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1. 发明授权

US07335999B2 Fluid actuated rotating device including a low power generator 失效
标题翻译：流体致动的旋转装置包括低功率发生器
公开(公告)号：US07335999B2
公开(公告)日：2008-02-26
申请号：US10869552
申请日：2004-06-15
申请人： Calvin C. Potter , David M. Eschborn
发明人： Calvin C. Potter , David M. Eschborn
IPC分类号： F03B13/12 , F03B13/00 , H02P9/04
CPC分类号： F03B13/00 , F02C7/27 , F05B2220/602 , F05B2270/404 , F05D2220/62 , F05D2270/44 , H02P9/04 , H02P9/307 , H02P2101/30 , H02P2207/03 , Y02B10/50
摘要： A fluid-powered actuator assembly is modified to include a low power generator. The low power generator rotates in response to a drive force received from the actuator assembly, and thus only generates electrical power when the actuator assembly is operating. The low power generator is used to supply electrical power to various sensors and circuits, which may be used to implement prognostic and health monitoring capabilities for the actuator assembly.
摘要翻译：流体动力致动器组件被修改为包括低功率发生器。低功率发生器响应于从致动器组件接收的驱动力而旋转，并且因此仅在致动器组件操作时产生电力。低功率发生器用于向各种传感器和电路供电，可用于实现致动器组件的预测和健康监测功能。

2. 发明授权

US07251550B2 Aircraft accessory monitor 失效
标题翻译：飞机附件监视器
公开(公告)号：US07251550B2
公开(公告)日：2007-07-31
申请号：US10677567
申请日：2003-10-01
申请人： David M. Eschborn , Paul S. Evans , Casey Hanlon , Calvin C. Potter , Glenn H. Lane , Gary A. Farnsworth , Louie T. Gaines , David M. Mathis
发明人： David M. Eschborn , Paul S. Evans , Casey Hanlon , Calvin C. Potter , Glenn H. Lane , Gary A. Farnsworth , Louie T. Gaines , David M. Mathis
IPC分类号： G06F7/00
CPC分类号： G05B23/0254 , G07C5/008 , G07C5/0825 , G07C5/0858
摘要： Methods and apparatus are provided for monitoring an aircraft accessory. The apparatus comprises a processor associated with said aircraft accessory, a transducer coupled to said processor and operable to produce parametric data relating to said aircraft accessory and a memory coupled to said processor having baseline parametric data residing therein, wherein said baseline parametric data comprises the parametric data obtained during an acceptance test procedure. The method comprises installing a transducer configured to produce parametric data relating to said aircraft accessory, coupling said transducer to a processor associated with said aircraft accessory, coupling said processor to a memory associated with said aircraft accessory, recording baseline parametric data relating to said aircraft accessory in said memory during an acceptance test procedure for said aircraft accessory.
摘要翻译：提供了用于监视飞行器附件的方法和装置。所述设备包括与所述飞行器附件相关联的处理器，耦合到所述处理器并可操作以产生与所述飞行器附件相关的参数数据的传感器和耦合到所述处理器的存储器，其中驻留有驻留参考数据的基准参数数据，其中所述基准参数数据包括参数在验收测试程序中获得的数据。该方法包括安装一个被配置成产生与所述飞行器附件相关的参数数据的换能器，将所述换能器耦合到与所述飞机附件相关联的处理器，将所述处理器耦合到与所述飞行器附件相关联的存储器，记录与所述飞机附件相关的基准参数数据在所述飞机附件的验收测试程序期间在所述存储器中。

3. 发明申请

US20100001678A1 MOTOR CONTROL ARCHITECTURE FOR SIMULTANEOUSLY CONTROLLING MULTIPLE MOTORS 有权
标题翻译：同时控制多台电机的电机控制架构
公开(公告)号：US20100001678A1
公开(公告)日：2010-01-07
申请号：US12167762
申请日：2008-07-03
申请人： Calvin C. Potter , Casey Hanlon , Paul T. Wingett
发明人： Calvin C. Potter , Casey Hanlon , Paul T. Wingett
IPC分类号： G05B19/18
CPC分类号： G05B19/0421 , B64C13/50
摘要： A motor control architecture is provided that simultaneously controls multiple motors. The motor control system includes memory, a plurality of motor control processors, and a communication controller. The motor control processors are each responsive to control signals supplied from the communication controller to selectively retrieve system commands and motor positions from the memory, to generate motor commands, and to supply the generated motor commands to the memory. The communication controller selectively receives system commands and transmits the received system commands to the memory, selectively supplies the command signals to selected ones of the motor control processors, selectively receives motor positions from a plurality of motors, selectively transmits motor positions to the memory, selectively retrieves generated motor commands supplied to the memory, and selectively transmits the retrieved motor commands.
摘要翻译：提供了同时控制多个电机的电机控制架构。电动机控制系统包括存储器，多个电动机控制处理器和通信控制器。电动机控制处理器各自响应于从通信控制器提供的控制信号，以选择性地从存储器检索系统命令和电动机位置，以产生电动机命令，并将生成的电动机命令提供给存储器。通信控制器选择性地接收系统命令并将接收到的系统命令发送到存储器，选择性地将命令信号提供给电动机控制处理器中的选定的一个，选择性地从多个电动机接收电动机位置，选择性地将电动机位置传送到存储器检索提供给存储器的生成的电动机命令，并且选择性地发送所检索的电动机命令。

4. 发明授权

US07610828B2 Flight control surface actuator assembly including a free trial mechanism 有权
标题翻译：飞行控制表面执行器组件包括一个免费试用机制
公开(公告)号：US07610828B2
公开(公告)日：2009-11-03
申请号：US11331755
申请日：2006-01-13
申请人： Paul T. Wingett , Casey Hanlon , Calvin C. Potter
发明人： Paul T. Wingett , Casey Hanlon , Calvin C. Potter
IPC分类号： F16H1/24
CPC分类号： B64C13/503 , B64C13/28 , F16H25/20 , F16H25/2204 , Y10T74/19735
摘要： A flight control surface actuator includes a mechanism that enables the actuator translation member to be selectively decoupled from the actuator rotating member. The actuator includes an actuation member, a translation member, an extension member, and a locking member. The actuation member is adapted to receive a drive force and is configured, in response to the drive force, to rotate and cause the translation member to translate. The extension member surrounds at least a portion of the translation member and is configured to be selectively coupled to, and decoupled from, the translation member. The locking member surrounds at least a portion of the extension tube and is movable between a lock position, in which the locking member couples the extension member to the translation member, and a release position, in which the locking member decouples the extension member from the translation member.
摘要翻译：飞行控制表面致动器包括能够使致动器平移构件与致动器旋转构件选择性地分离的机构。致动器包括致动构件，平移构件，延伸构件和锁定构件。致动构件适于接受驱动力，并且响应于驱动力而构造为旋转并使翻译构件平移。延伸构件围绕平移构件的至少一部分并且被构造成选择性地联接到平移构件并与其平行。锁定构件围绕延伸管的至少一部分，并且可在锁定位置与锁定位置之间移动，锁定构件将延伸构件与平移构件联接在一起，并且释放位置中，锁定构件将延伸构件与翻译会员

5. 发明授权

US07549605B2 Electric flight control surface actuation system for aircraft flaps and slats 有权
标题翻译：用于飞机襟翼和板条的电动飞行控制表面致动系统
公开(公告)号：US07549605B2
公开(公告)日：2009-06-23
申请号：US11192622
申请日：2005-07-29
申请人： Casey Hanlon , Paul T. Wingett , Calvin C. Potter
发明人： Casey Hanlon , Paul T. Wingett , Calvin C. Potter
IPC分类号： B64C13/50
CPC分类号： B64C13/503
摘要： An aircraft flight control surface actuation system includes a plurality of electric motors-driven flap actuators, and a plurality of electric motor-driven slat actuators. The motor-driven actuators receive activation signals from flap and slat actuator controllers and is, in response to the activation signals, move the flaps and slats between stowed and a deployed positions. The flap and slat actuator controllers each include a plurality of independent actuator control channels that independently supply the activation signals to the motor-driven actuators.
摘要翻译：飞机飞行控制表面致动系统包括多个电动马达驱动的翼片致动器和多个电动马达板条致动器。马达驱动的致动器接收来自翼片和板条致动器控制器的启动信号，并且响应于激活信号，在收起和展开位置之间移动翼片和板条。翼片和板条致动器控制器各自包括多个独立的致动器控制通道，其独立地向马达驱动的致动器提供启动信号。

6. 发明申请

US20080156939A1 Active pilot flight control stick system with passive electromagnetic feedback 审中-公开
标题翻译：主动飞行员控制杆系统具有无源电磁反馈
公开(公告)号：US20080156939A1
公开(公告)日：2008-07-03
申请号：US11649011
申请日：2007-01-03
申请人： Casey Hanlon , Calvin C. Potter , Paul T. Wingett , Dean R. Wilkens , Stephen G. Abel
发明人： Casey Hanlon , Calvin C. Potter , Paul T. Wingett , Dean R. Wilkens , Stephen G. Abel
IPC分类号： B64C13/46 , B64C13/04 , H02P23/04 , H02K21/00
CPC分类号： B64C13/507
摘要： A pilot flight control stick haptic feedback mechanism provides variable force feedback to the pilot flight control stick. The flight control stick is movable to a control position in a displacement direction. A motor control unit is operable to selectively supply motor feedback signals to a motor that is coupled to the flight control stick. The motor is responsive to the motor feedback signals to supply a variable feedback force to the flight control stick in a direction that opposes the displacement direction. A passive electromagnetic damping mechanism is electrically coupled to the motor and is at least selectively and passively supplies a non-braking damping force to the flight control stick.
摘要翻译：驾驶员飞行控制杆触觉反馈机构向驾驶员飞行控制杆提供可变的力反馈。飞行控制杆可以在位移方向上移动到控制位置。马达控制单元可操作以选择性地将马达反馈信号提供给耦合到飞行控制杆的马达。电动机响应于电动机反馈信号，以向与该位移方向相反的方向向飞行控制棒提供可变的反馈力。被动电磁阻尼机构电耦合到电动机，并且至少选择性地和被动地向飞行控制棒提供非制动阻尼力。

7. 发明授权

US07119520B2 Energy storage flywheel test control system 失效
标题翻译：储能飞轮测试控制系统
公开(公告)号：US07119520B2
公开(公告)日：2006-10-10
申请号：US10793545
申请日：2004-03-03
申请人： Paul T. Wingett , Sharon K. Brault , George J. Klupar , Calvin C. Potter
发明人： Paul T. Wingett , Sharon K. Brault , George J. Klupar , Calvin C. Potter
IPC分类号： H02P9/00 , H02H3/17
CPC分类号： F03G3/08
摘要： A system and method for removing energy from the rotating group in an energy storage flywheel system during flywheel system testing includes one or more sensors is operable to sense operational parameters of the energy storage flywheel and to supply a sensor signals representative thereof. A primary control circuit is coupled to receive the sensor signals and, in response thereto, selectively supplies a primary brake activation signal to a brake. The brake, in response to the brake activation signal, selectively supplies a brake force to the energy storage flywheel.
摘要翻译：用于在飞轮系统测试期间从能量存储飞轮系统中的旋转组中去除能量的系统和方法包括一个或多个传感器可操作以感测能量存储飞轮的操作参数并且提供代表其的传感器信号。主控制电路被耦合以接收传感器信号，并且响应于此，选择性地向制动器提供初级制动器启动信号。制动器响应于制动器启动信号选择性地向储能飞轮提供制动力。

8. 发明授权

US08015889B2 Ballscrew with an integral high-efficiency thrust bearing 失效
标题翻译：滚珠丝杠带有一体的高效推力轴承
公开(公告)号：US08015889B2
公开(公告)日：2011-09-13
申请号：US11545971
申请日：2006-10-10
申请人： Paul T. Wingett , Calvin C. Potter , Brent L. Bristol , Casey Hanlon , Kellan Geck , Louie T. Gaines
发明人： Paul T. Wingett , Calvin C. Potter , Brent L. Bristol , Casey Hanlon , Kellan Geck , Louie T. Gaines
IPC分类号： F16H25/22
CPC分类号： F16H25/20 , F16C19/08 , F16C33/581 , F16C43/06 , F16H25/2204 , F16H2025/2081 , Y10S384/906 , Y10T74/18576 , Y10T74/19744 , Y10T74/19749
摘要： A linear actuator includes a thrust bearing that is integral to the actuation member. The actuator includes a translation member and an actuation member. The actuation member is responsive to a drive force to rotate. The translation member is configured to translate in response to actuation member. The thrust bearing is coupled to the actuation member and includes an inner race, an outer race, and a plurality of balls. The thrust bearing is configured as a zero lead ballscrew, with the inner race integrally formed on the actuation member, and the plurality of balls disposed between the inner and outer races.
摘要翻译：线性致动器包括与致动构件成一体的止推轴承。致动器包括平移构件和致动构件。致动构件响应于驱动力旋转。翻译构件被配置为响应于致动构件而平移。推力轴承联接到致动构件并且包括内座圈，外座圈和多个球。推力轴承构造为零引线滚珠丝杠，内圈整体形成在致动构件上，并且多个球设置在内圈和外圈之间。

9. 发明申请

US20090072083A1 Actuation system with redundant motor actuators 审中-公开
标题翻译：具有冗余电机执行器的驱动系统
公开(公告)号：US20090072083A1
公开(公告)日：2009-03-19
申请号：US11445876
申请日：2006-06-02
申请人： Casey Hanlon , Calvin C. Potter , Paul T. Wingett , John T. Morris
发明人： Casey Hanlon , Calvin C. Potter , Paul T. Wingett , John T. Morris
IPC分类号： B64C9/00 , H02K16/00
CPC分类号： H02K21/24 , B64C13/505 , H02K16/00 , H02K2213/06
摘要： A multi-redundant motor may be used to implement a relatively small, lightweight redundant actuator assembly package. The motor is implemented as a brushless DC motor and includes N-number of stators and M-number of rotors. Each stator has a plurality of independent stator coils disposed thereon, and N is an integer greater than two. Each permanent magnet rotor is disposed between, and is spaced axially apart from, two of the stators. Each rotor has a plurality of magnetic dipoles disposed thereon, and M is an integer equal to (N−1).
摘要翻译：可以使用多冗余电动机来实现相对较小，重量轻的冗余致动器组件封装。电动机实现为无刷直流电动机，包括N个定子和M个转子。每个定子具有设置在其上的多个独立的定子线圈，并且N是大于2的整数。每个永磁转子设置在两个定子之间，并且与两个定子轴向分开。每个转子具有多个设置在其上的磁偶极子，M是等于（N-1）的整数。

10. 发明授权

US07357093B2 Submarine ejection optimization control system and method 失效
标题翻译：潜艇喷射优化控制系统及方法
公开(公告)号：US07357093B2
公开(公告)日：2008-04-15
申请号：US11170862
申请日：2005-06-30
申请人： Calvin C. Potter , Dennis M. Alexander , Paul T. Wingett
发明人： Calvin C. Potter , Dennis M. Alexander , Paul T. Wingett
IPC分类号： B63G8/28 , B63B1/00
CPC分类号： B63G8/32 , F41F3/10
摘要： A submersible vehicle object ejection control system stores a plurality of pump speed command profiles. Each pump speed command profile is based on vehicle depth, vehicle speed, type of object being ejected, maximum noise emission magnitude during object ejection, and object exit velocity. The system also receives data representative of current vehicle depth, current vehicle speed, and the type of object being ejected. In response to these data, the system retrieves one of the plurality of pump speed command profiles and supplies pump speed commands representative of the retrieved pump speed command profile.
摘要翻译：潜水车辆物体喷射控制系统存储多个泵速度指令轮廓。每个泵速指令轮廓基于车辆深度，车辆速度，被排出的物体的类型，物体喷射期间的最大噪声发射幅度和物体离开速度。该系统还接收代表当前车辆深度，当前车辆速度和被弹出物体的类型的数据。响应于这些数据，系统检索多个泵速指令轮廓中的一个，并提供表示检索的泵速命令轮廓的泵速指令。

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