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。

公开(公告)号：US4808075A

公开(公告)日：1989-02-28

申请号：US123605

申请日：1987-11-20

申请人： Emilio Pariani ,  Vittorio Caramaschi ,  Pierluigi Castelli

发明人： Emilio Pariani ,  Vittorio Caramaschi ,  Pierluigi Castelli

IPC分类号： B64C27/37 ,  B64C27/32 ,  B64C27/38

CPC分类号： B64C27/322

摘要： A helicopter rotor on which each blade is connected in articulated manner to a center hub by means of a fork, the vertical plane movement of which is limited, below a given speed of the rotor, by a pair of limit rocker arms located between the hub and a ring nut mounted for rotation on the fork and angularly integral with the hub by means of a rod of variable length connected in articulated manner to a slide supported on the hub and arranged substantially horizontally and crosswise in relation to the blade.

摘要翻译： 一种直升机转子，每个叶片通过叉子以铰接的方式连接到中心毂，其垂直平面运动受到转子的给定速度的限制，位于毂之间的一对限位摇臂 以及环形螺母，其安装成用于在叉上旋转并且通过可变长度的杆以与铰接的方式成角度地成一体的环形螺母连接到支撑在轮毂上的滑块，并且相对于叶片基本上水平且横向地设置。

公开(公告)号：US4652211A

公开(公告)日：1987-03-24

申请号：US830543

申请日：1986-02-18

申请人： Pierluigi Castelli ,  Vittorio Caramaschi

发明人： Pierluigi Castelli ,  Vittorio Caramaschi

IPC分类号： B64C27/35 ,  B64C27/32 ,  B64C27/48 ,  B64C27/38

CPC分类号： B64C27/322

摘要： Helicopter rotor on which each blade is connected in articulated manner to a center hub by means of a forkthe vertical plane movement of which, at rotor speeds below a given set value, is limited by a pair of limit rocker arms located between the hub and a ring nut mounted in rotary manner on the forkand rendered angularly integral with the hub by means of a compass drive.

摘要翻译： 直升机转子，每个叶片通过叉子以铰接方式连接到中心毂，其转子速度低于给定设定值的垂直平面运动由一对位于轮毂和 环形螺母以旋转方式安装在叉上，并通过罗盘驱动器与轮毂成角度地成一体。

公开(公告)号：US4549851A

公开(公告)日：1985-10-29

申请号：US606183

申请日：1984-05-02

申请人： Emilio Pariani

发明人： Emilio Pariani

IPC分类号： B64C27/32 ,  B64C27/39

CPC分类号： B64C27/322

摘要： Helicopter rotor on which the blades are each connected to a center hub plate by means of a U-shaped fork connected to the hub by an elastomer support, the latter supporting a static supporting device for limiting dynamic oscillation on the relative blade in the vertical plane, the said device providing for use of a pin faceted on the side, mounted so as to turn on a taper seat integral with the relative fork and designed to engage with a mating surface integral with the hub.

摘要翻译： 直升机转子，其叶片各自通过由弹性体支撑件连接到轮毂的U形叉连接到中心轮毂板，后者支撑静态支撑装置，用于限制垂直平面中的相对叶片上的动态振动 所述装置提供使用在侧面上分针的销，安装成使得与相关叉形成一体的锥形座，并被设计成与与轮毂一体的配合表面接合。

公开(公告)号：US4419051A

公开(公告)日：1983-12-06

申请号：US348889

申请日：1982-02-16

申请人： Richard T. DeRosa

发明人： Richard T. DeRosa

IPC分类号： B64C27/32 ,  B64C27/33 ,  B64C27/58 ,  B64C27/38

CPC分类号： B64C27/58 ,  B64C27/322 ,  B64C27/33

摘要： A rotor system for a helicopter including a tension/torsion component which is fabricated from composite material and as a compound curved, continuous loop twin tension/torsion beam. Each end of the twin tension/torsion beam includes two curved (wrapped) ends which are oriented substantially orthogonally. At one end the curved ends extend about the flap hinge, and at the other end the curved ends extend about the fold and lead/lag hinge of the rotor system. To accommodate the twin tension/torsion beam at the flap hinge a support fitting is provided with lugs which are made compatible with the rotor hub lugs, and to accommodate the twin tension/torsion beam at the fold and lead/lag hinge a pitch varying structure is provided with twin beam engaging clevis surfaces.

摘要翻译： 一种用于直升机的转子系统，其包括由复合材料制成的拉伸/扭转部件，并且作为复合弯曲的连续环形双张力/扭转梁。 双张力/扭转梁的每一端包括基本上正交取向的两个弯曲（包裹的）端部。 在一端，弯曲的端部围绕翼片铰链延伸，并且在另一端，弯曲的端部围绕转子系统的折叠和引导/延迟铰链延伸。 为了在翼片铰链处适应双张力/扭转梁，支撑配件设置有与转子毂凸耳相容的凸耳，并且在折叠处和牵引/延迟铰链处适应双张力/扭力梁，俯仰变化结构 设有双梁接合U形夹表面。

公开(公告)号：US4368006A

公开(公告)日：1983-01-11

申请号：US176151

申请日：1980-08-07

申请人： Donald L. Ferris ,  Robert C. Rybicki

发明人： Donald L. Ferris ,  Robert C. Rybicki

IPC分类号： B64C27/32 ,  B64C27/40

CPC分类号： B64C27/322

摘要： An improved droop stop for a fully articulated helicopter rotor is providedherein curved mating surfaces are employed between the spindle pad and the centrifugal droop stop static support arm to provide surface rather than line contact therebetween during centrifugal operation. The centers of the curved surfaces are coincident at the pivot point of the droop stop centrifugal arm to force the downward load of the blade to pass through this pivot point.

摘要翻译： 提供了一种用于完全铰接的直升机转子的改进的下垂停止件，其中在主轴垫和离心下垂停止静力支撑臂之间采用弯曲配合表面，以在离心操作期间提供表面而不是线间接触。 弯曲表面的中心在下垂停止离心臂的枢转点处重合，以迫使叶片的向下的载荷通过该枢转点。

公开(公告)号：US4074952A

公开(公告)日：1978-02-21

申请号：US700455

申请日：1976-06-28

申请人： Evan A. Fradenburgh ,  Jay M. Yarm

发明人： Evan A. Fradenburgh ,  Jay M. Yarm

IPC分类号： B64C11/00 ,  B64C27/32 ,  B64C27/54 ,  B64C11/28

CPC分类号： B64C27/322 ,  B64C11/003 ,  B64C27/54

摘要： A locking control system and an overtravel safety stop system are presented for a variable length rotor blade system. The lock system has a lock mechanism operated by a pilot actuated lock shaft to lock and unlock the blade adjustment system. A traveling nut locks the blade adjustment system to prevent overretraction or overextension.

摘要翻译： 提出了一种可变长度的转子叶片系统的锁定控制系统和超程安全停止系统。 锁定系统具有由先导驱动的锁定轴操作的锁定机构，以锁定和解锁刀片调整系统。 行进的螺母锁定刀片调整系统以防止过度伸缩或过度伸展。

公开(公告)号：US3932059A

公开(公告)日：1976-01-13

申请号：US540309

申请日：1975-01-10

申请人： Robert C. Rybicki

发明人： Robert C. Rybicki

IPC分类号： B64C27/32 ,  B64C27/35 ,  B64C27/48 ,  B64C27/38

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

摘要： A fully articulated helicopter rotor having an elastomeric type main bearing which is reactive of all blade motions about the intersecting blade pitch change, lead-lag, and coning axes, including blade droop supporting and limiting members for static and dynamic operating conditions wherein coupling influences between the separate blade motions are precluded. In reacting these blade weight loadings and dynamic thrust forces, the droop members specifically provide full area contact bearing surfaces to distribute the large forces from the blades into the rotor hub proper while avoiding scuffing or rolling contact between the parts, and the high bearing stresses which would result from either point or line contact only.

摘要翻译： 一种完全铰接的直升机转子，其具有弹性体型主轴承，所述弹性体主轴承围绕相交叶片间距变化，牵引滞后和锥形轴线的所有叶片运动反应，包括用于静态和动态操作条件的叶片下垂支撑和限制构件， 单独的叶片运动被排除。 在使这些叶片重量负载和动态推力反应时，下垂构件具体提供全面接触的支承表面，以将大的力从叶片分配到转子毂中，同时避免部件之间的磨损或滚动接触，以及高的承载应力 将由点或线接触产生。

公开(公告)号：US3853426A

公开(公告)日：1974-12-10

申请号：US39282573

申请日：1973-08-29

申请人： UNITED AIRCRAFT CORP

发明人： RYBICKI R

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

CPC分类号： B64C27/35 ,  B64C27/322

摘要： An elastomeric helicopter rotor having a blade mounted by means of an elastomeric bearing for universal motion about the intersection of the blade pitch change, flapping and lead-lag axes and including blade coning and droop stops, including a conical ring member rotatably mounted about the pitch change axis of the blade and coning and droop stops constituting circular segments of conical members whose centers lie on the blade leadlag axes and with the ring member and coning stop and droop stop members presenting mating surfaces to one another so that as the blade moves in lead-lag motion while the blade ring member is in contact with either the coning stop surface or the droop stop surfaces, a relative motion will be established therebetween for full support of the blade throughout the lead-lag motion, without affecting blade pitch angle or flapping angle, without preventing independent blade pitch change and without scuffing of parts. Most importantly, the droop stops are both a dynamic droop stop supported from the hub for limiting blade droop during flight, and a static droop stop supported loosely from and pivotable on said dynamic droop stop, for further limiting blade droop at low rotor speeds or at rotor rest, so that blade loading against said static droop stop will move said static droop stop into engagement with said dynamic droop stop to impart said load directly through both droop stops so engaged into the hub. The loose pivot between the static and dynamic droop stops involves substantial diametral clearance providing for almost frictionless operation of the static droop stop, and causing the blade load to bypass the pivot connection. The looseness of the pivot connection and the shape of the static droop stop will accommodate misalignment between the contacting surfaces. This misalignment, which is allowed by the flexibility of the blade supporting elastomeric bearing, will cause the static droop stop to rotate on the dynamic droop stop and realign itself under load, and provide proper contact rather than corner loading.

公开(公告)号：US2946391A

公开(公告)日：1960-07-26

申请号：US55625255

申请日：1955-12-29

申请人： BOEING CO

发明人： LEMONT JR HAROLD E

IPC分类号： B64C27/32

CPC分类号： B64C27/322