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1. 发明申请

US20060144996A1 Apparatus for the adjustment of horizontal stabilizers for aircraft 失效
标题翻译：用于调整飞机水平稳定器的装置
公开(公告)号：US20060144996A1
公开(公告)日：2006-07-06
申请号：US11236405
申请日：2005-09-26
申请人： Udo Carl , Axel Votter
发明人： Udo Carl , Axel Votter
IPC分类号： B64C13/00
CPC分类号： B64C13/34 , B64C5/10
摘要： The present disclosure related to an apparatus for the adjustment of horizontal stabilizers for aircraft in relation to the aircraft axis with mechanical power transmission from two drives to the horizontal stabilizer. In accordance with the present disclosure, two differential transmissions coupled via a connection shaft drive the horizontal stabilizer via mechanical transmission means such as a respective spindle and a spindle nut.
摘要翻译：本公开涉及一种用于调整飞行器相对于飞行器轴线的水平稳定器的装置，其具有从两个驱动器到水平稳定器的机械动力传递。根据本公开，通过连接轴联接的两个差速传动器通过诸如相应主轴和主轴螺母的机械传动装置驱动水平稳定器。

2. 发明授权

US4765568A Method and system for controlling the elevator assemblies of an aircraft 失效
标题翻译：用于控制飞机电梯组件的方法和系统
公开(公告)号：US4765568A
公开(公告)日：1988-08-23
申请号：US94831
申请日：1987-09-09
申请人： Udo Carl , Homayoun Dilmaghani
发明人： Udo Carl , Homayoun Dilmaghani
IPC分类号： B64C13/42 , B64C13/50 , G05D1/00 , B64C13/00
CPC分类号： G05D1/0077 , B64C13/42 , B64C13/503 , Y02T50/44
摘要： A fly-by-wire control system for the elevator assemblies of an aircraft isquipped with a mechanical auxiliary control (8) and with a synchronizing coupling (10). The electrical control links connecting the controlling computers to the elevator drives are each equipped with an override mechanism (4,2). A mechanical cable link (9) of the auxiliary mechanical control (8) connects a pilot operated mechanical control member such as a pitch control wheel having a detent to the respective override mechanism. This combination makes sure that the pilot initiated control signals have performance priority over any other signals at all times. The synchronizing coupling (10) is arranged between the mechanical control links leading to the respective elevator flap drives to assure a symmetric flap deflection on both sides at high speed flight under failure conditions. Centering springs (12) assure a centered position of the flap if the respective flap side signal transmission linkage (4.4) is affected by a mechanical failure (rupture) at low speed.
摘要翻译：用于飞行器的电梯组件的线控控制系统配备有机械辅助控制（8）和同步联轴器（10）。将控制计算机连接到电梯驱动器的电气控制链路各配备有超控机构（4,2）。辅助机械控制器（8）的机械电缆连杆（9）将诸如具有制动器的俯仰控制轮的先导操作的机械控制构件连接到相应的超越机构。这种组合确保导频发起的控制信号始终具有优于任何其他信号的性能优先级。同步联轴器（10）设置在通向相应电梯折翼驱动器的机械控制连杆之间，以确保在故障条件下高速飞行时两侧的对称翼片偏转。如果相应的挡板侧信号传动联动装置（4.4）受到低速机械故障（破裂）的影响，定心弹簧（12）可确保挡板的中心位置。

3. 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。

4. 发明授权

US07464896B2 Apparatus for the adjustment of horizontal stabilizers for aircraft 失效
标题翻译：用于调整飞机水平稳定器的装置
公开(公告)号：US07464896B2
公开(公告)日：2008-12-16
申请号：US11236405
申请日：2005-09-26
申请人： Udo Carl , Axel Vötter
发明人： Udo Carl , Axel Vötter
IPC分类号： B64C13/00
CPC分类号： B64C13/34 , B64C5/10
摘要： An apparatus is described for the adjustment of horizontal stabilizers for aircraft in relation to the aircraft axis with mechanical power transmission from two drives to the horizontal stabilizer. The apparatus may include two differential transmissions coupled via a connection shaft that drive the horizontal stabilizer via a mechanical transmission, such as a respective spindle and a spindle nut.
摘要翻译：描述了一种用于调整相对于飞机轴线的飞行器的水平稳定器的装置，其具有从两个驱动器到水平稳定器的机械动力传递。该装置可以包括经由连接轴联接的两个差速传动装置，所述连接轴通过诸如相应主轴和主轴螺母的机械传动装置驱动水平稳定器。

5. 发明授权

US06536714B2 Pressure control system for a pressure-expandable displacement element 失效
公开(公告)号：US06536714B2
公开(公告)日：2003-03-25
申请号：US09837637
申请日：2001-04-17
申请人： Wolfgang Gleine , Knut Mau , Udo Carl
发明人： Wolfgang Gleine , Knut Mau , Udo Carl
IPC分类号： B64C344
CPC分类号： B64C9/24 , B64C3/46 , Y02T50/14 , Y02T50/32
摘要： An elastically expandable hollow displacement element is secured to the rear surface of an aircraft wing slat. When the displacement element is contracted, the slat may be retracted onto the wing's leading edge. When the slat is extended, the displacement element is expanded to protrude convexly from the slat, thereby preventing vortex formation in the slat air gap and reducing aero-acoustic noise. A pressure control system for inflating and deflating the displacement element includes a bleed air line connected from the aircraft engine bleed air system to the displacement element, a shut-off valve and a pressure control valve interposed in series in the bleed air line, and a slat contour controller connected by respective signal lines to the valves, which control the quantity and the pressure of the bleed air supplied into the displacement element, for properly inflating the same.

6. 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。

7. 发明授权

US6023134A Power conversion system for bi-directional conversion between hydraulic power and electrical power 失效
标题翻译：电力转换系统，用于液压和电力之间的双向转换
公开(公告)号：US6023134A
公开(公告)日：2000-02-08
申请号：US958416
申请日：1997-10-27
申请人： Udo Carl , Wolfgang Besing , Stefan Frischemeier
发明人： Udo Carl , Wolfgang Besing , Stefan Frischemeier
IPC分类号： F02C7/32 , H02K7/18 , F03B3/10 , F03B13/00
CPC分类号： F02C7/32 , Y02T50/671 , Y10S60/911
摘要： A bi-directional power conversion system interconnects hydraulic and electrical power systems on-board a vehicle such as an air-craft, whereby the power conversion system can selectively convert available electrical power to needed hydraulic power or vice versa. The power conversion system includes a hydraulic machine (15) connected to the hydraulic system (10) of the vehicle, an electrical machine (20) connected to the electrical system (3) of the vehicle through a power converter and control unit (22), a rotational drive shaft (14) mechanically interconnecting the hydraulic machine (15) and the electrical machine (20), and a priority and safety control unit (26) that controls the operation of the system. In a first operating mode, for example in the event of a failure of a primary electrical generator (2), the hydraulic machine (15) operates as a hydraulic motor driven by available hydraulic power from the hydraulic system (10) to drive the electrical machine (20) which operates as an electrical generator to provide electrical power into the electrical system (3). In a second operating mode, for example in the event of a failure of a primary hydraulic pump (9), the electrical machine (20) operates as an electric motor driven by electric power from the electrical system (3) to drive the hydraulic machine (15) operating as a hydraulic pump to provide hydraulic power into the hydraulic system (10). A hydraulic valve arrangement (18) and an electrical switch arrangement (21), as well as pressure and speed regulators are controlled by the control unit (26), and the system operation is monitored by sensors connected to the control unit (26), to activate the appropriate operating mode.
摘要翻译：双向电力转换系统将诸如飞机之类的车辆上的液压和电力系统相互连接，由此电力转换系统可以选择性地将可用的电力转换为所需的液压动力，反之亦然。电力转换系统包括连接到车辆的液压系统（10）的液压机（15），通过功率转换器和控制单元（22）连接到车辆的电气系统（3）的电机（20）机械地互连液压机器（15）和电机（20）的旋转驱动轴（14）以及控制系统操作的优先级和安全控制单元（26）。在第一操作模式中，例如在主发电机（2）发生故障的情况下，液压机器（15）作为由来自液压系统（10）的可用液压动力驱动的液压马达操作以驱动电气机器（20），其作为发电机工作以向电气系统（3）提供电力。在第二操作模式中，例如在主液压泵（9）发生故障的情况下，电机（20）作为由电气系统（3）驱动的电动机驱动液压机（15）作为液压泵操作以向所述液压系统（10）提供液压动力。液压阀装置（18）和电气开关装置（21）以及压力和速度调节器由控制单元（26）控制，并且系统操作由连接到控制单元（26）的传感器监控，激活适当的操作模式。

8. 发明授权

US06394396B2 Aerodynamic noise reducing structure for aircraft wing slats 失效
标题翻译：飞机机翼板条的气动降噪结构
公开(公告)号：US06394396B2
公开(公告)日：2002-05-28
申请号：US09837638
申请日：2001-04-17
申请人： Wolfgang Gleine , Knut Mau , Udo Carl
发明人： Wolfgang Gleine , Knut Mau , Udo Carl
IPC分类号： B64C300
CPC分类号： B64D15/04 , B64C3/46 , B64C9/24 , B64C2230/06 , B64C2230/14 , B64C2230/20 , Y02T50/14 , Y02T50/166 , Y02T50/32
摘要： A hollow expandable and contractible displacement element is secured onto the concave rear surface of a slat facing the leading edge of an aircraft wing. A bleed air line supplies engine bleed air into the hollow displacement element to selectively expand or contract the displacement element, which is preferably elastically expandable. When the slat is extended, the displacement element is expanded to fill-out the concave cavity on the rear surface of the slat so as to prevent formation of a vortex in the slat air gap and thereby to reduce aero-acoustic noise. When the slat is retracted, the displacement element is contracted to be conformingly accommodated in the sickle-shaped space between the slat and the leading edge of the wing.
摘要翻译：中空的可膨胀和可收缩的位移元件固定在面向飞行器机翼的前缘的板条的凹面后表面上。排放空气管线将引擎排放空气提供到中空位移元件中，以选择性地膨胀或收缩位移元件，该位移元件优选是可弹性膨胀的。当板条延伸时，位移元件膨胀以填充板条的后表面上的凹腔，以防止在板条气隙中形成涡流，从而降低空气声学噪声。当缝翼缩回时，位移元件收缩成适合地容纳在翼板和翼片的前缘之间的镰刀状空间中。

9. 发明授权

US4762294A Elevator control system especially for an aircraft 失效
标题翻译：电梯控制系统特别适用于飞机
公开(公告)号：US4762294A
公开(公告)日：1988-08-09
申请号：US94824
申请日：1987-09-09
申请人： Udo Carl
发明人： Udo Carl
IPC分类号： B64C13/42 , B64C13/50 , G05D1/00
CPC分类号： G05D1/0077 , B64C13/42 , B64C13/503 , Y02T50/44
摘要： An elevator control system especially for an aircraft such as an airplane,s equipped with an electrically controllable elevator flap drive system for the elevator flap on each side of the aircraft. Additionally, the system is equipped with a mechanically controlled auxiliary drive system which is responsive to a hand wheel operated by the pilot. A single hand wheel has mechanical connecting links to the elevator flaps on both sides of the aircraft. Monitoring features enable the pilot to test the auxiliary mechanical drive system without actually switching on that system. The auxiliary mechanically operated system is functional even if all other power systems failed, since a ram air turbine is provided for generating the hydraulic pressure for driving the auxiliary system.
摘要翻译：特别是用于诸如飞机的飞机的电梯控制系统配备有用于在飞行器的每一侧上的电梯翼片的电可控电梯折翼驱动系统。此外，该系统配备有机械控制的辅助驱动系统，其响应于由驾驶员操作的手轮。单手轮具有到飞机两侧的电梯襟翼的机械连接连接。监控功能使飞行员能够在没有实际打开该系统的情况下测试辅助机械驱动系统。即使所有其他电力系统故障，辅助机械操作系统也是有效的，因为提供了用于产生用于驱动辅助系统的液压的冲压空气涡轮机。

10. 发明授权

US4759515A Drive control for a vertical rudder of an aircraft 失效
标题翻译：驱动控制飞机的垂直方向舵
公开(公告)号：US4759515A
公开(公告)日：1988-07-26
申请号：US94830
申请日：1987-09-09
申请人： Udo Carl
发明人： Udo Carl
IPC分类号： B64C13/42 , B64C13/50 , G05D1/00 , B64C13/04
CPC分类号： B64C13/503 , B64C13/42 , G05D1/0077 , Y02T50/44
摘要： A vertical rudder control and drive system for an aircraft, such as an aiane, is equipped with electrically controllable vertical rudder drive systems on each side of the aircraft. Additionally, the control system is equipped with a mechanically controllable auxiliary drive system for the operation of the vertical rudder in response to foot pedals operated by the pilot when there should be a failure in the electrically controlled drive systems. A mechanical control signal transmitting link is provided between the foot pedals and the hydro-mechanical drive for the vertical rudder. Monitoring features enable the pilot to test the mechanical drive system without actually using that system in flight. Preflight tests may be performed.
摘要翻译：用于飞机（例如飞机）的垂直方向舵控制和驱动系统在飞行器的每一侧配备有电可控垂直方向舵驱动系统。此外，控制系统配备有机械可控的辅助驱动系统，用于在电控驱动系统中应该发生故障时响应于由飞行员操作的脚踏板来操作垂直方向舵。在脚踏板和用于垂直方向舵的水力机械驱动器之间提供机械控制信号传输链路。监控功能使飞行员无需在飞行中实际使用该系统即可测试机械驱动系统。可以执行预检测试。

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