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81. 发明公开

EP3081480A3 ELECTRO-HYDRAULIC SERVO VALVE CONTROL SYSTEM 有权
标题翻译：控制系统的电动伺服阀液压
公开(公告)号：EP3081480A3
公开(公告)日：2016-11-23
申请号：EP16164384.6
申请日：2016-04-08
申请人： Goodrich Corporation
发明人： SUMMERS, Camila , RONNING, Eric Duane
IPC分类号： B64C13/00 , H02M7/5387 , G05B19/46
CPC分类号： G05D7/0635 , B64C13/00 , B64C13/40 , B64C13/503 , G05B15/02 , G05B19/46 , G05B2219/34024 , G05B2219/41292 , G05B2219/41317 , G05B2219/41318 , G05B2219/42237 , H02M7/5387
摘要： A control system 100 includes an electro-hydraulic servo valve configured to move about a plurality of positions in response to receiving an analog bi-polar current signal. An electronic field programmable gate array (FPGA) 104 generates first and second digital pulse width modulation (PWM) signals according to an adjustable duty cycle. An electronic bridge circuit 106 is in electrical communication with the FPGA to convert the first and second digital PWM signals into the bi-polar current signal. An electronic current sensing circuit 110 is in electrical communication with the bridge circuit, the current sensing circuit 110 configured to generate a digital feedback signal indicating an average current level of the bi-polar signal. The FPGA controls the duty cycle based on at least the average current level indicated by the digital feedback signal.

82. 发明公开

EP3076043A1 LINEAR HYDRAULIC DAMPING DEVICE 有权转让
标题翻译： LINEARE HYDRAULISCHEDÄMPFUNGSVORRICHTUNG
公开(公告)号：EP3076043A1
公开(公告)日：2016-10-05
申请号：EP15305489.5
申请日：2015-04-02
申请人： Goodrich Actuation Systems SAS
发明人： Socheleau, Jérôme
IPC分类号： F16F9/348
CPC分类号： F15B15/1423 , B64C13/36 , B64C13/40 , F16F9/348
摘要： A linear hydraulic damping device (48) comprises a damper body (58) defining a first chamber (74) having a first fluid inlet (80) and a second chamber (76) having a second fluid inlet (82). The chambers (74, 76) are separated by a wall (78) which has at least one first passage (86) and at least one second passage (88) connecting the chambers (74, 76). The first passage (86) has a first end (90) opening into the first chamber (74) and a second end (92) opening into the second chamber (76). The second passage (88) has a first end (94) opening into the second chamber (76) and a second end (96) opening into the first chamber (74). Respective first and second movable elements (120, 122) are received within the chambers (74, 76) and are resiliently biased towards the wall (78) by a respective spring (130, 132) to a closed position in which the first movable element (120) closes the first end (90) of the first passage (86) but does not close the second end (96) of the second passage (88) and in which the second movable element (122) closes the first end (94) of the second passage (88) but does not close the second end (92) of the first passage (86). The respective movable elements (120, 122) are movable away from their closed positions against the force of the springs (130, 132) by entry of fluid into the respective chambers to create respective variable damping orifices between the first ends (90, 94) of the first and second passages (86, 88) and the respective movable elements (120, 122).
摘要翻译：线性液压阻尼装置（48）包括限定具有第一流体入口（80）的第一室（74）和具有第二流体入口（82）的第二室（76）的阻尼体（58）。腔室（74,76）由壁（78）分开，壁（78）具有连接腔室（74,76）的至少一个第一通道（86）和至少一个第二通道（88）。第一通道（86）具有通向第一室（74）的第一端（90）和通向第二室（76）的第二端（92）。第二通道（88）具有通向第二室（76）的第一端（94）和通向第一室（74）的第二端（96）。相应的第一和第二可移动元件（120,122）被容纳在所述腔室（74,76）内并且通过相应的弹簧（130,132）朝向所述壁（78）弹性偏压到关闭位置，在所述关闭位置，所述第一可移动元件（120）关闭第一通道（86）的第一端（90），但不关闭第二通道（88）的第二端（96），并且第二可移动元件（122）封闭第一端（94））而不关闭第一通道（86）的第二端（92）。相应的可移动元件（120,122）可通过将流体进入相应的腔室中来抵抗弹簧（130,132）的力而从其关闭位置移动，以在第一端（90,94）之间产生相应的可变阻尼孔，的第一和第二通道（86,88）和相应的可移动元件（120,122）。

83. 发明公开

EP3025956A1 ENGINE DRIVEN PUMP (EDP) AUTOMATIC DEPRESSURIZATION SYSTEM 有权
标题翻译：自动化设备DRUCKENTLASTUNGSSYSTEM MIT MOTORBETRIEBENER PUMPE（EDP）
公开(公告)号：EP3025956A1
公开(公告)日：2016-06-01
申请号：EP15196298.2
申请日：2015-11-25
申请人： The Boeing Company
发明人： WILSON, Thomas Michael , HASENOEHRL, Thomas Raymond , CHIN, Edmond C. , LESYNA, Mark William
IPC分类号： B64C13/36 , F02C7/32
CPC分类号： G05D16/2066 , B64C13/36 , B64C13/40 , B64C25/22 , B64D41/00 , F02C7/32
摘要： An automatic engine driven pump (EDP) depressurization system for an aircraft is disclosed. The aircraft includes at least two EDPs (30a) driven by a main engine for converting mechanical power provided by the main engine into hydraulic power for distribution by a hydraulic system. The EDP depressurization system includes a depressurization device (70a) corresponding to each of the at least two EDPs (30a) and a control module (80). The depressurization devices (70a) are each energized to depressurize a respective EDP (30a). The control module (80) is in signal communication with each of the depressurization devices (70a). The control module (80) includes control logic for automatically generating a depressurization signal that energizes one of the depressurization devices based on a plurality of operational conditions of the aircraft.
摘要翻译：公开了一种用于飞行器的自动发动机驱动泵（EDP）减压系统。飞机包括由主发动机驱动的至少两个EDP（30a），用于将由主发动机提供的机械动力转换成液压动力以通过液压系统分配。 EDP减压系统包括对应于至少两个EDP（30a）和控制模块（80）中的每一个的减压装置（70a）。减压装置（70a）各自通电以对各个EDP（30a）进行减压。控制模块（80）与每个减压装置（70a）进行信号通信。控制模块（80）包括控制逻辑，用于根据飞行器的多个操作条件，自动产生对一个减压装置通电的减压信号。

84. 发明公开

EP2942274A1 FLY BY WIRE SERVOS WITH INTERNAL LOOP CLOSURE 审中-公开
标题翻译： FLY-BY-WIRE SERVOS MIT INNEREM REGELSCHLEIFENVERSCHLUSS
公开(公告)号：EP2942274A1
公开(公告)日：2015-11-11
申请号：EP15155772.5
申请日：2015-02-19
申请人： Sikorsky Aircraft Corporation
发明人： Cotton, Bryan S. , Harrigan, Matthew , Winslow, Christopher L.
IPC分类号： B64C13/40 , B64C13/50 , F15B13/00 , F15B18/00 , B64C27/57
CPC分类号： B64C13/503 , B64C13/40 , B64C13/504 , B64C27/57 , B64C27/64 , B64C27/68 , F15B18/00 , Y02T50/44
摘要： Embodiments are directed to obtaining a first analog signal corresponding to a position error between a commanded gang output of a plurality of electro-mechanical actuators configured to be run in parallel with one another and a measured gang output of the plurality of electro-mechanical actuators (212), obtaining a second analog signal corresponding to an output torque, and processing, by a circuit, the first analog signal and the second analog signal to generate and output a discrete that indicates a status of the torque in terms of direction and magnitude.
摘要翻译：实施例旨在获得对应于构造成彼此平行运行的多个机电致动器的命令组合输出之间的位置误差的第一模拟信号和多个机电致动器的测量的组合输出（ 212），获得对应于输出转矩的第二模拟信号，以及通过电路处理所述第一模拟信号和所述第二模拟信号以产生并输出表示所述转矩的方向和幅度方面的状态的离散度。

85. 发明授权

EP2803572B1 Distributeur hydraulique double d'une servocommande de manoeuvre des pales d'un rotor de giravion 有权
标题翻译：伺服控制器的液压双歧管用于控制旋翼飞机的转子的叶片
公开(公告)号：EP2803572B1
公开(公告)日：2015-10-28
申请号：EP14001385.5
申请日：2014-04-16
申请人： Airbus Helicopters
发明人： Bihel, Jean-Romain , Leguay, Pascal , Marger, Thibaut
IPC分类号： B64C27/58 , B64C27/64 , F15B13/04 , F15B20/00
CPC分类号： F15B13/01 , B64C13/40 , B64C27/605 , B64C27/64 , F15B11/02 , F15B13/0402 , F15B20/008 , F15B2211/8636 , F15B2211/8752 , F15B2211/8757 , F16K11/07 , F16K11/0704 , F16K11/0708

86. 发明公开

EP2736804A1 RUDDER BIAS GAIN CHANGER 失效
公开(公告)号：EP2736804A1
公开(公告)日：2014-06-04
申请号：EP11740776.7
申请日：2011-07-26
申请人： Learjet Inc. , Short Brothers Plc
发明人： BUTLER, Harris , VELETAS, Mihalis
IPC分类号： B64C13/24
CPC分类号： B64C13/28 , B64C13/24 , B64C13/26 , B64C13/40
摘要： A bias gain system (10) for aircraft rudder comprises a pair of connector ends (21) receiving an actuation force from a bias actuator (12). A rudder bar interface is positioned between the connector ends. The interface rotates about the rudder bar (11) as a function of the actuation forces from the bias actuators. A mechanism comprising links and joints between the connector ends and the rudder bar is actuatable between a contracted configuration, in which first moment arms are defined between the connector ends and the rudder bar interface, and an expanded gain configuration, in which second moment arms have a greater dimension than the first moment arms. An actuator is connected to the mechanism to actuate the mechanism independently from the actuation forces from the bias actuators, to move the mechanism between configurations. An aircraft and a method for controlling a torque on a rudder bar of an aircraft are also provided.
摘要翻译：用于飞机方向舵的偏置增益系统（10）包括接收来自偏置致动器（12）的致动力的一对连接器端部（21）。舵杆接口位于连接器端部之间。接口根据来自偏压致动器的致动力绕舵杆（11）旋转。包括连接器端部和舵杆之间的连杆和接头的机构可以在其中第一力矩臂被限定在连接器端部和舵杆接口之间的收缩构型与扩张增益构造之间致动，其中第二力臂具有比第一时刻武器更大的维度。致动器连接到机构以独立于来自偏压致动器的致动力致动机构，以在配置之间移动机构。还提供了一种用于控制飞机的舵杆上的扭矩的飞行器和方法。

87. 发明公开

EP2722274A2 Flow control actuator with an adjustable frequency 有权
标题翻译： Flusssteuerungsaktuator mit einer einstellbaren Frequenz
公开(公告)号：EP2722274A2
公开(公告)日：2014-04-23
申请号：EP13184675.0
申请日：2013-09-17
申请人： The Boeing Company
发明人： Raghu, Surya
IPC分类号： B64C21/04 , B64C21/08
CPC分类号： F15B21/12 , B64C13/40 , B64C21/04 , B64C21/08 , B64C2230/04 , B64C2230/06 , B64C2230/18 , F16L55/04 , F17D1/02 , Y02T50/166 , Y10T137/0318 , Y10T137/0324
摘要： A method and apparatus comprising a structure (204) and a chamber (210) within the structure (204). The structure (204) has an input port (206) and an output port (208). The chamber (204) is configured to channel a fluid (212) from the input port (206) to the output port (208) of the structure (204). A volume (214) of the chamber (210) is configured to change such that a frequency (216) at which the fluid 212) flows out of the output port (208) changes at the output port (208).
摘要翻译：一种包括结构（204）内的结构（204）和室（210）的方法和装置。结构（204）具有输入端口（206）和输出端口（208）。腔室（204）被配置为将流体（212）从输入端口（206）引导到结构（204）的输出端口（208）。腔室（210）的体积（214）被配置为改变使得流体212流出输出端口（208）的频率（216）在输出端口（208）处改变。

88. 发明公开

EP2678219A4 ELASTOMERIC SIGNAL TRANSMISSION AND MOTION AMPLIFICATION 有权
标题翻译：弹性体信令和运动GAIN
公开(公告)号：EP2678219A4
公开(公告)日：2014-01-01
申请号：EP11867613
申请日：2011-06-13
申请人： BELL HELICOPTER TEXTRON INC
发明人： SCHANK TROY C , STAMPS FRANK B
IPC分类号： B64C13/40 , B64C27/615 , F15B7/08 , F15B21/06
CPC分类号： F04B7/00 , B64C11/38 , B64C13/40 , B64C27/615 , B64C2027/7272 , F15B15/088 , F15B15/14 , Y02T50/34

89. 发明公开

EP2527248A2 Suppressing electrical failure effects in servo control systems 有权
标题翻译： Servolenkungssystemen的Unterdrückungvon elektrischen Fehlerwirkungen
公开(公告)号：EP2527248A2
公开(公告)日：2012-11-28
申请号：EP12169236.2
申请日：2012-05-24
申请人： The Boeing Company
发明人： Matsui, Gen
IPC分类号： B64C13/40 , B64C13/50
CPC分类号： B64C13/40 , B64C13/503
摘要： Systems to manage servo controls are disclosed. In some embodiments servo controls may implemented in systems to deflect control surfaces in aircraft. In one embodiment, a system to manage the output of a servo valve (220) comprises a first plurality of feedback loops (270) to receive a plurality of commands representative of a desired piston (252) position and to generate, from the plurality of commands, a plurality of position difference signals (315) which represent a difference between a desired piston (252) position and a current piston (252) position, a plurality of amplifiers (206, 210) to generate, from the plurality of position difference signals (315), a corresponding plurality of magnetic flux target signals (320), a second plurality of feedback loops (272) to receive, from the plurality of amplifiers (206, 210), the plurality of magnetic flux target signals (320), wherein the magnetic flux target signals (320) represent a desired magnetic flux measurement in the servo valve (220), and to generate, from the plurality of magnetic flux target signals (320), a plurality of magnetic flux difference signals (325) which represent a difference between a desired magnetic flux measurement and a current magnetic flux measurement, and an assembly to regulate the servo valve (220) using the plurality of magnetic flux target signals (320). Other embodiments may be described.
摘要翻译：公开了管理伺服控制的系统。在一些实施例中，伺服控制可以在系统中实现以使飞机中的控制表面偏转。在一个实施例中，管理伺服阀（220）的输出的系统包括第一多个反馈回路（270），以接收表示期望活塞（252）位置的多个指令，并且从多个命令，表示期望的活塞（252）位置和当前活塞（252）位置之间的差的多个位置差信号（315），多个放大器（206,210），从多个位置差信号（315），相应的多个磁通目标信号（320），第二多个反馈回路（272），用于从多个放大器（206,210）接收多个磁通量目标信号（320），其中所述磁通目标信号（320）表示所述伺服阀（220）中的所需磁通量测量值，并且从所述多个磁通目标信号（320）生成多个磁通量差信号（325）代表 t是希望的磁通量测量和电流磁通测量之间的差异，以及使用多个磁通量目标信号（320）来调节伺服阀（220）的组件。可以描述其他实施例。

90. 发明公开

EP2412629A2 Damping test method, control apparatus, hydraulic system, and program 有权
标题翻译： Dämpfungstestverfahren，Steuerungsvorrichtung，Hydrauliksystem und Programm
公开(公告)号：EP2412629A2
公开(公告)日：2012-02-01
申请号：EP11175545.0
申请日：2011-07-27
申请人： Nabtesco Corporation
发明人： Fukui, Atsushi , Suzuki, Kazuyuki , Ogawa, Toshiaki , Mori, Atsushi
IPC分类号： B64C13/40 , B64F5/00
CPC分类号： B64C13/40 , B64F5/60 , Y02T50/44
摘要： The control apparatus acquires an ideal velocity characteristic of a control surface(104,105), and the temperature of pressure oil of the actuator (11,12) to be tested and the operating speed of the control surface (104,105) when the actuator is attached to the control surface. The control apparatus corrects the ideal velocity characteristic of the control surface by using the pressure oil temperature and the control surface operating speed. The control apparatus sets an upper limit and a lower limit by using a predicted value for a fluctuation range for a fluctuation factor that causes a fluctuation of the control surface operating speed, with reference to the corrected ideal velocity characteristic, measures the pressure oil temperature and the operating speed by actuating the control surface (104,105), with the actuator to be tested placed in a damping mode, and determines whether the measured value falls within the range between the upper limit and the lower limit.
摘要翻译：控制装置获取控制表面（104,105）的理想速度特性，以及待执行器的执行机构（11,12）的压力油的温度和执行机构附接到控制表面（104,105）时的操作速度控制面。控制装置通过使用压力油温度和控制面操作速度来校正控制面的理想速度特性。控制装置通过使用引起控制面操作速度的波动的波动因数的波动范围的预测值，参照校正后的理想速度特性来测定压力油温和通过致动控制表面（104,105）的操作速度，待测试的执行器处于阻尼模式，并确定测量值是否在上限和下限之间的范围内。

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