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公开(公告)号：US09908614B2
公开(公告)日：2018-03-06
申请号：US14701032
申请日：2015-04-30
发明人： Igor Cherepinsky , Harshad S. Sane
CPC分类号： B64C13/04 , B64C13/503 , B64C27/56 , B64D11/0689
摘要： A system and method for controlling a trajectory of a vehicle includes a crew seat with first and second inceptors mounted to a portion of the crew seat; a processor with memory having instructions stored thereon that cause the system to: receive signals indicative of a trajectory for the vehicle; receive signals indicative of a deviation in a trajectory of the vehicle; and transmit signals for controlling a flight path of the vehicle. A second inceptor is configured for selecting one or more menus on a user display and being configured to interact with a fly-by-wire control system for transmitting signals indicative of movement of flight surface of the vehicle. The crew seat is configured to be located on the vehicle, in a control station remotely located from the vehicle, or in a second vehicle remotely located from the vehicle.
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公开(公告)号：US09764830B2
公开(公告)日：2017-09-19
申请号：US13736169
申请日：2013-01-08
发明人： Travis L. Yates , Bradley D. Linton
摘要： According to one embodiment, a method of adjusting an aircraft pedal assembly includes providing a pedal linkage coupled between a pedal and an attachment assembly situated proximate to an aircraft instrument panel. A brake cylinder is provided coupled between the pedal and the attachment assembly. The pedal linkage is rotated in response to an adjustment input. The pedal linkage is maintained approximately parallel to the brake cylinder during rotation of the pedal linkage.
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公开(公告)号：US20170253320A1
公开(公告)日：2017-09-07
申请号：US15442115
申请日：2017-02-24
摘要： A method of retrofitting a mechanically controlled aircraft with a fly-by-wire system includes removing a mechanical links between mechanical pilot inputs and actuators operable to drive flight surfaces. Electromechanical actuators are coupled between a plurality of vehicle management computers and the actuators. Each of the electromechanical actuators is operable to receive commands from the vehicle management computers and output a mechanical force to an input linkage of one of the actuators. Electromechanical pilot input modules are coupled to the mechanical pilot inputs. Each of the electromechanical pilot input modules is operable to convert a pilot-driven input force of an instance of the mechanical pilot inputs into an electronic signal indicative of the pilot-driven input force. At least one high performance computer is coupled to at least one of the vehicle management computers. The high performance computer executes one or more high level intelligence algorithms to selectively operate the aircraft autonomously.
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公开(公告)号：US09656746B2
公开(公告)日：2017-05-23
申请号：US14609905
申请日：2015-01-30
发明人： Geoffrey C Latham , Carlos A Fenny , Jean-Sébastien Plante , Brady Atkins , Guifré Julio , Marc Denninger , Charles Eric Covington , Paul Wilson
摘要： According to one embodiment, a trim actuator for a pilot input device includes a driven member and a driving member configured to receive mechanical energy from a power source. A magnetorheological (MR) fluid is disposed between the driving member and the driven member and configured to transmit a variable amount of mechanical energy from the driving member to the driven member. An output member configured to be coupled between the driven member and the pilot input device. A magnetic circuit configured to deliver a magnetic field towards the MR fluid. The magnetic circuit is configured to control movement of the pilot input device by varying the strength of the magnetic field delivered towards the first MR fluid.
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5.发明申请ADVANCED EMERGENCY COLLECTIVE ACTUATOR WITH FRICTION PULL-OFF AND METHOD FOR A HELICOPTER 有权具有摩擦力的高级紧急收集执行器和直升机的方法公开(公告)号：US20170008624A1
公开(公告)日：2017-01-12
申请号：US15158521
申请日：2016-05-18
发明人： Mark Marvin , John E. Mercer , Derek Vetter
CPC分类号： B64C27/57 , B64C27/006 , B64C27/56 , B64C27/58 , B64C27/59
摘要： An emergency collective actuator includes an actuator motor to produce an actuation force and an actuator linkage that directly engages a friction control lever that is pivotally supported on the collective stick of a helicopter to apply the actuation force directly to the friction control lever such that the actuation force initially disengages the friction control and then reduces the adjustable pitch toward a minimum collective pitch position. The actuator can include a clutch that slips to allow the pilot to overcome the actuation force and that slips responsive to an engagement of the friction control by the pilot, but otherwise the clutch co-rotates with the motor shaft to bias the adjustable pitch toward a minimum collective pitch position.
摘要翻译： 紧急集体执行器包括致动器马达以产生致动力和致动器连杆，其直接接合摩擦控制杆，所述摩擦控制杆枢转地支撑在直升机的集体杆上，以将致动力直接施加到摩擦控制杆，使得致动 力最初脱离摩擦控制，然后将可调节距减小到最小集体俯仰位置。 致动器可包括离合器，其滑动以允许飞行员克服致动力，并且响应于飞行员的摩擦控制的接合滑动，但是否则离合器与马达轴共同旋转以将可调俯仰偏压朝向 最低集体职位。
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公开(公告)号：US20160357215A1
公开(公告)日：2016-12-08
申请号：US15117981
申请日：2014-02-11
发明人： Jon Francis Kull
CPC分类号： G05G5/06 , B64C13/0421 , B64C27/56 , G05G1/04
摘要： A control system includes at least one lever configured to receive an operator input, a bellcrank coupled to the at least one lever and configured to rotate when the operator input exceeds a threshold, a support structure of the bellcrank which movably holds the bellcrank, and at least one magnet which forms a magnetic field which forms a positive detent between the bellcrank and the support structure of the bellcrank.
摘要翻译： 控制系统包括至少一个杠杆，其配置成接收操作者输入;联结到所述至少一个杠杆并配置成当所述操作者输入超过阈值时旋转的曲拐;所述曲拐的支撑结构，其可动地保持所述曲拐， 至少一个磁体，其形成一个磁场，该磁场在曲拐和曲拐的支撑结构之间形成一个积极的定位。
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公开(公告)号：US20160333947A1
公开(公告)日：2016-11-17
申请号：US15107763
申请日：2015-02-02
申请人： SOCIÉTÉ DE COMMERCIALISATION DES PRODUITS DES LAé RECHERCHE APPLIQUÉE SOCPRA SCIENCES ET GÉNIE S.E.
发明人： JEAN-SEBASTIEN PLANTE , MARC DENNINGER , PATRICK CHOUINARD , GUIFRE JULIO , JEAN-PHILIPPE LUCKING BIGUE , NICOLAS HUPPE , JEAN-FRANCOIS DESROSIERS
CPC分类号： F16D37/008 , B64C13/28 , B64C27/08 , B64C27/12 , B64C27/56 , B64C27/605 , B64C27/64 , B64C27/68 , B64C27/78 , B64D31/14 , B64D35/02 , B64D35/04 , F16D27/14 , F16D37/02 , F16D2037/001 , F16D2037/007 , F16H25/20 , F16H2025/2059 , Y02T50/44 , Y10T74/18704
摘要： A magnetorheological fluid clutch apparatus comprises an input rotor adapted to be coupled to a power input, the input rotor having a first set of at least one input shear surface, and a second set of at least one output shear surface. An output rotor is rotatably mounted about the input rotor for rotating about a common axis with the input rotor, the output rotor having a first set of at least one output shear surface, and a second set of at least one output shear surface, the first sets of the input rotor and the output rotor separated by at least a first annular space and forming a first transmission set, the second sets of the input rotor and the output rotor separated by at least a second annular space and forming a second transmission set. Magnetorheological fluid is in each of the annular spaces, the MR fluid configured to generate a variable amount of torque transmission between the sets of input rotor and output rotor when subjected to a magnetic field. A pair of electromagnets are configured to deliver a magnetic field through the MR fluid, the electromagnets configured to vary the strength of the magnetic field, whereby actuation of at least one of the pair of electromagnets results in torque transmission from the at least one input rotor to the output rotor.
摘要翻译： 磁流变流体离合器装置包括适于联接到动力输入的输入转子，所述输入转子具有第一组至少一个输入剪切表面和第二组至少一个输出剪切表面。 输出转子围绕输入转子可旋转地安装，用于与输入转子围绕公共轴线旋转，输出转子具有第一组至少一个输出剪切表面，第二组至少一个输出剪切表面，第一组 输入转子和输出转子的组由至少第一环形空间分开并形成第一变速器组，第二组输入转子和输出转子由至少第二环形空间分开并形成第二变速器组。 磁流变流体在每个环形空间中，MR流体构造成在受到磁场时在输入转子和输出转子组之间产生可变量的扭矩传递。 一对电磁体被配置成通过MR流体输送磁场，电磁体被配置为改变磁场的强度，由此致动该对电磁体中的至少一个导致来自至少一个输入转子的转矩传递 到输出转子。
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公开(公告)号：US09475577B2
公开(公告)日：2016-10-25
申请号：US14205886
申请日：2014-03-12
发明人： Patricia Wills , Brian Lafon , Ricky Jenkins
摘要： One example of a retention system for a rotorcraft pedal assembly includes an insertion member, an axial retention member, and a transverse retention member. The insertion member, which is inserted through a side of a pedal assembly, includes a spring compressible against the side of the pedal assembly in response to the insertion member being inserted through the side. The axial retention member receives and retains the insertion member on an opposing side of the pedal assembly. The transverse retention member is inserted through a passage formed in the axial retention member to secure the axial retention member against the side of the pedal assembly.
摘要翻译： 用于旋翼飞机踏板组件的保持系统的一个示例包括插入构件，轴向保持构件和横向保持构件。 通过踏板组件侧插入的插入构件包括响应于插入构件插入通过侧面而抵靠踏板组件侧面的弹簧可压缩。 轴向保持构件将插入构件接收并保持在踏板组件的相对侧上。 横向保持构件通过形成在轴向保持构件中的通道插入，以将轴向保持构件固定在踏板组件的侧面上。
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公开(公告)号：US09272780B2
公开(公告)日：2016-03-01
申请号：US13763574
申请日：2013-02-08
发明人： John E. Mercer , Nicolas Albion , Mark Bartel , Marc Feifel , Mark Marvin
CPC分类号： B64C27/57 , B64C13/18 , B64C13/42 , B64C27/56 , B64C27/59 , B64C27/64 , B64C27/68 , G05D1/0077 , G05D1/0816 , G05D1/0858 , G05D1/102 , Y02T50/44
摘要： A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.
摘要翻译： 直升机自动驾驶系统包括用于直升机飞行的姿态保持的内循环，包括施加到内循环的给定水平的冗余。 外部环路被配置为提供关于直升机的飞行的导航功能，其包括与内部循环不同的冗余级别。 致动器在联动装置上提供制动力，用于在停电期间稳定直升机的飞行。 致动器是机电的并且接收电驱动信号以提供直升机的自动飞行控制，而不需要直升机中的液压辅助系统。 自动驾驶仪可以在液压辅助系统的故障模式下操作直升机。 使用相关的传感器输入描述了多个飞行模式，包括基于速率和真实姿态模式。
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10.发明申请公开(公告)号：US20150353192A1
公开(公告)日：2015-12-10
申请号：US14452245
申请日：2014-08-05
发明人： Brian D. Morrison
CPC分类号： B64C27/08 , B64C27/32 , B64C27/56 , B64C27/57 , B64D27/24 , B64D31/04 , B64D31/06 , B64D43/00 , G01C23/005 , Y02T50/54 , Y02T50/62
摘要： Methods and systems for a full-scale vertical takeoff and landing manned or unmanned electric aircraft, having an all-electric, non-hydrocarbon-powered lift and propulsion system, an integrated avionics system for navigation and guidance, and simple joystick and throttle controls to provide the operator with ‘drive by wire’ style direction control. The vehicle employs counter-rotating sets of propellers and lift is provided by multiple pairs of small electric motors driving directly-connected, counter-rotating sets of propellers. Automatic computer monitoring by one or a plurality of programmed redundant digital motor management computer or autopilot controls each motor-controller and motor to produce pitch, bank and elevation, while simultaneously restricting the flight regime that the pilot can command. Sensed multi-axis information and parameter values about vehicle state are used to provide stable vehicle control and to detect when stable vehicle operating limits are about to be exceeded.
摘要翻译： 具有全电动，非碳氢化合物驱动的电梯和推进系统的全尺寸垂直起飞和着陆载人或无人电动飞机的方法和系统，用于导航和引导的集成航空电子系统，以及简单的操纵杆和节气门控制 为操作员提供“通过线驱动”式方向控制。 车辆采用反旋转螺旋桨组，升降机由多对小型电动马达提供，这些小型电动机驱动直接连接，反向旋转的螺旋桨组。 由一个或多个编程的冗余数字电机管理计算机或自动驾驶仪进行的自动计算机监视控制每个电动机控制器和电动机以产生音调，组合和高程，同时限制驾驶员可以指挥的飞行状态。 用于检测车辆状态的多轴信息和参数值用于提供稳定的车辆控制，并检测何时将要超出稳定的车辆运行极限。
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