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    Aircraft propeller balancing system
    4.
    发明授权
    Aircraft propeller balancing system 有权
    飞机螺旋桨平衡系统

    公开(公告)号：US08961140B2

    公开(公告)日：2015-02-24

    申请号：US13273341

    申请日：2011-10-14

    申请人： Askari Badre-Alam ,  David Boswell ,  Donald Morris ,  Wayne Lee Winzenz

    发明人： Askari Badre-Alam ,  David Boswell ,  Donald Morris ,  Wayne Lee Winzenz

    IPC分类号： B64C11/08 ,  F01D25/04 ,  B64C11/00

    CPC分类号： B64C11/008 ,  F01D25/04 ,  Y10S416/50 ,  Y10T29/49332

    摘要： An aircraft system and method with a first counterweight rotating balancing rotor mass concentration, and a second counterweight rotating balancing rotor mass concentration to balance a first aircraft propeller. 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. The system/method utilizes a first control system controller to control the coils and position the mass concentrations to balance the first aircraft propeller. The system/method includes a third counterweight rotating balancing rotor mass concentration, and a fourth counterweight rotating balancing rotor mass concentration to balance a second aircraft propeller which positioned and controlled by a second control system controller.

    摘要翻译： 一种具有第一配重旋转平衡转子质量浓度的飞行器系统和方法，以及用于平衡第一飞行器螺旋桨的第二配重旋转平衡转子质量集中。 该系统包括具有第一内侧电磁线圈的内侧电磁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以飞行器传动轴转动机构为中心的第二配重平衡转子。 系统/方法利用第一控制系统控制器来控制线圈并定位质量浓度以平衡第一飞机螺旋桨。 该系统/方法包括第三配重旋转平衡转子质量浓度，以及第四配重旋转平衡转子质量浓度以平衡由第二控制系统控制器定位和控制的第二飞行器螺旋桨。

    HELICOPTER VIBRATION CONTROL SYSTEM AND CIRCULAR FORCE GENERATION SYSTEMS FOR CANCELING VIBRATIONS
    5.
    发明申请
    HELICOPTER VIBRATION CONTROL SYSTEM AND CIRCULAR FORCE GENERATION SYSTEMS FOR CANCELING VIBRATIONS 有权
    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。

    AIRCRAFT VEHICULAR PROPULSION SYSTEM MONITORING DEVICE AND METHOD
    6.
    发明申请
    AIRCRAFT VEHICULAR PROPULSION SYSTEM MONITORING DEVICE AND METHOD 失效
    飞机车辆推进系统监控装置及方法

    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。

    Method and system for controlling helicopter vibrations
    7.
    发明申请
    Method and system for controlling helicopter vibrations 有权
    控制直升机振动的方法和系统

    公开(公告)号：US20060054738A1

    公开(公告)日：2006-03-16

    申请号：US11149514

    申请日：2005-06-10

    申请人： Askari Badre-Alam ,  Douglas Swansor ,  Jeffrey Cranmer

    发明人： Askari Badre-Alam ,  Douglas Swansor ,  Jeffrey Cranmer

    IPC分类号： B64C27/00

    CPC分类号： F16F7/1011 ,  B64C27/001 ,  B64C2027/005

    摘要： A method/system for controlling helicopter vibrations is provided that includes a vibration canceling force generator for actively generating a vibration canceling force. The system includes a resonant actuator having a natural resonant frequency and a resonant actuator electronic control system. The resonant actuator electronic control system provides an electrical drive current to the resonant actuator to drive the resonant actuator about the resonant frequency when commanded by a received command signal. The resonant actuator has a feedback output with the feedback output fed back into the resonant actuator electronic control system wherein the resonant actuator electronic control system adjusts the electrical drive current based on the resonant actuator feedback output to generate the vibration canceling force.

    摘要翻译： 提供一种用于控制直升机振动的方法/系统，其包括用于主动产生振动消除力的振动消除力发生器。 该系统包括具有固有谐振频率的谐振致动器和谐振致动器电子控制系统。 当由接收到的命令信号命令时，谐振致动器电子控制系统向谐振致动器提供电驱动电流以围绕谐振频率驱动谐振致动器。 谐振致动器具有反馈输出，反馈输出反馈到谐振致动器电子控制系统中，其中谐振致动器电子控制系统基于谐振致动器反馈输出来调节电驱动电流以产生振动消除力。

    Aircraft propeller balancing system
    8.
    发明授权
    Aircraft propeller balancing system 有权
    飞机螺旋桨平衡系统

    公开(公告)号：US08961139B2

    公开(公告)日：2015-02-24

    申请号：US12925138

    申请日：2010-10-14

    申请人： Askari Badre-Alam ,  David Boswell ,  Donald Morris ,  Wayne Winzenz

    发明人： Askari Badre-Alam ,  David Boswell ,  Donald Morris ,  Wayne Winzenz

    IPC分类号： B64C11/08 ,  F01D25/04 ,  B64C11/00

    CPC分类号： B64C11/008 ,  F01D25/04 ,  Y10S416/50 ,  Y10T29/4902 ,  Y10T74/2127

    摘要： An aircraft system/method for propeller balancing. The system includes an inboard driver with a first and second inboard electromagnetic coil, the inboard 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.

    摘要翻译： 一种用于螺旋桨平衡的飞机系统/方法。 该系统包括内部驱动器，其具有第一和第二内侧电磁线圈，内侧驱动器和第一配重平衡转子和第二配重平衡转子以飞行器螺旋桨轴旋转机器构件为中心，第一内侧电磁线圈靠近第一内侧磁体 第一配重平衡转子的内侧电磁线圈驱动器靠近飞机螺旋桨轴旋转机构的旋转轴线，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 将所述至少第一配重平衡转子的第一内侧磁体逐步地电磁致动所述第一配重平衡转子围绕所述旋转机械构件并相对于所述内侧电磁线圈驱动器到第一r otor保持平衡位置。

    ROTARY WING AIRCRAFT VIBRATION CONTROL SYSTEM WITH RESONANT INERTIAL ACTUATORS
    10.
    发明申请
    ROTARY WING AIRCRAFT VIBRATION CONTROL SYSTEM WITH RESONANT INERTIAL ACTUATORS 审中-公开
    具有谐振惯性执行器的旋转式飞机振动控制系统

    公开(公告)号：US20130311012A1

    公开(公告)日：2013-11-21

    申请号：US13983463

    申请日：2012-02-03

    申请人： Paul Black ,  Doug Swanson ,  Askari Badre-Alam ,  David Edeal ,  Douglas Pedersen

    发明人： Paul Black ,  Doug Swanson ,  Askari Badre-Alam ,  David Edeal ,  Douglas Pedersen

    IPC分类号： B64C27/00 ,  H02K33/00 ,  H02P25/02

    CPC分类号： B64C27/001 ,  B64C2027/004 ,  F16F7/1011 ,  H02K33/00 ,  H02P25/032

    摘要： A control system for resonant inertial actuators estimates operating parameters of the resonant inertial actuators based on voltage and current feedback and dynamically limits selected parameters to maintain the safe, efficient, and cost effective operation of the resonant inertial actuators. Resistance within the electrical drives for the resonant inertial actuators is estimated from the voltage and current feedback and in conjunction with the modeling of the resonant inertial actuators other operating parameters are calculated or otherwise estimated. Having regard for the responsiveness of the resonant inertial actuators to changes in command signals, the command signals are adjusted to dynamically limit the estimated parameters.

    摘要翻译： 谐振惯性致动器的控制系统基于电压和电流反馈来估计谐振惯性致动器的运行参数，并且动态地限制所选择的参数以维持谐振惯性致动器的安全，有效和成本有效的操作。 根据电压和电流反馈来估计谐振惯性致动器的电驱动器内的电阻，并结合谐振惯性致动器的建模，计算或估计其他操作参数。 考虑到谐振惯性致动器对指令信号变化的响应性，调整指令信号以动态地限制估计的参数。