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82 条记录 (耗时 0.014 秒)

    Lifting arrangement for aircraft fuselage
    61.
    发明公开
    Lifting arrangement for aircraft fuselage 审中-公开
    用于飞机机身的浮力装置

    公开(公告)号：EP1405787A3

    公开(公告)日：2004-04-21

    申请号：EP03384203.0

    申请日：2003-09-03

    申请人： Munoz Saiz, Manuel

    发明人： Munoz Saiz, Manuel

    IPC分类号： B64C23/00

    CPC分类号： B64C1/0009 ,  B64C3/58 ,  B64C5/18 ,  B64C23/005 ,  B64C39/10 ,  B64C2001/0045

    摘要： A lifting arrangement for aircraft fuselages (1) that consists of placing longitudinal vertical or slanted fins or plates (4) on the lower and lateral lower part of the whole fuselage, said fins form a channel with the underside of the fuselage, including nose, fuselage and tail, open on their lower area and also add longitudinal horizontal or laterally slanted fins (6,7) on the lateral middle or middle-to-low area of the fuselage and with a slight sloping up on the nose, said fins are arranged in such a way that the upper fins are more projected laterally, and because of this arrangement and their sloping up on the nose direct the air flow downward and backward.

    Lifting arrangement for aircraft fuselage
    62.
    发明公开
    Lifting arrangement for aircraft fuselage 审中-公开
    AuftriebsvorrichtungfürFlugzeugrümpfe

    公开(公告)号：EP1405787A2

    公开(公告)日：2004-04-07

    申请号：EP03384203.0

    申请日：2003-09-03

    申请人： Munoz Saiz, Manuel

    发明人： Munoz Saiz, Manuel

    IPC分类号： B64C23/00

    CPC分类号： B64C1/0009 ,  B64C3/58 ,  B64C5/18 ,  B64C23/005 ,  B64C39/10 ,  B64C2001/0045

    摘要： A lifting arrangement for aircraft fuselages that consists of placing longitudinal vertical or slanted fins or plates on the lower and lateral lower part of the whole fuselage, said fins form a channel with the underside of the fuselage, including nose, fuselage and tail, open on their lower area and also add longitudinal horizontal or laterally slanted fins on the lateral middle or middle-to-low area of the fuselage and with a slight sloping up on the nose, said fins are arranged in such a way that the upper fins are more projected laterally, and because of this arrangement and their sloping up on the nose direct the air flow downward and backward.

    摘要翻译： 纵向垂直或倾斜的翅片定位在机身的下侧部分（4）上。 翅片与机身的下侧（3）形成通道，包括在下部区域打开的鼻子和尾巴。 在机身的侧面中部或中部至下部的纵向水平或横向倾斜的翅片包括朝向鼻子的斜面，以将气流向下和向后引导。

    AN AIRCRAFT CONTROL SURFACE DEPLOYMENT SYSTEM
    63.
    发明公开
    AN AIRCRAFT CONTROL SURFACE DEPLOYMENT SYSTEM 审中-公开

    公开(公告)号：EP4375183A1

    公开(公告)日：2024-05-29

    申请号：EP23210640.1

    申请日：2023-11-17

    申请人： Airbus Operations Limited

    发明人： CUSTANCE, Denys ,  LOPEZBOIX, Marc

    IPC分类号： B64C3/58 ,  B64C9/02 ,  B64C9/32

    CPC分类号： B64C3/58 ,  B64C9/02 ,  B64C9/323

    摘要： An aircraft control surface deployment system (100) for an aircraft structure, for example a spoiler deployment system for an aircraft wing, comprises a cam body (300), an actuator (200) and a coupling mechanism (120). The actuator (200) moves the cam body (300) such that it raises and lowers the aircraft control surface (400). The actuator (200) is connected to the cam body (300) via the coupling mechanism (120). The coupling mechanism (120) has a first portion (320) connected to the cam body (300) and a second portion (220) connected to the actuator (200), configured such that the coupling mechanism (120) allows some free relative movement and rotation of the first and second portions (220, 320). Loads transverse to the axis of movement of the actuator (200), resulting from relative movement of the cam body (300), are not transferred to the actuator (200).

    WINGLET
    65.
    发明公开
    WINGLET 审中-公开
    小翼

    公开(公告)号：EP3248863A1

    公开(公告)日：2017-11-29

    申请号：EP17172495.8

    申请日：2017-05-23

    申请人： Airbus Operations Limited

    发明人： Paisley, Jon ,  Savage, Trudie ,  Moore, Samuel ,  Meisner, Anthony

    IPC分类号： B64C1/26 ,  B64C3/26 ,  B64C23/06 ,  B64C5/08

    CPC分类号： B64C23/069 ,  B64C1/26 ,  B64C3/10 ,  B64C3/26 ,  B64C3/58 ,  B64C5/08 ,  B64C23/06 ,  Y02T50/162

    摘要： Disclosed is a winglet for attachment to a wing portion of an aircraft. The winglet comprises a winglet root. The winglet root defines a recess for receiving a connector of the wing portion in use and comprises at least one protrusion for receipt into at least one corresponding hole of the wing portion in use. A portion of the winglet root that at least partially defines an upper or a lower side of the recess has at least one hole extending therethrough for receiving a fastener for fastening the winglet to the connector when the connector is located in the recess.

    摘要翻译： 公开了用于附接到飞机的机翼部分的小翼。 小翼包括小翼根部。 小翼根部限定用于在使用中接收机翼部分的连接器的凹部，并且包括至少一个突起，用于在使用中接收到机翼部分的至少一个对应的孔中。 至少部分地限定凹槽的上侧或下侧的小翼根部的一部分具有至少一个穿过其延伸的孔，用于接收紧固件，以便当连接器位于凹槽中时将小翼紧固到连接器。

    WING TIP DEVICE
    66.
    发明授权
    WING TIP DEVICE 有权
    FLÜGELSPITZENVORRICHTUNGEN

    公开(公告)号：EP2947006B1

    公开(公告)日：2017-04-12

    申请号：EP15167224.3

    申请日：2011-07-07

    申请人： Airbus Operations Limited ,  Airbus Operations GmbH ,  Deutsches Zentrum für Luft- und Raumfahrt e.V.

    发明人： Wright, Christopher ,  Chu, James, K. ,  Himisch, Jan

    IPC分类号： B64C23/06 ,  B64C3/58

    CPC分类号： B64C23/065 ,  B64C3/58 ,  B64C23/069 ,  Y02T50/164 ,  Y10T29/49716

    摘要： A wing tip device for fixing to the outboard end of a wing (401), the wing (401) defining a wing plane, the wing tip device comprising: an upper wing-like element (404) projecting upwardly with respect to the wing plane and having a trailing edge (416); and a lower wing-like element (407) fixed with respect to the upper wing-like element (404) and having a root chord and a trailing edge (417), the lower wing-like element (407) root chord intersecting with the upper wing-like element (404), and the lower wing-like element (407) projecting downwardly from the intersection, wherein the upper wing-like element (404) is larger than the lower wing-like element (407) and the trailing edge (417) of the lower wing-like element is adjacent the trailing edge (416) of the upper wing-like element at the intersection, and wherein an included angle between the upper and lower wing-like elements (404, 407) 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.

    摘要翻译： 一种翼尖装置，用于固定到翼（401）的外侧端，所述翼（401）限定翼平面，所述翼尖装置包括：相对于翼平面向上突出的上翼形元件（404） 并具有后缘（416）; 和相对于上翼形元件（404）固定并具有根弦和后缘（417）的下翼形元件（407），所述下翼形元件（407）的根弦与 上翼状元件（404）和从交叉点向下突出的下翼形元件（407），其中上翼形元件（404）大于下翼状元件（407），并且尾翼 下翼形元件的边缘（417）在相交处邻近上翼形元件的后缘（416），并且其中上翼形元件（404,407）之间的夹角在 交叉点小于或等于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。