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******** Shi * ho *** i ***** ne *** ha ******* e ***** e *** ku *** su *** ****** shi * ku **

机译:******** shi * 好哦 *** i ***** 呢 *** 哈 ******* 哦 ***** 哦 *** 哭 *** 苏 *** ****** 是 * 哭 **

摘要

A fully articulated helicopter rotor having an elastomeric type main bearing which is reactive of all blade motions about the intersecting blade pitch change, lead-lag, and coning axes, including blade droop supporting and limiting members for static and dynamic operating conditions wherein coupling influences between the separate blade motions are precluded. In reacting these blade weight loadings and dynamic thrust forces, the droop members specifically provide full area contact bearing surfaces to distribute the large forces from the blades into the rotor hub proper while avoiding scuffing or rolling contact between the parts, and the high bearing stresses which would result from either point or line contact only.
机译:一种全铰接的直升机旋翼,具有弹性体型主轴承,该主轴承可响应所有桨叶围绕相交桨距变化,超前滞后和圆锥轴线的运动,包括用于静态和动态工况的桨叶下垂支撑件和限制件,其中,耦合影响排除了单独的刀片运动。在应对这些叶片重量载荷和动态推力时,下垂部件专门提供了全面积接触轴承表面,以将来自叶片的大力分配到适当的转子轮毂中,同时避免部件之间的擦伤或滚动接触以及高轴承应力仅由点或线接触引起。

著录项

  • 公开/公告号JPS5195396A

    专利类型

  • 公开/公告日1976-08-20

    原文格式PDF

  • 申请/专利权人

    申请/专利号JP19760001966

  • 发明设计人

    申请日1976-01-09

  • 分类号B64C27/32;B64C27/35;B64C27/48;

  • 国家 JP

  • 入库时间 2022-08-23 03:05:24

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