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Keller pressure jet rotor system

机译:凯勒压力喷射转子系统

摘要

A helicopter aircraft with an upper hollow center circular plenum in gaseous communication with a plurality of hollow hinged attached rotor blades. Below the plenum and in gaseous communication with it are two fan jet engines whose gaseous output can be inputted to the plenum and their attached hollow rotor blades through a operator controlled valve system. This same valve system can be adjusted to completely or partially by-pass the plenum and discharge the jet engines' gas to a common rear rudder located on the aircraft's to provide directional control to the aircraft when in flight. The plenum is shaped lenticular in cross section similar to an airplane wing to provide a lifting body when the helicopter is in forward flight.
机译:一种具有上部空心中心圆形增压室的直升机飞机,该增压室与多个空心铰接的旋翼叶片气态连通。在气室下方并与之气态连通的是两个风扇喷气发动机,其气体输出可通过操作员控制的阀门系统输入气室及其相连的空心转子叶片。可以调节该同一阀系统,以完全或部分绕过增压室并将喷气发动机的气体排放到位于飞机上的公共后舵,从而在飞行中为飞机提供方向控制。增压室的横截面形状类似于飞机机翼,当直升机在向前飞行时提供升力。

著录项

  • 公开/公告号US5984635A

    专利类型

  • 公开/公告日1999-11-16

    原文格式PDF

  • 申请/专利权人 KELLER;MERRILL MANSON;

    申请/专利号US19980138395

  • 发明设计人 MERRILL MANSON KELLER;

    申请日1998-08-24

  • 分类号B63H11/12;

  • 国家 US

  • 入库时间 2022-08-22 01:39:16

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