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    AIRCRAFT AND FLIGHT SYSTEM
    191.
    发明公开
    AIRCRAFT AND FLIGHT SYSTEM 审中-公开

    公开(公告)号：EP3375707A1

    公开(公告)日：2018-09-19

    申请号：EP18161784.6

    申请日：2018-03-14

    Applicant: Ricoh Company Ltd.

    Inventor： SAKUMA, Hideomi

    IPC: B64C11/46 ,  B64C29/02

    CPC classification number: B64C29/02 ,  B64C11/46 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/146 ,  B64C2201/165 ,  G05D1/0808

    Abstract: An aircraft includes propellers (21, 22) at a center of the airframe (1); a first power source (23); a pitch adjuster (51-1, 51-2, 52); attitude control propellers (31-1, 31-2, 31-3, 31-4); a second power source (32-1, 32-2, 32-3, 32-4); and a control circuit (100) to control attitude of the airframe (1). The control circuit (100) includes a first yaw rotation generation control unit to control first yaw rotation generated by torques of the propellers (21, 22) with the pitch adjuster; and a second yaw rotation generation control unit to control a second yaw rotation generated by torques generated by a difference in rotation speed between the attitude control propellers (31-1, 31-2, 31-3, 31-4). The control circuit is configured to control the first yaw rotation generation control unit and the second yaw rotation generation control unit in accordance with a magnitude of a command value of yaw rotation.

    SYSTEM FOR INTEGRATING A DIESEL ENGINE IN A DRONE
    194.
    发明公开
    SYSTEM FOR INTEGRATING A DIESEL ENGINE IN A DRONE 审中-公开
    EINER DROHNE系统ZUM INTEGRIEREN EINES DIESELMOTORS

    公开(公告)号：EP2720943A1

    公开(公告)日：2014-04-23

    申请号：EP12731301.3

    申请日：2012-06-18

    Applicant: Cassidian SAS ,  EADS France

    Inventor： SOUTIF, Christophe ,  JOUBERT, Emmanuel

    IPC: B64C27/14 ,  B64C39/02 ,  B64D27/04

    CPC classification number: B64D27/02 ,  B64C27/14 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/044 ,  B64D27/04

    Abstract: The present invention relates to a rotary-wing drone (1) comprising a frame in which are located: - a set of sensors (13) designed for performing tasks of surveillance and/or intelligence gathering and/or assisting with the guidance of the drone (1), and - a control unit (14) associated with this set of sensors (13), characterized in that it comprises a diesel engine (4).

    Abstract translation: 本发明涉及一种旋转翼无人机（1），其包括框架，所述框架位于： - 一组传感器（13），其被设计用于执行监视和/或情报收集的任务和/或辅助无人机的引导 （1），和 - 与该组传感器（13）相关联的控制单元（14），其特征在于，其包括柴油发动机（4）。

    A coaxial transmission/center hub subassembly for a rotor assembly
    199.
    发明公开
    A coaxial transmission/center hub subassembly for a rotor assembly 失效
    KoaxialeÜbersetzungs-/ Zentriernaben-UnteranordnungfürRotoranordnung

    公开(公告)号：EP0861775A1

    公开(公告)日：1998-09-02

    申请号：EP97118360.3

    申请日：1993-06-18

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： CYCON, James P. ,  KOHLHEPP, Frederick, W., ,  MILLEA, Vincent, F.,

    IPC: B64C27/10 ,  B64C27/20

    CPC classification number: B64C27/10 ,  B64C27/14 ,  B64C27/20 ,  B64C27/33 ,  B64C27/605 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  F02B2075/025 ,  F16D3/06 ,  F16D3/185

    Abstract: A coaxial transmission/center hub subassembly (110) for a rotor assembly (100) of an unmanned aerial vehicle (10) having ducted, coaxial counter-rotating rotors (200, 202) defining a rotational axis (12) for the unmanned aerial vehicle (10), the unmanned aerial vehicle (10) having a toroidal fuselage (20) with a plurality of inwardly extending support struts (24) and including a powerplant subsystem (50), the rotor assembly (100) including upper and lower swashplate subassemblies (80), comprising:

    center hub support structure means (160, 146) intermediate said counter-rotating rotors (200, 202) for mounting said coaxial transmission/center hub (110) assembly in fixed coaxial relation to the toroidal fuselage (20) utilizing the plurality of inwardly extending support struts (24);
    a multi-member transmission housing (140); and
    a single stage transmission subsystem (120);
       characterized in that

    said multi-member transmission housing (140) includes upper and lower standpipe housings (142, 144) secured in combination with said center hub support structure means (160, 146) in opposed relation along the rotational axis (12) of the unmanned aerial vehicle (10), said upper and lower standpipe housings (142, 144) having external surfaces (142E, 144E) that function as sliding surfaces for the upper and lower swashplate subassemblies (80), respectively; and
    said single stage transmission subsystem (120) includes an upper bevel gear (128) that includes an upper rotor shaft (128R) rotatably mounted in combination with said upper standpipe housing (142), a lower bevel gear (130) that includes a lower rotor shaft (130R) rotatably mounted in combination with said lower standpipe housing (144), said upper and lower rotor shafts (128R, 130R) providing means for mounting the counter-rotating rotors (200, 202) in combination with said coaxial transmission/center hub subassembly (110), and an input gear (122) rotatably mounted in said center hub support structure means (160, 146) and being mechanically coupled in combination with said upper and lower bevel gears (128, 130) and the powerplant subsystem (50) to couple torque to the counter-rotating rotors (200, 202).

    Abstract translation: 一种用于无人驾驶飞行器（10）的转子组件（100）的同轴传输/中心轮毂子组件（110），其具有限定用于无人驾驶飞行器的旋转轴线（12）的导管同轴对转转子（200,202） （10），具有环形机身（20）的无人驾驶飞行器（10）具有多个向内延伸的支撑支柱（24）并且包括动力装置子系统（50），所述转子组件（100）包括上部和下部斜盘组件 （80），包括：中间轮毂支撑结构装置（160,146），其位于所述反向旋转转子（200,202）之间，用于将所述同轴传动/中心毂（110）组件以固定的同轴关系安装到环形机身（20） 利用所述多个向内延伸的支撑支柱（24）; 多构件变速器壳体（140）; 和单级传输子系统（120）; 其特征在于，所述多构件变速器壳体（140）包括与所述中心轮毂支撑结构装置（160,146）组合的上和下立管壳体（142,144），所述上立管和下立管壳体沿着所述中心轮毂支撑结构装置（160,146）的旋转轴线 所述上和下立管壳体（142,144）分别具有用作上部和下部斜盘组件（80）的滑动表面的外表面（142E，144E） 并且所述单级传动系统（120）包括上锥齿轮（128），所述上锥齿轮（128）包括与所述上立管壳体（142）组合可旋转地安装的上转子轴（128R），包括下部锥形齿轮（130） 与所述下立管壳体（144）可旋转地安装的转子轴（130R），所述上转子轴和下转子轴（128R，130R）提供用于将所述反向旋转转子（200,202）与所述同轴传动/ 中心轮毂子组件（110）和可旋转地安装在所述中心轮毂支撑结构装置（160,146）中并与所述上锥形齿轮和下锥齿轮（128,130）机械耦合的输入齿轮（122）和动力装置子系统 （50）以将扭矩耦合到所述反向旋转转子（200,202）。

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