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    AUTOMATED ROTATING TAIL ROTOR CONTROL
    51.
    发明申请
    AUTOMATED ROTATING TAIL ROTOR CONTROL 有权
    自动旋转尾转子控制

    公开(公告)号：US20150053815A1

    公开(公告)日：2015-02-26

    申请号：US13972369

    申请日：2013-08-21

    申请人： Sikorsky Aircraft Corporation

    发明人： Anthony Litwinowicz ,  James Rigsby ,  Cody Fegely ,  Mark W. Scott ,  John Knag

    IPC分类号： B64C27/82 ,  B64C19/00

    CPC分类号： B64C27/82 ,  B64C2027/8236 ,  B64C2027/8272

    摘要： Embodiments are directed to causing, by a computing device comprising a processor, a rotating tail rotor to operate in a tail rotor mode when an aircraft is operating at a speed less than a rudder control power threshold, receiving, by the computing device, a command that indicates a request to transition the aircraft, determining, by the computing device, that a rudder of the aircraft has control power in an amount greater than a second threshold based on receiving the command, and causing, by the computing device, the rotating tail rotor to operate in a pusher propeller mode based on determining that the rudder has control power in the amount greater than the second threshold.

    摘要翻译： 实施例涉及通过包括处理器的计算设备，当飞行器以小于舵控制功率阈值的速度操作时，使旋转尾部转子以尾部转子模式操作，由计算设备接收命令 其指示转换飞行器的请求，由计算设备确定基于接收到该命令，飞行器的方向舵具有大于第二阈值的控制功率，并且由计算设备使旋转尾部 转子基于确定方向舵具有大于第二阈值的量的控制功率在推进器螺旋桨模式下操作。

    Use of auxiliary rudders for yaw control at low speed
    52.
    发明授权
    Use of auxiliary rudders for yaw control at low speed 有权
    使用辅助方向舵进行低速偏航控制

    公开(公告)号：US08960594B2

    公开(公告)日：2015-02-24

    申请号：US13282985

    申请日：2011-10-27

    申请人： David L. Groen

    发明人： David L. Groen

    IPC分类号： B64C27/02 ,  B64C5/02 ,  B64C5/06 ,  B64C9/00 ,  B64C9/34 ,  B64C39/04

    CPC分类号： B64C27/18 ,  B64C5/02 ,  B64C5/06 ,  B64C9/00 ,  B64C9/34 ,  B64C27/025 ,  B64C27/027 ,  B64C27/82 ,  B64C39/04 ,  B64C2027/8245 ,  B64C2027/8272 ,  B64C2027/8281

    摘要： Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use.

    摘要翻译： 公开了在低空速和发动机故障中的一个或两个情况下控制旋翼航空器的偏航的装置和方法。 偏航推进在低速时提供横摆力矩。 偏航推进装置可以是空气喷射器或风扇。 气动风扇可以被释放到围绕风扇外部的通道的压缩空气驱动。 风扇可以由液压动力驱动。 用于偏航推进装置和其它系统的动力可由与转子接合的液压泵和/或发电机提供。 低速偏航控制可以由位于支柱的流管内的辅助方向舵提供。 辅助方向舵可以在不使用时向下折叠并与方向舵控制器脱离。

    AIRCRAFT TAIL ROTOR SYSTEM
    53.
    发明申请
    AIRCRAFT TAIL ROTOR SYSTEM 有权
    飞机尾转子系统

    公开(公告)号：US20150034760A1

    公开(公告)日：2015-02-05

    申请号：US13958161

    申请日：2013-08-02

    申请人： Sikorsky Aircraft Corporation

    发明人： John E. Hewitt

    IPC分类号： B64C27/82 ,  F16C33/58 ,  F16C41/00

    CPC分类号： B64C27/82 ,  F16C19/52 ,  F16C19/54 ,  F16C41/001 ,  F16C2326/43

    摘要： An aircraft tail rotor system is provided and includes a rotating element, a translating element and a structure including a first bearing in series with a second bearing, the first bearing including a component rotatable with and movable within the rotating element in accordance with translational movement of the translating element. The structure is configured to selectively use the second bearing to prevent transmission of rotational energy from the rotating element to the translating element in an event of a seizing of the first bearing.

    摘要翻译： 提供了一种飞机尾部转子系统，其包括旋转元件，平移元件和包括与第二轴承串联的第一轴承的结构，所述第一轴承包括可旋转并可在旋转元件内移动的部件， 翻译元素。 结构被配置为在第一轴承的卡住的情况下选择性地使用第二轴承来防止旋转能量从旋转元件传递到平移元件。

    Rotorcraft Anti-torque Control System
    54.
    发明申请
    Rotorcraft Anti-torque Control System 审中-公开
    转子防扭矩控制系统

    公开(公告)号：US20140374534A1

    公开(公告)日：2014-12-25

    申请号：US13925008

    申请日：2013-06-24

    申请人： Bell Helicopter Textron Inc.

    发明人： James M. McCollough ,  Carlos A. Fenny

    IPC分类号： B64C27/82

    CPC分类号： B64C27/82 ,  B64C2027/8254 ,  B64C2027/8272

    摘要： According to one embodiment, a rotorcraft includes a main rotor system, an anti-torque rotor system, an anti-torque rudder system, and an anti-torque control system. The anti-torque rudder system includes at least one rudder surface operable to provide a second force on the body in the direction of rotation of the at least one main rotor blade. The anti-torque control system is operable to receive a request to change an amount of anti-torque force applied to the body, compare a rotorcraft performance parameter to a threshold value, instruct one of the anti-torque rotor system or the anti-torque rudder system to change the amount of the first force if the rotorcraft performance parameter is less than the threshold value, and, if the rotorcraft performance parameter is greater than the threshold value, instruct the other of the anti-torque rotor system or the anti-torque rudder system to change the amount of the second force.

    摘要翻译： 根据一个实施例，旋翼航空器包括主转子系统，抗扭矩转子系统，抗扭矩舵系统和抗扭矩控制系统。 防扭矩舵系统包括至少一个方向舵表面，其可操作以在所述主体上沿所述至少一个主转子叶片的旋转方向提供第二力。 抗扭矩控制系统可操作以接收改变施加到车身的抗扭矩力的量的请求，将旋翼航空器的性能参数与阈值进行比较，指示抗扭矩转子系统或抗扭矩 方向舵系统，如果旋翼航空器的性能参数小于阈值，则改变第一力的量，并且如果旋翼航空器的性能参数大于阈值，则指示另一个抗扭矩转子系统或抗扭矩转子系统， 扭矩舵系统改变第二力的量。

    Hybrid aircraft having a rotary wing
    56.
    发明授权
    Hybrid aircraft having a rotary wing 有权
    混合飞机有一个旋翼

    公开(公告)号：US08840057B2

    公开(公告)日：2014-09-23

    申请号：US13628525

    申请日：2012-09-27

    申请人： EUROCOPTER

    发明人： Robin Moret

    IPC分类号： B64C27/22 ,  B64C27/26 ,  B64D35/04 ,  B64C27/82 ,  B64C27/12

    CPC分类号： B64C27/26 ,  B64C27/12 ,  B64C27/82

    摘要： An aircraft (1) having a fuselage (2), a power plant (10), a rotary wing (15) having at least one main rotor (16), and a fixed wing (20) comprising two half-wings (21, 22) extending on either side of the fuselage (2). The aircraft (1) also has at least two propulsive propellers (30) on either side of the fuselage (2). Each is positioned on respective ones of the half-wings (21, 22), and an anti-torque and yaw-control tail rotor (35). A transmission system (40) connects the power plant (10) to each main rotor (16) and the tail rotor (35). The transmission system (40) connects the power plant (10) to each propeller (30) via a respective differential mechanism (50) that is controllable on request so that each propeller (30) can be driven in cruising flight and need not be driven in rotation by the power plant (10) on the ground or while hovering.

    摘要翻译： 具有机身（2）的飞机（1），发电厂（10），具有至少一个主转子（16）的旋转翼（15）和包括两个半翼（21， 22）在机身（2）的两侧延伸。 飞机（1）还在机身（2）的两侧至少有两个推进螺旋桨（30）。 每个都位于半翼（21,22）中的相应一个上，以及防扭矩和偏航控制尾部转子（35）。 传动系统（40）将发电厂（10）连接到每个主转子（16）和尾转子（35）。 传动系统（40）通过相应的差速机构（50）将动力装置（10）连接到每个螺旋桨（30），该差速机构可根据要求进行控制，使得每个螺旋桨（30）能够在巡航飞行中被驱动并且不需要被驱动 由地面上的发电厂（10）旋转或盘旋时。

    ROTARY WING AIRCRAFT PITCH BEAM ATTACHMENT WITH ANTI-ROTATION PLATE DESIGN
    57.
    发明申请
    ROTARY WING AIRCRAFT PITCH BEAM ATTACHMENT WITH ANTI-ROTATION PLATE DESIGN 有权
    旋转翼飞机吊坠梁与反转板设计

    公开(公告)号：US20140241884A1

    公开(公告)日：2014-08-28

    申请号：US13778741

    申请日：2013-02-27

    申请人： SIKORSKY AIRCRAFT CORPORATION

    发明人： David N. Schmaling ,  Richard Thomas Hood ,  Evan Sobel

    IPC分类号： F01D7/00

    CPC分类号： F01D7/00 ,  B64C27/82 ,  F16D1/108 ,  F16D2001/103 ,  Y10T29/49321

    摘要： A retaining assembly for a tail rotor system is provided including a washer having a plurality of splines. The washer is configured to couple to an adjacent pitch change shaft. A retaining nut includes a self-locking feature and a flange arranged at a first end. The retaining nut is configured to threadably couple to the pitch change shaft such that the flange is in contact with the washer. The flange includes a plurality of first holes configured to at least partially align between the splines of the washer. A lock plate includes a body and a plurality of tabs extending generally perpendicularly from the body. The lock plate is slidably positioned about the pitch change shaft adjacent the flange. The lock plate is operably coupled to the retaining nut and the washer to limit rotational movement thereof relative to the pitch change shaft.

    摘要翻译： 提供了一种用于尾部转子系统的保持组件，其包括具有多个花键的垫圈。 垫圈构造成联接到相邻的变桨轴。 保持螺母包括自锁特征和布置在第一端的凸缘。 保持螺母构造成螺纹连接到变桨轴，使得凸缘与垫圈接触。 凸缘包括多个第一孔，其构造成在垫圈的花键之间至少部分对准。 锁板包括主体和大体上垂直于主体延伸的多个突出部。 锁定板围绕靠近凸缘的变桨轴可滑动地定位。 锁定板可操作地联接到保持螺母和垫圈以限制其相对于螺距变化轴的旋转运动。

    Aircraft provided with a swiveling tail rotor, and an associated method
    58.
    发明授权
    Aircraft provided with a swiveling tail rotor, and an associated method 有权
    飞机配有旋转尾部转子和相关方法

    公开(公告)号：US08763949B2

    公开(公告)日：2014-07-01

    申请号：US13314269

    申请日：2011-12-08

    申请人： Lionel Thomassey

    发明人： Lionel Thomassey

    IPC分类号： B64C27/54

    CPC分类号： B64C27/82

    摘要： An aircraft (1) having an airframe (4) extending from a rear end (4″) to a front end (4′), a rotary wing (2), and a tail rotor (10). The aircraft (1) also includes a power plant (20) driving said rotary wing (2) via a main power gearbox (30) secured to a mast (31) of said rotary wing (2), said power plant (20) driving said tail rotor (10) via a tail power gearbox (40). The aircraft possesses pivot means (43) for causing the tail rotor (10) to swivel in a reversible manner from a stationary first position (POS1) towards a second position (POS2). The aircraft also includes tilt means (50) for tilting said mast (31) in a reversible manner.

    摘要翻译： 具有从后端（4“）延伸到前端（4'）的机身（4）的飞行器（1），旋转翼（2）和尾部转子（10）。 飞机（1）还包括经由固定到所述旋转翼（2）的桅杆（31）的主动力齿轮箱（30）驱动所述旋转翼（2）的动力装置（20），所述动力装置（20）驱动 所述尾部转子（10）经由尾部动力齿轮箱（40）。 飞行器具有用于使尾部转子（10）以可逆的方式从固定的第一位置（POS1）朝向第二位置（POS2）旋转的枢转装置（43）。 飞机还包括用于以可逆方式倾斜所述桅杆（31）的倾斜装置（50）。

    ASYMMETRICAL SINGLE MAIN ROTOR UNMANNED AERIAL VEHICLE
    60.
    发明申请
    ASYMMETRICAL SINGLE MAIN ROTOR UNMANNED AERIAL VEHICLE 有权
    不对称单主转子无人驾驶车

    公开(公告)号：US20140008486A1

    公开(公告)日：2014-01-09

    申请号：US13532212

    申请日：2012-06-25

    申请人： Mark R. Alber ,  Jessica Newman

    发明人： Mark R. Alber ,  Jessica Newman

    IPC分类号： B64C27/12 ,  B64C27/82 ,  B64C27/06

    CPC分类号： B64C27/12 ,  B64C27/06 ,  B64C27/82 ,  B64C39/024 ,  B64C2027/8218 ,  B64C2201/024

    摘要： A single engine rotary wing aircraft is provided including a fuselage having a longitudinal first axis. A main rotor assembly is mounted to the fuselage for rotation about a second axis, perpendicular to the first axis. A tailboom is connected to an empennage. The tailboom is mounted to an end of the fuselage such that the tailboom is laterally offset from the first axis in a first direction. The rotary wing aircraft also includes a propulsion system. The single engine of the propulsion system is laterally offset from the first axis in a second direction opposite the first direction.

    摘要翻译： 提供了包括具有纵向第一轴线的机身的单个发动机旋翼飞行器。 主转子组件安装到机身上以围绕垂直于第一轴线的第二轴线旋转。 尾巴连接到一个尾翼。 尾杆安装到机身的一端，使得尾杆在第一方向上从第一轴线横向偏移。 旋翼飞机还包括推进系统。 推进系统的单个发动机在与第一方向相反的第二方向上与第一轴线横向偏移。