公开(公告)号：US20050075769A1

公开(公告)日：2005-04-07

申请号：US10677567

申请日：2003-10-01

申请人： David Eschborn ,  Paul Evans ,  Casey Hanlon ,  Calvin Potter ,  Glenn Lane ,  Gary Farnsworth ,  Louie Gaines ,  David Mathis

发明人： David Eschborn ,  Paul Evans ,  Casey Hanlon ,  Calvin Potter ,  Glenn Lane ,  Gary Farnsworth ,  Louie Gaines ,  David Mathis

IPC分类号： G05B23/02 ,  G07C5/00 ,  G07C5/08 ,  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。

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。

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。

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。

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。

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。

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。

公开(公告)号：US20070145180A1

公开(公告)日：2007-06-28

申请号：US11319869

申请日：2005-12-27

申请人： Andrew Johnson ,  Casey Hanlon ,  Calvin Potter

发明人： Andrew Johnson ,  Casey Hanlon ,  Calvin Potter

IPC分类号： B64C1/00

CPC分类号： B64C13/50 ,  B64C13/42

摘要： An aircraft flight control surface actuation system includes a plurality of flap actuators, and a plurality of slat actuators. The actuators receive actuator position commands from an actuator control unit and, in response, move flaps and slats between stowed and deployed positions. The flight control surface actuator control unit includes a plurality of independent actuator control channels. One or more of the independent actuator control channels is coupled to both a flap actuator and a slat actuator, and is configured to selectively supply the actuator position commands thereto.

摘要翻译： 飞机飞行控制表面致动系统包括多个翼片致动器和多个板条致动器。 执行器从致动器控制单元接收致动器位置命令，并且作为响应，在收起位置和展开位置之间移动襟翼和板条。 飞行控制表面致动器控制单元包括多个独立的致动器控制通道。 一个或多个独立的致动器控制通道联接到翼片致动器和板条致动器，并且被配置为选择性地向其提供致动器位置命令。

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

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.