公开(公告)号：US5649678A

公开(公告)日：1997-07-22

申请号：US423539

申请日：1995-04-17

申请人： Alan Nurick

发明人： Alan Nurick

IPC分类号： B64C27/82 ,  B64C27/00

CPC分类号： B64C27/82 ,  B64C2027/8245

摘要： In a helicopter having a main rotor, a tail boom and a circulation control slot along one side of the tail boom, and a thruster which is selectively directable at either side or both sides of the rear end of the tail boom, anti-torque and yaw control are effected by generating separate air flow streams of different pressures by means of separate pressure means and conducting said separate air flow streams at said different pressures in separate passages to respectively the circulation control slot and to the thruster.

摘要翻译： 在具有主转子，尾臂和沿尾梁一侧的循环控制槽的直升机中，以及在尾臂的后端的任一侧或两侧选择性地指向的推力器，抗扭矩和 通过分开的压力装置产生不同压力的分开的空气流动来实现偏航控制，并将分离的通道中的所述不同压力的分开的空气流分别传送到循环控制槽和推进器。

公开(公告)号：US5542818A

公开(公告)日：1996-08-06

申请号：US298317

申请日：1994-09-01

申请人： Jerome M. Monvaillier ,  Jacques J. Polveda

发明人： Jerome M. Monvaillier ,  Jacques J. Polveda

IPC分类号： B64C27/45 ,  B64C27/82 ,  B64C27/48

CPC分类号： B64C27/82 ,  B64C2027/8254

摘要： In the rotor, the pitch lever of each blade is connected to the tab of the pitch control spider by a ball joint mounted on a wrist pin and received with clearance in an oblong opening in a ring. The axially offset bearing surfaces of the cuff of the blade are mounted with a radial clearance in the bearings of the hub on which they swivel about the pitch axis of the blade. These radial clearances enable contacts of the ball joint against the edge of the opening on the side of the ends of its minor axis, but prevent these contacts on the side of the ends of the major axis of the oblong opening.

摘要翻译： 在转子中，每个叶片的俯仰杆通过安装在腕针上的球形接头连接到俯仰控制蜘蛛的翼片上，并且在环中的长方形开口中以间隙接收。 叶片的袖带的轴向偏置的支承表面在轮毂的轴承中以径向间隙安装，在轮毂的轴承中，它们围绕叶片的俯仰轴线旋转。 这些径向间隙使得球形接头抵靠着其短轴端部侧面上的开口边缘，但是防止这些接触件在长方形开口的长轴端部的一侧。

公开(公告)号：US5498129A

公开(公告)日：1996-03-12

申请号：US298953

申请日：1994-09-01

申请人： Andre-Michel L. Dequin ,  Louis J. Daldoss ,  Henri F. Barquet

发明人： Andre-Michel L. Dequin ,  Louis J. Daldoss ,  Henri F. Barquet

IPC分类号： B64C27/82

CPC分类号： B64C27/82 ,  B64C2027/8254

摘要： The rotor is supported within the duct by a stationary flow-straightener with vanes connecting the wall of the duct to a central body housing the mechanism for driving the rotor. This mechanism is surrounded by a casing equipped with radial arms bearing removable means for fastening to an internal flange of the body, so as to fasten the flow-straightener and the casing rigidly to one another, and both into the duct.

摘要翻译： 转子通过固定的流动矫直机被支撑在管道内，叶片将管道的壁连接到容纳用于驱动转子的机构的中心体。 该机构由配备有径向臂的壳体包围，该臂具有用于紧固到主体的内部凸缘的可移除装置，以将流动整流器和壳体彼此刚性地紧固并且两者都进入管道。

公开(公告)号：US5478204A

公开(公告)日：1995-12-26

申请号：US272448

申请日：1994-07-11

申请人： Rene A. Desjardins ,  Francis H. McArdle

发明人： Rene A. Desjardins ,  Francis H. McArdle

IPC分类号： B64C27/45 ,  B64C27/82 ,  B64C27/48

CPC分类号： B64C27/82 ,  B64C27/45 ,  B64C2027/8254

摘要： A tail rotor for a rotary wing aircraft is located in a laterally directed duct located at the end of a tail cone extending rearward from the aircraft cabin and at the base of an empennage extending upward from the duct. The rotor includes a rotor shaft driveably connected to a power source, a rotor hub connected to the rotor shaft, a rotating control shaft, a stationary control shaft, and an actuator connected to the stationary control shaft for moving the rotating control shaft axially. The rotor hub includes rotor arms each supporting a pitch shaft-blade spar assembly for pivotable movement about a pitch axis. A pitch beam supports flexures, each connected to a pitch arm offset laterally from the associated pitch axis. The flexures driveably connect the pitch arms to the pitch beam and transmit pitch control motion to the blades as the pitch beam moves along the rotor axis. Pitch bearings, on which the pitch shafts turn about the pitch axes, are supported on a rotor hub shell fixed to the rotor hub.

摘要翻译： 用于旋转飞行器的尾部转子位于横向定向的管道中，该导管位于从飞机机舱向后延伸的尾锥的端部处，并且位于从管道向上延伸的尾叶的底部。 转子包括可驱动地连接到电源的转子轴，连接到转子轴的转子毂，旋转控制轴，固定控制轴和连接到静止控制轴的致动器，用于轴向移动旋转控制轴。 转子轮毂包括转子臂，每个转子臂支撑俯仰轴叶片翼梁组件，用于围绕俯仰轴线的可枢转运动。 俯仰梁支撑挠曲件，每个弯曲件连接到从关联的俯仰轴线横向偏移的俯仰臂。 当俯仰梁沿着转子轴线移动时，挠曲件将节距臂可调节地连接到俯仰梁并且将俯仰控制运动传递到叶片。 俯仰轴绕节距轴转动的俯仰轴承支撑在固定在转子轮毂上的转子轮毂壳上。

公开(公告)号：US5249925A

公开(公告)日：1993-10-05

申请号：US972640

申请日：1992-11-06

申请人： Bruno Guimbal ,  Jean-Pierre Jalaguier

发明人： Bruno Guimbal ,  Jean-Pierre Jalaguier

IPC分类号： B64C11/32 ,  B64C27/58 ,  B64C27/82 ,  F04D29/36 ,  B64C11/06

CPC分类号： F04D29/36 ,  B64C11/32 ,  B64C27/82 ,  B64C2027/8254

摘要： A variable-pitch multi-blade rotor for use as the anti-torque rear rotor of a rotating wing aircraft has a rotor with a central shaft rotated about a central axis, a hub constrained to rotate with the central shaft about the central axis, blades distributed around the central axis with each blade being connected to the central shaft by a twistable element, a pitch control disk for the blades which is constrained to rotate with the central shaft but free to slide axially relative to the central shaft, and a member for controlling the sliding of the pitch control disk along the central shaft. Each blade root is secured to a transverse thrust and pitch control lever forming a yoke having one end hinged to the hub and another end hinged to the pitch control disk.

摘要翻译： 用作旋转翼飞机的抗扭矩后转子的可变桨距多叶片转子具有转子，中心轴围绕中心轴线旋转，轮毂被限制为随中心轴绕中心轴线旋转，叶片 分布在中心轴线周围，每个叶片通过可扭转元件连接到中心轴，用于叶片的俯仰控制盘被限制为与中心轴一起旋转但可相对于中心轴轴向滑动， 控制俯仰控制盘沿着中心轴的滑动。 每个叶片根部固定到横向推力和俯仰控制杆，其形成具有铰接到毂的一端的轭，另一端铰接到俯仰控制盘。

公开(公告)号：US5209430A

公开(公告)日：1993-05-11

申请号：US788908

申请日：1991-11-07

申请人： John C. Wilson ,  Cynthia A. Crowell ,  Henry L. Kelley

发明人： John C. Wilson ,  Cynthia A. Crowell ,  Henry L. Kelley

IPC分类号： B64C23/00 ,  B64C27/04 ,  B64C27/82

CPC分类号： B64C27/82 ,  B64C23/00 ,  B64C27/04 ,  B64C2027/8245

摘要： A system for improving yaw control at low speeds consists of one strake placed on the upper portion of the fuselage facing the retreating rotor blade and another strake placed on the lower portion of the fuselage facing the advancing rotor blade. These strakes spoil the airflow on the helicopter tail boom during hover, low speed flight and right or left sidewards flight so that less side thrust is required from the tail rotor.

摘要翻译： 用于改善低速度的偏航控制的系统包括：放置在面向后退转子叶片的机身的上部上的一个行走板，以及放置在机身的面向前进的转子叶片的下部的另一个行星架。 在悬停，低速飞行和右侧或左侧飞行期间，这些横摆破坏了直升机尾翼上的气流，从而需要从尾部转子减少侧向推力。

公开(公告)号：US5205512A

公开(公告)日：1993-04-27

申请号：US746635

申请日：1991-08-19

申请人： William E. Rumberger

发明人： William E. Rumberger

IPC分类号： B64C27/82

CPC分类号： B64C27/82 ,  B64C2027/8245

摘要： A fluid control apparatus for proportionally directing fluid from a single conduct to multiple exhaust ports around the periphery of the duct. A controller is provided which is rotatably supported in the duct by an axial shaft. The shaft supports a radial barrier vane extending along its length and a helical vane forming a single 360.degree. helical wall surrounding the shaft. Rotation of the controller exhaust to shaft axis directs the fluid to the appropriate exhaust ports according to its angular position.

摘要翻译： 流体控制装置，用于将流体从单个导体成比例地引导到围绕管道周边的多个排气口。 设置有通过轴向可旋转地支撑在管道中的控制器。 轴支撑沿其长度延伸的径向阻挡叶片和形成围绕轴的单个360°螺旋壁的螺旋叶片。 控制器排气到轴轴的旋转根据其角度位置将流体引导到适当的排气口。

公开(公告)号：US5174523A

公开(公告)日：1992-12-29

申请号：US895166

申请日：1992-06-05

申请人： David E. H. Balmford

发明人： David E. H. Balmford

IPC分类号： B64C27/04 ,  B64C27/26 ,  B64C27/82

CPC分类号： B64C27/12 ,  B64C27/14 ,  B64C27/26 ,  B64C27/82 ,  B64C2027/8236 ,  B64C2027/8272 ,  B64C27/04

摘要： A compound helicopter includes a main sustaining rotor for hover and low speed flight, a propeller for providing propulsion in high speed flight and an engine. Engine output power is controlled so as to ensure efficient use of available power in both modes of operation. A preferred form of control includes a variable area exhaust nozzle from a gas turbine engine which has the advantage also in providing an augmenting jet thrust during high speed flight.

摘要翻译： 复合直升机包括用于悬停和低速飞行的主维持转子，用于在高速飞行中提供推进的螺旋桨和发动机。 控制发动机输出功率，以确保在两种运行模式下有效利用可用功率。 一种优选的控制形式包括来自燃气涡轮发动机的可变区域排气喷嘴，其具有在高速飞行期间提供增大喷射推力的优点。

公开(公告)号：US4759514A

公开(公告)日：1988-07-26

申请号：US913275

申请日：1986-09-30

申请人： John E. Burkam

发明人： John E. Burkam

IPC分类号： B64C27/82

CPC分类号： B64C27/82

摘要： A yaw rate stabilizer for the tail rotor of a helicopter includes a tail rotor shaft rotatably supporting a tail rotor on which rotor blades are radially mounted to develop a lift force directed substantially horizontal and transverse to the longitudinal axis of the aircraft. A slider is provided connected by pitch links to the rotor. The angle of attack of the blades varies with the displacement of the slider relative to a rotor. The rotor shaft is mounted pivotably by a universal joint on the tail of the helicopter fuselage. A frame, pivotably aligned with the universal joint, is supported by a tension or compression spring and connected to a collective pitch transfer lever. The slider, which is slidably mounted on the rotor shaft, moves toward the tail rotor and increases the collective pitch of the blades as a result of the rotor pivoting at the universal joint to precession caused by a transient, yaw moment applied to the rotor by a transverse gust of wind. The blades develop increased lift directed opposite to the gust which opposes the yaw moment and stabilizes the aircraft.

摘要翻译： 用于直升机的尾部转子的偏航率稳定器包括可转动地支撑尾部转子的尾部转子轴，转子叶片径向地安装在该转子叶片上，以形成基本上水平且横向于飞行器的纵向轴线的升力。 提供了一个通过到转子的俯仰连接连接的滑块。 叶片的迎角随着滑块相对于转子的位移而变化。 转子轴通过万向接头可枢转地安装在直升机机身的尾部。 与万向节枢转地对准的框架由张力或压缩弹簧支撑并连接到集体倾斜传递杆。 可滑动地安装在转子轴上的滑块朝向尾部转子移动，并且由于转子在万向接头处的枢轴转动而导致的叶片的总体间距由于通过施加到转子的瞬时横摆力矩引起的进动 横风阵风 叶片产生与阵风相反的增大的升力，其反对横摆力矩并使飞机稳定。

公开(公告)号：US4726547A

公开(公告)日：1988-02-23

申请号：US927660

申请日：1986-11-05

申请人： Herbert Zimmer

发明人： Herbert Zimmer

IPC分类号： B64C27/06 ,  B64C27/32 ,  B64C27/46 ,  B64C27/467 ,  B64C27/82 ,  B64C5/02

CPC分类号： B64C27/325 ,  B64C27/82 ,  B64C2027/8236 ,  B64C2027/8272

摘要： A helicopter having the usual tiltable, vertical thrust and lift producing rotor, a separate forward thrust producing propeller as well as provisions for yaw control and compensation is improved in that the propeller is constructed as unshrouded propulsion device. A pair of flow deflecting rudders is arranged downstream from the propeller and symmetrically to both sides of the craft; a frame on the tail portion of the craft includes vertical shafts for pivotally mounting the rudders. A T shaped support structure in the frame includes regular elevational, horizontally extending stabilizer fins and carrier arms. An elevator is arranged upstream from the propeller and from one of the elevational stabilizer fins. The elevator reaches laterally beyond and longitudinally alongside the one fin or beyond a circle provided by the propeller.

摘要翻译： 具有通常可倾斜，垂直推力和提升产生转子的直升机，单独的向前推力产生螺旋桨以及用于偏航控制和补偿的设备被改进，因为螺旋桨构造为无罩推进装置。 一对流动偏转方向舵被布置在螺旋桨的下游并对称于工艺的两侧; 工艺尾部的框架包括用于枢转地安装方向舵的垂直轴。 框架中的T形支撑结构包括规则的正面，水平延伸的稳定片和承载臂。 升降机布置在螺旋桨的上游和其中一个竖立的翼片上。 电梯横向延伸超过并沿着一个翼片纵向延伸或超过由螺旋桨提供的圆。