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公开(公告)号：US20190189373A1
公开(公告)日：2019-06-20
申请号：US16200919
申请日：2018-11-27
申请人： AIRBUS HELICOPTERS
发明人： Kamel ABDELLI , Olivier SELLIER
CPC分类号： H01H23/14 , B64D31/04 , B64D35/00 , H01H23/003 , H01H23/30 , H01H25/04 , H01H2205/002 , H01H2205/004 , H01H2221/016 , H01H2225/014 , H01H2235/028 , H01H2239/03
摘要： An electrical control mechanism having a support. A central body that is movable in rotation about a central axis of rotation (AXROTC) carries a button that is movable in rotation relative to the central body about an offset axis of rotation (AXROTD) parallel to the central axis of rotation (AXROTC). First return means are interposed between the central body and the button, with second return means being interposed between the central body and the support. Two primary electric switches are interposed between the button and the central body on either side of a plane containing the central axis of rotation (AXROTC) and the offset axis of rotation (AXROTD). Two secondary electric switches are interposed between the support and the central body on either side of the plane.
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公开(公告)号：US20180099738A1
公开(公告)日：2018-04-12
申请号：US15287467
申请日：2016-10-06
CPC分类号： B64D31/04 , B64C13/30 , B64C29/0033 , G05G9/047
摘要： The present invention includes a thrust control apparatus, method and kit for a tiltrotor craft comprising a thrust control handle; a first and a second bar connected to the thrust control handle and connected to a floor support; a first end of a transverse bar connected to the first bar; a linker connected to a second end of the transverse bar; and a crankbell connected to the floor support below the first and a second bars, wherein a first end of the crankbell is connected to the linker, wherein the thrust control handle has a substantially linear motion that controls engine thrust, and the crankbell transfers the substantially linear motion of the handle into a substantially perpendicular motion that engages an engine thrust control at a second end of the crankbell.
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公开(公告)号：US09612131B2
公开(公告)日：2017-04-04
申请号：US13442564
申请日：2012-04-09
摘要： A method includes receiving, at a processor from a camera, image data associated with a control panel. The method also includes presenting one or more images at a display. The one or more images are generated based on the image data. The method includes determining a location of a first control of the control panel based on the image data and based on control settings data. The method includes providing an indication of the location of the first control at the display, and providing an indication of a desired configuration of the first control at the display.
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4.发明申请公开(公告)号：US20170081038A1
公开(公告)日：2017-03-23
申请号：US14861712
申请日：2015-09-22
发明人： Dave Looper , Scot Coffey , Yufei Xiong
摘要： Embodiments of a single lever turboprop control method and system are provided, which utilize torque-based and/or power-based scheduling to achieve a desired (e.g., substantially proportional) relationship between control lever position and the power output of a turboprop engine. In one embodiment, the method includes the step or process of monitoring, at an Engine Control Unit (ECU), for receipt of a Power Lever Angle (PLA) signal from a single lever control device. When a PLA control signal received at the ECU, a target torque or power output is established as a function of at least the PLA control signal. A first engine setpoint, such as a blade angle setpoint or an engine rotational speed setpoint, is determined utilizing the target torque output. An operational parameter of the turboprop engine is then adjusted in accordance with the first engine setpoint.
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公开(公告)号：US09598177B2
公开(公告)日：2017-03-21
申请号：US13500861
申请日：2010-10-05
申请人： Hafid Elabellaoui , Jean-Eric Besold , Marie-Noël Besold , Aurélie Besold , Stéphanie Besold , Antoine Besold , Sébasiten Pautard , David Engler , Etienne Merlet
CPC分类号： B64D31/06 , B64D31/04 , Y10T74/20238
摘要： An aeroengine control device comprising a mount, having pivotally mounted thereon a code wheel together with a main lever and a secondary lever, both for turning the code wheel, each lever being movable between a rest position and a maximum actuation position, the secondary lever being mounted to pivot on the main lever. A connecting rod connects the secondary lever in permanent manner to the code wheel and the main lever is provided with a connection member arranged to co-operate with a portion in relief secured to the code wheel and with a portion in relief secured to the mount in such a manner that the connection member attaches to the code wheel when the main lever is moved while the secondary lever is in its rest position and attaches to the mount, thereby releasing the code wheel to turn, when the secondary lever is moved while the main lever is in its rest position, while movement of either lever is prevented when the other lever is away from its rest position.
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公开(公告)号：US09550578B2
公开(公告)日：2017-01-24
申请号：US14171847
申请日：2014-02-04
发明人： Sue McCullough , Mahesh Sivaratri
CPC分类号： B64D43/00 , B64D31/04 , G06F3/167 , G08G5/0021 , G08G5/003 , G10L15/00 , G10L15/08 , G10L15/22 , G10L15/26 , G10L2015/085 , G10L2015/223 , G10L2015/228
摘要： A system and method are provided for programming a flight management system in response to a voice input. The voice input is validated (the pilot spoken vocabulary is thereby filtered (e.g., adapted) to improve recognition accuracy and reduce false positives) by comparing the current operational state of the aircraft (for example, climb, level flight, descent, speed, altitude, and heading), operation validities and availabilities (for example, operations allowed and not allowed) based on the flight management system planned and predicted lateral and vertical trajectory of the flight route (flight plan) from origin/present position to destination, and the requested action being taken.
摘要翻译： 提供了一种响应于语音输入来编程飞行管理系统的系统和方法。 语音输入被验证（通过比较飞行器的当前操作状态（例如爬升，水平飞行，下降，速度，高度），对飞行员口语词汇进行过滤（例如，适应）以提高识别精度并减少误报） ，航向和目的地的飞行路线（飞行计划）的横向和纵向轨迹，以及预计的飞行管理系统的运行有效性和可用性（例如，允许和不允许的操作），以及 要求采取行动。
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公开(公告)号：US20170017257A1
公开(公告)日：2017-01-19
申请号：US15270732
申请日：2016-09-20
发明人： Dale Wayne Sparks
摘要： A single lever system including a condition cable controlling mechanism configured for controlling adjustment of a condition cable, a power cable controlling mechanism configured for controlling adjustment of a power cable, and a single lever coupled to the condition cable controlling mechanism and to the power cable controlling mechanism. The condition cable controlling mechanism prevents adjustment of the condition cable when the lever is controlling adjustment of the power cable. The power cable controlling mechanism prevents adjustment of the power cable when the lever is controlling adjustment of the condition cable.
摘要翻译： 一种单杠杆系统，包括配置成用于控制条件电缆的调节的条件电缆控制机构，配置用于控制电力电缆的调节的电力电缆控制机构，以及耦合到状态电缆控制机构的单个控制杆和电力电缆控制 机制。 当控制杆控制电力电缆的调整时，条件电缆控制机构防止条件电缆的调整。 当控制杆控制条件电缆的调整时，电源线控制机构可防止电源线的调整。
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公开(公告)号：US09487302B2
公开(公告)日：2016-11-08
申请号：US14547384
申请日：2014-11-19
发明人： Yoshihiro Nagashima
CPC分类号： B64D31/06 , B64D31/04 , B64D31/14 , F02C7/262 , F02C9/28 , F05D2270/092 , F05D2270/312 , G05D1/042
摘要： The invention deals with the restriction on the mode change of an engine due to latching in the case of restarting the engine that has stopped in flight. A FADEC that controls an engine of an aircraft in accordance with a mode, includes a latch operating section that latches the mode, and an in-parking/in-flight determining section that determines whether the aircraft is on the ground or flying off the ground. The latch operating section operates when the in-parking/in-flight determining section determines the aircraft is on the ground, and does not operate when the in-parking/in-flight determining section determines that the aircraft is in fight.
摘要翻译： 本发明涉及在重新启动在飞行中停止的发动机的情况下由于锁定引起的发动机的模式变化的限制。 根据模式控制飞行器的发动机的FADEC包括锁定模式的闩锁操作部分和用于确定飞机是在地面上还是从地面飞离的飞行中的停车/飞行中确定部分 。 当停车/飞行中确定部分确定飞机在地面时，闩锁操作部分操作，并且在停车/飞行中确定部分确定飞机正在进行战斗时不操作。
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9.发明授权Device for controlling the power of an engine and for controlling a thrust reverser device 有权用于控制发动机功率并控制推力反向装置的装置公开(公告)号：US09422061B2
公开(公告)日：2016-08-23
申请号：US14889624
申请日：2014-05-02
摘要： A device for controlling the power of an engine and of a thrust reverser device. The invention includes a frame on which a primary cam track is formed, a thrust lever hinged to the frame, a thrust reverser lever hinged to the thrust lever, a bearing face arranged on the thrust reverser lever, a locking lever hinged to the thrust lever and comprising a first end and a second end. When the thrust lever has been pivoted by a predefined angle relative to the idle position of same, actuation of the thrust reverser lever is blocked, both by the second end of the locking lever pressing against the bearing face of the thrust reverser lever, and by the first end of the locking lever pressing against the primary cam track.
摘要翻译： 用于控制发动机和推力反向装置的动力的装置。 本发明包括一个其上形成有一个主凸轮轨道的框架，一个铰接在框架上的止推杆，一个铰接到推力杆上的推力反向杆，一个设置在推力反向杆上的一个支承面，一个铰链到推杆上的锁定杆 并且包括第一端和第二端。 当推力杆相对于其怠速位置枢转预定角度时，推力反向杆的致动被锁定杆的第二端压靠在推力反向杆的支承面上，并且通过 锁定杆的第一端压靠在主凸轮轨道上。
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公开(公告)号：US09212625B2
公开(公告)日：2015-12-15
申请号：US14151816
申请日：2014-01-10
IPC分类号： F02K5/00 , F02C3/32 , B64D27/10 , B64D27/12 , B64D27/14 , F01D15/10 , F02K3/06 , F02C7/32 , B64D31/04 , B64D27/02
CPC分类号： F02K5/00 , B64D27/10 , B64D27/12 , B64D27/14 , B64D31/04 , B64D2027/026 , F01D15/10 , F02C7/32 , F02K3/06 , F05D2220/34 , Y02T50/44 , Y02T50/64
摘要： A hybrid aerodynamic thrust system as a prime mover for aircraft or other high-speed vehicles. An arrangement of dual thrust resources to alternately accommodate low and high airspeed regimes. Electromotive force is used in lieu of hot section power turbines to achieve engine air compression or alternately perform thrust work at low velocities.
摘要翻译： 作为飞机或其他高速车辆的原动机的混合气动推力系统。 双重推力资源的布置，以交替地适应低空和高空速制度。 使用电动力代替热段动力涡轮机以实现发动机空气压缩或者以低速交替地执行推力工作。
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