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将现有单旋翼实验台进行改装,以适合于纵列式双旋翼的实验研究。基于PIV技术,针对悬停和前飞状态下的纵列式双旋翼时的桨尖涡特性进行了测量。通过改变前后旋翼的水平和轴向间距,调整两旋翼之间的重叠区域,研究了不同气动布局纵列式双旋翼干扰状态下的尾迹结构,并与单旋翼进行了对比。结果表明:悬停状态,随两旋翼纵向间距的增加,桨尖涡的轴向位移也逐渐增大,但桨尖涡径向位移并不是随纵向间距的改变而规律变化,在纵向间距为1.8R附近时最小;而双旋翼轴向间距的变化对桨尖涡的径向和轴向位移均有影响,但变化都不是很大。
The existing single-rotor test-bed modified for tandem dual-rotor experimental study. Based on the PIV technique, the tip vortex characteristics were measured when the tandem twin rotors were hovering and pre-flying. By changing the horizontal and axial distances of the front and rear rotors and adjusting the overlapping area between the two rotors, the wake structure of the tandem twin rotor with different aerodynamic layout is studied and compared with the single rotor. The results show that the axial displacement of tip vortex also increases with the increase of longitudinal distance between two rotors, but the radial displacement of tip vane does not change regularly with the change of longitudinal distance, and the longitudinal distance is 1.8 R near the smallest; and the change of the axial distance between the two rotor blade tip vortex radial and axial displacement are affected, but the change is not great.