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公开(公告)号：EP2386485B1
公开(公告)日：2018-11-28
申请号：EP11166014.8
申请日：2011-05-13
申请人： Nabtesco Corporation
发明人： Fukui, Atsushi
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.
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公开(公告)号：EP2381322B1
公开(公告)日：2018-09-26
申请号：EP11163677.5
申请日：2011-04-26
申请人： Nabtesco Corporation
发明人： Nakagawa, Shingo , Fukui, Atsushi
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.
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3.发明公开Damping test method, control apparatus, hydraulic system, and program 有权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
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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公开(公告)号：EP2383181A2
公开(公告)日：2011-11-02
申请号：EP11164151.0
申请日：2011-04-28
申请人： Nabtesco Corporation
发明人： Nakagawa, Shingo , Fukui, Atsushi
CPC分类号： B64C13/40 , B64C13/42 , F15B2211/20515 , F15B2211/20576 , F15B2211/62 , F15B2211/8633 , Y02T50/44
摘要： A pump unit (12) installed inside a wing (100), and a panel body (11) constituting part of a wing structure portion forming a surface structure of the wing (100) are provided. The pump unit (12) includes a backup hydraulic pump (13) that can supply pressure oil to an actuator when a loss or reduction occurs in the function of an aircraft central hydraulic power source and an electric motor (14) that drives this pump. Except for at least the panel body, the wing structure portion is formed from fiber reinforced plastics. The panel body (11) is formed of a metallic material.
摘要翻译： 设置在机翼（100）内的泵单元（12）和构成机翼（100）的表面结构的机翼结构部分的一部分的面板体（11）。 泵单元（12）包括备用液压泵（13），当在飞行器中央液压动力源和驱动该泵的电动机（14）的功能中发生损失或减少时，能够向致动器供应压力油。 除了至少面板主体之外，翼结构部分由纤维增强塑料形成。 面板主体（11）由金属材料形成。
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公开(公告)号：EP2412629B1
公开(公告)日：2018-12-12
申请号：EP11175545.0
申请日：2011-07-27
申请人： Nabtesco Corporation
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.
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6.发明公开
公开(公告)号：EP2412629A3
公开(公告)日：2017-07-05
申请号：EP11175545.0
申请日：2011-07-27
申请人： Nabtesco Corporation
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，以及当致动器附接到控制表面（104,105）时待测试的致动器（11,12）的压力油的温度和控制表面（104,105）的操作速度 控制面。 控制装置通过使用压力油温度和控制表面操作速度来校正控制表面的理想速度特性。 控制装置参照修正后的理想速度特性，通过使用引起控制表面操作速度波动的波动因子的波动范围的预测值来设置上限和下限，测量压力油温度并且 通过致动控制表面（104,105）的操作速度，待测试的致动器置于阻尼模式，并确定测量值是否落入上限和下限之间的范围内。
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公开(公告)号：EP2383181A3
公开(公告)日：2017-05-31
申请号：EP11164151.0
申请日：2011-04-28
申请人： Nabtesco Corporation
发明人： Nakagawa, Shingo , Fukui, Atsushi
CPC分类号： B64C13/40 , B64C13/42 , F15B2211/20515 , F15B2211/20576 , F15B2211/62 , F15B2211/8633 , Y02T50/44
摘要： A pump unit (12) installed inside a wing (100), and a panel body (11) constituting part of a wing structure portion forming a surface structure of the wing (100) are provided. The pump unit (12) includes a backup hydraulic pump (13) that can supply pressure oil to an actuator when a loss or reduction occurs in the function of an aircraft central hydraulic power source and an electric motor (14) that drives this pump. Except for at least the panel body, the wing structure portion is formed from fiber reinforced plastics. The panel body (11) is formed of a metallic material.
摘要翻译： 提供安装在机翼（100）内的泵单元（12）和构成形成机翼（100）的表面结构的机翼结构部分的一部分的面板体（11）。 泵单元12包括备用液压泵13，该备用液压泵13可以在飞机中央液压动力源和驱动该泵的电动机14的功能发生损失或减少时向致动器供应压力油。 除了至少面板本体外，翼结构部分由纤维增强塑料形成。 面板主体（11）由金属材料形成。
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8.发明公开Aircraft control apparatus and aircraft control system 审中-公开Flugzeugsteuerungsvorrichtung und Flugzeugsteuerungssystem
公开(公告)号：EP2595023A3
公开(公告)日：2015-03-18
申请号：EP12192728.9
申请日：2012-11-15
CPC分类号： G06F17/00 , B64C13/503 , G05D1/0077
摘要： A plurality of control channels each include a power supply, an interface that receives a manipulation signal, an arithmetic processing portion that calculates and generates an operation command signal for actuators based on the manipulation signal, and a signal determination unit that determines a control signal for finally controlling the operation of the actuators and outputs the control signal. The arithmetic processing portions respectively provided in the plurality of control channels have designs different from one another. Each of the signal determination units determines the control signal by receiving a first operation command signal generated by the arithmetic processing portion of the control channel in which that signal determination unit is provided, and a second operation command signal generated in the arithmetic processing portion of another of the control channels, and comparing the first operation command signal and the second operation command signal, and outputs the control signal.
摘要翻译： 多个控制通道各自包括电源，接收操作信号的接口，运算处理部分，其基于操作信号计算并产生用于致动器的操作命令信号;以及信号确定单元，其确定用于 最后控制执行器的运行并输出控制信号。 分别设置在多个控制通道中的算术处理部分具有彼此不同的设计。 每个信号确定单元通过接收由其中提供该信号确定单元的控制信道的运算处理部分产生的第一操作命令信号和在另一个的算术处理部分中生成的第二操作命令信号来确定控制信号 并且比较第一操作命令信号和第二操作命令信号，并输出控制信号。
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公开(公告)号：EP2595023A2
公开(公告)日：2013-05-22
申请号：EP12192728.9
申请日：2012-11-15
CPC分类号： G06F17/00 , B64C13/503 , G05D1/0077
摘要： A plurality of control channels each include a power supply, an interface that receives a manipulation signal, an arithmetic processing portion that calculates and generates an operation command signal for actuators based on the manipulation signal, and a signal determination unit that determines a control signal for finally controlling the operation of the actuators and outputs the control signal. The arithmetic processing portions respectively provided in the plurality of control channels have designs different from one another. Each of the signal determination units determines the control signal by receiving a first operation command signal generated by the arithmetic processing portion of the control channel in which that signal determination unit is provided, and a second operation command signal generated in the arithmetic processing portion of another of the control channels, and comparing the first operation command signal and the second operation command signal, and outputs the control signal.
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公开(公告)号：EP2457825A2
公开(公告)日：2012-05-30
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).
摘要翻译： 第一致动器（14a）通过从包括第一飞机中央液压泵（104a）的第一飞机中央液压动力源（104）供应压力油而操作，从而驱动控制表面（103a）。 第二致动器（14b）通过从包括第二飞机中央液压泵（105a）的第二飞机中央液压动力源（105）供应压力油而操作，从而驱动控制表面。 备用液压泵（18）安装在飞机（100）的机翼（102a）内部，并且设置成能够在第一致动器（14a）的功能损失或劣化时向第一致动器 发生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）中的至少一个。 备用液压泵（18）的最大排出压力被设定为大于第一飞机中央液压泵（104a）和第二飞机中央液压泵（104b）的最大排出压力。
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