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

Applicant: LORD CORP ,  MARK R JOLLY ,  BADRE-ALAM ASKARI ,  ALTIERI RUSSELL ,  MEYERS ANDREW D

Inventor： MARK R JOLLY ,  BADRE-ALAM ASKARI ,  ALTIERI RUSSELL ,  MEYERS ANDREW D

CPC classification number: B64C27/001 ,  B64C2027/004 ,  B64C2027/005 ,  F16F15/002 ,  F16F15/223

Abstract: 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.

Abstract translation: 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。

公开(公告)号：WO2011046620A3

公开(公告)日：2011-11-24

申请号：PCT/US2010002764

申请日：2010-10-14

Applicant: LORD CORP ,  WINZENZ WAYNE ,  BOSWELL DAVID ,  BADRE-ALAM ASKARI ,  MORRIS DONALD

Inventor： WINZENZ WAYNE ,  BOSWELL DAVID ,  BADRE-ALAM ASKARI ,  MORRIS DONALD

IPC: B64C11/00

CPC classification number: B64C11/008 ,  F01D25/04 ,  Y10S416/50 ,  Y10T29/4902 ,  Y10T74/2127

Abstract: An aircraft system and method with a first counterweight rotating balancing rotor including holding stepping inboard magnets and outboard mass concentration, and a second counterweight rotating balancing rotor including holding stepping inboard magnets and outboard mass concentration. The system includes an.inboard electromagnetic coil driver with a first inboard electromagnetic coil, and a second inboard electromagnetic coil, the inboard electromagnetic coil driver and the first counterweight balancing rotor and the second counterweight balancing rotor centered around the aircraft propeller shaft rotating machine member with the first inboard electromagnetic coil proximate the first inboard magnets of the first counterweight balancing rotor, with the inboard electromagnetic coil driver proximate the rotation axis of the aircraft propeller shaft rotating machine member and the first counterweight balancing rotor outboard of the inboard electromagnetic coil driver with the first inboard electromagnetic coil generating a electromagnetic field to electromagnetically step the first inboard magnets of the at least first counterweight balancing rotor to electromagnetically actuate rotational movement of the first counterweight balancing rotor around the rotating machine member and relative to the inboard electromagnetic coil driver to a first rotor held balancing position. The second inboard electromagnetic coil is proximate the second counterweight balancing rotor, with the second inboard electromagnetic coil proximate the second inboard magnets of the second counterweight balancing rotor, wherein the second inboard electromagnetic coil generates an electromagnetic field to electromagnetically step the second inboard magnets of the second counterweight balancing rotor to electromagnetically actuate rotational movement of the second counterweight balancing rotor around the rotation axis and relative to the inboard electromagnetic coil driver and to a second rotor held position.

Abstract translation: 一种具有第一配重旋转平衡转子的飞行器系统和方法，包括保持踏板内侧磁体和外侧质量集中，以及包括保持踏板内侧磁体和外侧质量集中的第二配重旋转平衡转子。 该系统包括具有第一内侧电磁线圈的电子线圈驱动器和第二内置电磁线圈，内侧电磁线圈驱动器和第一配重平衡转子和第二配重平衡转子以飞机螺旋桨轴旋转机器构件为中心， 靠近第一配重平衡转子的第一内侧磁体的第一内侧电磁线圈，内侧电磁线圈驱动器靠近飞机驱动轴转动机构的旋转轴线，并且内侧电磁线圈驱动器的第一配重平衡转子外侧与 第一内侧电磁线圈产生电磁场以电磁步进所述至少第一配重平衡转子的第一内侧磁体，以电磁致动第一配重平衡转子围绕旋转机器m的旋转运动 并且相对于内侧电磁线圈驱动器到第一转子保持平衡位置。 第二内侧电磁线圈靠近第二配重平衡转子，其中第二内侧电磁线圈靠近第二对重平衡转子的第二内侧磁体，其中第二内侧电磁线圈产生电磁场以电磁地步进第二内侧磁体 第二配重平衡转子，用于电磁地驱动第二配重平衡转子围绕旋转轴线和相对于内侧电磁线圈驱动器和第二转子保持位置的旋转运动。

公开(公告)号：WO2004094954A3

公开(公告)日：2005-04-21

申请号：PCT/US2004012477

申请日：2004-04-21

Applicant: LORD CORP

Inventor： ALTIERI RUSSELL E ,  KUHN JAMES F ,  JOLLY MARK R ,  SOUTHWARD STEVE C ,  BADRE-ALAM ASKARI ,  FOWLER LESLIE P

IPC: B64C29/00 ,  B64D45/00 ,  B64F5/00 ,  G01B7/31 ,  G06F7/00 ,  G01B7/30 ,  G01D5/243

CPC classification number: G01B7/31 ,  B64C29/005 ,  B64F5/60

Abstract: Methods and systems for monitoring rotating shafts (28) and couplings (30) in an aircraft vehicle propulsion system (22) 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 (22). The measurement system/method provides for a high reliability short take off vertical landing fixed wing aircraft in which the vehicle's dynamically rotating drive shaft system (28) and couplings (30) are monitored in real time. The vehicular shaft coupling misalignment measuring system utilizes multiple positional sensors (40) to provide highly reliable and precise determination of the dynamic characteristics of the rotating sensor target components of the propulsion system drive shaft (28). The relative position of the sensors (40) is rigidly fixed externally from the rotating targets with a structural frame. The misalignment measuring system provides a misalignment measurement of the propulsion system drive shaft flexible coupling which relates to a critical performance of rotating shaft (28) coupling in the operating of an aircraft vehicle (20). 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 (22).

Abstract translation: 描述了用于监视飞行器车辆推进系统（22）中的旋转轴（28）和联轴器（30）的方法和系统。 测量系统/方法提供了对固定翼飞行器车辆推进系统（22）中的旋转轴柔性联轴器的准确和精确的监视。 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，其中车辆的动态旋转驱动轴系统（28）和联轴器（30）被实时监控。 车辆轴联接器未对准测量系统利用多个位置传感器（40）来提供对推进系统驱动轴（28）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（40）的相对位置由具有结构框架的旋转靶材的外部固定地固定。 不对准测量系统提供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（20）的操作中联接的旋转轴（28）的关键性能。 该方法/系统用于监测旋转驱动轴系统并动态地测量固定翼飞行器推进系统（22）中的旋转驱动轴联轴器。

公开(公告)号：WO2009126626A2

公开(公告)日：2009-10-15

申请号：PCT/US2009039773

申请日：2009-04-07

Applicant: LORD CORP ,  JOLLY MARK R ,  MEYERS ANDREW D ,  MELLINGER DANIEL ,  IVERS DOUGLAS E ,  BADRE-ALAM ASKARI ,  SWANSON DOUGLAS A ,  ALTIERI RUSSEL E

Inventor： JOLLY MARK R ,  MEYERS ANDREW D ,  MELLINGER DANIEL ,  IVERS DOUGLAS E ,  BADRE-ALAM ASKARI ,  SWANSON DOUGLAS A ,  ALTIERI RUSSEL E

IPC: B64C27/00

CPC classification number: B64C27/001 ,  B64C2027/003 ,  B64C2027/005

Abstract: 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.

Abstract translation: 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，分布力产生数据 通信网络链路，分布式力产生数据通信系统网络链路至少连接在第一非旋转体圆周力产生器和旋转轮毂安装的振动控制系统之间，其中旋转毂安装的振动控制系统和第一非旋转体圆周力产生器com 通过分布式力产生数据通信网络发出振动控制数据，所述至少第一非旋转体圆周力产生器被控制以产生具有可控旋转力大小和可控旋转力相位的旋转力，所述可控旋转力幅度由 相对于与旋转的旋转旋翼相对于非旋转体的旋转旋翼相对旋转的旋转翼飞行器构件传感器数据来控制可控旋转力相位，其中由 所述至少第一非旋转体振动传感器被减小。

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

Applicant: LORD CORP ,  MARK R JOLLY ,  BADRE-ALAM ASKARI ,  ALTIERI RUSSELL ,  MEYERS ANDREW D

Inventor： MARK R JOLLY ,  BADRE-ALAM ASKARI ,  ALTIERI RUSSELL ,  MEYERS ANDREW D

IPC: B64C27/00

CPC classification number: B64C27/001 ,  B64C2027/004 ,  B64C2027/005 ,  F16F15/002 ,  F16F15/223

Abstract: 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.

Abstract translation: 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。

公开(公告)号：WO2014151420A3

公开(公告)日：2015-03-05

申请号：PCT/US2014025698

申请日：2014-03-13

Applicant: LORD CORP ,  MARGOLIS DONALD L ,  NORRIS MARK A ,  BADRE-ALAM ASKARI ,  OWENS JONATHAN

Inventor： MARGOLIS DONALD L ,  NORRIS MARK A ,  BADRE-ALAM ASKARI ,  OWENS JONATHAN

IPC: F04B47/00 ,  F04B11/00

CPC classification number: F04B49/08 ,  E21B21/00 ,  E21B21/08 ,  F04B11/00 ,  F04B19/22 ,  F04B43/02 ,  F04B49/065 ,  F04B53/14 ,  F04B53/16

Abstract: A pumping system includes an output conduit associated with an output of a positive displacement pump, a first sensor configured to measure a fluid flow characteristic (FFC) within the output conduit, a second sensor configured to measure a phase of the positive displacement pump, a feedforward active controller configured to receive information related to the FFC, receive information related to the phase of the positive displacement pump, and determine an FFC variability value, and a first fluid flow normalizer (FFN) configured to at least one of add fluid to the output of the positive displacement pump and remove fluid from the output of the positive displacement pump in response to a signal from the feedforward active controller.

Abstract translation: 泵送系统包括与正排量泵的输出相关联的输出管道，构造成测量输出管道内的流体流动特性（FFC）的第一传感器，被配置成测量正排量泵的相位的第二传感器， 前馈主动控制器，其被配置为接收与所述FFC相关的信息，接收与所述正排量泵的相位相关的信息，并确定FFC变异性值;以及第一流体流量规定器（FFN），其被配置为将至少一个添加流体 输出正排量泵，并根据来自前馈有效控制器的信号从正排量泵的输出中移出流体。

公开(公告)号：WO2012021202A3

公开(公告)日：2012-07-05

申请号：PCT/US2011038043

申请日：2011-05-26

Applicant: LORD CORP ,  JOLLY MARK ,  MILLER LANE ,  BADRE-ALAM ASKARI

Inventor： JOLLY MARK ,  MILLER LANE ,  BADRE-ALAM ASKARI

IPC: B64C27/80

CPC classification number: B64C27/001 ,  B64C27/008 ,  B64C2027/004

Abstract: Rotary wing aircraft electronic control system including a tachometer (552) and a plurality of nonrotating body vibration control sensors (554) outputting at least first nonrotating body vibration sensor data correlating to vibrations. The system includes a plurality of nonrotating body force generators (530) to input a vibration control force into said nonrotating aerostructure body. The system includes a data communications network link (150) linking together the nonrotating body force generators the tachometer sensor, the vibration control sensors, and an actuating force generator rotor track balance electronic controller (411), the actuating force generator rotor track balance electronic controller including at least a first computer processor with the actuating force generator rotor track controller controlling the nonrotating body force generators to input vibration control forces into the nonrotating aerostructure body and computing a rotor track solution for aircraft rotor blades.

Abstract translation: 旋转翼飞行器电子控制系统包括转速计（552）和多个非旋转体振动控制传感器（554），其输出与振动相关的至少第一非旋转振动传感器数据。 该系统包括多个非旋转体力发生器（530），用于将振动控制力输入到所述非旋转航空结构体中。 该系统包括将非旋转体力发生器，转速计传感器，振动控制传感器和致动力发生器转子轨道平衡电子控制器（411）连接在一起的数据通信网络链路（150），致动力发生器转子轨道平衡电子控制器 包括至少具有致动力发生器转子轨道控制器的第一计算机处理器，其控制非旋转体力发生器以将振动控制力输入到非旋转航空结构体中并计算用于飞行器转子叶片的转子轨道解决方案。

公开(公告)号：WO2010053933A9

公开(公告)日：2010-07-29

申请号：PCT/US2009063193

申请日：2009-11-04

Applicant: LORD CORP ,  BADRE-ALAM ASKARI ,  JANOWSKI MICHAEL D

Inventor： BADRE-ALAM ASKARI ,  JANOWSKI MICHAEL D

IPC: F16F7/10 ,  F16F1/20 ,  F16F1/22 ,  F16F7/116

CPC classification number: F16F7/104 ,  F16F1/185 ,  F16F1/20 ,  F16F3/12 ,  F16F7/1011 ,  F16F15/03 ,  Y10T29/49609

Abstract: A resonant inertial force generator for controlling vibrations of a structure includes a compliant spring comprising a stack of flexures and elastomeric shims in alternating arrangement, a driven inertial mass coupled to the compliant spring to generate a vibration controlling force.

Abstract translation: 用于控制结构振动的谐振惯性力发生器包括柔性弹簧，该柔性弹簧包括交替排列的挠性件和弹性垫片，耦合到柔性弹簧的驱动惯性质量以产生振动控制力。

公开(公告)号：WO2009126608A3

公开(公告)日：2009-12-17

申请号：PCT/US2009039745

申请日：2009-04-07

Applicant: LORD CORP ,  JOLLY MARK R ,  MEYERS ANDREW D ,  MELLINGER DANIEL ,  IVERS DOUGLAS E ,  BADRE-ALAM ASKARI ,  SWANSON DOUGLAS A ,  ALTIERI RUSSELL E

Inventor： JOLLY MARK R ,  MEYERS ANDREW D ,  MELLINGER DANIEL ,  IVERS DOUGLAS E ,  BADRE-ALAM ASKARI ,  SWANSON DOUGLAS A ,  ALTIERI RUSSELL E

IPC: B64C27/00

CPC classification number: B64C27/001 ,  B64C2027/004

Abstract: A vehicle (520) a nonrotating vehicle body (524), a rotating machine member (522), and including a vehicle vibration control system (409), the vehicle vibration control system including a controller (411), a vehicle rotating machine member sensor (552) for inputting vehicle rotating machine member data correlating to the relative rotation of the vehicle rotating machine member rotating relative to the nonrotating vehicle body into the vehicle vibration control system controller, at least a first nonrotating vehicle body vibration sensor (554), for inputting at least first nonrotating vehicle body vibration sensor data correlating to vehicle vibrations into the controller, at least a first nonrotating vehicle body circular force generator (530), fixedly coupled with the nonrotating vehicle body and controlled to produce a rotating force with a controllable rotating force magnitude and a controllable rotating force phase, wherein the vehicle vibration sensed by the at least first nonrotating vehicle body vibration sensor is reduced.

Abstract translation: 车辆（520），非旋转车体（524），旋转机械部件（522），并且包括车辆振动控制系统（409），所述车辆振动控制系统包括控制器（411），车辆旋转机构传感器 （552），用于将与所述车辆旋转机构相对于所述非旋转动力车身旋转的相对旋转相关的车辆旋转机构部件数据输入到所述车辆振动控制系统控制器中，至少第一非旋转车体振动传感器（554），其用于 将与车辆振动相关的至少第一非旋转车身振动传感器数据输入到所述控制器中，至少第一非旋转车体圆周力产生器（530），其与所述非旋转车体固定地联接并被控制以产生具有可控旋转的旋转力 力大小和可控旋转力相位，其中由至少第一非线性感测的车辆振动 车身振动传感器减少。

公开(公告)号：WO2015195664A3

公开(公告)日：2016-03-10

申请号：PCT/US2015036029

申请日：2015-06-16

Applicant: LORD CORP

Inventor： NORRIS MARK A ,  BADRE-ALAM ASKARI ,  EDEAL DAVID ,  O'NEIL DANIEL ,  MEYERS ANDREW D

IPC: F16F15/00 ,  B60K1/00 ,  B60P3/00 ,  E21B43/26 ,  F16F15/18

CPC classification number: E21B43/26 ,  E21B17/073 ,  E21B47/00 ,  F04B11/00 ,  F04B19/22 ,  F04B23/00 ,  F04B49/065 ,  F16F15/002 ,  F16F15/18

Abstract: Systems and methods are disclosed herein that include providing an active torsion damper control system that includes a rotatable component (206) and a rotatable measurement interface (302) disposed on the rotatable component, the rotatable measurement interface having at least one torsional strain gauge configured to measure a strain of the rotatable component, a torque management (306) computer configured to determine a resonant frequency of the rotatable component and a corrective torque needed to be applied to the rotatable component to excite the resonant frequency as a function of the measured strain, and a correction motor (308) configured to impart the corrective torque on the rotatable component.

Abstract translation: 本文公开的系统和方法包括提供主动扭力阻尼器控制系统，其包括可旋转部件（206）和设置在可旋转部件上的可旋转测量接口（302），所述可旋转测量接口具有至少一个扭转应变计，其被配置为 测量可旋转部件的应变;扭矩管理（306）计算机，其被配置为确定可旋转部件的共振频率以及需要施加到可旋转部件以根据所测量的应变激发谐振频率的校正扭矩， 以及校正马达（308），其被配置为将所述校正扭矩赋予所述可旋转部件。