发明名称 Helicopter vibration control system and rotating assembly rotary forces generators for canceling vibrations
摘要 A rotary blade rotating hub mounted rotating assembly vibration control system including a first imbalance mass concentration rotor, a second imbalance mass concentration rotor, a third imbalance mass concentration rotor, and a fourth imbalance mass concentration rotor. The first imbalance mass concentration rotor has a first imbalance mass concentration rotor center axis rotation centered on the rotating assembly center rotation axis. The second imbalance mass concentration rotor has a second imbalance mass concentration rotor center axis rotation centered on the rotating assembly center rotation axis. The third imbalance mass concentration rotor has a third imbalance mass concentration rotor center axis rotation centered on the rotating assembly center rotation axis. The fourth imbalance mass concentration rotor has a fourth imbalance mass concentration rotor center axis rotation centered on the rotating assembly center rotation axis. The first and second imbalance mass concentration rotors are driven at a first rotation speed greater than the rotating assembly operational rotation frequency while controlling the rotational position of the first imbalance mass concentration and the second imbalance mass concentration to produce a first rotating net force vector to inhibit a first vibration frequency. The third and fourth imbalance mass concentration rotors are driven at a second rotation speed greater than the rotating assembly operational rotation frequency while controlling the rotational position of the third imbalance mass concentration and the fourth imbalance mass concentration to produce a second rotating net force vector to inhibit a second vibration frequency.
申请公布号 US8435002(B2) 申请公布日期 2013.05.07
申请号 US20090637174 申请日期 2009.12.14
申请人 JOLLY MARK R.;MEYERS ANDREW D.;LORD CORPORATION 发明人 JOLLY MARK R.;MEYERS ANDREW D.
分类号 F01D5/10 主分类号 F01D5/10
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