公开(公告)号：EP4402423A1

公开(公告)日：2024-07-24

申请号：EP22777287.8

申请日：2022-09-09

申请人： MBDA UK Limited

发明人： THORNTON, Jeffrey

IPC分类号： F42B10/14 ,  B64C9/02

CPC分类号： F42B10/14 ,  B64C5/10 ,  B64C9/00 ,  B64C3/56

公开(公告)号：EP3392135A1

公开(公告)日：2018-10-24

申请号：EP18168450.7

申请日：2018-04-20

申请人： Hamilton Sundstrand Corporation

发明人： HARRINGTON, Erik ,  BISHOP, Yuniya S. ,  MILLER, Christian

IPC分类号： B64C13/28 ,  F16D3/74

CPC分类号： B64C13/28 ,  B64C9/00 ,  F16D3/74

摘要： An aircraft is provided. The aircraft includes fuselage (11), an aerodynamic element (12) extending from the fuselage and including a main section (15) and an adjustable section (16) which is adjustable relative to the main section, a power distribution unit (PDU) (25) configured to generate torque to drive an adjustment of the adjustable section, an actuator (30), torque tubes (40) and elastomeric couplings (50). The PDU is disposed proximate to a fuselage-aerodynamic interface. The actuator is disposed along the aerodynamic element and is receptive of the torque for driving the adjustment of the adjustable section. The torque tubes transmit the torque from the PDU to the actuator and are arranged between the PDU and the actuator such that adjacent torque tubes define an obtuse angle. The elastomeric couplings are disposed at respective ends of each of the torque tubes to enable torque transmission between at least the adjacent torque tubes defining the obtuse angle.

公开(公告)号：EP3241742A1

公开(公告)日：2017-11-08

申请号：EP16382198.6

申请日：2016-05-06

申请人： Airbus Operations S.L.

发明人： GARCIA NIETO, Carlos ,  PEREIRA MOSQUEIRA, Fernando ,  VELEZ DE MENDIZABAL ALONSO, Iker ,  GUINALDO FERNANDEZ, Enrique ,  HONORATO RUIZ, Francisco Javier

IPC分类号： B64C5/02 ,  B64C9/00

CPC分类号： B64C9/00 ,  B64C5/02 ,  B64C9/02 ,  Y02T50/44

摘要： An aircraft aerodynamic surface (1) comprising a torsion box (2) having a front spar (21) and rear spar (22), a first control surface (3) comprising a front spar (31) and a trailing edge (32) and a second control surface (4) comprising a front spar (41), a trailing edge (42), and means (5, 6, 7, 8) for pivotally attaching the first control surface (3) and the second control surface (4) to the rear spar (22) of the torsion box (2), the first control surface is an inboard control surface (4) comprising two lateral ribs (9, 9'), six inner ribs (11, 12, 13, 14, 15, 10) and an inner spar (16), and the second control surface (3) is an outboard control surface which comprising two lateral ribs (20, 20'), three internal ribs (17, 18, 19), two internal spars (24, 24') and one internal spar (23).

摘要翻译： 一种包括具有前翼梁（21）和后翼梁（22）的扭力箱（2）的飞机空气动力学表面（1），包括前翼梁（31）和后缘（32）的第一控制表面（3）以及 （3）和第二控制表面（4）的装置（5,6,7,8）的第二控制表面（4），所述第二控制表面包括前翼梁（41），后缘（42） ）连接到扭力箱（2）的后翼梁（22），第一控制表面是内侧控制表面（4），该内侧控制表面包括两个侧肋（9,9'），六个内肋（11,12,13,14 ，所述第二控制表面（3）是外侧控制表面，所述外侧控制表面包括两个侧肋（20,20'），三个内肋（17,18,19），两个内肋 内部翼梁（24,24'）和一个内部翼梁（23）。

公开(公告)号：EP3222515A1

公开(公告)日：2017-09-27

申请号：EP17162428.1

申请日：2017-03-22

申请人： Airbus (S.A.S.)

发明人： ZHANG, Feng ,  GUO, Li

IPC分类号： B64C7/00 ,  B64C9/02 ,  B64C5/02 ,  B64C9/08

CPC分类号： B64C9/00 ,  B64C5/02 ,  B64C7/00 ,  B64C9/02 ,  B64C9/08 ,  Y02T50/32

摘要： The present invention relates to a sealing device and an associated flight control surface mechanism and an associated aircraft. According to an aspect of the present invention, a sealing device (100, 100') for a flight control surface mechanism (10) of an aircraft (1) is provided, the flight control surface mechanism includes a fixed part (20) and a movable wing surface (40), the movable wing surface is attached to the fixed part in a manner of being movable relative to the fixed part. The sealing device includes a fixed seal (120) attached to the fixed part and a movable seal (140, 140') attached to the movable wing surface so as to move with the movement of the movable wing surface, the movable seal and the fixed seal cooperate with each other in order to provide an aerodynamic sealing for the flight control surface mechanism. According to the present invention, a good aerodynamic sealing of the flight control surface mechanism can be effectively maintained, and the efficiency of the movable wing surface and thus the aerodynamic performance of the flight control surface mechanism can be effectively ensured.

摘要翻译： 本发明涉及密封装置和相关的飞行控制表面机构以及相关的飞行器。 根据本发明的一个方面，提供了一种用于飞机（1）的飞行控制表面机构（10）的密封装置（100,100'），所述飞行控制表面机构包括固定部分（20）和 可动翼表面（40），所述可动翼表面以​​能够相对于所述固定部分运动的方式附接到所述固定部分。 密封装置包括固定到固定部分的固定密封件（120）和附接到可动翼面的可动密封件（140,140'），以随着可动翼面，可动密封件和固定部件 密封件彼此协作以便为飞行控制表面机构提供空气动力学密封。 根据本发明，能够有效地保持飞行控制表面机构的良好的空气动力学密封，并且可以有效地确保飞行控制表面机构的可动机翼表面的效率以及因此的空气动力学性能。

公开(公告)号：EP3210883A1

公开(公告)日：2017-08-30

申请号：EP16382084.8

申请日：2016-02-29

申请人： Airbus Operations, S.L.

发明人： CRESPO PEÑA, Soledad ,  GARCÍA NIETO, Carlos ,  VELEZ DE MENDIZABAL ALONSO, Iker ,  GUINALDO FERNANDEZ, Enrique

IPC分类号： B64C3/20 ,  B32B5/02 ,  B64D45/02

CPC分类号： B32B5/028 ,  B29C70/24 ,  B29L2031/3085 ,  B32B5/02 ,  B32B5/06 ,  B32B15/02 ,  B32B37/14 ,  B32B2038/008 ,  B32B2260/021 ,  B32B2260/046 ,  B32B2262/106 ,  B32B2305/076 ,  B32B2305/72 ,  B32B2605/18 ,  B64C1/00 ,  B64C3/20 ,  B64C9/00 ,  B64C2001/0072 ,  B64D45/02 ,  D05D2209/12 ,  Y02T50/43

摘要： The present invention refers in general to the configuration and manufacturing method for a trailing edge (3) of an aircraft airfoil (2), such as a control surface or a lifting surface. The trailing edge of the invention is formed and configured by upper and lower composite covers (4,5), which are stitched to each other with a metallic wire (9), such as the metallic wire (9) is electrically in contact with upper and lower metallic meshes (6,7) to provide electrical continuity between meshes. According to the method of the invention, upper and lower covers (4,5) configuring the trailing edge (3), are stitched with the metallic wire (9) before curing the covers, so that the metallic wire gets embedded within the composite material. The invention provides a trailing edge (3) for an aircraft airfoil (2), which is easy to manufacture and that at the same time fulfills aerodynamic, mechanical and electrical conductivity requirements.

摘要翻译： 本发明总体上涉及用于飞机机翼（2）的后缘（3）的构造和制造方法，例如控制表面或提升表面。 本发明的后缘由上部和下部复合盖（4,5）形成和构造，所述上部和下部复合盖（4,5）利用金属丝（9）彼此缝合，例如金属丝（9）与上部 和较低的金属网（6,7）以提供网眼之间的电连续性。 根据本发明的方法，在固化盖之前，将构成后缘（3）的上盖和下盖（4,5）与金属丝（9）缝合，使得金属丝嵌入复合材料 。 本发明提供了用于飞机机翼（2）的后缘（3），其容易制造并且同时满足空气动力学，机械和导电性要求。

公开(公告)号：EP2956358A1

公开(公告)日：2015-12-23

申请号：EP14751884.9

申请日：2014-02-10

申请人： Gulfstream Aerospace Corporation

发明人： FREUND, Donald

IPC分类号： B64C30/00

CPC分类号： B64C23/00 ,  B64C3/185 ,  B64C3/20 ,  B64C3/38 ,  B64C3/42 ,  B64C9/00 ,  B64C17/10 ,  B64C30/00 ,  B64D37/00 ,  Y02T50/14 ,  Y02T50/44

摘要： A system for controlling a magnitude of a sonic boom caused by off-design operation of a supersonic aircraft includes a sensor configured to detect a condition of the supersonic aircraft. The system further includes a control surface that is mounted to a wing of the supersonic aircraft. The system still further includes a processor communicatively coupled to the sensor and operatively coupled with the control surface. The processor is configured to (1) receive information from the sensor indicative of the condition of the supersonic aircraft, (2) determine that there is a deviation between a lift distribution and a design-condition lift distribution based on the information, and (3) control the control surface to move in a manner that reduces the deviation. The magnitude of the sonic boom is reduced when the deviation is reduced.

摘要翻译： 用于控制由超音速飞机的非设计操作引起的音爆大小的系统包括配置成检测超音速飞行器的状况的传感器。 该系统还包括安装到超音速飞行器的机翼上的控制表面。 该系统还包括通信地耦合到传感器并与控制表面可操作地耦合的处理器。 处理器被配置为（1）从传感器接收指示超音速飞行器的状况的信息，（2）基于该信息确定升力分布与设计条件升力分布之间存在偏差，以及（3） ）控制控制表面以减小偏差的方式移动。 当偏差减小时，音爆的幅度减小。

公开(公告)号：EP2944566A1

公开(公告)日：2015-11-18

申请号：EP15162586.0

申请日：2015-04-07

申请人： The Boeing Company

发明人： Mahmulyin, Vedad

IPC分类号： B64C13/16 ,  B64C13/50 ,  G05D1/00 ,  G05D1/08

CPC分类号： B64C13/00 ,  B64C5/02 ,  B64C9/00 ,  B64C13/04 ,  B64C13/16 ,  B64C13/503 ,  B64D43/02 ,  G05D1/0066

摘要： A method of controlling an elevator of an aircraft may include identifying a current stabilizer angle of incidence of a stabilizer of the aircraft. The stabilizer may include an elevator pivotably coupled to the stabilizer. The method may further include comparing the current stabilizer angle of incidence with a threshold stabilizer angle of incidence, and selecting an elevator position limit that is more restrictive if the current stabilizer angle of incidence is greater than or equal to the threshold stabilizer angle of incidence. The method may additionally include moving the elevator to a commanded elevator position that is no greater than the elevator position limit.

摘要翻译： 控制飞行器的电梯的方法可以包括识别飞行器的稳定器的当前稳定器入射角。 稳定器可以包括可枢转地联接到稳定器的升降机。 该方法还可以包括将当前稳定器入射角与阈值稳定角入射进行比较，并且如果当前稳定入射角大于或等于阈值稳定器入射角，则选择更严格的电梯位置极限。 该方法可以另外包括将电梯移动到不大于电梯位置限制的指令电梯位置。

公开(公告)号：EP2927113A1

公开(公告)日：2015-10-07

申请号：EP15150881.9

申请日：2015-01-13

申请人： The Boeing Company

发明人： Sheahan, James Joseph ,  Drouin, Donald V

IPC分类号： B64C3/56 ,  B64C9/02 ,  B64C13/38 ,  B64C13/40 ,  B64C13/50

CPC分类号： B64C13/34 ,  B64C9/00 ,  B64C9/02 ,  B64C13/26 ,  B64C13/38 ,  B64C13/40 ,  B64C13/50 ,  Y02T50/32 ,  Y02T50/44 ,  Y10T29/49826

摘要： An air vehicle, an actuator assembly and a method of manufacture are provided in order to incorporate the actuator assembly within the outer mold line of the air vehicle. In regards to an air vehicle, the air vehicle includes a primary structure and a movable structure configured to be controllably moved relative to the primary structure. The air vehicle also includes an actuator assembly configured to cause the movable structure to be positioned relative to the primary structure. The actuator assembly includes an actuator housing and an actuation mechanism. The actuation mechanism is at least partially disposed within the actuator housing and is configured to provide for relative movement between the primary structure and the movable structure. At least a portion of the actuator assembly is built into at least one of the primary structure and the movable structure so as to be within an outer mold line of the air vehicle.

摘要翻译： 提供了一种机动车辆，致动器组件和制造方法，以将致动器组件并入到空中交通工具的外部模具线内。 关于空中飞行器，该空中飞行器包括一个主结构和一个构造成可相对于主结构可控地移动的可移动结构。 空中车辆还包括构造成使可移动结构相对于主结构定位的致动器组件。 致动器组件包括致动器壳体和致动机构。 所述致动机构至少部分地设置在所述致动器壳体内并且构造成提供所述主结构和所述可移动结构之间的相对运动。 致动器组件的至少一部分内置在主结构和可移动结构中的至少一个中，以便在空中车辆的外部模具线内。

公开(公告)号：EP2862798A2

公开(公告)日：2015-04-22

申请号：EP14181531.6

申请日：2014-08-20

申请人： Airbus Operations Limited

发明人： Axford, Timothy

IPC分类号： B64C9/00

CPC分类号： B64C3/58 ,  B64C9/00 ,  B64C9/323 ,  B64C9/34 ,  B64F5/10

摘要： The present invention concerns an aircraft structure (401, 402) for being moveably mounted externally on an aircraft (400), the aircraft structure being an aerodynamic structure comprising a structural component 100 providing structural strength and stiffness to the aircraft structure, the structural component comprising an integral fixing (116, 117) for moveably mounting the aerodynamic structure externally to the aircraft, and an integral fixing (115) for attachment to an actuator for actuating movement of the aircraft structure with respect to the aircraft, and an aerodynamic surface component (200, 300) attached to one side of the structural component, the aerodynamic surface component providing an aerodynamic external surface of the aircraft structure. The invention also concerns a method of manufacture.

摘要翻译： 本发明涉及一种用于可移动地外部地安装在飞行器（400）上的飞行器结构（401,402），飞行器结构是包括提供飞行器结构的结构强度和刚度的结构部件100的空气动力结构，该结构部件包括 用于将空气动力学结构可移动地安装到飞行器外部的整体固定件（116,117）以及用于附接到用于致动飞行器结构相对于飞机的运动的致动器的整体式固定件（115）和空气动力学表面部件 200,300），所述空气动力学表面部件提供所述飞行器结构的空气动力学外表面。 本发明还涉及一种制造方法。

公开(公告)号：EP2773556A1

公开(公告)日：2014-09-10

申请号：EP12805568.8

申请日：2012-10-20

申请人： EADS Deutschland GmbH

发明人： HIEBL, Manfred ,  PONGRATZ, Hans Wolfgang

IPC分类号： B64C3/30 ,  B64C39/02

CPC分类号： B64C39/02 ,  B64C3/30 ,  B64C9/00 ,  B64C27/41 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/105 ,  B64C2201/122 ,  B64C2201/165 ,  B64D39/00 ,  B64D2041/005 ,  B64D2211/00 ,  Y02T90/36

摘要： An unmanned high altitude aircraft, in particular a stratosphere aircraft, comprising at least one fuselage (10), wings (13, 14), control surfaces (13", 14", 20', 20", 21', 21") and at least one drive device (15, 16, 17) that has at least one drive machine and at least one propeller (15', 16' 17'), is characterised in that each wing (13, 14) has a plurality of tubes (40, 41, 42, 43, 44) and wing spars (46' 46") that extend in one direction transversally, preferably perpendicularly, to the longitudinal axis of the fuselage (Z) and are surrounded by a skin that forms a wing covering (45) and defines the cross-sectional contour of the wing, the cross-sectional contour forming a laminar profile that generates high lift when there is low flow resistance. Each wing (13, 14) is provided with a winglet (13', 14') that extends transversally to the longitudinal axis of the wing on its free end which faces away from the fuselage (10), and the winglet (13' 14') is provided with a movable control surface (13", 14") that enables an aerodynamic side force to be generated in order to bring the aircraft into an oblique bank position.

摘要翻译： 高空无人空中平流层飞行器包括机身，机翼，控制面和包括发动机和螺旋桨的推进系统。 每个翼具有沿垂直于纵向机身轴线的方向延伸的多个软管和翼梁，并且被形成机翼覆盖物的皮肤包围，所述机翼覆盖物确定机翼的横截面轮廓，横截面轮廓形成层流 当流动阻力低时产生高升力的翼型。 在远离机身的自由端处，每个机翼具有横向于纵向翼轴线延伸的小翼。 小翼具有可移动的控制表面，其允许产生空气动力学侧力，以使空中飞行器处于堆积位置。