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11. 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。

12. 发明申请

US20050178927A1 Linear, hydraulic pivot drive 失效
标题翻译：线性，液压枢轴驱动
公开(公告)号：US20050178927A1
公开(公告)日：2005-08-18
申请号：US10505678
申请日：2003-02-21
申请人： Ulf Breuer , Peter Jaenker , Thomas Lorkowski
发明人： Ulf Breuer , Peter Jaenker , Thomas Lorkowski
IPC分类号： B64C13/40 , F15B15/06 , F15B15/08
CPC分类号： F15B15/068 , B64C13/40 , Y10T74/18056
摘要： The invention relates to a linear, hydraulic pivot drive, especially for the flap control system of aerodynamic structures. Said pivot drive comprises a housing provided with ports for introducing a hydraulic medium, a piston which is arranged inside the housing and can be axially displaced by the effect of the hydraulic medium, and an output shaft which is provided with coarse threads and interacts with the piston in order to cover the axial displacement of the piston into a rotational movement. The invention is characterized in that the output shaft is integrated into the piston, the coarse threads running in the same direction and engaging in the piston, and the cross-section of the piston has a spline profile for effectively preventing a rotational movement of the piston.
摘要翻译：本发明涉及一种线性液压枢转驱动装置，特别适用于空气动力结构的挡板控制系统。所述枢转驱动器包括设置有用于引入液压介质的端口的壳体，布置在壳体内部并且可以通过液压介质的作用而轴向移位的活塞，以及设置有粗螺纹并与其相互作用的输出轴活塞，以便将活塞的轴向位移覆盖成旋转运动。本发明的特征在于，输出轴被集成到活塞中，粗螺纹沿相同方向延伸并接合活塞，并且活塞的横截面具有花键轮廓，用于有效地防止活塞的旋转运动。

13. 发明授权

US06663345B2 Rotor blade with control flaps 失效
标题翻译：转子叶片带控制翼片
公开(公告)号：US06663345B2
公开(公告)日：2003-12-16
申请号：US09908978
申请日：2001-07-20
申请人： Thomas Lorkowski , Frank Hermle
发明人： Thomas Lorkowski , Frank Hermle
IPC分类号： B64C27615
CPC分类号： B64C27/615 , B64C2027/7266 , Y02T50/34
摘要： Rotor blade for a helicopter having an aerodynamic control flap, particularly a camber flap, is integrated essentially in the contour of the blade profile. The camber flap is swivellably arranged on an axis of rotation and is linked to a control rod of a control device outside the axis of rotation, for converting a linear movement into a swivelling movement of the control flap. The control device is disposed by way of roller bearings and bolts aligned in the span direction. Devices are provided which absorb by way of the control flap centrifugal forces of the control device resulting from the rotation of the rotor blade.
摘要翻译：用于具有空气动力学控制翼片，特别是外倾翼的直升机的转子叶片基本上集成在叶片轮廓的轮廓中。外倾板可旋转地布置在旋转轴线上，并且连接到控制装置的控制杆外部的旋转轴线，用于将直线运动转换成控制挡板的旋转运动。控制装置通过在跨度方向对齐的滚柱轴承和螺栓来设置。提供了通过由转子叶片旋转导致的控制装置离心力吸收的装置。

14. 发明授权

US06371415B1 Aerodynamic component with a leading edge flap 失效
标题翻译：具有前缘皮瓣的气动元件
公开(公告)号：US06371415B1
公开(公告)日：2002-04-16
申请号：US09658905
申请日：2000-09-11
申请人： Thomas Lorkowski , Frank Hermle , Peter Jaenker
发明人： Thomas Lorkowski , Frank Hermle , Peter Jaenker
IPC分类号： B64C1324
CPC分类号： B64C27/001 , B64C27/615 , B64C2027/7283 , Y02T50/34
摘要： An aerodynamic component such as a helicopter rotor blade has an aerodynamic flow profile, a free end and a mounting end forming a blade root for attachment to a rotor mast. A blade section between the root and the free end has a leading edge and a trailing edge as viewed in the flow or chord direction. The blade is enclosed on its suction side and its pressure side with a respective skin. A nose flap or leading edge flap is secured to the leading edge by a bearing or hinge. The blade tilting angle is adjustable by piezo-drive elements arranged in at least one pair forming an actuator for each nose flap. The piezo-elements of a pair are arranged in the chord direction one behind the other and the pair is secured to the body of the blade by a fixed point positioned between the elements of a pair. The expansion and contraction from the piezo-element closer to the trailing edge is transmitted to the flap by a push rod. The expansion and contraction of the piezo-element closer to the leading edge is transmitted to the flap by a pronged pull-fork. The push rod and the pull-fork drive a free end of a lever secured to the flap, whereby a displacement of the push rod or of the pull fork causes the tilting adjustment of the flap by a push-pull action.
摘要翻译：诸如直升机转子叶片的空气动力学部件具有空气动力学流动分布，自由端和形成用于附接到转子桅杆的叶片根部的安装端。根部和自由端之间的叶片部分具有从流动或弦向方向观察的前缘和后缘。叶片在其吸力侧和其压力侧被封闭，并具有相应的皮肤。鼻翼或前缘皮瓣通过轴承或铰链固定到前缘。刀片倾斜角度可以通过布置在至少一对中的压电驱动元件来调节，形成每个鼻翼的致动器。一对的压电元件沿着弦方向一个在另一个之上布置，并且该对被固定在一对位置的元件之间的固定点。来自压电元件的靠近后缘的膨胀和收缩通过推杆传递到翼片。靠近前缘的压电元件的膨胀和收缩通过叉形叉子传递到翼片。推杆和拉叉驱动固定到翼片的杠杆的自由端，由此推杆或拉叉的位移通过推拉动作导致翼片的倾斜调节。

15. 发明授权

US09045224B2 High lift system for an aircraft 有权
标题翻译：飞机高升程系统
公开(公告)号：US09045224B2
公开(公告)日：2015-06-02
申请号：US13530151
申请日：2012-06-22
申请人： Burkhard Gölling , Thomas Lorkowski
发明人： Burkhard Gölling , Thomas Lorkowski
IPC分类号： B64C3/00 , B64C21/04 , B64C9/16 , B64C9/38
CPC分类号： B64C21/04 , B64C9/16 , B64C9/38 , Y02T50/166 , Y02T50/44
摘要： A high lift system with a main wing and regulating flaps, also bearing devices for the mounting of the regulating flaps, and positioning devices for the positioning of the regulating flaps, wherein the respective bearing device and/or positioning device is at least partially provided with a fairing, having a flow control device for purposes of controlling the flow around the high lift system with at least one inlet duct with at least one inlet, which device is located on or underneath the lower face of the high lift system, wherein at least one outlet duct for air is furthermore provided, which is connected with the inlet duct in a fluid-communicating manner, and has at least one outlet, which is located on the upper face in the region of at least one regulating flap of the high lift system.
摘要翻译：具有主翼和调节翼片的高升力系统，用于安装调节翼片的轴承装置和用于定位调节翼片的定位装置，其中相应的轴承装置和/或定位装置至少部分地设置有整流罩，具有流量控制装置，用于通过具有至少一个入口的至少一个入口管道控制高升程系统周围的流动，该装置位于高升力系统的下表面上或下方，其中至少还提供了一个用于空气的出口管道，其以流体连通的方式与入口管道连接，并且具有至少一个出口，其位于高升力的至少一个调节翼片的区域中的上表面上系统。

16. 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。

17. 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。

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