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1. 发明授权

EP3126222B1 AN AIRCRAFT COMPRISING A FOLDABLE AERODYNAMIC STRUCTURE AND A METHOD OF MANUFACTURING A FOLDABLE AERODYNAMIC STRUCTURE FOR AN AIRCRAFT 有权
公开(公告)号：EP3126222B1
公开(公告)日：2018-12-05
申请号：EP15714916.2
申请日：2015-04-02
申请人： Airbus Operations Limited
发明人： ALEXANDER, Stuart , RANDALL, John
IPC分类号： B64C3/40 , B64C3/42 , B64C3/56
CPC分类号： B64C3/56 , B64C3/40 , B64C3/42 , B64F5/10 , Y02T50/14
摘要： A method of manufacturing a foldable aerodynamic structure, such as a wing, for an aircraft. The wing (1) including an inner region (1) and an outer region (3) rotatable relative to the inner region between a flight configuration and a ground configuration. The method includes designing the foldable aerodynamic structure by determining the location and orientation of an Euler axis of rotation (11) about which the outer region rotates to achieve the ground configuration and determining a cut plane (13), perpendicular to that Euler axis, separating the inner and outer regions; and iteratively repeating this process until a preferred cut plane (13) is obtained that satisfies at least one design criteria.

2. 发明公开

EP3372490A1 FLEXIBLE CONTROL SURFACES AND RELATED METHODS 有权
公开(公告)号：EP3372490A1
公开(公告)日：2018-09-12
申请号：EP18160272.3
申请日：2018-03-06
申请人： The Boeing Company
发明人： ETLING, Keith Allan , GREEN, Jennifer R. , SPICKNALL, Stephen L.
IPC分类号： B64C3/52 , B64C9/12 , B64C9/08 , B64C3/26 , B64C3/44 , B64C3/48 , B64C9/18
CPC分类号： B64C3/26 , B64C3/48 , B64C3/52 , B64C9/08 , B64C9/12 , B64C9/14 , B64C9/18 , B64C2003/543 , Y02T50/14 , Y02T50/32
摘要： Flexible control surfaces and related methods are disclosed. Example apparatus disclosed herein include an airfoil (124) including a skin (712), the skin having perforations (142) filled with an elastomer to increase a flexibility of the skin (712); and a flexible core (714) adjacent the perforations (142) of the skin to support the skin.

3. 发明公开

EP3368410A1 AIR VEHICLE AND METHOD AND APPARATUS FOR CONTROL THEREOF 有权
公开(公告)号：EP3368410A1
公开(公告)日：2018-09-05
申请号：EP16788768.6
申请日：2016-10-28
申请人： BAE Systems PLC
发明人： WRIGHT, Julian, David , COLOSIMO, Nicholas, Giacomo, Robert , WARSOP, Clyde
IPC分类号： B64C3/46 , B64C3/48 , B64C3/44 , B64C29/02
CPC分类号： B64C3/46 , B64C3/14 , B64C3/44 , B64C3/48 , B64C39/024 , B64C2003/142 , B64C2201/021 , Y02T50/14
摘要： A wing member (14b) for an air vehicle (10), said wing member comprising a core section (20) defining its longitudinal axis and having upper and lower surfaces, at least one of said surfaces comprising apparatus (22) selectively configurable between at least two positions, wherein in a fully extended position, at least portions of said apparatus extend outwardly from said respective surface so as to increase the effective cross-sectional area of said wing member and define an effective aerofoil in respect thereof.

4. 发明授权

EP2727829B1 Wing fold controller 有权
公开(公告)号：EP2727829B1
公开(公告)日：2018-09-05
申请号：EP13190099.5
申请日：2013-10-24
申请人： The Boeing Company
发明人： Lassen, Matthew August , Douglas, Chad Richard , Jones, Kelly Thomas , Kenning, Terence Boyd
IPC分类号： B64C3/56 , B64C23/06
CPC分类号： B64C3/56 , B64C23/072 , Y02T50/14 , Y02T50/164 , Y02T50/54
摘要： Illustrative embodiments may provide for an apparatus and method of controlling the folding of a wing. The apparatus may include a sensor, an actuator, and a wing fold controller. The method may include receiving a status of at least one of an aircraft and a wing fold system of the aircraft by the wing fold controller of the wing fold system. The method may also include receiving an automated command by the wing fold controller in response to receiving the status. The method may also include operating the wing fold system by the wing fold controller based on the automated command and the status. The method may also include transitioning a wingtip of a wing of the aircraft to one of a flight position and a folded position by an actuator of the wing fold system in response to commands from the wing fold controller.

5. 发明授权

EP2952429B1 SLIDEABLE DIVERGENT TRAILING EDGE DEVICE 有权
公开(公告)号：EP2952429B1
公开(公告)日：2018-08-01
申请号：EP15165345.8
申请日：2015-04-28
申请人： The Boeing Company
发明人： Jamison, Flint M , Amorosi, Stephen R , Klein, Michael K
IPC分类号： B64C9/02 , B64C9/16
CPC分类号： B64C13/24 , B64C3/28 , B64C3/38 , B64C3/50 , B64C9/02 , B64C9/16 , B64C2003/147 , Y02T50/12 , Y02T50/14 , Y02T50/32 , Y02T50/44
摘要： A wing (130) includes a trailing edge, which may include a moveable flight control surface (230), and a divergent trailing edge device (240) slideable along an aft surface of the trailing edge or moveable flight control surface (230) between a stowed position and a fully deployed position. The divergent trailing edge device (240) is located entirely within the trailing edge or moveable flight control surface (230) when stowed, and it increases lift over drag of the wing (130) when deployed.

6. 发明公开

EP3335984A1 METHODS AND APPARATUS TO CONTROL AN AIRCRAFT FOLDING WINGTIP 有权转让
公开(公告)号：EP3335984A1
公开(公告)日：2018-06-20
申请号：EP17203486.0
申请日：2017-11-24
申请人： The Boeing Company
发明人： NIEMIEC, Aaron
IPC分类号： B64C3/56
CPC分类号： B64C3/56 , Y02T50/14
摘要： Methods and apparatus to control an aircraft folding wingtip assembly are disclosed. An example apparatus disclosed herein includes a detection module 210 to determine a status of a component of a folding wingtip assembly operatively coupled to a wing (102) of an aircraft and determine a flight stage of the aircraft. The example apparatus further includes a sequence and control module to generate a command to control a movement of the folding wingtip assembly, and a gatekeeper module to validate the command based on the status and the flight stage.

7. 发明公开

EP3326908A1 A ROTATIONAL JOINT FOR AN AIRCRAFT FOLDING WING 有权
公开(公告)号：EP3326908A1
公开(公告)日：2018-05-30
申请号：EP17175328.8
申请日：2017-06-09
申请人： Airbus Operations Limited , Airbus Operations GmbH
发明人： BISHOP, Benjamin , LORENZ, Christian
IPC分类号： B64C3/56
CPC分类号： B64C3/56 , Y02T50/14
摘要： An aircraft (2) comprising a wing (1), the wing (1) comprising a fixed wing (3) and a wing tip device (4) that is rotatable between a flight configuration and a ground configuration, the wing having a rotational joint (101) that rotatably couples the wing tip device (4) to the fixed wing (3), the rotational joint having an outer race (8) and an inner race (9), one of which is rotationally fixed relative to the wing tip device (4), to rotate about a rotational axis (B), and the other of which is rotationally fixed relative to the fixed wing (3), a rotational drive member (70) and the race that is rotationally fixed relative to the wing tip device (4) each being provided with a coupling section (110, 111, 114), the coupling sections being coupled to each other by a coupling member (119), that is received in a bore (112, 113) in one of the coupling sections, such that rotation of the drive member (70) rotates the race that is rotationally fixed relative to the wing tip device, to rotate the wing tip device (4) from one configuration to the other, wherein the coupling member (119) is mounted in the bore such that it is movable radially within the bore.

8. 发明授权

EP3022115B1 VERÄNDERBARES FLÜGELPROFIL 有权
标题翻译：改变翼型
公开(公告)号：EP3022115B1
公开(公告)日：2017-12-13
申请号：EP14744444.2
申请日：2014-07-10
申请人： Airbus Defence and Space GmbH
发明人： HASLACH, Horst
IPC分类号： B64C3/48
CPC分类号： B64C3/44 , B64C3/185 , B64C3/48 , B64C9/00 , B64C2003/445 , Y02T50/14

9. 发明公开

EP3230161A1 VEHICULE AERIEN LEGER SANS EQUIPAGE A DECOLLAGE VERTICAL 审中-公开
公开(公告)号：EP3230161A1
公开(公告)日：2017-10-18
申请号：EP15808600.9
申请日：2015-12-11
申请人： Université Pierre et Marie Curie - UPMC , Centre National de la Recherche Scientifique
发明人： MORIN, Pascal , GASTE, Olivier , PHUNG, Duc-Kien
IPC分类号： B64C3/38 , B64C27/22 , B64C29/00
CPC分类号： B64C29/0025 , B64C3/385 , B64C13/28 , B64C27/26 , B64C39/024 , B64C2201/027 , B64C2201/088 , B64C2201/104 , B64C2201/108 , B64C2201/165 , Y02T50/14
摘要： The disclosure thus relates to a light unmanned vertical takeoff aerial vehicle (1) which comprises at least two fixed coplanar propulsion devices (7) and at least one wing (3) providing the drone (1) with lift. The coplanar propulsion devices (7) and the wing (3) are each arranged on the framework (10) of the drone (1) such that the plane of the chord of the profile of the wing (3) is substantially parallel to the plane defined by the two coplanar propulsion devices (7). The wing (3) is capable of a pivoting movement with respect to the framework (10) about an axis parallel to the pitch axis of the drone (1). The disclosure also relates to a method for controlling a light unmanned aerial vehicle (1) like the one described hereinabove, which involves a step of controlling the orientation of the wing (3), which uses at least one parameter pertaining to the flight of the drone (1).
摘要翻译：因此，本公开涉及一种轻型无人垂直起飞架空飞行器（1），其包括至少两个固定共面推进装置（7）和至少一个提供无人驾驶飞机（1）的升降机翼（3）。共面推进装置（7）和机翼（3）分别布置在无人驾驶飞机（1）的框架（10）上，使得机翼（3）的轮廓翼弦的平面基本平行于平面由两个共面推进装置（7）限定。机翼（3）能够围绕平行于无人机（1）的俯仰轴线的轴线相对于框架（10）枢转运动。本公开还涉及一种用于控制如上文所述的轻型无人驾驶飞行器（1）的方法，其包括控制机翼（3）的方位的步骤，该方法使用至少一个与飞行器无人机（1）。

10. 发明公开

EP3204246A1 CENTRAL WING PANEL FOR A FLYING VEHICLE AND METHOD OF ITS CONTROL 失效
标题翻译：一种飞行器的中央翼面板及其控制方法
公开(公告)号：EP3204246A1
公开(公告)日：2017-08-16
申请号：EP15801514.9
申请日：2015-10-08
申请人： AeroMobil, s.r.o.
发明人： KLEIN, Stefan
IPC分类号： B60F5/02 , B64C3/56 , B64C37/00
CPC分类号： B64C3/56 , B60F5/02 , B64C37/00 , Y02T50/14
摘要： A central wing panel for a hybrid transportation vehicle for ground and air transportation configured to enable transitioning between an air mode and a ground mode. The central wing panel has a front frame section and a rear frame section connected by one or more cross members. The central wing panel is configured to rotate enabling adjustment of an angle of attack of the vehicle. The rear frame section is configured to rotate enabling coupling and uncoupling of the rear frame section from a first wing and a second wing for transitioning between the air mode and the ground mode. The central wing panel is also configured to allow rotation of ailerons and flaps so that they fold over onto the top front portion of the wings.
摘要翻译：用于地面和空中运输的混合运输车辆的中央翼板。中央翼片具有由一个或多个横向构件连接的前框架部分和后框架部分。中央翼片还可以具有第一竖直轴线和第二竖直轴线，第一竖直轴线和第二竖直轴线定位在前部框架区段的相对端部附近，其中第一翼部构造成围绕第一竖直轴线旋转并且第二翼部构造成围绕第一竖直轴线旋转第二垂直轴，用于在空气模式和地面模式之间转换。中央翼片还可以具有第一水平轴线，该第一水平轴线沿着前框架部分的下部基本平行地延伸，其中中央翼片构造成围绕第一水平轴线旋转，从而能够调节车辆的迎角。中央翼片还可具有沿后部框架部分的下部延伸的第二水平轴线，其中后部框架部分构造成绕第二水平轴线旋转以使后部框架部分能够与第一机翼以及用于在空气模式和地面模式之间转换的第二机翼。中央翼片还可以具有沿着翼的后缘延伸的第三水平轴线，从而允许副翼和翼片旋转，使得它们折叠到翼的顶部前部上，从而减小翼的深度。

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