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    Système de commandes de vol simplifiées comportant un dispositif de friction débrayable
    22.
    发明公开
    Système de commandes de vol simplifiées comportant un dispositif de friction débrayable 有权
    Vereinfachtes Flugsteuerungssystem mitausrückbarerKupplungsvorrichtung

    公开(公告)号：EP2384969A2

    公开(公告)日：2011-11-09

    申请号：EP11003320.6

    申请日：2011-04-20

    申请人： EUROCOPTER

    发明人： Leguay, Pascal ,  Carlavan, Cédric

    IPC分类号： B64C13/10 ,  B64C27/56 ,  B64C27/59 ,  G05D1/08 ,  G05G5/03 ,  G05G5/22

    CPC分类号： B64C13/10 ,  B64C13/30 ,  B64C27/59 ,  G05G5/08 ,  G05G5/22 ,  Y02T50/44

    摘要： La présente invention concerne un dispositif de friction (11) pour maintenir dans une position déterminée un organe de commande (2,8) comportant :
    - une pièce de contact (16) mobile entre une position stable débrayée et une position stable embrayée et inversement, ladite position stable embrayée correspondant à une position dans laquelle la pièce de contact (16) est en appui sur l'organe de commande (2,8) de manière à établir une force de friction déterminée,
    - des moyens d'entraînement pour déplacer la pièce de contact (16) entre les deux positions stables,

    caractérisé en ce qu'il comprend un moyen de commande à distance pour activer et désactiver les moyens d'entraînement.

    摘要翻译： 装置（11）具有接触件（16），该接触件在已解除的稳定位置和离合的稳定位置之间移动，反之亦然。 离合器的稳定位置对应于这样的位置，其中接触片以这样的方式支撑在飞行器的手动控制单元（2）即循环棒上，以便建立确定的摩擦力。 机电驱动单元将接触片移动到已解除的和离合的稳定位置之间，并且远程控制单元（14）激活和停用驱动单元。 还包括用于简化的自动控制系统的独立权利要求，其包括作用在飞行器的控制轴上的手动控制单元。

    A CYCLIC PITCH ANGLE ADJUSTMENT APPARATUS
    26.
    发明公开
    A CYCLIC PITCH ANGLE ADJUSTMENT APPARATUS 审中-公开

    公开(公告)号：EP4086171A1

    公开(公告)日：2022-11-09

    申请号：EP21400009.3

    申请日：2021-05-05

    申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH

    发明人： Czech, Ian-Luca

    IPC分类号： B64C27/54 ,  B64C27/59 ,  B64C27/72

    摘要： The present embodiments relate to a cyclic pitch angle adjustment apparatus 200 for a rotor 110 or propeller, to a rotor 110 with such a cyclic pitch angle adjustment apparatus 200, and to a rotorcraft 100 with such a rotor 110. The cyclic pitch angle adjustment apparatus 200 includes levers 230a, 230b that rotate rotor blades 212a, 212b around associated pitch axes 235a, 235b, rods 240a, 240b that mechanically link the levers 230a, 230b with a bearing 220 such that the rods 240a, 240b are movable relative to a central point 223, the bearing 220 being attached to a central rod 250 that is movable and adapted for adjusting the cyclic pitch angle of the rotor blades 112 from one pitch angle in one position to another pitch angle in another position 265.

    REDUNDANT HELICOPTER PITCH CHANGE BEARING
    28.
    发明公开
    REDUNDANT HELICOPTER PITCH CHANGE BEARING 审中-公开

    公开(公告)号：EP3587845A1

    公开(公告)日：2020-01-01

    申请号：EP19182757.5

    申请日：2019-06-27

    申请人： Sikorsky Aircraft Corporation

    发明人： WITTKE, Kevin M. ,  HOWARD, Bertrand J.

    IPC分类号： F16C19/52 ,  B64C11/32 ,  B64C27/59 ,  B64C27/605 ,  B64C27/78 ,  B64C27/82 ,  F16C19/54 ,  F16C39/02

    摘要： An aircraft rotor system includes a rotating pitch change shaft which rotates about an axis, a translating element disposed within the rotating pitch change shaft and movable along the axis and a pitch change bearing assembly which transfers movement of the translating element to the pitch change shaft. The pitch change bearing assembly includes a primary bearing and a secondary bearing coupled to the rotating pitch change shaft via the translating element when the primary bearing is in a first mode. A thrust shoulder is coupled to the translating element. The thrust shoulder is movable into engagement with the secondary bearing in response to failure of the primary bearing such that in a second mode, movement of the translating element is primarily transferred to the pitch change shaft via the secondary bearing.

    ADJUSTMENT OF TRACK AND BALANCE OF A MULTI-BLADE ROTOR
    29.
    发明授权
    ADJUSTMENT OF TRACK AND BALANCE OF A MULTI-BLADE ROTOR 有权

    公开(公告)号：EP3296198B1

    公开(公告)日：2018-11-14

    申请号：EP16400042.4

    申请日：2016-09-15

    申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH

    发明人： Büsing, Moritz

    IPC分类号： B64C27/00 ,  B64C27/605 ,  B64C11/32 ,  B64C27/32 ,  B64C27/59 ,  B64C27/72

    CPC分类号： B64C27/59 ,  B64C11/32 ,  B64C27/008 ,  B64C27/32 ,  B64C27/605 ,  B64C2027/7216

    摘要： The invention is related to a multi-blade rotor (1) of a rotary wing aircraft, the multi-blade rotor (1) comprising at least one rotor blade (2) that defines a pitch axis (3) and that is provided with an associated pitch-control lever (5) that is operatively coupled to a pitch link rod (4), the pitch link rod (4) defining a longitudinal axis (4a), wherein the associated pitch-control lever (5) comprises an accommodation (5a) that is located on the longitudinal axis (4a) of the pitch link rod (4) at a predetermined distance (4c) from the pitch axis (3) of the at least one rotor blade (2), the pitch link rod (4) being operatively coupled to the associated pitch-control lever (5) at the accommodation (5a) of the associated pitch-control lever (5), wherein the predetermined distance (4c) is adjustable in order to enable adjustment of track and balance of the multi-blade rotor (1).

    MULTI-SHAFT POWER SOURCE UNMANNED FLIGHT EQUIPMENT
    30.
    发明公开
    MULTI-SHAFT POWER SOURCE UNMANNED FLIGHT EQUIPMENT 审中-公开
    多轴电源无人飞行设备

    公开(公告)号：EP3279087A1

    公开(公告)日：2018-02-07

    申请号：EP17182959.1

    申请日：2017-07-25

    申请人： Ewatt Technology Co., Ltd.

    发明人： ZHAO, Guocheng ,  LUO, Wei ,  QI, Pengcheng

    IPC分类号： B64C27/08 ,  B64C27/12 ,  B64C27/59 ,  B64D35/04

    CPC分类号： F02B61/04 ,  B64C27/08 ,  B64C27/12 ,  B64C27/14 ,  B64C27/59 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/108 ,  B64D35/04 ,  F02B67/06 ,  F02B73/00 ,  F02B75/16 ,  F16H1/222 ,  F16H7/02 ,  F16H37/065

    摘要： The present invention discloses a multi-shaft power source unmanned flight equipment, and belongs to the technical field of unmanned aerial vehicles. The multi-shaft power source unmanned flight equipment comprises a frame (1), a plurality of rotor sets (2) and a power device (3). The plurality of rotor sets (2) are rotatably fixed on the frame (1), and the power device (3) is correspondingly movably connected with each rotor set (2) respectively. Power is provided for flight of the unmanned flight equipment by the power device (3) with oil drive characteristics, mechanical kinetic energy is generated by burning a combustion material pre-injected in the power device (3), and rotors (21) in each rotor set (2) correspondingly connected with the power device are driven to rotate, thereby replacing the traditional electric multi-rotor unmanned aerial vehicle structure adopting electric modes such as batteries, electronic speed controllers and the like to supply power and provide power for the rotation of the rotors (21); and the unmanned flight equipment has the characteristics of long duration and strong loading capacity.

    摘要翻译： 本发明公开了一种多轴动力源无人飞行器，属于无人机技术领域。 该多轴动力源无人飞行器包括机架（1），多个转子组（2）和动力装置（3）。 多个转子组（2）可转动地固定在机架（1）上，动力装置（3）分别与每个转子组（2）对应活动连接。 动力装置（3）为具有油驱特性的无人飞行装备提供动力，通过燃烧预先注入动力装置（3）中的燃烧材料产生机械动能，并且每个转子（21）中的转子 驱动与动力装置对应连接的转子组（2）旋转，从而代替采用电池，电子调速器等电动模式的传统电动多旋翼无人机结构为旋转动力提供动力并提供动力 的转子（21）; 无人飞行器具有持续时间长，载重能力强的特点。