首先通过对旋翼桨叶叶素的受力分析,建立了适用于大入流角和大挥舞角的非线性旋翼桨叶挥舞方程。为了使所建立的挥舞方程具有更好的通用性,首次将Snel失速模型应用于直升机旋翼失速状态下升力系数的确定问题,并通过对特定翼型进行仿真试验,验证了Snel失速模型在旋翼问题研究中的有效性。试验表明该模型具有很好的准确性,且由于该模型中不含任何试验参数,实用性强。 First of all, through the analysis of the force of the blade propeller, a nonlinear blade rotation equation is established for large inflow angle and large swing angle. For the first time, the Snel stalling model is applied to determine the lift coefficient of a helicopter rotor stalling state. In order to make the swinging equation established more universal, the Snel stalling model is validated for the rotor problem The validity of the study. Experiments show that the model has a good accuracy, and because the model does not contain any test parameters, practicality.