专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

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. 发明申请

US20110024574A1 Aerodynamic Body And High-Lift System Comprising Such An Aerodynamic Body 有权
标题翻译：包括这种空气动力学体的气动体和高升力系统
公开(公告)号：US20110024574A1
公开(公告)日：2011-02-03
申请号：US12936421
申请日：2009-04-07
申请人： Thomas Lorkowski
发明人： Thomas Lorkowski
IPC分类号： B64C23/02
CPC分类号： B64C21/04 , B64C21/08 , B64C2230/04 , B64C2230/06 , B64C2230/18 , B64C2230/22 , Y02T50/166
摘要： An aerodynamic body with an outside with a top and bottom in relation to the direction of airflow, with lateral end parts that form the lateral ends of the aerodynamic body when viewed across the direction of airflow, where in the interior of the aerodynamic body a duct with an airflow drive with a drive motor and a compressor means that is driven by the aforesaid and that is arranged in the duct is arranged, with at least one inlet at the bottom and/or at at least one of the lateral end parts of the aerodynamic body and with at least one outlet at the top of the aerodynamic body for influencing the airflow at the aerodynamic body is arranged, where in the duct a sleeve is arranged which is rotatable by means of a drive motor, which sleeve includes at least one recess which at a particular rotational position of the sleeve can be made to at least in part coincide with the outlet at the top of the aerodynamic body so that the air that has been compressed by the compressor flows through the recess in the sleeve and through the outlet, as well as a high-lift system comprising such an aerodynamic body.
摘要翻译：空气动力体，其具有相对于气流方向具有顶部和底部的外部，侧向端部在气流方向观察时形成空气动力体的侧端，其中在空气动力体的内部具有管道具有驱动马达的气流驱动器和由上述驱动并设置在管道中的压缩机装置布置成在底部和/或至少一个侧向端部处的至少一个入口空气动力体并且在空气动力体的顶部具有影响空气动力体的气流的至少一个出口被布置，其中在管道中布置有可通过驱动马达旋转的套筒，该套筒包括至少一个在套筒的特定旋转位置处的凹部可以被制成至少部分地与空气动力体的顶部处的出口重合，使得被压缩机压缩的空气流过套筒中的凹槽并通过出口，以及包括这种空气动力体的高升力系统。

3. 发明授权

US06481964B2 Rotor blade having a control flap 失效
公开(公告)号：US06481964B2
公开(公告)日：2002-11-19
申请号：US09908736
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 , B64C27/473 , B64C2027/7266 , Y02T50/34
摘要： A rotor blade for a helicopter has a blade root for a fastening in the area of the rotor mast and a radially exterior blade tip. An aerodynamic control flap is integrated essentially in the contour of the blade profile is swivellably disposed in the rotor blade between the blade root and the blade tip. The control flap is disposed at its two ends in each case by way of roller bearings on bearing bolts aligned in the span direction of the rotor blade. The bearing of the control flap which is radially on the outside has devices which provide a support with respect to the centrifugal forces of the control flap upon the rotor blade resulting from the rotation of the rotor blade.

4. 发明申请

US20100282900A1 System for Reducing Aerodynamic Noise at a Supplementary Wing of an Aircraft 有权
标题翻译：降低飞机辅助翼空气动力噪声的系统
公开(公告)号：US20100282900A1
公开(公告)日：2010-11-11
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： B64C1/40
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

US08408498B2 Aerodynamic body and high-lift system comprising such an aerodynamic body 有权
标题翻译：包括这种空气动力体的空气动力体和高升力系统
公开(公告)号：US08408498B2
公开(公告)日：2013-04-02
申请号：US12936421
申请日：2009-04-07
申请人： Thomas Lorkowski
发明人： Thomas Lorkowski
IPC分类号： B64C15/14
CPC分类号： B64C21/04 , B64C21/08 , B64C2230/04 , B64C2230/06 , B64C2230/18 , B64C2230/22 , Y02T50/166
摘要： An aerodynamic body with an outside with a top and bottom in relation to the direction of airflow, with lateral end parts that form the lateral ends of the aerodynamic body when viewed across the direction of airflow, where in the interior of the aerodynamic body a duct with an airflow drive with a drive motor and a compressor means that is driven by the aforesaid and that is arranged in the duct is arranged, with at least one inlet at the bottom and/or at at least one of the lateral end parts of the aerodynamic body and with at least one outlet at the top of the aerodynamic body for influencing the airflow at the aerodynamic body is arranged, where in the duct a sleeve is arranged which is rotatable by means of a drive motor, which sleeve includes at least one recess which at a particular rotational position of the sleeve can be made to at least in part coincide with the outlet at the top of the aerodynamic body so that the air that has been compressed by the compressor flows through the recess in the sleeve and through the outlet, as well as a high-lift system comprising such an aerodynamic body.
摘要翻译：空气动力体，其具有相对于气流方向具有顶部和底部的外部，侧向端部在气流方向观察时形成空气动力体的侧端，其中在空气动力体的内部具有管道具有驱动马达的气流驱动器和由上述驱动并设置在管道中的压缩机装置布置成在底部和/或至少一个侧向端部处的至少一个入口空气动力体并且在空气动力体的顶部具有影响空气动力体的气流的至少一个出口被布置，其中在管道中布置有可通过驱动马达旋转的套筒，该套筒包括至少一个在套筒的特定旋转位置处的凹部可以被制成至少部分地与空气动力体的顶部处的出口重合，使得被压缩机压缩的空气流过套筒中的凹槽并通过出口，以及包括这种空气动力体的高升力系统。

6. 发明申请

US20100294893A1 AERODYNAMIC COMPONENT WITH A DEFORMABLE OUTER SHELL 审中-公开
标题翻译：具有可变外壳的空气动力部件
公开(公告)号：US20100294893A1
公开(公告)日：2010-11-25
申请号：US12785785
申请日：2010-05-24
申请人： Olaf HEINTZE , Hans Peter MONNER , Markus KINTSCHER , Johannes RIEMENSCHNEIDER , Thomas LORKOWSKI
发明人： Olaf HEINTZE , Hans Peter MONNER , Markus KINTSCHER , Johannes RIEMENSCHNEIDER , Thomas LORKOWSKI
IPC分类号： B64C3/44
CPC分类号： B64C3/48
摘要： The invention relates to an aerodynamic component, in particular a wing, a landing flap, a pitch elevator, a yaw rudder, a fin or tail. The aerodynamic component comprises an outer shell and at least one supporting element supporting said outer shell. A drive unit rotates the supporting element. A supporting region is created between the supporting element and the outer shell. The supporting region transfers deformation forces from the drive unit via the supporting element to the outer shell. The supporting element is designed and configured for changing the distance of the supporting region from a longitudinal plane of the aerodynamic component with a rotation of the supporting element. The outer shell comprises an elastic deformation region. The elastic deformation region is elastically deformed by the deformation forces with a rotation of the supporting element.
摘要翻译：本发明涉及一种空气动力学部件，特别是机翼，着陆挡板，俯仰电梯，偏航舵，鳍或尾翼。空气动力学部件包括外壳和支撑所述外壳的至少一个支撑元件。驱动单元旋转支撑元件。在支撑元件和外壳之间产生支撑区域。支撑区域通过支撑元件将驱动单元的变形力传递到外壳。支撑元件被设计和构造成随着支撑元件的旋转而改变支撑区域与空气动力学部件的纵向平面的距离。外壳包括弹性变形区域。弹性变形区域随着支撑元件旋转的变形力弹性变形。

7. 发明授权

US07028602B2 Linear, hydraulic pivot drive 失效
标题翻译：线性，液压枢轴驱动
公开(公告)号：US07028602B2
公开(公告)日：2006-04-18
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： F15B15/08 , B64C13/36
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。

8. 发明申请

US20130026300A1 HIGH LIFT SYSTEM FOR AN AIRCRAFT 有权
标题翻译：用于飞机的高起升系统
公开(公告)号：US20130026300A1
公开(公告)日：2013-01-31
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： B64C21/08 , B64C9/18
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。

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

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）。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式