大型水陆两栖飞机T型尾翼颤振影响因素分析

Influencing factor of large amphibious aircraft T-tail flutter

T型尾翼由于布局形式的特殊性,颤振行为往往较常规布局复杂。根据大型水陆两栖飞机的研制需求,建立了T型尾翼颤振分析的理论模型,并开展了T型尾翼缩比模型颤振风洞试验,研究了T型尾翼的颤振特性及来流迎角、部件连接刚度、操纵面连接刚度等因素对颤振特性的影响。理论和试验结果均表明,大型水陆两栖飞机T型尾翼的颤振临界型态为垂尾扭转型颤振,其主要影响因素为来流迎角;在给定的范围内,部件连接刚度、操纵面连接刚度均对垂尾扭转型颤振影响不大。研究结果为大型水陆两栖飞机的研制提供了依据。

Due to the special configuration,flutter characteristics of T-tail empennage were more complicated than conventional configuration.Base on the design needs of large amphibious,T-tail flutter analysis modeling was constituted,and the experimentation of reduced scale T-tai1 model was carried out in the wind tunnel.By theoretical analysis and wind tunnel test,T-tail flutter characteristics of large amphibious aircraft and the influence of angle of attack,assembly connecting stiffness,control surface connecting stiffness upon T-tail flutter were studied.Results of analysis and test show that the critical flutter format of T-tail was torsion flutter of fin,angle of attack was the mainly influence factor.Within the given range,influences of assembly connect stiffness,control surface connecting stiffness were slight on T-tail flutter.It provides reference for the design of large firefighting amphibious aircraft.