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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. 发明申请

WO2008051286A2 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：WO2008051286A2
公开(公告)日：2008-05-02
申请号：PCT/US2007/008301
申请日：2007-04-02
申请人： THE BOEING COMPANY , 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 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.
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，其还包括具有大致固定形状的流动表面的可展开的前缘面板，联接到面板的大斗杆，以及连接到面板和牛仔的连杆机构在收起位置和展开位置之间移动面板。该机构可以包括第一支撑连杆，第二支撑连杆以及第一，第二和第三定位连杆。定位连杆可以在前缘面板，牛角，第一支撑连杆和第二支撑连杆之间可枢转地连接，使得当处于展开位置时，前缘面板与翼型件形成间隙。定位连杆可以是在特定的机翼跨度位置处联接在支撑连杆，前缘面板和长臂之间的唯一定位连杆。

3. 发明申请

WO2012009087A1 AIRCRAFT FLAP ACTUATOR ASSEMBLY 审中-公开
标题翻译：飞机飞行员执行器总成
公开(公告)号：WO2012009087A1
公开(公告)日：2012-01-19
申请号：PCT/US2011/040352
申请日：2011-06-14
申请人： THE BOEING COMPANY , SAKURAI, Seiya , WHEATON, James, M. , FOX, Stephen, J.
发明人： SAKURAI, Seiya , WHEATON, James, M. , FOX, Stephen, J.
IPC分类号： B64C9/16
CPC分类号： B64C9/16 , Y02T50/32
摘要： An aircraft flap actuator assembly (1) includes at least one fixed support (2), at least one track (40) having a curvilinear track surface (41) connected to the fixed support (2), at least one flap support (20, 24) adapted to traverse the curvilinear track surface, a trailing edge flap (36) connected to the at least one flap support (20, 24) and a flap actuator (28) engaging the at least one flap support (20, 24).
摘要翻译：一种飞机翼片致动器组件（1）包括至少一个固定支撑件（2），至少一个轨道（40），其具有连接到固定支撑件（2）的曲线轨道表面（41），至少一个翼片支撑件 24），其适于横越所述曲线轨道表面，连接到所述至少一个翼片支撑件（20,24）的后缘翼片（36）和接合所述至少一个翼片支撑件（20,24）的翼片致动器（28）。

4. 发明申请

WO2007056477A1 WING LEADING EDGE SLAT SYSTEM 审中-公开
公开(公告)号：WO2007056477A1
公开(公告)日：2007-05-18
申请号：PCT/US2006/043550
申请日：2006-11-07
申请人： THE BOEING COMPANY , JONES, Kelly, T. , FOX, Stephen, J. , AMOROSI, Stephen, R.
发明人： JONES, Kelly, T. , FOX, Stephen, J. , AMOROSI, Stephen, R.
IPC分类号： B64C9/24
CPC分类号： B64C9/22 , B64C13/34
摘要： A mechanism for extending and supporting a high-lift device (14) relative to an airfoil (10) has a pair of support ribs (26) coupled to the airfoil (10). A carrier track (28) is pivotally coupled to the high-lift device (14) and positioned between the pair of support ribs (26). The carrier track (28) has a slot opening along a lower length thereof. A gear rack (36) is coupled within the slot opening. A pinion gear (40) is positioned between the support ribs (26) and below the carrier track (28). The pinion gear (40) engages with the gear rack (36) for extending the high-lift device (14) relative to the airfoil (10). A plurality of rollers (30) is rotateably coupled to the support ribs (26) and in bearing contact with the carrier track (28). At least one roller (30) is positioned above the carrier track (28) and a second roller (30) is positioned below the carrier track (28). The second roller (30) is positioned concentrically with the pinion gear (40).
摘要翻译：用于相对于翼型件（10）延伸和支撑高升力装置（14）的机构具有联接到翼型件（10）的一对支撑肋（26）。承载轨道（28）枢转地联接到高升降装置（14）并且定位在所述一对支撑肋（26）之间。载体轨道（28）具有沿其较低长度的狭槽开口。齿条（36）联接在槽口内。小齿轮（40）位于支撑肋（26）之间并且位于载体轨道（28）的下方。小齿轮（40）与齿条（36）接合，用于相对于翼型件（10）延伸高升力装置（14）。多个辊（30）可旋转地联接到支撑肋（26）并且与承载轨道（28）的轴承接触。至少一个辊（30）位于载体轨道（28）上方，并且第二辊（30）位于载体轨道（28）的下方。第二辊（30）与小齿轮（40）同心地定位。

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