基于压电作动器的直升机旋翼振动主动闭环控制
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摘要
考虑直升机旋翼与空气流体的耦合作用,得出旋翼在流固耦合作用下的振动响应特性。基于压电效应,在旋翼前三阶模态变形最大处布臵压电片作为控制输入的作动器,由旋翼振动控制方程结合最优控制理论,同时考虑输出能量与振动控制效果,得到旋翼振动控制的闭环控制反馈增益矩阵;最后将反馈控制律作用于旋翼得到流固耦合环境下旋翼的控后振动响应,控制后的振动结果表明旋翼振动有所降低、桨毂载荷减小,说明振动控制律的有效性。
引文
1.尹春望,童国荣直升机振动水平控制技术途径探讨[J].直升机技术.2009年第4期
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6.周星德,姜冬菊.结构振动主动控制[M].北京:科学出版社,2003:37~54
2.Wood E R,Powers R,Cline J H,Hammond C E.On Developing and Flight Testing a Higher Harmonic Control System[J].Journal of the American Helicopter Society,1985,130(1):3~20.
3.Kessler C,Fuerst D,Arnold UTP.Open loop flight test results and closed loop status of the IBC syste m on the CH-53G helicopter[C].American helicopter Society 59th Annual Forum,2003.
4.Ford T.Vibration reduction and monitoring[J].Aircraft Engineering and Aerospace Technology.1991,71(1):21~24.
5.Kessler C,Fuerst D,Arnold U T P.Open loop flight test results and closed loop status of the IBC sy tem on the CH-53G helicopter[C].American helicopter Society 59th Annual Forum,2003.
6.周星德,姜冬菊.结构振动主动控制[M].北京:科学出版社,2003:37~54
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