公开(公告)号：WO2017216691A1

公开(公告)日：2017-12-21

申请号：PCT/IB2017/053435

申请日：2017-06-09

Applicant: BOMBARDIER INC. ,  SHORT BROTHERS PLC

Inventor： POLONI, Matthew ,  LARDY, Julien ,  MASSEY, Jeffrey ,  JASEM, Faris

IPC: B64C9/02

CPC classification number: B64C3/26 ,  B64C7/00 ,  B64C9/02 ,  B64C9/14 ,  B64D15/04 ,  Y02T50/32

Abstract: Apparatus for improving flow characteristics around aircraft wings by obstructing air flow through an aperture formed in a wing skin for a movable duct or track are disclosed. In one embodiment, the apparatus comprises a substantially rigid panel movable at least partially across the aperture for at least partially occluding the aperture and for accommodating movement of a slat track extending through the aperture. In another embodiment, the apparatus comprises a hinged panel configured to swing outwardly from an outer side of the wing skin toward an open position to accommodate movement of an anti-icing duct extending through the aperture and to swing toward a closed position at least partially occluding the aperture.

Abstract translation: 公开了一种用于通过阻挡空气流动通过用于可动管道或轨道的机翼蒙皮中形成的孔口来改善飞机机翼周围流动特性的装置。 在一个实施例中，所述设备包括基本上刚性的面板，所述面板至少部分地可移动穿过所述孔，用于至少部分地封闭所述孔并适应延伸穿过所述孔的板条轨道的移动。 在另一个实施例中，所述设备包括铰接面板，所述铰接面板构造成从所述机翼蒙皮的外侧向打开位置向外摆动以适应延伸穿过所述孔的防冰管的运动并且朝向闭合位置摆动，所述闭合位置至少部分地闭塞 光圈。

公开(公告)号：WO2014113458A1

公开(公告)日：2014-07-24

申请号：PCT/US2014/011658

申请日：2014-01-15

Applicant: OTTO, William M.

Inventor： OTTO, William M.

IPC: B64C1/00 ,  F16F7/104 ,  F16F15/08

CPC classification number: B64C25/20 ,  B64C1/00 ,  B64C1/065 ,  B64C1/069 ,  B64C1/10 ,  B64C3/185 ,  B64C3/26 ,  B64C3/58 ,  B64C5/02 ,  B64C5/16 ,  B64C9/02 ,  B64C9/16 ,  B64C9/20 ,  B64C13/30 ,  B64C25/02 ,  B64C25/10 ,  B64C25/12 ,  B64C25/14 ,  B64C25/18 ,  B64C25/22 ,  B64C2025/125 ,  B64D33/10 ,  B64D37/04 ,  F02B37/001 ,  Y02T50/32 ,  Y02T50/44

Abstract: A support unit for a structure within a pressure vessel that includes an external load distribution plate, an internal load distribution plate, a standoff unit between the external load distribution plate and the internal load distribution plate that extends through an opening in a pressure vessel.

Abstract translation: 用于压力容器内的结构的支撑单元，其包括外部负载分配板，内部负载分配板，外部负载分配板和内部负载分配板之间的隔离单元，所述支架单元延伸穿过压力容器中的开口。

公开(公告)号：WO2013106125A3

公开(公告)日：2013-09-06

申请号：PCT/US2012061328

申请日：2012-10-22

Applicant: GULFSTREAM AEROSPACE CORP ,  GRIECO JAMES R ,  PAKHLEVANYAN GARY

Inventor： GRIECO JAMES R ,  PAKHLEVANYAN GARY

IPC: B64C9/16

CPC classification number: B64C9/02 ,  B64C9/16 ,  Y02T50/32 ,  Y02T50/44 ,  Y10T29/49815

Abstract: A flap roller arrangement for supporting a flap on a wing of an aircraft is disclosed herein. The flap roller arrangement includes, but is not limited to, a roller assembly that is configured for rolling engagement with a flap track of the wing and for engagement with a flap fitting. The flap roller arrangement further includes a retaining member that is removably coupled to the roller assembly. The roller assembly is configured to egress through an opening in the flap fitting in a direction away from the flap track. The retaining member is configured to obstruct egress of the roller assembly through the opening when the retaining member is coupled to the roller assembly. The roller assembly is enabled to egress through the opening when the retaining member is removed from the roller assembly.

Abstract translation: 本文公开了一种用于将翼片支撑在飞机机翼上的翼瓣辊装置。 挡风玻璃辊装置包括但不限于配置成与机翼的挡板导轨滚动接合并用于与挡板配件接合的滚子组件。 挡风玻璃辊装置还包括可拆卸地连接到滚轮组件的保持构件。 滚轮组件构造成沿远离翼轨道的方向通过翼配件中的开口。 保持构件构造成当保持构件联接到辊子组件时阻止辊子组件通过开口的外出。 当保持构件从辊子组件移除时，辊子组件能够通过开口离开。

公开(公告)号：WO2012016717A1

公开(公告)日：2012-02-09

申请号：PCT/EP2011/003966

申请日：2011-08-08

Applicant: AIRBUS OPERATIONS GMBH ,  FISCHER, Markus ,  WEBER, Carsten

Inventor： FISCHER, Markus ,  WEBER, Carsten

IPC: B64C9/32 ,  B64C5/08

CPC classification number: B64C3/50 ,  B64C5/08 ,  B64C9/323 ,  B64C2003/145 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44

Abstract: The invention relates to an auxiliary flap arrangement for modifying the profile of an aerodynamic body, in particular the trailing edge of the aerodynamic body. The auxiliary flap arrangement here exhibits at least two auxiliary flaps (20, 40) that can be adjusted by means of an adjustment device (60) while coupled to each other.

Abstract translation: 本发明涉及一种辅助翼片装置，用于改变空气动力体的轮廓，特别是空气动力体的后缘。 这里的辅助翼片装置表现出至少两个辅助翼片（20,40），其可以通过调节装置（60）在彼此耦合的同时进行调节。

公开(公告)号：WO2011134924A3

公开(公告)日：2011-12-29

申请号：PCT/EP2011056514

申请日：2011-04-26

Applicant: AIRBUS OPERATIONS GMBH ,  KORDT MICHAEL

Inventor： KORDT MICHAEL

IPC: B64C13/16

CPC classification number: B64C13/16 ,  B64C9/34 ,  Y02T50/32 ,  Y02T50/44

Abstract: System and method for minimising buffeting in the case of an aircraft (2), wherein buffeting load control elements (10) which are provided in aerofoils of the aircraft (2) can be at least partly moved out of the aerofoils by a control means (1) to reduce buffeting loads acting on the aircraft (2).

Abstract translation: 在飞机（2）的情况下最小化缓冲的系统和方法，其中设置在飞行器（2）的机翼中的缓冲负载控制元件（10）可以通过控制装置（至少部分地）移出机翼 1）减少作用在飞机上的缓冲载荷（2）。

公开(公告)号：WO2011022179A2

公开(公告)日：2011-02-24

申请号：PCT/US2010/043553

申请日：2010-07-28

Applicant: THE BOEING COMPANY ,  THORNTON, Gregory, J. ,  BARR, Mark

Inventor： THORNTON, Gregory, J. ,  BARR, Mark

IPC: B64C9/02

CPC classification number: F16C41/00 ,  B64C9/02 ,  B64C9/22 ,  F16C23/043 ,  F16C33/201 ,  F16C2202/30 ,  F16C2326/43 ,  Y02T50/32 ,  Y02T50/44

Abstract: A method of providing conditional electrical isolation for a bearing is disclosed. An inner race coupled to a first structure and an outer race coupled to a second structure are provided. An isolative means is provided for conditionally electrically isolating the first structure from the second structure.

Abstract translation: 公开了一种为轴承提供有条件电气隔离的方法。 提供了联接到第一结构的内座圈和联接到第二结构的外座圈。 提供隔离装置用于有条件地使第一结构与第二结构电隔离。

公开(公告)号：WO2010103157A1

公开(公告)日：2010-09-16

申请号：PCT/ES2010/070141

申请日：2010-03-11

Applicant: AIRBUS OPERATIONS, S.L. ,  VELA ORGE, Pilar ,  NAMER, Arnaud ,  PASCUAL FUERTES, Angel ,  SIMÓN CALERO, Francisco Javier

Inventor： VELA ORGE, Pilar ,  NAMER, Arnaud ,  PASCUAL FUERTES, Angel ,  SIMÓN CALERO, Francisco Javier

IPC: B64C9/10 ,  B64C5/10 ,  B64C13/28

CPC classification number: B64C9/10 ,  B64C5/02 ,  Y02T50/32 ,  Y02T50/44

Abstract: El sistema incorpora medios (16) de transmisión de deflexión para proporcionar una posición de deflexión de un dispositivo (8) hipersustentador móvil, instalado en el HTP (2) móvil de una aeronave (1), para cada posición del ángulo de calado del HTP (2). Preferiblemente, los medios (16) de transmisión de deflexión (18, 20, 23) consisten esencialmente en una ligadura mecánica conectada entre el dispositivo (8) hipersustentador y la aeronave (1).

Abstract translation: 该系统包括偏转传动装置（16），用于为HTP（2）的设定角度的每个位置提供安装在飞行器（1）的移动HTP（2）上的可移动翼片（8）的偏转位置， 。 优选地，用于传输挠曲（18,20,23）的装置（16）基本上包括连接在翼片（8）和飞行器（1）之间的机械连接件。

公开(公告)号：WO2009056873A1

公开(公告)日：2009-05-07

申请号：PCT/GB2008/050996

申请日：2008-10-27

Applicant: AIRBUS UK LIMITED ,  CATHELAIN, Francois ,  KAY, Edmund

Inventor： CATHELAIN, Francois ,  KAY, Edmund

IPC: B64C9/24

CPC classification number: B64C9/24 ,  B64C2009/143 ,  Y02T50/32

Abstract: An actuation system configured to deploy a high-lift device on a leading edge of an aircraft wing. The system comprises: a link pivotally connected to the wing at a first pivot point and to the high-lift device at a second pivot point; a first actuation mechanism configured to rotate the high-lift device about the first pivot point; and a second actuation mechanism configured to rotate the high-lift device about the second pivot point. The second actuation mechanism is operable independently of the first actuation mechanism, and can be operated in order to generate a sealing force between the high-lift device and the leading edge of the aircraft wing.

Abstract translation: 一种致动系统，其构造成在飞机机翼的前缘部署高升力装置。 该系统包括：在第一枢转点处枢转地连接到机翼的连杆和在第二枢转点处的高升力装置; 第一致动机构，其构造成围绕第一枢转点旋转高升降机构; 以及第二致动机构，其构造成围绕第二枢转点旋转高升降机构。 第二致动机构可独立于第一致动机构操作，并且可以操作以便在高升力装置和飞机机翼的前缘之间产生密封力。

公开(公告)号：WO2009017896A2

公开(公告)日：2009-02-05

申请号：PCT/US2008067544

申请日：2008-06-19

Applicant: BOEING CO ,  COUGHLIN RAY F

Inventor： COUGHLIN RAY F

IPC: B64C9/14 ,  B64C21/02

CPC classification number: B64C9/16 ,  B64C2009/143 ,  Y02T50/32

Abstract: In one embodiment, an apparatus is provided for covering and uncovering a flap opening in an aircraft. The apparatus comprises a door member, a torque tube roller member, at least one roller member, and a biasing member. The door member may be adapted to cover and uncover a flap opening. The torque tube roller member may be attached with the door member, and may be adapted to be pushed by a torque tube member attached with a flap of an aircraft. The door member may be adapted to be driven from a closed position covering a flap opening into an open position uncovering a flap opening. The roller member may be attached with the door member and may be adapted to follow at least one track member. The biasing member may be attached with the door member for biasing the door member towards a closed position covering a flap opening.

Abstract translation: 在一个实施例中，提供了用于覆盖和露出飞行器中的翼片开口的装置。 该装置包括门构件，扭矩管辊构件，至少一个辊构件和偏置构件。 门构件可以适于覆盖和露出翼片开口。 扭矩管辊构件可以与门构件一起安装，并且可以适于被附接有飞行器的翼片的扭矩管构件推动。 门构件可以适于从覆盖翼片开口的关闭位置驱动到暴露翼片开口的打开位置。 辊构件可以与门构件相连，并且可以适于跟随至少一个轨道构件。 偏置构件可以与门构件附接，用于将门构件偏压到覆盖翼片开口的关闭位置。

公开(公告)号：WO2008100286A3

公开(公告)日：2009-01-15

申请号：PCT/US2007018747

申请日：2007-08-23

Applicant: BLR AEROSPACE L L C ,  DESROCHE ROBERT J

Inventor： DESROCHE ROBERT J

IPC: B64C3/58 ,  B64C9/18 ,  B64C23/06

CPC classification number: B64C3/58 ,  B64C9/18 ,  B64C23/069 ,  Y02T50/164 ,  Y02T50/32 ,  Y10T29/49826

Abstract: An aircraft can include a wing (42) with a leading edge (64) and a trailing edge (66). The wing has a main body (74) and movable control surfaces (80, 82) coupled to the main body. The wing (42) generates lifting forces when the aircraft is in flight. The movable control surfaces can be used to control the generated lifting forces. A spanwise flow inhibitor (70) extends from the outer wingtip (96) of the wing. At least one gurney flap (100, 102) extends generally downwardly from at least a portion of the trailing edge (66) of the wing. The flap at least partially counteracts a change in center of lift attributable to the spanwise flow inhibitor.

Abstract translation: 飞机可以包括具有前缘（64）和后缘（66）的翼（42）。 翼具有主体（74）和联接到主体的可移动控制表面（80,82）。 当飞行器飞行时，机翼（42）产生提升力。 可动控制面可用于控制产生的提升力。 翼展式阻流器（70）从机翼的外翼尖（96）延伸。 至少一个轮辋翼片（100,102）从机翼的后缘（66）的至少一部分大致向下延伸。 翼片至少部分地抵消了由翼展方向阻流剂引起的升力中心的变化。