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    "> Directional and stabilizing device having a faired and slanted antitorque rotor and a disymmetric
    11.
    发明授权
    Directional and stabilizing device having a faired and slanted antitorque rotor and a disymmetric "V" empennage, and a helicopter equipped with such a device 失效
    定向和稳定装置具有流畅和倾斜的反转子转子和不对称的“V”尾翼，以及配备有这种装置的直升机

    公开(公告)号：US4809931A

    公开(公告)日：1989-03-07

    申请号：US62656

    申请日：1987-06-16

    申请人： Rene L. Mouille ,  Philippe A. Rollet

    发明人： Rene L. Mouille ,  Philippe A. Rollet

    IPC分类号： B64C27/82

    CPC分类号： B64C27/82 ,  B64C2027/8254 ,  B64C2027/829

    摘要： A directional and stabilizing device is provided including a faired antitorque rotor, driven in rotation in a transverse aperture formed in a fairing slanted with respect to the vertical by an angle between 0.degree. and 45.degree.. It also includes a "V" empennage fixed to the top of the fairing and the two aerodynamic surfaces of which extend disymmetrically with respect to the vertical plane passing through the top of this fairing, the aerodynamic surfaces being slanted in angular planes between 0.degree. and 45.degree..

    摘要翻译： 提供了一种定向和稳定装置，包括一个流动的反转子转子，其旋转驱动在横向孔中，横向孔形成在相对于垂直方向倾斜0°至45°之间的角度的整流罩中。 它还包括固定在整流罩顶部的“V”尾翼，其两个空气动力学表面相对于穿过该整流罩顶部的垂直平面不对称地延伸，空气动力学表面倾斜在0°和 45度。

    Helicopter rotor
    15.
    发明授权
    Helicopter rotor 失效
    直升机转子

    公开(公告)号：US4407633A

    公开(公告)日：1983-10-04

    申请号：US300091

    申请日：1981-09-08

    申请人： Rene L. Mouille

    发明人： Rene L. Mouille

    IPC分类号： B64C27/32 ,  B64C27/35 ,  B64C27/51 ,  B64C27/38

    CPC分类号： B64C27/35 ,  B64C27/32 ,  B64C27/51

    摘要： Rotary-wing aircraft rotor comprising a rigid hub coupled to the root of each blade in which a trailing return brace comprises a stack of metal plates alternating with plates of visco-elastic material the ends of which being coupled via a ball joint respectively to the root of one blade and to a place of the hub such that the brace is always slightly inclined.

    摘要翻译： 旋转翼飞机转子包括联接到每个叶片的根部的刚性轮毂，其中拖尾返回支架包括与粘弹性材料板交替的金属板堆叠，其粘结弹性材料的端部分别通过球接头连接到根部 一个叶片和一个轮毂的位置使得支架总是略微倾斜。

    High performance blade for helicopter rotor
    16.
    发明授权
    High performance blade for helicopter rotor 失效
    用于直升机转子的高性能刀片

    公开(公告)号：US4392781A

    公开(公告)日：1983-07-12

    申请号：US243348

    申请日：1981-03-13

    申请人： Rene' L. Mouille ,  Jacques R. Gallot ,  Jean-Marc E. Pouradier

    发明人： Rene' L. Mouille ,  Jacques R. Gallot ,  Jean-Marc E. Pouradier

    IPC分类号： B64C27/46 ,  B64C27/467

    CPC分类号： B64C27/467 ,  Y10S416/02

    摘要： The present invention relates to a high performance blade for helicopter rotor presenting an aerodynamic surface produced by profiles of which the aerodynamic twist increases from the end profile towards the root profile and is then reversed and becomes zero at the fastenings of the blade. According to the invention, the angle of twist formed by the zero lift chord C.sub.o of a profile of the aerodynamic surface and a reference plane P passing through the center of the fastenings of the blade to the hub of the rotor, is, for the end profile, at the most equal to a value .theta..sub.1 of 0.3 degrees. The invention is more particularly applied to the obtaining of rotary wings, for example for helicopters, capable of very high performances, particularly in rapid forward flight under high load.

    摘要翻译： 本发明涉及一种用于直升机转子的高性能叶片，其具有由空气动力学扭曲从端部轮廓朝向根轮廓增加的轮廓产生的空气动力学表面，然后在叶片的紧固件处被反转并变为零。 根据本发明，通过空气动力学表面轮廓的零提升弦Co和通过叶片的紧固件的中心到转子轮毂的参考平面P形成的扭转角度为了结束 轮廓，最等于0.3度的θ1值。 本发明更具体地应用于获得具有非常高性能的直升机的旋转翼，特别是在高负载下的快速向前飞行中。

    Variable-pitch rotor, specially for a rotary-wing aircraft
    17.
    发明授权
    Variable-pitch rotor, specially for a rotary-wing aircraft 失效
    可变桨距转子，专门用于旋翼飞机

    公开(公告)号：US4222709A

    公开(公告)日：1980-09-16

    申请号：US923433

    申请日：1978-07-10

    申请人： Rene L. Mouille

    发明人： Rene L. Mouille

    IPC分类号： B64C27/33 ,  B64C27/38

    CPC分类号： B64C27/33

    摘要： The invention relates to a variable-pitch rotor, specially for a rotary-wing aircraft. Each blade of the rotor is connected to the hub by a flexible connecting member comprising a radial bundle of fibres, each agglomerated by a resin and secured together by a vulcanized elastomer. A rigid tubular sleeve surrounds the connecting member without contact thereto. The outer end of the tubular sleeve is secured to the root part of the blade and its inner end is secured to a rigid ring, to which a blade pitch control lever is externally articulated. Spherical ball and socket joint members are inserted between the rigid ring and rigid parts of the rotor hub. Frequency adaptors are associated with the ball and socket joint members.

    摘要翻译： 本发明涉及一种专门用于旋翼飞机的可变桨距转子。 转子的每个叶片通过包括一束径向纤维束的柔性连接构件连接到轮毂，每个纤维束由树脂凝聚并由硫化弹性体固定在一起。 刚性管状套筒围绕连接构件而不与其接触。 管状套管的外端固定到叶片的根部，并且其内端固定到刚性环，叶片俯仰控制杆从外部铰接到该刚性环上。 球形球窝接头构件插入转子毂的刚性环和刚性部件之间。 频率适配器与球窝接头构件有关。

    Gyrocraft rotor hub body
    18.
    发明授权
    Gyrocraft rotor hub body 失效
    Gyrocraft转子毂体

    公开(公告)号：US5267833A

    公开(公告)日：1993-12-07

    申请号：US799245

    申请日：1991-11-27

    申请人： Rene L. Mouille

    发明人： Rene L. Mouille

    IPC分类号： B64C11/02 ,  B64C27/32 ,  B64C27/35 ,  B64C27/48

    CPC分类号： B64C27/32 ,  B64C27/322 ,  B64C27/35 ,  B64C27/48

    摘要： Gyrocraft rotor hub body (1) in which each blade (2) is linked to the body (1) by articulations and linking members the body includes two strong elements (7, 8) whose planes are substantially parallel to each other and perpendicular to the axis of the mast (3) of the rotor. The two elements (7, 8) are separated from each other by a space which is of sufficient size to permit the housing of the articulations which are advantageously embodied in the form of laminated spherical stops (5), one of the armatures (16) of which moves integrally with the (17) is fixed with respect to the two elements of the hub body and is arranged in the vicinity of the periphery of these elements so as to constitute a rigid bracing. The two elements are rings, an external ring (7) and an internal ring (8) each forming a rigid rim and which are linked by a thin wall (9) of substantially cylindrical form, and which comprises at least as many openings (10) as there are blades (2) each opening (10) has dimensions sufficient for the passage of the linking and articulation members of the corresponding blade (2) with their angular flappings.

    摘要翻译： 其中每个叶片（2）通过铰接和连接构件连接到主体（1）的陀螺转子轮毂体（1），该主体包括两个强力元件（7,8），它们的平面基本上彼此平行并垂直于 转子的桅杆（3）的轴线。 两个元件（7,8）通过具有足够尺寸的空间彼此分开，以允许有利地以层叠的球形止挡件（5）的形式体现关节的外壳，电枢（16）中的一个 其与（17）一体地移动相对于轮毂体的两个元件固定，并且布置在这些元件的周边附近，以构成刚性支撑。 两个元件是环，外环（7）和内环（8），每个形成刚性边缘并且由大体圆柱形形式的薄壁（9）连接，并且包括至少一个开口（10 ），因为存在叶片（2），每个开口（10）具有足够的尺寸以使相应的叶片（2）的连接和铰接构件以其角度翻转通过。

    Gyrocraft articulated rotor head with intermediate sleeves between hub and blades
    19.
    发明授权
    Gyrocraft articulated rotor head with intermediate sleeves between hub and blades 失效
    GYROCRAFT AROTULATED转子头与中心线和叶片之间的中间线

    公开(公告)号：US5242266A

    公开(公告)日：1993-09-07

    申请号：US806399

    申请日：1991-12-13

    申请人： Rene L. Mouille

    发明人： Rene L. Mouille

    IPC分类号： B64C27/48

    CPC分类号： B64C27/48

    摘要： Gyrocraft rotor head including a hub connected to each blade (2) of the rotor by a linking member which is integral with the blade (2) and which is linked to the hub body by a laminated spherical stop. Each blade (2) is fitted with an assembly (20) for elastic recall in drag with incorporated damping, one of whose extremities (22) is linked to the member linking the blade to the hub body. The linking member is constituted by an intermediate sleeve (11) comprising one part in the form of a ring (12) and one part fitted with at least one double clevis (14), the intermediate sleeve (11) being a single integral assembly of which the ring (12) surrounds the laminated spherical stop with which it is integrated and of which the double clevis or clevises interact with the structure for integration of the blade (2).

    摘要翻译： 旋转转子头包括通过与叶片（2）成一体的连接构件连接到转子的每个叶片（2）的轮毂，并且通过层叠的球形止挡件连接到轮毂体。 每个叶片（2）装配有用于弹性回缩的组件（20），其具有结合的阻尼，其中一个末端（22）连接到将叶片连接到轮毂体的构件。 连接构件由中间套筒（11）构成，中间套筒（11）包括环形（12）形式的一部分和一部分装配有至少一个双钩子（14），中间套筒（11）是单个整体组件 环（12）围绕层叠的球形止挡件，其与其一体化，并且其中双U形夹或U形夹与用于叶片（2）的整合的结构相互作用。

    Flapping restrainer device for rotorcraft rotor blades, and rotor head comprising said device
    20.
    发明授权
    Flapping restrainer device for rotorcraft rotor blades, and rotor head comprising said device 失效
    用于旋翼飞行器转子叶片的挡板限制装置和包括所述装置的转子头

    公开(公告)号：US5007799A

    公开(公告)日：1991-04-16

    申请号：US411128

    申请日：1989-09-22

    申请人： Rene L. Mouille ,  Robert J. Suzzi

    发明人： Rene L. Mouille ,  Robert J. Suzzi

    IPC分类号： B64C27/48 ,  B64C27/32

    CPC分类号： B64C27/322

    摘要： The invention relates to a flapping restrainer device for the blades of a rotorcraft main rotor, and a rotor head comprising the same. The lower restrainers comprise a reciprocal star-shaped plate (32), having as many radial branches (33) as blades, and each one of the branches being engaged into a radial opening (6) of the hub (3). Outside the latter, the star-shaped plate (32) cooperates with supporting runners (47) integral with the blades. The upper restrainers comprise, for each blade, a stop which is retractable by the effect of the centrifugal force and which is composed of a lever (52), pivoting on a pivot (53) carried by the hub (3), and a first arm (55) of which constitutes a stop finger directed towards an upper supporting component (60) integral with the blade, while a second arm (56) carries a governor weight (57) and a nose (58) for support against a shoulder (59) integral with the hub (3).

    摘要翻译： 本发明涉及一种用于旋翼航空器主转子的叶片的挡板限制装置以及包括其的转子头。 下限制器包括具有与叶片一样多的径向分支（33）的互倒星形板（32），并且每个分支接合到轮毂（3）的径向开口（6）中。 在后者之外，星形板（32）与与叶片成一体的支撑流道（47）协作。 上限制器包括用于每个叶片的止挡件，该止挡件可通过离心力的作用而缩回，该止挡件由在枢轴（53）承载的枢轴（53）上枢转的杆（52）和第一 手臂（55）构成指向与刀片成一体的上部支撑部件（60）的止挡手指，而第二臂（56）承载有调节器重量（57）和用于支撑肩部的鼻部（58） 59）与轮毂（3）成一体。