悬停状态带磁流变减摆器直升机的动稳定性分析  

The helicopter dynamic stability analysis in hover condition using magneto-rheological dampers

作　　者：卫丽君[1] 李书[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《振动工程学报》2012年第6期745-751,共7页Journal of Vibration Engineering

基　　金：国家863计划项目资助(2012AA112201);国家自然科学基金资助项目(10772013);航空科学基金资助项目(20100251007);中央高校基本科研业务费专项奖金资助项目

摘　　要：建立了适用于直升机悬停状态动稳定性的磁流变减摆器模型,悬停状态下动力入流模型采用动量理论模型,与直升机旋翼/机体耦合动力学方程组联立,采用Simulink时域仿真的方法计算得到磁流变减摆器对悬停状态下直升机动稳定的影响,对比了不同电压下磁流变减摆器对桨叶挥舞摆振运动的影响。结果表明:对于磁流变减摆器,施加不同电压可得到不同的阻尼力,该性质可以抑制直升机悬停状态动不稳定性。Magneto-rheological damper model suitable for helicopter air resonance and momentum theory model of hover con- dition involving momentum theory were built in this paper. The equations of the two models with the dynamic equations of helicopter rotor/body coupling were solved by Simulink time domain simulation method to obtain the helicopter dynamic stability influenced by Magneto-theological damper and compared the blade flapping and lagging impacted by Magneto-theological dampers under different voltages. It could be conclude that under a certain voltage, Magneto-theological damper was not influenced by duel-frequent excitation, and was good at restraining the helicopter air resonance.

关 键 词：磁流变减摆器 悬停状态 动稳定性 时域 

分 类 号：V212.5[航空宇航科学与技术—航空宇航推进理论与工程] V214.42