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1. 发明申请

WO2007068413A2 METHOD AND DEVICE FOR PROVIDING AUTOMATIC LOAD ALLEVIATION TO A HIGH LIFT SURFACE SYSTEM, IN PARTICULAR TO A LANDING FLAP SYSTEM, OF AN AIRCRAFT 审中-公开
标题翻译：用于向自动负载表示系统提供自动负载校正的方法和装置，特别是对于飞行器的登陆翼片系统
公开(公告)号：WO2007068413A2
公开(公告)日：2007-06-21
申请号：PCT/EP2006/011867
申请日：2006-12-08
申请人： AIRBUS DEUTSCHLAND GMBH , FLEDDERMANN, Andreas , HARTWIG, Wolfgang , DARBOIS, Alexandre , RICHTER, Martin
发明人： FLEDDERMANN, Andreas , HARTWIG, Wolfgang , DARBOIS, Alexandre , RICHTER, Martin
IPC分类号： B64C13/24 , B64D45/00 , G05D1/00
CPC分类号： B64C13/16
摘要： Described are a method and a device for providing automatic load alleviation to a high lift surface system, in particular to a landing flap system, of an aircraft when a blockage occurs, wherein in response to a control signal emitted by a control device (31, 32, 35) at least one high lift surface (11, 12, 21), which is actuated by means of a local mechanical final control element (16, 26), is brought to a predetermined position by a central drive unit (13, 23) that is connected by way of a rotary shaft arrangement (15, 25) to the local final control element (16, 26) by means of generating a torque transmitted by the central drive unit (13, 23) to the rotary shaft arrangement (15, 25). According to the invention, if a signal is registered that indicates that there is a blockage within the high lift surface system, the torque transmitted by the central drive unit (13, 23) to the rotary shaft arrangement (15, 25) is automatically reduced to a predetermined low torque value, and the position of the high lift surface system is fixed.
摘要翻译：描述了一种用于在发生堵塞时向飞行器的高升力表面系统（特别是飞机的起落架系统）提供自动负载减轻的方法和装置，其中响应于由控制装置（31）发出的控制信号， 32,35），通过局部机械终控制元件（16,26）致动的至少一个高升程表面（11,12,21）通过中央驱动单元（13,13）被带到预定位置， 23），其通过产生由中央驱动单元（13,23）传递到旋转轴装置的转矩而通过旋转轴装置（15,25）连接到局部最终控制元件（16,26）（15,25）。根据本发明，如果登记指示高升力面系统内存在堵塞的信号，则由中央驱动单元（13,23）传递到旋转轴装置（15,25）的扭矩被自动减小达到预定的低扭矩值，并且高升程面系统的位置是固定的。

2. 发明申请

WO2007068413A3 METHOD AND DEVICE FOR PROVIDING AUTOMATIC LOAD ALLEVIATION TO A HIGH LIFT SURFACE SYSTEM, IN PARTICULAR TO A LANDING FLAP SYSTEM, OF AN AIRCRAFT 审中-公开
标题翻译：用于向高升力表面系统（特别是着陆襟翼系统）提供对飞行器的自动载荷降低的方法和装置
公开(公告)号：WO2007068413A3
公开(公告)日：2007-08-02
申请号：PCT/EP2006011867
申请日：2006-12-08
申请人： AIRBUS GMBH , FLEDDERMANN ANDREAS , HARTWIG WOLFGANG , DARBOIS ALEXANDRE , RICHTER MARTIN
发明人： FLEDDERMANN ANDREAS , HARTWIG WOLFGANG , DARBOIS ALEXANDRE , RICHTER MARTIN
IPC分类号： B64C13/24 , B64D45/00 , G05D1/00
CPC分类号： B64C13/16
摘要： Described are a method and a device for providing automatic load alleviation to a high lift surface system, in particular to a landing flap system, of an aircraft when a blockage occurs, wherein in response to a control signal emitted by a control device (31, 32, 35) at least one high lift surface (11, 12, 21), which is actuated by means of a local mechanical final control element (16, 26), is brought to a predetermined position by a central drive unit (13, 23) that is connected by way of a rotary shaft arrangement (15, 25) to the local final control element (16, 26) by means of generating a torque transmitted by the central drive unit (13, 23) to the rotary shaft arrangement (15, 25). According to the invention, if a signal is registered that indicates that there is a blockage within the high lift surface system, the torque transmitted by the central drive unit (13, 23) to the rotary shaft arrangement (15, 25) is automatically reduced to a predetermined low torque value, and the position of the high lift surface system is fixed.
摘要翻译：所描述的是一种用于在发生堵塞时向航空器的高升力面系统，尤其是降落襟翼系统提供自动减载的方法和装置，其中响应于由控制装置（31,32）发出的控制信号，其特征在于，至少一个借助于局部机械终端控制元件（16,26）致动的高升力表面（11,12,21）通过中央驱动单元（13,23）被带到预定位置，（15,25）通过产生由所述中央驱动单元（13,23）传递到所述旋转轴装置（16,26）的扭矩而连接到所述局部最终控制元件（16,26）（15,25）。根据本发明，如果登记了指示高升力面系统内存在阻塞的信号，则由中央驱动单元（13,23）传递到旋转轴装置（15,25）的转矩自动减小到预定的低扭矩值，并且高升力面系统的位置是固定的。

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