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1. 发明授权

US08888036B2 Primary flight controls 有权
标题翻译：主要飞行控制
公开(公告)号：US08888036B2
公开(公告)日：2014-11-18
申请号：US13534193
申请日：2012-06-27
申请人： Bruno Chaduc , Boris Grohmann , Christophe Tempier
发明人： Bruno Chaduc , Boris Grohmann , Christophe Tempier
IPC分类号： B64C11/00 , B64C27/68 , B64C27/64 , B64C27/625 , B64C13/50
CPC分类号： B64C27/625 , B64C13/503 , B64C27/64 , B64C27/68 , Y02T50/44
摘要： Primary flight controls (10) for main and/or tail rotors (4) of helicopters with electro-mechanical interface between any of fly-by-wire and/or fly-by-light controls and hydraulic servo actuators (8) for control force amplification towards said main and/or tail rotor controls (4). For each of the main and/or tail rotor controls (4) there is provided but one of the hydraulic servo actuators (8), connected by one mechanical linkage (7) to one electro motor (5), said one hydraulic servo actuator (8) being of the type having the one mechanical linkage (7) connected to its input (29) and its output (30) and the one electro motor (5) being of the direct drive type, the position of said electro motor (5) having a reference to said one mechanical linkage (7) and the torque delivered by said electro motor (5) to the hydraulic servo actuator (8) being related to the power consumption of said electro motor (5).
摘要翻译：用于直升机的主和/或尾转子（4）的主飞行控制（10），其具有在线控和/或飞越控制之间的电 - 机械接口和用于控制力的液压伺服致动器（8）朝向所述主和/或尾部转子控制器（4）的放大。对于每个主转子控制器和/或尾部转子控制器（4），只有一个液压伺服致动器（8）通过一个机械联动装置（7）连接到一个电动马达（5），所述一个液压伺服致动器 8）是具有连接到其输入端（29）和其输出端（30）的一个机械连杆（7）和一个电动机（5）是直接驱动型的类型，所述电动马达（5）的位置）和所述电动马达（5）传递到所述液压伺服驱动器（8）的扭矩与所述电动马达（5）的功率消耗有关。

2. 发明授权

US08628046B2 Control system 有权
标题翻译：控制系统
公开(公告)号：US08628046B2
公开(公告)日：2014-01-14
申请号：US13116117
申请日：2011-05-26
申请人： Boris Grohmann , Gregor Paulmann
发明人： Boris Grohmann , Gregor Paulmann
IPC分类号： B64C13/04
CPC分类号： B64C13/42 , B64C27/56
摘要： The invention relates to a control system and to a method of operating such a control system, particularly to a control system for pilot command inputs for a helicopter, with a mechanical input signal (2), at least one electric position sensor (21, 21′) for said input signal (2), at least one electric power supply (25, 25′) and at least one controllable, electromechanical actuator (27, 27′) fed by the at least one electric power supply (25, 25′) and controlled by the at least one electric position sensor (21, 21′). The mechanical input signal (2) is applied mechanically to the at least one controllable electromechanical actuator (27, 27′).
摘要翻译：本发明涉及一种控制系统和一种操作这种控制系统的方法，特别涉及一种用于具有机械输入信号（2）的至少一个电气位置传感器（21,21）的用于直升机的导向命令输入的控制系统 '），至少一个电源（25,25'）和由至少一个电源（25,25'）馈送的至少一个可控制的机电致动器（27,27'），用于所述输入信号（2））并由所述至少一个电位置传感器（21,21'）控制。机械输入信号（2）机械地施加到至少一个可控机电致动器（27,27'）。

3. 发明申请

US20060231593A1 Friction welding device 失效
标题翻译：摩擦焊接装置
公开(公告)号：US20060231593A1
公开(公告)日：2006-10-19
申请号：US10538519
申请日：2003-11-26
申请人： Erwin Bayer , Boris Grohmann , Josef-Ritz Weg , Peter Jaenker
发明人： Erwin Bayer , Boris Grohmann , Josef-Ritz Weg , Peter Jaenker
IPC分类号： B23K20/12
CPC分类号： B23K20/1205 , B23K20/129 , B23K2101/001
摘要： A friction-welding device for the integral joining of components, having an oscillator, which generates a periodic movement of a component and a welding surface provided thereon relative to another, static component and a welding surface provided thereon, with directions of movement parallel to the welding surfaces, having a compression device which presses the welding surfaces together, and a cartridge which accommodates the moved component. The oscillator includes two or a greater, even number of piezoactuators, which are arranged in pairs on a line of application and are able to be prestressed with respect to the cartridge from opposite sides under pressure generation and are able to be moved in a synchronous, oscillating manner together therewith and the component.
摘要翻译：一种用于整体接合具有振荡器的部件的摩擦焊接装置，其产生相对于另一个静电部件和设置在其上的焊接表面的部件和其上设置的焊接表面的周期性运动，其中移动方向平行于焊接表面，具有将焊接表面压在一起的压缩装置和容纳移动部件的盒。振荡器包括两个或更多个偶数个压电致动器，它们在一条应用线上成对布置，并且能够在压力产生下从相对侧相对于盒预加应力，并且能够以同步，与其一起振荡的方式和组件。

4. 发明申请

US20130168501A1 PRIMARY FLIGHT CONTROLS 有权
标题翻译：主要飞行控制
公开(公告)号：US20130168501A1
公开(公告)日：2013-07-04
申请号：US13534193
申请日：2012-06-27
申请人： Bruno Chaduc , Boris Grohmann , Christophe Tempier
发明人： Bruno Chaduc , Boris Grohmann , Christophe Tempier
IPC分类号： B64C27/625
CPC分类号： B64C27/625 , B64C13/503 , B64C27/64 , B64C27/68 , Y02T50/44
摘要： Primary flight controls (10) for main and/or tail rotors (4) of helicopters with electro-mechanical interface between any of fly-by-wire and/or fly-by-light controls and hydraulic servo actuators (8) for control force amplification towards said main and/or tail rotor controls (4). For each of the main and/or tail rotor controls (4) there is provided but one of the hydraulic servo actuators (8), connected by one mechanical linkage (7) to one electro motor (5), said one hydraulic servo actuator (8) being of the type having the one mechanical linkage (7) connected to its input (29) and its output (30) and the one electro motor (5) being of the direct drive type, the position of said electro motor (5) having a reference to said one mechanical linkage (7) and the torque delivered by said electro motor (5) to the hydraulic servo actuator (8) being related to the power consumption of said electro motor (5).
摘要翻译：用于直升机的主和/或尾转子（4）的主飞行控制（10），其具有在线控和/或飞越控制之间的电 - 机械接口和用于控制力的液压伺服致动器（8）朝向所述主和/或尾部转子控制器（4）的放大。对于每个主转子控制器和/或尾部转子控制器（4），只有一个液压伺服致动器（8）通过一个机械联动装置（7）连接到一个电动马达（5），所述一个液压伺服致动器 8）是具有连接到其输入端（29）和其输出端（30）的一个机械连杆（7）和一个电动机（5）是直接驱动型的类型，所述电动马达（5）的位置）和所述电动马达（5）传递到所述液压伺服驱动器（8）的扭矩与所述电动马达（5）的功率消耗有关。

5. 发明授权

US08191835B2 Wing of an aircraft 有权
标题翻译：机翼
公开(公告)号：US08191835B2
公开(公告)日：2012-06-05
申请号：US12448142
申请日：2007-12-11
申请人： Boris Grohmann , Johann Reichenberger , Thomas Lorkowski
发明人： Boris Grohmann , Johann Reichenberger , Thomas Lorkowski
IPC分类号： B64C3/50
CPC分类号： B64C9/02 , B64C7/00 , B64C2009/143
摘要： A wing of an aircraft has a mainplane, which has an upper face, a lower face and an aerodynamically shaped area. The wing has an additional airfoil which is articulated on the mainplane and can be extended from a retracted state with a slot area being opened between the mainplane and the additional airfoil. The wing also has a variable-position slot-varying apparatus which is arranged on the lower face, forms a part of the aerodynamic profile of the additional airfoil or mainplane when the additional airfoil is extended, and at least partially covers the slot area between the mainplane and the additional airfoil on the lower face when the additional airfoil is in the retracted state. The slot-varying apparatus can be varied between a curved configuration, in which it forms a part of an aerodynamic profile, and an extended configuration, in which it at least partially covers the slot area.
摘要翻译：飞机机翼有一个主面板，上面，下面和空气动力学形状的区域。机翼具有附加的翼型件，其在主平面上铰接，并且可以从缩回状态延伸，其中槽面区域在主平面和附加翼型之间打开。机翼还具有可变位置槽变装置，其布置在下表面上，当附加翼型件延伸时，形成附加翼型件或主平面的空气动力学轮廓的一部分，并且至少部分地覆盖主翼面和另外的翼面在下表面上，当附加翼型处于缩回状态时。槽改变装置可以在其形成空气动力学轮廓的一部分的弯曲构型和延伸构型之间变化，其中它至少部分地覆盖槽区域。

6. 发明授权

US08162607B2 Rotor blade for a rotary wing aircraft 有权
标题翻译：用于旋翼飞机的转子叶片
公开(公告)号：US08162607B2
公开(公告)日：2012-04-24
申请号：US12158928
申请日：2006-12-08
申请人： Boris Grohmann , Christoph Maucher , Andree Altmikus , Stephan Mangelsdorf
发明人： Boris Grohmann , Christoph Maucher , Andree Altmikus , Stephan Mangelsdorf
IPC分类号： B64C27/615
CPC分类号： B64C27/615 , B64C2027/7283 , B64C2027/7288 , Y02T50/34
摘要： A rotor blade including a rotor blade profile including a profile tip region, a profile trailing edge region including a trailing edge and a profile body having a profile core. A covering skin including an upper skin and a lower skin encase the profile core. A reversibly bendable flexural actuator including a first actuator end disposed at the trailing edge region of the rotor blade profile and a second actuator end projecting past the profile body toward the trailing edge. The second actuator end forms part of the trailing edge region and forms a movable rotor blade flap, the movable rotor blade flap being deformable into an arc-shaped rotor blade flap deflection upon a bending of the flexural actuator.
摘要翻译：一种转子叶片，其包括转子叶片轮廓，该转子叶片轮廓包括轮廓顶端区域，轮廓后缘区域，包括后缘和具有轮廓芯的轮廓体。包括上皮和下皮的覆盖皮包围型芯。一种可逆地弯曲的弯曲致动器，包括设置在转子叶片轮廓的后缘区域的第一致动器端部和向轮廓体朝向后缘突出的第二致动器端部。第二致动器端部构成后缘区域的一部分并且形成可动转子叶片挡板，可动转子叶片挡板可变形成在弯曲致动器的弯曲时偏转的弧形转子叶片。

7. 发明申请

US20120032031A1 CONTROL SYSTEM 有权
标题翻译：控制系统
公开(公告)号：US20120032031A1
公开(公告)日：2012-02-09
申请号：US13116117
申请日：2011-05-26
申请人： Boris Grohmann , Gregor Paulmann
发明人： Boris Grohmann , Gregor Paulmann
IPC分类号： B64C13/04
CPC分类号： B64C13/42 , B64C27/56
摘要： The invention relates to a control system and to a method of operating such a control system, particularly to a control system for pilot command inputs for a helicopter, with a mechanical input signal (2), at least one electric position sensor (21, 21′) for said input signal (2), at least one electric power supply (25, 25′) and at least one controllable, electromechanical actuator (27, 27′) fed by the at least one electric power supply (25, 25′) and controlled by the at least one electric position sensor (21, 21′). The mechanical input signal (2) is applied mechanically to the at least one controllable electromechanical actuator (27, 27′).
摘要翻译：本发明涉及一种控制系统和一种操作这种控制系统的方法，特别涉及一种用于具有机械输入信号（2）的至少一个电气位置传感器（21,21）的用于直升机的导向命令输入的控制系统 '），至少一个电源（25,25'）和由至少一个电源（25,25'）馈送的至少一个可控制的机电致动器（27,27'），用于所述输入信号（2））并且由所述至少一个电位置传感器（21,21'）控制。机械输入信号（2）机械地施加到至少一个可控机电致动器（27,27'）。

8. 发明授权

US07880366B2 Three-dimensional stack-type piezo element and piezoelectric actuator having such a stack-type piezo element 有权
标题翻译：具有这种堆叠型压电元件的三维堆叠型压电元件和压电致动器
公开(公告)号：US07880366B2
公开(公告)日：2011-02-01
申请号：US12158617
申请日：2006-12-08
申请人： Boris Grohmann , Peter Konstanzer , Stefan Storm
发明人： Boris Grohmann , Peter Konstanzer , Stefan Storm
IPC分类号： H01L41/08
CPC分类号： B64C3/48 , H01L41/0831 , H01L41/0833 , H01L41/094 , H01L41/098 , Y10T29/42
摘要： A three-dimensional stack-type piezo element has at least one surface that is shaped perpendicular to layer planes of the stack, so that, at least in sections, it is not parallel to a stacking direction of the piezo element.
摘要翻译：三维堆叠型压电元件具有至少一个垂直于堆叠层的平面形状的表面，使得至少在部分中它不平行于压电元件的层叠方向。

9. 发明授权

US07766281B2 System for reducing aerodynamic noise at a supplementary wing of an aircraft 有权
标题翻译：用于降低飞机辅助翼面空气动力学噪音的系统
公开(公告)号：US07766281B2
公开(公告)日：2010-08-03
申请号：US11791367
申请日：2005-11-09
申请人： Thomas Lorkowski , Boris Grohmann
发明人： Thomas Lorkowski , Boris Grohmann
IPC分类号： B64C3/50
CPC分类号： B64C3/50 , B64C9/14 , B64C2009/143
摘要： A system for reducing aerodynamic noise of a supplementary wing of an aircraft is provided. The supplementary wing is hinged to a main wing and is extendable when a gap region between the main wing and the supplementary wing is opened. The system includes a separating surface which can be moved into the gap region when the supplementary wing is extended and which extends at least partially along a separation flow line between a vortex flow region and a gap flow for the air flowing in the gap region. The separating surface is an n-stable surface which through an actuator device can be moved between at least one of the stable states and at least one additional state.
摘要翻译：提供了一种降低飞机辅助翼的气动噪声的系统。辅助机翼铰接到主翼，当主翼和辅助翼之间的间隙打开时，可以延伸。该系统包括分离表面，当分离表面延伸时，该分离表面可以移动到间隙区域中，并且至少部分地沿涡流流动区域和在间隙区域中流动的空气的间隙流之间的分离流线延伸。分离表面是通过致动器装置可以在至少一个稳定状态和至少一个附加状态之间移动的n稳定表面。

10. 发明申请

US20100181415A1 ROTOR BLADE FOR A ROTARY WING AIRCRAFT 审中-公开
标题翻译：旋转叶片用于旋转式飞机
公开(公告)号：US20100181415A1
公开(公告)日：2010-07-22
申请号：US12666421
申请日：2008-06-05
申请人： Andree Altmikus , Markus Bauer , Boris Grohmann , Stephan Mangelsdorf , Christoph Maucher , Rupert Pfaller , Elif Ahci
发明人： Andree Altmikus , Markus Bauer , Boris Grohmann , Stephan Mangelsdorf , Christoph Maucher , Rupert Pfaller , Elif Ahci
IPC分类号： B64C27/00 , B64C11/04
CPC分类号： B64C27/473 , B64C27/615 , B64C2027/7283 , Y02T50/34
摘要： The invention relates to a rotor blade (20), especially for a rotary wing aircraft. The invention is characterized in that an aerodynamically effective rotor blade profile with a profile nose region (21), a profile base body (20a) with a profile core, an upper and lower cover skin (30) that envelops the profile core (22), and a profile rear edge region (23) with a rear edge (40) and a reversibly bendable supporting member (26) that can be attached with the first end to the end region of the profile base body (20a) pointing toward the rear edge (40) and projects with the second end freely out of the profile base body (20a) and its end region toward the rear edge (40) and forms a movable rotor blade flap (24), and several actuators (35) that are dynamically connected to the projecting second end of the reversibly bendable supporting member (26) and an arc-shaped flap deflection can be initiated via the change in length of the actuators, the second end of the reversibly bendable supporting member (26) that forms the rotor blade flap (24) viewed in the direction of the span (S) being divided by notches (34) into several segments to which at least one actuator (35) at a time is assigned.
摘要翻译：本发明涉及一种转子叶片（20），特别是用于旋翼飞机。本发明的特征在于，具有轮廓鼻部区域（21），具有轮廓芯的轮廓基体（20a），包围轮廓芯（22）的上部和下部覆盖皮肤（30））的空气动力学有效的转子叶片轮廓，，以及具有后边缘（40）和可逆弯曲的支撑构件（26）的型材后边缘区域（23），其可以将第一端附接到指向后侧的型材基体（20a）的端部区域边缘（40）并且其第二端自由地突出到轮廓基体（20a）之外并且其端部区域朝向后边缘（40）突出并且形成可动转子叶片挡板（24），并且几个致动器（35）动态地连接到可逆弯曲的支撑构件（26）的突出的第二端，并且可以经由致动器的长度的改变来启动弧形的翼片偏转，形成可逆弯曲支撑构件的可逆弯曲的支撑构件（26）的第二端转子叶片翼片（24）沿sp方向观察一个（S）被切口（34）划分成多个段，至少一个致动器（35）一次分配给该段。

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