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1. 发明申请

WO2007091990A8 AIRCRAFT WING COMPOSED OF COMPOSITE AND METAL PANELS 审中-公开
标题翻译：飞机组成的复合材料和金属面板
公开(公告)号：WO2007091990A8
公开(公告)日：2010-12-23
申请号：PCT/US2006001017
申请日：2006-01-11
申请人： BOEING CO , MUNSEN VICTOR A , MCGINTY DANIEL E , KORDEL JAN A , TANNER RICHARD B , RAMPTON SCOTT N , BURFORD IAN C , FOX BRUCE R , KELLY JAMES M , JOHNSON MILES O
发明人： MUNSEN VICTOR A , MCGINTY DANIEL E , KORDEL JAN A , TANNER RICHARD B , RAMPTON SCOTT N , BURFORD IAN C , FOX BRUCE R , KELLY JAMES M , JOHNSON MILES O
IPC分类号： B64C3/00
CPC分类号： B64C3/00
摘要： Aircraft wing assemblies having both composite and metal panels are disclosed. In one embodiment, a wing assembly includes a support structure, an upper panel assembly formed from a metal material and coupled to the support structure, and a lower panel assembly formed from a composite material and coupled to the support structure. The metal material may be aluminum, titanium, or any other suitable metal, and the composite material may be a carbon fiber reinforced plastic (CFRP) material or other suitable composite material. In another embodiment, the upper panel assembly includes a downwardly depending first web portion, and the lower panel assembly includes an upwardly depending second web portion, the second web portion being proximate the first web portion, and an interface member of an isolating material is disposed between the first and second web portions.
摘要翻译：公开了具有复合材料和金属板的飞机机翼组件。在一个实施例中，翼组件包括支撑结构，由金属材料形成并联接到支撑结构的上面板组件，以及由复合材料形成并联接到支撑结构的下部面板组件。金属材料可以是铝，钛或任何其它合适的金属，并且复合材料可以是碳纤维增强塑料（CFRP）材料或其它合适的复合材料。在另一个实施例中，上面板组件包括向下悬垂的第一腹板部分，并且下面板组件包括向上悬垂的第二腹板部分，第二腹板部分靠近第一腹板部分，并且设置隔离材料的接口构件在第一和第二纤维网部分之间。

2. 发明申请

WO2007062005A1 AIRCRAFT TRAILING EDGE DEVICES, INCLUDING DEVICES WITH NON-PARALLEL MOTION PATHS, AND ASSOCIATED METHODS 审中-公开
标题翻译：飞机牵引装置，包括具有非平行运动装置的装置及相关方法
公开(公告)号：WO2007062005A1
公开(公告)日：2007-05-31
申请号：PCT/US2006/045001
申请日：2006-11-20
申请人： THE BOEING COMPANY , LACY, Douglas, S. , BEYER, Kevin, W. , BROWN, Stephen, T. , DEES, Paul, W. , HUYNH, Neal, V. , KORDEL, Jan, A. , PROW, Clayton, A. , SAKURAI, Seiya
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.
摘要翻译：公开了包括具有非平行运动路径（241,242,243）的装置和相关方法的飞机后缘装置（230）。根据一个实施例的装置包括机翼（220）和联接到机翼的内侧后缘（231）装置，并且可沿着第一运动路径（241）相对于机翼在第一收起位置和第一展开位置之间移动，。外侧后缘（232）装置可以联接到内侧后缘装置的翼外侧，并且可以沿着不平行于第一运动路径的第二运动路径（242）相对于机翼移动。中间后缘装置（260）可以联接在内侧和外侧后缘装置之间，并且可以沿着不平行于第一和第二运动路径的第三运动路径（243）移动。每个后缘装置可以在移动到它们各自的展开位置时相对于机翼打开间隙。

3. 发明申请

WO2007091990A3 AIRCRAFT WING COMPOSED OF COMPOSITE AND METAL PANELS 审中-公开
标题翻译：飞机组成的复合材料和金属面板
公开(公告)号：WO2007091990A3
公开(公告)日：2007-10-04
申请号：PCT/US2006001017
申请日：2006-01-11
申请人： BOEING CO , MUNSEN VICTOR A , MCGINTY DANIEL E , KORDEL JAN A , TANNER RICHARD B , RAMTON SCOTT N , BURFORD IAN C , FOX BRUCE R , KELLY JAMES M , JOHNSON MILES O
发明人： MUNSEN VICTOR A , MCGINTY DANIEL E , KORDEL JAN A , TANNER RICHARD B , RAMTON SCOTT N , BURFORD IAN C , FOX BRUCE R , KELLY JAMES M , JOHNSON MILES O
IPC分类号： B64C3/00
CPC分类号： B64C3/00
摘要： Aircraft wing assemblies having both composite and metal panels are disclosed. In one embodiment, a wing assembly includes a support structure, an upper panel assembly formed from a metal material and coupled to the support structure, and a lower panel assembly formed from a composite material and coupled to the support structure. The metal material may be aluminum, titanium, or any other suitable metal, and the composite material may be a carbon fiber reinforced plastic (CFRP) material or other suitable composite material. In another embodiment, the upper panel assembly includes a downwardly depending first web portion, and the lower panel assembly includes an upwardly depending second web portion, the second web portion being proximate the first web portion, and an interface member of an isolating material is disposed between the first and second web portions.
摘要翻译：公开了具有复合材料和金属板的飞机机翼组件。在一个实施例中，翼组件包括支撑结构，由金属材料形成并联接到支撑结构的上面板组件，以及由复合材料形成并联接到支撑结构的下部面板组件。金属材料可以是铝，钛或任何其它合适的金属，并且复合材料可以是碳纤维增强塑料（CFRP）材料或其它合适的复合材料。在另一个实施例中，上面板组件包括向下悬垂的第一腹板部分，并且下面板组件包括向上悬垂的第二腹板部分，第二腹板部分靠近第一腹板部分，并且设置隔离材料的接口构件在第一和第二纤维网部分之间。

4. 发明申请

WO2007091990A2 AIRCRAFT WING COMPOSED OF COMPOSITE AND METAL PANELS 审中-公开
标题翻译：由复合材料和金属板组成的飞机翼
公开(公告)号：WO2007091990A2
公开(公告)日：2007-08-16
申请号：PCT/US2006/001017
申请日：2006-01-11
申请人： THE BOEING COMPANY , MUNSEN, Victor, A. , MCGINTY, Daniel, E. , KORDEL, Jan, A. , TANNER, Richard, B. , RAMTON, Scott, N. , BURFORD, Ian, C. , FOX, Bruce, R. , KELLY, James, M. , JOHNSON, Miles, O.
发明人： MUNSEN, Victor, A. , MCGINTY, Daniel, E. , KORDEL, Jan, A. , TANNER, Richard, B. , RAMTON, Scott, N. , BURFORD, Ian, C. , FOX, Bruce, R. , KELLY, James, M. , JOHNSON, Miles, O.
IPC分类号： B64C3/00
CPC分类号： B64C3/00
摘要： Aircraft wing assemblies having both composite and metal panels are disclosed. In one embodiment, a wing assembly includes a support structure, an upper panel assembly formed from a metal material and coupled to the support structure, and a lower panel assembly formed from a composite material and coupled to the support structure. The metal material may be aluminum, titanium, or any other suitable metal, and the composite material may be a carbon fiber reinforced plastic (CFRP) material or other suitable composite material. In another embodiment, the upper panel assembly includes a downwardly depending first web portion, and the lower panel assembly includes an upwardly depending second web portion, the second web portion being proximate the first web portion, and an interface member of an isolating material is disposed between the first and second web portions.
摘要翻译：公开了具有复合面板和金属面板的飞机机翼组件。在一个实施例中，机翼组件包括支撑结构，由金属材料形成并耦合到支撑结构的上面板组件，以及由复合材料形成并耦合到支撑结构的下面板组件。金属材料可以是铝，钛或任何其他合适的金属，并且复合材料可以是碳纤维增强塑料（CFRP）材料或其他合适的复合材料。在另一个实施例中，上面板组件包括向下悬垂的第一腹板部分，并且下面板组件包括向上悬垂的第二腹板部分，第二腹板部分靠近第一腹板部分，并且设置隔离材料的界面构件在第一和第二幅部分之间。

5. 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。

6. 发明申请

WO2009075963A2 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：WO2009075963A2
公开(公告)日：2009-06-18
申请号：PCT/US2008/082146
申请日：2008-10-31
申请人： THE BOEING COMPANY , 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
CPC分类号： B64C9/02 , B64C9/16 , Y02T50/32 , Y02T50/44
摘要： Trailing edge device catchers and associated systems and methods are disclosed. A system in accordance with one embodiment includes a wing having a wing support, a trailing edge device carried by and movable relative to the wing and having a device support, and a coupling connected between the wing and the trailing edge device. The coupling can include a pivot joint that includes a pivot element aligned along a pivot axis and connected between the wing support and the device support. The coupling can further include an actuator 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 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 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：公开了追尾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机翼支撑件的机翼，后缘装置，其相对于机翼承载并可移动并具有装置支撑件，以及连接在机翼和后缘装置之间的联轴器。联接器可以包括枢转接头，其包括枢转元件，枢转元件沿着枢转轴线对准并且连接在机翼支撑件和设备支撑件之间。联接器还可以包括联接在翼和后缘装置之间的致动器，其中致动器具有第一位置，在该第一位置中后缘装置被收起，以及第二位置，其中后缘装置被展开，其中空气流当后缘装置处于第二位置时，位于翼和后缘装置之间的间隙。凸轮轨道由机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。凸轮由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内。凸轮偏离枢转轴线，并且在正常操作期间，凸轮可以沿着包括凸轮轨道的负载路径承载负载或第一负载，并且当至少一个枢轴元件，翼片支撑和设备支撑发生，凸轮可以承载大于沿着负载路径的第一负载的第二非零负载。

7. 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。

8. 发明申请

WO2013081697A3 JAM PROTECTION AND ALLEVIATION FOR CONTROL SURFACE LINKAGE MECHANISMS 审中-公开
标题翻译： JAM保护和控制表面链接机制
公开(公告)号：WO2013081697A3
公开(公告)日：2014-11-27
申请号：PCT/US2012052624
申请日：2012-08-28
申请人： BOEING CO , MACLEAN ROBERT DOUGLAS , KORDEL JAN A , STEYAERT WARREN H , BOES DAVID DOUGLAS
发明人： MACLEAN ROBERT DOUGLAS , KORDEL JAN A , STEYAERT WARREN H , BOES DAVID DOUGLAS
IPC分类号： B64C9/02 , B64C9/16
CPC分类号： B64C13/32 , B64C9/02 , B64C9/16 , Y10T29/49826
摘要： A flaperon mechanism that provides jam protection while preventing the component departing from the airplane or causing unacceptable collateral damage. The jam protection feature comprises a controlled failure (fused) mechanism that is associated with the flaperon and flaperon hinge panel and maintains functional movement of the devices. Additional features can be added to the mechanism to block, shield, allow runout and shed other obstruction avenues.
摘要翻译：襟翼机构，能够防止组件离开飞机或造成不可接受的附带损坏，从而提供果酱保护。阻塞保护功能包括与襟人和襟翼铰链板相关联的受控故障（熔断）机构，并保持设备的功能运动。可以添加其他功能来阻止，屏蔽，允许跳动和流失其他障碍途径的机制。

9. 发明申请

WO2013081697A2 JAM PROTECTION AND ALLEVIATION FOR CONTROL SURFACE LINKAGE MECHANISMS 审中-公开
标题翻译： JAM保护和控制表面链接机制
公开(公告)号：WO2013081697A2
公开(公告)日：2013-06-06
申请号：PCT/US2012/052624
申请日：2012-08-28
申请人： THE BOEING COMPANY , MACLEAN, Robert Douglas , KORDEL, Jan A. , STEYAERT, Warren H. , BOES, David Douglas
发明人： MACLEAN, Robert Douglas , KORDEL, Jan A. , STEYAERT, Warren H. , BOES, David Douglas
IPC分类号： B64C13/32
CPC分类号： B64C13/32 , B64C9/02 , B64C9/16 , Y10T29/49826
摘要： A flaperon mechanism that provides jam protection while preventing the component departing from the airplane or causing unacceptable collateral damage. The jam protection feature comprises a controlled failure (fused) mechanism that is associated with the flaperon and flaperon hinge panel and maintains functional movement of the devices. Additional features can be added to the mechanism to block, shield, allow runout and shed other obstruction avenues.
摘要翻译：襟副翼机构，在防止组件离开飞机或造成不可接受的附带损坏的同时提供果酱保护。阻塞保护功能包括与襟人和襟副翼铰链板相关联的受控故障（熔断）机构，并保持设备的功能运动。可以添加其他功能来阻止，屏蔽，允许跳动和流失其他障碍途径的机制。

10. 发明申请

WO2008054360A3 SEAL ASSEMBLIES FOR USE WITH DROOPED SPOILERS AND OTHER CONTROL SURFACES ON AIRCRAFT 审中-公开
公开(公告)号：WO2008054360A3
公开(公告)日：2008-05-08
申请号：PCT/US2006/033812
申请日：2006-08-29
申请人： THE BOEING COMPANY , 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.
IPC分类号： B64C9/02 , B64C7/00
摘要： Aerodynamic seals (140) for use with control surfaces (114a) on aircraft (100) are described herein. In one embodiment, a seal assembly for use with an aircraft includes a first seal member (342) and a second seal member (352). The first seal member has a first proximal portion (344) configured to be attached to a fixed airfoil portion (108) of the aircraft, and a first distal portion (346) configured to extend outwardly from the fixed airfoil portion toward a movable control surface. The second seal member has a second proximal portion (356) 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.

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