旋翼结构参数及动力学参数对直升机操纵稳定性的影响研究

Theoretical Investigation of Effects of Rotor Parameters on Helicopter Stability and Control

分析了直升机旋翼的预锥角、预掠角、桨叶根部的约束刚度和阻尼对直升机操纵性和稳定性的影响。旋翼的动力学模型采用有挥舞铰和摆振铰外伸量、桨叶根部在挥舞和摆振两个方向上都带有弹性约束的形式；旋翼桨盘处的诱导速度分布采用自前向后直线增大的形式。分析结果表明：旋翼的预锥角和预掠角对直升机全机的稳定性和操纵性的影响可以略去不计，而桨叶根部挥舞方向上的弹性约束刚度对直升机全机的操纵稳定性有较大影响，摆振方向上的弹性约束刚度和桨叶的摆振运动对直升机稳定性的影响不大，可以略去不计。

The effects of rotor parameters on helicopter stability and control is investigated. The rotor dynamical model takes the form of an articulated rotor with flap and lag hinge offset,precone and prelag angle and hinge spring. The distribution of induced velocity at the rotor is assumed linearly variable over the disk. The results show that the flap hinge spring rate has a great effect on helicopter stability and control, but precone and prelag angle,lag hinge spring rate and blade lag motion can be negligible.