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1. 发明公开

EP3176075A1 AIRCRAFT WING FAIRING DRIVE ASSEMBLY 有权
标题翻译：飞机翼起步驱动总成
公开(公告)号：EP3176075A1
公开(公告)日：2017-06-07
申请号：EP16191800.8
申请日：2016-09-30
申请人： The Boeing Company
发明人： OSBORN, Matthew James , SAKURAI, Seiya , CLARK, Benjamin A. , PENN, Steven C.
IPC分类号： B64C9/16
摘要： A fairing drive assembly (200) couples a flap assembly of a wing of an aircraft to a fairing of the wing. The fairing drive assembly may include a fairing cam (204) including a first joint and a second joint, and a flap link (240) pivotally coupled to the first joint of the fairing cam and the flap assembly. A fairing drive arm (220) is pivotally coupled to the second joint and the fairing. The fairing cam is configured to rotate upon actuation of the flap assembly and deflect the fairing away from the flap assembly.
摘要翻译：整流装置驱动组件（200）将飞机机翼的襟翼组件连接到机翼的整流罩。整流装置驱动组件可以包括整流罩凸轮（204），其包括第一接头和第二接头以及枢转地联接到整流罩凸轮和襟翼组件的第一接头的襟翼连杆（240）。整流罩驱动臂（220）枢转地连接到第二接头和整流罩。整流罩凸轮构造成在致动襟翼组件时旋转并使整流罩偏离襟翼组件。

2. 发明公开

EP0120011A1 MODULAR MULTI-ENGINE THRUST CONTROL ASSEMBLY 失效
标题翻译：模块建设EXPENSIVE DEVICE FOR MULTI-发动机的性能。
公开(公告)号：EP0120011A1
公开(公告)日：1984-10-03
申请号：EP83900294.0
申请日：1982-09-30
申请人： The Boeing Company
发明人： SAKURAI, Seiya
IPC分类号： B64D31
CPC分类号： B64D31/04 , Y10T74/20238 , Y10T74/20396 , Y10T74/20612 , Y10T74/2063
摘要： Assemblage modulaire de leviers de commande de la poussée pour la commande manuelle par le pilote des modes de fonctionnement de poussée vers l'avant/point mort/poussée inversée d'un aéronef à moteurs multiples. L'assemblage comprend des leviers de commande pouvant être actionnés manuellement par le pilote (24L, 24R) possédant chacun une partie fixe de levier (69L, 69R) et une manivelle solidaire (42L, 42R) montée autour d'un axe fixe de pivotement (44) et une partie de manche extensible radialement (85L, 85R et 26L, 26R), les parties de levier à point de pivotement fixe (69L, 69R) et les parties de manche extensibles radialement (85L, 85R) étant reliées par un assemblage coulissant (70L, 70R) et un assemblage de levier (71L, 71R) possédant un rouleau (64L, 64R) mobile dans une fente arquée (66L, 66R); des organes inhibiteurs de pivotement (48L, 48R et 49L, 49R) servant à inhiber le mouvement du rouleau (64L, 64R) à l'intérieur de la fente (66L, 66R) lorsque les moteurs ne sont pas configurés correctement; des organes (31L, 31R, 60L, 60R, 58L, 58R, 55L, 55R) servant à dégager les organes inhibiteurs lorsque les moteurs sont configurés correctement; une pluralité de séparateurs (30L, 30R) de sens opposés, et disposés à différentes distances de l'axe de pivotement (44) des leviers de commande (24L, 24R) et reliés aux manivelles respectives (42L, 42R) par des assemblages de liaison (29L, 29R) de différentes longueurs; les leviers de commande (24L, 24R) et les composants actifs associés étant montés à l'intérieur d'un boîtier étroit et compact (22).

3. 发明授权

EP1940680B2 SEAL ASSEMBLIES FOR USE WITH DROOPED SPOILERS AND OTHER CONTROL SURFACES ON AIRCRAFT 有权
标题翻译：密封组件，可用于飞机上的摔倒的SP AND和其他控制表面
公开(公告)号：EP1940680B2
公开(公告)日：2018-02-28
申请号：EP06851632.7
申请日：2006-08-29
申请人： The Boeing Company
发明人： KORDEL, Jan A. , SAKURAI, Seiya , BOWERS, Bret A. , GLASSMOYER, Chris , WILLIAMS, Darren B.
IPC分类号： B64C9/02 , B64C7/00
CPC分类号： B64C7/00 , B64C9/18 , B64C2009/143 , Y02T50/32 , Y10S277/916
摘要： Aerodynamic seals for use with control surfaces on aircraft are described herein. In one embodiment, a seal assembly for use with an aircraft includes a first seal member and a second seal member. The first seal member has a first proximal portion configured to be attached to a fixed airfoil portion of the aircraft, and a first distal portion configured to extend outwardly from the fixed airfoil portion toward a movable control surface. The second seal member has a second proximal portion configured to be attached to the movable control surface, and a second distal portion configured to extend outwardly from the control surface toward the fixed airfoil portion. In this embodiment, the second distal portion is further configured to movably contact the first distal portion to at least partially seal the gap between the fixed airfoil portion and the movable control surface as the control surface moves relative to the fixed airfoil portion.

4. 发明公开

EP2222552A2 TRAILING EDGE DEVICE REDUNDANT MOUNTING SYSTEM AND METHOD 有权
标题翻译：系统和方法安装冗余OUTLET边缘设备的
公开(公告)号：EP2222552A2
公开(公告)日：2010-09-01
申请号：EP08860051.5
申请日：2008-10-31
申请人： The Boeing Company
发明人： KORDEL, Jan A. , SAKURAI, Seiya , BALZER, Michael A. , DOVEY, John V.
IPC分类号： B64C9/16 , B64C9/02
CPC分类号： B64C9/02 , B64C9/16 , Y02T50/32 , Y02T50/44
摘要： Trailing edge device catchers and associated system and method are disclosed xn the form of a redundant mounting system and method. A system in accordance with one embodiment includes a wing having a wmg support (214,217,218), a trailing edge device (236) carried by and movable relative to the wing and having a device support (234), and a coupling connected between the wing and the trailing edge device The coupling includes a pivot joint that includes a pivot element (253) aligned along a pivot axis and connected between the wing support and the device support The coupling can further include an actuator (236) coupled between the wing and the trailing edge device, with the actuator having a first position in which the trailing edge device is stowed, and a second position in which the trailing edge device is deployed, with an air flow gap located between the wing and the trailing edge device when the trailing edge device is in the second position. A cam track (254e) is carried by one of the wing and the trailing edge device and has opposing cam track surfaces fixed relative to each other A cam (257e) is carried by the other of the wing and trailing edge device and is positioned within the cam track between the opposing cam track surfaces The cam is offset from the pivot axis and during normal operation the cam can carry no load or a first load along a load path that includes the cam track, and when a decrease in support provided by at least one of the pivot element, the wing support and the device support occurs, the cam can carry a second non-zero load greater than the first load along the load path.

5. 发明授权

EP2032434B1 LINK MECHANISMS FOR GAPPED RIGID KRUEGER FLAPS, AND ASSOCIATED SYSTEMS AND METHODS 有权
标题翻译：杠杆机构刚性克鲁格分裂倍和相关系统和方法
公开(公告)号：EP2032434B1
公开(公告)日：2010-06-02
申请号：EP07861281.9
申请日：2007-04-02
申请人： The Boeing Company
发明人： FOX, Stephen J. , SAKURAI, Seiya
IPC分类号： B64C9/22
CPC分类号： B64C9/22 , Y02T50/32 , Y02T50/44

6. 发明授权

EP0120011B1 MODULAR MULTI-ENGINE THRUST CONTROL ASSEMBLY 失效
标题翻译：模块化多发动机控制组件
公开(公告)号：EP0120011B1
公开(公告)日：1989-03-01
申请号：EP83900294.6
申请日：1982-09-30
申请人： THE BOEING COMPANY
发明人： SAKURAI, Seiya
IPC分类号： G05G5/02 , G05G7/00 , G05G13/00
CPC分类号： B64D31/04 , Y10T74/20238 , Y10T74/20396 , Y10T74/20612 , Y10T74/2063
摘要： A modular thrust control lever assembly for manual pilot control of the forward/idle/reverse thrust operational modes of multiple engine aircraft and including manually manipulable pilot control levers (24L, 24R) each having a fixed lever portion (69L, 69R) and an integral crank (42L, 42R) mounted about a fixed pivot axis (44) and a radially extendable handle portion (85L, 85R and 26L, 26R) with the fixed pivoted lever portions (69L, 69R) and radially extendable handle portion (85L, 85R) being secured together by a slide assembly (70L, 70R) and a lever assembly (71L, 71R) having a roller (64L, 64R) movable in an arcuate slot (66L, 66R); pivotal inhibit means (48L, 48R and 49L, 49R) for inhibiting motion of the roller (64L, 64R) within the slot (66L, 66R) when the engines are not properly configured; means (31L, 31R, 60L, 60R, 58L, 58R, 55L, 55R) for disengaging said inhibit means when the engines are properly configured; a plurality of resolvers (30L, 30R) of opposite hand and disposed at different distances from the pivot axis (44) of the control levers (24L, 24R) and interconnected to respective ones of the cranks (42L, 42R) by linkage assemblies (29L, 29R) of different lengths; with said control levers (24L, 24R) and associated operating components being mounted within a thin, compact housing (22).

7. 发明公开

EP3418185A1 ACTUATOR ASSEMBLIES TO DEPLOY AIRCRAFT LEADING EDGE FLAPS AND SEALS FOR AIRCRAFT LEADING EDGE FLAPS 有权转让
公开(公告)号：EP3418185A1
公开(公告)日：2018-12-26
申请号：EP18178794.6
申请日：2018-06-20
申请人： The Boeing Company
发明人： JOHNSON, Patterson , SAKURAI, Seiya , SANTINI, Gregory M. , KONINGS, Christopher A. , CLARK, Adam M.
IPC分类号： B64C9/34 , B64C9/22
CPC分类号： B64C9/34 , B64C9/22
摘要： Example actuator assemblies (224) to deploy aircraft leading edge flaps and seals for aircraft leading edge flaps (202) are described herein. An example apparatus includes an aircraft flap (202) that is movable between a stowed position and a deployed position. The flap includes a top panel (308). A notch (372) is formed in the top panel and extends into a side of the top panel near a trailing edge (313) of the flap. The example apparatus also includes a seal (1000) coupled to the flap. The seal (1000) is movable to cover the notch (372) when the flap (202) is in the deployed position.

8. 发明授权

EP2296964B1 AIRCRAFT FILLET FAIRINGS WITH FIXED AND MOVEABLE PORTIONS, AND ASSOCIATED SYSTEMS AND METHODS 有权
标题翻译：与固定板等部件和运动部件及相关系统和方法平面围巾
公开(公告)号：EP2296964B1
公开(公告)日：2012-12-19
申请号：EP08874230.9
申请日：2008-05-09
申请人： The Boeing Company
发明人： LACY, Douglas S. , BENN, Gregory S. , WHEATON, James M. , SANTINI, Gregory M. , SAKURAI, Seiya , SMITH, Lawrence D.
IPC分类号： B64C7/00 , B64C9/16 , B64C3/58 , B64C9/02 , B64C9/04
CPC分类号： B64C7/00 , B64C3/58 , B64C9/02 , B64C9/04 , B64C9/16

9. 发明公开

EP2296964A1 AIRCRAFT FILLET FAIRINGS WITH FIXED AND MOVEABLE PORTIONS, AND ASSOCIATED SYSTEMS AND METHODS 有权
标题翻译：与固定板等部件和运动部件及相关系统和方法平面围巾
公开(公告)号：EP2296964A1
公开(公告)日：2011-03-23
申请号：EP08874230.9
申请日：2008-05-09
申请人： The Boeing Company
发明人： LACY, Douglas S. , BENN, Gregory S. , WHEATON, James M. , SANTINI, Gregory M. , SAKURAI, Seiya , SMITH, Lawrence D.
IPC分类号： B64C7/00 , B64C9/16
CPC分类号： B64C7/00 , B64C3/58 , B64C9/02 , B64C9/04 , B64C9/16
摘要： Aircraft fillet fairings with fixed and moveable portions, and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a wing (10) having an upper surface (111), an inboard portion, and an outboard portion. A deployable flap (140) is carried by the wing at the inboard portion. The flap has an upper surface and is moveable relative to the wing between a stowed position and a deployed position, with the flap extending aft of the wing when in the deployed position. The system further includes a fillet (120) that in turn includes a forward portion fixed relative to the wing and projecting upwardly from the wing upper surface, and an aft portion (122) that is moveable with the flap. The aft portion projects upwardly from the flap upper surface and is generally aligned with the forward portion in an axial direction.

10. 发明授权

EP1963179B1 AIRCRAFT TRAILING EDGE DEVICES, INCLUDING DEVICES WITH NON-PARALLEL MOTION PATHS, AND ASSOCIATED METHODS 有权
标题翻译：后端设备对于飞机包括与非平行运动CARS设备和相关方法
公开(公告)号：EP1963179B1
公开(公告)日：2010-06-16
申请号：EP06844458.7
申请日：2006-11-20
申请人： THE BOEING COMPANY
发明人： LACY, Douglas, S. , BEYER, Kevin, W. , BROWN, Stephen, T. , DEES, Paul, W. , HUYNH, Neal, V. , KORDEL, Jan, A. , PROW, Clayton, A. , SAKURAI, Seiya
IPC分类号： B64C9/16
CPC分类号： B64C9/16 , B64C2009/143
摘要： Aircraft trailing edge devices (230) , including devices with non-parallel motion paths (241, 242, 243) , and associated methods are disclosed. A device in accordance with one embodiment includes a wing (220) and an inboard trailing edge (231) device coupled to the wing and movable relative to the wing between a first stowed position and a first deployed position along a first motion path (241) . An outboard trailing edge (232) device can be coupled to the wing outboard of the inboard trailing edge device, and can be movable relative to the wing along a second motion path (242) that is non-parallel to the first motion path. An intermediate trailing edge device (260) can be coupled between the inboard and outboard trailing edge devices and can be movable along a third motion path (243) that is non-parallel to both the first and second motion paths. Each of the trailing edge devices can open a gap relative to the wing when moved to their respective deployed positions.

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