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1.发明授权Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods 有权飞机后缘装置，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
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。
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2.发明授权Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods 有权飞机后缘装置，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
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。
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3.发明授权Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods 有权飞机后缘装置，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
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。
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4.发明申请Aircraft Trailing Edge Devices, Including Devices Having Forwardly Positioned Hinge Lines, and Associated Methods 有权飞机后端设备，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
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。
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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
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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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
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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7.发明申请AIRCRAFT TRAILING EDGE DEVICES, INCLUDING DEVICES HAVING FORWARDLY POSITIONED HINGE LINES, AND ASSOCIATED METHODS 有权飞机牵引装置，包括具有前进定位铰链的装置及相关方法公开(公告)号：US20100170998A1
公开(公告)日：2010-07-08
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： B64C3/50
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。
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公开(公告)号：US09688384B1
公开(公告)日：2017-06-27
申请号：US13623597
申请日：2012-09-20
申请人： Michael A. Balzer , Jan A. Kordel
发明人： Michael A. Balzer , Jan A. Kordel
摘要： Methods and apparatus to control a gap between movable aircraft wing components are disclosed. An example apparatus includes a body having a trailing edge and a leading edge. The leading edge is to be coupled to an aircraft wing. The trailing edge is to engage a flap of the aircraft wing. The body includes a structure located between the trailing edge and the leading edge. The structure is to engage the flap to maintain a distance between the body and the flap.
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公开(公告)号：US08870125B2
公开(公告)日：2014-10-28
申请号：US13187634
申请日：2011-07-21
摘要： A system for pneumatically actuating a split flap hingedly mounted near or at a trailing edge of an airfoil. The system includes a bladder system disposed between the split flap and the upper surface of the airfoil. The split flap is a small-chord (usually 1-3% of total wing chord) long-span lower panel which separates from the airfoil trailing edge by means of a hinge or a flexible lower skin. Deployment of the split flap is actuated pneumatically by the inflatable bladder system. The split flap may exist at a fixed wing trailing edge, a moving flap trailing edge, or an empennage trailing edge. The pneumatic bladder provides distributed force to extend and retract the split flap. This pneumatic approach eliminates extra drag, reduces cost and weight, and lessens flutter concerns.
摘要翻译： 一种用于气动地致动分开的翼片的系统，其铰接地安装在翼型件的后缘附近或其后缘。 该系统包括设置在分裂翼片和翼型件的上表面之间的气囊系统。 襟翼是一个小和弦（通常是总翼弦的1-3％）长跨度下面板，通过铰链或柔性下皮肤与翼型后缘分离。 通过可充气膀胱系统气动地驱动分裂瓣的部署。 分裂瓣可以存在于固定的翼缘后缘，移动的翼片后缘或尾翼的后缘。 气动气囊提供分布的力以延伸和缩回分裂瓣。 这种气动方式消除了额外的阻力，降低了成本和重量，并减轻了颤抖的担忧。
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公开(公告)号：US20130020444A1
公开(公告)日：2013-01-24
申请号：US13187634
申请日：2011-07-21
摘要： A system for pneumatically actuating a split flap hingedly mounted near or at a trailing edge of an airfoil. The system includes a bladder system disposed between the split flap and the upper surface of the airfoil. The split flap is a small-chord (usually 1-3% of total wing chord) long-span lower panel which separates from the airfoil trailing edge by means of a hinge or a flexible lower skin. Deployment of the split flap is actuated pneumatically by the inflatable bladder system. The split flap may exist at a fixed wing trailing edge, a moving flap trailing edge, or an empennage trailing edge. The pneumatic bladder provides distributed force to extend and retract the split flap. This pneumatic approach eliminates extra drag, reduces cost and weight, and lessens flutter concerns.
摘要翻译： 一种用于气动地致动分开的翼片的系统，其铰接地安装在翼型件的后缘附近或其后缘。 该系统包括设置在分裂翼片和翼型件的上表面之间的气囊系统。 襟翼是一个小和弦（通常是总翼弦的1-3％）长跨度下面板，通过铰链或柔性下皮肤与翼型后缘分离。 通过可充气膀胱系统气动地驱动分裂瓣的部署。 分裂瓣可以存在于固定的翼缘后缘，移动的翼片后缘或尾翼的后缘。 气动气囊提供分布的力以延伸和缩回分裂瓣。 这种气动方式消除了额外的阻力，降低了成本和重量，并减轻了颤抖的担忧。
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