公开(公告)号：WO2022261720A1

公开(公告)日：2022-12-22

申请号：PCT/AU2022/050608

申请日：2022-06-17

Applicant: HYPER Q AEROSPACE HOLDINGS PTY LTD

Inventor： BATTEN, Peter James

IPC: B64C27/10 ,  B64C27/605 ,  B64C27/72 ,  B64C27/80

Abstract: A swashplate assembly for controlling rotor blades of a rotorcraft, comprising a rotating assembly, wherein the rotating assembly is arranged to rotate with the rotor blades about an axis and is coupled to the rotor blades; a base assembly, wherein the base assembly includes a first portion and a second portion, and the rotating assembly is guided by the base assembly to set blade angles of the rotor blades as the rotating assembly rotates with the rotor blades, wherein the second portion is arranged to induce a change in blade angle of the rotor blades.

公开(公告)号：WO2022174998A1

公开(公告)日：2022-08-25

申请号：PCT/EP2022/050739

申请日：2022-01-14

Applicant: ALINA + ERIK GRÄDENER GBR

Inventor： GRÄDENER, Erik

IPC: B64C27/605 ,  B64C27/04 ,  B64C27/64 ,  B64C27/68

Abstract: Anordnung zum Steuern der Blattstellung von Rotorblättem (17) an einem Rotor, enthaltend eine zweiteilige Taumelscheibe (10; 100) mit einem drehenden Teil (12; 112) und einem nicht-drehenden Teil (14; 114), welches über ein Lager (16; 116) mit dem drehenden Teil verbunden ist, wobei der nicht-drehende Teil (14; 114) der Taumelscheibe (10; 100) eine Taumelscheiben-Ebene definiert; Übertragungselemente (18; 118) zur Übertragung von Kräften mittels der Taumelscheibe (10; 100) auf die Rotorblätter (17); (c) eine nicht-drehende Basis (34; 134); Gelenkstangen (28; 110), über welche der nicht-drehende Teil (14; 114) der Taumelscheibe mit der Basis (34; 134) gelenkig verbunden ist und welche eine Neigung der Taumelscheiben-Ebene um wenigstens eine Achse senkrecht zur Drehachse des Rotors erlauben, wobei jede der Gelenkstangen an jeweils einem zugehörigen Verbindungspunkt mit dem nicht-drehenden Teil der Taumelscheibe verbunden ist; und wenigstens einen Antrieb zum Bewegen des nicht-drehenden Teils der Taumelscheibe; ist dadurch gekennzeichnet, dass der Antrieb an einem Angriffspunkt der Anordnung angreift, welcher beabstandet zu dem Verbindungspunkt zwischen dem nicht-drehenden Teil der Taumelscheibe und der Gelenkstange angeordnet ist.

公开(公告)号：WO2021187541A1

公开(公告)日：2021-09-23

申请号：PCT/JP2021/010917

申请日：2021-03-17

Applicant: 日本精工株式会社

Inventor： 熊谷　浩保 ,  郡司　大輔

IPC: B64C27/04 ,  B64C27/605 ,  B64D27/24 ,  F16H19/04 ,  F16H25/22

Abstract: モータで駆動される回転翼のピッチ角を可変としつつ、モータの回転軸の軸方向に推力発生装置をコンパクト化する。　推力発生装置（１）は、回転翼（Ｈ１～Ｈ３）の推力を発生させる推力発生用モータ（２）と、回転翼（Ｈ１～Ｈ３）のピッチ角を変化させる回転運動を発生させるピッチ可変用モータ（５）と、ピッチ可変用モータ（５）の回転運動を直線運動に変換する回転直動変換部（７）と、回転直動変換部（７）で変換された直線運動を回転運動に変換する直動回転変換部（８）とを備え、回転直動変換部（７）の少なくとも一部は、推力発生用モータ（２）内に収容される。

公开(公告)号：WO2021034973A1

公开(公告)日：2021-02-25

申请号：PCT/US2020/047066

申请日：2020-08-19

Applicant: KINETIC ANALYTICS LLC

Inventor： BUELNA, Terry ,  GUPTA, Neil, Rohin

IPC: B64C27/605 ,  B64C27/52 ,  B64C27/54 ,  B64C27/59 ,  B64C27/72 ,  B64C27/10 ,  B64C27/08

Abstract: A blade pitch control system includes a plurality of serially stacked swashplate assemblies, each having concentric, ring-shaped inner and outer sections, an associated output pitch link coupled to its outer section and an associated input pitch link coupled to its inner section. The inner and outer sections of each swashplate assembly includes pass through holes to accommodate input pitch links and output pitch links of adjacent ones of the stacked swashplate assemblies. The system also includes a plurality of actuators, each coupled to a respective input pitch link of a respective one of the stacked swashplate assemblies. A central static mast accommodates a rotor drive shaft and the stacked swashplate assemblies are configured to slide axially, parallel to a long axis of the static mast.

公开(公告)号：WO2020260980A1

公开(公告)日：2020-12-30

申请号：PCT/IB2020/054982

申请日：2020-05-26

Applicant: LEONARDO S.P.A.

Inventor： PODDA, Daniele ,  RUTILIO, Alessandro ,  POGGI, Stefano ,  LOSI, Fabrizio

IPC: B64C27/78 ,  B64C27/605

Abstract: An anti-torque rotor (4) is described comprising: a mast (6) rotatable about a first axis (A); a plurality of blades (8) rotatable about respective second axes (B); an element (16) slidable along the first axis (A) with respect to the mast (6), rotating integrally with the mast (6) and operatively connected to the blades (8); a control rod (10) slidable along axis (A); a first bearing (17) with a first ring (30) rotating integrally with element (16), a second ring (31) radially internal to the first ring (30) with respect to the first axis (A) and a plurality of first rolling bodies (32); a third ring (50) sliding integrally with the control rod (10) along the first axis (A) and angularly fixed with respect to the first axis (A); and a locking element (55) arranged in a standard configuration, in which it prevents the relative rotation of the second and third rings (31, 50) and movable from the standard configuration to at least one emergency configuration, in which it renders the second ring (31) free to rotate with respect to the third ring (50), when the first bearing (17) is in a failure condition.

公开(公告)号：WO2016124795A1

公开(公告)日：2016-08-11

申请号：PCT/EP2016/052654

申请日：2016-02-08

Applicant: VIMAR CREATIVE SA

Inventor： GRIGOLO, Vittorio ,  RIVA, Massimo

IPC: B64C27/605 ,  B64C27/78 ,  A63H27/00

CPC classification number: B64C27/605 ,  A63H27/12 ,  B64C27/78 ,  B64C2201/024

Abstract: The rotor unit(10) for a remote-controlled helicopter (100) comprising a drive shaft (12), a rotor head (30) mounted mobile in rotation with the drive shaft (12), said rotor head (30) comprising a hub (10) and two opposite blade supports (320) mounted in a rotary manner on the hub (310) about a pivoting axis, a control member (20) of the rotor head (30) mounted mobile on the drive shaft (12); a projecting arm (331) associated to each blade support (320), and a stay (330) connected between the projecting arm (331) and the swashplate (20). The rotor unit (10) also comprises a support element (332) pivoted to the stay (330) and to the hub (310) according to a pivoting axis (A4) parallel to the pivoting axis (A3) of the blade supports (320).

Abstract translation: 用于遥控直升机（100）的转子单元（10）包括驱动轴（12），与驱动轴（12）一起旋转安装的转子头（30），所述转子头（30）包括轮毂 （10）和两个相对的叶片支撑件（320），其以旋转方式围绕枢转轴线安装在所述轮毂（310）上;转子头部（30）的控制构件（20）可移动地安装在所述驱动轴（12）上; 与每个叶片支撑件（320）相关联的突出臂（331）和连接在突出臂（331）和斜盘（20）之间的撑杆（330）。 转子单元（10）还包括根据平行于叶片支撑件（320）的枢转轴线（A3）的枢转轴线（A4）枢转到支柱（330）和枢轴（310）的支撑元件（332） ）。

公开(公告)号：WO2014191934A3

公开(公告)日：2015-03-05

申请号：PCT/IB2014061782

申请日：2014-05-28

Applicant: SELEX ES SPA

Inventor： MANETTI VALERIO

IPC: B64C27/20 ,  B64C27/605 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C27/605 ,  B64C39/028 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/162

Abstract: A ducted- fan VTOL aircraft (1) in the mini and micro UAV classes, the aircraft (1) having a toroidal body (2) provided with a first axis (3) extending longitudinally along the toroidal body (2) and defining a fuselage (10) fitted with feet (4) for standing on the ground; the aircraft (1) also having a rotor (33) housed inside the toroidal body (2) and supported by the toroidal body (2), and a motor (9) having an output shaft (18) mounted to rotate the output shaft (18) about the first axis (3),- the rotor (32) being a rigid rotor (33) fitted on the output shaft (18) and equipped with a plurality of blades (42), which are uniformly distributed around the first axis (3), each one having a respective second axis (43) arranged transversally to the first axis (3) and a respective pitch about the respective second axis (43); and, for each blade (42), respective first and second motorized control devices (23, 50) to collectively vary and, respectively, cyclically vary the respective pitch.

Abstract translation: 在迷你和微型无人机类别中的风扇式垂直起降飞机（1），飞行器（1）具有环形体（2），其具有沿着环形体（2）纵向延伸并限定机身的第一轴线（3） （10）装有脚（4），用于站立在地面上; 飞行器（1）还具有容纳在环形体（2）内并由环形体（2）支撑的转子（33），以及具有安装以使输出轴旋转的输出轴（18）的马达（9） 18）围绕第一轴线（3）旋转， - 转子（32）是刚性转子（33），其安装在输出轴（18）上，并配备有多个叶片（42） （3），每个具有横向于所述第一轴线（3）布置的相应的第二轴线（43）和围绕所述相应的第二轴线（43）的相应的间距。 并且对于每个叶片（42），相应的第一和第二电动控制装置（23,50）共同地变化并且分别循环地改变相应的间距。

公开(公告)号：WO2013082853A1

公开(公告)日：2013-06-13

申请号：PCT/CN2012/000375

申请日：2012-03-26

Applicant: 深圳市沈氏彤创航天模型有限公司 ,  沈安平

Inventor： 沈安平

IPC: B64C27/605 ,  A63H27/133

CPC classification number: B64C27/605 ,  A63H27/12 ,  B64C2203/00

Abstract: 一种遥控模型直升机的向位器装置包括倾斜内盘（8），倾斜内盘的球头上连接有一组向位器装置（15），所述向位器装置由中心座（3）、希拉控制臂（4）和拉杆（9）组成，所述中心座同轴设置在倾斜内盘的上端，中心座的上端连接旋翼（16），希拉控制臂套在中心座下端并且通过第一轴套（5）及螺丝连接在中心座上，拉杆轴接在希拉控制臂的前端，拉杆的下端连接倾斜内盘的球头（12），所述遥控模型直升机向位器装置采用一组向位器，减少零件的用量，从而降低了生产成本。

公开(公告)号：WO2009153236A3

公开(公告)日：2010-04-15

申请号：PCT/EP2009057345

申请日：2009-06-15

Applicant: EADS DEUTSCHLAND GMBH ,  CHRISTMANN MARKUS ,  GROHMANN BORIS ,  JAENKER PETER

Inventor： CHRISTMANN MARKUS ,  GROHMANN BORIS ,  JAENKER PETER

IPC: B64C27/605

CPC classification number: B64C27/605

Abstract: Disclosed is a helicopter rotor comprising at least four electromechanical actuators (31-36) for actuating a swash plate (5). The reliability with which the helicopter is controlled is increased by means of redundant actuators.

Abstract translation: 具有用于操作斜板（5），其中，所述直升机控制的可靠性增加冗余的致动器的至少四个elektromechanisehen致动器（31-36）的直升机旋翼。

公开(公告)号：WO03086857A8

公开(公告)日：2004-06-17

申请号：PCT/RU0300156

申请日：2003-04-14

Applicant: OBSCHESTVO S OGRANICHENNOI OTV ,  AKARO ANDREY IGOREVICH ,  DENISOV ANATOLY ALEKSEEVICH ,  ZELINSKY ANATOLY MIKHAILOVICH ,  MEDVEDEV MIKHAIL MIKHAILOVICH

Inventor： AKARO ANDREY IGOREVICH ,  DENISOV ANATOLY ALEKSEEVICH ,  ZELINSKY ANATOLY MIKHAILOVICH ,  MEDVEDEV MIKHAIL MIKHAILOVICH

IPC: B64C39/08 ,  B64C27/08 ,  B64C27/605 ,  B64C39/00 ,  B64C11/46

CPC classification number: B64C39/006 ,  B64C27/08

Abstract: The inventive aerodynamic lifting-thrusting propulsion device comprises a frame (1) provided with an axis (2), said frame (1) being arranged with respect to the axis (2) in such a way that it is rotatable. At least two aerodynamic surfaces (3) are fixed to a fork joint in such a way that they oscillate synchronously with the rotation of the frame (1), the fork joint being fixed to a rod (5) which is arranged on said frame (1). The axis (2) is connected to each aerodynamic surface (3) by means of a mechanical transmission which enables the aerodynamic surface (3) to rotate synchronously and oppositely with respect to the rotation of the frame and the rod (5). The oscillation of the aerodynamic surfaces (3) is carried out by a mechanical copying device. Each aerodynamic surface can rotate around the axes which are parallel to the axes of the spider of the fork joint and pass through the aerodynamic surface (3). The frame (1) and the aerodynamic surfaces (3) rotate around the axis (2) with the aid of a rotary actuator. Each aerodynamic surface (3) synchronously rotates, by means of the mechanical transmission, in a direction opposite the circular motion thereof at an angle velocity which is equal to the angle velocity of said circular motion, whereby producing the progressive motion of the aerodynamic surfaces and regularly distributing aerodynamic forces therethrough. Each aerodynamic surface (3), synchronously with the rotation thereof, oscillates with the aid of the mechanical copying device, thereby producing a horizontal thrust simultaneously with a lifting force.

Abstract translation: 本发明的空气动力提升推进装置包括设置有轴线（2）的框架（1），所述框架（1）相对于轴线（2）以可旋转的方式布置。 至少两个空气动力学表面（3）以与框架（1）的旋转同步地摆动的方式固定到叉形接头，叉接头被固定到布置在所述框架上的杆（5） 1）。 轴线（2）通过机械传动装置连接到每个空气动力学表面（3），这使得空气动力学表面（3）能够相对于框架和杆（5）的旋转同步且相反地旋转。 气动表面（3）的振动由机械复印装置进行。 每个空气动力学表面可以围绕平行于叉接头的蜘蛛的轴的轴线旋转并且穿过空气动力学表面（3）。 借助于旋转致动器，框架（1）和空气动力学表面（3）围绕轴线（2）旋转。 每个空气动力学表面（3）通过机械变速器以与圆周运动的角速度相等的角速度与其圆周运动相反的方向同步旋转，从而产生空气动力学表面的逐渐运动， 定期分布空气动力。 每个空气动力学表面（3）与其旋转同步，借助于机械复制装置振荡，从而与提升力同时产生水平推力。