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公开(公告)号：US09097327B2
公开(公告)日：2015-08-04
申请号：US14174661
申请日：2014-02-06
申请人： NABTESCO CORPORATION
发明人： Toshiaki Ogawa , Koji Itoh , Makoto Nagashima
摘要： An actuator-link assembly includes an actuator having first and second opposing ends in order to drive a control surface of an aircraft and a link coupled to the actuator. The actuator has a rod portion having a tip end, located at first end of the actuator, said tip end pivotably attach to a control surface of an aircraft. The link includes a pair of linear portions, each having first and second opposing ends, wherein the linear portions are disposed alongside each other; a coupling portion connecting the first ends of linear portions, a fulcrum shaft attachment portion protruding from the coupling portion configured to pivotably attach to a fulcrum shaft for rotatably supporting the control surface; and an actuator attachment portion configured to pivotably attach to the second end of the actuator. A material constituting the linear portions and the coupling portion contains fiber reinforced plastic.
摘要翻译： 致动器连杆组件包括具有第一和第二相对端的致动器，以驱动飞行器的控制表面和联接到致动器的连杆。 致动器具有杆部分，其具有位于致动器的第一端处的尖端，所述尖端可枢转地附接到飞行器的控制表面。 连杆包括一对直线部分，每一个具有第一和第二相对端部，其中直线部分彼此并排配置; 连接直线部分的第一端的联接部分，从联接部分突出的支点轴安装部分，其构造成可枢转地附接到支点轴，以可旋转地支撑控制表面; 以及构造成可枢转地附接到致动器的第二端的致动器附接部分。 构成直线部分和联接部分的材料包含纤维增强塑料。
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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
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。
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公开(公告)号：US20150136910A1
公开(公告)日：2015-05-21
申请号：US13989453
申请日：2013-03-28
申请人： Mohammed Azad Hussain , Anthony Machell , Paul Robinson , Henry Alexander Maples , Chamwit Tridech , Alexander Bismarck
发明人： Mohammed Azad Hussain , Anthony Machell , Paul Robinson , Henry Alexander Maples , Chamwit Tridech , Alexander Bismarck
摘要： A morphing skin for an air vehicle structure, the skin being formed by a composite material which includes: a multiplicity of fibres, a matrix incorporating the fibres, and a thermo-sensitive material, such as a thermo-plastic. The thermo-sensitive material can be reversibly transitionable in response to a change in temperature, between (i) an ambient temperature mode in which the thermo-sensitive material is capable of transferring loads in the composite material, and (ii) a heated mode in which the ability of the thermo-sensitive material to transfer the loads is reduced. This can allow the stiffness of the skin to be temporarily reduced to enable the skin to be morphed into a different shape.
摘要翻译： 用于空气车辆结构的变形皮肤，皮肤由复合材料形成，所述复合材料包括：多根纤维，包含纤维的基体，以及热敏材料，例如热塑性塑料。 热敏材料可以响应于温度变化而可逆地转换，（i）热敏材料能够传递复合材料中的载荷的环境温度模式，和（ii）加热模式 热敏材料传递负载的能力降低。 这可以使皮肤的刚度暂时降低，以使皮肤变形成不同的形状。
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94.发明授权Method for monitoring a no-back device of an adjustable horizontal trim actuator, corresponding system and aircraft 有权用于监视可调节水平微调执行器，对应系统和飞行器的无背装置的方法公开(公告)号：US08918291B2
公开(公告)日：2014-12-23
申请号：US12888965
申请日：2010-09-23
申请人： Cedric Tallot , Laura Baxerres , Ivan Ferreol
发明人： Cedric Tallot , Laura Baxerres , Ivan Ferreol
CPC分类号： B64D45/00 , B64C5/10 , B64C13/24 , B64C13/28 , B64D2045/0085 , F16H25/2021
摘要： A method and a system for monitoring an actuator equipped with a no-back device or no-back brake, particularly an adjustable horizontal trim actuator provided in aircraft, the method including the steps of: determining a value representative of mechanical work produced by the actuator and comparing the determined value with ranges of values so as to detect a dysfunctioning of the said no-back device. If the actuator is a screw/nut type with a hydraulic motor, the value representative of the mechanical work is determined from an algebraic velocity of the motor and an algebraic differential of hydraulic pressure at terminals of the motor. A negative value corresponding to negative mechanical work then identifies a failure of the no-back device.
摘要翻译： 一种用于监测装备有无背装置或无背制动器的致动器的方法和系统，特别是在飞行器中提供的可调节水平微调致动器，该方法包括以下步骤：确定代表由致动器产生的机械作用的值 以及将所确定的值与所述值的范围进行比较，以便检测所述无返回装置的功能障碍。 如果执行器是具有液压马达的螺杆/螺母型，则代表机械功的值由马达的代数速度和马达端子处的液压的代数差来决定。 对应于负机械功能的负值则识别无背装置的故障。
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公开(公告)号：US20140312175A1
公开(公告)日：2014-10-23
申请号：US13867562
申请日：2013-04-22
申请人： The Boeing Company
发明人： Seiya Sakurai , Stephen J. Fox , Victor H. Reyes
摘要： A variable camber Krueger flap deployment linkage mechanism is presented. A first linkage assembly couples a flap assembly and an airfoil, and comprising a first drive arm, a first drive link, and a support arm. A second linkage assembly couples the flap assembly and the first drive arm, and comprises a drive transfer arm, a middle connection segment, and a bullnose link.
摘要翻译： 提出了一种可变的弧度Krueger挡板部署联动机构。 第一连杆组件联接翼片组件和翼型件，并且包括第一驱动臂，第一驱动连杆和支撑臂。 第二连杆组件联接翼片组件和第一驱动臂，并且包括驱动传递臂，中间连接段和长臂连杆。
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公开(公告)号：US20140263828A1
公开(公告)日：2014-09-18
申请号：US14264453
申请日：2014-04-29
发明人： Jack BLANCHARD , Andreas YIASOUMI
CPC分类号： B64C13/28 , B64C9/22 , H01B7/065 , H02G11/006 , Y02T50/44
摘要： A telescopic strut for electrically connecting a fixed structure of an aircraft to a movable structure mounted to the fixed structure, wherein the strut is adapted to be mechanically connected to the fixed structure by its one end and to be mechanically connected to the movable structure by its opposite end, the strut comprising a plurality of telescopic elements and containing a helically coiled electrical cable, wherein the cable is adapted to move between retracted and extended positions with the telescoping of the strut. Also, a method of operating an aircraft having a movable structure mounted to a fixed structure, and one or more of the telescopic struts mechanically and electrically connected between the fixed and movable structures.
摘要翻译： 一种用于将飞行器的固定结构电连接到安装到固定结构的可移动结构的伸缩支柱，其中所述支柱适于通过其一端机械连接到所述固定结构，并且通过其固定结构与所述可移动结构机械连接 所述支柱包括多个伸缩元件并且包含螺旋状卷绕的电缆，其中所述电缆适于在所述支柱的伸缩状态下在缩回位置和延伸位置之间移动。 而且，一种操作具有安装到固定结构的可移动结构的飞行器的方法，以及机械地和电连接在固定结构和可移动结构之间的一个或多个伸缩支柱。
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97.发明申请ACTUATION SYSTEM FOR A LIFT ASSISTING DEVICE AND LINED TRACK ROLLERS USED THEREIN 有权用于升降机辅助装置的启动系统和用于其的内置轨道滚子公开(公告)号：US20140061381A1
公开(公告)日：2014-03-06
申请号：US13719541
申请日：2012-12-19
IPC分类号： B64C13/28
CPC分类号： B64C13/28 , B64C9/02 , B64C9/22 , F16C11/02 , F16C23/041 , F16C29/045 , F16C2326/43 , Y02T50/44
摘要： An actuation system for deploying and retracting a lift assisting device of a leading edge of a wing of an aircraft including a track pivotally coupled to the lift assisting device. The track has first and second outer surfaces and side surfaces. The actuation system includes a shaft rotationally coupled within the wing of the aircraft and operable, in response to flight control signals, to deploy or retract the lift assisting device. The actuation system includes an actuator for actuating the lift assisting device, coupled to the shaft, between a retracted position to a deployed position along an arcuate path. The actuation system includes a plurality of track roller bearings rotatably contacting the first and second outer surfaces of the track to guide the track along the arcuate path. The plurality of track roller bearings includes one or more lined track roller assembly.
摘要翻译： 一种用于展开和缩回飞行器机翼的前缘的升降机辅助装置的致动系统，包括枢转地联接到升降机辅助装置的轨道。 轨道具有第一和第二外表面和侧表面。 致动系统包括旋转地联接在飞行器的翼内的轴，并且响应于飞行控制信号而可操作以展开或缩回提升辅助装置。 所述致动系统包括致动器，所述致动器用于致动所述提升辅助装置，所述升降机构联接到所述轴，在沿着弓形路径的缩回位置到展开位置之间。 致动系统包括多个滚动滚子轴承，其可旋转地接触轨道的第一和第二外表面以沿着弧形路径引导轨道。 多个滚轮轴承包括一个或多个衬里的滚轮组件。
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98.发明申请AIRCRAFT FLAP MECHANISM HAVING COMPACT LARGE FOWLER MOTION PROVIDING MULTIPLE CRUISE POSITIONS 有权具有提供多个巡航位置的紧凑型大型运动的飞机翼片机构公开(公告)号：US20130075537A1
公开(公告)日：2013-03-28
申请号：US13242296
申请日：2011-09-23
摘要： A trailing edge flap mechanism incorporates a support beam, a flap carrier beam supporting an aerodynamic flap, a first link interconnecting a first and second rotation points and a second link interconnecting third and fourth rotation points. The support beam has a ground connection on a first fixed axis of rotation. A connecting link has a ground connection on a second fixed axis of rotation and is connected to the first link intermediate the first and second rotation points. An actuator is connected with a drive link pivotally engaged to the first link for initial forward and aft movement of a nose profile of the Fowler flap substantially parallel to the wing lower surface with extending aft movement providing a rapidly changing angle of the flap with respect to the wing upper surface.
摘要翻译： 后缘翼片机构包括支撑梁，支撑气动翼片的翼片承载梁，互连第一和第二旋转点的第一连杆和互连第三和第四旋转点的第二连杆。 支撑梁在第一固定旋转轴线上具有接地连接。 连接链路在第二固定旋转轴线上具有接地连接，并且在第一和第二旋转点之间连接到第一连杆。 致动器与驱动连杆连接，该驱动连杆枢转地接合到第一连杆，用于使Fowler翼片的鼻部轮廓基本上平行于机翼下表面的初始向前和向后运动，具有延伸的后部运动，从而提供相对于翼片的快速变化的角度 机翼上表面。
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公开(公告)号：US08256714B2
公开(公告)日：2012-09-04
申请号：US12074737
申请日：2008-03-06
申请人： Jie Zhao
发明人： Jie Zhao
摘要： A modularized airplane includes two separably interconnected modules. A first module, incorporating substantial airplane styles, includes a fuselage portion and at least one wing or stabilizer with an associated control surface. A second module carries a set of essential flight components sufficing airplane operations, including propulsion unit, servo for moving control surface, and power source. Magnetic connectors affixed on the modules facilitate inter-modular structural connection. A control linkage assembly, linking control surface on first module and associated servo on second module, is formed with two portions longitudinally movable and separably connected by two magnetic connectors oppositely affixed on each portion. The structural connection and the servo-to-control surface linkage assembly facilitate substantially effortless inter-modular connections to form a functional airplane, as well as nondestructive inter-modular disconnection. The second module can be connected to different aerodynamic styled first modules to form airplanes for different applications, using same essential components.
摘要翻译： 模块化飞机包括两个可分离互连的模块。 包含大量飞机类型的第一模块包括机身部分和至少一个具有相关控制表面的机翼或稳定器。 第二个模块携带一套足够飞机操作的基本飞行组件，包括推进单元，用于移动控制面的伺服和电源。 固定在模块上的磁性连接器便于模块间结构连接。 将第一模块上的控制表面与第二模块上的相关联的伺服连接的控制联动组件形成有两个纵向可移动的部分，并且通过相对地固定在每个部分上的两个磁性连接器可分离地连接。 结构连接和伺服到控制表面连接装置有助于实现基本上毫不费力的模块间连接以形成功能飞机，以及非破坏性的模块间断开。 第二个模块可以连接到不同的空气动力风格的第一个模块，以形成用于不同应用的飞机，使用相同的基本组件。
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公开(公告)号：US20120091283A1
公开(公告)日：2012-04-19
申请号：US13275676
申请日：2011-10-18
申请人： Minoru Uchida , Hiroshi Yamanouchi
发明人： Minoru Uchida , Hiroshi Yamanouchi
摘要： An aircraft control surface operating device is provided for operating a control surface on an aircraft body portion to move between a retracted position and an extended position. The aircraft control surface operating device includes a control surface mounting assembly which movably secures the control surface to the aircraft body portion, a drive arm rotatable about a drive axis relative to the aircraft body portion, an actuator for rotating the drive, and a drive link connecting the drive arm to the control surface mounting assembly. The drive link has a control end connected to the control surface mounting assembly and a driven end connected to the drive arm via a drive bearing joint. The drive link connects the drive arm and the control surface mounting assembly such that rotation of the drive arm is causes extending or retracting movement of the control surface.
摘要翻译： 飞行器控制表面操作装置被提供用于操作飞机主体部分上的控制表面以在缩回位置和延伸位置之间移动。 飞行器控制表面操作装置包括控制表面安装组件，该控制表面安装组件将控制表面可移动地固定到飞行器主体部分，相对于飞行器主体部分可围绕驱动轴线旋转的驱动臂，用于旋转驱动器的致动器和驱动连杆 将驱动臂连接到控制表面安装组件。 驱动链路具有连接到控制表面安装组件的控制端和经由驱动轴承接头连接到驱动臂的从动端。 驱动链路连接驱动臂和控制表面安装组件，使得驱动臂的旋转引起控制表面的延伸或缩回运动。
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