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1. 发明授权

US4556365A Hub plate for a helicopter rotor, method of manufacturing it, and a helicopter rotor hub equipped with plates 失效
标题翻译：用于直升机转子的轮毂板，其制造方法以及配备有板的直升机转子轮毂
公开(公告)号：US4556365A
公开(公告)日：1985-12-03
申请号：US512002
申请日：1983-07-08
申请人： Rene L. Mouille , Jean-Luc M. Leman
发明人： Rene L. Mouille , Jean-Luc M. Leman
IPC分类号： B64C27/32 , B64C11/04
CPC分类号： B64C27/32
摘要： A hub plate and helicopter rotor incorporating same made of a composite material and comprising a laminated disc constituted by layers of fiber cloth having high mechanical strength. A frame of the disc is made of aligned layers of the cloth with the weft or warp of the cloth extending radially in the direction corresponding to the direction of centrifugal force acting on the plate when in use. The aligned layers are positioned at the core of the structure and at least at the surface of the structure in the peripheral portion of the disc. The disc is enclosed by a belt of parallel threads consisting of fibers having high mechanical strength fitted on radially outwardly projecting parts of the disc in recesses formed in the outer edge of the parts, the recesses being open to the exterior.
摘要翻译：包括由复合材料制成的轮毂板和直升机转子，包括由具有高机械强度的纤维布层构成的层压盘。盘的框架由布的对准层制成，其中布的纬纱或经纱沿着与在使用时作用在板上的离心力的方向对应的方向径向延伸。对准的层被定位在结构的芯部处，并且至少在盘的周边部分中的结构的表面处。该盘由平行线包围，该平行线由具有高度机械强度的纤维组成，该纤维具有安装在盘的径向向外突出部分上的形成在部件的外边缘中的凹部中，凹部向外部敞开。

2. 发明授权

US4504193A Helicopter rotor with articulation means integrated in the root of the blade 失效
标题翻译：具有铰接装置的直升机转子集成在叶片的根部
公开(公告)号：US4504193A
公开(公告)日：1985-03-12
申请号：US423401
申请日：1982-09-24
申请人： Rene L. Mouille
发明人： Rene L. Mouille
IPC分类号： B64C27/32 , B64C27/35 , B64C27/48 , B64C27/51
CPC分类号： B64C27/48 , B64C27/32 , B64C27/35 , B64C27/51
摘要： The invention concerns a helicopter rotor, the rigid hub (1) of which comprises a central drum (2) which is disposed substantially in line with the rotor mast (3) and which carries an upper plate (4) and a lower plate (6). This rigid hub (1) is connected to the root of each blade (26) by way of a laminated spherical stop (13) and a resilient-return drag brace. Each blade (26) comprises, in the zone of its root, a rigid loop (27) which surrounds the laminated spherical stop (13) in a continuous manner and is engaged in the inner movable fitting (24) of this stop (13) by means of a wedge (30) co-operating with the outer fixed fitting (15) of the stop (13).
摘要翻译：本发明涉及一种直升机转子，其刚性轮毂（1）包括中心鼓（2），其基本上与转子桅杆（3）成一直线设置并且承载上板（4）和下板（6））。该刚性轮毂（1）通过层叠的球形止动件（13）和弹性回复拖链连接到每个叶片（26）的根部。每个叶片（26）在其根部的区域中包括以连续的方式围绕层压的球形止动件（13）并且接合在该止动件（13）的内部可动配件（24）中的刚性环（27）通过与止动件（13）的外部固定配件（15）配合的楔形件（30）。

3. 发明授权

US5242130A Method and device for the reduction of the oscillations of a divergent nature of the fuselage of a helicopter 失效
标题翻译：用于减少直升机的融合的多种性质的振荡的方法和装置
公开(公告)号：US5242130A
公开(公告)日：1993-09-07
申请号：US905453
申请日：1992-06-29
申请人： Rene L. Mouille , Philippe Roesch
发明人： Rene L. Mouille , Philippe Roesch
IPC分类号： B64C27/00 , B64C27/72
CPC分类号： B64C27/001 , B64C27/72 , B64C2027/002 , B64C2027/7233 , Y02T50/34 , Y10S416/50
摘要： Method and device for the reduction of the oscillations of a divergent nature induced in the fuselage (2) of a helicopter (1) by its rotary wings (3) when they are turning. According to the invention, the oscillations are detected (at 17, 18) and they are converted (at 19, 20) into electrical signals, which are used (at 13) in order to produce pitch variations of the blades (4) of the rotary wings (3), in such a way that a rotating torque vector opposing said oscillations results.
摘要翻译：直升机（1）在机身（1）的机身（2）中由旋转翼（3）转动时引起的发散特性振荡的方法和装置。根据本发明，检测振荡（在17,18处），并将它们（在19,20）转换成电信号（在13处），以便产生叶片（4）的间距变化旋转翼（3），使得产生与所述振荡相反的旋转扭矩矢量。

4. 发明授权

US4732540A Integrated hub-mast and gyroplane rotor head comprising it 失效
标题翻译：集成的桅杆和陀螺仪转子头包括它
公开(公告)号：US4732540A
公开(公告)日：1988-03-22
申请号：US886278
申请日：1986-07-16
申请人： Rene L. Mouille , Bruno Guimbal
发明人： Rene L. Mouille , Bruno Guimbal
IPC分类号： B64C27/35 , B64C27/32 , B64C27/38
CPC分类号： B64C27/32
摘要： The integrated hub-mast (1) of the invention is composed of a tubular single piece body whose hub body forming part (3) is integral, on the side of its end end opposite the mast (2), with a reinforcing ring (5) and in which openings (6) are pierced. For each blade of the rotor, a stratified spherical stop (16) is fixed against the ring (5) and is retained in the hub body (3) and this stop (16) is also fixed to the ends integral to the hub body (3) of the lower (24) and upper (25) branches of a forked fastening part (23) connecting the blade (22) to the stop (16), the lower branch (24) passing through an opening (6) in the hub (3). A central flapping stop (30) is mounted on a support (31), in the hub-mast (1), which carries external fastenings for coupling to the resilient drag return and damping members of the blade.
摘要翻译：本发明的集成轮毂 - 桅杆（1）由一个管状的单件本体组成，其中毂体形成部分（3）在与桅杆（2）相对的端部一侧具有一体的加强环（5）），并且其中开口（6）被刺穿。对于转子的每个叶片，分层的球形止挡件（16）固定抵靠环（5）并且保持在轮毂体（3）中，并且该止动件（16）也固定到与轮毂体一体的端部将所述叶片（22）连接到所述止动件（16）的叉形紧固部件（23）的下部（24）和上部（25）分支中的下部分支（3）枢纽（3）。中心扑动止动件（30）安装在轮毂桅杆（1）中的支撑件（31）上，所述支撑件承载用于联接到所述叶片的弹性阻力返回和阻尼构件的外部紧固件。

5. 发明授权

US4458862A Antiresonant suspension device for helicopter 失效
标题翻译：用于直升机的反谐振悬挂装置
公开(公告)号：US4458862A
公开(公告)日：1984-07-10
申请号：US470704
申请日：1983-02-28
申请人： Rene L. Mouille , Gerard C. L. Genoux , Pierre E. Hege
发明人： Rene L. Mouille , Gerard C. L. Genoux , Pierre E. Hege
IPC分类号： F16F15/02 , B64C27/00 , B64C27/51 , B64C27/06
CPC分类号： B64C27/001 , B64C2027/002 , B64C2027/005 , Y10S416/50
摘要： The invention relates to aeronautics in general, and in particular to a suspension device for helicopter, comprising a flexible mounting plate at the center of which is fixed the bottom of the main gear box whose top is supported by hinged oblique bars. The mounting plate offers radial arms hinged to the base of the bars and to the fuselage of the helicopter. These arms bear flapping weights creating forces of inertia with reactions at the attachment points of direction opposite the elastic reactions of deformation of the mounting plate. A device of this type enables the vibrations on board helicopters to be reduced.
摘要翻译：本发明一般涉及航空，特别涉及一种用于直升机的悬挂装置，其包括柔性安装板，其中心部分固定在主齿轮箱的底部，其顶部由铰接的倾斜杆支撑。安装板提供径向臂，铰接到杆的底部和直升机的机身。这些手臂具有挥动重量，产生与安装板的变形的弹性反应相反的方向的附接点处的反应的惯性力。这种装置能够减少直升机上的振动。

6. 发明授权

US5316442A Articulated rotor head for gyroplanes 失效
标题翻译：用于陀螺仪的铰接转子头
公开(公告)号：US5316442A
公开(公告)日：1994-05-31
申请号：US994749
申请日：1992-12-22
申请人： Rene L. Mouille
发明人： Rene L. Mouille
IPC分类号： B64C27/35 , B64C27/48
CPC分类号： B64C27/35
摘要： The invention relates to an articulated rotor head for gyroplanes comprising a rigid central hub body (1), perpendicularly integrated with a drive shaft (2), each blade (3) being radially fixed to the hub body (1) by means of connecting and articulating components. These components each comprise:a spherical laminated elastomer stop (4) housed in the central hub body;a hollow sleeve (5) rigidly locked to the spherical laminated stop (4);an elastic return and drag damping brace (9) of the blade (3) arranged between the sleeve and the outer part of the rigid hub body (1) on a contiguous sleeve;a connecting and pitch articulation spindle (6) of the blade (3) connected to the foot of the blade (3) and a pitch lever (8) rigidly locked to the spindle (6) and which swivels about the pitch axis inside the sleeve (5) on two bearings, one of which at least forms a thrust stop (7) to transmit, from the spindle (6) in the sleeve (5), the thrust loads originating from the centrifugal forces on the blade (3).
摘要翻译：本发明涉及一种用于陀螺仪的铰接式转子头，其包括与驱动轴（2）垂直成一体的刚性中心毂体（1），每个叶片（3）通过连接和铰接部件。这些部件各自包括：容纳在中心毂体中的球形层压弹性体止挡件（4）刚性地锁定到球形层压止动件（4）的中空套筒（5）; 布置在所述套筒和所述刚性轮毂体（1）的外部部分之间的所述叶片（3）上的弹性返回和阻尼阻尼支架（9）在连续的套筒上; 连接到叶片（3）的脚部的叶片（3）的连接和俯仰铰接轴（6）和刚性地锁定到主轴（6）的变桨杆（8），并且围绕套筒（5）在两个轴承上，其中一个轴承至少形成从套筒（5）中的主轴（6）传递来自叶片（3）上的离心力的推力载荷的推力停止件（7）。

7. 发明授权

US5228640A Device for the elastic coupling between two parts, and aircraft with rotating wings comprising said device 失效
标题翻译：用于两部件之间的弹性联接的装置，以及包括装置的旋转翼的飞机
公开(公告)号：US5228640A
公开(公告)日：1993-07-20
申请号：US897986
申请日：1992-06-16
申请人： Rene L. Mouille
发明人： Rene L. Mouille
IPC分类号： B64C27/00 , F16F13/00
CPC分类号： B64C27/001 , F16F13/00
摘要： A device for elastic coupling between two parts, especially the principal transmission box and the fuselage of an aircraft with rotating wings, such as a helicopter, includes first and second inner and outer tubular bodies, and an elastic connection, housed in the annular space existing between the first and second bodies and coupling the first and second bodies in a leaktight fashion. The annular space is separated by the elastic connection into first and second chambers filled with a liquid, the first and second chambers being in communication with the inside of the first body. On the inside of said first body, there is a liquid distributor provided with an elastic damping connection and including two pistons, which are coupled by a piston rod and separated from each other by the distance separating orifices in the first and second chambers.
摘要翻译：用于两部分之间弹性联接的装置，特别是具有旋转翼的飞机（如直升机）的主要传输箱和机身包括第一和第二内管和外管，以及容纳在现有环形空间中的弹性连接在第一和第二主体之间并且以密封方式联接第一和第二主体。环形空间被弹性连接分隔成填充有液体的第一和第二室，第一和第二室与第一主体的内部连通。在所述第一主体的内侧，设有一个液体分配器，该液体分配器具有弹性阻尼连接件，并包括两个活塞，活塞通过活塞杆联接并在第一和第二腔室中彼此隔开分隔开的孔。

8. 发明授权

US4304525A Helicopter rotor 失效
标题翻译：直升机转子
公开(公告)号：US4304525A
公开(公告)日：1981-12-08
申请号：US43878
申请日：1979-05-30
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。

9. 发明授权

US4281967A Resonator device for damping the vibrations of a rotor of a rotary-wing aircraft 失效
标题翻译：用于阻尼旋翼飞机转子振动的谐振器装置
公开(公告)号：US4281967A
公开(公告)日：1981-08-04
申请号：US9578
申请日：1979-02-05
申请人： Rene L. Mouille , Gerard C. L. Genoux , Marc A. Declercq , Jean-Luc M. Leman , Robert J. Suzzi
发明人： Rene L. Mouille , Gerard C. L. Genoux , Marc A. Declercq , Jean-Luc M. Leman , Robert J. Suzzi
IPC分类号： B64C27/00 , B64C27/32
CPC分类号： B64C27/001 , B64C2027/003 , Y10S416/50 , Y10T464/50
摘要： The invention relates to a device for damping the vibrations of a rotary-wing aircraft rotor. An annular weight is disposed concentrically of the rotor axis. This weight is supported by at least three resiliently deformable elements such as helical springs, radially biased in directions distributed regularly around the rotor axis. The inner ends of the springs directly bear on a part extending the rotor shaft axially. Their outer ends directly bear on the annular weight so that the spring apply statically balanced centrifugal thrusts to the annular weight. The springs are so still that they support the annular weight without substantially bending.
摘要翻译：本发明涉及一种用于阻尼旋翼飞机转子振动的装置。环形重物与转子轴线同心设置。这种重量由至少三个可弹性变形的元件（例如螺旋弹簧）支撑，径向偏压地围绕转子轴线规则地分布。弹簧的内端直接承载在轴向上延伸转子轴的部分上。它们的外端直接承受环形重量，使得弹簧将静态平衡的离心推力施加到环形重物上。弹簧仍然如此，使得它们支撑环形重量而基本不弯曲。

10. 发明授权

US4274510A Multi-directional suspension means for rotor aircraft 失效
标题翻译：用于转子飞机的多方向悬挂装置
公开(公告)号：US4274510A
公开(公告)日：1981-06-23
申请号：US21778
申请日：1979-03-19
申请人： Rene L. Mouille , Edwin Ortega
发明人： Rene L. Mouille , Edwin Ortega
IPC分类号： B64C27/51 , B64C27/00 , F16F15/00 , F16F15/02 , B64D27/00
CPC分类号： F16F15/02 , B64C27/001 , B64C2027/002 , Y10S416/50 , Y10T464/50
摘要： Suspension means for mechanical elements which have a plate rigid with an element which is to be suspended. The rigid plate is connected to fixed mountings by flexible studs working in compression and by a deformable articulated system composed of connecting rods and a floating cross-member, ensuring rotationally rigid connection and providing for absorption of a torque originating from the suspended element, while allowing the element to perform translatory movements.
摘要翻译：用于机械元件的悬挂装置，其具有与待悬挂的元件刚性的板。刚性板通过以压缩方式工作的柔性螺柱和由连接杆和浮动横梁组成的可变形铰接系统连接到固定安装座，确保旋转刚性连接并提供吸收来自悬挂元件的扭矩，同时允许执行翻译运动的元素。

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