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    DYNAMIC PITCH ADJUSTMENT DEVICES, SYSTEMS, AND METHODS
    2.
    发明公开
    DYNAMIC PITCH ADJUSTMENT DEVICES, SYSTEMS, AND METHODS 审中-公开
    动态倾斜控制设备，系统和程序

    公开(公告)号：EP3063063A1

    公开(公告)日：2016-09-07

    申请号：EP14796985.1

    申请日：2014-10-31

    申请人： LORD Corporation

    发明人： JOLLY, Mark R. ,  HALILOVIC, Haris ,  MILLER, Lane

    IPC分类号： B64C27/08 ,  B64C27/51

    CPC分类号： B64C27/001 ,  B64C27/51 ,  B64C27/605 ,  B64C27/615 ,  B64C27/64 ,  B64C2027/003 ,  B64C2027/7266 ,  Y02T50/34

    摘要： Vibration control systems, devices, and methods are provided for a rotary wing aircraft having a rotor including a plurality of blades (20) each attached to a hub (10) at its root end and capable of pitching with respect to the hub (10). The systems, devices, and methods include a blade pitch adjuster (100) that is passively adjustable in response to aerodynamic loading on the plurality of blades (20) to adjust a pitch of one of the plurality of blades (20) with respect to the hub (10) based on a frequency of the aerodynamic loading. The blade pitch adjusters (100) can be configured to exhibit relatively high stiffness at the rotor rotating frequency and tailored dynamics at frequencies higher than the rotor rotating frequency such that hub loads at one or more higher harmonics are reduced.

    HUB-MOUNTED ACTIVE VIBRATION CONTROL (HAVC) DEVICES, SYSTEMS, AND METHODS
    6.
    发明公开
    HUB-MOUNTED ACTIVE VIBRATION CONTROL (HAVC) DEVICES, SYSTEMS, AND METHODS 有权
    HAVC-VORRICHTUNGEN，-SYSTEME以外地区

    公开(公告)号：EP2911937A2

    公开(公告)日：2015-09-02

    申请号：EP13854198.2

    申请日：2013-10-23

    申请人： LORD Corporation

    发明人： JOLLY, Mark R. ,  ALTIERI, Russell E. ,  WINZENZ, Wayne L. ,  BRANNAN, Warren F. ,  BLACK, Paul R. ,  SWANSON, Doug A.

    IPC分类号： B64C27/00 ,  F16F15/22

    CPC分类号： B64C27/001 ,  B64C2027/003

    摘要： Hub-mounted active vibration control (HAVC) devices, systems, and related methods are provided. An HAVC device includes a housing having a tolerance ring attached to a rotary hub. The tolerance ring can accommodate dissimilar coefficients of thermal expansion between dissimilar metals. The HAVC device can also include a plurality of coaxial ring motors configured to rotate a plurality of imbalance masses for controlling vibration. An HAVC system can further include a de-icing distributor for communicating instructions to one or more heating sources provided at one or more rotary blades of a vehicle or aircraft. A method of controlling vibratory loads occurring at a moving platform can include providing a moving platform, mounting a vibration control device to a portion of the moving platform, and rotating at least one pair of imbalance masses such that the combined forces of the masses substantially cancel unwanted vibration of the platform.

    摘要翻译： 提供了一种轮毂式主动振动控制（HAVC）系统。 HAVC系统包括附接到旋转毂（702）并被构造成与其一起旋转的机械单元（300）。 机械单元（300）包括以基本相同的频率共转动的至少一对不平衡质量对。 在机械单元（300）的至少一部分上设置除冰分配器（208），其中除冰分配器被配置为将指令传送到设置在一个或多个旋转叶片处的一个或多个加热源。

    HELICOPTER REDUCED VIBRATION ISOLATOR AXIAL SUPPORT STRUT
    8.
    发明授权
    HELICOPTER REDUCED VIBRATION ISOLATOR AXIAL SUPPORT STRUT 有权
    AXIALSTÜTZSTREBE用于直升机的减少隔振器

    公开(公告)号：EP2015988B1

    公开(公告)日：2011-07-27

    申请号：EP07868267.1

    申请日：2007-05-07

    申请人： LORD CORPORATION

    发明人： MCGUIRE, Dennis ,  MILLER, Lane R. ,  JOLLY, Mark R. ,  BADRE-ALAM, Askari

    IPC分类号： B64C27/00 ,  F16F13/26

    CPC分类号： B64C27/001 ,  B64C2027/002 ,  F16F13/262

    摘要： Helicopter reduced vibration axial support struts and aircraft suspension system are disclosed with at least one vibration controlling fluid containing strut. The powered struts include an outer rigid housing (28) containing an inner rigid member (32) and first (62) and second (64) variable volume fluid chambers. Fluid pressure differentials are created between the first and second variable volume fluid chambers to control motion between the strut ends. The powered fluid containing struts, support isolators, suspension systems, and methods of operation provide reduced helicopter aircraft vibrations.

    HELICOPTER REDUCED VIBRATION ISOLATOR AXIAL SUPPORT STRUT
    9.
    发明公开
    HELICOPTER REDUCED VIBRATION ISOLATOR AXIAL SUPPORT STRUT 有权
    AXIALSTÜTZSTREBE用于直升机的减少隔振器

    公开(公告)号：EP2015988A2

    公开(公告)日：2009-01-21

    申请号：EP07868267.1

    申请日：2007-05-07

    申请人： LORD CORPORATION

    发明人： MCGUIRE, Dennis ,  MILLER, Lane R. ,  JOLLY, Mark R. ,  BADRE-ALAM, Askari

    IPC分类号： B64C27/00 ,  F16F15/00 ,  F16F9/00

    CPC分类号： B64C27/001 ,  B64C2027/002 ,  F16F13/262

    摘要： Helicopter reduced vibration axial support struts and aircraft suspension system are disclosed with at least one vibration controlling fluid containing strut. The powered struts include an outer rigid housing (28) containing an inner rigid member (32) and first (62) and second (64) variable volume fluid chambers. Fluid pressure differentials are created between the first and second variable volume fluid chambers to control motion between the strut ends. The powered fluid containing struts, support isolators, suspension systems, and methods of operation provide reduced helicopter aircraft vibrations.