飞机发动机唇口防冰对飞行安全具有十分重要的意义,对于热气防冰系统,防冰腔的解耦形式对防冰的效果影响很大。本文以某无人机发动机进气道防冰系统为模型,针对双蒙皮防冰腔结构进行了仿真分析,在不同的飞行状态、环境和引气条件下,对防冰表面温度、水膜厚度、溢流水状态进行计算,为防冰系统的设计提供依据。 Anti-icing on the lip of aircraft engine is of great significance for flight safety. For the anti-ice system, the decoupling form of anti-icing cavity has a great effect on the anti-icing effect. In this paper, taking the anti-icing system of a drone engine inlet as a model, this paper simulates the structure of the double-skin anti-icing chamber. Under different flight conditions, environment and air entrainment conditions, the anti-ice surface temperature, Thickness, overflow water state calculation, provide the basis for the anti-ice system design.