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公开(公告)号：US07243881B2
公开(公告)日：2007-07-17
申请号：US10860438
申请日：2004-06-03
申请人： Seiya Sakurai , Stephen J. Fox , Kevin W. Beyer , Douglas S. Lacy , Paul L. Johnson , Stephen L. Wells , Jack S. Noble , Paul T. Meredith , Neal V. Huynh , Russell R. Christianson , Paul M. Vijgen , Michael F. Fitzpatrick , Clayton A. Prow , Edward W. Gronenthal
发明人： Seiya Sakurai , Stephen J. Fox , Kevin W. Beyer , Douglas S. Lacy , Paul L. Johnson , Stephen L. Wells , Jack S. Noble , Paul T. Meredith , Neal V. Huynh , Russell R. Christianson , Paul M. Vijgen , Michael F. Fitzpatrick , Clayton A. Prow , Edward W. Gronenthal
IPC分类号： B64C9/22
摘要： Trailing edge devices configured to carry out multiple functions, and associated methods of use and manufacture are disclosed. An external fluid flow body (e.g., an airfoil) configured in accordance with an embodiment of the invention includes a first portion and a second portion, at least a part of the second portion being positioned aft of the first portion, with the second portion being movable relative to the first portion between a neutral position, a plurality of upward positions, and a plurality of downward positions. A guide structure can be coupled between the first and second portions, and an actuator can be operatively coupled between the first and second portions to move the second portion relative to the first portion. In one embodiment, a flexible surface can track the motion of the second portion and can expose a gap at some positions. In another embodiment, a controller can be coupled to the actuator and can be configured to direct the actuator to move the second portion to a high lift setting, a high drag setting, a roll setting, and a trim setting. In yet another embodiment, trailing edge devices on an airfoil can have scaled, mechanically similar guide structures.
摘要翻译： 被配置为执行多个功能的后端设备以及相关联的使用和制造方法被公开。 根据本发明的实施例配置的外部流体流动体（例如，翼型）包括第一部分和第二部分，第二部分的至少一部分位于第一部分的后部，第二部分是 相对于第一部分在中立位置，多个向上位置和多个向下位置之间移动。 引导结构可以联接在第一和第二部分之间，并且致动器可以可操作地联接在第一和第二部分之间，以相对于第一部分移动第二部分。 在一个实施例中，柔性表面可以跟踪第二部分的运动并且可以在某些位置暴露间隙。 在另一个实施例中，控制器可以联接到致动器，并且可以被配置为引导致动器将第二部分移动到高提升设置，高阻力设置，滚转设置和修剪设置。 在另一个实施例中，翼型件上的后缘装置可以具有缩放的机械上相似的导向结构。
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2.发明授权Method and apparatus for controlling airflow with a gapped trailing edge device having a flexible flow surface 有权用具有柔性流动面的有间隙后缘装置控制气流的方法和装置公开(公告)号：US07258308B2
公开(公告)日：2007-08-21
申请号：US10188988
申请日：2002-07-02
申请人： Kevin W. Beyer , Stephen J. Fox , Douglas S. Lacy , Paul T. Meredith , Clayton A. Prow , Seiya Sakurai , Stephen L. Wells
发明人： Kevin W. Beyer , Stephen J. Fox , Douglas S. Lacy , Paul T. Meredith , Clayton A. Prow , Seiya Sakurai , Stephen L. Wells
IPC分类号： B64C9/16
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.
摘要翻译： 一种用具有柔性流动面的有间隙后缘装置控制气流的方法和装置。 翼型件可以包括具有第一前缘，第一流动表面和与第一流动表面相对的第二流动表面的第一部分。 翼型件还可以包括具有第二前缘和后缘的第二部分，其中第二部分的至少一部分位于第一部分的后部。 第二部分可相对于第一位置和第二位置之间的第一部分移动，当第二部分处于第二位置时，第二前缘与第一部分的至少一部分分开一个气流间隙。 第二部分包括柔性流动表面，当第二部分处于第一位置时具有第一形状，并且当第二部分处于第二位置时具有与第一形状不同的第二形状。
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3.发明授权Aircraft trailing edge devices, including devices with non-parallel motion paths, and associated methods 有权飞机后缘装置，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。
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4.发明申请Aircraft Trailing Edge Devices, Including Devices With Non-Parallel Motion Paths, and Associated Methods 有权飞机后端设备，包括具有非并行运动路径的设备以及相关方法公开(公告)号：US20090146017A1
公开(公告)日：2009-06-11
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
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。
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5.发明授权Aircraft trailing edge devices, including devices with non-parallel motion paths, and associated methods 有权飞机后缘装置，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：US07475854B2
公开(公告)日：2009-01-13
申请号：US11284247
申请日：2005-11-21
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。
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6.发明授权Method and apparatus for controlling airflow with a leading edge device having a flexible flow surface 有权用于具有柔性流动表面的前缘装置控制气流的方法和装置公开(公告)号：US06796534B2
公开(公告)日：2004-09-28
申请号：US10238130
申请日：2002-09-10
申请人： Kevin W. Beyer , Stephen J. Fox , Douglas S. Lacy , Seiya Sakurai
发明人： Kevin W. Beyer , Stephen J. Fox , Douglas S. Lacy , Seiya Sakurai
IPC分类号： B64C350
CPC分类号： B64C3/48
摘要： Methods and apparatuses for controlling airflow with a leading edge device having a flexible flow surface. In one embodiment, the airfoil includes a first portion having a first flow surface and a second flow surface facing opposite from the first flow surface. The second portion of the airfoil has a leading edge and is movably coupled to the first position. The second portion can move between a first position and a second position offset from the first position by an angle of from about 45° to about 90° or more. The second portion includes a flexible flow surface having a first shape when the second portion is in the first position and a second shape different than the first shape when the second portion is in the second position. A guide structure can be coupled between the first portion and the second portion. In another embodiment, the airfoil can have inbound and outbound leading edge portions with an inbound guide structure having a first mechanical arrangement and an outbound guide structure having a second mechanical arrangement different than the first.
摘要翻译： 用于具有柔性流动表面的前缘装置控制气流的方法和装置。 在一个实施例中，翼型件包括具有第一流动表面的第一部分和与第一流动表面相对的第二流动表面。 翼型件的第二部分具有前缘并且可移动地联接到第一位置。 第二部分可以在从第一位置偏移约45°至约90°或更大的角度的第一位置和第二位置之间移动。 第二部分包括当第二部分处于第一位置时具有第一形状的柔性流动表面和当第二部分处于第二位置时与第一形状不同的第二形状。 引导结构可以联接在第一部分和第二部分之间。 在另一个实施例中，翼型件可以具有入口和出口的前缘部分，其具有具有第一机械装置的入站引导结构和具有不同于第一机构的第二机械装置的出站引导结构。
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7.发明申请Link Mechanisms, Including Stephenson II Link Mechanisms for Multi-Position Flaps and Associated Systems and Methods 有权链接机制，包括Stephenson II链接机制的多位置襟翼和相关系统和方法公开(公告)号：US20100140414A1
公开(公告)日：2010-06-10
申请号：US12331193
申请日：2008-12-09
申请人： Kevin W. Beyer , Seiya Sakurai
发明人： Kevin W. Beyer , Seiya Sakurai
摘要： Link mechanisms, including Stephenson II link mechanisms for multi-position flaps and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes an airfoil having an external flow surface with an upper portion and a lower portion, and with the airfoil forming a base link. The system further includes a six-bar linkage coupled to the airfoil and having a Stephenson II configuration, including a binary second link pivotably connected to the airfoil, a ternary third link pivotably connected to the second link, a binary fourth link pivotably connected to the third link, a ternary fifth link pivotably connected to the airfoil and the fourth link, and a binary sixth link pivotably connected to the third link and the fifth link. The system can further include a deployable leading edge panel carried by the linkage, with the leading edge panel being movable via the linkage between a stowed position and at least one deployed position.
摘要翻译： 公开了包括用于多位置襟翼的斯蒂芬森II链接机构和相关系统和方法的链接机构。 根据特定实施例的系统包括具有外部流动表面的机翼，其具有上部和下部，并且翼型形成基部连杆。 该系统还包括联接到翼型件并具有斯蒂芬森II构造的六杆连杆，其包括可枢转地连接到翼型件的二元第二连杆，可枢转地连接到第二连杆的三元第三连杆，可枢转地连接到第二连杆的二进制第四连杆 第三连杆，可枢转地连接到翼型件和第四连杆的三元第五连杆，以及可枢转地连接到第三连杆和第五连杆的二元第六连杆。 所述系统还可以包括由所述联动装置承载的可展开的前缘面板，所述前缘面板可通过所述连接件在收起位置与至少一个展开位置之间移动。
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8.发明授权Link mechanisms, including Stephenson II link mechanisms for multi-position flaps and associated systems and methods 有权链接机制，包括用于多位置襟翼的Stephenson II连杆机构及相关系统和方法公开(公告)号：US08226048B2
公开(公告)日：2012-07-24
申请号：US12331193
申请日：2008-12-09
申请人： Kevin W. Beyer , Seiya Sakurai
发明人： Kevin W. Beyer , Seiya Sakurai
IPC分类号： B64C3/50
摘要： Link mechanisms, including Stephenson II link mechanisms for multi-position flaps and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes an airfoil having an external flow surface with an upper portion and a lower portion, and with the airfoil forming a base link. The system further includes a six-bar linkage coupled to the airfoil and having a Stephenson II configuration, including a binary second link pivotably connected to the airfoil, a ternary third link pivotably connected to the second link, a binary fourth link pivotably connected to the third link, a ternary fifth link pivotably connected to the airfoil and the fourth link, and a binary sixth link pivotably connected to the third link and the fifth link. The system can further include a deployable leading edge panel carried by the linkage, with the leading edge panel being movable via the linkage between a stowed position and at least one deployed position.
摘要翻译： 公开了包括用于多位置襟翼的斯蒂芬森II链接机构和相关系统和方法的链接机构。 根据特定实施例的系统包括具有外部流动表面的机翼，其具有上部和下部，并且翼型形成基部连杆。 该系统还包括联接到翼型件并具有斯蒂芬森II构造的六杆连杆，其包括可枢转地连接到翼型件的二元第二连杆，可枢转地连接到第二连杆的三元第三连杆，可枢转地连接到第二连杆的二进制第四连杆 第三连杆，可枢转地连接到翼型件和第四连杆的三元第五连杆，以及可枢转地连接到第三连杆和第五连杆的二元第六连杆。 所述系统还可以包括由所述联动装置承载的可展开的前缘面板，所述前缘面板可通过所述连接件在收起位置与至少一个展开位置之间移动。
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9.发明授权公开(公告)号：US06299108B1
公开(公告)日：2001-10-09
申请号：US09209341
申请日：1998-12-11
IPC分类号： B64K914
CPC分类号： B64D45/0005 , B64C9/02 , B64C9/16 , B64C13/50 , B64D2045/001
摘要： An accurate and compact flap skew detection system that operates independent of the flap-drive system comprises, in a preferred embodiment, three major elements; a rotary position sensor located on fixed wing structure; a push-pull link and crank arm to convert translational flap motion into rotary sensed motion at the sensor; and a computer processing means to process the rotational sensed information and to compute a flap skew algorithm. Inter-flap and intra- flap translational motion is sensed and compared using a plurality of rotary sensors. Sensors falling outside of predetermined limits or violating control law rules indicate a non-synchronous or asymmetrical “skewed” condition.
摘要翻译： 在优选实施例中独立于翼片驱动系统操作的精确和紧凑的襟翼偏斜检测系统包括三个主要元件; 位于固定翼结构的旋转位置传感器; 一个推拉连杆和曲柄臂，用于将平移的襟翼运动转换成传感器的旋转感测运动; 以及计算机处理装置，用于处理旋转感测信息并计算襟翼偏斜算法。 使用多个旋转传感器检测和比较翼片间和翼内平移运动。 超出预定限制或违反控制规则规则的传感器表示非同步或不对称的“偏斜”状态。
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