摘要
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。
It is important for aircraft safety to provide ice protection for engine inlet lip,the hot pressure air protection is used as a current method,the disassemble coupling quomodo of ice protection structure influences ice protection effect seriously. The article analysis the hot pressure air protection effects on the base of a pilotless aircraft engine inlet lip model,and calculates the surface temperature,water film thickness,overflowwater state on different flight state,provides the design foundation of ice protection system.
出处
《飞机设计》
2016年第6期58-64,共7页
Aircraft Design
关键词
热气防冰
进气道唇口
流场
结冰厚度
hot pressure air protection
engine inlet lip
model
thickness
