公开(公告)号：WO2015040370A3

公开(公告)日：2015-05-14

申请号：PCT/GB2014052791

申请日：2014-09-15

Applicant: AIRBUS OPERATIONS LTD

Inventor： DIDEY ARNAUD ,  WILSON FRASER

IPC: B64C25/40

CPC classification number: B64C25/405 ,  B64C25/34 ,  Y02T50/823

Abstract: The invention is a drive system for rotating a wheel of an aircraft landing gear. The drive system includes a motor operable to rotate a drive pinion via a drive path, and a driven gear adapted to be mounted to the wheel. The drive system has a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear via the drive path. The drive path has a plurality of shafts rotatable about respect shaft axes, including an output shaft. The output shaft is operable to pivot about the axis of rotation of another shaft axis spaced from the output shaft axis. Also, an aircraft landing gear having a wheel and the drive system, where the driven gear of the drive system is mounted to the wheel.

Abstract translation: 本发明是用于旋转飞机起落架的车轮的驱动系统。 驱动系统包括可操作以经由驱动路径旋转驱动小齿轮的马达和适于安装到车轮的从动齿轮。 驱动系统具有第一构造，其中驱动小齿轮能够与从动齿轮啮合，以允许马达经由驱动路径驱动从动齿轮。 驱动路径具有可围绕轴线旋转的多个轴，包括输出轴。 输出轴可操作以围绕与输出轴轴线间隔开的另一轴轴的旋转轴线枢转。 而且，具有车轮和驱动系统的飞机起落架，其中驱动系统的从动齿轮安装在车轮上。

公开(公告)号：WO2014060748A3

公开(公告)日：2014-06-05

申请号：PCT/GB2013052697

申请日：2013-10-16

Applicant: AIRBUS OPERATIONS LTD

Inventor： VAGHELA NARESH

IPC: B29D23/00 ,  B29C70/84

CPC classification number: F16L21/035 ,  B29C70/766 ,  B29C73/02 ,  B29D23/003 ,  Y10T29/49719

Abstract: The present invention provides a method of manufacturing or repairing a pipe 1, the method comprising the steps of providing a pipe portion 2, the pipe portion having a channel 20 running along a surface of the pipe portion, the channel having an internal surface, placing a filler material 21 against the internal surface of the channel, and removing some of the filler material to provide a groove 22 inside the channel of the pipe portion. The present invention also provides a pipe 1 or pipe portion 2.

Abstract translation: 本发明提供了一种制造或修理管道1的方法，该方法包括以下步骤：提供管道部分2，管道部分具有​​沿管道部分的表面延伸的通道20，通道具有内表面， 抵靠通道内表面的填充材料21以及去除一些填充材料以在管部分的通道内提供凹槽22。 本发明还提供了管道1或管道部分2。

公开(公告)号：WO2011158015A3

公开(公告)日：2012-02-02

申请号：PCT/GB2011051046

申请日：2011-06-03

Applicant: AIRBUS OPERATIONS LTD ,  SOENARJO MOCHAMAD AGOES

Inventor： SOENARJO MOCHAMAD AGOES

IPC: B64C1/26

CPC classification number: C08L23/02 ,  B64C1/26 ,  B64C3/187 ,  C08K3/04 ,  C08K5/14 ,  C08K5/34924 ,  Y10T29/49622 ,  C08L2666/02

Abstract: An aircraft wing box spanwise joint (2), comprising a rib having a web, and a pair of rib fittings joined together, each rib fitting forming a closed loop around the periphery of the rib, wherein the rib is integrally formed with one of the rib fittings (16,18). Also, an aircraft wing including two or more of the joints (2). Also, a method of forming an aircraft wing box spanwise joint, the method comprising forming a pair of rib fittings, wherein one of the rib fittings is integrally formed with a rib having a web, each rib fitting forming a closed loop around the periphery of the rib, bringing the rib fittings together, and joining the rib fittings together.

Abstract translation: 一种飞机机翼翼展关节（2），包括具有腹板的肋和连接在一起的一对肋配件，每个肋配件围绕肋的周边形成闭合环，其中肋与 肋配件（16,18）。 另外，包括两个或更多个接头（2）的飞机机翼。 另外，形成飞机机翼翼展方向接头的方法，所述方法包括形成一对肋配件，其中所述肋配件中的一个与具有腹板的肋一体地形成，每个肋配件围绕所述肋配件的周边形成闭环 肋，使肋配件在一起，并将肋配件连接在一起。

公开(公告)号：WO2010052022A3

公开(公告)日：2010-05-14

申请号：PCT/EP2009/008018

申请日：2009-11-10

Applicant: AIRBUS OPERATIONS GMBH ,  AIRBUS OPERATIONS LTD. ,  SCHLIPF, Bernhard ,  PAYNE, Christoper ,  GIBBERT, Markus ,  DOSTMANN, Tom

Inventor： SCHLIPF, Bernhard ,  PAYNE, Christoper ,  GIBBERT, Markus ,  DOSTMANN, Tom

IPC: B64C9/02 ,  B64C9/22

Abstract: Flügel, aufweisend eine zwischen einer eingefahrenen und einer ausgefahrenen Stellung bewegbare Stellklappe (1) und eine Spaltabdeckungs-Vorrichtung (10) mit einem Stellhebel (13) und einer an diesem angeordneten Spaltabdeckungs-Klappe (11) mit einer Strömungsoberfläche (11a), wobei der Stellhebel (13) mit der Spaltabdeckungs-Klappe (11) mittels einer Vorspannvorrichtung (20) in eine erste Stellung vorgespannt ist, bei der sich die Spaltabdeckungs-Klappe (11) im Inneren (B) des Flügels (F) befindet, und wobei die Stellklappe (1) und der Stellhebel (13) mit der Spaltabdeckungs-Klappe (11) mechanisch derart gekoppelt sind, dass bei dem Bewegen der Stellklappe (1) in ihre eingefahrene Stellung ein Bewegen des Stellhebels (1) entgegen der durch die Vorspannvorrichtung (20) bewirkten Vorspannung in eine zweite Stellung erfolgt, und wobei die Strömungsoberfläche (11a) der Spaltabdeckungs-Klappe (11) in der zweiten Stellung des Stellhebels (13) zwischen der Oberseite (2) der eingefahrenen Stellklappe (1) und der Flügel-Strömungsoberfläche (7) verläuft.

公开(公告)号：WO2010052022A2

公开(公告)日：2010-05-14

申请号：PCT/EP2009008018

申请日：2009-11-10

Applicant: AIRBUS OPERATIONS GMBH ,  AIRBUS OPERATIONS LTD ,  SCHLIPF BERNHARD ,  PAYNE CHRISTOPER ,  GIBBERT MARKUS ,  DOSTMANN TOM

Inventor： SCHLIPF BERNHARD ,  PAYNE CHRISTOPER ,  GIBBERT MARKUS ,  DOSTMANN TOM

IPC: B64C7/00 ,  B64C9/02

CPC classification number: B64C9/02 ,  B64C9/22

Abstract: The invention relates to a vane having a regulating flap (1) that can be moved between a retracted position and an extended position and a gap covering device (10) having an adjusting lever (13) and a gap covering flap (11) arranged thereon, having a flow surface (11 a), ° wherein the adjusting lever (13) having the gap covering flap (11) is prestressed by a prestressing device (20) into a first position in which the gap covering flap (11) is located in the interior (B) of the vane (F), and ° wherein the regulating flap (1) and the adjusting lever (13) having the gap covering flap (11) are coupled mechanically such that when the regulating flap (1) moves into the retracted position thereof, the adjusting lever (1) moves into a second position against the prestress produced by the prestressing device (20), and ° wherein the flow surface (11 a) of the gap covering flap (11) in the second position of the adjusting lever (13) runs between the top side (2) of the retracted regulating flap (1) and the vane flow surface (7).

Abstract translation: 翼，其包括在缩回位置和伸出位置可移动的控制阻尼器之间的（1）和一个间隙盖装置（10）与致动杆（13）和布置在该间隙中盖片（11），其具有流动表面（11），° 其中，所述致动杆（13）与所述间隙盖片（11）由一个偏置装置的装置（20）被偏置到第一位置，其中，所述间隙盖折翼（11）在所述翼的内部（B）（F），和 °，其中，所述蝶形阀（1）和与所述间隙盖片（11）的调节杆（13）机械地耦合，使得，在移动蝶阀（1）时在其缩回位置，致动杆的运动（1）抵靠通过 偏压装置（20）引起的偏压到第二位置发生，并且°其中，所述流动表面（11）的顶部之间的致动杆（13）的第二位置的间隙盖片（11）的（2）代 ř缩回蝶阀（1）和翼流动表面（7）。

公开(公告)号：WO2010007415A2

公开(公告)日：2010-01-21

申请号：PCT/GB2009050844

申请日：2009-07-14

Applicant: AIRBUS OPERATIONS LTD ,  WINTER DARREN JOHN

Inventor： WINTER DARREN JOHN

IPC: B64C1/06 ,  B64C3/18

CPC classification number: B64C1/064 ,  B29C70/504 ,  B29D99/0007 ,  B64C3/182 ,  B64C2001/0072 ,  Y02T50/433

Abstract: A stiffener has an elongate web element and at least one elongate foot element, the web element and foot element being connected by a curved elbow, wherein the radius of the curved elbow is greater over a first portion of the stiffener than over a second portion of the stiffener. A roll forming die comprises first and second rollers, the first roller having a shaped section arranged to be located within a correspondingly shaped recess in the circumferential surface of the second roller, the first and second rollers defining a gap there between corresponding to the desired shape to be imparted on an elongate member passed between the rollers, the desired shape including a curved elbow between a web and a foot portion, wherein the shape of the recess in the second roller and the shape of the corresponding section of the first roller vary around a portion of the rollers circumference such that the radius of curvature of the gap between the rollers corresponding to the curved elbow varies between a minimum and a maximum value. The stiffener is formed by feeding an elongate member through the roll forming die and rotating the die rollers between a first and a second position as a portion of the elongate member is fed between the die rollers, whereby the radius of the curved elbow formed in the stiffener is varied.

Abstract translation: 加强件具有细长腹板元件和至少一个细长的脚元件，腹板元件和脚元件通过弯曲的弯头连接，其中弯曲弯头的半径在加强件的第一部分之上比在第二部分 加强筋 辊成型模具包括第一和第二辊，第一辊具有成形部分，该成形部分布置成位于第二辊的圆周表面中的相应形状的凹部内，第一和第二辊在其间限定相应于期望形状的间隙 被赋予在通过辊之间的细长构件上，期望的形状包括在腹板和脚部之间的弯曲弯头，其中第二辊中的凹部的形状和第一辊的相应部分的形状围绕 辊的一部分圆周使得对应于弯曲弯头的辊之间的间隙的曲率半径在最小值和最大值之间变化。 加强件通过将细长构件通过辊成型模具进给而形成，并且当细长构件的一部分被供给到模具辊之间时，模具辊在第一和第二位置之间旋转，由此形成在弯曲弯头中的弯曲弯头的半径 加强件是多样的。

公开(公告)号：WO2022084645A1

公开(公告)日：2022-04-28

申请号：PCT/GB2021/052525

申请日：2021-09-29

Applicant: AIRBUS OPERATIONS LTD. ,  THE UNIVERSITY OF BRISTOL

Inventor： COSENTINO, Enzo ,  LLEWELLYN-JONES, Catherine ,  ARENA, Gaetano ,  GROH, Rainer ,  PIRRERA, Alberto

IPC: B64C3/44 ,  F03D1/00

Abstract: A flow control device (60) on a structure such that strain in the structure is at least partially transferred to the flow control device. The flow control device has at least two states, or shapes, separated by an elastic instability region. The flow control device is arranged to rapidly transition, or snap through, from the first state to the second state when strain in the structure exceeds an activation threshold of the flow control device (60). In an example, a spoiler (12) on an aerofoil has a rest position where it is substantially flush with the low pressure surface and an activated position where it protrudes from the low pressure surface and modifies the airflow over that surface. The spoiler (12) bends to move from the rest position to the activated position when the strain in the aerofoil crosses a threshold. The deployed spoiler (12) reduces the lift on the aerofoil, acting to reduce the lift induced strain of the aerofoil to which the spoiler is attached.

公开(公告)号：WO2014023938A2

公开(公告)日：2014-02-13

申请号：PCT/GB2013052059

申请日：2013-08-01

Applicant: AIRBUS OPERATIONS LTD

Inventor： BOND-THORLEY ANDREW ,  HANKINSON NEIL ,  FREEMANTLE RICHARD

IPC: G01N29/22 ,  G01N29/24

CPC classification number: G01N29/24 ,  G01N29/221 ,  G01N2291/106

Abstract: An ultrasonic inspection tool ( 100; 200} has a chassis ( 102; 202} with a two part body ( 1 16; 216), an aperture ( 130; 230) for providing a clear Sine of sight between an array { 146; 246) and a workpiece, and a series of feet (134, 136: 272, 274, 276, 278., 280, 282) for sliding along the workpiece.

Abstract translation: 超声波检查工具（100; 200）具有带有两部分主体（116; 216）的底座（102; 202），用于在阵列（146; 246）之间提供清晰的正弦 ）和工件，以及用于沿工件滑动的一系列脚（134,136：272,274,276,278,280,282）。

公开(公告)号：WO2012131335A3

公开(公告)日：2013-11-07

申请号：PCT/GB2012050644

申请日：2012-03-22

Applicant: AIRBUS OPERATIONS LTD ,  WHITLOCK RHONA ,  DEL TIN MASSIMO ,  DALTON PETER ,  FORD GEORGE ,  HILL MICHAEL JOHN ,  HUNTBATCH ADRIAN ,  BREEZE LAURENCE

Inventor： WHITLOCK RHONA ,  DEL TIN MASSIMO ,  DALTON PETER ,  FORD GEORGE ,  HILL MICHAEL JOHN ,  HUNTBATCH ADRIAN ,  BREEZE LAURENCE

IPC: B64C3/00 ,  B64C23/06

CPC classification number: B64C3/26 ,  B64C3/187 ,  B64C23/065 ,  B64C23/069 ,  Y02T50/164

Abstract: A joint comprising first and second rib components, the first rib having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface; and the second rib having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface, wherein the abutment surfaces of the respective ribs are abutting and joined with a tension joint, and wherein the lugs are pinned to form a pinned lug joint by aligning respective holes in the plurality of lugs such that the lugs of the first and second ribs are interleaved and have one or more pins passing through the aligned lug holes. The joint may be used for attaching a wing tip device to the outboard end of an aircraft wing.

Abstract translation: 包括第一和第二肋部件的接头，所述第一肋具有邻接表面和邻近所述邻接表面设置的多个凸耳; 并且所述第二肋具有邻接表面和邻近所述邻接表面设置的多个凸耳，其中所述相应肋的邻接表面与张力接头邻接并接合，并且其中所述凸耳被固定以形成钉扎的凸耳接头，由 对准多个凸耳中的相应孔，使得第一和第二肋的凸耳交错并且具有穿过对准的凸耳孔的一个或多个销。 接头可以用于将翼尖装置附接到飞机机翼的外侧端。

公开(公告)号：WO2013007987A2

公开(公告)日：2013-01-17

申请号：PCT/GB2012051581

申请日：2012-07-06

Applicant: AIRBUS OPERATIONS LTD ,  TOPPING SIMON ,  PAYNE CHRISTOPHER ,  WILLIAMS LLIFON ,  MAYNEORD MARTIN ,  BELFOURD DAVID ,  HUE XAVIER ,  AIRBUS OPERATIONS GMBH

Inventor： TOPPING SIMON ,  PAYNE CHRISTOPHER ,  WILLIAMS LLIFON ,  MAYNEORD MARTIN ,  BELFOURD DAVID ,  HUE XAVIER

CPC classification number: B64C13/34 ,  B64C9/02 ,  B64C9/22

Abstract: An aircraft wing comprising a main wing element with a spar and a leading edge rib which is supported by the spar and extends forward of the spar; a high lift device which is movably mounted to the main wing element; and an actuation mechanism comprising a drive shaft and a gear train. The gear train comprising a drive cog which is carried by the drive shaft, an actuator cog which is coupled to the high lift device, and one or more intermediate cogs which are mounted to the rib and coupled in series with the drive cog and the actuator cog so as to transmit torque from the drive cog to the actuator cog which moves the high lift device between a retracted position and an extended position in which the high lift device increases the camber of the wing. The sizes of the cogs in the gear train are selected so that the drive shaft rotates at a higher rate than the high lift device.

Abstract translation: 一种飞机机翼，包括具有翼梁的主翼元件和由翼梁支撑并延伸到翼梁前方的前缘肋骨; 可移动地安装到主翼元件的高升降装置; 以及包括驱动轴和齿轮系的致动机构。 齿轮系包括由驱动轴承载的驱动齿轮，联接到高提升装置的致动器齿轮和一个或多个中间齿轮，其安装到肋并与驱动齿轮串联连接，并且致动器 齿轮，以便将扭矩从驱动齿轮传递到致动器齿轮，致动器齿轮使高升程装置在缩回位置和伸出位置之间移动，在该位置，高升程装置增加机翼的弯度。 选择齿轮系中的齿轮的尺寸，使得驱动轴以比高提升装置更高的速度旋转。