为研究直升机旋翼模型结冰特性，利用哈尔滨冬季低温环境模拟结冰条件，在航空工业气动院（Aerodynamics Research Institute, AVIC）季节性移动式结冰风洞开展直升机旋翼模型结冰试验。基于1.5 m量级旋翼试验台及带加热除冰装置的直升机旋翼缩比模型，研究典型结冰试验状态下旋翼结冰情况及旋翼台振动水平、旋翼气动性能的变化，并分析了环境温度对旋翼结冰气动特性的影响。结果表明：旋翼桨叶结冰主要集中在前缘，从桨叶根部到桨尖方向，结冰厚度逐渐增加；试验中旋翼台振动水平持续恶化，同时旋翼气动性能显著下降；在更低的环境温度下，旋翼结冰没有进一步降低其气动性能。

In order to study the icing characteristics of helicopter rotor model, the icing test of helicopter rotor model was carried out in the natural icing wind tunnel of Aerodynamics Research Institute (AVIC) by using the low-temperature environment in Harbin in winter to simulate the icing conditions. Based on the 1.5 m rotor test rig and the helicopter rotor scale model with woven wire heater, the rotor icing conditions, the rotor vibration level and the rotor aerodynamic performance changes under typical icing test conditions were studied, and the influence of ambient temperature on the rotor aerodynamic characteristics was analyzed. The results show that the icing of rotor blades is mainly concentrated in the leading edge, and the icing thickness gradually increases from blade root to blade tip. In the test, the vibration level of the rotor table continues to deteriorate, and the aerodynamic performance of the rotor decreases significantly. At lower ambient temperatures, the rotor icing does not further degrade its aerodynamic performance.