带后缘附翼的桨叶气动扭转变形特性

Torsion of blade with trailing-edge flap under air loads

针对修正的Greensberg准定常气动理论建立了带后缘附翼的桨叶运动方程.在此基础上,研究了不同的附翼偏角下桨叶扭转角沿着展向的分布规律,同时,也研究了不同的附翼偏转角下桨叶挥舞方向的变形情况.数值结果表明:当附翼偏转角为6°时,桨尖的扭转角为-3.8°;当附翼偏转角为-6°时,桨尖的扭转角为3°.附翼偏转角对桨叶挥舞方向的变形也有很大的影响,当附翼偏转角为6°时,桨尖挥舞位移为0.16R,比附翼无偏转时减少了50.8%.因此,通过后缘附翼的偏转使桨叶产生扭转变形在理论上是可行的.

The method of twisting the blade using a trailing-edge flap is presented in this paper. The dynamic model of the rotor blade with the trailing-edge flap is developed based on the modified Greensberg quasi-static aerodynamic theory. The effect of flap deflection on the torsion of the blade is investigated. Results show that the angles of torsion are equal to -3.8° and 3° when the flap deflection is 6° and -6°, respectively. The flap deflection has a powerful effect on the blade bending deformation in flapping direction. When the flap deflection is 6°, the tip flapping displacement is 0. 16 R. It is decreased by 50. 8% in comparison with that without any flap deflection. So it is feasible to twist the blade by using the trailing-edge flap.