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：WO2006135405A3

公开(公告)日：2007-02-22

申请号：PCT/US2005030909

申请日：2005-08-30

Applicant: LORD CORP ,  JOLLY MARK ,  HILDEBRAND STEPHEN ,  ALTIERI RUSSELL ,  IVERS DOUGLAS ,  FERGUSON MATTHEW

Inventor： JOLLY MARK ,  HILDEBRAND STEPHEN ,  ALTIERI RUSSELL ,  IVERS DOUGLAS ,  FERGUSON MATTHEW

IPC: B64C27/00

CPC classification number: F16F15/265 ,  B64C27/001 ,  B64C2027/003 ,  F16F15/22 ,  F16F15/267

Abstract: 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.

Abstract translation: 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。

公开(公告)号：WO2013152300A3

公开(公告)日：2013-12-27

申请号：PCT/US2013035468

申请日：2013-04-05

Applicant: LORD CORP ,  FUHRER ZACHARY ,  JOLLY MARK ,  MARR CONOR

Inventor： FUHRER ZACHARY ,  JOLLY MARK ,  MARR CONOR

IPC: B64C27/51 ,  F16F9/504

CPC classification number: B64C27/51 ,  B64C27/32 ,  F16F9/064 ,  F16F9/20 ,  F16F9/504 ,  F16F13/08 ,  F16F2230/16

Abstract: A method for controlling helicopter ground resonance and air resonance motions as well as centrifugal force switching dampers are disclosed. A helicopter lead-lag damper (30) has a first ground resonance motion damping rate stage (FDR) and a second air resonance motion damping rate stage (SDR). The damper (30) includes a centrifugal force switch (52). The damper (30) is oriented relative to the rotary wing rotation axis (26) and helicopter blade (24). An in-flight rotation rate of the centrifugal force switching damper (30) actuates the centrifugal force switch (52) with the damper switching from the first ground resonance motion damping rate stage (FDR) to the second air resonance motion damping rate stage (SDR).

Abstract translation: 公开了一种用于控制直升机地面共振和空气共振运动的方法以及离心力开关阻尼器。 直升机牵引滞后阻尼器（30）具有第一接地共振运动阻尼速率级（FDR）和第二空气谐振运动阻尼速率级（SDR）。 阻尼器（30）包括离心力开关（52）。 阻尼器（30）相对于旋转翼旋转轴线（26）和直升机叶片（24）定向。 离心力切换阻尼器30的飞行中旋转速度致动离心力开关52，其中阻尼器从第一接地共振运动阻尼率阶段（FDR）切换到第二空气共振运动阻尼速率级（SDR ）。

公开(公告)号：WO2012138816A3

公开(公告)日：2014-05-08

申请号：PCT/US2012032249

申请日：2012-04-05

Applicant: ALLRED CHARLES ,  DOWNING MARSHALL ,  FUHRER ZACHARY ,  JOLLY MARK ,  SMITH MATTHEW ,  LORD CORP

Inventor： ALLRED CHARLES ,  DOWNING MARSHALL ,  FUHRER ZACHARY ,  JOLLY MARK ,  SMITH MATTHEW

IPC: B64C27/35 ,  F16F1/41

CPC classification number: F16C27/06 ,  B64C27/35 ,  F16F1/41 ,  Y10T29/49643

Abstract: Motion control bearings and methods making such with the capability to monitor properties therein is provided. Devices and methods for creating and using motion control bearings for rotary wing aircraft in particular are disclosed using wireless communication and monitoring of multiple load, motion and health related information items related to the bearing and blade at the wing hub. Static and dynamic blade orientation provides additional information on flight regime, thrust vectors, and gross vehicle weight. Power is provided using kinetic energy power harvesting.

Abstract translation: 提供了运动控制轴承和使其具有监控其性能的方法。 特别是用于创建和使用用于旋翼飞机的运动控制轴承的装置和方法公开了使用无线通信和监视与翼中心轴承和叶片相关的多个负载，运动和健康相关信息项。 静态和动态叶片方向提供有关飞行状态，推力矢量和车辆总重量的更多信息。 使用动能收集功率提供动力。

公开(公告)号：WO2011137417A3

公开(公告)日：2011-12-15

申请号：PCT/US2011034719

申请日：2011-05-02

Applicant: JOLLY MARK ,  BLACK PAUL ,  LORD CORP

Inventor： JOLLY MARK ,  BLACK PAUL

IPC: B64C27/00

CPC classification number: B64C27/001 ,  B64C2027/003 ,  B64C2027/004

Abstract: A rotary wing aircraft vehicle vibration control system includes a hub mounted vibration control system. The system includes a sensor for outputting data correlating to relative rotation of the hub rotating about the Z axis relative to the nonrotating body, first sensor outputting first data correlating to vibrations. The system includes first/second nonrotating body force generators fixedly coupled with the helicopter body proximate the transmission and oriented relative to the Z-axis, and a link linking together the force generators and the hub mounted vibration control system wherein such are controlled to produce forces wherein the vibration sensed by the first nonrotating body vibration sensor is reduced.

Abstract translation: 旋翼飞机车辆振动控制系统包括轮毂安装的振动控制系统。 该系统包括用于输出与围绕Z轴相对于非旋转体旋转的轮毂的相对旋转相关的数据的传感器，第一传感器输出与振动相关的第一数据。 该系统包括第一/第二非旋转体力发生器，其与直升机主体固定地相邻于传动装置并相对于Z轴定向;以及将力发生器和轮毂安装的振动控制系统连接在一起的连杆，其中， 其中由所述第一非旋转体振动传感器感测到的振动减小。