公开(公告)号：EP1940680B2

公开(公告)日：2018-02-28

申请号：EP06851632.7

申请日：2006-08-29

申请人： The Boeing Company

发明人： KORDEL, Jan A. ,  SAKURAI, Seiya ,  BOWERS, Bret A. ,  GLASSMOYER, Chris ,  WILLIAMS, Darren B.

IPC分类号： B64C9/02 ,  B64C7/00

CPC分类号： B64C7/00 ,  B64C9/18 ,  B64C2009/143 ,  Y02T50/32 ,  Y10S277/916

摘要： Aerodynamic seals for use with control surfaces on aircraft are described herein. In one embodiment, a seal assembly for use with an aircraft includes a first seal member and a second seal member. The first seal member has a first proximal portion configured to be attached to a fixed airfoil portion of the aircraft, and a first distal portion configured to extend outwardly from the fixed airfoil portion toward a movable control surface. The second seal member has a second proximal portion configured to be attached to the movable control surface, and a second distal portion configured to extend outwardly from the control surface toward the fixed airfoil portion. In this embodiment, the second distal portion is further configured to movably contact the first distal portion to at least partially seal the gap between the fixed airfoil portion and the movable control surface as the control surface moves relative to the fixed airfoil portion.

公开(公告)号：EP2902314B1

公开(公告)日：2017-07-19

申请号：EP14153117.8

申请日：2014-01-29

申请人： Airbus Operations GmbH

发明人： Henning, Frieder ,  Brady, Michael ,  Zantz, Tanno

IPC分类号： B64C9/22 ,  B64C9/24 ,  F03D1/06

CPC分类号： B64C9/22 ,  B64C9/24 ,  B64C13/50 ,  B64C2009/143 ,  F03D1/0641 ,  Y02E10/721

摘要： A high lift system (2) for an aircraft comprises a wing structure (4) and a leading edge slat (6) movably supported relative to a leading edge of the wing structure (4), the leading edge slat (6) comprises a leading edge (14) and a trailing edge (16), wherein the trailing edge (16) is configured to take different positions to form a gap between the leading edge slat (6) and the wing structure (4), a skin (8) and enclosing an interior space (18) of the leading edge slat (6), the skin (8) having a flexible leading skin (10) section facing away from the wing structure (4), a flexible trailing skin section (12) facing towards the wing structure (4), at least one actuation arrangement (20) arranged inside the interior space (18) for selectively introducing a normal force onto at least one of the leading skin section (10) and the trailing skin section (12), wherein said normal force changes the profile of the skin (8) in such a way that the trailing edge (16) changes its position relative to the wing structure (4) to selectively close or open the gap between the leading edge slat (6) and the wing structure (4). This provides a mechanical actuation concept to achieve an active gap control through structural morphing of a slat body.

摘要翻译： 一种用于飞机的高升力系统（2）包括机翼结构（4）和相对于机翼结构（4）的前缘可移动地支撑的前缘缝翼（6），前缘缝翼（6）包括前缘 （6）和所述机翼结构（4）之间形成间隙的不同位置，皮肤（8），所述皮肤（8）和所述前缘（14）以及后缘（16） （6）的内部空间（18），所述蒙皮（8）具有背向所述机翼结构（4）的柔性前蒙皮（10）部分，柔性的后蒙皮部分（12） 朝向所述机翼结构（4），布置在所述内部空间（18）内的至少一个致动装置（20），用于将法向力选择性地引导到所述前蒙皮区段（10）和所述后蒙皮区段（12）中的至少一个上， ，其中所述法向力以这样的方式改变蒙皮（8）的轮廓，使得后缘（16）相对于 机翼结构（4）选择性地关闭或打开前缘缝翼（6）和机翼结构（4）之间的间隙。 这提供了机械驱动概念，以通过板条体的结构变形实现有效的间隙控制。

公开(公告)号：EP3184416A1

公开(公告)日：2017-06-28

申请号：EP16203459.9

申请日：2016-12-12

申请人： Airbus Operations Limited

发明人： VINCENT, Tristan ,  SHARP, Kim ,  HOPTROFF, David

IPC分类号： B64C3/50 ,  F02K1/80 ,  F16J15/00 ,  B64C9/02 ,  B64C9/18 ,  F02C7/28 ,  B64C9/16 ,  B64C9/14

CPC分类号： F16J15/02 ,  B64C3/50 ,  B64C9/02 ,  B64C9/16 ,  B64C9/20 ,  B64C2009/143 ,  F02C7/28 ,  F02K1/805 ,  F16J15/00

摘要： An aircraft wing (2) has a fixed wing portion (2a) and a trailing edge flap (3b) movable with respect to the fixed wing portion to define a gap (g) between the fixed wing and the flap. A seal assembly (8) for sealing the gap has a first rigid seal member (8a) fixed to the fixed wing portion and a second resilient seal member (8b) fixed to an upper surface leading edge (15) portion of the flap. The trailing edge flap is deployable between a first flap position in which the trailing edge flap conforms to a profile of the fixed wing portion, a second flap position in which the trailing edge flap is deflected upwardly from the first flap position, and a third flap position in which the trailing edge flap is deflected downwardly from the first flap position. In the first flap position the first seal member contacts the second seal member to at least partially seal the gap, and in the second flap position the first seal member presses against the second seal member and deflects the second seal member to at least partially seal the gap.

摘要翻译： 飞机机翼（2）具有相对于固定机翼部分可移动的固定机翼部分（2a）和后缘襟翼（3b），以在固定机翼和襟翼之间限定间隙（g）。 用于密封间隙的密封组件（8）具有固定到固定翼部分的第一刚性密封构件（8a）和固定到翼片的上表面前缘（15）部分的第二弹性密封构件（8b）。 后缘襟翼可在第一襟翼位置和第三襟翼之间展开，在第一襟翼位置中，后缘襟翼与固定的机翼部分的轮廓相符，第二襟翼位置中后缘襟翼从第一襟翼位置向上偏转， 后缘襟翼从第一襟翼位置向下偏转的位置。 在第一襟翼位置中，第一密封构件接触第二密封构件以至少部分地密封间隙，并且在第二襟翼位置中，第一密封构件压靠第二密封构件并且偏转第二密封构件以至少部分地密封 间隙。

公开(公告)号：EP2669190B1

公开(公告)日：2017-05-10

申请号：EP13167503.5

申请日：2013-05-10

申请人： The Boeing Company

发明人： Kordel, Jan A. ,  Sakurai, Seiya

IPC分类号： B64C9/14 ,  B64C9/18

CPC分类号： B64C1/10 ,  B64C9/16 ,  B64C9/18 ,  B64C2009/143

摘要： A rotary actuated high lift gapped aileron linkage (304) is presented. A high lift gapped aileron (306) couples to an airfoil at a hinge line (418) and changes a camber of the airfoil. A rotary actuator (312) coupled to the high lift gapped aileron produces a rotary motion of the high lift gapped aileron in response to an actuation command. A droop panel (308) positioned over the hinge line enhances lift of the high lift gapped aileron. A cove lip door (310) positioned under the hinge line provides an airflow over the high lift gapped aileron. The deployment linkage mechanism coupled to the high lift gapped aileron positions the droop panel and the cove lip door in response to the rotary motion.

摘要翻译： 提出了旋转致动的高升力有间隙副翼连杆（304）。 高升力有间隙的副翼（306）在铰接线（418）处耦合到翼型并且改变翼型的外倾角。 耦合到高升力有间隙副翼的旋转致动器（312）响应于致动命令产生高升力有间隙副翼的旋转运动。 定位在铰接线上的下垂面板（308）增强了高升力有间隙的副翼的升力。 位于铰接线下方的海湾边门（310）在高升力有间隙的副翼上提供气流。 联接到高升力有间隙副翼的展开联动机构响应于旋转运动来定位下垂板和凹腔唇门。

公开(公告)号：EP2832638A1

公开(公告)日：2015-02-04

申请号：EP13768891.7

申请日：2013-03-29

申请人： The Society of Japanese Aerospace Companies ,  Kawasaki Jukogyo Kabushiki Kaisha

发明人： ISOTANI, Kazuhide ,  HAYAMA, Kenji

IPC分类号： B64C9/18

CPC分类号： B64C21/08 ,  B64C3/50 ,  B64C9/02 ,  B64C9/18 ,  B64C2009/143 ,  B64C2230/14 ,  Y02T50/166

摘要： A high-lift device (3) comprises a flap body (11) which is provided at a rear portion of a main wing (2) which generates a lift for the air vehicle such that the flap body is deployed with respect to the main wing and stowed in the main wing and extends along a wingspan direction of the main wing (2); and a gap increasing section (20, 30) provided at an end portion (11a) of the flap body (11) in an extending direction of the flap body, to increase a gap between the rear portion of the main wing (2) and a front portion of the flap body (11) in a state in which the flap body is deployed.

摘要翻译： 高升降装置（3）包括翼片主体（11），其设置在主翼（2）的后部，其产生用于空中飞行器的升降机，使得翼片主体相对于主翼 并存放在主翼中并沿着主翼（2）的翼展方向延伸; 以及在翼片主体的延伸方向上设置在翼片主体（11）的端部（11a）处的间隙增加部（20,30），以增加主翼（2）的后部与 翼片主体（11）的前部部分处于翼片主体展开的状态。

公开(公告)号：EP2711290A1

公开(公告)日：2014-03-26

申请号：EP13185031.5

申请日：2013-09-18

申请人： The Boeing Company

发明人： Dahl, Bruce A. ,  Quandt, Gene A.

IPC分类号： B64C9/32 ,  B64C9/14

CPC分类号： B64C9/20 ,  B64C9/323 ,  B64C2009/143 ,  Y02T50/32

摘要： An aircraft flap system and an associated method are provided to facilitate ground roll breaking without compromising in-flight performance. The aircraft flap system includes a first flap (12) and a panel (14) pivotally attached to the first flap, such as to a rearward portion of the first flap (12). The aircraft flap system also includes an actuator (15) configured to controllably position the panel in a stowed position and in a deployed position. In the stowed position, the panel serves as a continuation of the first flap (12), thereby contributing to the lift provided by the first flap during flight. Conversely, in the deployed position, a panel is articulated relative to the first flap (12), thereby reducing or eliminating the lift otherwise provided by the flap, following landing of the aircraft.

摘要翻译： 提供飞行器翼片系统和相关联的方法以便于地面滚动断裂而不损害飞行性能。 飞行器翼片系统包括第一翼片（12）和枢转地附接到第一翼片的面板（14），例如到第一翼片（12）的后部。 飞行器翼片系统还包括致动器（15），其构造成将面板可控地定位在收起位置和展开位置。 在收起位置中，面板用作第一挡板（12）的延续部，从而有助于在飞行期间由第一挡板提供的升力。 相反，在展开位置中，面板相对于第一挡板（12）铰接，从而减少或消除在飞行器着陆之后由挡板提供的升降机。

公开(公告)号：EP2524865A1

公开(公告)日：2012-11-21

申请号：EP12168617.4

申请日：2012-05-21

申请人： AIRBUS OPERATIONS LIMITED

发明人： Parker, Simon John

IPC分类号： B64C9/12 ,  B64C9/16 ,  B64C13/00 ,  B64C9/32

CPC分类号： B64C9/20 ,  B64C9/16 ,  B64C2009/143

摘要： An aircraft wing assembly, comprising: a fixed wing portion; a first flight control surface; a first actuator operatively coupled to the first flight control surface for moving the first flight control surface with respect to the fixed wing portion; a second flight control surface disposed adjacent the first flight control surface; a second actuator operatively coupled to the second flight control surface for moving the second flight control surface with respect to the fixed wing portion; a control system operatively coupled to the first and second actuators for controlling movement of the first and second flight control surfaces; and a third actuator selectively engaged with the second flight control surface for engaging and moving the second flight control surface out of a path of movement of the first flight control surface only in the event of a failure in the second actuator or its control, so as to avoid direct contact between the first and second flight control surfaces. Also, a method of operating an aircraft wing assembly.

摘要翻译： 一种飞机机翼组件，包括：固定翼部分; 第一个飞行控制面; 第一致动器，其可操作地联接到所述第一飞行控制表面，用于相对于所述固定翼部分移动所述第一飞行控制表面; 设置在第一飞行控制表面附近的第二飞行控制表面; 第二致动器，其可操作地联接到所述第二飞行控制表面，用于相对于所述固定翼部分移动所述第二飞行控制表面; 控制系统，其可操作地联接到所述第一和第二致动器，用于控制所述第一和第二飞行控制表面的运动; 以及第三致动器，其选择性地与所述第二飞行控制表面接合，用于仅在所述第二致动器或其控制中发生故障的情况下将所述第二飞行控制表面从所述第一飞行控制表面的移动路径接合和移动，从而 以避免第一和第二飞行控制表面之间的直接接触。 另外，操作飞机机翼组件的方法。

公开(公告)号：EP2149495A4

公开(公告)日：2012-10-31

申请号：EP08764375

申请日：2008-05-20

申请人： MITSUBISHI HEAVY IND LTD

发明人： HIRAI MAKOTO ,  MAEDA ICHIRO

IPC分类号： B64C9/24

CPC分类号： B64C9/24 ,  B64C2009/143

公开(公告)号：EP1868887B1

公开(公告)日：2011-01-19

申请号：EP06724150.5

申请日：2006-04-07

申请人： Airbus Operations GmbH

发明人： BENDER, Klaus ,  BOETTGER, Ole

IPC分类号： B64C9/14

CPC分类号： B64C9/20 ,  B64C9/02 ,  B64C9/18 ,  B64C2009/143 ,  Y02T50/44

摘要： The present invention relates to a device for adjusting the lift characteristics of an aircraft with a high lift device (2) that is movably attachable to a wing element (1) and that comprises at least one slot covering device (3; 4), wherein the at least one slot covering device (3; 4), is movably attachable to the wing element (1). The slot covering device (3; 4) is designed to regulate the size of a slot (7) between the wing element (1) and the high lift device (2).

公开(公告)号：EP2149495A1

公开(公告)日：2010-02-03

申请号：EP08764375.5

申请日：2008-05-20

申请人： Mitsubishi Heavy Industries, Ltd.

发明人： HIRAI, Makoto ,  MAEDA, Ichiro

IPC分类号： B64C9/24

CPC分类号： B64C9/24 ,  B64C2009/143

摘要： The present invention provides high-lift devices, wings, and noise reduction structures for the high-lift devices capable of suppressing the occurrence of aerodynamic noise while restricting an increase in airframe weight. A high-lift device includes: a slat main body (4) that is disposed so as to be able to extend from and retract into a main wing; a concave part (5) that is formed on the slat main body (4) at a location that faces the main wing, so as to be able to accommodate at least a part of a leading edge of the main wing; and an airflow control part (6) that is disposed at an area in the concave part (5) facing an upper surface of the main wing, that is accommodated between the main wing and the concave part when the slat main body (4) is retracted into the main wing, and that suppresses turbulence colliding against the area in the concave part (5) facing the upper surface of the main wing when the slat main body (4) is extended from the main wing.

摘要翻译： 本发明为能够抑制空气动力噪声的发生同时限制机身重量的增加的高升力装置提供高升力装置，机翼和降噪结构。 高升降装置包括：板条主体（4），其被设置成能够从主翼伸出并缩回到主翼中; 形成在所述板条主体（4）上的面向所述主翼的位置的凹部（5），以能够容纳所述主翼的前缘的至少一部分; 以及气流控制部（6），其设置在所述凹部（5）的面向所述主翼的上表面的区域，当所述板条主体（4）为 并且当主板（4）从主翼部延伸时，能够抑制湍流与面向主翼的上表面的凹部（5）的区域碰撞。