专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明申请

US20160072425A1 ACTIVE IMPACT FORCE/TORQUE CONTROL FOR AN ELECTROMECHANICAL ACTUATOR 有权
标题翻译：电动执行器的主动冲击力/扭矩控制
公开(公告)号：US20160072425A1
公开(公告)日：2016-03-10
申请号：US14780344
申请日：2014-05-29
申请人： EATON CORPORATION
发明人： John David Neely , John Mendenhall White
IPC分类号： H02P29/02 , B64C5/08 , B64C13/00 , B64C5/10 , G05D15/01 , G05D17/02
CPC分类号： B64C5/08 , B64C5/10 , B64C13/00 , G05D15/01 , G05D17/02 , H02P5/00 , H02P29/027 , H02P29/032 , H02P29/40
摘要： A system that improves on known systems for reducing output torque by a motor in the event of a jam may include an electromechanical actuator (EMA), a motor configured to drive the EMA and a controller. The controller may be coupled to the motor and configured to receive a speed of the EMA and a position of the EMA. The controller may be further configured to determine whether a jam of the EMA is imminent or is occurring according to the EMA speed, EMA position, and a known range of motion of the EMA, and to provide an input signal to the motor to reduce a torque of the motor if a jam of the EMA is imminent or is occurring.
摘要翻译：在已知系统中改进的用于在发生卡纸时由马达减小输出扭矩的系统可以包括机电致动器（EMA），被配置为驱动EMA的马达和控制器。控制器可以耦合到电动机并且被配置为接收EMA的速度和EMA的位置。控制器还可以被配置为根据EMA速度，EMA位置和EMA的已知运动范围确定EMA的卡纸是否即将发生或正在发生，并且向马达提供输入信号以减少如果EMA堵塞即将发生或正在发生，则电机的转矩。

2. 发明申请

US20170077856A1 THREE-PHASE VARIABLE REFERENCE PULSE WIDTH MODULATION 审中-公开
标题翻译：三相可变参考脉冲宽度调制
公开(公告)号：US20170077856A1
公开(公告)日：2017-03-16
申请号：US15251186
申请日：2016-08-30
申请人： Eaton Corporation
发明人： Sayeed Ahmed Mir , John David Neely , Stan Lawrence Seely , John Mendenhall White
IPC分类号： H02P23/00 , H02P25/03 , H02P27/08
CPC分类号： H02P23/0077 , H02M7/5387 , H02P25/03 , H02P27/04 , H02P27/08 , H02P2209/13
摘要： A system includes a three phase AC or brushless DC motor, an inverter and a controller. The inverter is electrically coupled to the motor. The controller is -electrically coupled to the inverter. The controller is configured to control the inverter to deliver a three phase pulse width modulated voltage to the AC motor, wherein the three phase pulse width modulation comprises a repeating two-cycle pattern.
摘要翻译：系统包括三相交流或无刷直流电动机，逆变器和控制器。逆变器电耦合到电动机。控制器电耦合到逆变器。所述控制器被配置为控制所述逆变器以向AC电动机传送三相脉宽调制电压，其中所述三相脉宽调制包括重复的两周期模式。

3. 发明申请

US20150314852A1 ELECTRONIC FLAP ACTUATION SYSTEM 审中-公开
标题翻译：电子翼片动作系统
公开(公告)号：US20150314852A1
公开(公告)日：2015-11-05
申请号：US14648342
申请日：2013-03-13
申请人： EATON CORPORATION
发明人： John David Neely , Thomas Austen Blair , Peter Anthony Torres
IPC分类号： B64C9/38
CPC分类号： B64C9/38 , B64C13/505
摘要： A flap actuation system for an aircraft can include a first flap panel connected with a first in-board actuator and a first out-board actuator. A first electronic control unit (ECU) can be electrically coupled to and configured to control the first in-board actuator, and a second ECU can be electrically coupled to and configured to control the first out-board actuator. The flap system may further include a second flap panel connected with a second in-board actuator and a second out-board actuator. A third ECU can be electrically coupled to and configured to control the second in-board actuator, and a fourth ECU can be electrically coupled to and configured to control the second out-board actuator.
摘要翻译：用于飞行器的翼片致动系统可以包括与第一板载致动器连接的第一翼片板和第一外板致动器。第一电子控制单元（ECU）可以电耦合到并被配置为控制第一板载致动器，并且第二ECU可以电耦合到并且被配置成控制第一外板致动器。翼片系统还可以包括与第二板载致动器和第二外板致动器连接的第二挡板。第三ECU可以电耦合到并被配置成控制第二板载致动器，并且第四ECU可以电耦合到并被配置成控制第二外侧执行器。

4. 发明授权

US10284129B2 Three-phase variable reference pulse width modulation 有权
公开(公告)号：US10284129B2
公开(公告)日：2019-05-07
申请号：US15251186
申请日：2016-08-30
申请人： Eaton Corporation
发明人： Sayeed Ahmed Mir , John David Neely , Stan Lawrence Seely , John Mendenhall White
IPC分类号： H02P23/00 , H02P25/03 , H02P27/08 , H02P27/04 , H02M7/5387 , H02M7/48
摘要： A system includes a three phase AC or brushless DC motor, an inverter and a controller. The inverter is electrically coupled to the motor. The controller is -electrically coupled to the inverter. The controller is configured to control the inverter to deliver a three phase pulse width modulated voltage to the AC motor, wherein the three phase pulse width modulation comprises a repeating two-cycle pattern.

5. 发明授权

US09988139B2 Fault tolerant electronic control architecture for aircraft actuation system 有权
公开(公告)号：US09988139B2
公开(公告)日：2018-06-05
申请号：US14780328
申请日：2014-05-29
申请人： EATON CORPORATION
发明人： John David Neely , Stanley Lawrence Seely , John Mendenhall White
IPC分类号： B64C13/42 , G05D1/00 , B64C9/16
CPC分类号： B64C13/42 , B64C9/16 , G05D1/0077
摘要： An electronic control architecture for an aircraft actuation system may include a first channel and a second channel. The first channel may be configured to receive one or more inputs comprising a movement command, to produce an output to control a component of the system, and to receive feedback from the component respective of movement of the component. The first channel may comprise a fault detection module configured to compare the feedback to the command to determine if the first channel is functioning properly. The second channel may be configured to receive the one or more inputs and, if the first channel is not functioning properly, to produce an output to control the component.

6. 发明授权

US09758236B2 Active impact force/torque control for an electromechanical actuator 有权
公开(公告)号：US09758236B2
公开(公告)日：2017-09-12
申请号：US14780344
申请日：2014-05-29
申请人： EATON CORPORATION
发明人： John David Neely , John Mendenhall White
IPC分类号： H02P29/032 , B64C5/08 , G05D15/01 , G05D17/02 , H02P29/024 , H02P5/00 , B64C5/10 , B64C13/00 , H02P29/40
CPC分类号： B64C5/08 , B64C5/10 , B64C13/00 , G05D15/01 , G05D17/02 , H02P5/00 , H02P29/027 , H02P29/032 , H02P29/40
摘要： A system that improves on known systems for reducing output torque by a motor in the event of a jam may include an electromechanical actuator (EMA), a motor configured to drive the EMA and a controller. The controller may be coupled to the motor and configured to receive a speed of the EMA and a position of the EMA. The controller may be further configured to determine whether a jam of the EMA is imminent or is occurring according to the EMA speed, EMA position, and a known range of motion of the EMA, and to provide an input signal to the motor to reduce a torque of the motor if a jam of the EMA is imminent or is occurring.

7. 发明申请

US20160068256A1 FAULT TOLERANT ELECTRONIC CONTROL ARCHITECTURE FOR AIRCRAFT ACTUATION SYSTEM 有权
标题翻译：用于飞机执行系统的容错电子控制架构
公开(公告)号：US20160068256A1
公开(公告)日：2016-03-10
申请号：US14780328
申请日：2014-05-29
申请人： EATON CORPORATION
发明人： John David Neely , Stanley Lawrence Seely , John Mendenhall White
IPC分类号： B64C13/42 , G05D1/00
CPC分类号： B64C13/42 , B64C9/16 , G05D1/0077
摘要： An electronic control architecture for an aircraft actuation system may include a first channel and a second channel. The first channel may be configured to receive one or more inputs comprising a movement command, to produce an output to control a component of the system, and to receive feedback from the component respective of movement of the component. The first channel may comprise a fault detection module configured to compare the feedback to the command to determine if the first channel is functioning properly. The second channel may be configured to receive the one or more inputs and, if the first channel is not functioning properly, to produce an output to control the component.
摘要翻译：用于飞行器致动系统的电子控制架构可以包括第一通道和第二通道。第一通道可以被配置为接收包括移动命令的一个或多个输入，以产生用于控制系统的部件的输出，以及接收来自该部件的反馈的部件的运动。第一通道可以包括故障检测模块，其被配置为将反馈与命令进行比较，以确定第一通道是否正常工作。第二通道可以被配置为接收一个或多个输入，并且如果第一通道不能正常工作，则产生用于控制部件的输出。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式