直升机旋翼积冰的数值模拟

Numerical simulation of ice accretion on helicopter rotor

为研究直升机旋翼桨叶积冰问题,通过对积冰形成机理和直升机飞行原理的分析,建立了基于CFD(Computational Fluid Dynamics)技术的直升机旋翼桨叶结冰预测的理论模型;采用欧拉法求解水滴控制方程,在经典Messinger模型的基础上提出了积冰表面质能平衡的改进模型;以UH-60型直升机和CH-47型直升机为样机,具体分析了积冰条件下直升机桨叶冰形预测的方法,为进一步研究直升机结冰后的飞行动力学问题及防除冰系统的设计奠定了基础,对提高直升机飞行安全性具有积极意义.

In order to study the prediction of ice accretion on helicopter rotor,a theoretical rotor icing model was founded based on the computational fluid dynamics（CFD） technique by analyzing the theory of ice accretion and helicopter flight.Euler two-phase flow theory was used in solving the governing equations corresponding to droplets,and a modified model of the mass and heat transfer on ice surface was proposed based on the classical Messinger model.The method of prediction of ice shape on rotor was analyzed detailedly by using UH-60 and CH-47 as examples,and they can lay the foundation of the research about the helicopter dynamics in the icing condition and the design of anti/de-ice system.The result shows that the method has positive significance of improving the flight safety performance of helicopter.