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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。

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