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11. 发明授权

US08090482B2 Distributed active vibration control systems and rotary wing aircraft with suppressed vibrations 有权
标题翻译：具有抑制振动的分布式主动振动控制系统和旋翼飞机
公开(公告)号：US08090482B2
公开(公告)日：2012-01-03
申请号：US12288867
申请日：2008-10-24
申请人： Mark R. Jolly , Askari Badre-Alam , Russell E. Altieri , Andrew D. Meyers
发明人： Mark R. Jolly , Askari Badre-Alam , Russell E. Altieri , Andrew D. Meyers
IPC分类号： G05D1/00
CPC分类号： B64C27/001 , B64C2027/004 , B64C2027/005 , F16F15/002 , F16F15/223
摘要： An aircraft with an aerostructure and at least one rotating machine creating troublesome vibrations, with the aircraft including a power source outputting electromagnetic force generator power outputs, a first and second distributed active vibration electromagnetic force generator, the first and second force generator including a distributed electronic control system and an electromagnetically driven mass, the force generators fixed to the aerostructure at first and second distributed active vibration control system sites, and electrical power distribution lines connecting the force generators with the power source with the power outputs outputted to the electromagnetic force generators, and a distributed force generator data communications network linking together the first and second distributed electronic control systems wherein the distributed electronic control systems communicate force generator vibration control data through the distributed force generator data communications network independently of the electrical power distribution lines to minimize the troublesome vibrations.
摘要翻译：具有航空结构的飞机和至少一个旋转机器产生麻烦的振动，飞机包括输出电磁力发生器功率输出的电源，第一和第二分布式主动振动电磁力发生器，第一和第二力发生器包括分布式电子控制系统和电磁驱动质量块，将力发生器固定在第一和第二分布式主动振动控制系统位置处的航空结构，以及将力发生器与电源连接的电力分配线与输出到电磁力发生器的功率输出，以及将第一和第二分布式电子控制系统连接在一起的分布式力发生器数据通信网络，其中分布式电子控制系统通过分布式力发生器数据通信传递力发生器振动控制数据独立于电力配电线路以最小化麻烦的振动。

12. 发明申请

US20110259994A1 HELICOPTER VIBRATION CONTROL SYSTEM AND ROTATING ASSEMBLY ROTARY FORCES GENERATORS FOR CANCELING VIBRATIONS 审中-公开
标题翻译：直升机振动控制系统和旋转组件旋转发电机取消振动
公开(公告)号：US20110259994A1
公开(公告)日：2011-10-27
申请号：US13128901
申请日：2009-12-14
申请人： Mark R. Jolly , Andrew D. Meyers
发明人： Mark R. Jolly , Andrew D. Meyers
IPC分类号： B64C27/51 , G05D19/00 , F01D5/10
CPC分类号： B64C27/001 , B64C2027/003 , F16F15/22 , G05D19/02 , Y10S416/50
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.
摘要翻译：一种旋转叶片旋转毂安装的旋转组件振动控制系统（20），包括第一不平衡质量浓度转子（28），第二不平衡质量浓度转子（44），第三不平衡质量浓度转子（38'）和第四不平衡质量浓度转子（44'）。第一不平衡质量浓度转子具有以旋转组件中心旋转轴线（28）为中心的第一不平衡质量浓度转子中心旋转轴线（136）。第二不平衡质量浓度转子具有以旋转组件中心旋转轴为中心的第二不平衡质量浓度转子中心旋转轴线（142）。第三不平衡质量浓度转子具有以旋转组件中心旋转轴为中心的转子中心旋转中心轴（136'）的第三不平衡质量浓度。第四不平衡质量浓度转子具有以旋转组件中心旋转轴为中心的第四不平衡质量浓度转子中心旋转轴线（142'）。第一和第二不平衡质量浓度转子以大于旋转组件操作旋转频率的第一旋转速度被驱动，同时控制第一不平衡质量浓度和第二不平衡质量浓度的旋转位置，以产生第一旋转净力向量以抑制第一振动频率。第三和第四不平衡质量浓度转子以大于旋转组件操作旋转频率的第二旋转速度被驱动，同时控制第三不平衡质量浓度和第四不平衡质量浓度的旋转位置，以产生第二旋转净力向量来抑制第二振动频率。

13. 发明申请

US20100221110A1 HELICOPTER VIBRATION CONTROL SYSTEM AND ROTATING ASSEMBLY ROTARY FORCES GENERATORS FOR CANCELING VIBRATIONS 有权
标题翻译：直升机振动控制系统和旋转组件旋转发电机取消振动
公开(公告)号：US20100221110A1
公开(公告)日：2010-09-02
申请号：US12637174
申请日：2009-12-14
申请人： MARK R. JOLLY , ANDREW D. MEYERS
发明人： MARK R. JOLLY , ANDREW D. MEYERS
IPC分类号： B64C27/51
CPC分类号： B64C27/001 , B64C2027/003 , F04D27/02 , F04D29/662 , F16F15/223
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.
摘要翻译：一种旋转叶片旋转轮毂安装的旋转组件振动控制系统，包括第一不平衡质量浓度转子，第二不平衡质量浓度转子，第三不平衡质量浓度转子和第四不平衡质量浓度转子。第一不平衡质量浓度转子具有以旋转组件中心旋转轴为中心的第一不平衡质量浓度转子中心轴线旋转。第二不平衡质量浓度转子具有以旋转组件中心旋转轴为中心的第二不平衡质量浓度的转子中心轴旋转。第三不平衡质量浓度转子具有以转动组件中心旋转轴为中心的第三不平衡质量浓度转子中心轴旋转。第四不平衡质量浓度转子具有以旋转组件中心旋转轴为中心的第四不平衡质量浓度转子中心轴旋转。第一和第二不平衡质量浓度转子以大于旋转组件操作旋转频率的第一旋转速度被驱动，同时控制第一不平衡质量浓度和第二不平衡质量浓度的旋转位置，以产生第一旋转净力向量以抑制第一振动频率。第三和第四不平衡质量浓度转子以大于旋转组件操作旋转频率的第二旋转速度被驱动，同时控制第三不平衡质量浓度和第四不平衡质量浓度的旋转位置，以产生第二旋转净力向量来抑制第二振动频率。

14. 发明申请

US20090254230A1 Distributed active vibration control systems and rotary wing aircraft with suppressed vibrations 有权
公开(公告)号：US20090254230A1
公开(公告)日：2009-10-08
申请号：US12288867
申请日：2008-10-24
申请人： Mark R. Jolly , Askari Badre-Alam , Russell E. Altieri , Andrew D. Meyers
发明人： Mark R. Jolly , Askari Badre-Alam , Russell E. Altieri , Andrew D. Meyers
IPC分类号： G05B13/02 , G06F17/00
CPC分类号： B64C27/001 , B64C2027/004 , B64C2027/005 , F16F15/002 , F16F15/223
摘要： An aircraft with at least one rotating machine creating troublesome vibrations, the aircraft comprised of an aerostructure, the aircraft including: a power source, the power source outputting a plurality of electromagnetic force generator power outputs, the aerostructure including a plurality of distributed active vibration control system sites, at least a first distributed active vibration electromagnetic force generator, the first distributed active vibration electromagnetic force generator including a first distributed electronic control system and a first electromagnetically driven mass, the first distributed active vibration electromagnetic force generator fixed to the aerostructure at a first distributed active vibration control system site, at least a second distributed active vibration electromagnetic force generator, the second distributed active vibration electromagnetic force generator including a second distributed electronic control system and a second electromagnetically driven mass, the second distributed active vibration electromagnetic force generator fixed to the aerostructure at a second distributed active vibration control system site, a plurality of electrical power distribution lines, the electrical power distribution lines connecting the electromagnetic force generators with the power source with the electromagnetic force generator power outputs outputted to the electromagnetic force generators, a distributed force generator data communications network, the distributed force generator data communications system network linking together the at least first and second distributed electronic control systems wherein the distributed electronic control systems communicate force generator vibration control data through the distributed force generator data communications network independently of the electrical power distribution lines to minimize the troublesome vibrations.

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