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    BODY TAB YAW DEFLECTOR
    3.
    发明申请
    BODY TAB YAW DEFLECTOR 审中-公开

    公开(公告)号：US20170341730A1

    公开(公告)日：2017-11-30

    申请号：US15479654

    申请日：2017-04-05

    申请人： Lockheed Martin Corporation

    发明人： Kenneth Merle Dorsett

    IPC分类号： B64C9/02 ,  B64C9/34 ,  B64C3/10

    CPC分类号： B64C9/02 ,  B64C3/10 ,  B64C5/06 ,  B64C5/08 ,  B64C5/10 ,  B64C9/12 ,  B64C9/323 ,  B64C9/326 ,  B64C9/34 ,  Y02T50/32 ,  Y02T50/44

    摘要： In one embodiment, an apparatus includes a first deflector configured to couple to a shaft of an aircraft. The first deflector may form part of a top surface of the aircraft when in a first closed position. The apparatus may further include a second deflector configured to couple to the shaft and form part of a bottom surface of the aircraft when in a second closed position. The first deflector and the second deflector may be configured to be positioned at a junction of a body of the aircraft and a wing of the aircraft. The first deflector and the second deflector may be configured to simultaneously pivot from the closed positions to respective first and second open positions upon actuation of the shaft.

    HYDRAULIC ACTUATOR
    5.
    发明申请
    HYDRAULIC ACTUATOR 有权
    液压执行器

    公开(公告)号：US20160096617A1

    公开(公告)日：2016-04-07

    申请号：US14872406

    申请日：2015-10-01

    申请人： NABTESCO CORPORATION

    发明人： Koji ITO

    IPC分类号： B64C13/40 ,  F15B15/20 ,  F15B15/16

    CPC分类号： B64C13/40 ,  B64C9/323 ,  F15B11/123 ,  F15B15/16 ,  F15B15/204 ,  F15B15/24

    摘要： A hydraulic actuator is adapted to drive a spoiler of a wing having a flap. When the hydraulic actuator drives the spoiler in an overlapping region where a driving range of the flap and a driving range of the spoiler overlap, an output suppressing structure suppress a drive output of the hydraulic actuator in the overlapping region to be less than that in a non-overlapping region other than the overlapping region.

    摘要翻译： 液压致动器适于驱动具有翼片的机翼的扰流板。 当液压致动器在翼片的驱动范围和扰流板的驱动范围重叠的重叠区域中驱动扰流板时，输出抑制结构抑制重叠区域中的液压致动器的驱动输出小于 重叠区域以外的非重叠区域。

    Control surface assembly
    6.
    发明授权
    Control surface assembly 有权
    控制面组装

    公开(公告)号：US09038964B2

    公开(公告)日：2015-05-26

    申请号：US13513219

    申请日：2010-12-06

    申请人： Eric Wildman

    发明人： Eric Wildman

    IPC分类号： B64C3/50 ,  B64C13/28 ,  B64C9/20 ,  B64C9/32 ,  B64C9/14

    CPC分类号： B64C13/28 ,  B64C9/20 ,  B64C9/323 ,  B64C2009/143 ,  Y10T29/49815

    摘要： An aerodynamic control surface assembly comprising: an aerodynamic control surface (4); an actuator (10) for controlling deployment of the control surface; and a locking mechanism (30) moveable from a locked to an unlocked position. When the locking mechanism is set to the locked position, the actuator is operatively coupled to the control surface and the control surface can move in dependently of the actuator when the locking mechanism is set to the unlocked position. Such an assembly may be used in an aircraft to prevent clashing between a deployed flap (16) and a drooped spoiler (4) in the event of an actuator control systems failure.

    摘要翻译： 一种空气动力学控制表面组件，包括：空气动力学控制表面（4）; 用于控制所述控制表面的展开的致动器（10）; 以及可从锁定位置移动到解锁位置的锁定机构（30）。 当锁定机构设置在锁定位置时，致动器可操作地联接到控制表面，并且当锁定机构被设置到解锁位置时，控制表面可以依靠致动器移动。 在发动机控制系统故障的情况下，这种组件可用于飞行器中以防止展开的挡板（16）和下垂的扰流器（4）之间的冲突。

    Deployable aerodynamic devices with reduced actuator loads, and related systems and methods
    8.
    发明授权
    Deployable aerodynamic devices with reduced actuator loads, and related systems and methods 有权
    减少执行器负载的可部署空气动力装置，以及相关系统和方法

    公开(公告)号：US07954769B2

    公开(公告)日：2011-06-07

    申请号：US11953672

    申请日：2007-12-10

    申请人： Glenn S. Bushnell

    发明人： Glenn S. Bushnell

    IPC分类号： B64C3/58 ,  B64C9/00

    CPC分类号： B64C9/10 ,  B64C9/02 ,  B64C9/32 ,  B64C9/323 ,  B64C9/34 ,  B64C13/38 ,  Y02T50/32 ,  Y02T50/44

    摘要： Deployable aerodynamic devices with reduced actuator loads, and related systems and methods are disclosed. An external flow system in accordance with a particular embodiment includes an external flow body, a deployable device carried by and movable relative to the external flow body, and a coupling connected between the external flow body and the deployable device. The system can further include an actuator device operatively coupled between the external flow body and the deployable device, with the actuator device positioned to move the deployable device along a motion path between a stowed position and the deployed position. The motion path can have a first portion over which the load delivered by the actuator device increases as the deployed device moves toward the deployed position, and a second portion over which the load delivered by the actuator device decreases as the deployed device moves toward the deployed position.

    摘要翻译： 公开了具有减少的致动器负载的可部署的空气动力学装置以及相关的系统和方法。 根据特定实施例的外部流动系统包括外部流动体，由外部流动体承载并可移动的可展开装置，以及连接在外部流动体和可部署装置之间的联接器。 该系统还可以包括可操作地联接在外部流动体和可展开装置之间的致动器装置，致动器装置被定位成沿着收起位置和展开位置之间的运动路径移动可展开装置。 运动路径可以具有第一部分，当被展开的装置朝向展开位置移动时，致动器装置输送的负载增加;以及第二部分，当被展开的装置朝向展开位置移动时，由致动装置输送的负载减小 位置。

    Flap device
    9.
    发明授权
    Flap device 失效
    襟翼装置

    公开(公告)号：US07891612B2

    公开(公告)日：2011-02-22

    申请号：US12117743

    申请日：2008-05-09

    申请人： Amirhossein Mahmoudi ,  Firouz Alizadeh Salimi

    发明人： Amirhossein Mahmoudi ,  Firouz Alizadeh Salimi

    IPC分类号： B64C3/50

    CPC分类号： B64C9/34 ,  B64C9/32 ,  B64C9/323 ,  B64C13/50

    摘要： A flap device adapted for location on or in a fluid interfacing surface such as an airfoil section, the device comprising a housing, a flap mounted for rotation at least partially within the housing, an entry in a leading portion of the housing, and at least one stop member associated with the housing and actuable between a non-operative parked position and an operative position in which in use the stop member is adapted to limit the movement of the flap within the housing thereby to vary the coefficient of lift and drag of the fluid interfacing surface or airfoil section.

    摘要翻译： 一种适于定位在诸如翼型部分的流体接口表面上或其中的翼片装置，所述翼片装置包括壳体，安装成用于至少部分地在所述壳体内旋转的翼片，所述壳体的引导部分中的入口，并且至少 一个止动构件，其与壳体相关联并且可在非操作的停放位置和操作位置之间致动，其中在使用中，止动构件适于限制翼片在壳体内的运动，从而改变该系统的升力和阻力系数 流体接口表面或翼型部分。

    AERODYNAMIC FAN CONTROL EFFECTOR
    10.
    发明申请
    AERODYNAMIC FAN CONTROL EFFECTOR 有权
    航空风扇控制效应器

    公开(公告)号：US20090230240A1

    公开(公告)日：2009-09-17

    申请号：US12047489

    申请日：2008-03-13

    申请人： Bradley A. Osborne ,  Scott L. Schwimley

    发明人： Bradley A. Osborne ,  Scott L. Schwimley

    IPC分类号： B64C9/00

    CPC分类号： B64C39/10 ,  B64C9/32 ,  B64C9/323 ,  B64C9/34 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44

    摘要： A fan control effector for an aircraft comprises at least one blade configured to be pivotably deployable in a radially outward direction from a retracted position to a deployed position such that the blade extends out of the aircraft. The fan control effector may be mounted in a symmetrical arrangement about a longitudinal axis on opposing wings of the aircraft. Furthermore, the fan control effector may comprise any number of blades for independent deployment outwardly from the wing. The blades are configured to be angularly deployable along a direction that is non-parallel to the longitudinal axis of the aircraft. The blades may be configured to be deployable sequentially from the wing starting with an initial deployment of an aft-most one of the blades.

    摘要翻译： 用于飞行器的风扇控制执行器包括至少一个叶片，其构造成可在径向向外的方向上从缩回位置枢转地展开到展开位置，使得叶片延伸出飞行器。 风扇控制效应器可以围绕飞机的相对翼上的纵向轴线对称地安装。 此外，风扇控制执行器可以包括用于从机翼向外独立部署的任何数量的叶片。 叶片构造成沿着不平行于飞行器的纵向轴线的方向成角度地展开。 叶片可以被构造成从机翼开始以最后一个叶片的初始部署顺序地展开。