悬停状态下无铰式旋翼动力学参数试验研究

An Experimental Investigation for the Dynamic Parameters of Helicopter Hingeless Rotor in Hover Condition

旋翼结构参数及动力学参数对旋翼动力学特性有着重要影响。随着旋翼结构型式的不断更新，在旋翼设计中需要考虑的动力学参数也相应增加，从而使旋翼的动力学问题更加复杂化。本文通过在２米旋翼试验台上进行的试验，用测量桨叶频响函数和稳态响应的方法研究了悬停状态预锥角、预掠角和总距角等旋翼结构参数对桨叶固有特性及气动弹性稳定性的影响规律，并同计算结果进行了比较。

The dynamic characteristics of a helicopter hingeless rotor in hovor condition are studied by tests. The natural frequency and aeroelastic of the rotor are examined for different rotor structural parameters. Some experimental results are given and discussed.