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1.发明授权
公开(公告)号：EP2581798B1
公开(公告)日：2017-02-08
申请号：EP12006436.5
申请日：2012-09-13
申请人： Airbus Helicopters
发明人： Mezan, Serge
CPC分类号： B64C27/78 , B64C13/22 , B64C13/44 , G05D1/0808 , G05D1/0825 , G05D1/0858
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公开(公告)号：EP3078101B1
公开(公告)日：2018-07-11
申请号：EP14789182.4
申请日：2014-09-19
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公开(公告)号：EP0236583A1
公开(公告)日：1987-09-16
申请号：EP86200408.2
申请日：1986-03-14
申请人： THE BOEING COMPANY
发明人： Herzog, Hans Karl , Sakurai, Seiya
CPC分类号： B64C13/503 , G05D1/0077 , Y02T50/54
摘要： An all-electric powered flight control system for an aircraft incorporating fault-tolerant avionics com3 bined with a redundant power actuation control system utilizing electro-mechanical devices for actuating aero3 dynamic control surfaces; and wherein, the redundancy is implemented through the division of the total aerody3 namic surface area to be actuated into multi-segments, with each control segment having its own channel in the avionic control system. The avionic control system is effective in minimizing the effects of power actuated control loads reacting through aircraft structure by the incorporation of an electronic gain control power module which is positioned between the power output side of an actuator (e.g., an electro-mechanical or electro-hydrau3 lic device) and the aerodynamic control surface or seg3 ment being actuated. Further, the avionic control system includes means for passivating a single control segment of the multi-segmented aerodynamic control sur3 face upon the malfunction of either its avionic control channel or its power actuator output.
摘要翻译： 一种全电动飞行控制系统，用于搭载容错航空电子系统的飞机，采用利用机电装置驱动航空3动态控制表面的冗余动力驱动控制系统; 并且其中，冗余通过将待致动的总空气3动力表面积的划分实现为多段，每个控制段在航空电子控制系统中具有其自己的通道。 航空电子控制系统通过结合位于致动器的动力输出侧之间的电子增益控制功率模块（例如，机电或电动机构）来最小化通过飞机结构反应的动力致动控制负载的影响， hydrau3 lic设备）和空气动力学控制表面或区段被启动。 此外，航空电子控制系统包括用于在其航空电子控制通道或其动力致动器输出的故障时钝化多分段空气动力学控制面3的单个控制段的装置。
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公开(公告)号：EP3767112B1
公开(公告)日：2024-09-18
申请号：EP19315074.5
申请日：2019-07-19
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公开(公告)号：EP3767112A1
公开(公告)日：2021-01-20
申请号：EP19315074.5
申请日：2019-07-19
摘要： An actuator control arrangement comprising: a hydraulic actuator (100) having a housing (200) and a piston rod (300) axially moveable within the housing between a neutral position, a retracted position and an extended position with respect to the housing in response to application of pressure to the piston rod; the arrangement further comprising a check valve (130) moveable between a first position (130X) providing a flow path between a pressure source (HP,LP) and the actuator, and a second position (130Y) in which the flow path is closed off; and characterised by a mechanical link (800) between the piston rod and the check valve, actuated in response to the piston rod passing a predetermined retracted position in a negative stroke direction, to set the check valve to the first position.
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6.发明公开SYSTEMS AND METHODS FOR OPERATING FLIGHT CONTROL SURFACES 审中-公开德国维也纳国家石油公司（VERFAHREN ZURBETÄTIGUNGVONFLUGSTEUERUNGSOBERFLÄCHEN）
公开(公告)号：EP2957500A1
公开(公告)日：2015-12-23
申请号：EP15165612.1
申请日：2015-04-29
申请人： The Boeing Company
发明人： Coffman, Jeffrey C
CPC分类号： B64C13/16 , B64C9/00 , 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。 一个系统包括具有两件式轴的控制装置，该两件式轴包括第一轴部分和第二轴部分，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且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：EP0236583B1
公开(公告)日：1989-12-13
申请号：EP86200408.2
申请日：1986-03-14
申请人： THE BOEING COMPANY
发明人： Herzog, Hans Karl , Sakurai, Seiya
CPC分类号： B64C13/503 , G05D1/0077 , Y02T50/54
摘要： An all-electric powered flight control system for an aircraft incorporating fault-tolerant avionics com3 bined with a redundant power actuation control system utilizing electro-mechanical devices for actuating aero3 dynamic control surfaces; and wherein, the redundancy is implemented through the division of the total aerody3 namic surface area to be actuated into multi-segments, with each control segment having its own channel in the avionic control system. The avionic control system is effective in minimizing the effects of power actuated control loads reacting through aircraft structure by the incorporation of an electronic gain control power module which is positioned between the power output side of an actuator (e.g., an electro-mechanical or electro-hydrau3 lic device) and the aerodynamic control surface or seg3 ment being actuated. Further, the avionic control system includes means for passivating a single control segment of the multi-segmented aerodynamic control sur3 face upon the malfunction of either its avionic control channel or its power actuator output.
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