公开(公告)号：EP3395671A1

公开(公告)日：2018-10-31

申请号：EP18173013.6

申请日：2017-05-03

申请人： Airbus Operations Limited

发明人： WILLIAMS, Geoffrey

IPC分类号： B64C1/06 ,  B29C70/20 ,  B64C1/26 ,  B64C3/18

CPC分类号： B64C3/185 ,  B29C70/30 ,  B29K2105/0872 ,  B29K2307/04 ,  B29L2031/3085 ,  B64C1/065 ,  B64C1/26 ,  B64C3/58 ,  Y02T50/43

摘要： An aerofoil shaped body comprises a plurality of longitudinal spars (11, 21), an upper aerofoil cover (22), and a lower aerofoil cover (12). The spars and the covers are made of composite laminate material. One of the spars is integrally formed with one of the covers to form a spar-cover such that the composite laminate material of the spar extends continuously into the cover through a fold region (14, 24) created between the spar and the cover.

公开(公告)号：EP2947006A1

公开(公告)日：2015-11-25

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

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 (301), the wing (301) defining a wing plane, the wing tip device comprising: an upper wing-like element (304) projecting upwardly and having a trailing edge; and a lower wing-like element (307) fixed with respect to the upper wing-like element (304) and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element (304), and the lower wing-like element (307) projecting downwardly from the intersection, wherein the upper wing-like element (304) is larger than the lower wing-like element (307) 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, and wherein the lower wing-like element (307) has an element planform area less than approximately 25% of the upper wing-like element planform area, and 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（301）的外侧端，所述翼（301）限定翼平面，所述翼尖装置包括：向上突出并具有后缘的上翼状元件（304） 和相对于上翼状元件（304）固定并具有根弦和后缘的下翼形元件（307），所述下翼形元件根弦与所述上翼形元件（ 304），并且所述下翼状元件（307）从所述交叉点向下突出，其中所述上翼形元件（304）大于所述下翼形元件（307），并且所述下翼形元件 在相交处的上翼状元件的后缘相邻，并且其中交叉点处的上翼状元件和下翼状元件之间的夹角小于或等于160度，并且其中下部 翼状元件（307）具有小于上翼状元件平面形状面积的约25％的元件平面形状面积，并且还具有带翼尖元件的翼部; 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。

公开(公告)号：EP2945862A1

公开(公告)日：2015-11-25

申请号：EP14740973.4

申请日：2014-01-15

申请人： Otto, William M.

发明人： Otto, William M.

IPC分类号： B64C25/10

CPC分类号： 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

摘要： A front landing gear system for an aircraft including a swing arm rotatively coupled to a wheel, a forward link arm rotatively coupled to the swing arm, a oleopneumatic cylinder rotatively coupled to the swing arm, second extension arm and a bulkhead, a plate rotatively coupled to the bulkhead, an actuation device rotatively coupled to the bulkhead and to the plate, where retraction of the linear actuation device causes the plate and extension arms to move upward towards the bulkhead.

公开(公告)号：EP2610169B1

公开(公告)日：2015-10-21

申请号：EP13161204.6

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： B64C3/58 ,  B64C23/06

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.

公开(公告)号：EP2593362A1

公开(公告)日：2013-05-22

申请号：EP11730015.2

申请日：2011-07-07

申请人： Airbus Operations Limited ,  Airbus Operations GmbH

发明人： WRIGHT, Christopher ,  CHU, James, K. ,  HIMISCH, Jan

IPC分类号： B64C23/06

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.

公开(公告)号：EP2296964B1

公开(公告)日：2012-12-19

申请号：EP08874230.9

申请日：2008-05-09

申请人： The Boeing Company

发明人： LACY, Douglas S. ,  BENN, Gregory S. ,  WHEATON, James M. ,  SANTINI, Gregory M. ,  SAKURAI, Seiya ,  SMITH, Lawrence D.

IPC分类号： B64C7/00 ,  B64C9/16 ,  B64C3/58 ,  B64C9/02 ,  B64C9/04

CPC分类号： B64C7/00 ,  B64C3/58 ,  B64C9/02 ,  B64C9/04 ,  B64C9/16

公开(公告)号：EP2514669A1

公开(公告)日：2012-10-24

申请号：EP11250481.6

申请日：2011-04-18

申请人： Claverham Limited

发明人： Brewer, Paul R. ,  Raval, Reg R. ,  Shorcott, Steven

IPC分类号： B64C3/58 ,  B64C27/615

CPC分类号： B64C3/58 ,  B64C27/615 ,  B64C2003/145 ,  B64C2027/7266 ,  Y02T50/12 ,  Y02T50/34

摘要： A gurney flap assembly (50) includes an actuator (100), and a flexible body (155) attaching to the actuator (100), the body (155) having a downwardly depending flap (160) for moving into and out of an airstream in a pressure side (85) of a wing (75), wherein the flexible body (155) flexes in reaction to motion of the actuator (100). This increases the lift force of the rotor blade, wing or aerofoil blade.

摘要翻译： 一个旋转翼片组件（50）包括致动器（100）和一个附接到致动器（100）的柔性主体（155），该主体（155）具有向下移动的翼片（160），用于移动和移出气流 在翼（75）的压力侧（85）中，其中柔性体（155）响应于致动器（100）的运动而弯曲。 这增加了转子叶片，机翼或机翼叶片的升力。

公开(公告)号：EP2296964A1

公开(公告)日：2011-03-23

申请号：EP08874230.9

申请日：2008-05-09

申请人： The Boeing Company

发明人： LACY, Douglas S. ,  BENN, Gregory S. ,  WHEATON, James M. ,  SANTINI, Gregory M. ,  SAKURAI, Seiya ,  SMITH, Lawrence D.

IPC分类号： B64C7/00 ,  B64C9/16

CPC分类号： B64C7/00 ,  B64C3/58 ,  B64C9/02 ,  B64C9/04 ,  B64C9/16

摘要： Aircraft fillet fairings with fixed and moveable portions, and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a wing (10) having an upper surface (111), an inboard portion, and an outboard portion. A deployable flap (140) is carried by the wing at the inboard portion. The flap has an upper surface and is moveable relative to the wing between a stowed position and a deployed position, with the flap extending aft of the wing when in the deployed position. The system further includes a fillet (120) that in turn includes a forward portion fixed relative to the wing and projecting upwardly from the wing upper surface, and an aft portion (122) that is moveable with the flap. The aft portion projects upwardly from the flap upper surface and is generally aligned with the forward portion in an axial direction.

公开(公告)号：EP1755945A2

公开(公告)日：2007-02-28

申请号：EP05733909.5

申请日：2005-04-07

申请人： Lee, John, R.

发明人： LEE, John, R. ,  LEE, Craig ,  EASTLAKE, Charles ,  LADESIC, James, G. ,  MAHR, Peter ,  PIERPONT, Peter, S. ,  ANDERSON, Richard, P.

IPC分类号： B64C3/54

CPC分类号： B64C3/54 ,  B64C3/56 ,  B64C3/58 ,  B64C11/001 ,  B64C23/072 ,  B64C39/04 ,  Y02T50/164

摘要： This invention relates generally to a lift augmentation system for an airframe. More particularly, the invention concerns the combination of extendable/retractable wing tips with an airframe for lift augmentation as well as wings that can pivot into a deployed position. Flexible surface elements may be rolled for storage and unrolled for deployment with at least one being on the suction surface of the wing and at least one being on the pressure surface of the wing.

摘要翻译： 本发明总体上涉及用于机身的升力增大系统。 更具体地说，本发明涉及可伸展/可伸缩翼梢与用于升力增强的机身的组合以及可枢转到展开位置的翼。 柔性表面元件可以被卷起来存储和展开展开，其中至少一个位于机翼的吸力表面上并且至少一个位于机翼的压力表面上。

公开(公告)号：EP1112927A1

公开(公告)日：2001-07-04

申请号：EP00500262.1

申请日：2000-12-20

申请人： Munoz Saiz, Manuel

发明人： Munoz Saiz, Manuel

IPC分类号： B64C1/00

CPC分类号： B64C1/0009 ,  B64C3/58 ,  B64C5/18 ,  B64C23/005 ,  B64C39/00 ,  B64C39/10 ,  B64C2001/0045

摘要： An aircraft lift arrangement that has a fuselage (1), wings (2), a nose (7), a tail (10) and a landing gear (11) and comprises a stretched, flattened fuselage (3) which produces the lift both during forward movement and in side winds, the bottom of which is preferably flat and the top rounded, with narrow lengthened wings used mainly to carry the engines (14) and provide the flight control surfaces (19), the nose inclined with a positive leading angle, the bottom surface (5) flat and the top rounded, and the tail sloping downward, its lower surface flat and the top rounded, to prevent release of the limit layer in upper areas, with large leading angles. The landing gear (11) is moved rearward somewhat to allow greater nose pitch up attitude during takeoff and landing.

摘要翻译： 具有机身（1），机翼（2），鼻子（7），尾部（10）和起落架（11）的飞行器升降机装置，并且包括拉伸的平坦的机身（3），其产生升降机 在向前运动和侧风期间，其底部优选地是平的，并且顶部是圆形的，其中窄的加长的翼主要用于承载发动机（14）并提供飞行控制表面（19），鼻子倾斜有正的引导 角度，底面（5）平坦，顶部圆形，尾部向下倾斜，下表面平整，顶部圆形，以防止上层限位层释放，具有较大的前角。 起落架（11）稍微向后移动，以允许在起飞和着陆期间更大的鼻子俯仰姿态。