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1. 发明申请

US20070108343A1 Flight control surface actuator assembly including a free trail mechanism 有权
标题翻译：飞行控制表面执行器组件包括自由轨道机构
公开(公告)号：US20070108343A1
公开(公告)日：2007-05-17
申请号：US11331755
申请日：2006-01-13
申请人： Paul Wingett , Casey Hanlon , Calvin Potter
发明人： Paul Wingett , Casey Hanlon , Calvin Potter
IPC分类号： B64C13/28
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

2. 发明申请

US20060289696A1 Electric flight control surface actuation system for aircraft flaps and slats 有权
公开(公告)号：US20060289696A1
公开(公告)日：2006-12-28
申请号：US11192622
申请日：2005-07-29
申请人： Casey Hanlon , Paul Wingett , Calvin Potter
发明人： Casey Hanlon , Paul Wingett , Calvin Potter
IPC分类号： B64C3/00
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.

3. 发明申请

US20060255207A1 Flight control surface actuation system with redundantly configured actuator assemblies 审中-公开
标题翻译：具有冗余配置的执行器组件的飞行控制表面致动系统
公开(公告)号：US20060255207A1
公开(公告)日：2006-11-16
申请号：US11193059
申请日：2005-07-28
申请人： Paul Wingett , Calvin Potter , Casey Hanlon , Dwayne Benson
发明人： Paul Wingett , Calvin Potter , Casey Hanlon , Dwayne Benson
IPC分类号： B64C13/00
CPC分类号： B64C13/00 , B64C13/341 , B64C13/504 , B64C13/505
摘要： A flight control surface actuator assembly includes a plurality of flight control surface actuators, and a pivot arm. Each flight control surface actuator is adapted to couple to a flight control surface, and each is further adapted to receive a drive force and is operable, upon receipt thereof, to move between at least an extended position and a retracted position. The pivot arm is rotationally coupled to, and is configured to pivot relative to, each of the flight control surface actuators, the pivot arm is also adapted to be rotationally coupled to, and configured to pivot relative to, a static airframe structure.
摘要翻译：飞行控制表面致动器组件包括多个飞行控制表面致动器和枢转臂。每个飞行控制表面致动器适于联接到飞行控制表面，并且每个飞行控制表面致动器进一步适于接收驱动力，并且在其接收时可操作以在至少延伸位置和缩回位置之间移动。枢转臂旋转地联接到每个飞行控制表面致动器并被构造成相对于每个飞行控制表面致动器枢转，枢转臂还适于旋转地联接到静止的机身结构并且被构造成相对于静止的机身结构枢转。

4. 发明申请

US20080018282A1 Component position determination circuit using a brushless DC motor commutation sensor 有权
标题翻译：组件位置确定电路采用无刷直流电机换向传感器
公开(公告)号：US20080018282A1
公开(公告)日：2008-01-24
申请号：US11481356
申请日：2006-07-05
申请人： Calvin Potter , Casey Hanlon , Paul Wingett
发明人： Calvin Potter , Casey Hanlon , Paul Wingett
IPC分类号： H02P7/00
CPC分类号： H02P6/14 , G05B2219/37171 , G05B2219/41321 , Y10S388/901
摘要： A position determination circuit uses the commutation sensor of a brushless DC motor to determine the position of an actuator and/or actuated component 125. The commutation sensor supplies a rotational position signal representative of the rotational position of the motor to a pulse generator. The pulse generator generates a pulse each time the rotational position signal represents a complete revolution of the brushless DC motor. The generated pulses are supplied to an integrator circuit, which selectively supplies a position signal having a voltage magnitude representative of the position of the actuator and/or component.
摘要翻译：位置确定电路使用无刷直流电机的换向传感器来确定致动器和/或致动部件125的位置。换向传感器将表示电机的旋转位置的旋转位置信号提供给脉冲发生器。每当旋转位置信号表示无刷直流电动机的完整转动时，脉冲发生器产生脉冲。产生的脉冲被提供给积分器电路，积分器电路选择性地提供具有代表致动器和/或部件的位置的电压幅度的位置信号。

5. 发明申请

US20070235594A1 Pilot flight control stick feedback system 审中-公开
标题翻译：飞行员控制杆反馈系统
公开(公告)号：US20070235594A1
公开(公告)日：2007-10-11
申请号：US11400251
申请日：2006-04-06
申请人： Paul Wingett , Calvin Potter , Casey Hanlon
发明人： Paul Wingett , Calvin Potter , Casey Hanlon
IPC分类号： B64C13/46
CPC分类号： B64C13/02 , B64C13/345 , B64C13/507 , G05G9/047 , G05G2009/04707 , G05G2009/04766
摘要： A pilot flight control stick haptic feedback mechanism provides variable force feedback to the pilot flight control stick based on actual aircraft conditions. The flight control stick is movable to a control position in a displacement direction. A control unit receives one or more signals representative of aircraft conditions and, in response thereto, selectively supplies a variable force feedback signal. A magnetic bearing is disposed adjacent at least a portion of the flight control stick, and is responsive to the variable force feedback signal to supply a variable magnetic feedback force to the flight control stick in a direction that opposes the displacement direction.
摘要翻译：驾驶员飞行控制杆触觉反馈机构根据实际飞机状况向飞行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。控制单元接收代表飞行器状况的一个或多个信号，并响应于此选择性地提供可变力反馈信号。磁性轴承设置在飞行控制杆的至少一部分附近，并且响应于可变力反馈信号，以向与该位移方向相反的方向向飞行控制杆提供可变的磁反馈力。

6. 发明申请

US20070109082A1 Power drive unit electromagnetic latch 失效
标题翻译：电源驱动单元电磁锁
公开(公告)号：US20070109082A1
公开(公告)日：2007-05-17
申请号：US11433118
申请日：2006-05-12
申请人： Calvin Potter , Casey Hanlon , Paul Wingett
发明人： Calvin Potter , Casey Hanlon , Paul Wingett
IPC分类号： H01H73/48
CPC分类号： H02K7/106 , H02K7/06 , H02K49/106
摘要： A no-back device for a power drive unit is configured such that, during operation of the power drive unit, the no-back device does not supply magnetic or frictional force against power drive unit rotation. The no-back device is implemented either redundantly or no-redundantly, and includes a latch rotor and an electromagnet. In both embodiments, the latch rotor is coupled to the power drive unit to rotate therewith, and the electromagnet is coupled to receive a flow of current and, upon receipt thereof, generates a magnetic field force that opposes rotation of the latch rotor. In the redundant embodiment, the no-back device further includes one or more permanent magnets, and the magnetic field generated by the electromagnet selectively opposes or aids the magnetic field supplied by the permanent magnet(s).
摘要翻译：用于动力驱动单元的无背装置被配置为使得在动力驱动单元的操作期间，无返回装置不向动力驱动单元旋转提供磁力或摩擦力。无背装置被冗余或不冗余地实现，并且包括闩锁转子和电磁体。在两个实施例中，闩锁转子联接到动力驱动单元以与其一起旋转，并且电磁体被联接以接收电流，并且在其接收时产生与闩锁转子的旋转相对的磁场力。在冗余实施例中，无背装置还包括一个或多个永磁体，并且由电磁体产生的磁场选择性地与由永磁体提供的磁场相反或有助于其提供的磁场。

7. 发明申请

US20070108342A1 Reconfigurable flight control surface actuation system and method 审中-公开
标题翻译：可重构飞行控制面驱动系统及方法
公开(公告)号：US20070108342A1
公开(公告)日：2007-05-17
申请号：US11387583
申请日：2006-03-23
申请人： Casey Hanlon , Paul Wingett , Calvin Potter
发明人： Casey Hanlon , Paul Wingett , Calvin Potter
IPC分类号： B64C13/02
CPC分类号： B64C13/505 , B64C13/506
摘要： A flight control surface actuation system, and the method implemented thereby, prevents an asymmetric secondary flight control surface deploy situation in the unlikely event one or more of the secondary flight control surfaces becomes inoperable. The system includes a control unit that receives one or more signals representative of operability of each of the secondary flight control surfaces. In response to these signal, the control unit determines the operability of each of the flight control surfaces and, upon determining that a flight control surface on one of the aircraft wings is inoperable, automatically moves, or inhibits movement of, one or more symmetric flight control surfaces on the other aircraft wing.
摘要翻译：飞行控制表面致动系统以及由此实施的方法防止在不太可能的情况下一个或多个次要飞行控制表面变得不可操作的不对称次级飞行控制表面部署情况。该系统包括控制单元，其接收代表每个次要飞行控制表面的可操作性的一个或多个信号。响应于这些信号，控制单元确定每个飞行控制表面的可操作性，并且在确定飞机机翼之一上的飞行控制表面不能操作时，自动地移动或阻止一个或多个对称飞行控制其他飞机机翼上的表面。

8. 发明申请

US20060055259A1 Fault-tolerant magnetic bearing position sensing and control system 审中-公开
标题翻译：容错磁轴承位置检测和控制系统
公开(公告)号：US20060055259A1
公开(公告)日：2006-03-16
申请号：US10941179
申请日：2004-09-14
申请人： Casey Hanlon , Calvin Potter , Paul Wingett
发明人： Casey Hanlon , Calvin Potter , Paul Wingett
IPC分类号： H02K7/09
CPC分类号： F16C32/0442 , F16C32/0446 , G05B9/03
摘要： A magnetic bearing sensing and control system and method provides increased tolerance to faults associated with the associated displacement sensors. The system includes a plurality of redundant displacement sensor sets to provide dual or triple displacement sensor redundancy, or higher if desired, and implements a process for determining when one or more displacement sensors is faulty. The system also compensates for determined sensor-related faults.
摘要翻译：磁轴承感测和控制系统和方法提供了与相关位移传感器相关联的故障的增加的容限。该系统包括多个冗余位移传感器组，以在需要时提供双重或三重位移传感器冗余度或更高，并且实现用于确定何时一个或多个位移传感器故障的过程。该系统还补偿确定的传感器故障。

9. 发明申请

US20070018040A1 Flight control surface actuation system with redundantly configured and lockable actuator assemblies 有权
标题翻译：飞行控制表面致动系统，具有冗余配置和可锁定的执行器组件
公开(公告)号：US20070018040A1
公开(公告)日：2007-01-25
申请号：US11192625
申请日：2005-07-28
申请人： Paul Wingett , Calvin Potter , Casey Hanlon , Dwayne Benson
发明人： Paul Wingett , Calvin Potter , Casey Hanlon , Dwayne Benson
IPC分类号： B64C13/00
CPC分类号： B64C13/42 , B64C13/00
摘要： A flight control surface actuator assembly includes a pair of flight control surface actuators and a pivot arm. One of the flight control surface actuators is coupled to a flight control surface and a static airframe structure, the other flight control surface actuator is coupled to the flight control surface and the pivot arm. The pivot arm coupled to the static airframe structure and is configured to pivot relative to the second flight control surface actuator and the static airframe structure.
摘要翻译：飞行控制表面致动器组件包括一对飞行控制表面致动器和枢转臂。飞行控制表面致动器中的一个联接到飞行控制表面和静态机身结构，另一个飞行控制表面致动器联接到飞行控制表面和枢转臂。枢转臂联接到静态机身结构并且构造成相对于第二飞行控制表面致动器和静止机身结构枢转。

10. 发明申请

US20070007385A1 Electric flight control surface actuation system electronic architecture 审中-公开
标题翻译：电动飞行控制面驱动系统电子架构
公开(公告)号：US20070007385A1
公开(公告)日：2007-01-11
申请号：US11192817
申请日：2005-07-29
申请人： Calvin Potter , Casey Hanlon , Paul Wingett
发明人： Calvin Potter , Casey Hanlon , Paul Wingett
IPC分类号： B64D33/00
CPC分类号： B64C13/505
摘要： An electric flight control surface actuation system is implemented using a low level control section and a high power section. The low level control section is disposed within an electronics bay within the aircraft, and is in operable communication with one or more flight computers via a communication bus. The flight computers supply flight control surface position commands to the low level control section, which in turn transmits actuator commands to the high power section via a plurality of redundant communication links. The high power section is disposed remotely from the low level control section and, in addition to being in operable communication with the low level control section, is coupled to an aircraft power bus and to each of the actuators. The high power section receives the actuator position commands transmitted from the low level control section and, in response, selectively energizes the actuators from the aircraft power bus.
摘要翻译：使用低电平控制部分和高功率部分实现电动飞行控制表面致动系统。低级控制部分设置在飞行器内的电子设备舱内，并且经由通信总线与一个或多个飞行计算机可操作地通信。飞行计算机向低级控制部分提供飞行控制表面位置命令，该低级控制部分又通过多个冗余通信链路将致动器命令传送到高功率部分。高功率部分远离低电平控制部分设置，并且除了与低电平控制部分可操作地通信之外，还耦合到飞行器电源总线和每个致动器。高功率部分接收从低电平控制部分发送的致动器位置命令，并且作为响应，从飞行器电力总线选择性地激励致动器。

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