专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明申请

US20220324549A1 SPOILER ACTUATION SYSTEMS AND METHODS FOR AIRCRAFT 有权
公开(公告)号：US20220324549A1
公开(公告)日：2022-10-13
申请号：US17526884
申请日：2021-11-15
申请人： The Boeing Company
发明人： Neal V. Huynh
IPC分类号： B64C9/20 , B64C13/42
摘要： An example aircraft disclosed herein includes a wing, a spoiler rotatably coupled to the wing, the spoiler movable between a cruise position and an upward position and between the cruise position and a droop position, and a spoiler actuation system coupled to a hydraulic system of the aircraft, the spoiler actuation system including a first piston and a second piston, a rack coupled between the first piston and the second piston, the rack movable between a first position and a second position, a pinion coupled to the rack, the pinion to rotate between a third position and a fourth position when the rack moves between the first position and the second position, a first crank arm coupled to the pinion, the first crank arm to rotate with the pinion between the third position and the fourth position, and a second crank arm coupled to the first crank arm and to the spoiler, the second crank arm to move the spoiler between the cruise position and the upward position when the first crank arm rotates between the third position and the fourth position.

2. 发明申请

US20220306282A1 TRAILING EDGE PANEL SUPPORT WITH BIASING ARRANGEMENT 有权
公开(公告)号：US20220306282A1
公开(公告)日：2022-09-29
申请号：US17703653
申请日：2022-03-24
申请人： Airbus Operations Ltd.
发明人： William Tulloch
IPC分类号： B64C9/02 , B64C9/20 , B64F5/10 , B64C13/34
摘要： A method of securing a lower trailing edge panel of an aircraft wing. The wing includes a wingbox with an upper cover, a lower cover, and a rear spar. A leading edge of the lower trailing edge panel is attached to the wingbox. A support structure is also attached to the wingbox and a connector is mounted to the trailing edge panel. A link is provided, with a first end and a second end. The second end of the link is pivotally attached to the support structure at a pivot joint. A biasing arrangement biases the link towards an upright orientation in which the first end of the link is higher than the pivot joint. The link is held in its upright orientation with the biasing arrangement; and then the first end of the link is attached to the connector.

3. 发明授权

US11192636B2 Aerodynamic redundant actuation system for aircraft 有权
公开(公告)号：US11192636B2
公开(公告)日：2021-12-07
申请号：US16813511
申请日：2020-03-09
申请人： THE BOEING COMPANY
发明人： Bret Alan Bowers , Scott Thomas Evoy
IPC分类号： B64C13/00 , B64C13/28 , B64C9/00 , B64C13/50 , B64C9/20 , B64C13/42 , B64C9/04
摘要： An actuation system for a control surface of an aircraft includes a drive lever. The drive lever includes a coupling end configured to pivotably couple to a plurality of wing attach fittings and a lever end. The lever end includes a first actuator fitting configured to pivotably couple to a first actuator on a forward side of the drive lever; a second actuator fitting configured to pivotably couple to a second actuator on an aft side of the drive lever; a first drive link fitting configured to couple, via a first drive link, to a control surface of an aircraft; and a second drive link fitting configured to couple, via a second drive link, to the control surface of the aircraft.

4. 发明授权

US11142302B1 Fluidic split flap systems for yaw control in forward flight 有权
公开(公告)号：US11142302B1
公开(公告)日：2021-10-12
申请号：US16833620
申请日：2020-03-29
申请人： Textron Innovations Inc.
发明人： Daniel Bryan Robertson , Kirk Landon Groninga , Matthew Edward Louis
IPC分类号： B64C21/08 , B64C9/20 , B64C29/00
摘要： An active flow control system for generating yaw control moments for an aircraft during forward flight. The system includes right and left yaw effectors disposed proximate the right and left wingtips of the wing. A pressurized air system includes a pressurized air source and a plurality of injectors operably associated with the right and left yaw effectors that influence the path of airflow above and below the yaw effectors. Based upon which of the injectors is injecting pressurized air, the right and left yaw effectors generate no yaw control moment, generate a yaw right control moment or generate a yaw left control moment.

5. 发明授权

US10988238B2 Flight control surface assembly 有权
公开(公告)号：US10988238B2
公开(公告)日：2021-04-27
申请号：US16230146
申请日：2018-12-21
申请人： Airbus Operations GmbH
发明人： Bernhard Schlipf , Peter Lücken
IPC分类号： B64C13/50 , B64C9/20 , B64C9/26 , B64D45/00 , B64C3/38 , B64C9/02
摘要： A flight control surface assembly for mounting to a main wing of an aircraft includes flight control surfaces side by side with a gap between each two of them, a connection assembly for movably connecting the flight control surfaces to the main wing to be selectively movable in a predetermined synchronous movement between retracted and extended positions, a drive arrangement operable to effect predetermined synchronous movement, and a control unit connected to the drive arrangement to control the drive arrangement. The flight control surface assembly includes for each gap a separate pair of electrical components with a first electrical component and a second electrical component fixedly mounted to a another one of the two flight control surfaces separated by the gap. The first and second electrical components of each pair are configured to wirelessly transfer electrical energy over the gap.

6. 发明授权

US10647412B2 Flight control augmentation system and method for high aspect ratio aircraft including: motorglider aircraft, optionally piloted vehicles (OPVs) and unpiloted air vehicles (UAVs) 有权
公开(公告)号：US10647412B2
公开(公告)日：2020-05-12
申请号：US16252322
申请日：2019-01-18
申请人： Marc Arnold
发明人： Marc Arnold
IPC分类号： B64C13/28 , B64C13/30 , B64C13/04 , B64C9/12 , B64C13/16 , B64C19/02 , B64C9/10 , B64C9/18 , B64C9/20 , B64C39/02 , G05D1/06 , B64C9/00
摘要： A control augmentation system for high aspect ratio aircraft has aileron/flaperon and throttle position sensors; spoiler and flap controls; a mode switch with manual, and landing modes; and a controller driving left and right spoiler and flap servos, the controller including at least one processor with memory containing firmware configured to: when the mode switch is in manual mode, drive both spoiler servos to a symmetrical position according to the spoiler control; when the mode switch is in landing mode, drive the left spoiler to a position dependent on aileron and throttle position, and the right spoiler to a position dependent on aileron and throttle position, the left and right spoiler positions differing whenever ailerons are not centered, and an average of spoiler positions is more fully deployed when the throttle position is at a low-power setting than when the throttle position is at a high-power setting.

7. 发明授权

US10479484B2 Methods and apparatus for controlling aircraft flight control surfaces 有权
公开(公告)号：US10479484B2
公开(公告)日：2019-11-19
申请号：US15695749
申请日：2017-09-05
申请人： The Boeing Company
发明人： Neal Van Huynh , Patrick Joseph McCormick
IPC分类号： B64C9/20 , B64C13/42 , B64C13/50
摘要： Methods and apparatus for controlling aircraft flight control surfaces are disclosed. An example apparatus includes a flight control surface controller to move a control surface of an aircraft to a target position via at least one of a first actuator or a second actuator associated with the control surface based on a command input received by the flight control surface controller. The flight control surface controller to: obtain a flight characteristic of the aircraft; compare the flight characteristic to a flight characteristic threshold; in response to a first comparison result, cause the first actuator to move the control surface to the target position based on the command input without moving the second actuator; and in response to a second comparison result, cause the first actuator and the second actuator to move the control surface to the target position based on the command input.

8. 发明申请

US20190291850A1 DISTRIBUTED TRAILING EDGE WING FLAP SYSTEMS 审中-公开
公开(公告)号：US20190291850A1
公开(公告)日：2019-09-26
申请号：US15926477
申请日：2018-03-20
申请人： The Boeing Company
发明人： Neal V. Huynh
IPC分类号： B64C9/20 , B64C13/42 , B64C13/50 , B64D45/00
摘要： Distributed trailing edge wing flap systems are described. An example wing flap system for an aircraft includes a flap, an actuator, a first hydraulic module, and a second hydraulic module. The flap is movable between a deployed position and a retracted position relative to a fixed trailing edge of a wing of the aircraft. The actuator is to move the flap relative to the fixed trailing edge. The first hydraulic module is located at the actuator. The second hydraulic module is located remotely from the first hydraulic module and includes a local power unit. The actuator is hydraulically drivable via first pressurized hydraulic fluid to be supplied from a hydraulic system of the aircraft to the actuator via the second hydraulic module and further via the first hydraulic module. The actuator is also hydraulically drivable via second pressurized hydraulic fluid to be supplied from the local power unit to the actuator via the second hydraulic module and further via the first hydraulic module.

9. 发明申请

US20180170521A1 WING, FLAP, AND AIRCRAFT 审中-公开
公开(公告)号：US20180170521A1
公开(公告)日：2018-06-21
申请号：US15577055
申请日：2016-04-14
申请人： JAPAN AEROSPACE EXPLORATION AGENCY
发明人： Mitsuhiro Murayama , Kazuomi Yamamoto
IPC分类号： B64C9/20 , B64C23/06
CPC分类号： B64C9/20 , B64C3/10 , B64C9/18 , B64C23/06 , Y02T50/162
摘要： The present invention is directed to reducing noise resulting from a wing tip vortex of a wing such as a flap. A flap of an aircraft includes a flap main body provided to a parent wing in a deployable manner, and a vortex generation portion including a protruding member, the protruding member being provided to protrude from an upper surface at least at an end of the flap main body on an outboard side in a span direction and forming a predetermined angle to an axial direction of the aircraft. A rear end of the protruding member is located on the side adjacent to a side-end edge at the end of the flap main body in the span direction relative to a virtual line passing through a front end of the protruding member and being parallel to the axial direction.

10. 发明授权

US09771141B2 Leading edge system and method for approach noise reduction 有权
公开(公告)号：US09771141B2
公开(公告)日：2017-09-26
申请号：US14035011
申请日：2013-09-24
申请人： The Boeing Company
发明人： Matthew A. Moser , Michael R. Finn , Duk Park , Christopher A. Konings
IPC分类号： B64C9/16 , B64C9/20 , B64C9/22 , B64C9/24 , B64C13/28
CPC分类号： B64C9/16 , B64C9/20 , B64C9/22 , B64C9/24 , B64C13/28 , Y02T50/32 , Y02T50/44
摘要： A slat control system for an aircraft may include a flight control computer configured to generate a gap command in response to an occurrence of a gap-command condition. The slat control system may further include an edge control system including an edge control device having a plurality of control device positions including at least one designated control device position. The slat control system may additionally include a device actuation system configured to move a leading edge device of an aircraft. The edge control system may be configured to automatically command the device actuation system to extend the leading edge device from a sealed position to a gapped position when the edge control device is in the designated control device position and the gap command is received by the edge control system.

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式