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1. 发明申请

US20150321753A1 CIRCULAR FORCE GENERATOR DEVICES, SYSTEMS, AND METHODS FOR USE IN AN ACTIVE VIBRATION CONTROL SYSTEM 审中-公开
标题翻译：用于主动振动控制系统的循环发电机装置，系统和方法
公开(公告)号：US20150321753A1
公开(公告)日：2015-11-12
申请号：US14647700
申请日：2013-11-22
申请人： Paul R. BLACK , Doug A. SWANSON , Askari BADRE-ALAM , Michael D. JANOWSKI , Russell E. ALTIERI , Andrew D. MEYERS , Jihan RYU , LORD CORPORATION
发明人： Paul R. BLACK , Doug A. SWANSON , Askari BADRE-ALAM , Michael D. JANOWSKI , Russell E. ALTIERI , Andrew D. MEYERS , Jihan RYU
IPC分类号： B64C27/00 , F16F7/10
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。

2. 发明授权

US08162606B2 Helicopter hub mounted vibration control and circular force generation systems for canceling vibrations 有权
标题翻译：直升机轮毂安装的振动控制和圆形力产生系统，用于消除振动
公开(公告)号：US08162606B2
公开(公告)日：2012-04-24
申请号：US12419775
申请日：2009-04-07
申请人： Mark R. Jolly , Andrew D. Meyers , Daniel Mellinger , Douglas E. Ivers , Askari Badre-Alam , Douglas A. Swanson , Russell E. Altieri
发明人： Mark R. Jolly , Andrew D. Meyers , Daniel Mellinger , Douglas E. Ivers , Askari Badre-Alam , Douglas A. Swanson , Russell E. Altieri
IPC分类号： F04D29/26 , F01D5/26 , B64C11/00
CPC分类号： B64C27/001 , B64C2027/003 , F16F15/22 , G05D19/02 , Y10S416/50
摘要： A rotary wing aircraft including a vehicle vibration control system. The vehicle vibration control system includes a rotating hub mounted vibration control system, the rotating hub mounted vibration control system mounted to the rotating rotary wing hub with the rotating hub mounted vibration control system rotating with the rotating rotary wing hub. The vehicle vibration control system includes a rotary wing aircraft member sensor for outputting rotary wing aircraft member data correlating to the relative rotation of the rotating rotary wing hub member rotating relative to the nonrotating body, at least a first nonrotating body vibration sensor, the at least first nonrotating body vibration sensor outputting at least first nonrotating body vibration sensor data correlating to vibrations, at least a first nonrotating body circular force generator, the at least a first nonrotating body circular force generator fixedly coupled with the nonrotating body, and a distributed force generation data communications network link.
摘要翻译：一种包括车辆振动控制系统的旋翼飞机。车辆振动控制系统包括旋转轮毂安装的振动控制系统，旋转轮毂安装的振动控制系统安装到旋转的旋翼轮毂上，旋转轮毂安装的振动控制系统与旋转的旋翼轮毂一起旋转。车辆振动控制系统包括旋转翼飞行器构件传感器，用于输出与旋转的旋翼轮毂构件相对于非旋转体相对旋转相关的旋转翼飞行器构件数据，至少第一非旋转体振动传感器，至少第一非旋转体振动传感器，至少输出与振动相关的第一非旋转体振动传感器数据，至少第一非旋转体圆周力产生器，与所述非旋转体固定连接的所述至少第一非旋转体圆周力产生器，以及分布力产生数据通信网络链接。

3. 发明授权

US08435002B2 Helicopter vibration control system and rotating assembly rotary forces generators for canceling vibrations 有权
标题翻译：直升机振动控制系统和旋转组件旋转力发生器，用于消除振动
公开(公告)号：US08435002B2
公开(公告)日：2013-05-07
申请号：US12637174
申请日：2009-12-14
申请人： Mark R. Jolly , Andrew D. Meyers
发明人： Mark R. Jolly , Andrew D. Meyers
IPC分类号： F01D5/10
CPC分类号： B64C27/001 , B64C2027/003 , F04D27/02 , F04D29/662 , F16F15/223
摘要： A rotary blade rotating hub mounted rotating assembly vibration control system including a first imbalance mass concentration rotor, a second imbalance mass concentration rotor, a third imbalance mass concentration rotor, and a fourth imbalance mass concentration rotor. The first imbalance mass concentration rotor has a first imbalance mass concentration rotor center axis rotation centered on the rotating assembly center rotation axis. The second imbalance mass concentration rotor has a second imbalance mass concentration rotor center axis rotation centered on the rotating assembly center rotation axis. The third imbalance mass concentration rotor has a third imbalance mass concentration rotor center axis rotation centered on the rotating assembly center rotation axis. The fourth imbalance mass concentration rotor has a fourth imbalance mass concentration rotor center axis rotation centered on the rotating assembly center rotation axis. The first and second imbalance mass concentration rotors are driven at a first rotation speed greater than the rotating assembly operational rotation frequency while controlling the rotational position of the first imbalance mass concentration and the second imbalance mass concentration to produce a first rotating net force vector to inhibit a first vibration frequency. The third and fourth imbalance mass concentration rotors are driven at a second rotation speed greater than the rotating assembly operational rotation frequency while controlling the rotational position of the third imbalance mass concentration and the fourth imbalance mass concentration to produce a second rotating net force vector to inhibit a second vibration frequency.
摘要翻译：一种旋转叶片旋转轮毂安装的旋转组件振动控制系统，包括第一不平衡质量浓度转子，第二不平衡质量浓度转子，第三不平衡质量浓度转子和第四不平衡质量浓度转子。第一不平衡质量浓度转子具有以旋转组件中心旋转轴为中心的第一不平衡质量浓度转子中心轴线旋转。第二不平衡质量浓度转子具有以旋转组件中心旋转轴为中心的第二不平衡质量浓度的转子中心轴旋转。第三不平衡质量浓度转子具有以转动组件中心旋转轴为中心的第三不平衡质量浓度转子中心轴旋转。第四不平衡质量浓度转子具有以旋转组件中心旋转轴为中心的第四不平衡质量浓度转子中心轴旋转。第一和第二不平衡质量浓度转子以大于旋转组件操作旋转频率的第一旋转速度被驱动，同时控制第一不平衡质量浓度和第二不平衡质量浓度的旋转位置，以产生第一旋转净力向量以抑制第一振动频率。第三和第四不平衡质量浓度转子以大于旋转组件操作旋转频率的第二旋转速度被驱动，同时控制第三不平衡质量浓度和第四不平衡质量浓度的旋转位置，以产生第二旋转净力向量来抑制第二振动频率。

4. 发明申请

US20120158217A1 DISTRIBUTED ACTIVE VIBRATION CONTROL SYSTEMS AND ROTARY WING AIRCRAFT WITH SUPPRESSED VIBRATIONS 有权
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：US20120158217A1
公开(公告)日：2012-06-21
申请号：US13333196
申请日：2011-12-21
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 , H02K15/00
CPC分类号： B64C27/001 , B64C2027/004 , B64C2027/005 , F16F15/002 , F16F15/223
摘要： A method and system is disclosed for controlling problematic vibrations in an aircraft having. The method and system have the ability to cancel problematic rotary wing helicopter vibrations using independent active force generator power and with distributed communications therebetween.
摘要翻译：公开了一种用于控制飞机中有问题的振动的方法和系统。该方法和系统具有使用独立的主动力发生器功率并且在其间具有分布式通信来消除有问题的旋转翼直升机振动的能力。

5. 发明申请

US20100034655A1 HELICOPTER HUB MOUNTED VIBRATION CONTROL AND CIRCULAR FORCE GENERATION SYSTEMS FOR CANCELING VIBRATIONS 有权
公开(公告)号：US20100034655A1
公开(公告)日：2010-02-11
申请号：US12419775
申请日：2009-04-07
申请人： Mark R. JOLLY , Andrew D. MEYERS , Daniel MELLINGER , Douglas E. IVERS , Askari BADRE-ALAM , Douglas A. SWANSON , Russell E. ALTIERI
发明人： Mark R. JOLLY , Andrew D. MEYERS , Daniel MELLINGER , Douglas E. IVERS , Askari BADRE-ALAM , Douglas A. SWANSON , Russell E. ALTIERI
IPC分类号： B64C27/32 , B63H3/08
CPC分类号： B64C27/001 , B64C2027/003 , F16F15/22 , G05D19/02 , Y10S416/50
摘要： A rotary wing aircraft including a vehicle vibration control system. The vehicle vibration control system includes a rotating hub mounted vibration control system, the rotating hub mounted vibration control system mounted to the rotating rotary wing hub with the rotating hub mounted vibration control system rotating with the rotating rotary wing hub. The vehicle vibration control system includes a rotary wing aircraft member sensor for outputting rotary wing aircraft member data correlating to the relative rotation of the rotating rotary wing hub member rotating relative to the nonrotating body, at least a first nonrotating body vibration sensor, the at least first nonrotating body vibration sensor outputting at least first nonrotating body vibration sensor data correlating to vibrations, at least a first nonrotating body circular force generator, the at least a first nonrotating body circular force generator fixedly coupled with the nonrotating body, a distributed force generation data communications network link, the distributed force generation data communications system network link linking together at least the first nonrotating body circular force generator and the rotating hub mounted vibration control system wherein the rotating hub mounted vibration control system and the first nonrotating body circular force generator communicate force generation vibration control data through the distributed force generation data communications network, the at least first nonrotating body circular force generator controlled to produce a rotating force with a controllable rotating force magnitude and a controllable rotating force phase, the controllable rotating force magnitude controlled from a minimal force magnitude up to a maximum force magnitude, and with the controllable rotating force phase controlled in reference to the rotary wing aircraft member sensor data correlating to the relative rotation of the rotating rotary wing hubrotating relative to the nonrotating body wherein the vibration sensed by the at least first nonrotating body vibration sensor is reduced.

6. 发明申请

US20120136533A1 HELICOPTER VIBRATION CONTROL SYSTEM AND CIRCULAR FORCE GENERATION SYSTEMS FOR CANCELING VIBRATIONS 有权
标题翻译：直升机振动控制系统和消除振动的循环发电系统
公开(公告)号：US20120136533A1
公开(公告)日：2012-05-31
申请号：US12971026
申请日：2010-12-17
申请人： Mark R. Jolly , Andrew D. Meyers , Daniel Mellinger , Douglas E. Ivers , Askari Badre-Alam , Douglas A. Swanson , Russell E. Altieri
发明人： Mark R. Jolly , Andrew D. Meyers , Daniel Mellinger , Douglas E. Ivers , Askari Badre-Alam , Douglas A. Swanson , Russell E. Altieri
IPC分类号： G06F19/00 , G05D15/00 , B64C27/473 , G05D19/00 , F16F7/00 , F16F7/10
CPC分类号： B64C27/001 , B64C2027/003 , F16F15/22 , G05D19/02 , Y10S416/50
摘要： A rotary wing aircraft including a vehicle vibration control system. The vehicle vibration control system includes a rotary wing aircraft member sensor for outputting rotary wing aircraft member data correlating to the relative rotation of the rotating rotary wing hub member rotating relative to the nonrotating body, at least a first nonrotating body vibration sensor, the at least first nonrotating body vibration sensor outputting at least first nonrotating body vibration sensor data correlating to vibrations, at least a first nonrotating body circular force generator, the at least a first nonrotating body circular force generator fixedly coupled with the nonrotating body, the at least first nonrotating body circular force generator controlled to produce a rotating force with a controllable rotating force magnitude and a controllable rotating force phase, the controllable rotating force magnitude controlled from a minimal force magnitude up to a maximum force magnitude, and with the controllable rotating force phase controlled in reference to the rotary wing aircraft member sensor data correlating to the relative rotation of the rotating rotary wing hub rotating relative to the nonrotating body wherein the vibration sensed by the at least first nonrotating body vibration sensor is reduced.
摘要翻译：一种包括车辆振动控制系统的旋翼飞机。车辆振动控制系统包括旋转翼飞行器构件传感器，用于输出与旋转的旋翼轮毂构件相对于非旋转体相对旋转相关的旋转翼飞行器构件数据，至少第一非旋转体振动传感器，至少至少第一非旋转体圆周力产生器，至少第一非旋转体圆周力产生器，其与所述非旋转体固定连接，所述至少第一非旋转体振动传感器，至少第一非旋转体振动传感器，至少第一非旋转体振动传感器，主体圆形力发生器被控制以产生具有可控旋转力量级和可控旋转力相位的旋转力，可控旋转力量值从最小力量控制到最大力量值，并且可控旋转力相位被控制在参考旋转翼型飞行器构件传感器数据与旋转的旋转翼型轮毂相对于非旋转体相对旋转，其中由至少第一非旋转体振动传感器感测的振动减小。

7. 发明授权

US08639399B2 Distributed active vibration control systems and rotary wing aircraft with suppressed vibrations 有权
标题翻译：具有抑制振动的分布式主动振动控制系统和旋翼飞机
公开(公告)号：US08639399B2
公开(公告)日：2014-01-28
申请号：US13333196
申请日：2011-12-21
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： A method and system is disclosed for controlling problematic vibrations in an aircraft having. The method and system have the ability to cancel problematic rotary wing helicopter vibrations using independent active force generator power and with distributed communications therebetween.
摘要翻译：公开了一种用于控制飞机中有问题的振动的方法和系统。该方法和系统具有使用独立的主动力发生器功率并且在其间具有分布式通信来消除有问题的旋转翼直升机振动的能力。

8. 发明授权

US06296093B1 Vibration-damped machine and control method therefor 失效
标题翻译：减振机及其控制方法
公开(公告)号：US06296093B1
公开(公告)日：2001-10-02
申请号：US09188654
申请日：1998-11-09
申请人： Mark A. Norris , Andrew D. Meyers , Donald L. Margolis
发明人： Mark A. Norris , Andrew D. Meyers , Donald L. Margolis
IPC分类号： F16F710
CPC分类号： F16F7/1005 , B23Q11/0032 , B25J19/0091 , G05B19/404 , G05D19/02 , Y10T409/304312
摘要： A vibration-damped machine and method including beam being capable of gross movements in space relative to a stationary frame, means including a motor for causing the beam's gross movements; the gross movements tending to induce vibration into the beam, sensors for providing a signal representative of the induced beam vibration, an linear-acting inertial actuator mounted to the beam, and control means for receiving the signal and generating an output signal to actively drive the linear-acting inertial actuator at the appropriate phase, frequency and magnitude to damp induced beam vibrations. Embodiments of the vibration-damped machine are illustrated for a gantry robot, a horizontal machining center, an adhesive dispenser and a pivoting robot. The linear-acting inertial actuator is preferably controlled according to an inertial damping control method where the actuator is forced to behave as a damper attached to ground.
摘要翻译：一种振动阻尼机器和方法，包括能够相对于静止框架在空间中大体移动的梁，包括用于引起梁的粗大运动的电机的装置; 趋向于引起振动进入梁的总运动，用于提供表示感应波束振动的信号的传感器，安装到波束的线性作用惯性致动器以及用于接收信号并产生输出信号的主动驱动线性作用惯性致动器在适当的相位，频率和幅度以减弱感应的波束振动。振动阻尼机器的实施例示出了龙门机器人，卧式加工中心，粘合剂分配器和枢转机器人。线性惯性致动器优选地根据惯性阻尼控制方法来控制，其中致动器被迫作为附接到地面的阻尼器。

9. 发明申请

US20150321752A1 VIBRATION DAMPING DEVICES, SYSTEMS, AND METHODS FOR AIRCRAFT 审中-公开
标题翻译：用于飞机的振动阻尼装置，系统和方法
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。

10. 发明授权

US09073627B2 Helicopter vibration control system and circular force generation systems for canceling vibrations 有权
标题翻译：直升机振动控制系统和用于消除振动的圆形力产生系统
公开(公告)号：US09073627B2
公开(公告)日：2015-07-07
申请号：US12971026
申请日：2010-12-17
申请人： Mark R. Jolly , Andrew D. Meyers , Daniel Mellinger , Douglas E. Ivers , Askari Badre-Alam , Douglas A. Swanson , Russell E. Altieri
发明人： Mark R. Jolly , Andrew D. Meyers , Daniel Mellinger , Douglas E. Ivers , Askari Badre-Alam , Douglas A. Swanson , Russell E. Altieri
IPC分类号： G06F19/00 , G05D15/00 , G05D19/00 , B64C27/00 , F16F15/22
CPC分类号： B64C27/001 , B64C2027/003 , F16F15/22 , G05D19/02 , Y10S416/50
摘要： A rotary wing aircraft including a vehicle vibration control system. The vehicle vibration control system includes a rotary wing aircraft member sensor for outputting rotary wing aircraft member data correlating to the relative rotation of the rotating rotary wing hub member rotating relative to the nonrotating body, at least a first nonrotating body vibration sensor, the at least first nonrotating body vibration sensor outputting at least first nonrotating body vibration sensor data correlating to vibrations, at least a first nonrotating body circular force generator, the at least a first nonrotating body circular force generator fixedly coupled with the nonrotating body, the at least first nonrotating body circular force generator controlled to produce a rotating force with a controllable rotating force magnitude and a controllable rotating force phase, the controllable rotating force magnitude controlled from a minimal force magnitude up to a maximum force magnitude, and with the controllable rotating force phase controlled in reference to the rotary wing aircraft member sensor data correlating to the relative rotation of the rotating rotary wing hub rotating relative to the nonrotating body wherein the vibration sensed by the at least first nonrotating body vibration sensor is reduced.
摘要翻译：一种包括车辆振动控制系统的旋翼飞机。车辆振动控制系统包括旋转翼飞行器构件传感器，用于输出与旋转的旋翼轮毂构件相对于非旋转体相对旋转相关的旋转翼飞行器构件数据，至少第一非旋转体振动传感器，至少至少第一非旋转体圆周力产生器，至少第一非旋转体圆周力产生器，其与所述非旋转体固定连接，所述至少第一非旋转体振动传感器，至少第一非旋转体振动传感器，至少第一非旋转体振动传感器，主体圆形力发生器被控制以产生具有可控旋转力量级和可控旋转力相位的旋转力，可控旋转力量值从最小力量控制到最大力量值，并且可控旋转力相位被控制在参考旋转翼型飞行器构件传感器数据与旋转的旋转翼型轮毂相对于非旋转体相对旋转，其中由至少第一非旋转体振动传感器感测的振动减小。

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