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

作　　者：吕继航 曾毅 罗琳胤 LYU Ji-hang;ZENG Yi;LUO Lin-yin(Strength Research Department, China Aviation General Aircraft Institute, Zhuhai 519040, China)

机构地区：[1]中航通飞研究院强度研究室,广东珠海519040

出　　处：《飞行力学》2018年第2期6-10,共5页Flight Dynamics

基　　金：工信部民机科研项目(MJ-2014-F-06)

摘　　要：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.

关 键 词：T型尾翼 颤振 影响因素 风洞试验 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程]