公开(公告)号：EP3301015A1

公开(公告)日：2018-04-04

申请号：EP17194415.0

申请日：2013-06-21

申请人： Bombardier Inc. ,  Learjet Inc.

发明人： XI, Fengfeng ,  FINISTAURI, Allan Daniel ,  MOOSAVIAN, Amin

IPC分类号： B64C3/44 ,  B64C3/52

CPC分类号： B64C3/38 ,  B64C3/385 ,  B64C3/40 ,  B64C3/44 ,  B64C3/52 ,  B64C3/54 ,  B64C2003/445 ,  B64C2003/543 ,  Y02T50/14

摘要： A morphing wing for an aircraft includes a top surface, a bottom surface, a leading edge, a trailing edge, a tip, and a root. A plurality of structural ribs is disposed between the root and tip so that they extend between the top surface and the bottom surface and intersect with a lateral axis thereof. At least one active member connects between two adjacent structural ribs along or at a first angle to the lateral axis. The active member is actively adjustable. At least one passive member connects between the two adjacent structural ribs along or at a second angle to the lateral axis. The passive member is passively adjustable. Adjustment of at least one active member moves the adjacent structural ribs with respect to one another, thereby morphing the wing from a first configuration to a second configuration.

摘要翻译： 飞机的变形机翼包括顶面，底面，前缘，后缘，尖端和根部。 多个结构肋设置在根部和尖端之间，使得它们在顶部表面和底部表面之间延伸并且与其横向轴线相交。 至少一个活动构件沿着或者相对于横向轴线以第一角度连接在两个相邻的结构肋之间。 活动构件可主动调整。 至少一个被动构件沿着或者相对于横向轴线以第二角度连接在两个相邻结构肋之间。 被动部件被动调节。 至少一个主动构件的调节使相邻的结构肋相对于彼此移动，由此使机翼从第一构型变形为第二构型。

公开(公告)号：EP3294624A1

公开(公告)日：2018-03-21

申请号：EP16724685

申请日：2016-05-04

申请人： DESLYPPER CHRISTIAN ROGER RENE

发明人： DESLYPPER CHRISTIAN ROGER RENE

IPC分类号： B64C29/00 ,  B64C3/54 ,  B64C37/00

CPC分类号： B64C29/0025 ,  B64C3/54 ,  B64C39/12

摘要： Convertible airplane capable of flying with the speed and economy of use of an airplane and of taking off/landing vertically and of flying/hovering like a helicopter. The craft that forms the subject of the invention takes the appearance of a conventional airplane, having a fuselage (1), a wing (2), a stabilizer (3) and a rudder (4), as well as one or more jet or turboprop engines (5) for propulsion, and comprises exposable rotors (6 and 7) installed in the wing and possibly in the stabilizer or in the fuselage and providing lift for vertical take off and landing and hovering flight. For horizontal flight and horizontal take off/landing, the rotors are completely encased inside the wing and possibly the stabilizer or the fuselage.

公开(公告)号：EP3077282B1

公开(公告)日：2017-12-27

申请号：EP15766257.8

申请日：2015-07-09

申请人： Akhmejanov, Alibi

发明人： Akhmejanov, Alibi

IPC分类号： B64C9/38 ,  B64C15/14 ,  B64C21/10 ,  B64C29/00

CPC分类号： B64C3/10 ,  B64C3/44 ,  B64C3/54 ,  B64C9/00 ,  B64C9/38 ,  B64C15/14 ,  B64C21/10 ,  B64C29/0016 ,  B64C39/024 ,  Y02T50/166 ,  Y02T50/32

公开(公告)号：EP3134314A1

公开(公告)日：2017-03-01

申请号：EP15714912.1

申请日：2015-04-02

申请人： Airbus Operations Limited

发明人： AXFORD, Tim ,  FONG, Tony ,  ALEXANDER, Stuart

IPC分类号： B64C23/06 ,  B64C3/18 ,  B64C3/54 ,  B64C3/56

CPC分类号： B64C23/072 ,  B64C3/185 ,  B64C3/54 ,  B64C3/546 ,  B64C3/56 ,  Y02T50/14 ,  Y02T50/164

摘要： An aircraft including a wing (1) and a wing tip device (6). The wing tip device (6) is moveable between a flight configuration for use during flight and a ground configuration for use during ground-based operations. In the ground configuration the wing tip device is folded inwardly from the flight configuration such that the span of the aircraft is reduced. The wing tip device (6) is connected to the wing along a hinge axis (14) by spar beams (10 and 12) of the wing tip device, one of the beams being mounted for pivoting about a fixed axis and the other beam being mounted on a spherical bearing (15) to provide greater freedom of movement. Various actuator arrangements may be provided to pivot the wing tip device.

摘要翻译： 一种包括翼（1）和翼尖装置（6）的飞机。 翼尖装置（6）可以在飞行期间使用的飞行构型和在地面操作期间使用的地面构型之间移动。 在地面构造中，翼尖装置从飞行构造向内折叠，使得飞行器的跨度减小。 翼尖装置（6）通过翼尖装置的翼梁梁（10和12）沿着铰链轴线（14）连接到机翼，其中一个梁被安装成围绕固定轴线枢转，另一个梁是 安装在球面轴承（15）上以提供更大的移动自由度。 可以提供各种致动器装置以枢转翼尖装置。

公开(公告)号：EP2834146A4

公开(公告)日：2015-12-09

申请号：EP13773104

申请日：2013-03-22

申请人： TAMARACK AEROSPACE GROUP INC

发明人： GUIDA NICHOLAS R

IPC分类号： B64C23/06 ,  B64C3/38 ,  B64C5/10 ,  B64C13/16

CPC分类号： B64C3/54 ,  B64C5/16 ,  B64C13/16 ,  B64C23/076 ,  Y02T50/145 ,  Y02T50/164

摘要： An active wing extension includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes multiple controllable airflow modification devices coupled thereto. By virtue of having multiple controllable airflow modification devices, the wing extension is capable of adjusting control surfaces of the multiple controllable airflow modification devices in response to in-flight conditions, to reduce wing loads, improve wing fatigue characteristics, increase range, and/or increase efficiency.

摘要翻译： 主动翼延伸部包括基本上平行于飞行器的翼的主体部分，好像它是机翼的延伸部分。 主体部分可附接到飞行器机翼并且包括耦合到其上的多个可控气流改变装置。 由于具有多个可控气流改变装置，机翼延伸部能够响应于飞行中的条件来调节多个可控气流改变装置的控制表面，以减少机翼载荷，改善机翼疲劳特性，增加范围和/或 提高效率。

公开(公告)号：EP2755889A1

公开(公告)日：2014-07-23

申请号：EP12750366.2

申请日：2012-08-21

申请人： EADS Deutschland GmbH ,  Airbus Operations GmbH

发明人： HAVAR, Tamas ,  PEREZ-SANCHEZ, Juan ,  ENDER, Tobias ,  SEACK, Oliver

IPC分类号： B64C9/16

CPC分类号： B64C13/28 ,  B64C3/54 ,  B64C9/02 ,  B64C9/16

摘要： The invention relates to a lift flap bearing device (22, 24) which is improved with respect to aerodynamics, installation space, and assembly for guiding and adjusting a first lift flap (16; 18) and a second lift flap (18; 20), comprising a first guiding device (30) for guiding the first lift flap (16; 18) and comprising a second guiding device (32) for guiding the second lift flap (18; 20). The first and the second guiding device (30, 32) each has a first curved guiding rail (40) and a second curved guiding rail (42).

摘要翻译： 相对于空气动力学，建筑空间和组装，升降板轴承装置得到改进，用于引导和调节第一升降襟翼和第二提升襟翼。 提升板轴承装置包括用于引导第一提升挡板的第一引导装置和用于引导第二提升挡板的第二引导装置。 第一和第二引导装置各自具有第一弯曲导轨和第二弯曲导轨。

公开(公告)号：EP2285671B1

公开(公告)日：2012-10-24

申请号：EP09747107.2

申请日：2009-04-16

申请人： Raytheon Company

发明人： SAR, David, R. ,  SANDERSON, Terry, M.

IPC分类号： B64C3/54 ,  F03G7/06 ,  C22F1/18 ,  B29C61/00

CPC分类号： B64C3/54 ,  B29C61/00 ,  B29L2031/3085 ,  F01D5/14 ,  F01D5/28 ,  F05B2240/31 ,  F05D2250/70 ,  Y02T50/14 ,  Y02T50/671 ,  Y02T50/673 ,  Y10T428/12333

摘要： A shape-changing structural member has a shape-changing material, such as a suitable foam material, for example a polymer foam capable of withstanding at least 300% strain or a metal alloy foam capable of withstanding at least 5% strain. Springs, such as one or more coil springs, provide structural support for the shape-changing material. The springs may also be used to provide forces to expand and contract the shape change material. The springs may include pairs of concentric springs, one inside of another. The concentric springs may surround an underlying skeleton structure that supports the shape-changing material and/or aids in changing the shape of the material. The concentric springs may or may not be wrapped around the underlying skeleton structure. Multiple springs or pairs of springs may be coupled together using a sheet metal connector.

公开(公告)号：EP2452873A2

公开(公告)日：2012-05-16

申请号：EP11187906.0

申请日：2011-11-04

申请人： Bell Helicopter Textron Inc.

发明人： Robertson, Daniel B ,  Groninga, Kirk L

IPC分类号： B64C3/54 ,  B64C15/02 ,  B64C27/26 ,  B64C27/82

CPC分类号： B64C27/22 ,  B64C3/54 ,  B64C15/02 ,  B64C27/26 ,  B64C27/82 ,  B64C2027/8245 ,  Y02T50/14

摘要： A system and method to control flight of an aircraft. The aircraft (101; 1001) having an engine (111; 1017) with a rotatably nozzle assembly (401) configured to create forward propulsion and yaw control of the aircraft (101; 1001). The engine exhaust (129c) passing through the nozzle (401) is redirected with a valve (419) disposed within the nozzle (401). Lift is created with a lift system (1009) carried by the wing (1007) of the aircraft (1001). Additional lift is created during flight with a retractable wing extension (1015) disposed within the wing (1007) of the aircraft (1001).

摘要翻译： 一种控制飞机飞行的系统和方法。 具有具有可旋转喷嘴组件（401）的发动机（111; 1017）的飞行器（101; 1001）被配置成产生飞行器（101; 1001）的向前推进和偏航控制。 通过喷嘴（401）的发动机排气（129c）通过设置在喷嘴（401）内的阀（419）重新定向。 升降机由飞行器（1001）的机翼（1007）承载的升降机系统（1009）产生。 在飞行期间产生额外的升力，其中可伸展的机翼延伸部（1015）设置在飞行器（1001）的机翼（1007）内。

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：EP0973676B8

公开(公告)日：2005-08-24

申请号：EP98919740.5

申请日：1998-04-08

申请人： Lee, John, R.

发明人： Wagner, Fred A. III

IPC分类号： B64C3/54

CPC分类号： B64C3/54 ,  Y02T50/14

摘要： A retractable airfoil assembly (20) augments the wing surface area (28) of an aircraft (22) enabling it to fly without stalling at reduced speeds during takeoff and landing. The airfoil assembly includes flexible sails (42, 44) and a furling mast (24) for extending and retracting the sails. The furling mast includes a furling drum mounted for clockwise and counterclockwise rotation on a static tube (50). The flexible sail assembly also includes guide tracks (80) located along a leading edge (101) or tailing edge (40) of the wings. The tracks guide the flexible sails during extension and retraction. A drive cable (26) extends and retracts the sails (42, 44) along the guide tracks and maintains tension in the sails while they are extended.

摘要翻译： 可缩回的翼型组件（20）增大了飞机（22）的机翼表面区域（28），使其能够在起飞和着陆期间以降低的速度飞行而不会失速。 翼型组件包括用于延伸和收回帆的柔性帆（42,44）和收拢桅杆（24）。 收拢的桅杆包括一个安装在静态管（50）上顺时针和逆时针旋转的收卷鼓。 柔性帆组件还包括沿着机翼的前缘（101）或后缘（40）定位的导轨（80）。 轨道在延伸和收回期间引导柔性帆。 驱动缆索（26）沿着导轨延伸和缩回帆（42,44），并在帆延伸时保持帆中的张力。