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    DRIVE SHAFT SYSTEM HANGER BEARING
    11.
    发明申请
    DRIVE SHAFT SYSTEM HANGER BEARING 审中-公开

    公开(公告)号：US20170203837A1

    公开(公告)日：2017-07-20

    申请号：US15312769

    申请日：2015-03-23

    申请人： SIKORSKY AIRCRAFT CORPORATION

    发明人： Yuriy GMIRYA ,  Rodger W. BOWMAN

    IPC分类号： B64C27/12 ,  B64C27/82 ,  B64C27/06 ,  F16C27/06

    CPC分类号： B64C27/12 ,  B64C27/06 ,  B64C27/14 ,  B64C27/82 ,  F16C19/06 ,  F16C23/08 ,  F16C23/086 ,  F16C27/066

    摘要： A hanger bearing assembly for a shaft assembly includes a plurality of bearing elements arranged around a circumference of a shaft assembly, each bearing element having a bearing element diameter. A bearing inner race is positioned between the plurality of bearing elements and the shaft assembly and extends circumferentially about the shaft assembly. The bearing inner race includes an outer wall interactive with the plurality of bearing elements. The outer wall has a linear profile extending in an axial direction. A bearing outer race is positioned radially outboard of the plurality of bearing elements and extends circumferentially about the shaft assembly. The bearing outer race includes an inner surface interactive with the plurality of bearing elements and having a curvilinear inner surface profile extending in the axial direction.

    Advanced control relationship for a deflectable stabilizer
    13.
    发明授权
    Advanced control relationship for a deflectable stabilizer 有权

    公开(公告)号：US09703294B2

    公开(公告)日：2017-07-11

    申请号：US15146081

    申请日：2016-05-04

    申请人： AIRBUS HELICOPTERS

    发明人： Herve Morel ,  Nicolas Queiras

    IPC分类号： G05D1/08 ,  B64C13/16 ,  B64C27/82

    CPC分类号： G05D1/0816 ,  B64C13/16 ,  B64C27/82 ,  B64C2027/8281 ,  G05D1/0858

    摘要： A method of controlling a deflection angle of pitching stabilizer means for an aircraft. The method includes a preliminary stage for preparing at least one control relationship delivering a setpoint angle that is to be reached by the deflection angle as a function of at least one flight parameter of the aircraft and of an incidence parameter of the pitching stabilizer means. During an operational stage an operational stage (STP2), a “flight” value is determined for each of the flight parameters, a “setpoint” value is determined for the incidence parameter, a setpoint angle is determined by inputting the flight values and setpoint value into the control relationship, and at least one actuator is actuated in order to cause the deflection angle of the pitching stabilizer means to reach the setpoint angle.

    ROTATION OF DISENGAGED ROTOR
    14.
    发明申请
    ROTATION OF DISENGAGED ROTOR 审中-公开

    公开(公告)号：US20170190417A1

    公开(公告)日：2017-07-06

    申请号：US15324524

    申请日：2015-07-06

    申请人： SIKORSKY AIRCRAFT CORPORATION

    发明人： Ashley Devito ,  Henry E. Voegeli ,  Joseph Pantalone, III

    IPC分类号： B64C27/82 ,  B64C27/12

    CPC分类号： B64C27/82 ,  B64C27/12 ,  B64C2027/8236 ,  B64C2027/8272

    摘要： Embodiments of the invention include a vehicle including an engine and a rotor including a plurality of rotor blades in a path of exhaust from the engine. The vehicle includes a rotor control assembly configured to connect the rotor to a rotation force source to rotate the rotor and configured to rotate the rotor at a prescribed minimum rotation rate greater than zero based on at least one of disengaging the rotor from the rotation force source and receiving a control signal to disengage the rotor from the rotation force source. The rotor control assembly is designed to rotate the rotor at the prescribed minimum rotation rate based on at least one system attribute of the vehicle that is affected by a rotation rate of the rotor.

    ELEVATOR LOAD ALLEVIATING CONTROL FOR A ROTARY WING AIRCRAFT
    18.
    发明申请
    ELEVATOR LOAD ALLEVIATING CONTROL FOR A ROTARY WING AIRCRAFT 审中-公开
    电动机负载控制旋转式飞机

    公开(公告)号：US20170029093A1

    公开(公告)日：2017-02-02

    申请号：US15300972

    申请日：2014-04-02

    申请人： Sikorsky Aircraft Corporation

    发明人： Erez Eller ,  Aaron L. Greenfield ,  Ole Wulff ,  Matthew A. White ,  Matthew T. Luszcz

    IPC分类号： B64C13/50 ,  B64C13/18 ,  B64C27/08 ,  B64C27/82

    CPC分类号： B64C13/503 ,  B64C13/18 ,  B64C27/08 ,  B64C27/10 ,  B64C27/57 ,  B64C27/82 ,  B64C2027/8236 ,  B64C2027/8272 ,  B64C2027/8281 ,  Y02T50/44

    摘要： One aspect is a flight control system for a rotary wing aircraft including a main rotor system and an elevator control system. A flight control computer of the flight control system includes processing circuitry configured to execute control logic. The control logic includes an inverse plant model that produces a main rotor feed forward command based on a pitch rate command, and a load alleviation control filter configured to reduce loads on a main rotor system and produce an elevator command for an elevator control system. A transformed elevator command filter produces a main rotor pitch adjustment command based on the elevator command, and a main rotor command generator generates an augmented main rotor feed forward command for the main rotor system based on the main rotor feed forward command and the main rotor pitch adjustment command.

    摘要翻译： 一个方面是用于包括主转子系统和电梯控制系统的旋翼飞机的飞行控制系统。 飞行控制系统的飞行控制计算机包括配置成执行控制逻辑的处理电路。 控制逻辑包括基于俯仰速率指令产生主转子前馈命令的逆电厂模型，以及负载减轻控制滤波器，其被配置为减少主转子系统上的负载并产生用于电梯控制系统的电梯命令。 转换后的升降机指令滤波器基于电梯指令产生主转子桨距调整指令，主转子指令发生器基于主转子前进指令和主转子间距产生主转子系统的增大主转子前馈指令 调整指令。

    Multi-Propulsion Design for Unmanned Aerial Systems
    19.
    发明申请
    Multi-Propulsion Design for Unmanned Aerial Systems 审中-公开
    无人空中系统的多推进设计

    公开(公告)号：US20170015417A1

    公开(公告)日：2017-01-19

    申请号：US14839960

    申请日：2015-08-29

    申请人： Reference Technologies Inc

    发明人： Allen Paul Bishop

    IPC分类号： B64C39/02 ,  B64C27/82 ,  B64C29/04

    CPC分类号： B64C39/024 ,  B64C27/20 ,  B64C27/82 ,  B64C29/04 ,  B64C2027/8227 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/108 ,  B64D2027/026

    摘要： A propulsion system for a ducted fan vertical takeoff and landing aircraft (VTOL) powered by multiple electric motors with two, counter rotating electric motors comprising the primary thrust generation within a ducted fan component and 3 or more external electric motors providing lift, stability and directional control of the aircraft. Through the use of counter rotating ducted fans, the aircraft does not require the need for internal stators—either fixed or adjustable angle. Power to the electric motors is sourced by either onboard batteries, a ground based power source via a ground to aircraft tether, or an on board fuel cell or combustion engine driving an alternator.

    摘要翻译： 一种用于由具有两个逆向旋转电动机的多个电动机驱动的管道风扇垂直起降飞机（VTOL）的推进系统，其包括在管道风扇部件内的主要推力产生和提供升力，稳定性和定向的3个或更多个外部电动马达 控制飞机。 通过使用反向旋转管道风扇，飞机不需要内部定子 - 固定或可调角度。 电动机的功率来自车载电池，地面电源通过地面到飞机系绳，或车载燃料电池或驱动交流发电机的内燃机。

    Non-uniform blade distribution for rotary wing aircraft
    20.
    发明授权
    Non-uniform blade distribution for rotary wing aircraft 有权
    旋翼飞机的不均匀叶片分布

    公开(公告)号：US09528375B2

    公开(公告)日：2016-12-27

    申请号：US13689941

    申请日：2012-11-30

    申请人： Mark R. Alber

    发明人： Mark R. Alber

    IPC分类号： B64C27/82 ,  F01D5/02 ,  B64C27/22

    CPC分类号： F01D5/02 ,  B64C27/22 ,  B64C27/82 ,  B64C2027/8236

    摘要： A translational thrust system for a rotary wing aircraft is provided including a propeller system. The propeller system includes more than one pair of propeller blades extending radially outward from a rotatable propeller hub. Each pair of propeller blades includes a first propeller blade and a second propeller blade arranged diametrically opposite one another about a circumference of the propeller hub. Each pair of propeller blades is arranged at an angle to an adjacent pair of propeller blades such that the angle is less than is the pairs of propeller blades were uniformly distributed around the circumference of the propeller hub.

    摘要翻译： 提供了一种用于旋翼飞机的平移推力系统，包括螺旋桨系统。 螺旋桨系统包括从旋转螺旋桨毂径向向外延伸的多对螺旋桨叶片。 每对螺旋桨叶片包括第一螺旋桨叶片和第二螺旋桨叶片，所述第一螺旋桨叶片和第二螺旋桨叶片围绕螺旋桨轮毂的圆周彼此沿直径相对地布置。 每对螺旋桨叶片与相邻的一对螺旋桨叶片成角度地设置，使得角度小于螺旋桨叶片周围均匀分布的角度。