公开(公告)号：EP2439139A2

公开(公告)日：2012-04-11

申请号：EP11184315.7

申请日：2011-10-07

申请人： Nabtesco Corporation

发明人： Nakagawa, Shingo ,  Fukui, Atsushi

IPC分类号： B64C13/42

CPC分类号： B64C13/42 ,  Y02T50/44

摘要： A hydraulic pump is installed inside a wing at which a control surface is provided, and supplies pressure oil to an actuator when a loss or degradation occurs in the function of aircraft central hydraulic power sources. An electric motor is installed inside the wing and drives the backup hydraulic pump. A driver is installed inside the wing and drives the electric motor. A cooling device is installed inside the wing and simultaneously cools the backup hydraulic pump, the electric motor, and the driver.

公开(公告)号：EP2381322A2

公开(公告)日：2011-10-26

申请号：EP11163677.5

申请日：2011-04-26

申请人： Nabtesco Corporation

发明人： Nakagawa, Shingo ,  Fukui, Atsushi

IPC分类号： G05B9/03

CPC分类号： G05B9/03 ,  B64C13/42 ,  G05B23/0237 ,  G05B2219/14014 ,  G05B2219/24182 ,  G05B2219/24188 ,  G05B2219/24191 ,  G05D1/0077

摘要： An operation control apparatus includes a command generation portion that generates a command signal for commanding operation of a control surface, and first and second monitoring portions that monitor an abnormality of operation of first and second control portions, respectively, of the actuator control apparatus. The actuator control apparatus includes first and second control portions that generate a control signal for an actuator for driving the control surface and that are different in design, and a switching unit that switches the connection to the actuator from one of the first and second control portions to the other, when an abnormality is detected by the first and second monitoring portions. Accordingly, it is possible to monitor a generic failure, and realize redundancy enabling control of the overall operation of the actuator, from start to finish, when a generic failure has occurred, thus realizing further simplification and streamlining of the configuration.

摘要翻译： 操作控制装置包括：命令生成部，其生成用于指示控制面的操作的指令信号;以及第一和第二监视部，分别监视致动器控制装置的第一和第二控制部的动作异常。 致动器控制装置包括第一和第二控制部分，其产生用于驱动控制表面并且设计不同的致动器的控制信号;以及切换单元，其从第一和第二控制部分之一切换到致动器的连接 另一方面，当第一和第二监视部分检测到异常时。 因此，当发生一般的故障时，可以监视一般的故障，并实现从始至终的致动器的整体操作的冗余，从而进一步简化和简化配置。

公开(公告)号：EP2631171B1

公开(公告)日：2019-09-04

申请号：EP13156715.8

申请日：2013-02-26

申请人： Nabtesco Corporation

发明人： Fukui, Atsushi

IPC分类号： B64C13/40 ,  B64C13/42

公开(公告)号：EP2402247A3

公开(公告)日：2017-07-05

申请号：EP11172137.9

申请日：2011-06-30

申请人： Nabtesco Corporation

发明人： Fukui, Atsushi

IPC分类号： B64C13/42

CPC分类号： B64C13/42 ,  F15B18/00 ,  F15B2211/20576 ,  F15B2211/62 ,  F15B2211/8752 ,  Y02T50/44

摘要： When a loss or degradation in the function of one of a first aircraft central hydraulic power source (104) and a second aircraft central hydraulic power source (105) occurs, a controller performs a control so as to operate the other backup hydraulic pump, out of a first backup hydraulic pump (18a) and a second backup hydraulic pump (18b), which is connected downstream of the other hydraulic power source, which is the other of the first and second aircraft central hydraulic power sources. Oil flowing through the other backup hydraulic pump is cooled by an oil cooler of the other hydraulic power source by operation of the other backup hydraulic pump in a state where the other hydraulic power source is being operated.

摘要翻译： 当第一飞机中央液压动力源（104）和第二飞机中央液压动力源（105）中的一个发生功能损失或降级时，控制器执行控制以便操作另一个备用液压泵， 第一备用液压泵18a和第二备用液压泵18b连接，该第二备用液压泵18b连接在作为第一和第二飞机中央液压源中的另一个的另一液压动力源的下游。 在另一个液压动力源被操作的状态下，通过另一个备用液压泵的操作，流过另一个备用液压泵的油被另一个液压动力源的油冷却器冷却。

公开(公告)号：EP2457825A3

公开(公告)日：2017-05-10

申请号：EP11191062.6

申请日：2011-11-29

申请人： Nabtesco Corporation

发明人： Fukui, Atsushi ,  Takagi, Norimasa

IPC分类号： B64C13/42

CPC分类号： B64C13/42 ,  F15B2211/20592 ,  F15B2211/30505 ,  F15B2211/50536 ,  F15B2211/5753 ,  F15B2211/6313 ,  F15B2211/6336 ,  F15B2211/6651 ,  F15B2211/7107 ,  F15B2211/8757

摘要： A first actuator (14a) drives a control surface (103a) by being operated by supply of pressure oil from a first aircraft central hydraulic power source (104) including a first aircraft central hydraulic pump (104a) . A second actuator (14b) drives the control surface by being operated by supply of pressure oil from a second aircraft central hydraulic power source (105) including a second aircraft central hydraulic pump (105a) . A backup hydraulic pump (18) is installed inside a wing (102a) of the aircraft (100) and is provided so as to be able to supply pressure oil to the first actuator (14a) when a loss or degradation in a function of at least one of the first aircraft central hydraulic power source (104) and the second aircraft central hydraulic power source (105) occurs. A maximum discharge pressure of the backup hydraulic pump (18) is set to be greater than maximum discharge pressures of the first aircraft central hydraulic pump (104a) and the second aircraft central hydraulic pump (104b).

公开(公告)号：EP2386485A3

公开(公告)日：2017-05-03

申请号：EP11166014.8

申请日：2011-05-13

申请人： Nabtesco Corporation

发明人： Fukui, Atsushi

IPC分类号： B64C13/40 ,  B64C13/42

CPC分类号： B64C13/42 ,  B64C13/504 ,  Y02T50/44

摘要： A pump unit installed inside a wing (102) includes a backup hydraulic pump (20) that can supply pressure oil to an actuator (104) when a loss or reduction occurs in the function of an aircraft central hydraulic power source (105) and an electric motor that drives the pump. A wing structure (102) portion forming the surface structure of the wing is provided with an inlet port and an exhaust port that are formed therethrough. The inlet port is provided so as to be opened and closed by an inlet port opening/closing portion, and the exhaust port is provided so as to be opened and closed by an exhaust port opening/closing portion.

摘要翻译： 安装在机翼（102）内的泵单元包括备用液压泵（20），当在飞行器中央液压动力源（105）的功能中发生损失或减少时，可以向致动器（104）供应压力油 驱动泵的电动机。 形成翼的表面结构的翼结构（102）部分设置有穿过其形成的入口和排气口。 入口端口设置成由入口开闭部分打开和关闭，并且排气口设置成由排气口打开/关闭部分打开和关闭。

公开(公告)号：EP2381322A3

公开(公告)日：2013-09-18

申请号：EP11163677.5

申请日：2011-04-26

申请人： Nabtesco Corporation

发明人： Nakagawa, Shingo ,  Fukui, Atsushi

IPC分类号： G05B9/03 ,  B64C13/00 ,  G05B23/02 ,  G05D1/00

CPC分类号： G05B9/03 ,  B64C13/42 ,  G05B23/0237 ,  G05B2219/14014 ,  G05B2219/24182 ,  G05B2219/24188 ,  G05B2219/24191 ,  G05D1/0077

摘要： An operation control apparatus includes a command generation portion that generates a command signal for commanding operation of a control surface, and first and second monitoring portions that monitor an abnormality of operation of first and second control portions, respectively, of the actuator control apparatus. The actuator control apparatus includes first and second control portions that generate a control signal for an actuator for driving the control surface and that are different in design, and a switching unit that switches the connection to the actuator from one of the first and second control portions to the other, when an abnormality is detected by the first and second monitoring portions. Accordingly, it is possible to monitor a generic failure, and realize redundancy enabling control of the overall operation of the actuator, from start to finish, when a generic failure has occurred, thus realizing further simplification and streamlining of the configuration.

公开(公告)号：EP2634425A2

公开(公告)日：2013-09-04

申请号：EP13156713.3

申请日：2013-02-26

申请人： Nabtesco Corporation

发明人： Fukui, Atsushi

IPC分类号： F04B1/12 ,  F04B1/20 ,  F04B1/32

摘要： A rotational shaft 22 receives input of torque that is output from an electric motor 19. A housing 23 rotatably supports the rotational shaft 22. A cylinder block 24 inside the housing 23 rotates with the rotational shaft 22. The pistons 25 are supported relative to the respective cylinder chambers 24a in the cylinder block 24 so as to be slidably displaceable. A swash plate 26 is provided so as to come into contact with ends of the pistons 25 and be rotatable around the rotational shaft 22 with the pistons 25, and be rotatable about a rotation centerline that is obliquely inclined relative to the rotational shaft 22. A case 27 inside the housing 23 is pivotably supported relative to the housing 23. A bearing portion 28 holds the swash plate 26 relative to the case 27 so as to be rotatable around the rotation centerline.

公开(公告)号：EP2617646A2

公开(公告)日：2013-07-24

申请号：EP13150850.9

申请日：2013-01-10

申请人： Nabtesco Corporation

发明人： Takeda, Minoru ,  Fukui, Atsushi

IPC分类号： B64C13/42 ,  B64C13/50

CPC分类号： F04B17/03 ,  B64C13/42 ,  B64C13/50 ,  B64C13/504 ,  Y02T50/44

摘要： A backup hydraulic pump (17) supplies pressure oil to an actuator (11a) when a loss or degradation of the function of an aircraft central hydraulic power source (104) occurs. A control valve (15a, 15b) controls the operation of the actuator (11a) by controlling supply and discharge of the pressure oil to/from the actuator (11a). The control valve has a main body (27) provided with a pressure oil port (32a-f), a spool portion (28) that moves in a sliding manner within the main portion and switches a path of the pressure oil, and a drive portion (29). The drive portion (29) is connected to an end of the spool portion (28) and drives the spool portion (28) by electromagnetic force so as to control the position of the spool portion (28) based on an electric signal.

摘要翻译： 当发生航空器中央液压动力源（104）的功能的损失或劣化时，备用液压泵（17）向致动器（11a）供应压力油。 控制阀（15a，15b）通过控制向执行器（11a）的供给和排出压力油来控制致动器（11a）的操作。 控制阀具有设置有压力油口（32a-f）的主体（27），在主体部内以滑动方式移动的阀芯部（28），切换压力油的路径，驱动 部分（29）。 驱动部分29连接到卷轴部分28的端部，并通过电磁力驱动卷轴部分28，以便基于电信号控制卷轴部分28的位置。