公开(公告)号：EP2543589A1

公开(公告)日：2013-01-09

申请号：EP11290312.5

申请日：2011-07-06

申请人： EUROCOPTER ,  Eurocopter Deutschland GmbH

发明人： Grohmann, Boris ,  Chaduc, Bruno ,  Tempier, Christophe

IPC分类号： B64C13/50 ,  B64C27/64 ,  B64C27/68

CPC分类号： B64C27/625 ,  B64C13/503 ,  B64C27/64 ,  B64C27/68 ,  Y02T50/44

摘要： The present invention relates to primary flight controls (10) for main and/or tail rotors (4) of helicopters with an electro-mechanical interface between any of Fly-By-Wire and/or of Fly-by-light controls and hydraulic servo actuators (8) for control force amplification towards said main and/or tail rotor controls (4). For each of the main and/or tail rotor controls (4) there is provided but one of the hydraulic servo actuators (8), connected by one mechanical linkage (7) to one electro motor (5), said one hydraulic servo actuator (8) being of the type having the one mechanical linkage (7) connected to its input (29) and its output (30) and the one electro motor (5) being of the direct drive type, the position of said electro motor (5) having a reference to said one mechanical linkage (7) and the torque delivered by said electro motor (5) to the hydraulic servo actuator (8) being related to the power consumption of said electro motor (5).

摘要翻译： 本发明涉及用于直升机的主和/或尾转子（4）的主飞行控制装置（10），其具有在飞行之间和/或飞越控制之间的电 - 机械接口和液压伺服 用于对所述主和/或尾部转子控制器（4）进行控制力放大的致动器（8）。 对于每个主转子控制器和/或尾部转子控制器（4），只有一个液压伺服致动器（8）通过一个机械连杆（7）连接到一个电动机（5），所述一个液压伺服致动器 8）是具有连接到其输入端（29）的一个机械联动装置（7），其输出端（30）和一个电动马达（5）是直接驱动型的，所述电动马达（5）的位置 ）与所述电动马达（5）输送到所述液压伺服驱动器（8）的扭矩相关联，并与所述电动马达（5）的功率消耗相关。

公开(公告)号：EP2341252A1

公开(公告)日：2011-07-06

申请号：EP09425544.5

申请日：2009-12-30

申请人： Agusta S.p.A.

发明人： Vanni, Roberto

IPC分类号： F15B11/042 ,  B64C27/64

CPC分类号： F15B11/0423 ,  B64C27/64 ,  F15B2211/20553 ,  F15B2211/6654

摘要： An aircraft (1) having at least one in-flight attitude control system (4, 5), in turn having at least one actuator (6; 7); and a hydraulic circuit connected to the actuator (6; 7) and having at least one pump (8) designed to deliver a first flow when the pressure of the hydraulic circuit is above a presettable threshold value. The pump (8) is designed to deliver a second flow greater than the first flow, and the aircraft (1) has a sensor (11a, 11b, 12, 13) for detecting a quantity associated with the pressure of the hydraulic circuit; and a programmable central control unit (10), which controls the pump (8) to deliver the second flow when the quantity detected by the sensor (11a, 11b, 12, 13) corresponds to a pressure of the hydraulic circuit below the threshold value.

摘要翻译： 1。具有至少一个飞行中姿态控制系统（4,5）的飞机（1），所述飞行姿态控制系统又具有至少一个致动器（6; 7）; 以及连接到所述致动器（6; 7）并具有至少一个泵（8）的液压回路，所述泵设计成当所述液压回路的压力高于可预设的阈值时输送第一流量。 泵（8）被设计成输送大于第一流量的第二流量，并且飞机（1）具有用于检测与液压回路的压力相关的量的传感器（11a，11b，12,13） 以及可编程中央控制单元（10），当由所述传感器（11a，11b，12,13）检测到的量对应于所述液压回路的压力低于所述阈值时，所述可编程中央控制单元（10）控制所述泵（8） 。

公开(公告)号：EP4406834A1

公开(公告)日：2024-07-31

申请号：EP23217802.0

申请日：2023-12-18

申请人： Textron Innovations Inc.

发明人： Harrell, Clifton Lee

IPC分类号： B64C27/64 ,  B64C13/50 ,  B64C27/605 ,  G05D109/25

CPC分类号： B64C27/64 ,  B64C13/503 ,  B64C27/605

摘要： In an embodiment, an aircraft such as a rotorcraft (101) includes an actuator (401) and a flight control computer (205) interfaced with the actuator (401). The flight control computer (205) is configured to: increase an initiating force output by an initiating channel (403) of the actuator; stop the increasing of the initiating force in response to observing restraining forces on restraining channels (403) of the actuator; hold the initiating force at a quiescent initiating value while the restraining channels (403) hold the restraining forces at quiescent restraining values; increase the initiating force to a target initiating value while the restraining channels (403) increase the restraining forces to target restraining values; calculate a force fight test result by summing a difference between the target initiating value and the quiescent initiating value with differences between the target restraining values and the quiescent restraining values; and indicate the actuator failed verification in response to the force fight test result being greater than a first predetermined threshold.

公开(公告)号：EP3290332B1

公开(公告)日：2018-09-12

申请号：EP17186225.3

申请日：2017-08-14

申请人： Honeywell International Inc.

发明人： FUTA, JR., Paul W. ,  SHELBY, Dugan ,  DUTKA, Martin ,  MCROBERTS, Brad

IPC分类号： B64C11/38 ,  B64C27/64 ,  F16K31/122

CPC分类号： B64C11/38 ,  B64C11/385 ,  B64C27/64

摘要： A propeller pitch control actuation system includes a relatively lightweight, relatively inexpensive means for selectively preventing the propeller pitch control actuator from commanding reverse pitch positions.

公开(公告)号：EP3099954A4

公开(公告)日：2017-12-13

申请号：EP15742733

申请日：2015-02-02

申请人： SOCIÉTÉ DE COMMERCIALISATION DES PRODUITS DE LA RECH APPLIQUÉE SOCPRA SCIENCES SANTÉ ET HUMAINES S E

发明人： PLANTE JEAN-SÉBASTIEN ,  DENNINGER MARC ,  CHOUINARD PATRICK ,  JULIÓ GUIFRÉ ,  LUCKING BIGUÉ JEAN-PHILIPPE ,  HUPPÉ NICOLAS ,  DESROSIERS JEAN-FRANÇOIS

IPC分类号： F16D37/02 ,  F16D27/00

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： In some embodiments, a rotorcraft flight control actuator includes a driving member configured to receive mechanical energy from a power source, a driven member, a magnetorheological (MR) fluid 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 a flight control device of a rotor system, and a magnetic circuit configured to deliver a magnetic field towards the MR fluid, the magnetic circuit configured to vary the strength of the magnetic field in response to inputs.

公开(公告)号：EP3218614A1

公开(公告)日：2017-09-20

申请号：EP15797380.1

申请日：2015-11-13

申请人： Domin Fluid Power Limited

发明人： COLLINS, Andrew John

IPC分类号： F15B18/00

CPC分类号： F15B18/00 ,  B64C27/64 ,  F15B9/09 ,  F15B13/0406 ,  F15B2211/8757

摘要： A servo actuator (1) comprises an actuator housing (4); an actuator member (2) located within the actuator housing (4) and at least one spool (8) located in a cavity (6) formed within the actuator housing (4). The housing (4) also comprises a first set of internal ports including an inlet port (P), an outlet port (T) and a pair of control ports (SI, S2), the inlet port (P) being arranged for connection to a first pressurised supply and a second set of internal ports comprising an inlet port (P' ), an outlet port (T' ) and a pair of control ports (SI', S2'), the inlet port (P' ) being arranged for connection to a second pressurised supply. In use, movement of the spool (8) alters the flow path of fluid through the first and second set of internal ports to control the movement of the actuator member (2).

摘要翻译： 伺服致动器1被提供。 伺服致动器1包括：致动器壳体4; 位于致动器壳体4内的致动器构件2; 以及位于致动器壳体4内形成的空腔6中的至少一个阀芯8.壳体4还包括第一组内部端口，该第一组内部端口包括入口端口P，出口端口T和一对控制端口S1，S2， 入口端口P连接到第一加压供应源; 以及第二组内部端口，其包括入口端口P，出口端口T; 和一对控制口S1，S2，入口P连接到第二加压供应。 在使用中，卷轴8的移动改变了流过第一和第二组内部端口的流体的流动路径，以控制致动器构件2的移动。

公开(公告)号：EP3130537A1

公开(公告)日：2017-02-15

申请号：EP16180081.8

申请日：2016-07-19

申请人： Airbus Helicopters

发明人： SEQUERA, Damien ,  JALAGUIER, Jean-Pierre ,  GREGORCZYK, Wojciech

IPC分类号： B64C27/51 ,  B64C27/635 ,  F16F13/06

CPC分类号： B64C27/635 ,  B64C27/51 ,  B64C27/64 ,  B64D45/00 ,  F16F13/06

摘要： La présente invention concerne un dispositif d'amortissement (7) muni d'un premier organe de liaison (10), d'un deuxième organe de liaison (20), d'un organe élastique (80) et d'un système hydraulique (30). Le système hydraulique (30) comporte un carter extérieur (31) et une tige (40), ledit premier organe de liaison (10) étant fixé de manière réversible au carter extérieur (31), ledit organe élastique (80) étant disposé autour d'une partie saillante (43) de la tige (40), ledit organe élastique (80) comportant au moins un moyen élastique (83) interposé entre une première armature (81) et une deuxième armature (82), la première armature (81) étant fixée de manière réversible audit carter extérieur (31), la deuxième armature (82) étant solidaire en translation de ladite partie saillante (43), ledit deuxième organe de liaison (20) étant fixé de manière réversible à ladite partie saillante (43).

摘要翻译： 具有第一连接构件，第二连接构件，弹性构件和液压系统的阻尼装置。 所述液压系统包括外壳和杆，所述第一连接构件以可逆方式紧固到所述外壳，所述弹性构件围绕所述杆的突出部分布置，所述弹性构件包括插入在所述外壳之间的至少一个弹性装置 第一强度构件和第二强度构件，第一强度构件被可逆地紧固到外壳，第二强度构件被限制为与突出部分平移地移动，并且连接构件被可逆地紧固到突出部 一部分。

公开(公告)号：EP3069990A1

公开(公告)日：2016-09-21

申请号：EP15400013.7

申请日：2015-03-20

申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH

发明人： Grohmann, Boris ,  Rohr, Thomas ,  Klaubert, Jens

IPC分类号： B64C13/46

CPC分类号： B64C13/46 ,  B64C13/08 ,  B64C13/22 ,  B64C27/04 ,  B64C27/605 ,  B64C27/64 ,  Y02T50/44

摘要： The invention relates to an artificial force feel generating device 6 for generation of an artificial feeling of force on an inceptor 4a of a vehicle control system 10, said inceptor 4a being adapted for controlling a servo-assisted control unit 4, 3 of said vehicle control system 10 via a mechanical linkage 5, wherein at least one first force generating device and at least one second force generating device are mechanically connected to said inceptor 4a, said first force generating device being provided for generating a nominal force acting in operation on said inceptor 4a and said second force generating device being provided for generating a tactile cue force acting in operation on said inceptor 4a, said first and second force generating devices being arranged in parallel. The invention relates further to an aircraft comprising such an artificial force feel generating device.

摘要翻译： 本发明涉及一种在人造力感觉的车辆控制系统10的操纵器4a中生成装置6生成的力上的人工感觉，说操纵器4A是用于控制所述车辆的控制的伺服辅助的控制单元4，3 angepasst 通过机械联动装置5的系统10中，worin至少一个第一力产生装置和至少一个第二力产生装置机械地连接到所述操纵器4a中，所述提供用于产生在所述操纵器在外科手术中起作用的公称力第一力产生装置 图4a和所述被设置用于产生在手术在所述操纵器4a中作用的触觉提示力的第二力产生装置，所述平行布置的第一和第二力产生装置。 本发明在包括进一步涉及飞机试图强行人工感觉产生装置。

公开(公告)号：EP2812764A4

公开(公告)日：2016-07-06

申请号：EP13787117

申请日：2013-02-08

申请人： MERLIN TECHNOLOGY INC

发明人： ALBION NICOLAS ,  BARTEL MARK ,  FEIFEL MARC ,  MARVIN MARK ,  MERCER JOHN

IPC分类号： B64C13/18 ,  B64C13/42 ,  B64C27/04 ,  B64C27/56 ,  B64C27/57 ,  B64C27/64 ,  B64C27/68 ,  G05D1/08 ,  G05D1/10

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.

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。