公开(公告)号：US06394387B1

公开(公告)日：2002-05-28

申请号：US09742010

申请日：2000-12-22

申请人： Lazar Mitrovic

发明人： Lazar Mitrovic

IPC分类号： B64C2712

CPC分类号： F16C27/04 ,  B64C27/12 ,  B64C27/14 ,  F16C2326/43 ,  F16H1/2827

摘要： A rotor shaft support and drive arrangement comprises a bearing damper including a number of interconnected oil cylinders circumferentially distributed about a rotor to dampen the vibration thereof. A flexible diaphragm coupling is provided for transmitting a driving torque. The flexible diaphragm coupling provides improved misalignment capability.

摘要翻译： 转子轴支撑和驱动装置包括轴承阻尼器，其包括围绕转子周向分布的多个相互连接的油缸，以阻尼其振动。 提供柔性隔膜联接器用于传递驱动扭矩。 柔性隔膜联轴器提供改进的不对准能力。

公开(公告)号：US06302356B1

公开(公告)日：2001-10-16

申请号：US09378195

申请日：1999-08-20

申请人： John M. Hawkins

发明人： John M. Hawkins

IPC分类号： B64C2712

CPC分类号： B64C27/12

摘要： A twin turbine engine helicopter has a two-stage main reduction gearbox, the input stage having a speed reduction ratio exceeding 5.5:1, into an epicyclic gear train second stage ratio about 6:1 for approximately 30:1 or higher overall ratio output to the main rotor. In various embodiments, the first stage uses face gears, or bevel gears, with a reduction greater than 5.5:1 and a second stage epicyclic gear train using single or double row helical or spur gears. The first stage gears are straddle mounted in the housing.

摘要翻译： 双涡轮发动机直升机具有两级主减速齿轮箱，输入级具有超过5.5:1的减速比，其行星齿轮系第二级比例约为6:1，大约30:1或更高的总输出比 主转子。 在各种实施例中，第一级使用大于5.5:1的减速齿轮或锥齿轮，以及使用单列或双列螺旋或正齿轮的第二级行星齿轮系。 第一级齿轮跨骑安装在壳体中。

公开(公告)号：US06712313B2

公开(公告)日：2004-03-30

申请号：US10392644

申请日：2003-03-20

申请人： Elio Zoppitelli ,  Eric Cornille

发明人： Elio Zoppitelli ,  Eric Cornille

IPC分类号： B64C2712

CPC分类号： F16D3/70 ,  B64C27/32 ,  B64C27/41 ,  B64C29/0033

摘要： A constant velocity drive mechanism of a rotary-wing aircraft rotor, comprises a torque splitting differential mechanism, comprising a driving disc integral in rotation with a rotor mast and connected to each of two driven discs either side of the driving disc, by a least one connecting pin hinged to each of the discs by one of three ball joint connections. Each of the driven discs is connected to a hub of the rotor by at least one of two driving devices, each of which is also hinged to the hub, so as to drive the hub in rotation about a geometrical axis which can be inclined in all directions about the axis of rotation of the mast.

摘要翻译： 旋转翼飞行器转子的恒速驱动机构包括扭矩分离差速机构，包括与转子桅杆一体旋转的驱动盘，并连接到驱动盘的任一侧的两个从动盘中的每一个，至少一个 连接销通过三个球接头连接之一铰接到每个盘。 每个从动盘通过两个驱动装置中的至少一个连接到转子的轮毂，两个驱动装置中的每个驱动装置也铰接到轮毂上，以便围绕可以倾斜的几何轴线旋转轮毂 关于桅杆旋转轴线的方向。

公开(公告)号：US06758436B2

公开(公告)日：2004-07-06

申请号：US10277844

申请日：2002-10-23

申请人： Jeffrey Rehkemper ,  Keith Johnson

发明人： Jeffrey Rehkemper ,  Keith Johnson

IPC分类号： B64C2712

CPC分类号： A63H27/12 ,  B64C27/32 ,  B64C27/52

摘要： A propeller related vehicle in accordance with one embodiment of the present invention is described as a helicopter having an airframe housing a pneumatic motor mechanism for powering a main propeller attached to a main drive shaft. The helicopter further includes a horizontal stabilizing means attached between the main propeller and the main drive shaft, which permits the main propeller to freely pivot about the main drive shaft independently from the airframe. As such when the main propeller is rotating and the main propeller begins to pitch, the rotating main propeller has a centrifugal force created by the rotation thereof and will tend to pivot about the horizontal stabilizing means in a manner that offsets the pitch such that the helicopter remains in a substantially horizontal position.

摘要翻译： 根据本发明的一个实施例的螺旋桨相关车辆被描述为具有机身的直升机，该机身容纳用于为附接到主驱动轴的主螺旋桨供电的气动马达机构。 直升机还包括安装在主螺旋桨和主驱动轴之间的水平稳定装置，其允许主螺旋桨独立于机身围绕主驱动轴自由枢转。 因此，当主螺旋桨旋转并且主螺旋桨开始俯仰时，旋转主螺旋桨具有由其旋转产生的离心力，并且将倾向于以水平稳定装置的方式枢转，以使得俯仰偏移使得直升机 保持在基本上水平的位置。

公开(公告)号：US06659395B2

公开(公告)日：2003-12-09

申请号：US10189681

申请日：2002-07-08

申请人： Jeffrey Rehkemper ,  Keith Johnson ,  Nicholas Grisolia

发明人： Jeffrey Rehkemper ,  Keith Johnson ,  Nicholas Grisolia

IPC分类号： B64C2712

CPC分类号： B64C27/32 ,  A63H27/12 ,  B64C27/52

摘要： A propeller related vehicle in accordance with one embodiment of the present invention is described as a helicopter having an airframe housing a motor mechanism for powering a main propeller attached to a main drive shaft that extends vertically through the airframe and for powering a tail rotor. The helicopter further includes a horizontal stabilizing mechanism attached between the main propeller and the main drive shaft, which permits the main propeller to freely pivot about the main drive shaft independently from the airframe. As such when the main propeller is rotating and the main propeller begins to pitch, the rotating main propeller has a centrifugal force created by the rotation thereof and will tend to pivot about the horizontal stabilizing mechanism in a manner that offsets the pitch such that the helicopter remains in a substantially horizontal position. In addition various main propeller configurations may be employed that provide additional self-stabilization.

摘要翻译： 根据本发明的一个实施例的螺旋桨相关车辆被描述为具有机身的直升机，其具有容纳用于为主驱动轴连接的主螺旋桨供电的马达机构，所述主螺旋桨垂直延伸穿过机身并为尾部转子供电。 直升机还包括安装在主推进器和主驱动轴之间的水平稳定机构，其允许主螺旋桨独立于机身围绕主驱动轴自由枢转。 因此，当主螺旋桨旋转并且主螺旋桨开始俯仰时，旋转的主螺旋桨具有由其旋转产生的离心力，并且将趋向于以水平稳定机构的方式枢转，以偏移俯仰，使得直升机 保持在基本上水平的位置。 此外，可以采用提供额外的自稳定性的各种主要的螺旋桨结构。

公开(公告)号：US06484967B2

公开(公告)日：2002-11-26

申请号：US09860527

申请日：2001-05-21

申请人： Christoph Protte

发明人： Christoph Protte

IPC分类号： B64C2712

CPC分类号： A63H29/22 ,  A63H27/12 ,  A63H29/00

摘要： The present invention relates to a drive unit for a model helicopter comprising a fuselage in the central portion of which both the drive unit and a rotor shaft 1 are supported, characterized in that the drive unit comprises a horizontally arranged turbine 2 having a turbine shaft 3 which is extended in the inlet portion of the turbine 2 and connected to a transmission 4.