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    ISOLATOR DEVICES, SYSTEMS AND METHODS FOR AIRCRAFT
    1.
    发明申请
    ISOLATOR DEVICES, SYSTEMS AND METHODS FOR AIRCRAFT 审中-公开

    公开(公告)号：US20190144124A1

    公开(公告)日：2019-05-16

    申请号：US16098345

    申请日：2017-05-12

    申请人： LORD Corporation

    发明人： Daniel ZAMEROSKI

    IPC分类号： B64D27/26 ,  B64C27/00 ,  F16F15/02

    CPC分类号： B64D27/26 ,  B64C27/001 ,  B64C2027/003 ,  F02C7/20 ,  F05D2260/96 ,  F16F15/02 ,  Y02T50/44

    摘要： Aircraft isolator devices, systems, and methods for isolating a structural component within an aircraft can include an engine interface, airframe, and one or more (e.g., a plurality of) isolator devices attached to the engine interface and the airframe. In some aspects, the isolator devices have a housing, which has a first surface and a second surface that together at least partially define a perimeter of the housing and is configured for attachment to the airframe; an engine attachment component configured for attachment to the engine interface and disposed at least partially inside of the housing; and a plurality of elastomeric elements disposed on or over each of the first and second surfaces of the housing The plurality of elastomeric elements are spaced apart from the engine attachment component via the housing for improved heat dissipation from the engine, reducing operational temperatures of the elastomeric elements to prolong their use.

    HUB MOUNTED VIBRATION SUPPRESSION SYSTEM
    4.
    发明申请
    HUB MOUNTED VIBRATION SUPPRESSION SYSTEM 审中-公开

    公开(公告)号：US20170129595A1

    公开(公告)日：2017-05-11

    申请号：US15212978

    申请日：2016-07-18

    申请人： Moog Inc.

    发明人： Arturo M. Arce

    IPC分类号： B64C27/00

    CPC分类号： B64C27/001 ,  B64C2027/003 ,  F05D2260/96 ,  F05D2270/334 ,  F05D2270/304

    摘要： An improved vibration control actuation system for a rotary-wing aircraft having a plurality of rotor blades mounted to a rotor hub and driven about a central axis of rotation at an operational speed and in a rotational direction relative to a non-rotating body of the aircraft comprising a vibration control frame adapted to be mounted to the hub and to rotate relative to the hub about the central axis in a rotational direction opposite to the rotational direction of the hub, a frame motor configured to rotate the frame about the central axis, the frame supporting first and second motors configured to rotate first and second masses about first and second axes not concentric with the central axis, and a controller for receiving input signals and outputting command signals to the first and second motors.

    Rotor damper device, and an associated rotor and aircraft
    5.
    发明授权
    Rotor damper device, and an associated rotor and aircraft 有权
    转子减震装置，以及相关的转子和飞机

    公开(公告)号：US09079660B2

    公开(公告)日：2015-07-14

    申请号：US13440143

    申请日：2012-04-05

    申请人： Elio Zoppitelli ,  Etienne Rampal

    发明人： Elio Zoppitelli ,  Etienne Rampal

    IPC分类号： B64C27/32 ,  B64C27/51 ,  B64C27/35 ,  B64C27/635 ,  B64C27/00

    CPC分类号： B64C27/51 ,  B64C27/35 ,  B64C27/635 ,  B64C2027/003

    摘要： A damper device (10) for a rotor (2) having a rotary ring (11) and a plurality of levers (12), each lever (12) extending from a first end (12′) connected to the ring (11) by a first mechanical connection (20) to a second end (12″) suitable for being hinged to a blade (4). The damper device (10) includes non-rotary damper means (30) secured to non-rotary fastener means (40) and to a non-rotary member (51) of an interface (50), the interface (50) being interposed between the non-rotary damper means (30) and the ring (11) to convert a rotary movement of a blade (4) transmitted to a lever (12) into a movement in translation acting on the damper means (30).

    摘要翻译： 一种用于具有旋转环（11）和多个杠杆（12）的转子（2）的阻尼器装置（10），每个杠杆（12）从通过所述环（11）连接到所述环（11）的第一端（12'）延伸， 适于铰接到叶片（4）的第二端（12“）的第一机械连接（20）。 阻尼器装置（10）包括固定到非旋转紧固装置（40）和接口（50）的非旋转构件（51）的非旋转阻尼装置（30），所述界面（50）介于 所述非旋转阻尼装置（30）和所述环（11）将传递到杠杆（12）的叶片（4）的旋转运动转换成作用在所述阻尼装置（30）上的平移运动。

    HOVER AIRCRAFT ROTOR COMPRISING A VIBRATION DAMPING DEVICE
    6.
    发明申请
    HOVER AIRCRAFT ROTOR COMPRISING A VIBRATION DAMPING DEVICE 有权
    包含振动阻尼装置的HOVER飞机转子

    公开(公告)号：US20150098801A1

    公开(公告)日：2015-04-09

    申请号：US14503848

    申请日：2014-10-01

    申请人： AGUSTAWESTLAND S.p.A.

    发明人： Attilio COLOMBO

    IPC分类号： F01D25/04

    CPC分类号： F01D25/04 ,  B64C27/001 ,  B64C2027/003 ,  B64C2027/004 ,  B64C2027/005 ,  F16F7/1011 ,  F16F7/116

    摘要： A hover aircraft rotor having a hub which rotates about an axis and has a number of blades; a drive shaft connectable to a drive member of the aircraft and connected functionally to the hub to rotate the hub about the axis; and damping means for damping vibration transmitted to the shaft, and which include a mass designed to oscillate, in use, to oppose transmission to the shaft of vibration generated by rotation of the blades; the mass being free to oscillate parallel to the axis, to oppose transmission to the shaft of vibration having main components along the axis.

    摘要翻译： 悬架飞行器转子，其具有围绕轴线旋转并具有多个叶片的轮毂; 驱动轴，其可连接到飞行器的驱动构件并且功能地连接到所述轮毂以使所述轮毂围绕所述轴线旋转; 以及阻尼装置，用于阻尼传递到所述轴的振动，并且其包括设计成在使用中摆动以抵抗由所述叶片的旋转产生的振动产生轴的传递的质量; 质量自由地平行于轴线振荡，以抵抗具有沿着轴线的主要部件的振动轴的传递。

    Device and process for oscillation insulation in a transmission path
    8.
    发明授权
    Device and process for oscillation insulation in a transmission path 失效
    传输路径中振荡绝缘的装置和过程

    公开(公告)号：US08037981B1

    公开(公告)日：2011-10-18

    申请号：US10838233

    申请日：2004-05-05

    申请人： Marius Bebesel ,  Peter Jänker ,  Rudolf Maier ,  Henning Strehlow

    发明人： Marius Bebesel ,  Peter Jänker ,  Rudolf Maier ,  Henning Strehlow

    IPC分类号： F16F15/00

    CPC分类号： F16F15/005 ,  B64C2027/003

    摘要： Device and process for oscillation insulation in a transmission path. The device includes a first body structured and arranged to undergo an oscillation movement, at least one rigid connection element, a second body connected to the first body via the at least one rigid connection element, and an actuator device attached to the at least one connection element. A sensor unit is arranged in an interface area of the at least one connection element, and a regulator unit, connected to the sensor unit, is arranged to control the actuator device to perform an elastic deformation equivalent to an oscillation movement of the first body. The instant abstract is neither intended to define the invention disclosed in this specification nor intended to limit the scope of the invention in any way.

    摘要翻译： 传输路径中振荡绝缘的装置和过程。 该装置包括构造和布置成经历振荡运动的第一主体，至少一个刚性连接元件，经由至少一个刚性连接元件连接到第一主体的第二主体，以及附接到至少一个连接的致动器装置 元件。 传感器单元布置在所述至少一个连接元件的接口区域中，并且连接到所述传感器单元的调节器单元布置成控制所述致动器装置执行与所述第一主体的振荡运动相当的弹性变形。 本摘要既不旨在限定本说明书中公开的发明，也不旨在以任何方式限制本发明的范围。

    Helicopter vibration control system and rotary force generator for canceling vibrations
    9.
    发明授权
    Helicopter vibration control system and rotary force generator for canceling vibrations 有权
    直升机振动控制系统和旋转力发生器，用于消除振动

    公开(公告)号：US07942633B2

    公开(公告)日：2011-05-17

    申请号：US12286461

    申请日：2008-09-30

    申请人： Mark Jolly ,  Stephen Hildebrand ,  Russell Altieri ,  Matthew Ferguson ,  Douglas Ivers

    发明人： Mark Jolly ,  Stephen Hildebrand ,  Russell Altieri ,  Matthew Ferguson ,  Douglas Ivers

    IPC分类号： F01D5/26

    CPC分类号： F16F15/265 ,  B64C27/001 ,  B64C2027/003 ,  F16F15/22 ,  F16F15/267

    摘要： Helicopter rotating hub mounted vibration control system for a rotary wing hub having periodic vibrations while rotating at an operational rotation frequency. The vibration control system includes a housing attachable to the rotary wing hub and rotating with the hub at the operational frequency. The housing is centered about the rotary wing hub axis of rotation and has an electronics housing cavity subsystem and an adjacent rotor housing cavity subsystem. The rotor housing cavity contains a first coaxial ring motor with a first rotor and imbalance mass and a second coaxial ring motor with a second rotor and imbalance mass. The electronics housing cavity contains an electronics control system which receives sensor outputs and electrically controls and drives the first motor and the second motor such that the first imbalance mass and the second imbalance mass are driven at a vibration canceling rotation frequency greater than the operational rotation frequency wherein the helicopter rotary wing hub periodic vibrations are reduced.

    摘要翻译： 用于旋转翼毂的直升机旋转轮毂安装的振动控制系统，其具有以工作旋转频率旋转的周期性振动。 振动控制系统包括可附接到旋转翼毂并且以工作频率与轮毂一起旋转的壳体。 壳体围绕旋转翼轮毂旋转轴线居中，并且具有电子器件壳体腔子系统和相邻的转子壳体空腔子系统。 转子壳体腔包含具有第一转子和不平衡质量的第一同轴环电动机和具有第二转子和不平衡质量的第二同轴环电动机。 电子设备壳体腔包含电子控制系统，其接收传感器输出并电控制并驱动第一电动机和第二电动机，使得第一不平衡质量块和第二不平衡质量块以大于操作旋转频率的振动消除旋转频率被驱动 其中直升机旋转翼毂周期性振动减小。

    DISTRIBUTED-MASS DEVICE FOR REDUCING VIBRATION GENERATED BY A ROTORCRAFT LIFT ROTOR, AND A ROTOR HUB FITTED WITH SUCH A DEVICE
    10.
    发明申请
    DISTRIBUTED-MASS DEVICE FOR REDUCING VIBRATION GENERATED BY A ROTORCRAFT LIFT ROTOR, AND A ROTOR HUB FITTED WITH SUCH A DEVICE 有权
    用于减少由转子提升转子产生的振动的分配式装置以及装配有这样的装置的转子座

    公开(公告)号：US20100296931A1

    公开(公告)日：2010-11-25

    申请号：US12783608

    申请日：2010-05-20

    申请人： Vincent GIRARD

    发明人： Vincent GIRARD

    IPC分类号： B64C27/00

    CPC分类号： B64C27/001 ,  B64C27/32 ,  B64C27/35 ,  B64C2027/003 ,  F16F7/116

    摘要： A distributed mass device for reducing the vibration generated by a rotor, includes a support suitable for being constrained in rotation about an axis of rotation of the lift rotor. The distributed mass device further includes at least two main oscillating masses each provided with a through longitudinal recess, and each being connected to the support by respective deformable elements, the main oscillating masses being constrained to move solely in a horizontal plane by the deformable elements. The distributed mass device is provided with a secondary oscillating mass per main oscillating mass, each secondary oscillating mass being suspended inside the recess of the associated main oscillating mass by resilient elements.

    摘要翻译： 用于减小由转子产生的振动的分布式质量装置包括适于被围绕提升转子的旋转轴线旋转约束的支撑件。 分布质量装置还包括至少两个主振荡块，每个主振荡块均设置有贯穿纵向凹槽，并且每个主振荡块均通过相应的可变形元件连接到支撑件，主振荡块被限制为仅通过可变形元件在水平平面中移动。 分布式质量装置设置有每个主振荡块的次级振动块，每个次级振动块通过弹性元件悬挂在相关联的主振荡块的凹部内。