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1. 发明授权

US12097959B2 Underwing-mounted trailing edge flaps for wings of aircraft 有权
公开(公告)号：US12097959B2
公开(公告)日：2024-09-24
申请号：US18152687
申请日：2023-01-10
申请人： The Boeing Company
发明人： Kevin Raylin Tsai , Ryan Joseph Cazin
IPC分类号： B64C9/02 , B64C9/18 , B64C9/34
CPC分类号： B64C9/02 , B64C9/18 , B64C9/34
摘要： Underwing-mounted trailing edge flaps for wings of aircraft are disclosed. A flap pivotally coupled to the wing is movable between a stowed position located along a lower surface of the wing and a deployed position located rearward of a trailing edge of the wing. The flap includes a first edge, a second edge located opposite the first edge, a first surface extending between the first edge and the second edge, and a second surface located opposite the first surface and extending between the first edge and the second edge. The first edge is located rearward of the second edge when the flap is in the stowed position, and forward of the second edge when the flap is in the deployed position. A bullnose pivotally coupled to the flap at a location along the first edge pivots relative to the flap as the flap moves between the stowed and deployed positions.

2. 发明授权

US11970269B2 Assemblies for air vehicle control surfaces including a bullnose 有权
公开(公告)号：US11970269B2
公开(公告)日：2024-04-30
申请号：US17744272
申请日：2022-05-13
申请人： The Boeing Company
发明人： Mark S. Good , Kevin Tsai
IPC分类号： B64C9/34 , B64C9/16
CPC分类号： B64C9/34 , B64C9/16
摘要： Assemblies for air vehicle control surfaces and related methods are disclosed. An example apparatus includes a control surface; a bullnose carried by the control surface, the bullnose moveable relative to the control surface; a first actuator operatively coupled to the control surface to cause the control surface to rotate; and a second actuator operatively coupled to the control surface, the second actuator to cause the bullnose to move from a first position to a second position to cause an opening to be formed relative to the control surface, the movement of the bullnose independent of rotation of the control surface.

3. 发明授权

US11685512B2 Lift-changing mechanism 有权
公开(公告)号：US11685512B2
公开(公告)日：2023-06-27
申请号：US17307421
申请日：2021-05-04
申请人： SUBARU CORPORATION
发明人： Wataru Kobayashi , Hirotaka Hayashi , Mizuki Nakamura , Masafumi Sasaki
IPC分类号： B64C9/18 , B64C3/50 , B64C9/34
CPC分类号： B64C9/18 , B64C3/50 , B64C9/34
摘要： A lift-changing mechanism is configured to change generated by a wing of an aircraft and includes a slit and an opening and closing member. The slit extends in a wingspan direction inside the wing and forms openings on the lower surface of the wing and on the upper surface of the wing respectively. A part of airflow below the lower surface is allowed to flow toward the upper surface through the slit. The opening and closing member is configured to open and close the slit. When the opening and closing member opens the slit, lift generated on the wing is decreased compared with when the slit is closed.

4. 发明授权

US10618625B2 Integrated slat chine apparatus and methods 有权
公开(公告)号：US10618625B2
公开(公告)日：2020-04-14
申请号：US15648103
申请日：2017-07-12
申请人： The Boeing Company
发明人： David Daniel Leopold
IPC分类号： B64C3/50 , B64C9/22 , B64C23/06 , B64C3/58 , B64C9/26 , B64C9/34 , B64C21/00
CPC分类号： B64C3/50 , B64C3/58 , B64C9/22 , B64C9/26 , B64C9/34 , B64C21/00 , B64C23/06
摘要： Integrated slat chine apparatus and methods are described. An example apparatus includes a chine and a slat. The chine is coupled to an airfoil. The chine includes a lateral surface. The slat is located adjacent the lateral surface of the chine and coupled to the airfoil. The slat is movable relative to the airfoil between a stowed position and a deployed position. The slat is to expose the lateral surface of the chine when the slat is in the deployed position and to cover the lateral surface of the chine when the slat is in the stowed position.

5. 发明申请

US20170341731A1 YAW CONTROL IN AN AIRCRAFT 审中-公开
公开(公告)号：US20170341731A1
公开(公告)日：2017-11-30
申请号：US15166369
申请日：2016-05-27
申请人： Lockheed Martin Corporation
发明人： Kenneth Merle Dorsett , Robert Carl Storrie
IPC分类号： B64C9/34 , B64C13/28 , B64C9/02
CPC分类号： B64C9/34 , B64C5/08 , B64C5/10 , B64C9/02 , B64C9/12 , B64C9/323 , B64C13/28 , B64C13/30 , Y02T50/44
摘要： In one embodiment, an apparatus includes a first deflector configured to couple to a shaft of a wing of an aircraft and form part of a top surface of the wing when in a first closed position, and a second deflector configured to couple to the shaft and form part of a bottom surface of the wing when in a second closed position. The first deflector and the second deflector may be configured to be positioned proximate to the tip of the wing. The first deflector and the second deflector may be configured to simultaneously pivot from the closed positions to respective first and second open positions upon actuation of the shaft.

6. 发明申请

US20150353187A1 LEADING EDGE ASSEMBLY FOR AN AIRCRAFT 审中-公开
标题翻译：飞机前沿组装
公开(公告)号：US20150353187A1
公开(公告)日：2015-12-10
申请号：US14266063
申请日：2014-04-30
申请人： The Boeing Company
发明人： Clayton A. Smith
IPC分类号： B64C9/34 , B64C13/36
CPC分类号： B64C9/34 , B64C9/22 , B64C13/36 , B64C2009/143 , Y02T50/32
摘要： A wing assembly includes a main wing and a slat movable between stowed and deployed positions. The main wing includes a panel movable to a retracted position when the slat is in the stowed position, such that the slat outer surface and a wing upper surface define a first continuous outer mold line shape. The panel may further be movable to an extended position when the slat is in the deployed position, such that an outer surface of the panel and the wing upper surface define a second continuous outer mold line shape.
摘要翻译：翼组件包括主翼和可在收起位置和展开位置之间移动的板条。主翼包括当板条处于收起位置时可移动到缩回位置的板，使得板条外表面和机翼上表面限定第一连续的外模线形状。当板条处于展开位置时，面板还可以移动到延伸位置，使得面板的外表面和机翼上表面限定第二连续的外模线形状。

7. 发明申请

US20110272532A1 AIRCRAFT WING LOAD ALLEVIATION SYSTEM 有权
标题翻译：飞机装载系统
公开(公告)号：US20110272532A1
公开(公告)日：2011-11-10
申请号：US13138162
申请日：2010-02-16
申请人： Yukitaka Matsuda
发明人： Yukitaka Matsuda
IPC分类号： B64C3/50 , B64C13/16 , B64C9/34
CPC分类号： B64C13/16 , B64C9/10 , B64C9/323 , B64C9/34 , Y02T50/32
摘要： An aircraft wing load alleviation system incorporating a wing, a spoiler panel (14), a device (16, 17) which restricts circulation of air around a trailing edge of the spoiler and a control system. The spoiler panel is pivotally attached to the wing so that the spoiler panel can be rotated up from a lowered position to a raised position, thereby opening a void between the spoiler panel and the wing. The retractable device can be deployed from a retracted position to an extended position in which it restricts circulation of air around the trailing edge of the spoiler panel and into the void, thus reducing induced drag. The control system is configured to detect or predict an increase in the lift of the wing and rotate the spoiler panel to its raised position in response to a detected or predicted increase in the lift of the wing.
摘要翻译：包括机翼，扰流板（14），限制扰流器后缘周围的空气循环的装置（16,17）和控制系统的飞机机翼负载减轻系统。扰流面板枢转地附接到机翼，使得扰流板可以从降低的位置向上转动到升高位置，从而在扰流板和机翼之间打开空隙。可缩回装置可以从缩回位置展开到延伸位置，在该位置限制空气围绕扰流板的后缘周围的空气循环并进入空隙，从而减少诱发的阻力。控制系统被配置成检测或预测机翼升力的增加，并响应于机翼升力的检测或预测的增加而将扰流板旋转到其升高位置。

8. 发明申请

US20110226345A1 Deployable Aerodynamic Devices with Reduced Actuator Loads 有权
标题翻译：具有减少执行器负载的可部署空气动力学装置
公开(公告)号：US20110226345A1
公开(公告)日：2011-09-22
申请号：US13150334
申请日：2011-06-01
申请人： Glenn S. Bushnell
发明人： Glenn S. Bushnell
IPC分类号： F03B11/02 , B23P11/00
CPC分类号： B64C9/02 , B64C9/10 , B64C9/32 , B64C9/323 , B64C9/34 , B64C13/38 , Y02T50/32 , Y02T50/44 , Y10T137/0402 , Y10T137/8593
摘要： Deployable aerodynamic devices with reduced actuator loads, and related systems and methods are disclosed. An external flow system in accordance with a particular embodiment includes an external flow body, a deployable device carried by and movable relative to the external flow body, and a coupling connected between the external flow body and the deployable device. The system can further include an actuator device operatively coupled between the external flow body and the deployable device, with the actuator device positioned to move the deployable device along a motion path between a stowed position and the deployed position. The motion path can have a first portion over which the load delivered by the actuator device increases as the deployed device moves toward the deployed position, and a second portion over which the load delivered by the actuator device decreases as the deployed device moves toward the deployed position.
摘要翻译：公开了具有减少的致动器负载的可部署的空气动力学装置以及相关的系统和方法。根据特定实施例的外部流动系统包括外部流动体，由外部流动体承载并可移动的可展开装置，以及连接在外部流动体和可部署装置之间的联接器。该系统还可以包括可操作地联接在外部流动体和可展开装置之间的致动器装置，致动器装置被定位成沿着收起位置和展开位置之间的运动路径移动可展开装置。运动路径可以具有第一部分，当被展开的装置朝向展开位置移动时，致动器装置输送的负载增加;以及第二部分，当被展开的装置朝向展开位置移动时，由致动装置输送的负载减小位置。

9. 发明授权

US06729583B2 Device for articulating a flap to an aircraft aerodynamic surface 有权
标题翻译：用于将翼片铰接到飞行器空气动力学表面的装置
公开(公告)号：US06729583B2
公开(公告)日：2004-05-04
申请号：US10440300
申请日：2003-05-19
申请人： Jérôme Milliere
发明人： Jérôme Milliere
IPC分类号： B64C350
CPC分类号： B64C9/323 , B64C7/00 , B64C9/02 , B64C9/32 , B64C9/34 , Y02T50/32
摘要： An articulation device for articulating a flap to an aircraft aerodynamic surface, the flap having its front edge facing a rear edge of the aerodynamic surface and the articulation device including two fittings bearing the flap. The articulation device pivots about a common axle borne by the aerodynamic surface and arranged at the interior side thereof, in order to cause the flap to adopt either a retracted position or a deployed position. The portion of each fitting facing a corresponding cutout, when the flap is in the retracted position, is set back toward the inside with respect to the outer faces of the aerodynamic surface and the flap. A flat blanking piece, the shape of which corresponds to that of the cutout, is associated with each cutout. Each blanking piece is borne by a linkage articulated to the aerodynamic surface and to the flap.
摘要翻译：一种用于将翼片铰接到飞行器空气动力学表面的铰接装置，所述翼片具有面向空气动力学表面的后边缘的前边缘，并且所述关节运动装置包括承载所述翼片的两个配件。铰接装置围绕由空气动力学表面承载并且布置在其内侧的公共轴枢转，以便使翼片采用缩回位置或展开位置。当翼片处于缩回位置时，每个配件面对相应切口的部分相对于空气动力学表面和翼片的外表面朝内侧回落。与切口的形状相对应的平面冲切件与每个切口相关联。每个冲裁件由连接到空气动力学表面和翼片的连杆承担。

10. 发明授权

US2358985A Aircraft 失效
公开(公告)号：US2358985A
公开(公告)日：1944-09-26
申请号：US32047740
申请日：1940-02-23
申请人： MCANDREW JAMES P
发明人： MCANDREW JAMES P
IPC分类号： B64C3/54
CPC分类号： B64C9/22 , B64C3/54 , B64C9/24 , B64C9/34 , B64C23/06 , B64C2003/146 , B64C2003/148 , Y02T50/162

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