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1. 发明申请

WO2006135405A3 HELICOPTER VIBRATION CONTROL SYSTEM AND ROTARY FORCE GENERATOR FOR CANCELING VIBRATIONS 审中-公开
标题翻译：直升机振动控制系统和旋转发电机取消振动
公开(公告)号：WO2006135405A3
公开(公告)日：2007-02-22
申请号：PCT/US2005030909
申请日：2005-08-30
申请人： LORD CORP , JOLLY MARK , HILDEBRAND STEPHEN , ALTIERI RUSSELL , IVERS DOUGLAS , FERGUSON MATTHEW
发明人： JOLLY MARK , HILDEBRAND STEPHEN , ALTIERI RUSSELL , IVERS DOUGLAS , FERGUSON MATTHEW
IPC分类号： B64C27/00
CPC分类号： F16F15/265 , B64C27/001 , B64C2027/003 , F16F15/22 , F16F15/267
摘要： A helicopter rotating hub mounted vibration control system (20) for a helicopter rotary wing hub (22) having a periodic vibration (24) while rotating at a helicopter operational rotation frequency (26) . The helicopter rotating hub mounted vibration control system (20) includes an annular ring rotary housing (30) attachable to the helicopter rotary wing hub (22) and rotating with the helicopter rotary wing hub (22) at the helicopter operational rotation frequency (26) . The annular ring housing is centered about the rotary wing hub axis of rotation and has an electronics housing cavity subsystem (32) and preferably an adjacent coaxial rotor housing cavity subsystem (34) . The rotor housing cavity subsystem (34) contains a first coaxial frameless AC ring motor (36) having a first rotor with a first imbalance mass (40) and a second coaxial frameless AC ring motor (42) having a second rotor with a second imbalance mass (46) . The electronics housing cavity subsystem (32) contains an electronics control system (50) which receives sensor outputs and electrically controls and drives the first coaxial frameless AC ring motor (36) and the second coaxial frameless AC ring motor (42) such that the first imbalance mass (40) and the second imbalance mass (46) are directly driven at a vibration canceling rotation frequency (52) greater than the helicopter operational rotation frequency wherein the helicopter rotary wing hub periodic vibration (24) is reduced.
摘要翻译：一种用于在直升机操作旋转频率（26）旋转的同时具有周期性振动（24）的直升机旋转翼形轮毂（22）的直升机旋转轮毂安装的振动控制系统（20）。直升机旋转轮毂安装的振动控制系统（20）包括环形环旋转壳体（30），其可连接到直升机旋转翼毂（22）并且以直升机操作旋转频率（26）与直升机旋转翼毂（22）一起旋转，。环形壳体围绕旋转翼轮毂旋转轴线居中，并且具有电子器件壳体空腔子系统（32），并且优选地是相邻的同轴转子壳体空腔子系统（34）。转子壳体腔子系统（34）包含第一同轴无框架AC环形电动机（36），其具有具有第一不平衡块（40）的第一转子和具有第二不平衡的第二转子的第二同轴无框架AC环形电动机（42）质量（46）。电子设备壳体腔子系统（32）包含电子控制系统（50），其接收传感器输出并电控制并驱动第一同轴无框架AC环形电动机（36）和第二同轴无框架AC环形电动机（42），使得第一不平衡质量（40）和第二不平衡质量（46）以大于直升机旋转翼毂周期性振动（24）减小的直升机操作旋转频率的减振旋转频率（52）直接驱动。

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