assembly with a lower blade. A first antenna in one of upper blade and the lower blade, and a second antenna in the other of the upper blade and the lower blade. An oscillator to apply an excitation signal to the first antenna. A blade proximity monitor to monitor a magnitude of the excitation signal and an output signal from the second antenna to determine a distance between the upper blade and the lower blade.
摘要翻译：提供了一种飞机，其包括机身，延伸尾翼以及反向旋转的同轴主转子组件，其包括具有上叶片的上转子组件和具有下叶片的下转子组件。上叶片和下叶片之一中的第一天线，以及另一个上叶片和下叶片中的第二天线。用于向第一天线施加激励信号的振荡器。一种叶片接近监视器，用于监测激励信号的幅度和来自第二天线的输出信号，以确定上叶片和下叶片之间的距离。

8. 发明申请

WO2016054018A3 BLADE INDEXING OF A ROTARY WING AIRCRAFT 审中-公开
标题翻译：旋翼式飞机的叶片指数
公开(公告)号：WO2016054018A3
公开(公告)日：2016-04-07
申请号：PCT/US2015/052907
申请日：2015-09-29
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： HUNTER, David H. , CHASEN, Scott A. , CERGE, Brandon Michael , KOESSICK, Maximilian August , KOSTOSS, Michael J. , NUSSENBLATT, Eric Lucien , THOMAS, Justin , BUTLER, Christopher P.
IPC分类号： B64C27/10
摘要： An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly with a plurality of blades rotating in a first plane and a lower rotor assembly with a plurality of blades rotating in a second plane, each of the blades having a root end, a midpoint, and a tip end. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. The blades of the upper rotor assembly and the blades of the lower rotor assembly are indexed to improve tip end clearance between pairs of tip ends in the crossing plane as the tip ends move in respective first and second sinusoidal paths.
摘要翻译：提供了一种包括机身，延伸尾部以及反转同轴主转子组件的飞机，所述同轴主转子组件包括上转子组件和下转子组件，所述上转子组件具有在第一平面内旋转的多个叶片，多个叶片在第二平面内旋转，每个叶片具有根端，中点和末端。位于延伸尾部的平移推力系统，平移推力系统为机身提供平移推力。上部转子组件的叶片和下部转子组件的叶片被转位以当尖端在相应的第一和第二正弦路径中移动时改善交叉平面中的成对尖端之间的尖端间隙。

9. 发明申请

WO2014186045A2 FLEXBEAM TO ROTOR BLADE INTERFACE 审中-公开
标题翻译： FLEXBEAM到转子叶片接口
公开(公告)号：WO2014186045A2
公开(公告)日：2014-11-20
申请号：PCT/US2014/031010
申请日：2014-03-18
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： THOMAS, Justin , NUSSENBLATT, Eric Lucien , PARSONS, Eric S. , CASEY, Ryan Thomas , HUNTER, David H.
IPC分类号： B64C27/33
CPC分类号： B64C27/33 , B64C27/473 , B64C27/48 , Y10T29/49332
摘要： A spar for a rotor blade assembly is provided including a generally hollow tubular body. A spacer protrudes from at least one surface of the body along a length of the body. A hole extends through the body and the spacer. The hole is configured to align with a through hole in an adjacent flexbeam assembly. The spacer is configured to contact a surface of the adjacent flexbeam assembly to create a match fit between the body and the flexbeam assembly.
摘要翻译：提供了一种用于转子叶片组件的翼梁，包括大致中空的管状体。间隔件沿着身体的长度从身体的至少一个表面突出。孔延伸穿过主体和间隔件。孔构造成与相邻柔性梁组件中的通孔对准。间隔件构造成接触相邻柔性梁组件的表面以在主体和挠性束组件之间形成匹配配合。

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