-
公开(公告)号：US08272592B2
公开(公告)日：2012-09-25
申请号：US12640149
申请日：2009-12-17
IPC分类号： B64C11/00
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。
-
公开(公告)号：US07686246B2
公开(公告)日：2010-03-30
申请号：US11942381
申请日：2007-11-19
IPC分类号： B64C11/00
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。
-
公开(公告)号：US10308354B2
公开(公告)日：2019-06-04
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： G01C23/00 , G05D1/00 , G05D3/00 , G06F7/00 , G06F17/00 , B64C27/00 , F16F7/10 , 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.
-
公开(公告)号：US09404549B2
公开(公告)日：2016-08-02
申请号：US12774184
申请日：2010-05-05
CPC分类号： F16F7/104 , F16F1/185 , F16F1/20 , F16F3/12 , F16F7/1011 , F16F15/03 , Y10T29/49609
摘要： An electromagnetic inertial actuator includes a support base and a parallel arrangement of a first flexure part, a voice coil motor part, and a second flexure part. The parallel arrangement is cantilevered from the support base.
摘要翻译： 电磁惯性致动器包括支撑基座和第一弯曲部分，音圈电机部分和第二挠曲部分的平行布置。 平行布置是从支撑基座悬臂的。
-
公开(公告)号：US20120269626A1
公开(公告)日：2012-10-25
申请号：US13273341
申请日：2011-10-14
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。
-
公开(公告)号：US20110197703A1
公开(公告)日：2011-08-18
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
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。
-
公开(公告)号：US20110033310A1
公开(公告)日：2011-02-10
申请号：US12774184
申请日：2010-05-05
CPC分类号： F16F7/104 , F16F1/185 , F16F1/20 , F16F3/12 , F16F7/1011 , F16F15/03 , Y10T29/49609
摘要： An electromagnetic inertial actuator includes a support base and a parallel arrangement of a first flexure part, a voice coil motor part, and a second flexure part. The parallel arrangement is cantilevered from the support base.
摘要翻译： 电磁惯性致动器包括支撑基座和第一弯曲部分，音圈电机部分和第二挠曲部分的平行布置。 平行布置是从支撑基座悬臂的。
-
公开(公告)号：US20080179451A1
公开(公告)日：2008-07-31
申请号：US11942381
申请日：2007-11-19
IPC分类号： B64C11/00
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。
-
公开(公告)号：US20070233329A1
公开(公告)日：2007-10-04
申请号：US11224563
申请日：2005-09-12
申请人： Russell Altieri , James Kuhn , Mark Jolly , Steve Southward , Askari Badre-Alam , Leslie Fowler
发明人： Russell Altieri , James Kuhn , Mark Jolly , Steve Southward , Askari Badre-Alam , Leslie Fowler
IPC分类号： G05D1/00
CPC分类号： G01B7/31 , B64C29/005 , B64F5/60
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。
-
-
-
-
-
-
-
-
搜索结果
29 条记录 (耗时 0.049 秒)
