公开(公告)号：WO2008045011A3

公开(公告)日：2009-03-12

申请号：PCT/US2006019388

申请日：2006-05-19

Applicant: BELL HELICOPTER TEXTRON INC ,  RAUBER RICHARD ,  STAMPS FRANK B ,  BRASWELL JAMES LEE JR

Inventor： RAUBER RICHARD ,  STAMPS FRANK B ,  BRASWELL JAMES LEE JR

IPC: B64C27/22

CPC classification number: B64C27/41 ,  B64C27/52 ,  B64C29/0033 ,  F16C1/04

Abstract: A constant-velocity drive system for a rotary-wing aircraft rotor comprising a differential torque-splitting mechanism and a gimbal mechanism is disclosed. A rotary-wing aircraft having a rotary-wing aircraft rotor comprising a differential torque- splitting mechanism and a gimbal mechanism is disclosed.

Abstract translation: 公开了一种用于包括差动扭矩分离机构和万向节机构的旋翼飞机转子的恒速驱动系统。 公开了一种旋转翼飞行器，其具有包括差动扭矩分离机构和万向节机构的旋翼飞行器转子。

公开(公告)号：WO2014149511A1

公开(公告)日：2014-09-25

申请号：PCT/US2014/019143

申请日：2014-02-27

Applicant: CUPP, John Neal, Jr. ,  CUPP, Karen

Inventor： CUPP, John Neal, Jr.

IPC: B64C27/39

CPC classification number: B64C27/025 ,  A63H27/12 ,  B64C27/39 ,  B64C27/41 ,  B64C27/52 ,  B64C27/54

Abstract: A helicopter main rotor control system includes a trunnion head mountable to a rotatable helicopter mast wherein the trunnion head has a control bar pivot supported by the trunnion head and pivotal about an axis substantially at a right angle to the helicopter mast. A control bar extends through the control bar pivot at a right angle thereto, and a pair of opposing leaf hinges are pivotal about the control bar and centered about said trunnion head. Each leaf hinge has a hinge plate extending from the control bar and defines a rotor blade mount hole therethrough.

Abstract translation: 直升机主转子控制系统包括可安装到可旋转的直升机桅杆的耳轴头，其中耳轴头具有由耳轴头支撑的控制杆枢轴，并且围绕基本上与直升机桅杆成直角的轴线枢转。 控制杆以与其成直角的方式延伸穿过控制杆枢轴，并且一对相对的叶片铰链围绕控制杆枢转并围绕所述耳轴头居中。 每个叶铰链具有从控制杆延伸的铰链板并且限定通过其中的转子叶片安装孔。

公开(公告)号：WO2013061348A1

公开(公告)日：2013-05-02

申请号：PCT/IT2012/000322

申请日：2012-10-23

Applicant: K4A S.R.L.

Inventor： LIDAK, Vladimiro

IPC: B64C27/37

CPC classification number: F16D3/30 ,  B64C27/41 ,  Y10S464/905

Abstract: The invention relates to a constant velocity universal joint for each type of transmission and in particular for helicopters with rotors called gimballed, in which the hub (2) of a rotor equipped with blades (7) is supported on a transmission shaft (1), said "mast", by means of a cardan's suspension composed of two concentric rings ( 5A and 5B), a first inner ring (5A) has a revolute connection to two opposite pins (31) of the carrier (3) connected to transmission shaft (1) and a second outer ring (5B) has a revolute connection to two opposite pins (22) of the hub (2).The two concentric rings are also interconnected by a pair of swivel opposite pins (542), in quadrature with respect to the pins (31) connected to the transmission shaft and to the pins (22) of the hub, whose common axis (00) is stably maintained in a plane, said homokinetic, which bisects the angle between the axis of rotation of the hub (2) and the axis of rotation of the transmission shaft (1), by means of at least one (but preferably two) devices (6), original and improved, said bisectors, which are connected both to the transmission shaft and to hub, thus obtaining a homokinetic transmission of rotational motion between said transmission shaft (1) and said hub (2), to which the blades (7) are fixed irrespective of the angle of inclination the hub assumes with respect to the drive shaft.

Abstract translation: 本发明涉及用于每种传动装置的等速万向节，尤其涉及具有称为金枪球的转子的直升机，其中装有叶片（7）的转子的轮毂（2）支撑在传动轴（1）上， 所述“桅杆”通过由两个同心环（5A和5B）组成的万向节悬架，第一内环（5A）具有与连接到传动轴（3）的载体（3）的两个相对的销（31）的旋转连接 （1）和第二外圈（5B）具有与轮毂（2）的两个相对的销（22）的旋转连接。两个同心环也通过一对旋转相对的销（542）互连，与 相对于连接到传动轴的销（31）和其公共轴（00）稳定地保持在平面中的轮毂的销（22），所述同轴动力学将所述等轴旋转的轴线 轮毂（2）和传动轴（1）的旋转轴线通过至少一个 （但优选两个）装置（6），原始和改进的，所述二等分线连接到传动轴和轮毂，从而获得在所述传动轴（1）和所述轮毂（2）之间的旋转运动的同动力传递， ，叶片（7）固定在其上，而不管轮毂相对于驱动轴的倾斜角度如何。

公开(公告)号：WO2013060318A1

公开(公告)日：2013-05-02

申请号：PCT/DE2012/001021

申请日：2012-10-20

Applicant: EADS DEUTSCHLAND GMBH

Inventor： HIEBL, Manfred ,  PONGRATZ, Hans Wolfgang

IPC: B64C3/30 ,  B64C39/02

CPC classification number: B64C39/02 ,  B64C3/30 ,  B64C9/00 ,  B64C27/41 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/105 ,  B64C2201/122 ,  B64C2201/165 ,  B64D39/00 ,  B64D2041/005 ,  B64D2211/00 ,  Y02T90/36

Abstract: Ein unbemanntes Höhenluftfahrzeug, insbesondere Stratosphären-Luftfahrzeug, mit zumindest einem Rumpf (10), Tragflügeln (13, 14), Steuerflächen (13", 14", 20', 20", 21 ', 21") und zumindest einer Antriebseinrichtung (15, 16, 17), die zumindest eine Antriebsmaschine und zumindest einen Propeller (15', 16', 17') aufweist, zeichnet sich dadurch aus, dass der jeweilige Tragflügel (13, 14) eine Mehrzahl von sich in einer Richtung quer, vorzugsweise rechtwinklig, zur Rumpflängsachse (Z) erstreckenden Flügelholmen (46', 46") und Schläuchen (40, 41, 42, 43, 44) aufweist, die von einer eine Flügelbespannung (45) bildenden Haut umgeben sind, welche die Querschnittskontur des Tragflügels bestimmt, wobei die Querschnittskontur ein Laminarprofil bildet, das bei geringem Strömungswiderstand einen hohen Auftrieb erzeugt; dass der jeweilige Tragflügel (13, 14) an seinem vom Rumpf (10) abgewandten freien Ende mit einem sich quer zur Tragflügellängsachse erstreckenden Winglet (13', 14') versehen ist und dass das Winglet (13', 14') mit einer bewegbaren Steuerfläche (13", 14") versehen ist, die die Erzeugung einer aerodynamischen Seitenkraft ermöglicht, um das Luftfahrzeug in eine Schrägrolllage zu bringen.

Abstract translation: 无人驾驶高空的飞机，特别是平流层飞行器，具有至少一个主体（10），翼片（13，14），凸轮表面（13”，14" ，20”，20”，21' ，21" ）和至少一个驱动装置（15 ，16，其具有至少一个驱动机和至少一个推进器（15“ 16' ，17”）17），其特征在于，相应的翼（13，14）具有多个横向的本身在一个方向上，优选 直角，以延伸护翼构件机身纵向轴线（Z）（46”，46“）和管（40，41，42，43，44），一个翼覆盖的形成（45）皮肤包围，这决定了机翼的横截面轮廓 其中，所述横截面轮廓形成了一个层流分布，这产生在低流动阻力的高扬程，即面向远离机身各翼（13，14）（10）的自由端具有横向延伸到翼型件纵向轴线的小翼（13”，14' ）已经 rsehen并且所述小翼（13”，14' ）上设置有可移动的控制表面（13”，14" ），这使得空气动力学侧力的产生，使飞机在倾斜辊的位置。

公开(公告)号：WO2009088495A1

公开(公告)日：2009-07-16

申请号：PCT/US2008/050213

申请日：2008-01-04

Applicant: BELL HELICOPTER TEXTRON INC. ,  STAMPS, Frank, B. ,  TISDALE, Patrick, R.

Inventor： STAMPS, Frank, B. ,  TISDALE, Patrick, R.

IPC: B64C27/00

CPC classification number: B64C29/0033 ,  B64C27/32 ,  B64C27/41 ,  B64C2027/125 ,  F16D3/33 ,  Y10S464/904

Abstract: A constant-velocity drive system for an aircraft rotor has a gimbal mechanism and a differential torque-combining mechanism. The gimbal mechanism has gimbals driven in rotation by a rotor mast about a mast axis, the gimbals providing for gimballing relative to the mast about gimbal axes generally perpendicular to the mast axis. The differential torque-combining mechanism is connected to the gimbal mechanism and configured to be driven in rotation about the mast axis by the gimbal mechanism. The differential mechanism is capable of gimballing relative to the mast about the gimbal axes, the differential torque-combining mechanism having an output component attached to a yoke of the rotor for driving the yoke in rotation with the differential torque- combining mechanism.

Abstract translation: 用于飞行器转子的恒速驱动系统具有万向节机构和差动转矩组合机构。 万向节机构具有围绕桅杆轴线的转子桅杆旋转驱动的万向节，所述万向架相对于桅杆提供关于通常垂直于桅杆轴线的万向轴线的槌球。 差速转矩组合机构连接到万向节机构，并且构造成通过万向节机构围绕桅杆轴线旋转。 该差速机构能够相对于桅杆围绕万向轴进行槌球，该差速扭矩组合机构具有附接到转子的轭的输出部件，用于通过差速转矩组合机构来旋转该轭。

公开(公告)号：WO1987004402A1

公开(公告)日：1987-07-30

申请号：PCT/US1987000091

申请日：1987-01-14

Applicant: ROMAN, Stephan

IPC: B64C27/35

CPC classification number: B64C27/41

Abstract: A bladed aircraft rotor (13) having blades (12) mounted by means of flexible devices (19) providing freedom for blade motions, at least in the flapping sense and in the pitch-change sense, without employment of flapping or pitch bearings or pivots, the rotor also being provided with a central bearingless joint (39) for transmitting thrust forces while providing freedom for angular movement of the rotor as a whole about a center point on the axis of rotation. A constant velocity torque-transmitting system (42-42) is also provided.

公开(公告)号：WO2016118980A4

公开(公告)日：2017-02-02

申请号：PCT/ZA2016000002

申请日：2016-01-13

Applicant: GROENEWALD FELIX ERROL

Inventor： GROENEWALD FELIX ERROL

IPC: B64C27/52 ,  B64C27/32

CPC classification number: B64C27/41 ,  B64C27/12 ,  B64C27/32 ,  B64C27/52 ,  B64C27/605

Abstract: A helicopter with a rotor pivotally connected to a shaft by a universal joint or bail and socket joint. The helicopter Includes: a fuselage; a rotor mast that is fixed against relative rotation with respect to the fuselage; at least one blade; a motor for rotating the at least one blade; and a universal joint or ball and socket joint. The universal joint or bail and socket joint: (i) is disposed between the at least one blade and the rotor mast, with the at least one blade being rotatable relative to the universal joint or ball and socket joint; (ii) is disposed between the motor and the rotor mast; and (iii) is fixed against relative rotation with respect to the rotor mast, such that, pivoting of the universal joint or ball and socket joint causes the at least one blade and the motor to tilt.

Abstract translation: 具有转子的直升机通过万向接头或吊环和插座接头枢转地连接到轴。 直升机包括：机身; 转子桅杆相对于机身相对旋转固定; 至少一个叶片; 用于旋转所述至少一个叶片的马达; 和万向节或球窝接头。 所述万向接头或吊钩和接头接头：（i）设置在所述至少一个叶片和所述转子桅杆之间，所述至少一个叶片可相对于万向接头或球窝接头旋转; （ii）设置在电动机和转子桅杆之间; 和（iii）相对于转子桅杆的相对旋转固定，使得万向接头或球窝接头的枢转使至少一个叶片和电动机倾斜。

公开(公告)号：WO2016118980A2

公开(公告)日：2016-07-28

申请号：PCT/ZA2016/000002

申请日：2016-01-13

Applicant: GROENEWALD, Felix, Errol

Inventor： GROENEWALD, Felix, Errol

IPC: B64C27/32

CPC classification number: B64C27/41 ,  B64C27/12 ,  B64C27/32 ,  B64C27/52 ,  B64C27/605

Abstract: A helicopter with a rotor pivotally connected to a shaft by a universal joint or bail and socket joint. The helicopter Includes: a fuselage; a rotor mast that is fixed against relative rotation with respect to the fuselage; at least one blade; a motor for rotating the at least one blade; and a universal joint or ball and socket joint. The universal joint or bail and socket joint: (i) is disposed between the at least one blade and the rotor mast, with the at least one blade being rotatable relative to the universal joint or ball and socket joint; (ii) is disposed between the motor and the rotor mast; and (iii) is fixed against relative rotation with respect to the rotor mast, such that, pivoting of the universal joint or ball and socket joint causes the at least one blade and the motor to tilt.

Abstract translation: 具有转子的直升机通过万向接头或吊环和插座接头枢转地连接到轴。 直升机包括：机身; 转子桅杆相对于机身相对旋转固定; 至少一个叶片; 用于旋转所述至少一个叶片的马达; 和万向节或球窝接头。 所述万向接头或吊钩和接头接头：（i）设置在所述至少一个叶片和所述转子桅杆之间，所述至少一个叶片可相对于万向接头或球窝接头旋转; （ii）设置在电动机和转子桅杆之间; 和（iii）相对于转子桅杆的相对旋转固定，使得万向接头或球窝接头的枢转使至少一个叶片和电动机倾斜。

公开(公告)号：WO2010128378A3

公开(公告)日：2011-01-20

申请号：PCT/IB2010001037

申请日：2010-05-05

Applicant: K4A S R L ,  LIDAK VLADIMIRO

Inventor： LIDAK VLADIMIRO

IPC: B64C27/35 ,  B64C27/41

CPC classification number: B64C27/41 ,  B64C27/35 ,  F16D3/28 ,  F16D3/30 ,  F16D3/70

Abstract: The invention concerns a constant velocity joint for gimballed helicopter rotors in which the rotor hub (2) is connected to a drive shaft (mast) (1) by means of two opposing elastomeric laminated spherical bearings (4), which allow the said rotor hub to tilt on two axes, and whose upper and lower supports are located at the opposite ends of a horizontal cavity of the hub, inside which a series of improved elastomeric dragging devices have been installed (5) that are identical to each other and which are composed of spherical bearings to which are secured - externally and internally - two elastomeric cylindrical radially laminated bearings which slide elastically on their axis, such bearings being of different sizes but, at the same time, being also characterized by the fact that they have the same longitudinal rigidity. The external bearings of these devices are lodged in appropriate annular apertures which are arranged on a flange (3) secured to the mast, whereas the bearings that are inside the couplings are secured, by means of feathering bolts (6), to the hollow rotor hub (2). The rotor hub tilts relative to the mast also on account of the spherical couplings of the aforementioned dragging devices, whose centers - thanks to the identical rigidity of both elastomeric cylindrical bearings connected thereto - are arranged on a plane which bisects the angle between the mast flange and the rotor hub, thus creating a constant- velocity joint. This type of constant-velocity joint is used in a two- blade helicopter rotor and is also used in three-blade and multi-blade helicopter rotors in general. It is, moreover, used - in the event that constant-velocity joints are required - in generic appliances for the transmission of motion between two masts tilting towards each other.

Abstract translation: 本发明涉及一种用于微型直升机转子的恒速接头，其中转子轮毂（2）通过两个相对的弹性体层压球面轴承（4）连接到驱动轴（桅杆）（1），其允许所述转子毂 在两个轴上倾斜，并且其上和下支撑件位于轮毂的水平空腔的相对端处，其中已经安装了一系列改进的弹性拖动装置（5），其彼此相同，并且其中 由外部和内部固定的两个弹性圆柱形径向层压轴承组成的球面轴承，这些轴承在其轴线上弹性滑动，这种轴承具有不同的尺寸，但同时其特征还在于它们具有相同的 纵向刚度。 这些装置的外部轴承被放置在适当的环形孔中，该环形孔布置在固定到桅杆上的凸缘（3）上，而联轴器内部的轴承通过刨花螺栓（6）固定到中空转子 枢纽（2）。 由于上述牵引装置的球形联轴器，转子毂相对于桅杆倾斜，其中心 - 由于与其连接的两个弹性圆柱形轴承的刚度相同的刚度被布置在平面上，平面将桅杆法兰 和转子毂，从而形成恒速接头。 这种类型的等速接头用于双叶直升机转子中，并且一般也用于三叶片和多叶片直升机转子中。 此外，在需要等速接头的情况下，在用于彼此倾斜的两个桅杆之间的运动传递的通用装置中，还使用它。

公开(公告)号：WO2010128378A2

公开(公告)日：2010-11-11

申请号：PCT/IB2010/001037

申请日：2010-05-05

Applicant: K4A S.R.L. ,  LIDAK, Vladimiro

Inventor： LIDAK, Vladimiro

IPC: B64C27/35

CPC classification number: B64C27/41 ,  B64C27/35 ,  F16D3/28 ,  F16D3/30 ,  F16D3/70

Abstract: The invention concerns a constant velocity joint for gimballed helicopter rotors in which the rotor hub (2) is connected to a drive shaft (mast) (1) by means of two opposing elastomeric laminated spherical bearings (4), which allow the said rotor hub to tilt on two axes, and whose upper and lower supports are located at the opposite ends of a horizontal cavity of the hub, inside which a series of improved elastomeric dragging devices have been installed (5) that are identical to each other and which are composed of spherical bearings to which are secured - externally and internally - two elastomeric cylindrical radially laminated bearings which slide elastically on their axis, such bearings being of different sizes but, at the same time, being also characterized by the fact that they have the same longitudinal rigidity. The external bearings of these devices are lodged in appropriate annular apertures which are arranged on a flange (3) secured to the mast, whereas the bearings that are inside the couplings are secured, by means of feathering bolts (6), to the hollow rotor hub (2). The rotor hub tilts relative to the mast also on account of the spherical couplings of the aforementioned dragging devices, whose centers - thanks to the identical rigidity of both elastomeric cylindrical bearings connected thereto - are arranged on a plane which bisects the angle between the mast flange and the rotor hub, thus creating a constant- velocity joint. This type of constant-velocity joint is used in a two- blade helicopter rotor and is also used in three-blade and multi-blade helicopter rotors in general. It is, moreover, used - in the event that constant-velocity joints are required - in generic appliances for the transmission of motion between two masts tilting towards each other.

Abstract translation: 本发明涉及一种用于微型直升机转子的恒速接头，其中转子轮毂（2）通过两个相对的弹性体层压球面轴承（4）连接到驱动轴（桅杆）（1），其允许所述转子毂 在两个轴上倾斜，并且其上和下支撑件位于轮毂的水平空腔的相对端处，其中已经安装了一系列改进的弹性拖动装置（5），其彼此相同，并且其中 由外部和内部固定的两个弹性圆柱形径向层压轴承组成的球面轴承，这些轴承在其轴线上弹性滑动，这种轴承具有不同的尺寸，但同时其特征还在于它们具有相同的 纵向刚度。 这些装置的外部轴承被放置在适当的环形孔中，该环形孔布置在固定到桅杆上的凸缘（3）上，而联轴器内部的轴承通过刨花螺栓（6）固定到中空转子 枢纽（2）。 由于上述牵引装置的球形联轴器，转子毂相对于桅杆倾斜，其中心 - 由于与其连接的两个弹性圆柱形轴承的刚度相同的刚度被布置在平面上，平面将桅杆法兰 和转子毂，从而形成恒速接头。 这种类型的等速接头用于双叶直升机转子中，并且一般也用于三叶片和多叶片直升机转子中。 此外，在需要等速接头的情况下，在用于彼此倾斜的两个桅杆之间的运动传递的通用装置中，还使用它。