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.

IPC: B64C29/00 ,  B64C3/26 ,  B64F5/10

公开(公告)号：EP3202660A1

公开(公告)日：2017-08-09

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.

IPC: B64C3/18

Abstract: In one aspect, there is a rib assembly (155) for an aircraft wing including a rib web (230) having a top and a bottom, the rib web includes a first laminate (232), a second laminate (234), and a honeycomb panel (236) having an array of large cells disposed between the first laminate (232) and the second laminate (234), each cell having a width of at least 1 cm; and a plurality of skin flanges (240) for fixedly attaching the rib web (230) to a skin of the wing, each skin flange (240) has a base member (242s) having a first portion (242f) and a second portion (242d) and a vertical member (2421) extending from the base member (242s). The plurality of skin flanges (240) can be attached to the top and the bottom of the rib web (230) such that the second portion (242d) of the base member (242s) and the vertical member (2421) are attached to the rib web (230).

Abstract translation: 在一个方面，存在用于飞机机翼的肋组件（155），其包括具有顶部和底部的肋条腹板（230），肋条腹板包括第一层压板（232），第二层压板（234）和 蜂窝板（236），其具有设置在第一层压板（232）和第二层压板（234）之间的大单元阵列，每个单元的宽度至少为1cm; 以及用于将肋条腹板230固定地连接到机翼蒙皮上的多个蒙皮凸缘240，每个蒙皮凸缘240具有基座构件242s，该基座构件242s具有第一部分242f和第二部分 242d）和从基座构件（242s）延伸的垂直构件（2421）。 多个皮肤凸缘（240）可以被附接到肋条腹板（230）的顶部和底部，使得基部构件（242s）的第二部分（242d）和竖直构件（2421）被附接到肋条 肋网（230）。

公开(公告)号：EP3421353A1

公开(公告)日：2019-01-02

申请号：EP18167038.1

申请日：2018-04-12

Applicant: Bell Helicopter Textron Inc.

Inventor： PARHAM, Jr., Thomas Clement ,  BOSWORTH, Jeffrey ,  MILLER, Gary ,  STAMPS, Frank Bradley ,  CHOI, Jouyoung Jason ,  OLDROYD, Paul K. ,  RAUBER, Richard Erler ,  SEIFERT, Michael Scott

IPC: B64C3/26 ,  B64C29/00 ,  B64C1/12 ,  B64C3/20

Abstract: A wing airframe (36, 100, 222) for a wing (18, 102, 200) of a tiltrotor aircraft (10) includes a wing airframe coreassembly (110, 206) and a wing skin assembly (24, 118, 202) disposed on the wing airframe core assembly. The wing skin assembly (118, 202) includes an outer skin (52, 130, 208) and a damping sublayer (50, 128, 204), the damping sublayer interposed between the outer skin and the wing airframe core assembly (110, 206). The tiltrotor aircraft (10) includes a pylon assembly (30a, 30b) subject to aeroelastic movement during forward flight. The wing (18, 102, 200) is subject to deflection in response to the aeroelastic movement of the pylon assembly (30a, 30b). The damping sublayer (50, 128, 204) reduces the deflection of the wing (18, 102, 200), thereby stabilizing the wing during forward flight.

公开(公告)号：EP3263445A1

公开(公告)日：2018-01-03

申请号：EP16185727.1

申请日：2016-08-25

Applicant: Bell Helicopter Textron Inc.

Inventor： McCULLOUGH, John Richard ,  OLDROYD, Paul K.

IPC: B64C1/28 ,  B64C17/02 ,  B64C29/02 ,  B64C39/02 ,  B64C27/26 ,  B64C27/28 ,  B64D25/12 ,  B64C1/32 ,  B64C27/30 ,  B64D17/80

CPC classification number: B64C29/0033 ,  B64C1/28 ,  B64C1/32 ,  B64C11/28 ,  B64C17/02 ,  B64C27/26 ,  B64C27/28 ,  B64C27/30 ,  B64C29/02 ,  B64C39/024 ,  B64C39/08 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/185 ,  B64C2211/00 ,  B64D17/80 ,  B64D25/12 ,  G08G5/0065 ,  G08G5/0069 ,  G08G5/025

Abstract: In some embodiments, an aircraft (10) includes a flying frame (12) having an airframe (26), a propulsion system (34) attached to the airframe (26) and a flight control system (68) operably associated with the propulsion system (34) wherein, the flying frame (12) has a vertical takeoff and landing mode and a forward flight mode. A pod assembly (70) is selectively attachable to the flying frame (12) such that the flying frame (12) is rotatable about the pod assembly (70) wherein, the pod assembly (70) remains in a generally horizontal attitude during vertical takeoff and landing, forward flight and transitions therebetween.

Abstract translation: 在一些实施例中，飞行器（10）包括具有机身（26）的飞行框架（12），连接到机身（26）的推进系统（34）和可操作地与推进系统 （34），其中，所述飞行框架（12）具有垂直起飞和着陆模式以及前进飞行模式。 荚组件（70）可选择性地连接到飞行框架（12），使得飞行框架（12）可围绕荚组件（70）旋转，其中荚组件（70）在垂直起飞期间保持大致水平的姿态 和着陆，向前飞行和其间的过渡。

公开(公告)号：EP2832533B1

公开(公告)日：2016-03-23

申请号：EP13195029.7

申请日：2013-11-29

Applicant: Bell Helicopter Textron Inc.

Inventor： KENDRICK, Phillip A. ,  CARLSON, David G. ,  OLDROYD, Paul K.

IPC: B29D99/00 ,  B32B5/14 ,  B32B3/20 ,  B32B3/12 ,  B32B3/18 ,  B32B3/22

CPC classification number: B32B37/146 ,  B29C65/483 ,  B29C65/4835 ,  B29C65/486 ,  B29C65/5042 ,  B29C65/5057 ,  B29C65/7838 ,  B29C66/0042 ,  B29C66/1122 ,  B29C66/1142 ,  B29C66/5227 ,  B29C66/54 ,  B29C66/612 ,  B29C66/71 ,  B29C66/7212 ,  B29C66/72141 ,  B29C66/72143 ,  B29C66/7254 ,  B29C66/7392 ,  B29C66/7394 ,  B29C66/8122 ,  B29C66/81261 ,  B29C66/81467 ,  B29C66/8185 ,  B29C66/8284 ,  B29C66/83415 ,  B29D99/0021 ,  B29L2031/3076 ,  B29L2031/3088 ,  B29L2031/608 ,  B32B3/04 ,  B32B3/12 ,  B32B5/12 ,  B32B5/142 ,  B32B7/12 ,  B32B2038/0076 ,  B32B2260/023 ,  B32B2260/046 ,  B32B2307/302 ,  B32B2605/00 ,  B32B2605/18 ,  B64C1/18 ,  B64C3/20 ,  Y10T156/1093 ,  Y10T428/24149 ,  Y10T428/24165 ,  B29K2827/18 ,  B29K2307/04 ,  B29K2077/00 ,  B29K2309/08 ,  B29K2277/10 ,  B29K2071/00 ,  B29K2067/00 ,  B29K2061/00 ,  B29K2081/04 ,  B29K2063/00 ,  B29K2079/08 ,  B29K2031/00 ,  B29K2061/04

公开(公告)号：EP3418187A1

公开(公告)日：2018-12-26

申请号：EP18186939.7

申请日：2016-08-25

Applicant: Bell Helicopter Textron Inc.

Inventor： McCULLOUGH, John Richard ,  OLDROYD, Paul K.

IPC: B64C17/02 ,  B64C29/02 ,  B64C39/02 ,  B64C27/26 ,  B64D25/12 ,  G08G5/00 ,  G05D1/10 ,  B64C39/08 ,  B64C27/30 ,  B64D17/80

CPC classification number: B64C29/0033 ,  B64C1/28 ,  B64C1/32 ,  B64C11/28 ,  B64C17/02 ,  B64C27/26 ,  B64C27/28 ,  B64C27/30 ,  B64C29/02 ,  B64C39/024 ,  B64C39/08 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/185 ,  B64C2211/00 ,  B64D17/80 ,  B64D25/12 ,  G08G5/0065 ,  G08G5/0069 ,  G08G5/025

Abstract: The present disclosure relates to a transportation system and services method including receiving, at a transportation services provider system, a request for transportation of a pod assembly (170) having a current location and a destination; uploading a flight plan to a flight control system of a flying frame (112) including an airframe and a propulsion system; dispatching the flying frame (112) to the current location of the pod assembly (170); coupling the flying frame (112) to the pod assembly (170) at the current location of the pod assembly (170); transporting the pod assembly (170) by air from the current location of the pod assembly (170) to the destination of the pod assembly (170); and decoupling the pod assembly (170) from the flying frame (112) at the destination of the pod assembly (170).

公开(公告)号：EP3246248A1

公开(公告)日：2017-11-22

申请号：EP16173572.5

申请日：2016-06-08

Applicant: Bell Helicopter Textron Inc.

Inventor： PAULSON, Jared ,  OLDROYD, Paul K. ,  FOSKEY, Christopher

IPC: B64C11/26 ,  B64C27/473 ,  B64C29/00

CPC classification number: B64C11/28 ,  B64C11/26 ,  B64C27/473 ,  B64C27/50 ,  B64C29/0033 ,  B64C2027/4736

Abstract: A tiltrotor aircraft (10) includes a fuselage (12), a wing member (18) extending from the fuselage, an engine disposed relative to the wing member, a rotor hub assembly (26) mechanically coupled to the engine and a plurality of proprotor blade assemblies (28) rotatably mounted to the rotor hub assembly and operable for beamwise folding relative thereto. The proprotor blade assemblies each including a spar (40) and a sheath (52) extending spanwise along a leading edge of the spar. The spar has a root section (42), a main section (44) and a tip section (46). The spar has a generally oval cross section at radial stations along the main section of the spar with the root section of the spar forming an integral tang assembly (70) operable for coupling the spar to the rotor hub assembly.

Abstract translation: 倾转旋翼飞行器（10）包括机身（12），从机身延伸的翼件（18），发动机设置相对于机翼构件，转子轮毂组件（26）机械地联接到所述发动机和多个旋翼螺旋桨的 叶片组件（28），所述叶片组件可旋转地安装到所述转子毂组件并且可操作用于相对于所述叶片组件进行光束折叠。 每个推进器桨叶组件包括翼梁（40）和沿着翼梁的前缘沿翼展方向延伸的护套（52）。 翼梁具有根部（42），主部（44）和末端部（46）。 翼梁在沿着翼梁的主部分的径向站处具有大致椭圆形的横截面，翼梁的根部部分形成可操作用于将翼梁耦合到转子毂组件的整体柄脚组件（70）。

公开(公告)号：EP2832533A1

公开(公告)日：2015-02-04

申请号：EP13195029.7

申请日：2013-11-29

Applicant: Bell Helicopter Textron Inc.

Inventor： KENDRICK, Phillip A. ,  CARLSON, David G. ,  OLDROYD, Paul K.

IPC: B29D99/00 ,  B32B5/14 ,  B32B3/20 ,  B32B3/12 ,  B32B3/18 ,  B32B3/22

CPC classification number: B32B37/146 ,  B29C65/483 ,  B29C65/4835 ,  B29C65/486 ,  B29C65/5042 ,  B29C65/5057 ,  B29C65/7838 ,  B29C66/0042 ,  B29C66/1122 ,  B29C66/1142 ,  B29C66/5227 ,  B29C66/54 ,  B29C66/612 ,  B29C66/71 ,  B29C66/7212 ,  B29C66/72141 ,  B29C66/72143 ,  B29C66/7254 ,  B29C66/7392 ,  B29C66/7394 ,  B29C66/8122 ,  B29C66/81261 ,  B29C66/81467 ,  B29C66/8185 ,  B29C66/8284 ,  B29C66/83415 ,  B29D99/0021 ,  B29L2031/3076 ,  B29L2031/3088 ,  B29L2031/608 ,  B32B3/04 ,  B32B3/12 ,  B32B5/12 ,  B32B5/142 ,  B32B7/12 ,  B32B2038/0076 ,  B32B2260/023 ,  B32B2260/046 ,  B32B2307/302 ,  B32B2605/00 ,  B32B2605/18 ,  B64C1/18 ,  B64C3/20 ,  Y10T156/1093 ,  Y10T428/24149 ,  Y10T428/24165 ,  B29K2827/18 ,  B29K2307/04 ,  B29K2077/00 ,  B29K2309/08 ,  B29K2277/10 ,  B29K2071/00 ,  B29K2067/00 ,  B29K2061/00 ,  B29K2081/04 ,  B29K2063/00 ,  B29K2079/08 ,  B29K2031/00 ,  B29K2061/04

Abstract: A method of manufacturing a core stiffened structure includes orienting the plurality of core wafers (2401) in a non-uniform pattern onto a first face sheet (2805), the non-uniform pattern producing non-uniform spacing (2809) between adjacent core wafers; assembling a second face sheet (2803) onto the plurality of wafers (2401); and curing an adhesive to create a bond between the plurality of wafers (2401), the first face sheet (2805), and the second face sheet (2803).

Abstract translation: 一种制造芯加强结构的方法包括将多个芯晶片（2401）以不均匀图案定向到第一面板（2805）上，所述不均匀图案在相邻芯片之间产生不均匀间隔（2809） ; 将第二面板（2803）组装到所述多个晶片（2401）上; 以及固化粘合剂以在所述多个晶片（2401），所述第一面板（2805）和所述第二面板（2803）之间形成结合。

公开(公告)号：EP3263445B1

公开(公告)日：2018-10-17

申请号：EP16185727.1

申请日：2016-08-25

Applicant: Bell Helicopter Textron Inc.

Inventor： McCULLOUGH, John Richard ,  OLDROYD, Paul K.

IPC: B64C1/28 ,  B64C17/02 ,  B64C29/02 ,  B64C39/02 ,  B64C27/26 ,  B64C27/28 ,  B64D25/12 ,  B64C1/32 ,  B64C27/30 ,  B64D17/80

CPC classification number: B64C29/0033 ,  B64C1/28 ,  B64C1/32 ,  B64C11/28 ,  B64C17/02 ,  B64C27/26 ,  B64C27/28 ,  B64C27/30 ,  B64C29/02 ,  B64C39/024 ,  B64C39/08 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/185 ,  B64C2211/00 ,  B64D17/80 ,  B64D25/12 ,  G08G5/0065 ,  G08G5/0069 ,  G08G5/025

Abstract: In some embodiments, an aircraft (10) includes a flying frame (12) having an airframe (26), a propulsion system (34) attached to the airframe (26) and a flight control system (68) operably associated with the propulsion system (34) wherein, the flying frame (12) has a vertical takeoff and landing mode and a forward flight mode. A pod assembly (70) is selectively attachable to the flying frame (12) such that the flying frame (12) is rotatable about the pod assembly (70) wherein, the pod assembly (70) remains in a generally horizontal attitude during vertical takeoff and landing, forward flight and transitions therebetween.

公开(公告)号：EP3246248B1

公开(公告)日：2018-08-15

申请号：EP16173572.5

申请日：2016-06-08

Applicant: Bell Helicopter Textron Inc.

Inventor： PAULSON, Jared ,  OLDROYD, Paul K. ,  FOSKEY, Christopher

IPC: B64C11/26 ,  B64C27/473 ,  B64C29/00

CPC classification number: B64C11/28 ,  B64C11/26 ,  B64C27/473 ,  B64C27/50 ,  B64C29/0033 ,  B64C2027/4736

Abstract: A tiltrotor aircraft (10) includes a fuselage (12), a wing member (18) extending from the fuselage, an engine disposed relative to the wing member, a rotor hub assembly (26) mechanically coupled to the engine and a plurality of proprotor blade assemblies (28) rotatably mounted to the rotor hub assembly and operable for beamwise folding relative thereto. The proprotor blade assemblies each including a spar (40) and a sheath (52) extending spanwise along a leading edge of the spar. The spar has a root section (42), a main section (44) and a tip section (46). The spar has a generally oval cross section at radial stations along the main section of the spar with the root section of the spar forming an integral tang assembly (70) operable for coupling the spar to the rotor hub assembly.