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1. 发明申请

WO2014113114A2 HUB-MOUNTED ACTIVE VIBRATION CONTROL (HAVC) DEVICES, SYSTEMS, AND METHODS 审中-公开
标题翻译： HUB安装的主动振动控制（HAVC）设备，系统和方法
公开(公告)号：WO2014113114A2
公开(公告)日：2014-07-24
申请号：PCT/US2013/066381
申请日：2013-10-23
申请人： LORD CORPORATION , JOLLY, Mark R. , ALTIERI, Russell E. , WINZENZ, Wayne L. , BRANNAN, Warren F. , BLACK, Paul R. , SWANSON, Doug A.
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
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装置包括具有连接到旋转轮毂的公差环的壳体。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，其被配置为旋转多个不平衡块以控制振动。 HAVC系统还可以包括除冰分配器，用于将指令传达到设置在车辆或飞行器的一个或多个旋转叶片处的一个或多个加热源。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。

2. 发明申请

WO2014074831A2 IMPROVED SLIP RING DEVICES, SYSTEMS, AND METHODS 审中-公开
标题翻译：改进的滑环设备，系统和方法
公开(公告)号：WO2014074831A2
公开(公告)日：2014-05-15
申请号：PCT/US2013069167
申请日：2013-11-08
申请人： LORD CORP , ALTIERI RUSSELL E , JOLLY MARK R , BRANNAN WARREN F , MORRIS JR DONALD R , TRULL MICHAEL W , MARTIN RICHARD
发明人： ALTIERI RUSSELL E , JOLLY MARK R , BRANNAN WARREN F , MORRIS JR DONALD R , TRULL MICHAEL W , MARTIN RICHARD
IPC分类号： H01R39/24 , B64C27/32 , B64D15/12
CPC分类号： H01R39/08 , B64C27/32 , B64D15/12 , G01R31/04 , G01R31/327 , H01R39/24 , H02J5/005 , H04B5/0037
摘要： Improvements to slip rings and methods for the operation thereof include an improved slip ring assembly that has a stationary element, a rotating element rotatable with respect to the stationary element, a bearing assembly coupled between the stationary element and the rotating element, and one or more contact brushes on one of the stationary element or the rotating element. In some embodiments, the bearing assembly includes a primary bearing, a secondary bearing, a shear pin coupling the secondary bearing to the primary bearing, and an electrical monitoring circuit in communication with the shear pin. In some embodiments, the one or more contact brushes includes one or more metal fiber brushes constructed of a plurality of metal fibers that are configured to transmit one or more of electrical power or data between the stationary element and the rotating element.
摘要翻译：滑环的改进及其操作方法包括改进的滑环组件，其具有固定元件，可相对于静止元件旋转的旋转元件，联接在固定元件和旋转元件之间的轴承组件，以及一个或多个接触刷在固定元件或旋转元件之一上。在一些实施例中，轴承组件包括主轴承，次轴承，将次轴承连接到主轴承的剪切销以及与剪切销连通的电监控电路。在一些实施例中，一个或多个接触刷包括由多个金属纤维构成的一个或多个金属纤维刷，所述多个金属纤维构造成在固定元件和旋转元件之间传输电力或数据中的一个或多个。

3. 发明申请

WO2009055007A2 DISTRIBUTED ACTIVE VIBRATION CONTROL SYSTEMS AND ROTARY WING AIRCRAFT WITH SUPPRESSED VIBRATIONS 审中-公开
标题翻译：分布式主动振动控制系统和具有抑制振动的旋转式飞机
公开(公告)号：WO2009055007A2
公开(公告)日：2009-04-30
申请号：PCT/US2008012081
申请日：2008-10-24
申请人： LORD CORP , MARK R JOLLY , BADRE-ALAM ASKARI , ALTIERI RUSSELL , MEYERS ANDREW D
发明人： MARK R JOLLY , BADRE-ALAM ASKARI , ALTIERI RUSSELL , MEYERS ANDREW D
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 actiye 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.
摘要翻译：一种具有至少一个旋转机器的飞机产生麻烦的振动，该飞行器由航空结构组成，飞行器包括：电源，电源输出多个电磁力发生器功率输出，该航空结构包括多个分布式动力学振动控制系统站点，至少第一分布式主动振动电磁力发生器，所述第一分布式主动振动电磁力发生器包括第一分布式电子控制系统和第一电磁驱动质量块，所述第一分布式主动振动电磁力发生器固定在所述空气结构第一分布式主动振动控制系统现场，至少第二分布式主动振动电磁力发生器，所述第二分布式主动振动电磁力发生器包括第二分布式电子控制系统和第二电磁第二分布式主动振动电磁力发生器在第二分布式主动振动控制系统现场固定到航空结构，多个电力分配线，电力分配线将电磁力发生器与电源连接，电磁输出到电磁力发生器的力发电机功率输出，分布式力发生器数据通信网络，分布式力发生器数据通信系统网络将至少第一和第二分布式电子控制系统连接在一起，其中分布式电子控制系统将力发电机振动控制数据通过分布式力发生器数据通信网络独立于电力配电线路，以尽量减少麻烦的振动。

4. 发明申请

WO2008127362A2 AIRCRAFT WITH TRANSIENT-DISCRIMINATING PROPELLER BALANCING SYSTEM 审中-公开
标题翻译：具有瞬时分辨螺旋桨平衡系统的飞机
公开(公告)号：WO2008127362A2
公开(公告)日：2008-10-23
申请号：PCT/US2007/081101
申请日：2007-10-11
申请人： LORD CORPORATION , HILDEBRAND, Steve , ALTIERI, Russell , WINZENZ, Wayne
发明人： HILDEBRAND, Steve , ALTIERI, Russell , WINZENZ, Wayne
IPC分类号： B64C11/00 , G01M1/38
CPC分类号： B64C11/008 , G01M1/36
摘要： A system for balancing an aircraft propeller system receives a vibration signal from the aircraft propeller system and determines whether the vibration signal indicates a transient vibration condition. If it is determined that the vibration signal does not indicate a transient condition, the system enables a balance correction controller. The controller generates a balance correction signal based on the vibration signal, and balances the aircraft propeller system in response to the balance correction signal if the balance correction controller is enabled.
摘要翻译：用于平衡飞行器螺旋桨系统的系统从飞行器螺旋桨系统接收振动信号，并确定振动信号是否表示瞬时振动条件。如果确定振动信号不表示瞬态状态，则系统启用平衡校正控制器。控制器基于振动信号产生平衡校正信号，并且如果平衡校正控制器被使能，则平衡飞行器螺旋桨系统以响应平衡校正信号。

5. 发明申请

WO2006135405A3 HELICOPTER VIBRATION CONTROL SYSTEM AND ROTARY FORCE GENERATOR FOR CANCELING VIBRATIONS 审中-公开
标题翻译：直升机振动控制系统和旋转发电机取消振动
公开(公告)号：WO2006135405A3
公开(公告)日：2007-02-22
申请号：PCT/US2005030909
申请日：2005-08-30
申请人： LORD CORP , JOLLY MARK , HILDEBRAND STEPHEN , ALTIERI RUSSELL , IVERS DOUGLAS , FERGUSON MATTHEW
发明人： JOLLY MARK , HILDEBRAND STEPHEN , ALTIERI RUSSELL , IVERS DOUGLAS , FERGUSON MATTHEW
IPC分类号： B64C27/00
CPC分类号： F16F15/265 , B64C27/001 , B64C2027/003 , F16F15/22 , F16F15/267
摘要： A helicopter rotating hub mounted vibration control system (20) for a helicopter rotary wing hub (22) having a periodic vibration (24) while rotating at a helicopter operational rotation frequency (26) . The helicopter rotating hub mounted vibration control system (20) includes an annular ring rotary housing (30) attachable to the helicopter rotary wing hub (22) and rotating with the helicopter rotary wing hub (22) at the helicopter operational rotation frequency (26) . The annular ring housing is centered about the rotary wing hub axis of rotation and has an electronics housing cavity subsystem (32) and preferably an adjacent coaxial rotor housing cavity subsystem (34) . The rotor housing cavity subsystem (34) contains a first coaxial frameless AC ring motor (36) having a first rotor with a first imbalance mass (40) and a second coaxial frameless AC ring motor (42) having a second rotor with a second imbalance mass (46) . The electronics housing cavity subsystem (32) contains an electronics control system (50) which receives sensor outputs and electrically controls and drives the first coaxial frameless AC ring motor (36) and the second coaxial frameless AC ring motor (42) such that the first imbalance mass (40) and the second imbalance mass (46) are directly driven at a vibration canceling rotation frequency (52) greater than the helicopter operational rotation frequency wherein the helicopter rotary wing hub periodic vibration (24) is reduced.
摘要翻译：一种用于在直升机操作旋转频率（26）旋转的同时具有周期性振动（24）的直升机旋转翼形轮毂（22）的直升机旋转轮毂安装的振动控制系统（20）。直升机旋转轮毂安装的振动控制系统（20）包括环形环旋转壳体（30），其可连接到直升机旋转翼毂（22）并且以直升机操作旋转频率（26）与直升机旋转翼毂（22）一起旋转，。环形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空腔子系统（32），并且优选地是相邻的同轴转子壳体空腔子系统（34）。转子壳体腔子系统（34）包含第一同轴无框架AC环形电动机（36），其具有具有第一不平衡块（40）的第一转子和具有第二不平衡的第二转子的第二同轴无框架AC环形电动机（42）质量（46）。电子设备壳体腔子系统（32）包含电子控制系统（50），其接收传感器输出并电控制并驱动第一同轴无框架AC环形电动机（36）和第二同轴无框架AC环形电动机（42），使得第一不平衡质量（40）和第二不平衡质量（46）以大于直升机旋转翼毂周期性振动（24）减小的直升机操作旋转频率的减振旋转频率（52）直接驱动。

6. 发明申请

WO2014092975A1 IMPROVED CIRCULAR FORCE GENERATOR DEVICES, SYSTEMS, AND METHODS FOR USE IN AN ACTIVE VIBRATION CONTROL SYSTEM 审中-公开
标题翻译：改进的循环发电机装置，系统和用于主动振动控制系统的方法
公开(公告)号：WO2014092975A1
公开(公告)日：2014-06-19
申请号：PCT/US2013/071452
申请日：2013-11-22
申请人： LORD CORPORATION , BLACK, Paul, R. , SWANSON, Doug, A. , BADRE-ALAM, Askari , JANOWSKI, Michael, D. , ALTIERI, Russell, E. , MEYERS, Andrew, D. , RYU, Jihan
发明人： BLACK, Paul, R. , SWANSON, Doug, A. , BADRE-ALAM, Askari , JANOWSKI, Michael, D. , ALTIERI, Russell, E. , MEYERS, Andrew, D. , RYU, Jihan
IPC分类号： B64C27/00 , F16F15/22
CPC分类号： B64C27/001 , B64C2027/004 , F16F7/1011
摘要： Improved circular force generator devices (100), systems, and methods for use in an active vibration control system are disclosed. The present subject matter can include improved rotary actuator devices, systems, and methods in which a center shaft (120) is positioned in a fixed relationship with respect to a component housing (114). At least one movable body can be positioned in the component housing and rotatably coupled to the center shaft by a radial bearing (130), the at least one movable body comprising a motor (110) and at least one eccentric mass (150). With this configuration, the motor can be configured to cause rotation of the movable body about the center shaft to produce a rotating force with a controllable rotating force magnitude and a controllable rotating force phase.
摘要翻译：公开了用于主动振动控制系统的改进的圆周力发生装置（100），系统和方法。本主题可以包括改进的旋转致动器装置，系统和方法，其中中心轴（120）相对于部件壳体（114）以固定关系定位。至少一个可移动体可以被定位在部件壳体中并且通过径向轴承（130）可旋转地联接到中心轴，所述至少一个可移动体包括马达（110）和至少一个偏心质量块（150）。利用这种构造，马达可以构造成使可动体围绕中心轴旋转以产生具有可控旋转力大小和可控旋转力相位的旋转力。

7. 发明申请

WO2014074831A3 IMPROVED SLIP RING DEVICES, SYSTEMS, AND METHODS 审中-公开
公开(公告)号：WO2014074831A3
公开(公告)日：2014-05-15
申请号：PCT/US2013/069167
申请日：2013-11-08
申请人： LORD CORPORATION , ALTIERI, Russell E. , JOLLY, Mark R. , BRANNAN, Warren F. , MORRIS, Jr., Donald R. , TRULL, Michael W. , MARTIN, Richard
发明人： ALTIERI, Russell E. , JOLLY, Mark R. , BRANNAN, Warren F. , MORRIS, Jr., Donald R. , TRULL, Michael W. , MARTIN, Richard
IPC分类号： H01R39/24 , B64D15/12 , B64C27/32
摘要： Improvements to slip rings (200) and methods for the operation thereof include an improved slip ring assembly (200) that has a stationary element (202), a rotating element (210) rotatable with respect to the stationary (202) element, a bearing assembly coupled between the stationary element (202) and the rotating element (210), and one or more contact brushes (213) on one of the stationary element (202) or the rotating element (210). In some embodiments, the bearing assembly includes a primary bearing, a secondary bearing, a shear pin coupling the secondary bearing to the primary bearing, and an electrical monitoring circuit (206) in communication with the shear pin. In some embodiments, the one or more contact brushes (213) includes one or more metal fiber brushes constructed of a plurality of metal fibers that are configured to transmit one or more of electrical power or data between the stationary element (202) and the rotating element (210).

8. 发明申请

WO2009055007A3 DISTRIBUTED ACTIVE VIBRATION CONTROL SYSTEMS AND ROTARY WING AIRCRAFT WITH SUPPRESSED VIBRATIONS 审中-公开
标题翻译：分布式主动振动控制系统和具有抑制振动的旋转式飞机
公开(公告)号：WO2009055007A3
公开(公告)日：2009-07-30
申请号：PCT/US2008012081
申请日：2008-10-24
申请人： LORD CORP , MARK R JOLLY , BADRE-ALAM ASKARI , ALTIERI RUSSELL , MEYERS ANDREW D
发明人： MARK R JOLLY , BADRE-ALAM ASKARI , ALTIERI RUSSELL , MEYERS ANDREW D
IPC分类号： B64C27/00
CPC分类号： B64C27/001 , B64C2027/004 , B64C2027/005 , F16F15/002 , F16F15/223
摘要： An aircraft (20) with at least one rotating machine (22) including: a power source (26), outputting a plurality of electromagnetic force generator power outputs, an aerostructure (24) including a plurality of distributed actiye vibration control system sites, at least a first distributed active vibration electromagnetic force generator (30), including a first distributed electronic control system (32) and a first electromagnetically driven mass (34), the first force generator fixed to the aerostructure at a first site (28), at least a second distributed active vibration electromagnetic force generator including a second distributed electronic control system and a second electromagnetically driven mass, the second force generator fixed to the aerostructure at a second site, a plurality of electrical power distribution lines (40), connecting the electromagnetic force generators with the power source-with the power outputs outputted to the electromagnetic force generators, a distributed force generator data communications network (50) linking together the at least first. and second distributed electronic control systems wherein the 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：一种具有至少一个旋转机器（22）的飞机（20），包括：输出多个电磁力发生器功率输出的电源（26），包括多个分布式活动振动控制系统位置的航空结构（24），至少一个第一分布式主动振动电磁力发生器（30），其包括第一分布式电子控制系统（32）和第一电磁驱动质量块（34），所述第一力发生器在第一位置（28）处固定到所述航空结构，至少一个第二分布式主动振动电磁力发生器，其包括第二分布式电子控制系统和第二电磁驱动质量块，所述第二力发生器固定在第二场所的航空结构，多个配电线路（40）具有电源的力发生器 - 输出到电磁力发生器的功率输出，分布式f 所述发电机数据通信网络（50）至少连接在一起。以及第二分布式电子控制系统，其中控制系统通过分布式力发生器数据通信网络与电力分配线路独立地传递力发生器振动控制数据，以最小化麻烦的振动。

9. 发明申请

WO2009055007A9 DISTRIBUTED ACTIVE VIBRATION CONTROL SYSTEMS AND ROTARY WING AIRCRAFT WITH SUPPRESSED VIBRATIONS 审中-公开
公开(公告)号：WO2009055007A9
公开(公告)日：2009-04-30
申请号：PCT/US2008/012081
申请日：2008-10-24
申请人： LORD CORPORATION , MARK, R. Jolly , BADRE-ALAM, Askari , ALTIERI, Russell , MEYERS, Andrew, D.
发明人： MARK, R. Jolly , BADRE-ALAM, Askari , ALTIERI, Russell , MEYERS, Andrew, D.
IPC分类号： B64C27/00
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 actiye 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.

10. 发明申请

WO2008127362A3 AIRCRAFT WITH TRANSIENT-DISCRIMINATING PROPELLER BALANCING SYSTEM 审中-公开
标题翻译：具有瞬时分辨螺旋桨平衡系统的飞机
公开(公告)号：WO2008127362A3
公开(公告)日：2008-12-18
申请号：PCT/US2007081101
申请日：2007-10-11
申请人： LORD CORP , HILDEBRAND STEVE , ALTIERI RUSSELL , WINZENZ WAYNE
发明人： HILDEBRAND STEVE , ALTIERI RUSSELL , WINZENZ WAYNE
IPC分类号： B64C11/00 , G01M1/38
CPC分类号： B64C11/008 , G01M1/36
摘要： A system (10) for balancing an aircraft propeller (12) system receives a vibration signal from the aircraft propeller system and determines whether the vibration signal indicates a transient vibration condition. If it is determined that the vibration signal does not indicate a transient condition, the system enables a balance correction controller (5). The controller generates a balance correction signal based on the vibration signal, and balances the aircraft propeller system in response to the balance correction signal if the balance correction controller is enabled.
摘要翻译：用于平衡飞行器螺旋桨（12）系统的系统（10）从飞机螺旋桨系统接收振动信号，并确定振动信号是否表示瞬时振动状态。如果确定振动信号不表示瞬时状态，则系统启用平衡校正控制器（5）。控制器基于振动信号产生平衡校正信号，并且如果平衡校正控制器被使能，则平衡飞行器螺旋桨系统以响应平衡校正信号。

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