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Coaxial Counter-Rotating Unmanned Helicopter

机译:同轴反旋转无人直升机

摘要

To configure the yaw axis control mechanism of a coaxial counter-rotating unmanned helicopter to be able to accurately control the pitch angle of the upper rotor blade by a simple configuration even if the precise adjustment is not performed. A rudder control rod is inserted into a main mast of a coaxial counter-rotating helicopter, a lower end portion thereof is connected to an output lever of the rudder servo, and a mixing rod head is fixed to an upper end portion. A link mechanism connected to the upper swash plate is attached to a side surface portion of the mixing rod head, the vertical displacement of the mixing rod head moving up and down together with the rudder control rod is converted into a displacement for tilting an upper blade holder around the spindle via the link mechanism, thereby changing the pitch angle of the upper rotor blades.
机译:为了配置同轴反向旋转无人直升机的偏航轴控制机构,即使不进行精确的调整,也能够通过简单的构造来精确地控制上旋翼桨叶的桨距角。方向舵控制杆插入同轴反向旋转直升机的主桅杆中,其下端部连接至方向舵伺服器的输出杆,并且混合杆头固定至上端部。连接到上斜盘的连杆机构附接到混合杆头的侧表面部分,混合杆头与方向舵控制杆一起上下移动的垂直位移被转换成用于倾斜上叶片的位移。通过连杆机构将其固定在主轴周围,从而改变上转子叶片的桨距角。

著录项

  • 公开/公告号US2015321754A1

    专利类型

  • 公开/公告日2015-11-12

    原文格式PDF

  • 申请/专利权人 HIROBO CO. LTD.;

    申请/专利号US201414272839

  • 发明设计人 TAKAKAZU UEBORI;SHUNICHI SUZUKI;

    申请日2014-05-08

  • 分类号B64C27/10;G05D1/00;B64C39/02;

  • 国家 US

  • 入库时间 2022-08-21 14:38:30

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