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1. 发明授权

US06460802B1 Helicopter propulsion and control system 失效
标题翻译：直升机推进和控制系统
公开(公告)号：US06460802B1
公开(公告)日：2002-10-08
申请号：US09660784
申请日：2000-09-13
申请人： Elwood G. Norris
发明人： Elwood G. Norris
IPC分类号： B64C2752
CPC分类号： B64C27/14 , B64C27/10 , B64C27/52
摘要： A helicopter propulsion and control system configured for actuating a helicopter airframe according to control inputs of an operator, comprising a counter-rotating rotor set tiltably coupled to the airframe at a first location, the rotor set having a downward thrust vector and a power assembly configured to actuate the counter-rotating rotor set, having a center of gravity, and being fixedly coupled to the rotor set so as to be tiltable therewith, the center of gravity of said power assembly being disposed below the first location where the rotor set is tiltably coupled to the airframe and a control actuator operatively coupled between the power assembly and the airframe to enable the center of gravity of the airframe to move with respect to the center of gravity of the power assembly, and with respect to the thrust vector of the rotor set, whereby pitch and roll of the airframe are controllable by the operator.
摘要翻译：一种直升机推进和控制系统，其配置成根据操作者的控制输入来致动直升机机身，所述直升机机身包括在第一位置处可倾斜地联接到所述机身的反向旋转转子组，所述转子组具有向下的推力矢量和配置的功率组件驱动具有重心的反向旋转转子组，并且固定地联接到转子组以便与其倾斜，所述动力组件的重心设置在转子组可倾斜的第一位置的下方联接到机身和可操作地联接在动力组件和机身之间的控制致动器，以使得机身的重心相对于动力组件的重心移动，并且相对于转子的推力矢量由此，机身的俯仰和滚转由操作者控制。

2. 发明授权

US06293492B1 Coaxial twin-rotor type helicopter 有权
标题翻译：同轴双转子式直升机
公开(公告)号：US06293492B1
公开(公告)日：2001-09-25
申请号：US09387493
申请日：1999-09-01
申请人： Gennai Yanagisawa
发明人： Gennai Yanagisawa
IPC分类号： B64C2752
CPC分类号： B64C27/10 , B64C27/52
摘要： A one-man helicopter 1 in which a drive transmission 10 that transmits driving force to upper and lower rotors 5 and 6 comprises first and second planet gear mechanisms 100 and 200 provided with a common carrier 104. When the common carrier 104 is rotated by a motor 301, a differential motion is generated between the two planet gear mechanisms. This results in the rotors being rotated at different velocities, which can be used to control yaw. A fore-and-aft swing mechanism 400 and right-and-left swing mechanism 500 depend from the lower end of a vertical shaft 41 on which the rotors are supported. Moving a stick 8 forward or backward, or to either side, tilts the vertical shaft 41 in the same direction. When the stick 8 is not subjected to a controlling force, the vertical shaft 41 reverts automatically to its original vertical state. This configuration makes it possible to realize a coaxial twin-rotor type helicopter having a compact, structurally simple control mechanism.
摘要翻译：一个单人直升机1，其中将驱动力传递到上下转子5和6的驱动变速器10包括设置有公共载架104的第一和第二行星齿轮机构100和200.当公共载架104旋转一个电动机301在两个行星齿轮机构之间产生差速运动。这导致转子以不同的速度旋转，这可以用于控制偏航。前后摆动机构400和左右摆动机构500从其上支撑有转子的竖直轴41的下端部分。向前或向后或向任一侧移动杆8使垂直轴41沿相同方向倾斜。当棒8不受控制力时，垂直轴41自动地回复到其原始垂直状态。这种构造使得可以实现具有紧凑的，结构简单的控制机构的同轴双转子型直升机。

3. 发明授权

US06830214B2 Rotary-wing aircraft 失效
标题翻译：旋翼飞机
公开(公告)号：US06830214B2
公开(公告)日：2004-12-14
申请号：US10194672
申请日：2002-07-12
申请人： Franklin D. Carson
发明人： Franklin D. Carson
IPC分类号： B64C2752
CPC分类号： B64C27/82 , B64C27/605 , B64C2027/8281
摘要： A preferred embodiment of a rotary-wing aircraft includes a fuselage, a tail boom fixedly coupled the fuselage, a pylon fixedly coupled to the tail boom, and a main rotor assembly rotatably coupled to the fuselage and comprising a hub and a plurality of rotor blades pivotally coupled to the hub. The preferred embodiment also includes a cyclic control adapted to vary an orientation of the rotor blades in relation to the hub on a cyclical basis, and a horizontal stabilizer mounted on one of the pylon and the tail boom. At least a portion of the horizontal stabilizer is movable in relation to the one of the pylon and the tail boom and a position of the at least a portion of the horizontal stabilizer is controllable independent of the cyclic control.
摘要翻译：旋转翼飞行器的优选实施例包括机身，固定地连接机身的尾臂，固定地连接到尾吊杆的挂架和可旋转地联接到机身的主转子组件，并且包括毂和多个转子叶片枢转地联接到轮毂。优选实施例还包括循环控制，其适于在循环的基础上改变转子叶片相对于轮毂的取向，以及安装在塔架和尾吊杆中的一个上的水平稳定器。水平稳定器的至少一部分可相对于塔架和尾梁中的一个移动，并且水平稳定器的至少一部分的位置可以独立于循环控制来控制。

4. 发明授权

US06641365B2 Optimum speed tilt rotor 有权
公开(公告)号：US06641365B2
公开(公告)日：2003-11-04
申请号：US10029597
申请日：2001-10-24
申请人： Abraham E. Karem
发明人： Abraham E. Karem
IPC分类号： B64C2752
CPC分类号： B64C27/473 , B64C27/33 , B64C27/467 , B64C29/0033
摘要： A variable speed helicopter tilt rotor system and method for operating such a system are provided which allow the helicopter rotor to be operated at an optimal angular velocity in revolutions per minute (RPM) minimizing the power required to turn the rotor thereby resulting in helicopter performance efficiency improvements, reduction in noise, and improvements in rotor, helicopter transmission and engine life. The system and method provide for an increase in helicopter endurance and range. The system and method also provide a substantial improvement in helicopter performance during take-off, hover and maneuver. All such improvements are valid in helicopter mode when the helicopter is supported by rotor vertical lift, in airplane mode when the helicopter is supported by wing lift and the rotor is tilted forward to provide propulsive thrust and in conversion from helicopter mode to airplane mode.

5. 发明授权

US06467724B2 Articulated drive 失效
标题翻译：铰接式驱动
公开(公告)号：US06467724B2
公开(公告)日：2002-10-22
申请号：US09903782
申请日：2001-07-11
申请人： Hermann Kuenkler
发明人： Hermann Kuenkler
IPC分类号： B64C2752
CPC分类号： B64C29/0033 , B63H5/125 , B64B1/32 , B64B2201/00 , B64C11/02 , B64C27/28 , B64C27/52 , B64D35/00
摘要： An aircraft has a fuselage designed essentially as an aerostatic lift body and combined lift and propulsion devices which are articulated on the fuselage, are provided with propellers and form propulsion units and which in each case are tiltable between a lift position, in which the respective propeller rotation plane is essentially horizontal and the output shaft of the associated drive, said output shaft acting on the respective propeller shaft, is essentially vertical, and a propulsion position, in which the respective propeller rotation plane is essentially vertical and the output shaft of the associated drive, said output shaft acting on the respective propeller shaft, is essentially horizontal. The propeller rotation plane has all-round inclinability relative to the output shaft of the associated drive, said output shaft acting on the propeller shaft.
摘要翻译：飞机具有基本上被设计为空气静力升降机体的机身，并且在机身上铰接的组合的升降机和推进装置设置有螺旋桨和形式推进单元，并且在每种情况下都能够在提升位置之间倾斜，旋转平面基本上是水平的，并且相关联的驱动器的输出轴（所述输出轴作用在相应的传动轴上）基本上是垂直的，以及推进位置，其中相应的螺旋桨旋转平面基本上垂直并且相关联的输出轴驱动，所述输出轴作用在相应的传动轴上，基本上是水平的。螺旋桨旋转平面相对于相关驱动器的输出轴具有全方位的倾斜性，所述输出轴作用在传动轴上。

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