机翼结冰分析与防除冰系统设计验证

飞机在结冰条件下飞行时可能发生结冰,飞机一旦结冰,会对安全飞行带来较大的隐患,如何降低飞机结冰带来的危害已成为飞机设计研究的重点内容.通过FENSAP-ICE对机翼进行数值模拟,并通过改进Messinger结冰热力学模型模拟更加真实的飞行情况;分析不同飞行环境下,飞机结冰前后机翼气动特性的变化,同时针对机翼设计一套防除冰系统并验证其可行性.结果表明:飞行速度越大,机翼表面的局部水收集系数越大;环境温度会影响机翼结冰的类型和结冰厚度,机翼发生结冰时,其升力系数减小、阻力系数增大,机翼的气动特性受到严重的影响;设计的电热防冰系统可以有效地预防机翼表面结冰,也可以进行周期性除冰.

Analyses ofAircraft Icing and Design of Anti-icing System

Abstract:When flying in the conditions of icing,aircraft is more probably to arise the phenomena of icing.Once the aircraft iced up,There exists hidden dangers to the safety of the plane.So reducing the harm caused by it that becomes an important research topic.Based on FENSAP-ICE,I will beign the numerical simulation of wings through Improving thermodynamic model of Messinger icing ,which simulates more realistic flight conditions. To analyse changes of aerodynamic characteristics of wings before and after aircraft icing under the different flight conditions,Therefore verity the feasibility of the way through the C3D of FENSAP-ICE.The result indicates that environment temperature will affect the type and thickness of wing icing. the wings iced up,which caused the decrease of lift cofficient and the increase of drag cofficient and affected the areodynamic characteriseics of aircarft seriously.It is obvious that the electrothermal anti-icing system which designed not only can effectively prevent icing on the surface of the wing,but also can deice periodically.