摘要
根据气动弹性稳定性适航要求条款(CCAR25.629),研究了运输类飞机T型尾翼在结冰不利条件下的颤振特性问题。针对某大型灭火/水上救援水陆两栖飞机T型尾翼设计了低速颤振风洞模型,进行了翼面前缘不同结冰状态的颤振数值分析和风洞试验,同时采用阻尼外推法处理试验数据得到临界颤振速度。数值分析和试验结果表明,T尾颤振速度随前缘结冰积聚重量增大而有所提高,颤振形态仍属于垂尾弯扭耦合。
Base on the regulatory requirements C CAR25. 629 of eroelastic stability, the transport airplanes prob-lem is investigated after icing. For a lrge amphibious airplane T-tail＇ s flutter model, crried out flutter numerical analysis and wind tunnel test of different iceing accumulation on wing surface, and damping＇ s method is usd to extrapolate critical flutter speed. Numerical analysis and experimental results show flutter speed increases with the increase of the ice accumulation, and flutter form is coupled with vertical＇ s bending and torsion.
出处
《科学技术与工程》
北大核心
2016年第5期237-240,共4页
Science Technology and Engineering
关键词
T尾
颤振
翼面结冰
风洞试验
T-tail flutter iceing on wing surface wind tunnel test
