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1. 发明申请

WO2009075963A3 TRAILING EDGE DEVICE CATCHERS AND ASSOCIATED SYSTEMS AND METHODS 审中-公开
标题翻译：跟踪边缘设备捕获器和相关系统和方法
公开(公告)号：WO2009075963A3
公开(公告)日：2010-04-01
申请号：PCT/US2008082146
申请日：2008-10-31
申请人： BOEING CO , KORDEL JAN A , SAKURAI SEIYA , BALZER MICHAEL A , DOVEY JOHN V
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.
摘要翻译：以冗余安装系统和方法的形式公开了后端设备捕获器和相关联的系统和方法。根据一个实施例的系统包括具有wmg支撑件（214,217,218）的翼片，后缘装置（236），后缘装置（236）由相对于所述机翼承载并可相对于所述机翼运动并具有装置支撑件（234），以及联接件，所述后缘装置所述联接器包括枢转接头，所述枢转接头包括枢转元件（253），所述枢转元件（253）沿着枢转轴线对齐并且连接在所述翼片支撑件和所述装置支撑件之间。所述联接器还可包括联接在所述机翼和所述尾部所述致动器具有第一位置，在所述第一位置中所述后缘装置被收起;以及第二位置，所述后缘装置展开在所述第二位置，当所述翼缘和所述后缘装置之间的后缘设备处于第二位置。凸轮轨道（254e）由翼和后缘装置中的一个承载，并且具有相对于彼此固定的相对的凸轮轨道表面。凸轮（257e）由机翼和后缘装置中的另一个承载，并且位于相对的凸轮轨道表面之间的凸轮轨道凸轮偏离枢转轴线，并且在正常操作期间，凸轮可沿着包括凸轮轨道的负载路径承载负载或第一负载，并且当由于枢轴元件，机翼支撑件和设备支撑件中的至少一个发生，凸轮可承载沿着负载路径大于第一负载的第二非零负载。

2. 发明申请

WO2008054360A2 SEAL ASSEMBLIES FOR USE WITH DROOPED SPOILERS AND OTHER CONTROL SURFACES ON AIRCRAFT 审中-公开
标题翻译：密封组件与飞机上的飞机和其他控制面一起使用
公开(公告)号：WO2008054360A2
公开(公告)日：2008-05-08
申请号：PCT/US2006033812
申请日：2006-08-29
申请人： BOEING CO , KORDEL JAN A , SAKURAI SEIYA , BOWERS BRET A , GLASSMOYER CHRIS , WILLIAMS DARREN B
发明人： KORDEL JAN A , SAKURAI SEIYA , BOWERS BRET A , GLASSMOYER CHRIS , WILLIAMS DARREN B
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.
摘要翻译：这里描述了用于与飞机上的控制表面一起使用的气动密封件。在一个实施例中，与飞行器一起使用的密封组件包括第一密封构件和第二密封构件。第一密封构件具有构造成附接到飞机的固定翼型部分的第一近端部分，以及构造成从固定翼型部分朝向可移动控制表面向外延伸的第一远端部分。第二密封构件具有构造成附接到可移动控制表面的第二近端部分，以及被配置为从控制表面朝向固定翼型部分向外延伸的第二远端部分。在该实施例中，第二远端部分进一步构造成当控制表面相对于固定翼型部分移动时，可移动地接触第一远端部分以至少部分地密封固定翼型部分和可移动控制表面之间的间隙。

3. 发明申请

WO2008051286A3 LINK MECHANISMS FOR GAPPED RIGID KRUEGER FLAPS, AND ASSOCIATED SYSTEMS AND METHODS 审中-公开
标题翻译：针对刚果克鲁格片及其相关系统和方法的链接机制
公开(公告)号：WO2008051286A3
公开(公告)日：2008-08-14
申请号：PCT/US2007008301
申请日：2007-04-02
申请人： BOEING CO , FOX STEPHEN J , SAKURAI SEIYA
发明人： FOX STEPHEN J , SAKURAI SEIYA
IPC分类号： B64C9/22
CPC分类号： B64C9/22 , Y02T50/32 , Y02T50/44
摘要： Link mechanisms for gapped rigid Krueger flaps, and associated methods and systems are disclosed. A system in accordance with one embodiment includes a deployable leading edge assembly (120) that in turn includes a deployable leading edge panel (121) having a generally fixed-shape flow surface, a bullnose (123) coupled to the panel,, and a link mechanism (130) coupled to the panel and the bullnose to move the panel between a stowed position and a deployed position. The mechanism includes a first support link (131), a second support link (132), and first (133), second (134), and third (135) positioning links. The positioning links are pivotably connected among the leading edge panel, the bullnose, the first support link and the second support link so that the leading edge panel forms a gap (101) with the airfoil when in the deployed position. The positioning links are the only positioning links coupled between the support links, the leading edge panel, and the bullnose at a particular wing span location.
摘要翻译：公开了用于间隙刚性克鲁格襟翼的链接机构，以及相关联的方法和系统。根据一个实施例的系统包括可展开的前缘组件（120），所述前缘组件又包括具有大致固定形状的流动表面的可展开的前缘面板（121），连接到所述面板的雄牛（123）和连杆机构（130），其联接到所述面板和所述牛头以在所述收起位置和展开位置之间移动所述面板。该机构包括第一支撑连杆（131），第二支撑连杆（132）和第一（133），第二（134）和第三（135）定位连杆。所述定位连杆在所述前缘面板，所述牛芯，所述第一支撑连杆和所述第二支撑连杆之间可枢转地连接，使得所述前缘面板在处于展开位置时与所述翼型件形成间隙（101）。定位连杆是在特定翼展位置处联接在支撑连杆，前缘面板和大牛之间的唯一定位连杆。

4. 发明公开

EP1972200A4 FLUID KONJAC MATERIAL, METHOD OF PRODUCING THE SAME AND USE THEREOF 失效转让
标题翻译：液体KONJACMATERIAL，用于生产和使用
公开(公告)号：EP1972200A4
公开(公告)日：2009-03-18
申请号：EP07706521
申请日：2007-01-10
申请人： SAKURAI SEIYA
发明人： SAKURAI SEIYA
IPC分类号： A23L1/214 , A23L1/0528 , A23L1/30 , A23L1/308 , A23L2/38 , A23L2/52 , A61K31/736 , A61K36/888 , A61P3/06 , A61P9/00
CPC分类号： A61K31/736 , A23L2/38 , A23L2/52 , A23L19/01 , A23L19/115 , A23L29/244 , A23L33/105 , A23V2002/00 , A61K36/888 , A23V2250/5066 , A23V2200/332 , A23V2250/304
摘要： Konjac (Amorphophallus konjac) powder is swollen with water and dissolved therein, treated with an alkali at pH 10 or above and, after lowering the pH value to 8 or below, treated with an enzyme while lowering temperature under forcedly stirring. Thus, it is possible to provide a composition which fully sustains the gelling power and biological functions inherent to konjac mannan and enables more homogeneous mixing of a konjac material at a higher concentration with other food materials.

5. 发明专利

JPH05336916A 失效
公开(公告)号：JPH05336916A
公开(公告)日：1993-12-21
申请号：JP16832392
申请日：1992-06-04
申请人： SAKURAI SEIYA
发明人： SAKURAI SEIYA
IPC分类号： A23L11/00 , A23L3/36 , A23L1/20
摘要： PURPOSE:To prepare the subject bean curd freezable without forming cavities and giving a frozen bean curd which can be thawed without causing syneresis to form porous texture by mixing soya milk, oil and fat, starch and a thickener at specific ratios, heating the mixture, cooling to a prescribed temperature and coagulating the mixture with a coagulant. CONSTITUTION:The bean curd is prepared by adding 0.1-50 pts.wt. of oil and fat such as soybean oil, 5-20 pts.wt. of starch such as potato starch and, as necessary,

6. 发明专利

CA2824108C HINGED RAKED WING TIP 未知
公开(公告)号：CA2824108C
公开(公告)日：2019-08-06
申请号：CA2824108
申请日：2013-08-16
申请人： BOEING CO
发明人： DEES PAUL W , GOOD MARK S , SAKURAI SEIYA , KORDEL JAN A , FOX STEPHEN J , LASSEN MATTHEW A , FOX BRUCE ROBERT , WALKER STEVEN PAUL , SANTINI GREGORY M
IPC分类号： B64C3/56
摘要： A wing assembly that provides a longer wingspan in flight than when grounded at an airport comprises a raked wing tip having an outboard portion hinged to one of a main wing having at least one moveable control surface and an inboard raked wing tip portion. The outboard portion of the raked wing tip is movable between a folded position and an extended position in which the outboard portion is approximately in a same plane as the main wing or the inboard raked wing tip portion. The wing assembly further comprises a stub spar coupled to the outboard portion of the raked wing tip. The stub spar extends from an end of the outboard portion and is configured for insertion into the main wing or the inboard raked wing tip portion when the outboard portion is in the extended position.

7. 发明专利

ES2633215T3 Alerón separado de alta elevación accionado por rotación 未知
公开(公告)号：ES2633215T3
公开(公告)日：2017-09-19
申请号：ES13167354
申请日：2013-05-10
申请人： BOEING CO
发明人： KORDEL JAN A , SAKURAI SEIYA
IPC分类号： B64C9/16 , B64C9/14 , B64C9/18
摘要： Un sistema (232, 300) de alerón separado de alta velocidad accionado por rotación, que comprende: un alerón (306) separado de alta elevación que puede funcionar para acoplarse a una forma de ala (302) mediante un accionador (312) giratorio en una línea (418) de bisagra del alerón separado de alta elevación y el accionador giratorio y operable para cambiar una curvatura (416) de la forma de ala; el accionador (312) giratorio acoplado al alerón separado de alta velocidad y operable para producir un movimiento giratorio del alerón separado de alta elevación en respuesta a un comando de accionamiento; un panel (308) de caída posicionado sobre la línea de bisagra y operable para mejorar la elevación de un alerón separado de alta elevación; una puerta (310) de reborde de bóveda posicionada bajo la línea de bisagra y operable para proporcionar un flujo de aire sobre el alerón separado de alta elevación; y un mecanismo (304, 502, 602, 702, 802) de enlace de despliegue acoplado al alerón separado de alta elevación y operable para posicionar el panel de caída y la puerta de reborde de bóveda en respuesta al movimiento giratorio.

8. 发明专利

CA2824727A1 HORIZONTAL FOLDING WINGTIP 未知
公开(公告)号：CA2824727A1
公开(公告)日：2014-04-30
申请号：CA2824727
申请日：2013-08-23
申请人： BOEING CO
发明人： SANTINI GREGORY M , SAKURAI SEIYA
IPC分类号： B64C3/56
摘要： An apparatus of an aircraft, the apparatus may include a wing comprising an unfixed portion and a fixed portion. The unfixed portion movably may connect to the fixed portion. The unfixed portion may include a rotating portion to rotate the unfixed portion between a flight position and a folded position. The fixed portion may connect to the unfixed portion of the wing. A joint may allow rotation of the unfixed portion of the wing with respect to the fixed portion of the wing about a rotation axis.

9. 发明专利

DE602006015498D1 DICHTUNGSANORDNUNGEN ZUR VERWENDUNG MIT REGELDIFFERENZSPOILERN UND ANDEREN STEUERUNGSFLÄCHEN AUF EINEM FLUGZEUG 未知
公开(公告)号：DE602006015498D1
公开(公告)日：2010-08-26
申请号：DE602006015498
申请日：2006-08-29
申请人： BOEING CO
发明人： KORDEL JAN A , SAKURAI SEIYA , BOWERS BRET A , GLASSMOYER CHRIS , WILLIAMS DARREN B
IPC分类号： B64C9/02 , B64C7/00

10. 发明专利

AT471276T 未知
公开(公告)号：AT471276T
公开(公告)日：2010-07-15
申请号：AT06844458
申请日：2006-11-20
申请人： BOEING CO
发明人： LACY DOUGLAS , BEYER KEVIN , BROWN STEPHEN , DEES PAUL , HUYNH NEAL , KORDEL JAN , PROW CLAYTON , SAKURAI SEIYA
IPC分类号： B64C9/16
摘要： Aircraft trailing edge devices, including devices with non-parallel motion paths, and associated methods are disclosed. A device in accordance with one embodiment includes a wing and an inboard trailing edge 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. An outboard trailing edge 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 that is non-parallel to the first motion path. An intermediate trailing edge device can be coupled between the inboard and outboard trailing edge devices and can be movable along a third motion path 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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