直升机旋翼瞬态气弹运动有限元模型研究

Research on Rotor Aeroelastic FEM Model in Transitional Flight

摘要:

从能量变分原理出发建立了旋翼的瞬态气弹有限元模型,模型考虑了旋翼转速加速度对桨叶动能变分的影响。采用叶素理论建立了桨叶在复杂流场中的气动载荷模型,模型计入了旋翼主轴纵倾和横滚角的影响,研究了流场风速分量的计算。运用所建模型仿真分析了直升机在护卫舰尾流场内起动时桨叶的挥舞、摆振、扭转(变距)等瞬态运动过程。模型可用于旋翼的振动仿真分析、噪声估计和故障诊断方法的验证。

Abstract:

A finite element model of the aeroelastic helicopter rotor in transitional flight is built from the energy variation principle, the blade response to the transient rotor speed is especially considered. The elemental aerodynamic forces are figured out according to the rotor element theory in more complex inflow model. All components of wind velocity and pitch angle and roll angle of the main rotor shaft are considered in the air speed calculation. The transient responses of the blade in flap, lag and pitch displacement are simulated using a frigate wake flow. The model here can be widely used in the vibration analysis, noise estimation or fault diagnosis of the helicopter rotor.