摘要
简述了展向冰脊形成的机理及形状,介绍了国内外关于飞机结冰的研究现状。依据仿真计算和风洞试验结果,分析了展向冰脊对Y-8飞机副翼铰链力矩的影响。分析结果表明:大多数情况下,对称冰脊使得铰链力矩减小;不对称冰脊产生的最大铰链力矩系数超过飞行员能克服的数值。该项研究结果可为飞机防冰、除冰系统的设计及飞行员操纵提供参考。
This paper present the mechanism for forming process of spanwise ridge ice and its shape, and describes the current state of research about aircraft icing both at home and abroad. According to the re- sults of simulation and wind tunnel experiments, this paper analyzes the effects of spanwise ridge ice on aileron hinge moment of Y-8 aircraft. The results show that, in most cases, symmetrical ridge ice de- crease the hinge moment; the maximum hinge moment induced by asymmetrical ridge ice is beyond of pi- lot capability. The results give a reference for the design of anti-/de-icing systems and for the pilot han-dling of the aircraft.
出处
《飞行力学》
CSCD
北大核心
2015年第4期364-367,380,共5页
Flight Dynamics
关键词
结冰
展向冰脊
铰链力矩
ice accretion
spanwise ridge ice
hinge moment
