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    AIRCRAFT ASSEMBLY WITH MOVEABLE DEVICE
    1.
    发明公开
    AIRCRAFT ASSEMBLY WITH MOVEABLE DEVICE 审中-公开

    公开(公告)号：US20240253766A1

    公开(公告)日：2024-08-01

    申请号：US18422909

    申请日：2024-01-25

    Applicant: AIRBUS OPERATIONS LIMITED

    Inventor： Denys CUSTANCE

    IPC: B64C9/02 ,  B64C3/26 ,  B64C3/58

    CPC classification number: B64C9/02 ,  B64C3/58 ,  B64C3/26

    Abstract: An aircraft assembly is disclosed having a cover with an outer aerodynamic surface and an aperture with a stop adjacent an edge of the aperture, and a moveable device for extending through the aperture in the cover. The moveable device carries a panel attached to the moveable device by a plurality of leaf springs. The assembly is configured so that when the moveable device is moved towards a retracted position the panel bears against the stop forming a substantially flush surface with the outer aerodynamic surface of the cover surrounding the aperture. The panel is displaced from the moveable device by elastic deformation of at least some of the leaf springs.

    A ROTATIONAL JOINT FOR AN AIRCRAFT FOLDING WING
    4.
    发明申请
    A ROTATIONAL JOINT FOR AN AIRCRAFT FOLDING WING 审中-公开

    公开(公告)号：US20180194453A1

    公开(公告)日：2018-07-12

    申请号：US15737608

    申请日：2016-06-06

    Applicant: Airbus Operations Limited

    Inventor： John David RANDALL ,  Stuart ALEXANDER ,  Matthew HARDING

    IPC: B64C3/56 ,  B64C23/06

    CPC classification number: B64C3/56 ,  B64C3/58 ,  B64C5/08 ,  B64C23/072 ,  Y02T50/14

    Abstract: A folding wing having a wing tip device (3) rotatable between flight and ground configurations, about an Euler axis of rotation (11). The wing tip device (3) and a fixed wing (1) are separated along an oblique cut plane (13) passing through the upper and lower surfaces of the folding wing. A rotational joint (15) for coupling the wing tip device (3) to the fixed wing (1) during rotation between the ground and flight configurations. The rotational joint includes a follower (17a) and a guide (17b), one which being fixed relative to the wing tip device and the other being fixed relative to the fixed wing. The follower and guide interlock such as by interlocking rings. The follower is received in the guide such that during rotation between the ground and flight configurations the follower moves along the arcuate path defined by the guide.

    SPIN RESISTANT AIRCRAFT CONFIGURATION
    6.
    发明申请
    SPIN RESISTANT AIRCRAFT CONFIGURATION 审中-公开
    抗旋转飞机配置

    公开(公告)号：US20170021916A1

    公开(公告)日：2017-01-26

    申请号：US15090945

    申请日：2016-04-05

    Applicant: ICON AIRCRAFT, INC.

    Inventor： Matthew Gionta ,  Jon Karkow ,  John Roncz ,  Dieter Koehler ,  David Lednicer

    IPC: B64C21/10 ,  B64C5/02 ,  B64C3/10

    CPC classification number: B64C21/10 ,  B64C3/10 ,  B64C3/58 ,  B64C5/02 ,  B64C21/00 ,  B64C23/06 ,  B64C35/001 ,  B64C35/008 ,  Y02T50/12 ,  Y02T50/162

    Abstract: A configuration and system for rendering an aircraft spin resistant is disclosed. Resistance of the aircraft to spinning is accomplished by constraining a stall cell to a wing region adjacent to the fuselage and distant from the wing tip. Wing features that facilitate this constraint include but are not limited to one or more cuffs, stall strips, vortex generators, wing twists, wing sweeps and horizontal stabilizers. Alone or in combination, aircraft configuration features embodied by the present invention render the aircraft spin resistant by constraining the stall cell, which allows control surfaces of the aircraft to remain operational to control the aircraft.

    Abstract translation: 公开了用于使飞机防旋转的构造和系统。 飞机对旋转的阻力是通过将失速室限制在与机身相邻并远离翼尖的机翼区域来实现的。 促成这种约束的翼特征包括但不限于一个或多个袖口，失速条，涡流发生器，翼扭，机翼扫掠和水平稳定器。 单独或组合地，由本发明体现的飞行器配置特征使得飞机通过约束失速单元来防旋转，这使得飞机的控制表面保持操作以控制飞行器。

    High-lift device of flight vehicle
    7.
    发明授权
    High-lift device of flight vehicle 有权
    飞机高架装置

    公开(公告)号：US09302761B2

    公开(公告)日：2016-04-05

    申请号：US14008139

    申请日：2012-03-28

    Applicant: Kazuhide Isotani ,  Kenji Hayama

    Inventor： Kazuhide Isotani ,  Kenji Hayama

    IPC: B64C23/06 ,  B64C3/58 ,  B64C9/18 ,  B64C9/28 ,  B64C21/02

    CPC classification number: B64C9/18 ,  B64C3/58 ,  B64C9/16 ,  B64C9/28 ,  B64C21/02 ,  B64C2230/22 ,  Y02T50/166 ,  Y02T50/44

    Abstract: A high-lift device of a flight vehicle includes: a flap main body provided at a trailing edge portion of a main wing of the flight vehicle so as to be extracted from and be retracted in the trailing edge portion and extending in a wing span direction of the main wing; and a vortex suppressing portion provided at a tip end portion of the flap main body in a wing span direction of the flap main body and configured to suppress a vortex rolling up from a lower surface of a tip end portion of the flap main body to an upper surface of the tip end portion.

    Abstract translation: 飞行器的高升力装置包括：翼片主体，其设置在飞行器车辆的主翼的后缘部分处，以便从后缘部分抽出并缩回到后翼部分中，并且沿翼展方向延伸 的主翼; 以及涡旋抑制部，其在所述翼片主体的翼展方向上设置在所述翼片主体的前端部，并且被构造成抑制从所述翼片主体的前端部的下表面到 前端部的上表面。

    Wing tip device
    8.
    发明授权
    Wing tip device 有权
    翼尖装置

    公开(公告)号：US09193445B2

    公开(公告)日：2015-11-24

    申请号：US14668471

    申请日：2015-03-25

    Applicant: AIRBUS OPERATIONS LIMITED ,  AIRBUS OPERATIONS GMBH

    Inventor： Christopher Wright ,  James K. Chu ,  Jan Himisch

    IPC: B64C23/06

    CPC classification number: B64C23/065 ,  B64C3/58 ,  B64C23/069 ,  Y02T50/164 ,  Y10T29/49716

    Abstract: A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection, wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, and wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees. Also, a wing with the wing tip device; an aircraft with the wing; a method of fitting, or retro-fitting, the wing tip device to a wing; a method of modifying an existing wing tip device; and a method of operating a wing with the wing tip device.

    Abstract translation: 一种翼尖装置，用于固定到翼的外侧端，所述翼限定翼平面，所述翼尖装置包括：相对于翼平面向上突出并具有后缘的上翼状元件; 以及相对于上翼形元件固定并具有根弦和后缘的下翼形元件，所述下翼形元件根弦与所述上翼形元件相交，并且所述下翼形元件 其中所述上翼形元件大于所述下翼形元件，并且所述下翼形元件的后缘在所述交叉点处邻近所述上翼状元件的后缘， 并且其中所述交叉点处的所述上翼状元件和下翼形元件之间的夹角小于或等于160度。 另外，一翼与翼尖装置; 一架飞机与翼; 将翼尖装置装配或改装成翼的方法; 修改现有翼尖装置的方法; 以及用翼尖装置操作机翼的方法。

    Wingtip fin of an aircraft
    9.
    发明授权
    Wingtip fin of an aircraft 有权
    翼飞翅飞机

    公开(公告)号：US09096308B2

    公开(公告)日：2015-08-04

    申请号：US13755314

    申请日：2013-01-31

    Applicant: AIRBUS OPERATIONS LIMITED

    Inventor： George Edmond ,  Robert L. J. Thompson

    IPC: B64C23/06 ,  B64C3/58 ,  H05K5/00 ,  G09F21/10

    CPC classification number: B64C3/58 ,  B64C23/069 ,  G09F21/10 ,  H05K5/0017 ,  Y02T50/164

    Abstract: A wingtip fin of an aircraft comprising an upstanding fin body, the fin body having an inboard face and an outboard face and a recess defined there within, a display screen assembly in the recess in the fin body, the display screen assembly comprising a translucent face, substantially flush with and forming at least part of the inboard face or the outboard face of the fin body, and a display screen arranged in the recess such that images displayed on the display screen are visible through the translucent face.

    Abstract translation: 一种飞机的翼尖，包括直立的翅片体，翅片本体具有内侧面，外侧面和在其内部限定的凹部，在翅片体的凹部中的显示屏组件，所述显示屏组件包括半透明面 与翅片本体的内侧面或外侧面的至少一部分基本齐平并形成，以及布置在凹部中的显示屏，使得通过半透明面可见显示在显示屏上的图像。

    Wing Tip Device
    10.
    发明申请
    Wing Tip Device 审中-公开
    翼尖装置

    公开(公告)号：US20150203191A1

    公开(公告)日：2015-07-23

    申请号：US14675007

    申请日：2015-03-31

    Applicant: AIRBUS OPERATIONS LIMITED ,  AIRBUS OPERATION GMBH

    Inventor： Christopher WRIGHT ,  James K. Chu ,  Jan Himisch

    IPC: B64C23/06

    CPC classification number: B64C23/065 ,  B64C3/58 ,  B64C23/069 ,  Y02T50/164 ,  Y10T29/49716

    Abstract: A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like clement projecting downwardly from the intersection, wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, and wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees. Also, a wing with the wing tip device; an aircraft with the wing; a method of fitting, or retro-fitting, the wing tip device to a wing; a method of modifying an existing wing tip device; and a method of operating a wing with the wing tip device.

    Abstract translation: 一种翼尖装置，用于固定到翼的外侧端，所述翼限定翼平面，所述翼尖装置包括：相对于翼平面向上突出并具有后缘的上翼状元件; 以及相对于上翼形元件固定并具有根弦和后缘的下翼形元件，所述下翼形元件根弦与所述上翼形元件相交，并且所述下翼形元件 其中上翼状元件大于下翼形元件，下翼形元件的后缘在相交处与上翼形元件的后缘相邻， 并且其中所述交叉点处的所述上翼状元件和下翼形元件之间的夹角小于或等于160度。 另外，一翼与翼尖装置; 一架飞机与翼; 将翼尖装置装配或改装成翼的方法; 修改现有翼尖装置的方法; 以及用翼尖装置操作机翼的方法。

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