悬停状态下无铰旋翼模型气弹稳定性试验

通过悬停状态下2m直径旋翼模型试验, 研究了旋翼结构参数及动力学参数对无铰旋翼桨叶气弹稳定性的影响, 参数包括桨叶总距角、预锥角、预掠角、摆振频率和旋翼转速。桨叶为挥-摆-扭耦合结构, 并能构成面内柔软和面内刚硬旋翼。试验采用在垂直方向以摆振后退型频率进行周期变距激振的新方法, 得到了与理论相一致的结论。 

AN EXPERIMENT ON AEROELASTIC STABILITY OF A HINGELESS ROTOR MODEL IN HOVER

A 2 m diameter,soft inplane or stiff inplane,isolated hingeless rotor model in hover has been tested to investigate its aeroelastic stability.The hingeless rotor blade is constructed with flap lag torsion coupling.The investigation aims at effects of structural and dynamic parameters,such as the collective pitch,precone,sweep,blade lag frequency and rotor rotational speed on the aeroelastic stability.A new and simple technique is applied to the tests so that the excitation of cyclic pitch is accomplished at the blade lag regressing frequency in vertical direction.The experiment shows that the aeroelastic stability of the hingeless rotor blade in hover is slightly influenced by the rotor rotational speed and the blade sweep,but strongly influenced by the collective pitch,precone and blade lag frequency.