基于旋翼冰风洞试验数据,考虑桨叶表面附着冰脱落及桨叶表面局部温度对结冰的影响,提出了旋翼结冰的工程模型,建立了直升机旋翼结冰后的飞行动力学模型,以UH-60A为样机,研究了直升机旋翼结冰后的平衡特性,分析了结冰对直升机稳定性的影响。根据有人驾驶垂直/短距起落飞机军用品质规范(MIL-F-83300)与军用旋翼飞行器驾驶品质要求(ADS-33E-PRF),分析了结冰时间、环境温度、液态水含量以及平均水滴直径对旋翼结冰后的直升机开环状态下的操纵特性、姿态敏捷性、轴间耦合特性以及垂直轴操纵功效的影响。计算结果的对比分析显示,旋翼结冰模型合理,直升机飞行动力学模型计算精度高,能够用来研究直升机旋翼结冰后的飞行动力学问题。

Based on the rotor icing tunnel data, and considering the effect of rotor blade ice shedding and local temperature variation on the rotor blade icing, an engineering rotor icing model is advanced. Then a flight dynamics model is built of a single rotor helicopter due to icing. The trim characteristics and stability of a UH-60A helicopter in icing conditions at the hover and in the forward flight are studied in detail. Using the military specification flying qualities of piloted V/STOL aircraft (MIL-F-83300) and the handling qualities requirements for military helicopters (ADS-33E-PRF), the effect of icing on the controllability, attitude quickness, interaxis coupling, and vertical axis control power of the helicopter open-loop system are analyzed in terms of icing time, atmospheric temperature, liquid water content, and median volumetric diameter. Calculation results indicate that the rotor icing model and the iced helicopter dynamics model are feasible and effective, and that they can be used to investigate issues in helicopter dynamics in rotor icing conditions.