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。

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。

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。

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：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。

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。

公开(公告)号：US20090055129A1

公开(公告)日：2009-02-26

申请号：US12099461

申请日：2008-04-08

申请人： Russell E. Altieri ,  James F. Kuhn ,  Mark R. Jolly ,  Steve C. Southward ,  Askari Badre-Alam ,  Leslie P. Fowler ,  Matthew Ferguson

发明人： Russell E. Altieri ,  James F. Kuhn ,  Mark R. Jolly ,  Steve C. Southward ,  Askari Badre-Alam ,  Leslie P. Fowler ,  Matthew Ferguson

IPC分类号： G01B7/24 ,  G06F15/00

CPC分类号： B64C29/005 ,  B64F5/60 ,  G01B7/31

摘要： Methods and systems for monitoring rotating shaft shafts and couplings in an aircraft propulsion system is described. The measurement system/method provides for accurate and precise monitoring of a rotating shaft flexible coupling in a fixed wing aircraft vehicle propulsion system. The measuring system/method provides for a high reliability short take off vertical landing fixed wing aircraft in which the vertical propulsion dynamically rotating drive shaft system and couplings are monitored in real time. The vehicular shaft coupling misalignment measuring system utilizes multiple positional sensors to provide highly reliable and precise determination of the dynamic characteristics of the rotating sensor target components of the propulsion system drive shaft. The relative position of the sensors is rigidly fixed externally from the rotating targets with a structural frame. The collar misalignment measuring system of the invention provide a misalignment measurement of the propulsion system drive shaft flexible coupling which relates to a critical performance of rotating shaft coupling in the operation of an aircraft vehicle. The method/system provides for monitoring a rotating drive shaft system and dynamically measuring a rotating drive shaft coupling in a fixed wing aircraft propulsion system.

摘要翻译： 描述了用于监测飞行器推进系统中的旋转轴轴和联轴器的方法和系统。 测量系统/方法可以精确和精确地监测固定翼飞机车辆推进系统中的旋转轴柔性联轴器。 测量系统/方法提供了一种高可靠性的短距离垂直着陆固定翼飞机，其中垂直推进动态旋转驱动轴系统和联轴器被实时监控。 车轴联轴器未对准测量系统利用多个位置传感器来提供对推进系统驱动轴的旋转传感器目标部件的动态特性的高度可靠和精确的确定。 传感器的相对位置通过结构框架从旋转目标的外部刚性固定。 本发明的套环未对准测量系统提供了推进系统驱动轴柔性联轴器的不对准测量，其涉及在飞行器车辆的操作中的旋转轴联轴器的关键性能。 该方法/系统提供用于监视旋转驱动轴系统并动态地测量固定翼飞机推进系统中的旋转驱动轴联轴器。

公开(公告)号：US20110204882A1

公开(公告)日：2011-08-25

申请号：US13083647

申请日：2011-04-11

申请人： Russell E. Altieri ,  James F. Kuhn ,  Mark R. Jolly ,  Steve C. Southward ,  Askari Badre-Alam ,  Leslie P. Fowler ,  Matthew Ferguson

发明人： Russell E. Altieri ,  James F. Kuhn ,  Mark R. Jolly ,  Steve C. Southward ,  Askari Badre-Alam ,  Leslie P. Fowler ,  Matthew Ferguson

IPC分类号： G01R33/06

CPC分类号： B64C29/005 ,  B64F5/60 ,  G01B7/31

摘要： Methods/systems for monitoring an aircraft propulsion system is described. The measurement system/method provides for accurate and precise monitoring of rotating members in an aircraft vehicle propulsion system. The measuring system/method provides for a high reliability aircraft in which the propulsion dynamically rotating drive shaft system and couplings are monitored in real time. The vehicular measuring system utilizes multiple positional sensors to provide highly reliable and precise determination of the dynamic characteristics of the rotating sensor target components of the aircraft system. The relative position of the sensors is rigidly fixed externally from the rotating targets with a structural frame. The measuring system provides a misalignment measurement of the propulsion system drive shaft flexible coupling which relates to a critical performance of rotating shaft coupling in the operation of an aircraft vehicle. The method/system provides for monitoring a rotating drive shaft system and dynamically measuring a rotating drive shaft coupling in an aircraft.

摘要翻译： 描述了用于监视飞行器推进系统的方法/系统。 测量系统/方法提供对飞行器车辆推进系统中的旋转构件的准确和精确的监测。 测量系统/方法提供了一种高可靠性飞机，其中推进动态旋转驱动轴系统和联轴器被实时监控。 车辆测量系统利用多个位置传感器来提供对航空器系统的旋转传感器目标部件的动态特性的高度可靠和精确的确定。 传感器的相对位置通过结构框架从旋转目标的外部刚性固定。 测量系统提供推进系统驱动轴柔性联轴器的不对中测量，其涉及在飞行器车辆的操作中旋转轴联轴器的关键性能。 该方法/系统提供用于监测旋转驱动轴系统并动态地测量飞行器中的旋转驱动轴联轴器。

公开(公告)号：US07925392B2

公开(公告)日：2011-04-12

申请号：US12099461

申请日：2008-04-08

申请人： Russell E. Altieri ,  James F. Kuhn ,  Mark R. Jolly ,  Steve C. Southward ,  Askari Badre-Alam ,  Leslie P. Fowler ,  Matthew Ferguson

发明人： Russell E. Altieri ,  James F. Kuhn ,  Mark R. Jolly ,  Steve C. Southward ,  Askari Badre-Alam ,  Leslie P. Fowler ,  Matthew Ferguson

IPC分类号： G01B7/24 ,  G01L3/00 ,  G06F15/00

CPC分类号： B64C29/005 ,  B64F5/60 ,  G01B7/31

摘要： Methods and systems for monitoring rotating shaft shafts and couplings in an aircraft propulsion system is described. The measurement system/method provides for accurate and precise monitoring of a rotating shaft flexible coupling in a fixed wing aircraft vehicle propulsion system. The measuring system/method provides for a high reliability short take off vertical landing fixed wing aircraft in which the vertical propulsion dynamically rotating drive shaft system and couplings are monitored in real time. The vehicular shaft coupling misalignment measuring system utilizes multiple positional sensors to provide highly reliable and precise determination of the dynamic characteristics of the rotating sensor target components of the propulsion system drive shaft. The relative position of the sensors is rigidly fixed externally from the rotating targets with a structural frame. The collar misalignment measuring system of the invention provide a misalignment measurement of the propulsion system drive shaft flexible coupling which relates to a critical performance of rotating shaft coupling in the operation of an aircraft vehicle. The method/system provides for monitoring a rotating drive shaft system and dynamically measuring a rotating drive shaft coupling in a fixed wing aircraft propulsion system.

摘要翻译： 描述了用于监测飞行器推进系统中的旋转轴轴和联轴器的方法和系统。 测量系统/方法可以精确和精确地监测固定翼飞机车辆推进系统中的旋转轴柔性联轴器。 测量系统/方法提供了一种高可靠性的短距离垂直着陆固定翼飞机，其中垂直推进动态旋转驱动轴系统和联轴器被实时监控。 车轴联轴器未对准测量系统利用多个位置传感器来提供对推进系统驱动轴的旋转传感器目标部件的动态特性的高度可靠和精确的确定。 传感器的相对位置通过结构框架从旋转目标的外部刚性固定。 本发明的套环未对准测量系统提供了推进系统驱动轴柔性联轴器的不对准测量，其涉及在飞行器车辆的操作中的旋转轴联轴器的关键性能。 该方法/系统提供用于监视旋转驱动轴系统并动态地测量固定翼飞机推进系统中的旋转驱动轴联轴器。