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    RESONANT OPERATING ROTOR ASSEMBLY
    2.
    发明申请
    RESONANT OPERATING ROTOR ASSEMBLY 审中-公开

    公开(公告)号：US20190047688A1

    公开(公告)日：2019-02-14

    申请号：US16041512

    申请日：2018-07-20

    申请人： FLIR Unmanned Aerial Systems AS

    发明人： Petter Muren ,  Trygve Frederik Marton ,  Ivar Johnsrud ,  Pal Hagh Sandberg ,  Christian Moengen ,  Jo Eyvin Bjaarstad

    IPC分类号： B64C27/00 ,  B64C27/625

    摘要： The present embodiments disclose a torque dependent and resonant operating thrust-generating rotor assembly including a cyclic pitch control system for controlling tilting moments about a longitudinal rotor blade axis of one or more rotor blades, in order to control the pitch angle of the rotor blades and thereby also the horizontal movements of a helicopter vehicle or a rotary wing aircraft. A rotor torque assembly of the rotor assembly is further configured to operate in resonance, thereby providing a resonant gain effecting a rotational offset in relation to changes in torque generated by the motor.

    Device for automatically stabilizing the yaw motion of a helicopter
    4.
    发明授权
    Device for automatically stabilizing the yaw motion of a helicopter 失效
    用于自动稳定直升机偏航运动的装置

    公开(公告)号：US5305968A

    公开(公告)日：1994-04-26

    申请号：US770013

    申请日：1991-09-30

    申请人： Paul E. Arlton

    发明人： Paul E. Arlton

    IPC分类号： B64C27/10 ,  B64C27/32 ,  B64C27/467 ,  B64C27/625 ,  B64C27/82

    CPC分类号： A63H27/12

    摘要： In a helicopter having a tail rotor with a plurality of rotor blades extending radially from a hollow rotor shaft which is mounted for rotation about a transverse rotor axis, and having a push-pull rod extending through the hollow shaft and operably connected to the blades to manually vary the collective pitch of the blades, a device for automatically stabilizing the yaw motion of the helicopter includes a gyroscopic assembly having a gyro rotor mounted to rotate with the tail rotor, to pivot about a substantially longitudinal pivot axis by and at the outboard end of the push-pull rod and to automatically vary the collective pitch of the blades in response to yaw motion.

    摘要翻译： 在具有尾转子的直升机中具有多个转子叶片，所述转子叶片从中空转子轴径向延伸，所述中空转子轴安装成围绕横向转子轴线旋转，并且具有延伸穿过中空轴并可操作地连接到叶片的推拉杆 手动地改变叶片的总体间距，用于自动稳定直升机的偏航运动的装置包括陀螺仪组件，该陀螺仪组件具有安装成与尾部转子一起旋转的陀螺仪转子，以绕着基本上纵向的枢转轴线枢转并在外侧端部 并且响应于偏航运动而自动地改变叶片的集合间距。

    Blade-mounted centrifugal pendulum
    5.
    发明授权
    Blade-mounted centrifugal pendulum 失效
    刀片式离心摆

    公开(公告)号：US4239455A

    公开(公告)日：1980-12-16

    申请号：US941134

    申请日：1978-09-11

    申请人： Willem Broekhuizen ,  Troy M. Gaffey ,  Mukund M. Joglekar ,  William D. Neathery

    发明人： Willem Broekhuizen ,  Troy M. Gaffey ,  Mukund M. Joglekar ,  William D. Neathery

    IPC分类号： B64C27/51 ,  B64C27/00 ,  B64C27/625 ,  B64C27/32

    CPC分类号： B64C27/001 ,  B64C2027/005 ,  Y10S416/50

    摘要： A helicopter having a multiblade main rotor lift unit includes a plurality of pendulus mass units (48,60) mounted to oscillate in the plane of the rotor. The mass units (48,60) are connected to a rotatable shaft (24) which passes through a blade grip (14) for each blade (16). Vibrations generated in the plane of the rotor system are damped by the oscillating pendulums (22) which are tuned to minimize the vibrations in the lift unit.

    摘要翻译： 具有多叶片主转子提升单元的直升机包括安装成在转子的平面中振荡的多个摆锤质量单元（48,60）。 质量单元（48,60）连接到可旋转的轴（24）上，该轴通过用于每个叶片（16）的刀片（14）。 在转子系统的平面中产生的振动被振荡摆锤（22）阻尼，振荡摆动器被调谐以最小化提升单元中的振动。

    Aerial vehicle
    7.
    发明授权
    Aerial vehicle 有权

    公开(公告)号：US11332242B2

    公开(公告)日：2022-05-17

    申请号：US17461719

    申请日：2021-08-30

    申请人： Unmanned Aerospace LLC

    发明人： Gad Shaanan

    IPC分类号： B64C29/00 ,  B64C27/32 ,  B64C27/57 ,  B64C27/59 ,  B64C27/64 ,  B64C27/625 ,  B64D27/24 ,  B64D31/00 ,  B64D35/02 ,  B64C27/82 ,  G05D1/10

    摘要： Aircraft capable of vertical takeoff and landing, hovering, and efficient forward flight are described. An aircraft includes two side mounted tiltable proprotors and a central rotor disposed above the proprotors. The proprotors are tiltable between at least a horizontal position for forward flight and a vertical position for vertical or hovering flight. The central rotor may be powered for vertical and transitional flight modes and may turn by free autorotation during forward flight. The proprotors may be differentially tilted during vertical or hovering flight to counter torque effects of the central rotor. The central rotor may be foldable and/or easily detachable from the aircraft to facilitate storage and transportation. Left and right proprotors may provide both forward thrust and attitude control. Control inputs to left and right proprotors may be connected directly to an autopilot creating closed loop actuation using motor RPM feedback.

    Primary flight controls
    10.
    发明授权
    Primary flight controls 有权
    主要飞行控制

    公开(公告)号：US08888036B2

    公开(公告)日：2014-11-18

    申请号：US13534193

    申请日：2012-06-27

    申请人： Bruno Chaduc ,  Boris Grohmann ,  Christophe Tempier

    发明人： Bruno Chaduc ,  Boris Grohmann ,  Christophe Tempier

    IPC分类号： B64C11/00 ,  B64C27/68 ,  B64C27/64 ,  B64C27/625 ,  B64C13/50

    CPC分类号： B64C27/625 ,  B64C13/503 ,  B64C27/64 ,  B64C27/68 ,  Y02T50/44

    摘要： Primary flight controls (10) for main and/or tail rotors (4) of helicopters with electro-mechanical interface between any of fly-by-wire and/or fly-by-light controls and hydraulic servo actuators (8) for control force amplification towards said main and/or tail rotor controls (4). For each of the main and/or tail rotor controls (4) there is provided but one of the hydraulic servo actuators (8), connected by one mechanical linkage (7) to one electro motor (5), said one hydraulic servo actuator (8) being of the type having the one mechanical linkage (7) connected to its input (29) and its output (30) and the one electro motor (5) being of the direct drive type, the position of said electro motor (5) having a reference to said one mechanical linkage (7) and the torque delivered by said electro motor (5) to the hydraulic servo actuator (8) being related to the power consumption of said electro motor (5).

    摘要翻译： 用于直升机的主和/或尾转子（4）的主飞行控制（10），其具有在线控和/或飞越控制之间的电 - 机械接口和用于控制力的液压伺服致动器（8） 朝向所述主和/或尾部转子控制器（4）的放大。 对于每个主转子控制器和/或尾部转子控制器（4），只有一个液压伺服致动器（8）通过一个机械联动装置（7）连接到一个电动马达（5），所述一个液压伺服致动器 8）是具有连接到其输入端（29）和其输出端（30）的一个机械连杆（7）和一个电动机（5）是直接驱动型的类型，所述电动马达（5）的位置 ）和所述电动马达（5）传递到所述液压伺服驱动器（8）的扭矩与所述电动马达（5）的功率消耗有关。