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    Method of laminar flow control using a door assembly
    51.
    发明授权
    Method of laminar flow control using a door assembly 有权
    使用门组件进行层流控制的方法

    公开(公告)号：US08484894B2

    公开(公告)日：2013-07-16

    申请号：US13551474

    申请日：2012-07-17

    申请人： Seiya Sakurai ,  Matthew D. Fevergeon

    发明人： Seiya Sakurai ,  Matthew D. Fevergeon

    IPC分类号： E05D15/50

    CPC分类号： B64C21/02 ,  B64C21/08 ,  B64C2230/20 ,  B64C2230/22 ,  B64D2241/00 ,  Y02T50/166

    摘要： A method of operating a door assembly may include pivoting a first door about a first pivot axis from a closed position to an open position such that the first door acts as an inlet. The method may further include pivoting the first door to the closed position, and pivoting a second door about a second pivot axis from a closed position to an open position when the first door is in the closed position such that the second door acts as an outlet facing in a direction opposite the first door. The method may additionally include pivoting the second pivot axis about the first pivot axis when pivoting the second door, the second door being of a smaller size than the first door and forming at least a portion of the first door.

    摘要翻译： 操作门组件的方法可以包括将第一门围绕第一枢转轴线从关闭位置枢转到打开位置，使得第一门用作入口。 该方法还可以包括将第一门枢转到关闭位置，并且当第一门处于关闭位置时使第二门围绕第二枢转轴线从关闭位置枢转到打开位置，使得第二门作为出口 面向与第一扇门相对的方向。 该方法可以另外包括在枢转第二门时枢转第二枢轴围绕第一枢转轴线，第二门的尺寸比第一门小，并形成第一门的至少一部分。

    METHOD OF LAMINAR FLOW CONTROL USING A DOOR ASSEMBLY
    52.
    发明申请
    METHOD OF LAMINAR FLOW CONTROL USING A DOOR ASSEMBLY 有权
    使用门组件的层流流量控制方法

    公开(公告)号：US20120280088A1

    公开(公告)日：2012-11-08

    申请号：US13551474

    申请日：2012-07-17

    申请人： Seiya Sakurai ,  Matthew D. Fevergeon

    发明人： Seiya Sakurai ,  Matthew D. Fevergeon

    IPC分类号： B64C21/08 ,  E06B3/50

    CPC分类号： B64C21/02 ,  B64C21/08 ,  B64C2230/20 ,  B64C2230/22 ,  B64D2241/00 ,  Y02T50/166

    摘要： A method of operating a door assembly may include pivoting a first door about a first pivot axis from a closed position to an open position such that the first door acts as an inlet. The method may further include pivoting the first door to the closed position, and pivoting a second door about a second pivot axis from a closed position to an open position when the first door is in the closed position such that the second door acts as an outlet facing in a direction opposite the first door. The method may additionally include pivoting the second pivot axis about the first pivot axis when pivoting the second door, the second door being of a smaller size than the first door and forming at least a portion of the first door.

    摘要翻译： 操作门组件的方法可以包括将第一门围绕第一枢转轴线从关闭位置枢转到打开位置，使得第一门用作入口。 该方法还可以包括将第一门枢转到关闭位置，并且当第一门处于关闭位置时使第二门围绕第二枢转轴线从关闭位置枢转到打开位置，使得第二门作为出口 面向与第一扇门相对的方向。 该方法可以另外包括在枢转第二门时枢转第二枢轴围绕第一枢转轴线，第二门的尺寸比第一门小，并形成第一门的至少一部分。

    Flap malfunction detection system
    53.
    发明授权
    Flap malfunction detection system 有权
    襟翼故障检测系统

    公开(公告)号：US08156887B2

    公开(公告)日：2012-04-17

    申请号：US12291194

    申请日：2008-11-07

    申请人： Kee How Tan ,  Seiya Sakurai ,  Gary D. Oakes ,  Philip Belanger ,  Jack S. Noble

    发明人： Kee How Tan ,  Seiya Sakurai ,  Gary D. Oakes ,  Philip Belanger ,  Jack S. Noble

    IPC分类号： B64C3/50

    CPC分类号： B64D45/0005 ,  B64D2045/001

    摘要： According to an embodiment, a flap malfunction indicator assembly for notifying an observer making a walk-around inspection of an aircraft of a malfunction of one or more connection points coupling a flap assembly to an aircraft wing includes a support mounted to the flap assembly having a perimeter defining an area, an indicator arm pivoted to the support and movable between a first stowed position in which a major portion of the arm is arranged substantially entirely within the area and a second deployed position in which a major portion of the arm is arranged substantially outside the area, a frangible pin or fastener securing the indicator arm to the support in the first stowed position, a trigger element mounted for rotation about a first pivot, an elongated pull linkage coupling the trigger element with a flap assembly, the pull linkage being supported for movement relative to the first pivot to cause rotation of the trigger element when malfunction of a flap assembly occurs, and a spring assembly at the support having one portion exerting a biasing force against a portion of the indicator arm located outside of the area, the spring assembly driving the indicator arm into the second deployed position when the frangible pin or fastener is broken.

    摘要翻译： 根据一个实施例，一种用于通知观察者对飞行器进行围绕检查以将翼片组件耦合到飞机机翼的一个或多个连接点的故障的通知的翼片故障指示器组件包括安装到翼片组件的支撑件，其具有 限定区域的周边，指示臂枢转到所述支撑件并且可在第一收起位置和第二展开位置之间移动，所述第一收起位置中所述臂的主要部分基本上完全设置在所述区域内;以及第二展开位置，其中所述臂的主要部分基本上布置 在所述区域外部，将所述指示器臂固定到所述第一收起位置中的所述支撑件的易碎销或紧固件，安装成围绕第一枢轴旋转的触发器元件，将所述触发器元件与翼片组件联接的细长拉动连杆， 支撑相对于第一枢轴的运动，以在出现翼片组件的故障时引起触发元件的旋转 在支撑件处的弹簧组件具有一部分对位于该区域外部的指示臂的一部分施加偏置力的弹簧组件，当易碎销或紧固件断裂时，弹簧组件将该指示臂驱动到第二展开位置。

    Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods
    54.
    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

    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。

    DOOR ASSEMBLY FOR LAMINAR FLOW CONTROL SYSTEM
    56.
    发明申请
    DOOR ASSEMBLY FOR LAMINAR FLOW CONTROL SYSTEM 有权
    层压流量控制系统门组件

    公开(公告)号：US20100181435A1

    公开(公告)日：2010-07-22

    申请号：US12356029

    申请日：2009-01-19

    申请人： Seiya Sakurai ,  Matthew D. Fevergeon

    发明人： Seiya Sakurai ,  Matthew D. Fevergeon

    IPC分类号： B64C21/06 ,  B64C1/14

    CPC分类号： B64C21/02 ,  B64C21/08 ,  B64C2230/20 ,  B64C2230/22 ,  B64D2241/00 ,  Y02T50/166

    摘要： A door assembly has a first door integrated with a second door. The first door has a first door cowl. The second door is pivotably mounted to the first door and has a second door cowl forming at least a portion of the first door cowl. The door assembly includes at least one actuator coupled to the first and second doors. Each one of the first and second doors is pivotable between open and closed positions and defines an opening when moved to the open position. The openings of the first and second doors face in opposite directions. The actuator is operative to pivotably move at least one of the first and second doors between the open and closed positions.

    摘要翻译： 门组件具有与第二门一体的第一门。 第一扇门有一个第一扇门。 第二门可枢转地安装到第一门，并且具有形成第一门罩的至少一部分的第二门罩。 门组件包括耦合到第一和第二门的至少一个致动器。 第一和第二门中的每一个可在打开位置和关闭位置之间枢转，并且当移动到打开位置时限定开口。 第一和第二门的开口面向相反的方向。 致动器可操作以在打开位置和关闭位置之间枢转地移动第一和第二门中的至少一个。

    Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods
    57.
    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

    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。