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1. 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。

2. 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.

3. 发明专利

DE69623384D1 未知
公开(公告)号：DE69623384D1
公开(公告)日：2002-10-10
申请号：DE69623384
申请日：1996-05-09
申请人： BOEING CO
发明人： ODELL RICHARD B , FOX STEPHEN J , SALMON HUW J , ENNES JOHN A
IPC分类号： E05B65/00 , B64C1/14
摘要： A latch-lock mechanism for an airplane cargo door (34) is disclosed. The latch-lock mechanism includes straight-through drive shafts rotated by a common powered drive unit (61). Affixed to the outer ends of the drive shafts are pull-in hooks (67) that co-act with pull-in pins affixed to the fuselage of the airplane adjacent to the sides of the cargo door opening. The co-action between the pull-in hooks and the pull-in pins pulls the cargo door into a closed position against a distorted fuselage cargo door opening. During opening, the co-action between the pull-in hooks and the pull-in pins force the door open against ice jams. After being pulled into a closed position, latch cams (89) rotated by the drive shafts are closed around latch pins (131). Thereafter, lock pawls (159) are moved into a closed position. The latch-lock mechanism also includes witness ports (193) located in the cargo door (34) that enable a mechanic to verify that the lock pawls (159) are in the closed position. The lock pawls (159) are prevented from closing unless they "feel" that the associated latch cam (89) is closed. The latch-lock handle mechanism also includes a lock handle housing (141) that must be opened in order to access a manual drive 90 DEG gear box (71) used to manually operate the power drive unit (61) and, thus, rotate the drive shafts. Further, mechanical fusing is provided to prevent the application of excessive manual force to the latch-lock mechanism. The lock handle housing (141) is closed by a lock handle (203) having latch whose holding force must be overcome by a pull force, which eliminates the possibility of the door being opened by hydrodynamic water pressure.

4. 发明专利

CA2810148A1 SWING TIP ASSEMBLY ROTATION JOINT 未知
公开(公告)号：CA2810148A1
公开(公告)日：2013-12-21
申请号：CA2810148
申请日：2013-03-21
申请人： BOEING CO
发明人： SAKURAI SEIYA , JONES KELLY T , FOX STEPHEN J , FOX BRUCE R , BENNETT NICHOLAS I , GOOD MARK S
IPC分类号： B64C3/56 , B64C3/40 , F16C11/04 , F16C11/10
摘要： A rotation joint and methods for rotationally coupling a swing tip assembly to a fluid-dynamic body are presented. A rotation plate configured to couple to the swing tip assembly comprises a slide ring comprising an open center, an upper slide surface, an inner slide surface, and a lower slide surface. An upper joint plate is slidably coupled to the upper slide surface and the inner slide surface is configured to couple the fluid-dynamic body. A lower joint plate is slidably coupled to the lower slide surface and the inner slide surface, and is coupled to the upper joint plate through the open center. The lower joint plate is configured to couple to the fluid-dynamic body.

5. 发明专利

AT469824T 未知
公开(公告)号：AT469824T
公开(公告)日：2010-06-15
申请号：AT07861281
申请日：2007-04-02
申请人： BOEING CO
发明人： FOX STEPHEN J , SAKURAI SEIYA
IPC分类号： B64C9/22
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 that in turn includes a deployable leading edge panel having a generally fixed-shape flow surface, a bullnose coupled to the panel, and a link mechanism coupled to the panel and the bullnose to move the panel between a stowed position and a deployed position. The mechanism can include a first support link, a second support link, and first, second, and third positioning links. The positioning links can be 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 with the airfoil when in the deployed position. The positioning links can be the only positioning links coupled between the support links, the leading edge panel, and the bullnose at a particular wing span location.

6. 发明专利

AU2003243738A1 METHOD AND APPARATUS FOR CONTROLLING AIRFLOW WITH A GAPPED TRAILING EDGE DEVICE HAVING A FLEXIBLE FLOW SURFACE 未知
公开(公告)号：AU2003243738A1
公开(公告)日：2004-01-23
申请号：AU2003243738
申请日：2003-06-19
申请人： BOEING CO
发明人： PROW CLAYTON A , FOX STEPHEN J , BEYER KEVIN W , SAKURAI SEIYA , MEREDITH PAUL T , WELLS STEPHEN L , LACY DOUGLAS S
IPC分类号： B64C9/18 , B64C9/14
摘要： A method and apparatus for controlling airflow with a gapped trailing edge device having a flexible flow surface. The airfoil can include a first portion having a first leading edge, a first flow surface, and a second flow surface facing opposite from the first flow surface. The airfoil can further include a second portion having a second leading edge and a trailing edge, with at least part of the second portion being positioned aft of the first portion. The second portion is moveable relative to the first portion between a first position and a second position, with the second leading edge separated from at least part of the first portion by an airflow gap when the second portion is in the second position. The second portion includes a flexible flow surface that has a first shape when the second portion is in the first position, and has a second shape different than the first shape when the second portion is in the second position.

7. 发明专利

CA2845038C HIGH-POSITIONED 2-POSITION VARIABLE CAMBER KRUEGER 未知
公开(公告)号：CA2845038C
公开(公告)日：2017-09-05
申请号：CA2845038
申请日：2014-03-05
申请人： BOEING CO
发明人： SAKURAI SEIYA , FOX STEPHEN J , REYES VICTOR H
IPC分类号： B64C13/28 , B64C3/50
摘要： A variable camber Krueger flap deployment linkage mechanism is presented. A first linkage assembly couples a flap assembly and an airfoil, and comprising a first drive arm, a first drive link, and a support arm. A second linkage assembly couples the flap assembly and the first drive arm, and comprises a drive transfer arm, a middle connection segment, and a bullnose link.

8. 发明专利

ES2603564T3 Flap Krueger de curvatura variable de 3 posiciones en posición elevada 未知
公开(公告)号：ES2603564T3
公开(公告)日：2017-02-28
申请号：ES12193411
申请日：2012-11-20
申请人： BOEING CO
发明人： SAKURAI SEIYA , FOX STEPHEN J , REYES VICTOR , CHARLES KARA MARIE
IPC分类号： B64C9/22 , B64C9/24
摘要： Un mecanismo de articulación de despliegue del flap que comprende: un primer montaje de articulación (506) que funciona para acoplarse a un montaje del flap (502) y un plano aerodinámico (302, 400), donde el primer montaje de articulación (506) comprende: un primer brazo motriz (512) acoplado al plano aerodinámico (302, 400), y que funciona para girar en un plano en el sentido de la cuerda (560); una primera articulación de accionamiento (514) acoplada al primer brazo motriz (512) y un extremo de salida del montaje del flap (502); y un brazo de soporte (516) acoplado a una parte de articulación del medio (520) de la primera articulación de accionamiento (514) y acoplado de forma giratoria al plano aerodinámico (302, 400); y un segundo montaje de articulación (508) que funciona para acoplarse al montaje del flap (502) y al plano aerodinámico (302, 400), donde el segundo montaje de articulación (508) comprende: un brazo motriz de transferencia (530) acoplado a una parte del flap del medio (532) del montaje del flap (502) y acoplado de forma giratoria al plano aerodinámico (302, 400); y una segunda articulación de accionamiento (528) acoplada de forma giratoria a una parte de brazo de transferencia del medio (536) del brazo motriz de transferencia (530) caracterizado por que tal brazo de soporte (516) y tal brazo motriz de transferencia (530) se acoplan de forma giratoria al plano aerodinámico (302,400) en una articulación común (522); tal segundo montaje de articulación (508) comprende además: un segundo brazo motriz (524) acoplado de forma giratoria al primer brazo motriz (512); un brazo de control de giro (526) acoplado al segundo brazo motriz (524) y el plano aerodinámico (302, 400), y que funciona para controlar un giro del segundo brazo motriz (524); donde tal segunda articulación de accionamiento (528) se acopla de forma giratoria a tal segundo brazo motriz (524).

9. 发明专利

CA2795637C HIGH-POSITIONED 3-POSITION VARIABLE CAMBER KRUEGER 未知
公开(公告)号：CA2795637C
公开(公告)日：2016-01-05
申请号：CA2795637
申请日：2012-11-14
申请人： BOEING CO
发明人： SAKURAI SEIYA , FOX STEPHEN J , REYES VICTOR , CHARLES KARA MARIE
IPC分类号： B64C3/44 , B64C3/50 , B64C9/04 , B64C13/24
摘要： A fluid-dynamic apparatus includes an airfoil, a flap assembly, and a link assembly including: a first drive arm; an actuator operable to rotate the first drive arm; a first drive link coupled to the first drive arm and to the trailing end portion of the flap assembly; a second drive arm rotatably coupled to the first drive arm such that the second drive arm rotates relative to the first drive arm in association with the rotation of the first drive arm; a drive transfer arm coupled to the airfoil; and a second drive link rotatably coupled to the second drive arm, to the drive transfer arm, and to the bullnose portion of the flap assembly.

10. 发明专利

BR102013003091A2 Curvatura de krueger variável em três posições em posição elevada 未知
公开(公告)号：BR102013003091A2
公开(公告)日：2015-06-16
申请号：BR102013003091
申请日：2013-02-07
申请人： BOEING CO
发明人： SAKURAI SEIYA , FOX STEPHEN J , REYES VICTOR , CHARLES KARA MARIE
IPC分类号： B64C13/30 , B64C3/50 , B64D45/00
摘要： Curvatura de krueger variável em três posições em posição elevada. A presente invenção refere-se a um sistema e um método para permitir o fluxo laminar natural ao longo de um corpo de fluido dinâmico utilizando uma aba da curvatura de krueger variável (306) são descritos. Uma sequência de posições da aba é implantada onde a aba da curvatura de krueger variável (306) está abaixo e atrás do bordo de ataque da asa (402, 540) antes de chegar a uma posição configurada de pouso e decolagem (554, 702). A aba da curvatura de krueger variável (306) é posicionada em uma posição elevada em relação a um bordo de ataque da asa (402, 540) quando a aba da curvatura de krueger variável (306) está totalmente implantada.

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