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 (20) including a first imbalance mass concentration rotor (28), a second imbalance mass concentration rotor (44), a third imbalance mass concentration rotor (38'), and a fourth imbalance mass concentration rotor (44'). The first imbalance mass concentration rotor has a first imbalance mass concentration rotor center axis of rotation (136) centered on the rotating assembly center rotation axis (28). The second imbalance mass concentration rotor has a second imbalance mass concentration rotor center axis of rotation (142) centered on the rotating assembly center rotation axis. The third imbalance mass concentration rotor has a third imbalance mass concentration rotor center axis of rotation (136') centered on the rotating assembly center rotation axis. The fourth imbalance mass concentration rotor has a fourth imbalance mass concentration rotor center axis of rotation (142') 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 CA2743447(A1) 申请公布日期 2010.06.17
申请号 CA20092743447 申请日期 2009.12.14
申请人 LORD CORPORATION 发明人 JOLLY, MARK R.;MEYERS, ANDREW D.
分类号 B64C27/00 主分类号 B64C27/00
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