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1. 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。

2. 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。

3. 发明申请

US20100019095A1 WING OF AN AIRCRAFT 有权
标题翻译：飞机的翅膀
公开(公告)号：US20100019095A1
公开(公告)日：2010-01-28
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： B64C9/24 , B64C9/34 , B64C9/02 , B64C9/18 , B64C13/00
CPC分类号： B64C9/02 , B64C7/00 , B64C2009/143
摘要： Wing of an aircraft having a mainplane (20), which has an upper face (22), a lower face (23) and an aerodynamically shaped area (21), and having an additional airfoil (10) which is articulated on the mainplane (20) and can be extended from a retracted state with a slot area (9) being opened between the mainplane (20) and the additional airfoil (10) and having a variable-position slot-varying apparatus (16) which is arranged on the lower face, forms a part of the aerodynamic profile of the additional airfoil (10) or mainplane (20) when the additional airfoil (10) is extended, and at least partially covers the slot area (9) between the mainplane (20) and the additional airfoil (10) on the lower face when the additional airfoil (10) is in the retracted state. The slot-varying apparatus (16) can be varied between a curved configuration, in which it forms a part of the aerodynamic profile of the additional airfoil (10) or mainplane (20) when the additional airfoil (10) is extended, and an extended configuration, in which it at least partially covers the slot area (9) between the mainplane (20) and the additional airfoil (10) on the lower face when the additional airfoil (10) is in the retracted state.
摘要翻译：具有主平面（20）的飞行器的翼，其具有上表面（22），下表面（23）和空气动力学形状的区域（21），并且具有铰接在主飞机上的附加翼型件（10）并且可以从缩回状态延伸，其中槽面区域（9）在主平面（20）和附加翼型件（10）之间打开，并且具有可变位置槽位变化装置（16）当附加翼型件（10）延伸时，形成附加翼型件（10）或主平面（20）的空气动力学轮廓的一部分，并且至少部分地覆盖主平面（20）与主平面（20）之间的槽区域（9）当附加翼型件（10）处于缩回状态时，下表面上的附加翼型件（10）。槽改变装置（16）可以在弯曲构型之间变化，在弯曲构型中，当附加翼型件（10）延伸时，其形成附加翼型件（10）或主平面（20）的空气动力学轮廓的一部分，并且延伸构造，其中当附加翼型件（10）处于缩回状态时，该构造件至少部分地覆盖下表面上的主平面（20）和附加翼型件（10）之间的槽区域（9）。

4. 发明申请

US20080251647A1 System For Reducing Aerodynamic Noise At A Supplementary Wing Of An Aircraft 有权
标题翻译：在飞机辅助翼上降低气动噪声的系统
公开(公告)号：US20080251647A1
公开(公告)日：2008-10-16
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： B64C21/00
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。

5. 发明授权

US08006941B2 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：US08006941B2
公开(公告)日：2011-08-30
申请号：US12829831
申请日：2010-07-02
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。

6. 发明申请

US20090001223A1 Flexible Control Surface for an Aircraft 审中-公开
标题翻译：灵活的飞机控制面
公开(公告)号：US20090001223A1
公开(公告)日：2009-01-01
申请号：US12158405
申请日：2006-12-20
申请人： Boris Grohmann , Peter Konstanzer , Thomas Lorkowski
发明人： Boris Grohmann , Peter Konstanzer , Thomas Lorkowski
IPC分类号： B64C3/48
CPC分类号： B64C3/48 , B64C3/50 , B64C9/00
摘要： A flexible control surface (1; 11, 14) comprises at least two actuators (3), which act on the control surface (1; 11, 14) at different points of action (2) which are offset laterally with respect to the circulating-flow direction (6) with respect to one another. The at least two actuators (3) are designed such that the points of action (2) can be deflected differently when the actuators (3) are operated at the same time. It is thus possible to elastically deform the control surface (1; 11, 14), in particular along the span width direction (9), without kinks, in which case it is possible to achieve uniform transitions along the control surface laterally with respect to the flow direction (6). The invention makes it possible to reduce vortices and noise induced by the control surface.
摘要翻译：柔性控制表面（1; 11,14）包括至少两个致动器（3），其在不同的作用点（2）处作用在控制表面（1; 11,14）上，所述不同的作用点（2）相对于循环 - 流方向（6）。至少两个致动器（3）被设计成使得当致动器（3）同时操作时，作用点（2）可以被不同地偏转。因此，可以使控制表面（1; 11,14）特别是沿着跨度宽度方向（9）弹性变形，而不会扭结，在这种情况下，可以相对于侧面沿着控制表面实现均匀的过渡流动方向（6）。本发明使得可以减少由控制表面引起的涡流和噪声。

7. 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。

8. 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'）。

9. 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。

10. 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。

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