公开(公告)号：US20150353191A1

公开(公告)日：2015-12-10

申请号：US14759126

申请日：2014-01-17

申请人： Mark R. JOLLY ,  Paul R. BLACK ,  Doug A. SWAMSPM ,  Doug G. PEDERSEN ,  LORD CORPORATION

发明人： Mark R. JOLLY ,  Paul R. BLACK ,  Doug A. SWANSON ,  Doug G. PEDERSEN

IPC分类号： B64C27/00

CPC分类号： B64C27/001 ,  B64C2027/004 ,  G05D19/02

摘要： Systems, methods, and computer program products for directional force weighting of an active vibration control system involve arranging a plurality of force generators in an array, identifying individual component forces corresponding to force outputs of each of the plurality of force generators, determining a combination of the individual component forces that will produce a desired total force vector, and adjusting the outputs of each of the plurality of force generators such that the combination of the individual component forces are at least substantially similar to the desired force vector.

摘要翻译： 用于主动振动控制系统的定向力加权的系统，方法和计算机程序产品涉及将多个力发生器布置在阵列中，识别与多个力发生器中的每一个的力输出相对应的各个分力，确定 将产生期望的总力矢量的单个分力，以及调节多个力发生器中的每一个的输出，使得各个分力的组合至少基本上类似于期望的力矢量。

公开(公告)号：US20150321752A1

公开(公告)日：2015-11-12

申请号：US14441993

申请日：2013-11-22

申请人： Michael W. TRULL ,  Michael D. JANOWSKI ,  Andrew D. MEYERS ,  LORD CORPORATION

发明人： Michael W. TRULL ,  Michael D. JANOWSKI ,  Andrew D. MEYERS

IPC分类号： B64C27/00 ,  F16F15/22

CPC分类号： B64C27/001 ,  B64C2027/004 ,  F16F15/223

摘要： Improved vibration damping devices (10), systems, and related methods are provided herein. In some aspects, damping devices and related methods can be used in single rotor or tandem rotor aircraft. In some aspects, a vibration damping device (10) for use in a vibration damping system of an aircraft can include a housing (10), at least two imbalance masses (42b, 44b) provided in a side-by-side configuration within the housing, and at least two more imbalance masses (40b, 46b) provided in a nested configuration within the housing. In some aspects, devices, systems, and methods include rotating any two imbalance masses provided within the housing in a same direction. Such rotation can result in a linear force for counteracting vibration occurring within the aircraft. In some aspects, devices described herein can include one or more processors for executing commands from a controller within a damping system.

摘要翻译： 本文提供了改进的减振装置（10），系统和相关方法。 在一些方面，阻尼装置和相关方法可用于单转子或串联转子飞机。 在一些方面，用于飞机的减振系统的减震装置（10）可以包括壳体（10），至少两个不平衡质量块（42b，44b）并排设置在内 壳体，以及设置在壳体内的嵌套构造中的至少两个不平衡质量块（40b，46b）。 在一些方面，装置，系统和方法包括以相同的方向旋转设置在壳体内的任何两个不平衡块。 这种旋转可以产生用于抵消在飞行器内发生的振动的线性力。 在一些方面，本文描述的装置可以包括用于在阻尼系统内执行来自控制器的命令的一个或多个处理器。

公开(公告)号：US20150232174A1

公开(公告)日：2015-08-20

申请号：US14434781

申请日：2013-10-23

申请人： Mark R. JOLLY ,  Russell E. ALTIERI ,  Wayne L. WINZENZ ,  Warren F. BRANNAN ,  Paul R. BLACK ,  Doug A. SWANSON ,  LORD CORPORATION

发明人： Mark R. Jolly ,  Russell E. Altieri ,  Wayne L. Winzenz ,  Warren F. Brannan ,  Paul R. Black ,  Doug A. Swanson

IPC分类号： B64C27/00 ,  F16F15/18 ,  F16F15/14

CPC分类号： B64C27/001 ,  B64C2027/003 ,  B64C2027/004 ,  F16F15/1485 ,  F16F15/18 ,  Y10T74/2128

摘要： Hub-mounted active vibration control (HAVC) devices, systems, and related methods are provided. An HAVC device (100) includes a housing (206) having a tolerance ring (600) attached to a rotary hub (702). 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 (308A, 308B, 310A, 310B) configured to rotate a plurality of imbalance masses for controlling vibration. An HAVC system can further include a de-icing distributor (208) for communicating instructions to one or more heating sources (HS) provided at one or more rotary blades (802) 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： 提供了集线器安装的主动振动控制（HAVC）设备，系统和相关方法。 HAVC装置（100）包括具有附接到旋转毂（702）的公差环（600）的壳体（206）。 公差环可以适应不同金属之间的不同的热膨胀系数。 HAVC装置还可以包括多个同轴环电动机（308A，308B，310A，310B），其被配置为旋转多个不平衡块以控制振动。 HAVC系统还可以包括用于将指令传送到设置在车辆或飞行器的一个或多个旋转叶片（802）处的一个或多个加热源（HS）的除冰分配器（208）。 一种控制在移动平台上发生的振动荷载的方法可以包括提供移动平台，将振动控制装置安装到移动平台的一部分，以及旋转至少一对不平衡块，使得组合力基本上消除 平台不必要的振动。

公开(公告)号：US20150097072A1

公开(公告)日：2015-04-09

申请号：US14047182

申请日：2013-10-07

申请人： Sikorsky Aircraft Corporation

发明人： William A. Welch

IPC分类号： B64C27/00 ,  F16F7/10

CPC分类号： B64C27/001 ,  B64C2027/004

摘要： A vibration control actuator includes a housing having a length between ends and a rotatable shaft located in the housing and extending along a housing length and which rotates about a shaft axis substantially parallel to the length. An inertia wheel assembly is operably connected to the rotatable shaft and configured to rotate therewith about the shaft axis. The inertia wheel assembly is in frictional contact with an inner wall of the housing and translatable to travel within the housing between the ends along at least a portion of the shaft axis.

摘要翻译： 振动控制致动器包括壳体，其具有在端部之间的长度和位于壳体中的旋转轴，并且沿着壳体长度延伸并且围绕基本上平行于长度的轴轴线旋转。 惯性轮组件可操作地连接到可旋转轴并构造成围绕轴线随其旋转。 所述惯性轮组件与所述壳体的内壁摩擦接触并且可平移以沿所述轴线的至少一部分在所述壳体内在所述端部之间移动。

公开(公告)号：US20150069173A1

公开(公告)日：2015-03-12

申请号：US14477003

申请日：2014-09-04

申请人： AIRBUS HELICOPTERS

发明人： Paul CRANGA ,  Alain EBERHARD ,  Jonathan RODRIGUEZ ,  Benoit ROGIER

IPC分类号： B64C27/00 ,  F16F15/02

CPC分类号： B64C27/001 ,  B64C2027/002 ,  B64C2027/004 ,  B64C2027/005 ,  F16F15/02

摘要： A suspension device (10) provided with at least one suspension means (20) comprising a flapper (21) performing pendulum motion, the flapper (21) being provided with a mass support (25) supporting at least one flapping mass (30). The mass support (25) is hinged to a carrier structure (2) for isolating and to a holder bar (15) for holding said mechanical assembly. The suspension device (10) includes at least one force generator (70), said suspension device (10) having at least one computer (50) connected to a measurement system (55) measuring the levels of vibration, and to said force generator (70) to regulate said amplitude and said phase actively by controlling the force generator (70) as a function of at least one measurement signal coming from said measurement system (55).

摘要翻译： 具有至少一个悬挂装置（20）的悬挂装置（10）包括执行摆动运动的挡板（21），所述挡板（21）设置有支撑至少一个扑动块（30）的质量支撑件（25）。 质量支撑件（25）铰接到用于隔离的承载结构（2）和用于保持所述机械组件的保持杆（15）。 悬挂装置（10）包括至少一个力发生器（70），所述悬挂装置（10）具有连接到测量振动水平的测量系统（55）的至少一个计算机（50）和所述力发生器 70）通过根据来自所述测量系统（55）的至少一个测量信号控制所述力发生器（70）来主动地调节所述振幅和所述相位。

公开(公告)号：US20140360830A1

公开(公告)日：2014-12-11

申请号：US14231940

申请日：2014-04-01

申请人： Textron Innovations Inc.

发明人： David Heverly ,  David A. Popelka ,  Frank B. Stamps

IPC分类号： B64C27/00

CPC分类号： B64C27/001 ,  B64C11/008 ,  B64C29/0033 ,  B64C2027/003 ,  B64C2027/004

摘要： A vibration attenuator for an aircraft has at least one weight mounted in a rotating system of a rotor hub of the aircraft, each weight being rotatable about an axis of rotation of the hub relative to the hub and to each other weight. Drive means are provided for rotating each weight about the axis of rotation at a selected speed for creating oscillatory shear forces that oppose and attenuate rotor-induced vibrations having a selected frequency. A vertically oriented vibration attenuator is configured to oppose and attenuate vertical rotor induced oscillatory forces that would otherwise travel vertical down the rotor mast and into the airframe. A vibration attenuator having weights rotating about separate axes offset from each other.

摘要翻译： 用于飞行器的振动衰减器具有安装在飞行器的转子轮毂的旋转系统中的至少一个重量，每个重量可围绕毂相对于轮毂的旋转轴线和彼此的重量旋转。 提供驱动装置，用于以选定的速度围绕旋转轴线旋转每个重量，以产生相对于和衰减具有所选频率的转子引起的振动的振荡剪切力。 垂直取向的振动衰减器被配置为抵抗和衰减垂直的转子诱导的振荡力，否则其将沿着转子桅杆向下垂直移动并进入机体。 振动衰减器，其具有围绕彼此偏移的分离轴线旋转的重物。

公开(公告)号：US20140341737A1

公开(公告)日：2014-11-20

申请号：US14124961

申请日：2012-05-25

申请人： Stefan Storm ,  Rudolf Maier ,  Andreas Wildschek

发明人： Stefan Storm ,  Rudolf Maier ,  Andreas Wildschek

IPC分类号： B64C9/00

CPC分类号： B64C9/00 ,  B64C5/08 ,  B64C13/16 ,  B64C2027/004 ,  B64D2045/0085 ,  F16F7/1011 ,  Y02T50/44

摘要： A device for reducing structural vibrations of aerofoils in an aircraft comprises, in the region of the aerfoil tips, at least one force generator (24a) acting substantially in the direction of movement of the vibrations. This arrangement has the advantage that such a force generator (24a) is considerably less susceptible to wear than conventional aerodynamic flaps and therefore effective vibration damping is possible with a reduced outlay on maintenance and greater efficiency.

摘要翻译： 用于减少飞行器中的机翼的结构振动的装置包括在翼型尖端的区域中至少一个作用在振动运动方向上的力发生器（24a）。 这种布置的优点是，这种力发生器（24a）比传统的空气动力襟翼明显不易磨损，因此有效的减振是可能的，同时在维护和降低的效率方面减少了花费。

公开(公告)号：US08090482B2

公开(公告)日：2012-01-03

申请号：US12288867

申请日：2008-10-24

申请人： Mark R. Jolly ,  Askari Badre-Alam ,  Russell E. Altieri ,  Andrew D. Meyers

发明人： Mark R. Jolly ,  Askari Badre-Alam ,  Russell E. Altieri ,  Andrew D. Meyers

IPC分类号： G05D1/00

CPC分类号： B64C27/001 ,  B64C2027/004 ,  B64C2027/005 ,  F16F15/002 ,  F16F15/223

摘要： An aircraft with an aerostructure and at least one rotating machine creating troublesome vibrations, with the aircraft including a power source outputting electromagnetic force generator power outputs, a first and second distributed active vibration electromagnetic force generator, the first and second force generator including a distributed electronic control system and an electromagnetically driven mass, the force generators fixed to the aerostructure at first and second distributed active vibration control system sites, and electrical power distribution lines connecting the force generators with the power source with the power outputs outputted to the electromagnetic force generators, and a distributed force generator data communications network linking together the first and second distributed electronic control systems wherein the distributed electronic control systems communicate force generator vibration control data through the distributed force generator data communications network independently of the electrical power distribution lines to minimize the troublesome vibrations.

摘要翻译： 具有航空结构的飞机和至少一个旋转机器产生麻烦的振动，飞机包括输出电磁力发生器功率输出的电源，第一和第二分布式主动振动电磁力发生器，第一和第二力发生器包括分布式电子 控制系统和电磁驱动质量块，将力发生器固定在第一和第二分布式主动振动控制系统位置处的航空结构，以及将力发生器与电源连接的电力分配线与输出到电磁力发生器的功率输出， 以及将第一和第二分布式电子控制系统连接在一起的分布式力发生器数据通信网络，其中分布式电子控制系统通过分布式力发生器数据通信传递力发生器振动控制数据 独立于电力配电线路以最小化麻烦的振动。

公开(公告)号：US20090254230A1

公开(公告)日：2009-10-08

申请号：US12288867

申请日：2008-10-24

申请人： Mark R. Jolly ,  Askari Badre-Alam ,  Russell E. Altieri ,  Andrew D. Meyers

发明人： Mark R. Jolly ,  Askari Badre-Alam ,  Russell E. Altieri ,  Andrew D. Meyers

IPC分类号： G05B13/02 ,  G06F17/00

CPC分类号： B64C27/001 ,  B64C2027/004 ,  B64C2027/005 ,  F16F15/002 ,  F16F15/223

摘要： An aircraft with at least one rotating machine creating troublesome vibrations, the aircraft comprised of an aerostructure, the aircraft including: a power source, the power source outputting a plurality of electromagnetic force generator power outputs, the aerostructure including a plurality of distributed active vibration control system sites, at least a first distributed active vibration electromagnetic force generator, the first distributed active vibration electromagnetic force generator including a first distributed electronic control system and a first electromagnetically driven mass, the first distributed active vibration electromagnetic force generator fixed to the aerostructure at a first distributed active vibration control system site, at least a second distributed active vibration electromagnetic force generator, the second distributed active vibration electromagnetic force generator including a second distributed electronic control system and a second electromagnetically driven mass, the second distributed active vibration electromagnetic force generator fixed to the aerostructure at a second distributed active vibration control system site, a plurality of electrical power distribution lines, the electrical power distribution lines connecting the electromagnetic force generators with the power source with the electromagnetic force generator power outputs outputted to the electromagnetic force generators, a distributed force generator data communications network, the distributed force generator data communications system network linking together the at least first and second distributed electronic control systems wherein the distributed electronic control systems communicate force generator vibration control data through the distributed force generator data communications network independently of the electrical power distribution lines to minimize the troublesome vibrations.

公开(公告)号：US20090116963A1

公开(公告)日：2009-05-07

申请号：US12352676

申请日：2009-01-13

申请人： William A. Welsh

发明人： William A. Welsh

IPC分类号： B64C27/51 ,  B64C27/32

CPC分类号： F16F15/145 ,  B64C27/001 ,  B64C2027/004 ,  F16F15/36 ,  Y10S416/50

摘要： A method and device for reducing vibratory noise in a system with an integral rotating member includes independently operable drive systems for controlling the angular velocity of at least two independently rotatable masses. Control signals manipulate the drive system to rotate each mass at optimal speed, direction and phase to reduce noise induced in the system by the rotating member.

摘要翻译： 一种用于减小具有整体旋转构件的系统中的振动噪声的方法和装置包括用于控制至少两个可独立旋转的质量块的角速度的独立可操作的驱动系统。 控制信号控制驱动系统以最佳速度，方向和相位旋转每个质量块，以减少由旋转构件在系统中引起的噪音。