公开(公告)号：US07604460B2

公开(公告)日：2009-10-20

申请号：US11589950

申请日：2006-10-31

申请人： Gilbert Mestre ,  Guy Cruveiller

发明人： Gilbert Mestre ,  Guy Cruveiller

IPC分类号： B64C27/33

CPC分类号： B64C27/48 ,  B64C27/33 ,  B64C27/82

摘要： A rotorcraft rotor includes a hub , a first blade having a first twistable structure secured to the hub by a first bolt and a first ring or washer , a second blade having a second twistable structure secured to the hub by a second bolt and a second ring or washer. The rotor includes a stop structure for preventing each ring or washer from turning relative to the hub or relative to the corresponding twistable structure.

摘要翻译： 旋翼航空器转子包括轮毂，第一叶片，其具有通过第一螺栓和第一环或垫圈固定到轮毂的第一可扭转结构，第二叶片，具有通过第二螺栓固定到轮毂的第二可扭转结构， 或洗衣机。 转子包括用于防止每个环或垫圈相对于轮毂或相对于相应的可扭转结构转动的止动结构。

公开(公告)号：US20090057480A1

公开(公告)日：2009-03-05

申请号：US11846566

申请日：2007-08-29

申请人： Charles Lin

发明人： Charles Lin

IPC分类号： B64C27/04

CPC分类号： B64C27/10 ,  B64C27/82 ,  B64C2027/8272

摘要： A helicopter tail assembly includes a tail boom that extends along a tail axis, a tail fin mounted on one end of the tail boom, and a rudder mounted on the tail fin and pivotable relative to the tail fin about a pivot axis that is inclined with respect to the tail axis at an angle greater than 0 degrees and less than 90 degrees.

摘要翻译： 一个直升机尾部组件包括一个沿着尾部轴线延伸的尾部吊杆，一个安装在尾部悬臂的一端上的尾翼，以及一个安装在尾翼上的方向舵，围绕一个枢转轴线枢转， 相对于尾轴以大于0度且小于90度的角度。

公开(公告)号：US20080093500A1

公开(公告)日：2008-04-24

申请号：US11662559

申请日：2004-09-28

申请人： Dudley Smith ,  Walter Joiner ,  Paul Madej ,  Charles Hollimon ,  Daniel Robertson

发明人： Dudley Smith ,  Walter Joiner ,  Paul Madej ,  Charles Hollimon ,  Daniel Robertson

IPC分类号： B64C27/82

CPC分类号： B64C27/82 ,  B64C2027/8245

摘要： A rotorcraft having an enhanced configuration in which a simple wing and a propulsive anti-torque system are combined is disclosed. The propulsive anti-torque system includes an anti-torque thruster system in which a variable pitch fan is installed internal to the tail boom of the rotorcraft and an anti-torque thruster nozzle is mounted at the extremity of the tail boom. The fan is driven directly from the main rotor drive. The configuration and location of the fan allows the primary exhaust from the engine to be mixed with the compressed air flow from the fan. The mixed air flow from the fan and the engine passes through the tail boom and out the thruster nozzle.

摘要翻译： 公开了一种具有增强结构的旋翼航空器，其中简单翼和推进式反扭矩系统组合在一起。 推进式反扭矩系统包括抗扭矩推进器系统，其中可变桨距风扇安装在旋翼航空器尾翼的内部，反扭矩推进器喷嘴安装在尾吊臂的末端。 风扇直接从主转子驱动器驱动。 风扇的配置和位置允许来自发动机的主排气与来自风扇的压缩空气流混合。 来自风扇和发动机的混合空气流通过尾部悬臂并从推进器喷嘴出来。

公开(公告)号：US07293963B2

公开(公告)日：2007-11-13

申请号：US11031651

申请日：2005-01-05

申请人： Joseph B. Ozelski ,  James E. Rothman ,  David L. Myers, Jr.

发明人： Joseph B. Ozelski ,  James E. Rothman ,  David L. Myers, Jr.

IPC分类号： F03B3/14 ,  B64C27/48

CPC分类号： B64C27/82

摘要： A boot provides for removable attachment to a tail rotor assembly to flexibly protect the interior of the tail rotor blade assemblies. The boot includes a first fastener strip mounted adjacent a first boot edge and a second fastener strip mounted adjacent a second boot edge. The first and second fastener strips are “hook and loop” material to removably attach the edges which permits relatively uncomplicated installation and removal of the boot.

摘要翻译： 靴子提供可拆卸地连接到尾部转子组件以灵活地保护尾部转子叶片组件的内部。 所述护罩包括邻近第一护罩边缘安装的第一紧固件条和邻近第二引导边缘安装的第二紧固件条。 第一和第二紧固带是“钩和环”材料，以可拆卸地附接边缘，这允许相对简单的安装和拆卸护罩。

公开(公告)号：US20070181742A1

公开(公告)日：2007-08-09

申请号：US11736506

申请日：2007-04-17

申请人： Alexander Van de Rostyne ,  Kei Choi

发明人： Alexander Van de Rostyne ,  Kei Choi

IPC分类号： B64C27/08

CPC分类号： A63H27/02 ,  A63H27/06 ,  A63H27/12 ,  A63H30/04 ,  B64C27/43 ,  B64C27/82

摘要： A flying object with tandem rotors, in particular a helicopter, has a main rotor and a tandem rotor each with propeller blades which are driven by a rotor shaft and which is hinge-mounted to this rotor shaft. The angle between the surface of rotation of the main rotor and the rotor shaft may vary. A swinging manner on an oscillatory shaft is essentially transverse to the rotor shaft of the main rotor and is directed transversally to the longitudinal axis of the vanes. The main rotor and the tandem rotor each have an auxiliary rotor connected respectively to the main rotor and tandem rotor by a mechanical link. The swinging motions of the auxiliary rotor controls the angle of incidence (A) of at least one of the propeller blades of the main rotor and tandem rotor. There is an acute angle of displacement when viewing the propeller blades relative to the vanes in a direction perpendicular to their respective rotational planes.

摘要翻译： 具有串联转子，特别是直升机的飞行物体具有主转子和串联转子，每个转子均具有由转子轴驱动并且铰链安装到该转子轴上的螺旋桨叶片。 主转子和转子轴的旋转表面之间的角度可以变化。 振荡轴上的摆动方式基本上横向于主转子的转子轴，横向于叶片的纵向轴线。 主转子和串联转子各自具有通过机械连杆分别连接到主转子和串联转子的辅助转子。 辅助转子的摆动运动控制主转子和串联转子的至少一个螺旋桨叶片的入射角（A）。 在垂直于它们各自的旋转平面的方向上相对于叶片观察螺旋桨叶片时，存在锐角的位移。

公开(公告)号：US07252479B2

公开(公告)日：2007-08-07

申请号：US11140706

申请日：2005-05-31

申请人： Ashish Bagai ,  Robert C. Moffitt ,  Robert H. Blackwell, Jr. ,  Timothy A. Krauss

发明人： Ashish Bagai ,  Robert C. Moffitt ,  Robert H. Blackwell, Jr. ,  Timothy A. Krauss

IPC分类号： B64C27/46

CPC分类号： B64C27/10 ,  B64C27/467 ,  B64C27/82 ,  B64C2027/8236 ,  Y10S416/02 ,  Y10S416/05

摘要： A main rotor blade exhibiting a unique planform shape in which the blade chord increases from the root end of the blade inboard region to the outer main region of the blade, where the blade chord achieves a maximum chord at a spanwise location within the main region, then decreases toward a distal tip end. The leading edge preferably is generally straight while the trailing edge is contoured to define the chord. Another characteristic feature of the rotor blade design is the location of the blade-feathering axis in which the feathering axis is located at a mid chord position over some inboard length of the rotor blade then transitions to a quarter chord location. Another characteristic feature is an airfoil distribution along the blade span that transitions from a blunt trailing edge to a sharp trailing edge airfoil suited for mid-range Mach number operation. The tip region preferably utilizes a transonic flow airfoil. Another characteristic feature of the rotor blade design is an unconventional combination of positive and negative twist gradients.

摘要翻译： 具有独特平台形状的主转子叶片，其中叶片弦从叶片内侧区域的根部端延伸到叶片的外部主区域，其中叶片弦在主区域内的翼展方向位置处达到最大弦线， 然后朝向远端尖端减小。 前缘优选地大体上是直的，而后缘被轮廓化以限定弦。 转子叶片设计的另一个特征是叶片羽化轴线的位置，其中羽化轴线位于转子叶片的一些内侧长度处的中间弦位置，然后转变到四分之一弦的位置。 另一个特征是沿着叶片跨度的翼型分布，其从钝的后缘转变成适用于中档马赫数操作的锋利的后缘翼型。 尖端区域优选地使用跨音速流动翼型件。 转子叶片设计的另一个特征是正负扭转梯度的非常规组合。

公开(公告)号：US06371408B1

公开(公告)日：2002-04-16

申请号：US09632041

申请日：2000-08-03

申请人： Dennis Halwes

发明人： Dennis Halwes

IPC分类号： B64C1134

CPC分类号： B64C13/00 ,  B64C27/82

摘要： Apparatus and methods for automatically altering tail rotor authority on a helicopter based on ambient air pressure and temperature changes utilizing a sealed bellows which extends or retracts based on temperature and or pressure changes thereby moving a target attached thereto. Target position movement is sensed by proximity sensors which in turn activate relays operating a drive motor which changes the pivot position of a walking beam, bell crank or other tail rotor pitch control mechanism positioned between a manual input linkage and an output linkage extending to the tail rotor pitch control thereby altering the maximum tail rotor control, tail rotor authority available by a given movement of the manual input linkage while concurrently controlling the alignment of the proximity sensors so that the target is maintained between the proximity sensors. The apparatus and methods provide a system for easily and inexpensively adapting helicopters to operate at higher altitudes since the density altitude compensator described herein automatically allows progressively higher tail rotor blade angles as the density of the air falls or temperature increases, thus allowing increased tail rotor control in hot, high conditions and vice versa without the need for complex microprocessor or other logic circuits.

摘要翻译： 使用基于环境空气压力和温度变化的直升机自动改变尾部转子权限的装置和方法，所述密封波纹管基于温度和/或压力变化而延伸或缩回，从而移动附着于其上的目标。 目标位置移动由接近传感器感测到，其继而启动操作驱动马达的继电器，该驱动马达改变位于手动输入连杆机构和延伸到尾部的输出连杆之间的步进梁，曲柄或其它尾部转子桨距控制机构的枢转位置 转子桨距控制，从而改变最大尾部转子控制，通过手动输入联动装置的给定运动可用的尾部转子权能，同时控制接近传感器的对准，使得目标物体保持在接近传感器之间。 该装置和方法提供了一种用于容易且低成本地适应直升机在更高海拔下操作的系统，因为这里描述的密度高度补偿器在空气密度降低或温度升高时自动允许逐渐更高的尾部转子叶片角度，从而允许增加尾部转子控制 在高温条件下，反之亦然，无需复杂的微处理器或其他逻辑电路。

公开(公告)号：US06290171B1

公开(公告)日：2001-09-18

申请号：US09167613

申请日：1998-10-06

申请人： André-Michel Dequin ,  Valery Lionel Delisle

发明人： André-Michel Dequin ,  Valery Lionel Delisle

IPC分类号： B64C2782

CPC分类号： B64C13/16 ,  B64C27/82 ,  B64C2027/8272 ,  G05D1/0858

摘要： The present invention relates to a device (1A) for controlling a hybrid countertorque system of a helicopter (He), which comprises a countertorque rotor (R2), and at least one aerodynamic steering surface (D). According to the invention, said device comprises means (1A) for controlling, as a matter of priority, the aerodynamic surface (D) so that it generates lift which represents at least part of a first control command, which can be executed by said surface (D), and to control the countertorque rotor (R2) in such a way that the combined action of the surface (D) and of the rotor (R2) represents a command for controlling the helicopter (He) in terms of yaw.

摘要翻译： 本发明涉及一种用于控制直升机（He）的混合逆转矩系统的装置（1A），其包括反转矩转子（R2）和至少一个空气动力学转向面（D）。根据本发明，所述装置 包括用于优先控制空气动力学表面（D）的装置（1A），使得其产生代表可由所述表面（D）执行的第一控制命令的至少一部分的升力，并且控制 反转矩转子（R2）以这样的方式使得表面（D）和转子（R2）的组合作用代表用于在偏航方面控制直升机（He）的命令。

公开(公告)号：US5934608A

公开(公告)日：1999-08-10

申请号：US8118

申请日：1998-01-16

申请人： Gregory E. Dockter

发明人： Gregory E. Dockter

IPC分类号： B64C27/82

CPC分类号： B64C27/82 ,  B64C2027/8245

摘要： The bi-directional air flow deflector of the present invention efficiently deflects air to the left opening and the right opening, and minimizes any vertical components of force which may be generated. The air flow vector exiting from each of the openings comprises a dominant horizontal force vector rather than a large component of force in the vertical direction. Vertical components of force may be added, if desired. The bi-directional air flow deflector provides reduced transmission torque requirements, and generally comprises a relatively small number of moving parts. A single moving part may be used to deflect air to either the left opening or the right opening, and this single moving part is not exposed to the outside environment and, accordingly, will generally provide reliable functionality. The bi-directional air flow deflector of the present invention is simple in design, comprises a small number of relatively easy to manufacture parts, and can be used to retrofit existing direct jet thrusters. The components of the bi-directional air flow deflector generally comprise relatively straight sides and surfaces, which require less sophisticated tooling and reduce costs. The reduced number of parts will require a smaller stock of parts for inventory and field support. The bi-directional air flow deflector can be assembled with generally less man power than prior art devices, and generally comprises an increased reliability. Since less energy is generally required to operate the bi-directional air flow deflector of the present invention, increased fuel efficiency can also be realized.

摘要翻译： 本发明的双向空气导流板有效地将空气偏转到左开口和右开口，并且使得可能产生的任何垂直的力分量最小化。 从每个开口排出的空气流动矢量包括主要的水平力矢量，而不是垂直方向上的大的力分量。 如果需要，可以添加力的垂直分量。 双向气流导流器提供降低的传动扭矩要求，并且通常包括相对较少数量的运动部件。 单个移动部件可以用于将空气偏转到左开口或右开口，并且该单个移动部件不暴露于外部环境，因此通常将提供可靠的功能。 本发明的双向气流导流器设计简单，包括少量相对容易制造的部件，可用于改造现有的直接喷射推进器。 双向空气导流器的部件通常包括相对直的侧面和表面，这需要较不复杂的工具并降低成本。 零件数量的减少将需要较少的零件库存和现场支持。 双向气流导流器可以以比现有技术的装置通常更少的人力组装，并且通常包括增加的可靠性。 由于通常需要较少的能量来操作本发明的双向空气导流板，所以也可以实现提高的燃料效率。

公开(公告)号：US5676335A

公开(公告)日：1997-10-14

申请号：US402997

申请日：1995-03-08

申请人： Edward C. Murgia, Jr. ,  Thomas M. Andrews

发明人： Edward C. Murgia, Jr. ,  Thomas M. Andrews

IPC分类号： B64C27/82 ,  B64B1/36

CPC分类号： B64C27/82 ,  B64C2027/8245

摘要： A system is disclosed for controlling the external flow passing along the external surface of an aircraft such as the tailboom of a helicopter. A fan blows air into a cavity within a surface, and the air exits the surface through one or more axially oriented slots. A ramp structure is positioned within the cavity and upstream of each slot, and a set of fence structures are mounted in each slot and spaced from each other as well as from the ramp structure. The ramp and fence structures trip the airflow which then couples to the downstream side of the ramp and fence structures, thus eliminating the axial airflow component adjacent to the slot, and exits the slot in a direction normal to the axis. The airflow exits the slot in a direction tangential to the external surface and generally parallel with the external flow, resulting in deflection of the external flow and generating lift which is used to augment antitorque control in the helicopter implementation described.

摘要翻译： 公开了一种用于控制沿着飞机的外表面（例如直升机的尾部）通过的外部流动的系统。 风扇将空气吹入表面内的空腔，并且空气通过一个或多个轴向定向的槽离开表面。 斜坡结构位于空腔内和每个槽的上游，并且一组栅栏结构安装在每个槽中并且彼此间隔开并且与斜坡结构隔开。 斜坡和围栏结构使气流跳动，然后将气流耦合到斜坡和围栏结构的下游侧，从而消除了与槽相邻的轴向气流分量，并沿垂直于轴线的方向离开槽。 气流以与外表面相切的方向离开狭槽，并且大致平行于外部流动，导致外部流动的偏转和产生用于增强所述直升机实施方式中的反控制的电梯。