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1. 发明申请

US20170291688A1 HIGH-LIFT DEVICE OF AIR VEHICLE 审中-公开
公开(公告)号：US20170291688A1
公开(公告)日：2017-10-12
申请号：US15629407
申请日：2017-06-21
申请人： THE SOCIETY OF JAPANESE AEROSPACE COMPANIES , KAWASAKI JUKOGYO KABUSHIKI KAISHA
发明人： Kazuhide ISOTANI , Kenji HAYAMA
IPC分类号： B64C9/18 , B64C21/08 , B64C9/02 , B64C3/50
CPC分类号： B64C21/08 , B64C3/50 , B64C9/02 , B64C9/18 , B64C2009/143 , B64C2230/14 , Y02T50/166
摘要： A high-lift device includes a flap body which is provided at a rear portion of a main wing which generates a lift for the air vehicle such that the flap body is deployed with respect to the main wing and stowed in the main wing and extends along a wingspan direction of the main wing; and a gap increasing section provided at an end portion of the flap body in an extending direction of the flap body, to increase a gap between the rear portion of the main wing and a front portion of the flap body in a state in which the flap body is deployed.

2. 发明申请

US20170175895A1 SEAL ASSEMBLY 审中-公开
公开(公告)号：US20170175895A1
公开(公告)日：2017-06-22
申请号：US15384949
申请日：2016-12-20
申请人： AIRBUS OPERATIONS LIMITED
发明人： Tristan VINCENT , Kim SHARP , David HOPTROFF
IPC分类号： F16J15/02 , B64C9/20
CPC分类号： F16J15/02 , B64C3/50 , B64C9/02 , B64C9/16 , B64C9/20 , B64C2009/143 , F02C7/28 , F02K1/805 , F16J15/00
摘要： An aircraft wing has a fixed wing portion and a trailing edge flap movable with respect to the fixed wing portion to define a gap between the fixed wing and the flap. A seal assembly has a first rigid seal member fixed to the fixed wing portion and a second resilient seal member fixed to an upper surface leading edge portion of the flap. The trailing edge flap is deployable between a first flap position in which the trailing edge flap conforms to a profile of the fixed wing portion, a second flap position in which the trailing edge flap is deflected upwardly from the first flap position, and a third flap position in which the trailing edge flap is deflected downwardly from the first flap position. In the first flap position the first seal member contacts the second seal member to at least partially seal the gap, and in the second flap position the first seal member presses against the second seal member and deflects the second seal member to at least partially seal the gap.

3. 发明授权

US09550559B1 Aircraft wing assemblies 有权
标题翻译：飞机机翼组件
公开(公告)号：US09550559B1
公开(公告)日：2017-01-24
申请号：US13936790
申请日：2013-07-08
申请人： The Boeing Company
发明人： Christopher K. Droney , Blaine K. Rawdon
IPC分类号： B64C9/00 , B64C9/18
CPC分类号： B64C9/18 , B64C3/185 , B64C3/187 , B64C3/26 , B64C2009/143
摘要： Aircraft wing assemblies are disclosed herein. An example apparatus disclosed herein includes a trailing edge of a wing of an aircraft. The trailing edge has a flexible skin defining a first surface. The example apparatus also includes a flap movably coupled to the trailing edge. The flap defines a second surface. The first surface and the second surface form a substantially continuous surface when the flap is in a stowed position and when the flap is in a deployed position.
摘要翻译：本文公开了飞机机翼组件。本文公开的示例性装置包括飞行器的翼的后缘。后缘具有限定第一表面的柔性皮肤。示例性装置还包括可移动地联接到后缘的折翼。挡板限定第二表面。当襟翼处于收起位置时，当襟翼处于展开位置时，第一表面和第二表面形成基本连续的表面。

4. 发明申请

US20150210379A1 HIGH LIFT SYSTEM FOR AN AIRCRAFT AND AIRCRAFT HAVING SUCH A HIGH LIFT SYSTEM 有权
标题翻译：用于具有这种高升程系统的飞机和飞机的高升程系统
公开(公告)号：US20150210379A1
公开(公告)日：2015-07-30
申请号：US14608271
申请日：2015-01-29
申请人： Airbus Operations GmbH
发明人： Frieder HENNING , Tanno Zantz , Michael Brady
IPC分类号： B64C9/22 , B64C13/50
CPC分类号： B64C9/22 , B64C9/24 , B64C13/50 , B64C2009/143 , F03D1/0641 , Y02E10/721
摘要： A high lift system for an aircraft comprises a wing structure and a leading edge slat movably supported relative to a leading edge of the wing structure, the leading edge slat comprises a leading edge and a trailing edge, wherein the trailing edge is configured to take different positions to form a gap between the leading edge slat and the wing structure, a skin and enclosing an interior space of the leading edge slat, the skin having a flexible leading skin section facing away from the wing structure, a flexible trailing skin section facing towards the wing structure, at least one actuation arrangement arranged inside the interior space for selectively introducing a normal force onto at least one of the leading skin section and the trailing skin section.
摘要翻译：用于飞行器的高升力系统包括机翼结构和相对于机翼结构的前缘可移动地支撑的前缘板条，所述前缘板条包括前缘和后缘，其中所述后缘被配置为采取不同的位置以形成前缘板条和机翼结构之间的间隙，皮肤并且包围前缘板条的内部空间，所述皮肤具有面向远离机翼结构的柔性导向皮肤部分，柔性后缘皮肤部分朝向机翼结构，布置在内部空间内的至少一个致动装置，用于将法向力选择性地引导到至少一个前皮肤部分和后皮肤部分上。

5. 发明授权

US08967549B2 Actuation system for leading edge high-lift device 有权
标题翻译：前缘高升力装置执行系统
公开(公告)号：US08967549B2
公开(公告)日：2015-03-03
申请号：US12733465
申请日：2008-10-27
申请人： Francois Cathelain , Edmund Kay
发明人： Francois Cathelain , Edmund Kay
IPC分类号： B64C3/50 , B64C9/24 , B64C9/14
CPC分类号： B64C9/24 , B64C2009/143 , Y02T50/32
摘要： An actuation system configured to deploy a high-lift device on a leading edge of an aircraft wing. The system comprises: a link pivotally connected to the wing at a first pivot point and to the high-lift device at a second pivot point; a first actuation mechanism configured to rotate the high-lift device about the first pivot point; and a second actuation mechanism configured to rotate the high-lift device about the second pivot point. The second actuation mechanism is operable independently of the first actuation mechanism, and can be operated in order to generate a sealing force between the high-lift device and the leading edge of the aircraft wing.
摘要翻译：一种致动系统，其构造成在飞机机翼的前缘部署高升力装置。该系统包括：在第一枢转点处枢转地连接到机翼的连杆和在第二枢转点处的高升力装置; 第一致动机构，其构造成围绕第一枢转点旋转高升降机构; 以及第二致动机构，其构造成围绕第二枢转点旋转高升降机构。第二致动机构可独立于第一致动机构操作，并且可以操作以便在高升力装置和飞机机翼的前缘之间产生密封力。

6. 发明申请

US20150053825A1 HIGH-LIFT DEVICE OF AIR VEHICLE 有权
标题翻译：高空作业装置
公开(公告)号：US20150053825A1
公开(公告)日：2015-02-26
申请号：US14389257
申请日：2013-03-29
申请人： THE SOCIETY OF JAPANESE AEROSPACE COMPANIES , KAWASAKI JUKOGYO KABUSHIKI KAISHA
发明人： Kazuhide Isotani , Kenji Hayama
IPC分类号： B64C3/50
CPC分类号： B64C21/08 , B64C3/50 , B64C9/02 , B64C9/18 , B64C2009/143 , B64C2230/14 , Y02T50/166
摘要： A high-lift device includes a flap body which is provided at a rear portion of a main wing which generates a lift for the air vehicle such that the flap body is deployed with respect to the main wing and stowed in the main wing and extends along a wingspan direction of the main wing; and a gap increasing section provided at an end portion of the flap body in an extending direction of the flap body, to increase a gap between the rear portion of the main wing and a front portion of the flap body in a state in which the flap body is deployed.
摘要翻译：一种高升力装置包括一个翼片主体，其设置在主翼的后部，其产生用于空中飞行器的升降机，使得翼片主体相对于主翼部署并且被收纳在主翼中并沿着主翼的翼展方向; 以及在翼片主体的延伸方向上设置在翼片主体的端部处的间隙增大部分，以在主翼的后部与翼片主体的前部之间增加间隙，身体被部署。

7. 发明申请

US20140048655A1 HIGH LIFT SYSTEM FOR AN AIRCRAFT AND METHOD FOR INFLUENCING THE HIGH LIFT CHARACTERISTICS OF AN AIRCRAFT 有权
标题翻译：用于航空器的高升力系统和影响飞机高飞行特性的方法
公开(公告)号：US20140048655A1
公开(公告)日：2014-02-20
申请号：US14063536
申请日：2013-10-25
申请人： Airbus Operations GmbH
发明人： Xavier Hue , Bernhard Schlipf
IPC分类号： B64C9/22 , B64C9/14
CPC分类号： B64C9/22 , B64C9/02 , B64C2009/143
摘要： A high lift system for an aircraft includes a basic body, a flap which is movably mounted on the basic body and has a flap edge, and a retaining element. The high lift system is set up to form a gap between the flap edge and the basic body. The retaining element is mounted on a region of the flap close to the flap edge and extends towards the basic body to restrict the distance between the flap edge and the basic body. The retaining element is preferably configured as a linear attachment means. Consequently, a gap dimension between a flap and a basic body can be influenced to restrict flexing effects during loading of the flap and of the basic body.
摘要翻译：用于飞行器的高升力系统包括基体，可移动地安装在基体上并具有翼片边缘的挡板和保持元件。高升力系统设置成在翼片边缘和基体之间形成间隙。保持元件安装在翼片的靠近翼片边缘的区域上，并朝向基体延伸以限制翼片边缘和基体之间的距离。保持元件优选地构造为线性附接装置。因此，可以影响翼片和基体之间的间隙尺寸，以限制翼片和基体的装载期间的弯曲效果。

8. 发明授权

US08651428B2 Aircraft wing assembly 有权
标题翻译：飞机机翼总成
公开(公告)号：US08651428B2
公开(公告)日：2014-02-18
申请号：US13476312
申请日：2012-05-21
申请人： Simon John Parker
发明人： Simon John Parker
IPC分类号： B64C13/16
CPC分类号： B64C9/20 , B64C9/16 , B64C2009/143
摘要： An aircraft wing assembly, comprising: a fixed wing portion; a first and second flight control surfaces; a first and second actuators operatively coupled to the first and second flight control surfaces for moving respective first and second flight control surfaces with respect to the fixed wing portion; a control system operatively coupled to the first and second actuators for controlling movement of the first and second flight control surfaces; and a third actuator selectively engaged with the second flight control surface for engaging and moving the second flight control surface out of a path of movement of the first flight control surface only in the event of a failure in the second actuator or its control, so as to avoid direct contact between the first and second flight control surfaces.
摘要翻译：一种飞机机翼组件，包括：固定翼部分; 第一和第二飞行控制面; 第一和第二致动器，其可操作地联接到第一和第二飞行控制表面，用于相对于固定翼部分移动相应的第一和第二飞行控制表面; 控制系统，可操作地联接到第一和第二致动器，用于控制第一和第二飞行控制表面的运动; 以及第三致动器，其选择性地与第二飞行控制表面接合，用于仅在第二致动器或其控制中的故障的情况下使第二飞行控制表面从第一飞行控制表面的移动路径接合和移动，从而以避免第一和第二飞行控制表面之间的直接接触。

9. 发明申请

US20130320151A1 ROTARY ACTUATED HIGH LIFT GAPPED AILERON 有权
标题翻译：旋转启动高升降飞机
公开(公告)号：US20130320151A1
公开(公告)日：2013-12-05
申请号：US13482537
申请日：2012-05-29
申请人： Jan A. Kordel , Seiya Sakurai
发明人： Jan A. Kordel , Seiya Sakurai
IPC分类号： B64C3/50 , B64C13/26 , B64C9/00
CPC分类号： B64C1/10 , B64C9/16 , B64C9/18 , B64C2009/143
摘要： A rotary actuated high lift gapped aileron system and method are presented. A high lift gapped aileron couples to an airfoil at a hinge line and changes a camber of the airfoil. A rotary actuator coupled to the high lift gapped aileron produces a rotary motion of the high lift gapped aileron in response to an actuation command. A droop panel positioned over the hinge line enhances lift of the high lift gapped aileron. A cove lip door positioned under the hinge line provides an airflow over the high lift gapped aileron. A deployment linkage mechanism coupled to the high lift gapped aileron positions the droop panel and the cove lip door in response to the rotary motion.
摘要翻译：提出了一种旋转驱动的高电梯间隙副翼系统和方法。一个高升降机的副翼在铰链上与翼型相连，并改变翼型的弯度。耦合到高电梯间隙副翼的旋转致动器响应于致动指令产生高升力带隙副翼的旋转运动。定位在铰链线上方的垂直面板增强了升降机间隙副翼的升力。位于铰链线下方的海湾唇门在高升高间隙副翼上提供气流。联接到高提升间隙副翼的展开联动机构响应于旋转运动而定位下垂面板和小湾唇门。

10. 发明授权

US08511619B2 Slat deployment mechanism 有权
标题翻译：板条部署机制
公开(公告)号：US08511619B2
公开(公告)日：2013-08-20
申请号：US12921582
申请日：2009-03-12
申请人： Alan Mann
发明人： Alan Mann
IPC分类号： B64C9/22 , B64C3/50 , B64C13/34
CPC分类号： B64C9/22 , B64C2009/143
摘要： An aircraft slat deployment mechanism including a first drive member coupled to a slat at a first pivot point and a second drive member coupled to the slat at a second pivot point offset from the first pivot point. A first rack is provided on the first drive member, and a first pinion is carried by the drive shaft. The first pinion is arranged to transmit mechanical power from the drive shaft to the first drive member via the first rack. A second rack is provided on the second drive member, and a second pinion is carried by the drive shaft. The second pinion has a different radius to the first pinion. The second pinion is arranged to transmit mechanical power from the drive shaft to the second drive member via the second rack, such that the first and second drive members move at a different speed.
摘要翻译：一种飞机板条展开机构，包括在第一枢转点处联接到板条的第一驱动构件和在离开第一枢转点的第二枢转点处联接到板条的第二驱动构件。第一齿条设置在第一驱动构件上，第一小齿轮由驱动轴承载。第一小齿轮布置成经由第一齿条将机械动力从驱动轴传递到第一驱动构件。第二齿条设置在第二驱动构件上，第二小齿轮由驱动轴承载。第二小齿轮具有与第一小齿轮不同的半径。第二小齿轮被布置成经由第二齿条将驱动轴的机械动力传递到第二驱动构件，使得第一和第二驱动构件以不同的速度移动。

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