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公开(公告)号：US20160308422A1
公开(公告)日：2016-10-20
申请号：US15101105
申请日：2014-09-19
CPC分类号： H02K7/145 , B64C13/42 , B64C13/44 , B64C13/50 , H02K5/225 , H02K7/00 , H02K7/10 , H02K7/108 , H02K7/116 , H02K7/14 , H02K2213/06 , H02K2213/09
摘要： An actuator including a frame, an electric motor fastened to the frame and to a rotor that is constrained to rotate with an outlet shaft, and a connector electrically connected to the motor and secured to the frame to be connected to a complementary connector. The actuator includes a secondary drive device having a secondary shaft having a first end that extends outside the frame and is arranged to be coupled to rotate with a rotary drive tool, a second end of the secondary shaft in rotation coupled with the outlet shaft, and an activation rod opening out into the connector is secured to the frame and arranged to prevent the secondary shaft from being coupled in rotation with the outlet shaft only when the complementary connector is connected to the connector secured to the frame.
摘要翻译： 一种致动器，包括框架，紧固到框架的电动机和被限制为与出口轴一起旋转的转子，以及电连接到电动机并固定到框架以连接到互补连接器的连接器。 所述致动器包括辅助驱动装置，所述辅助驱动装置具有副轴，所述副轴具有延伸到所述框架外部的第一端，并且被布置成与旋转驱动工具连接以旋转，所述次级轴的第二端与所述出口轴一起旋转，以及 打开到连接器中的激活杆被固定到框架并被布置成仅当辅助连接器连接到固定到框架的连接器时，防止副轴与出口轴旋转联接。
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公开(公告)号：US20160244152A1
公开(公告)日：2016-08-25
申请号：US14305838
申请日：2014-06-16
申请人： THE BOEING COMPANY
发明人： Jeffrey C. Coffman
CPC分类号： B64C13/16 , B64C9/00 , B64C13/28 , B64C13/44 , B64C13/50 , B64C13/506 , F03G1/00 , F16D11/14 , F16D28/00 , F16D2011/004
摘要： Systems and methods for operating flight control surfaces are provided. One system includes a control device having a two piece shaft including a first shaft portion and a second shaft portion, a spline key detachably coupling the first shaft portion and the second shaft portion, and a crankshaft operatively coupling the two piece shaft and a flight control surface. The control device further includes a driving mechanism coupled to the spline key and operable to move the spline key to engage and disengage the first and second shaft portions, wherein the first and second shaft portions are disengaged when a failure to the flight control surface is detected, causing the second shaft portion to drive the flight control surface to a safe position.
摘要翻译： 提供了操作飞行控制面的系统和方法。 一个系统包括具有包括第一轴部分和第二轴部分的两件式轴的控制装置，可拆卸地联接第一轴部分和第二轴部分的花键键和可操作地联接两件式轴的曲轴和飞行控制 表面。 所述控制装置还包括联接到所述花键键并可操作以使所述花键键移动以接合和分离所述第一和第二轴部分的驱动机构，其中当检测到所述飞行控制表面的故障时所述第一和第二轴部分脱离 使第二轴部分驱动飞行控制表面到安全位置。
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公开(公告)号：US4991800A
公开(公告)日：1991-02-12
申请号：US271438
申请日：1988-11-14
申请人： Robert A. Schwarz
发明人： Robert A. Schwarz
IPC分类号： B64C13/44
CPC分类号： B64C13/44
摘要： A backdrive system is provided for aircraft flight control surfaces, including a motor for driving a control surface. A fluid pressure responsive engaging/disengaging device is operatively associated between the motor and the control surface. The device may be a clutch normally engaged in the absence of to supply pressure or a brake normally disengaged in response to supply pressure. A supply of fluid pressure is connected to the device. An accumulator is connected in-line between the fluid pressure supply and the engaging/disengaging device for storing hydraulic energy during normal operation of the system and for releasing the stored hydraulic energy for at least a given period of time in the event of loss of supply pressure to allow the control surface to backdrive to a neutral position. A check-valve is provided between the fluid pressure supply and the accumulator to prevent return of hydraulic energy from the accumulator supply of fluid pressure when the supply pressure is lost. A bleed path is provided from the engaging/disengaging device to provide a time delay until the device is reengaged to lock up the control surface and prevent surface flutter.
摘要翻译： 为飞机飞行控制表面设置了一个反向驱动系统，包括用于驱动控制面的马达。 流体压力响应接合/分离装置可操作地联接在电动机和控制表面之间。 该装置可以是在没有供应压力的情况下通常接合的离合器或响应于供应压力正常脱开的制动器。 流体压力的供应被连接到装置。 蓄能器在流体压力供应和接合/分离装置之间在线连接，用于在系统的正常操作期间存储液压能量，并且在供应损失的情况下至少给定的时间段释放所储存的液压能量 压力允许控制表面反向驱动到中立位置。 在流体压力供应和蓄能器之间设置止回阀，以防止当供应压力损失时液压能量从蓄能器供给液体压力返回。 从接合/分离装置提供排放路径以提供时间延迟，直到装置重新接合以锁定控制表面并防止表面颤动。
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公开(公告)号：US10059439B2
公开(公告)日：2018-08-28
申请号：US14800346
申请日：2015-07-15
CPC分类号： B64C27/56 , B64C13/16 , B64C13/345 , B64C13/44 , B64C13/46 , B64C13/507 , B64C27/57 , B64D31/04 , G05D1/0072 , G05D1/0858
摘要： According to one embodiment, a pilot assistance system includes a trim assembly and a trim assembly control system. The trim assembly is operable to communicate with a pilot control device and operable to apply a force against the pilot control device in resistance of a command received from a pilot via the pilot control device. The trim assembly control system is in communication with the trim assembly, configured to identify a first pilot control device position relative to a reference pilot control device position, and configured to instruct the trim assembly to apply a cueing force against the pilot control device if the pilot control device is positioned proximate to the first pilot control device position.
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公开(公告)号：US20170017241A1
公开(公告)日：2017-01-19
申请号：US14800346
申请日：2015-07-15
CPC分类号： B64C27/56 , B64C13/16 , B64C13/44 , B64C13/46 , B64C27/57 , B64D31/04 , G05D1/0072 , G05D1/0858
摘要： According to one embodiment, a pilot assistance system includes a trim assembly and a trim assembly control system. The trim assembly is operable to communicate with a pilot control device and operable to apply a force against the pilot control device in resistance of a command received from a pilot via the pilot control device. The trim assembly control system is in communication with the trim assembly, configured to identify a first pilot control device position relative to a reference pilot control device position, and configured to instruct the trim assembly to apply a cueing force against the pilot control device if the pilot control device is positioned proximate to the first pilot control device position.
摘要翻译： 根据一个实施例，先导辅助系统包括修剪组件和修剪组件控制系统。 修剪组件可操作以与先导控制装置通信，并且可操作以通过先导控制装置对从先导控制装置接收到的命令的电阻施加对先导控制装置的力。 修剪组件控制系统与修剪组件连通，其被配置为相对于参考先导控制装置位置识别第一先导控制装置位置，并且被配置为指示装饰组件对先导控制装置施加提示力，如果 先导控制装置位于第一先导控制装置位置附近。
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公开(公告)号：US20140231591A1
公开(公告)日：2014-08-21
申请号：US14352501
申请日：2012-10-12
发明人： Yosuke Higuchi , Takeshi Matsuda
IPC分类号： B64C19/00
CPC分类号： B64C19/00 , B64C13/44 , G05D1/0858
摘要： An aircraft is provided with: an attitude control command calculating section which calculates an attitude control command for target attitude on the basis of a control stick operation amount; a gain value generating section which generates a gain value equal to or less than 1 which decreases as the control stick operation amount is larger; a multiplication section which multiplies the attitude control command for target attitude by the gain value; and a addition section which adds a rate damping control command to the attitude control command for target attitude multiplied by the gain value and outputs a result to a subtraction section for calculating an SAS command.
摘要翻译： 飞机设有：姿态控制指令计算部，其基于控制棒操作量计算目标姿态的姿态控制指令; 增益值生成部，其生成随着控制棒操作量较大而减小的等于或小于1的增益值; 乘法部分，用于将目标态度的姿态控制命令乘以增益值; 以及加法部分，其将速率衰减控制命令添加到用于目标姿态的姿态控制命令乘以增益值，并将结果输出到用于计算SAS命令的减法部分。
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公开(公告)号：US20140191087A1
公开(公告)日：2014-07-10
申请号：US14241232
申请日：2012-10-12
发明人： Yosuke Higuchi , Takeshi Matsuda
摘要： An aircraft is provided with a mechanical linkage that mechanically transmits an amount of manipulation of a control stick to a rudder controlling mechanism, an amount-of-manipulation sensor that detects the amount of manipulation, and an FBW control-law computing unit that calculates an FBW control-law command indicating an amount of control for a craft in accordance with the detected amount of manipulation. Also, with the aircraft, a high-pass filter outputs, among the control-stick manipulation amounts detected by the amount-of-manipulation sensor, an amount of change in the control-stick manipulation amounts; by subtracting the amount of change that has passed through the high-pass filter by means of the subtracting portion, the FBW control-law command serves as an SAS command; and the rudder controlling mechanism is driven by adding an amount of movement of an SAS actuator in accordance with the SAS command to the control-stick manipulation amount transmitted by the mechanical linkage.
摘要翻译： 飞机设置有机械联动装置，其将控制棒的操纵量机械地传递到方向舵控制机构，检测操纵量的操作量传感器，以及计算操作量的FBW控制律计算单元 FBW控制律命令，根据检测到的操作量指示飞行器的控制量。 此外，在飞行器中，高通滤波器在由操作量传感器检测到的控制棒操作量之中输出控制棒操纵量的变化量; 通过减去通过减法部分通过高通滤波器的变化量，FBW控制律命令用作SAS命令; 通过根据SAS命令将SAS致动器的移动量与通过机械连杆传递的控制棒操作量相加而驱动舵控制机构。
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公开(公告)号：US06189837B1
公开(公告)日：2001-02-20
申请号：US09182830
申请日：1998-10-29
申请人： Francis Matthews
发明人： Francis Matthews
IPC分类号： B64C1344
摘要： An improvement is presented for use in aircraft that have a battery (26), a hydraulically-operated aircraft component (such as a spoiler), and a hydraulic system having a return line (R). The improvement includes a hydraulic transfer cylinder assembly (20) for moving a particular aircraft component (32) in a desired direction during an emergency situation. A preferred assembly (50) includes a housing (52) having a cartridge (62) that is mounted directly to the housing base. The housing includes a first compartment (54), a second compartment (56) fillable with a hydraulic fluid, and a piston (58) separating the first and second compartments. The second compartment has an output port (53) that is in hydraulic communication with the particular aircraft component. The cartridge (62) includes a main firing element. Activation of the cartridge causes the main firing element to produce expanding gas that enters the first compartment (54) and forces the piston to translate, thus forcing hydraulic fluid out the output port (53). Means are provided for ensuring that the pressurized hydraulic fluid of the transfer cylinder assembly enters the hydraulically-operated component at a location that will force the component to move in the desired direction.
摘要翻译： 提出了一种用于具有电池（26），液压操作的飞行器部件（例如扰流器）的飞机和具有返回线（R）的液压系统的改进。 该改进包括用于在紧急情况期间使特定飞行器部件（32）在所需方向上移动的液压传动滚筒组件（20）。 优选的组件（50）包括具有直接安装到壳体基座的盒（62）的壳体（52）。 壳体包括第一隔室（54），可用液压流体填充的第二隔室（56）和分隔第一和第二隔室的活塞（58）。 第二隔室具有与特定飞行器部件液压连通的输出端口（53）。 盒（62）包括主发射元件。 筒的激活导致主发射元件产生进入第一隔室（54）的膨胀气体并迫使活塞平移，从而迫使液压流体流出输出端口（53）。 提供了用于确保传送滚筒组件的加压液压流体在将迫使部件沿期望方向移动的位置处进入液压操作部件的装置。
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9.发明申请公开(公告)号：US20170166297A1
公开(公告)日：2017-06-15
申请号：US15377646
申请日：2016-12-13
CPC分类号： B64C13/044 , B64C13/36 , B64C13/44 , Y02T50/44
摘要： An aircraft control comprises a mobile pedal and comprises a cylinder coupled to the pedal such that a displacement of the pedal according to at least a first direction reduces the volume of a first chamber of the cylinder. A control device comprises a fluid type bus system connecting two aircraft controls. Additionally, an aircraft is equipped with such a control device.
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公开(公告)号：US09660501B2
公开(公告)日：2017-05-23
申请号：US15101105
申请日：2014-09-19
IPC分类号： H02K7/14 , H02K5/22 , H02K7/00 , H02K7/10 , H02K7/116 , B64C13/42 , B64C13/44 , B64C13/50 , H02K7/108
CPC分类号： H02K7/145 , B64C13/42 , B64C13/44 , B64C13/50 , H02K5/225 , H02K7/00 , H02K7/10 , H02K7/108 , H02K7/116 , H02K7/14 , H02K2213/06 , H02K2213/09
摘要： An actuator including a frame, an electric motor fastened to the frame and to a rotor that is constrained to rotate with an outlet shaft, and a connector electrically connected to the motor and secured to the frame to be connected to a complementary connector. The actuator includes a secondary drive device having a secondary shaft having a first end that extends outside the frame and is arranged to be coupled to rotate with a rotary drive tool, a second end of the secondary shaft in rotation coupled with the outlet shaft, and an activation rod opening out into the connector is secured to the frame and arranged to prevent the secondary shaft from being coupled in rotation with the outlet shaft only when the complementary connector is connected to the connector secured to the frame.
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