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1. 发明申请

US20070080261A1 Method for load limitation in drive systems for a high lift system for aeroplanes 失效
标题翻译：用于飞机高升力系统的驱动系统中的负载限制方法
公开(公告)号：US20070080261A1
公开(公告)日：2007-04-12
申请号：US10579420
申请日：2004-11-12
申请人： Uwe Neumann , Udo Carl , Ben Holert
发明人： Uwe Neumann , Udo Carl , Ben Holert
IPC分类号： G05D1/00
CPC分类号： B64D45/0005 , B64D2045/001
摘要： The invention relates to a device for load limitation in a aircraft high lift system, said system comprising individual segments of landing flap systems and slat flap systems, and a drive unit. The inventive device for load limitation comprises a control unit that is connected to position sensors and is embodied in such a way as to process signals from the position sensors and to generate a signal for limiting the supplied drive power. The invention also relates to a method for load limitation. According to said method, signals from at least two position sensors are measured; at least one reference variable is calculated form the measured signals; each reference variable is compared with a corresponding threshold value pre-determined from a maximum authorized load; and a control signal is generated for limiting the drive power, when at least one of the reference variables reaches or exceeds the threshold value.
摘要翻译：本发明涉及一种用于飞机高升降系统中的负载限制的装置，所述系统包括着陆挡板系统和板条翼片系统的单独部分以及驱动单元。本发明的用于负载限制的装置包括连接到位置传感器的控制单元，并且以这样的方式实现，以便处理来自位置传感器的信号并产生用于限制所提供的驱动功率的信号。本发明还涉及一种用于负载限制的方法。根据所述方法，测量来自至少两个位置传感器的信号; 从测量信号计算出至少一个参考变量; 将每个参考变量与从最大授权负载预先确定的对应阈值进行比较; 并且当至少一个参考变量达到或超过阈值时，产生用于限制驱动功率的控制信号。

2. 发明授权

US08074937B2 Method for load limiting in drive systems for aircraft high lift systems 失效
标题翻译：用于飞机高升力系统的驱动系统中的负载限制方法
公开(公告)号：US08074937B2
公开(公告)日：2011-12-13
申请号：US10579420
申请日：2004-11-12
申请人： Udo Carl , Uwe Neumann , Ben Holert
发明人： Udo Carl , Uwe Neumann , Ben Holert
IPC分类号： B64C13/16
CPC分类号： B64D45/0005 , B64D2045/001
摘要： The invention relates to a device for load limitation in a aircraft high lift system, said system comprising individual segments of landing flap systems and slat flap systems, and a drive unit. The inventive device for load limitation comprises a control unit that is connected to position sensors and is embodied in such a way as to process signals from the position sensors and to generate a signal for limiting the supplied drive power. The invention also relates to a method for load limitation. According to said method, signals from at least two position sensors are measured; at least one reference variable is calculated form the measured signals; each reference variable is compared with a corresponding threshold value pre-determined from a maximum authorized load; and a control signal is generated for limiting the drive power, when at least one of the reference variables reaches or exceeds the threshold value.
摘要翻译：本发明涉及一种用于飞机高升降系统中的负载限制的装置，所述系统包括着陆挡板系统和板条翼片系统的单独部分以及驱动单元。本发明的用于负载限制的装置包括连接到位置传感器的控制单元，并且以这样的方式实现，以便处理来自位置传感器的信号并产生用于限制所提供的驱动功率的信号。本发明还涉及一种用于负载限制的方法。根据所述方法，测量来自至少两个位置传感器的信号; 从测量信号计算出至少一个参考变量; 将每个参考变量与从最大授权负载预先确定的对应阈值进行比较; 并且当至少一个参考变量达到或超过阈值时，产生用于限制驱动功率的控制信号。

3. 发明申请

US20070102589A1 Drive and Guide Arrangement for a Flap which is arranged on an Aircraft Mainplane 有权
标题翻译：安装在飞机主板上的襟翼的驱动和导向装置
公开(公告)号：US20070102589A1
公开(公告)日：2007-05-10
申请号：US11456076
申请日：2006-07-06
申请人： Ben Holert
发明人： Ben Holert
IPC分类号： B64C3/50
CPC分类号： B64C9/16
摘要： A drive and guidance apparatus for a flap which is arranged on an aircraft mainplane, in particular for a trailing-edge or landing flap, comprising a six-element guide chain with seven rotating joints with one or more shafts. In this case, a first coupling element, which is mounted via a crank that is connected to the aircraft mainplane such that it can rotate, itself in turn is connected to the flap and to a second coupling element such that it can rotate, which is mounted on the aircraft mainplane such that it can rotate. In this case, the second coupling element is connected to the flap via an oscillating support. According to the invention, the crank is arranged in such a manner that the rotation direction of the crank for extension of the flap corresponds to the rotation direction of the crank for the trailing-edge flap of the starboard wing, with the rotation direction of the crank for the trailing-edge flap of the starboard wing being counterclockwise when viewed from the aircraft fuselage.
摘要翻译：一种用于翼片的驱动和引导装置，其布置在飞行器主板上，特别是用于后缘或落地翼片，包括具有带有一个或多个轴的七个旋转接头的六元件导向链。在这种情况下，通过曲柄安装的第一联接元件，其连接到飞行器主平面，使得其可以旋转，自身依次连接到翼片和第二耦合元件，使得其可旋转，即安装在飞机主飞机上，使其可以旋转。在这种情况下，第二联接元件通过振动支撑件连接到翼片。根据本发明，曲柄被布置成使得用于延伸翼片的曲柄的旋转方向对应于右舷翼的后缘翼片的曲柄的旋转方向，其中旋转方向为从飞机机身观察时，右舷翼的后缘翼的曲柄是逆时针的。

4. 发明授权

US07861978B2 Drive and guide arrangement for a flap which is arranged on an aircraft mainplane 有权
标题翻译：安装在飞机主板上的挡板的驱动和导向装置
公开(公告)号：US07861978B2
公开(公告)日：2011-01-04
申请号：US11456076
申请日：2006-07-06
申请人： Ben Holert
发明人： Ben Holert
IPC分类号： B64C3/50
CPC分类号： B64C9/16
摘要： A drive and guidance apparatus for a trailing-edge/landing flap,-arranged on an aircraft mainplane, the apparatus comprising a six-element guide chain having seven rotating joints and one or more shafts; a first coupling element mounted via a crank connected to the mainplane wherein the crank can rotate, the coupling is connected to the flap and to a second coupling element wherein the first coupling can rotate, the second coupling mounted on the mainplane wherein the second coupling can rotate. The second coupling element is connected to the flap via an oscillating support. The crank is arranged wherein the rotation direction of the crank for extension of the flap corresponds to the rotation direction of the crank for the trailing-edge flap of the starboard wing of the mainplane, with the rotation direction of the crank for the trailing-edge flap of the starboard wing being counterclockwise when viewed from the aircraft fuselage.
摘要翻译：一种用于后缘/着陆挡板的驱动和引导装置，其安排在飞机主板上，该装置包括具有七个旋转接头和一个或多个轴的六元件导向链; 通过连接到主平面的曲柄安装的第一联接元件，其中曲柄可以旋转，联接器连接到翼片和第二联接元件，其中第一联接器可以旋转，第二联接器安装在主平面上，其中第二联接器旋转。第二联接元件通过振荡支撑件连接到翼片。曲柄被布置成其中用于延伸翼片的曲柄的旋转方向对应于主平面右舷翼的后缘翼片的曲柄的旋转方向，曲柄的旋转方向用于后缘从飞机机身观察时，右舷翼的翼片逆时针旋转。

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