公开(公告)号：US20130149149A1

公开(公告)日：2013-06-13

申请号：US13693192

申请日：2012-12-04

申请人： EUROCOPTER

发明人： Jean Mondet

IPC分类号： B64C27/57

CPC分类号： B64C27/57 ,  B64C27/322

摘要： An abutment mechanism for limiting the flapping of the blades of a rotor (1). High abutment members (6) can be moved into an engagement position by return means (13) exerting an intrinsic return force (R), and into a disengagement position by a flyweight (10) exerting a centrifugal force (C) under the effect of the rotor (1) rotating. At least one magnetic type bistable latch (15) is in selective engagement with the high abutment members (6). When the rotor (1) is stationary and while it is starting to rotate, an engagement latch (15) engages with the high abutment member (6) to prevent it passing from the engagement position towards the disengagement position. At a predetermined centrifugal force threshold, the engagement of the engagement latch (15) with the high abutment member (6) is broken, and the high abutment member (6) quickly passes into the disengagement position.

摘要翻译： 一种用于限制转子（1）的叶片振动的邻接机构。 高抵靠构件（6）可以通过施加固有返回力（R）的返回装置（13）移动到接合位置，并且通过施加离心力（C）的飞重（10）进入分离位置​​， 转子（1）旋转。 至少一个磁性双稳态闩锁（15）与高抵靠构件（6）选择性地接合。 当转子（1）处于静止状态并且当其开始旋转时，接合闩锁（15）与高抵靠构件（6）接合，以防止其从接合位置向分离位置移动。 在预定的离心力阈值下，接合闩锁（15）与高抵靠构件（6）的接合被破坏，并且高抵靠构件（6）快速进入分离位置​​。

公开(公告)号：US07448855B2

公开(公告)日：2008-11-11

申请号：US11356498

申请日：2006-02-17

申请人： Steven R. Carbaugh ,  Steven J. Spear

发明人： Steven R. Carbaugh ,  Steven J. Spear

IPC分类号： B64C27/39

CPC分类号： B64C27/322

摘要： A droop stop mechanism for a helicopter rotor blade includes a pair of opposing stops disposed on opposite sides of the blade's flap hinge. An interposer is mounted at the end of an arm on a rotatable shaft for rotation in a plane perpendicular to the hinge. A torsion spring disposed concentrically about the shaft has a first end that is fixed and a second end coupled to the shaft to bias the interposer to a position disposed between the stops, thereby limiting blade droop. A weight is attached to the shaft such that, with rotation of the rotor, centrifugal forces acting on the weight cause the shaft and arm to rotate so as to overcome the bias of the spring and urge the interposer out from between the stops, thereby allowing greater blade droop. The spring and shaft are sealed in a canister for protection from the elements.

摘要翻译： 用于直升机转子叶片的下垂停止机构包括设置在叶片翼片铰链的相对侧上的一对相对的挡块。 插入器安装在臂的端部在可旋转轴上，以在垂直于铰链的平面中旋转。 围绕轴同心设置的扭转弹簧具有固定的第一端和联接到轴的第二端，以将插入件偏置到设置在止动件之间的位置，从而限制叶片下垂。 重物附接到轴，使得随着转子的旋转，作用在重物上的离心力使轴和臂旋转，以克服弹簧的偏压并将插入件从止动件之间推出，从而允许 更大的叶片下垂。 弹簧和轴被密封在罐中以保护元件。

公开(公告)号：US20070086894A1

公开(公告)日：2007-04-19

申请号：US11251732

申请日：2005-10-17

申请人： David Zinni

发明人： David Zinni

IPC分类号： B64C27/50

CPC分类号： B64C27/322 ,  F16F1/3835 ,  F16F1/387 ,  F16F1/40 ,  F16F2236/123

摘要： An elastomeric bearing element having an outer race, an inner race, and at least two elastomeric segments secured between the inner and outer races is provided. The elastomeric segments are spaced from one another by a corresponding number of expansion segments. The elastomeric segments provide a first spring rate when a first force applied to the outer race places the elastomeric segments in compression and a second spring rate when a second force applied to the outer race places the elastomeric segments in shear. The second spring rate is lower than the first spring rate.

摘要翻译： 提供了一种具有外座圈，内座圈和固定在内座圈和外座圈之间的至少两个弹性片段的弹性轴承元件。 弹性片段彼此间隔开相应数量的扩张段。 当施加到外圈上的第一力使弹性体段处于压缩状态时，弹性片段提供第一弹簧刚度，而当施加到外圈上的第二力使弹性片段处于剪切状态时，弹性片段提供第二弹簧刚度。 第二弹簧率低于第一春弹率。

公开(公告)号：US06203277B1

公开(公告)日：2001-03-20

申请号：US09242218

申请日：1999-05-12

申请人： Philippe Maurice René Legendre ,  Etienne Jean Rampal

发明人： Philippe Maurice René Legendre ,  Etienne Jean Rampal

IPC分类号： B63H300

CPC分类号： B64C27/322

摘要： A rotorcraft, in particular helicopter, rotor includes a tubular pylon driven in rotation about its axis, which is the rotation axis of the rotor, from its foot. A hub is attached to the pylon by a flared base and includes two annular plates substantially radial to the rotor axis and spaced from each other along the rotor axis so that relative to the pylon one is an axially inside plate and the other is an axially outside plate. Each of at least two blades has its root connected to the hub by retaining and articulation arrangements retained between the plates of the hub and enabling relative angular movement of the blade at least in pitch about a longitudinal blade pitch change axis controlled by displacement by a pitch rod of a pitch lever attached to the blade root. The base has lateral openings through which pass arms of a pitch control plate which rotates with the hub and is mobile at least axially in the base, the end of each arm, outside the base, being articulated to one end of a pitch rod articulated at the other end to the pitch lever of a respective rotor blade.

摘要翻译： 旋翼航空器，特别是直升机，转子包括从其轴线旋转的管状塔架，其作为转子的旋转轴线从其轴线旋转。 轮毂通过喇叭形底座附接到塔架，并且包括两个基本上径向于转子轴线的环形板，并且沿着转子轴线彼此间隔开，使得相对于塔架是轴向内侧板，而另一个是轴向外侧 盘子。 至少两个叶片中的每一个叶片的根部通过保持在轮毂的板之间的保持和铰接装置而连接到轮毂，并且使叶片能够至少以俯仰为基础的纵向叶片间距变化轴线的间距相对角度运动 连接到叶片根部的俯仰杆的杆。 底座具有横向开口，通过该侧开口，桨距控制板的臂与轮毂一起旋转，并且在底座中至少轴向移动，每个臂的端部在基座外侧铰接到铰接在 另一端连接到相应转子叶片的俯仰杆上。

公开(公告)号：US5820341A

公开(公告)日：1998-10-13

申请号：US758790

申请日：1996-12-03

申请人： Jean Joseph Henri Mondet ,  Sylvie Jacqueline Garcin

发明人： Jean Joseph Henri Mondet ,  Sylvie Jacqueline Garcin

IPC分类号： B64C27/32 ,  B64C27/51

CPC分类号： B64C27/322

摘要： The device includes anti-cone stops projecting outward from at least two coaxial rings that can rotate about the rotor axis on the top face of the hub. Flyweights are each mechanically joined to one of the rings by a mechanism for driving the latter in rotation from the "ground" position, in which each anti-cone stop is facing an upper bearing shoe of the corresponding blade, to the "flight" position, in which the anti-cone stops are retracted against elastic mechanisms returning them to the "ground" position.

摘要翻译： 该装置包括从至少两个同轴环向外突出的防锥形止动件，所述至少两个同轴环可围绕毂的顶面上的转子轴线旋转。 飞行器通过机构将机身连接到其中一个环上，该机构用于将后者从“接地”位置旋转驱动，其中每个防锥止动器面向相应叶片的上轴承座，到达“飞行”位置 ，其中防锥形止挡件使弹性机构退回到“接地”位置。

公开(公告)号：US4737075A

公开(公告)日：1988-04-12

申请号：US885996

申请日：1986-07-16

申请人： Jean-Luc Leman ,  Bruno Guimbal

发明人： Jean-Luc Leman ,  Bruno Guimbal

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

CPC分类号： B64C27/322

摘要： The flapping stop device of the invention is intended for a gyroplane rotor comprising a hub (3) to which each blade (22) is connected by retaining and pivoting members (16) having two frames, one (17) of which is fixed to the hub (3) and the other (19) of which, in an internal radial position with respect to the first one, is locked for movement with the root (23) of the blade (22). The internal frame (19) has, projecting radially inwardly, at least one nose piece (29) having a stop surface and defining a convex cylindrical sliding surface (28) on the internal radial face of the frame (19). The nose piece or pieces (29) and the convex surface (28) cooperate respectively with one or more bearing surfaces (34) and a complementary concave surface (33) of a central stop (30) integral with the hub (3) or with the rotor mast (2).

摘要翻译： 本发明的颤动停止装置用于包括轮毂（3）的陀螺仪转子，所述轮毂（3）通过具有两个框架的保持和枢转构件（16）连接每个叶片（22），其中一个（17）固定到 轮毂（3）和另一个（19）在相对于第一个的内部径向位置被锁定以与叶片（22）的根部（23）一起运动。 内部框架（19）具有径向向内突出的至少一个具有止动表面并且在框架（19）的内部径向表面上限定凸形圆柱形滑动表面（28）的鼻部件（29）。 鼻部件（29）和凸形表面（28）分别与一个或多个轴承表面（34）和与毂（3）成一体的中心止动件（30）的互补凹面（33）配合，或与 转子桅杆（2）。

公开(公告)号：US4549852A

公开(公告)日：1985-10-29

申请号：US562056

申请日：1983-12-16

申请人： Edward S. Hibyan

发明人： Edward S. Hibyan

IPC分类号： B64C27/32

CPC分类号： B64C27/322

摘要： Apparatus for supporting the rotor blades of a helicopter is disclosed. Support in droop under both statically and dynamically loaded conditions is discussed. The droop stop mechanism 34 has low susceptibility to the deleterious effects of snow/ice or dirt contamination. The droop stop seat 42 is mounted for rotation in a corresponding receptacle 50 at the base of the rotor blade assembly 14 and is slidable between static stop and dynamic stop positions along the pitch axis of the blade to be supported.

摘要翻译： 公开了一种用于支撑直升机的转子叶片的装置。 讨论了在静态和动态加载条件下的下垂支持。 下垂停止机构34对雪/冰或污物污染的有害影响的敏感性低。 下垂停止座42被安装成转动在转子叶片组件14的底部处的对应的容器50中，并且可沿着待支撑的叶片的俯仰轴线的静态停止位置和动态停止位置之间滑动。

公开(公告)号：US4516909A

公开(公告)日：1985-05-14

申请号：US471344

申请日：1983-03-02

申请人： Vittorio Caramaschi ,  Pier Luigi Castelli

发明人： Vittorio Caramaschi ,  Pier Luigi Castelli

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

CPC分类号： B64C27/322 ,  B64C27/35

摘要： A helicopter rotor in which a central plate-like hub is provided with a plurality of axial apertures uniformly distributed around a central axis of rotation and each defined radially outwardly by a supporting peripheral bridge connected to a respective blade by a U-shape structure extending through the said aperture and coupled to the associated bridge by an elastomeric coupling; each U-shape structure being coupled to a respective radial projection of the hub by a further elastomeric coupling.

摘要翻译： 一种直升机转子，其中中央板状轮毂设置有围绕中心旋转轴线均匀分布的多个轴向孔，并且每个径向向外由通过延伸穿过的U形结构连接到相应叶片的支撑周向桥限定 所述孔并通过弹性体联接器联接到相关联的桥上; 每个U形结构通过另外的弹性体联接件联接到轮毂的相应的径向突起。

公开(公告)号：US3778189A

公开(公告)日：1973-12-11

申请号：US3778189D

申请日：1972-09-05

申请人： UNITED AIRCRAFT CORP

发明人： FERRIS D

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 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 ring member rotatably mounted about the pitch change axis on the blade and coning and droop stops constituting segments of circular members whose centers lie on the blade lead-lag 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 line or surface mating contact with either the coning stop surface or the static or dynamic droop stop surfaces, a relative rotation 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.

摘要翻译： 一种弹性直升机转子，其具有安装成用于围绕叶片俯仰变化，扑动和牵引滞后轴线的相交的通用运动的叶片，并且包括叶片锥形和下降停止点，包括围绕叶片上的俯仰变化轴线可旋转地安装的环形构件 并且下垂停止构成中心位于叶片前后轴上的圆形构件的段，并且环形构件和锥形停止和下垂停止构件彼此呈现配合表面，使得当叶片以超前滞后运动移动时，叶片 环形构件与锥形停止表面或静态或动态下垂停止面处于直线或表面配合接触，将在其间建立相对旋转，以在整个超前滞后运动中完全支撑叶片，而不影响叶片俯仰角或 拍打角度，而不会防止独立的叶片间距变化，并且不会磨损零件。

公开(公告)号：US2719593A

公开(公告)日：1955-10-04

申请号：US34046953

申请日：1953-03-05

申请人： UNITED AIRCRAFT CORP

发明人： ALEX RALPH P

IPC分类号： B64C27/32

CPC分类号： B64C27/322