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1. 发明授权

US09108715B2 Rotary actuated high lift gapped aileron 有权
标题翻译：旋转启动高升空盖副翼
公开(公告)号：US09108715B2
公开(公告)日：2015-08-18
申请号：US13482537
申请日：2012-05-29
申请人： Jan A. Kordel , Seiya Sakurai
发明人： Jan A. Kordel , Seiya Sakurai
IPC分类号： B64C3/50 , B64C1/10
CPC分类号： B64C1/10 , B64C9/16 , B64C9/18 , B64C2009/143
摘要： A rotary actuated high lift gapped aileron system and method are presented. A high lift gapped aileron couples to an airfoil at a hinge line and changes a camber of the airfoil. A rotary actuator coupled to the high lift gapped aileron produces a rotary motion of the high lift gapped aileron in response to an actuation command. A droop panel positioned over the hinge line enhances lift of the high lift gapped aileron. A cove lip door positioned under the hinge line provides an airflow over the high lift gapped aileron. A deployment linkage mechanism coupled to the high lift gapped aileron positions the droop panel and the cove lip door in response to the rotary motion.
摘要翻译：提出了一种旋转驱动的高电梯间隙副翼系统和方法。一个高升降机的副翼在铰链上与翼型相连，并改变了翼型的弯度。耦合到高电梯间隙副翼的旋转致动器响应于致动指令产生高升力带隙副翼的旋转运动。定位在铰链线上方的垂直面板增强了升降机间隙副翼的升力。位于铰链线下方的海湾唇门在高升高间隙副翼上提供气流。联接到高提升间隙副翼的展开联动机构响应于旋转运动而定位下垂面板和小湾唇门。

2. 发明授权

US08567726B2 Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods 有权
标题翻译：飞机后缘装置，包括具有向前定位的铰链线的装置以及相关联的方法
公开(公告)号：US08567726B2
公开(公告)日：2013-10-29
申请号：US13252011
申请日：2011-10-03
申请人： Douglas S. Lacy , Jan A. Kordel , John V. Dovey , Michael A. Balzer , Seiya Sakurai , Neal V. Huynh
发明人： Douglas S. Lacy , Jan A. Kordel , John V. Dovey , Michael A. Balzer , Seiya Sakurai , Neal V. Huynh
IPC分类号： B64C9/18
CPC分类号： B64C9/16 , B64C9/18 , Y02T50/32
摘要： Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods are disclosed. An aircraft system in accordance with one embodiment of the invention includes a wing and a trailing edge device coupled to the wing. The trailing edge device can be movable relative to the wing between a stowed position and a deployed position, with the trailing edge device having a leading edge, a trailing edge, an upper surface, and a lower surface. The upper surface can have an intersection point with the wing when the trailing edge device is in the stowed position. The motion of the trailing edge device relative to the wing can include rotational motion about a hinge line positioned forward of the intersection point, and a gap can be positioned between the trailing edge of the wing and the leading edge of the trailing edge device when the trailing edge device is in the deployed position.
摘要翻译：公开了包括具有向前定位的铰链线的装置的飞机后缘装置和相关方法。根据本发明的一个实施例的飞行器系统包括联接到机翼的翼和后缘装置。后缘装置可以在收起位置和展开位置之间相对于翼移动，后缘装置具有前缘，后缘，上表面和下表面。当后缘装置处于收起位置时，上表面可以与翼的交点。后缘装置相对于机翼的运动可以包括围绕位于交叉点前方的铰链线的旋转运动，并且当机翼的后缘和后缘装置的前缘之间可以定位间隙时后缘装置处于展开位置。

3. 发明申请

US20120018588A1 Aircraft Trailing Edge Devices, Including Devices Having Forwardly Positioned Hinge Lines, and Associated Methods 有权
标题翻译：飞机后端设备，包括具有向前定位的铰链线的设备以及相关方法
公开(公告)号：US20120018588A1
公开(公告)日：2012-01-26
申请号：US13252011
申请日：2011-10-03
申请人： Douglas S. Lacy , Jan A. Kordel , John V. Dovey , Michael A. Balzer , Seiya Sakurai , Neal V. Huynh
发明人： Douglas S. Lacy , Jan A. Kordel , John V. Dovey , Michael A. Balzer , Seiya Sakurai , Neal V. Huynh
IPC分类号： B64C3/50 , G05D1/08
CPC分类号： B64C9/16 , B64C9/18 , Y02T50/32
摘要： Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods are disclosed. An aircraft system in accordance with one embodiment of the invention includes a wing and a trailing edge device coupled to the wing. The trailing edge device can be movable relative to the wing between a stowed position and a deployed position, with the trailing edge device having a leading edge, a trailing edge, an upper surface, and a lower surface. The upper surface can have an intersection point with the wing when the trailing edge device is in the stowed position. The motion of the trailing edge device relative to the wing can include rotational motion about a hinge line positioned forward of the intersection point, and a gap can be positioned between the trailing edge of the wing and the leading edge of the trailing edge device when the trailing edge device is in the deployed position.
摘要翻译：公开了包括具有向前定位的铰链线的装置的飞机后缘装置和相关方法。根据本发明的一个实施例的飞行器系统包括联接到机翼的翼和后缘装置。后缘装置可以在收起位置和展开位置之间相对于翼移动，后缘装置具有前缘，后缘，上表面和下表面。当后缘装置处于收起位置时，上表面可以与翼的交点。后缘装置相对于机翼的运动可以包括围绕位于交叉点前方的铰链线的旋转运动，并且当机翼的后缘和后缘装置的前缘之间可以定位间隙时后缘装置处于展开位置。

4. 发明授权

US08038103B2 Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods 有权
标题翻译：飞机后缘装置，包括具有向前定位的铰链线的装置以及相关联的方法
公开(公告)号：US08038103B2
公开(公告)日：2011-10-18
申请号：US12497493
申请日：2009-07-02
申请人： Douglas S. Lacy , Jan A. Kordel , John V. Dovey , Michael A. Balzer , Seiya Sakurai , Neal V. Huynh
发明人： Douglas S. Lacy , Jan A. Kordel , John V. Dovey , Michael A. Balzer , Seiya Sakurai , Neal V. Huynh
IPC分类号： B64C9/18
CPC分类号： B64C9/16 , B64C9/18 , Y02T50/32
摘要： Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods are disclosed. An aircraft system in accordance with one embodiment of the invention includes a wing and a trailing edge device coupled to the wing. The trailing edge device can be movable relative to the wing between a stowed position and a deployed position, with the trailing edge device having a leading edge, a trailing edge, an upper surface, and a lower surface. The upper surface can have an intersection point with the wing when the trailing edge device is in the stowed position. The motion of the trailing edge device relative to the wing can include rotational motion about a hinge line positioned forward of the intersection point, and a gap can be positioned between the trailing edge of the wing and the leading edge of the trailing edge device when the trailing edge device is in the deployed position.
摘要翻译：公开了包括具有向前定位的铰链线的装置的飞机后缘装置和相关方法。根据本发明的一个实施例的飞行器系统包括联接到机翼的翼和后缘装置。后缘装置可以在收起位置和展开位置之间相对于翼移动，后缘装置具有前缘，后缘，上表面和下表面。当后缘装置处于收起位置时，上表面可以与翼的交点。后缘装置相对于机翼的运动可以包括围绕位于交叉点前方的铰链线的旋转运动，并且当机翼的后缘和后缘装置的前缘之间可以定位间隙后缘装置处于展开位置。

5. 发明授权

US07708231B2 Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods 有权
标题翻译：飞机后缘装置，包括具有向前定位的铰链线的装置以及相关联的方法
公开(公告)号：US07708231B2
公开(公告)日：2010-05-04
申请号：US11284113
申请日：2005-11-21
申请人： Douglas S. Lacy , Jan A. Kordel , John V. Dovey , Michael A. Balzer , Seiya Sakurai , Neal V. Huynh
发明人： Douglas S. Lacy , Jan A. Kordel , John V. Dovey , Michael A. Balzer , Seiya Sakurai , Neal V. Huynh
IPC分类号： B64C9/18
CPC分类号： B64C9/16 , B64C9/18 , Y02T50/32
摘要： Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods are disclosed. An aircraft system in accordance with one embodiment of the invention includes a wing and a trailing edge device coupled to the wing. The trailing edge device can be movable relative to the wing between a stowed position and a deployed position, with the trailing edge device having a leading edge, a trailing edge, an upper surface, and a lower surface. The upper surface can have an intersection point with the wing when the trailing edge device is in the stowed position. The motion of the trailing edge device relative to the wing can include rotational motion about a hinge line positioned forward of the intersection point, and a gap can be positioned between the trailing edge of the wing and the leading edge of the trailing edge device when the trailing edge device is in the deployed position.
摘要翻译：公开了包括具有向前定位的铰链线的装置的飞机后缘装置和相关方法。根据本发明的一个实施例的飞行器系统包括联接到机翼的翼和后缘装置。后缘装置可以在收起位置和展开位置之间相对于翼移动，后缘装置具有前缘，后缘，上表面和下表面。当后缘装置处于收起位置时，上表面可以与翼的交点。后缘装置相对于机翼的运动可以包括围绕位于交叉点前方的铰链线的旋转运动，并且当机翼的后缘和后缘装置的前缘之间可以定位间隙后缘装置处于展开位置。

6. 发明授权

US07744040B2 Aircraft trailing edge devices, including devices with non-parallel motion paths, and associated methods 有权
标题翻译：飞机后缘装置，包括具有非平行运动路径的装置，以及相关方法
公开(公告)号：US07744040B2
公开(公告)日：2010-06-29
申请号：US12264831
申请日：2008-11-04
申请人： Douglas S. Lacy , Kevin W. Beyer , Stephen T. Brown , Paul W. Dees , Neal V. Huynh , Jan A. Kordel , Clayton A. Prow , Seiya Sakurai
发明人： Douglas S. Lacy , Kevin W. Beyer , Stephen T. Brown , Paul W. Dees , Neal V. Huynh , Jan A. Kordel , Clayton A. Prow , Seiya Sakurai
IPC分类号： B64C3/50
CPC分类号： B64C9/16 , B64C2009/143
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.
摘要翻译：公开了包括具有非平行运动路径的装置和相关方法的飞行器后缘装置。根据一个实施例的装置包括机翼和内侧后缘装置，其联接到机翼并且可沿着第一运动路径在第一收起位置和第一展开位置之间相对于机翼移动。外侧后缘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相对于机翼移动。中间后缘装置可以联接在内侧和后侧后缘装置之间，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。

7. 发明授权

US07611099B2 Seal assemblies for use with drooped spoilers and other control surfaces on aircraft 有权
标题翻译：用于飞机上的下垂扰流板和其他控制面的密封组件
公开(公告)号：US07611099B2
公开(公告)日：2009-11-03
申请号：US11220446
申请日：2005-09-07
申请人： Jan A. Kordel , Seiya Sakurai , Bret A. Bowers , Christopher G. Glassmoyer , Darren B. Williams
发明人： Jan A. Kordel , Seiya Sakurai , Bret A. Bowers , Christopher G. Glassmoyer , Darren B. Williams
IPC分类号： B64C3/50
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

US20090146016A1 Trailing edge device catchers and associated systems and methods 有权
标题翻译：追尾设备捕获器及相关系统和方法
公开(公告)号：US20090146016A1
公开(公告)日：2009-06-11
申请号：US12001414
申请日：2007-12-11
申请人： Jan A. Kordel , Seiya Sakurai , Michael A. Balzer , John V. Dovey
发明人： Jan A. Kordel , Seiya Sakurai , Michael A. Balzer , John V. Dovey
IPC分类号： B64C3/50
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，该枢转元件沿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。

9. 发明申请

US20130320151A1 ROTARY ACTUATED HIGH LIFT GAPPED AILERON 有权
标题翻译：旋转启动高升降飞机
公开(公告)号：US20130320151A1
公开(公告)日：2013-12-05
申请号：US13482537
申请日：2012-05-29
申请人： Jan A. Kordel , Seiya Sakurai
发明人： Jan A. Kordel , Seiya Sakurai
IPC分类号： B64C3/50 , B64C13/26 , B64C9/00
CPC分类号： B64C1/10 , B64C9/16 , B64C9/18 , B64C2009/143
摘要： A rotary actuated high lift gapped aileron system and method are presented. A high lift gapped aileron couples to an airfoil at a hinge line and changes a camber of the airfoil. A rotary actuator coupled to the high lift gapped aileron produces a rotary motion of the high lift gapped aileron in response to an actuation command. A droop panel positioned over the hinge line enhances lift of the high lift gapped aileron. A cove lip door positioned under the hinge line provides an airflow over the high lift gapped aileron. A deployment linkage mechanism coupled to the high lift gapped aileron positions the droop panel and the cove lip door in response to the rotary motion.
摘要翻译：提出了一种旋转驱动的高电梯间隙副翼系统和方法。一个高升降机的副翼在铰链上与翼型相连，并改变翼型的弯度。耦合到高电梯间隙副翼的旋转致动器响应于致动指令产生高升力带隙副翼的旋转运动。定位在铰链线上方的垂直面板增强了升降机间隙副翼的升力。位于铰链线下方的海湾唇门在高升高间隙副翼上提供气流。联接到高提升间隙副翼的展开联动机构响应于旋转运动而定位下垂面板和小湾唇门。

10. 发明授权

US07766282B2 Trailing edge device catchers and associated systems and methods 有权
标题翻译：追尾设备捕获器及相关系统和方法
公开(公告)号：US07766282B2
公开(公告)日：2010-08-03
申请号：US12001414
申请日：2007-12-11
申请人： Jan A. Kordel , Seiya Sakurai , Michael A. Balzer , John V. Dovey
发明人： Jan A. Kordel , Seiya Sakurai , Michael A. Balzer , John V. Dovey
IPC分类号： B64C3/50
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，该枢转元件沿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。

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