T型尾翼颤振特性分析方法  

ANALYSIS OF T-TAIL FLUTTER

作　　者：吕斌[1] 吴志刚[1] 杨超[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《工程力学》2008年第2期230-234,共5页Engineering Mechanics

基　　金：国家自然科学基金项目(10432040;10502003);新世纪优秀人才计划(NCET-04-0170)

摘　　要：由于T型尾翼特殊的结构和气动布局形式,其颤振特性的分析比较复杂,飞行状态和一些常规分析可以忽略的参数如上反角都会对颤振速度有很大影响。针对这些特殊问题,分析了T型尾翼的颤振特性受平尾上反角、平尾上的定常气动力和固有振动形式等因素的影响。重点研究了T型尾翼颤振计算中特殊的附加非定常气动力,建立了T型尾翼非定常气动力和颤振分析方法。在低速风洞中开展了T型尾翼缩比模型的颤振试验,验证了分析方法。结果表明T型尾翼特殊的气动效应主要影响垂尾的弯扭耦合颤振形式,颤振速度随平尾攻角增加而降低,在设计中采用一定的平尾下反角设计能够提高T型尾翼的颤振速度。通过对试验结果的理论分析,阐述了这种效应产生的机理,并对实际设计提出建议。Due to the special structure and aerodynamic configuration, the flutter characteristic analysis of T-tail empennage is complicated and the flutter speed is influenced by flight condition and some parameters that had been omitted, e.g. stabilizer dihedral. To solve these problems, the influence of the dihedral of horizontalstabilizer, the steady lift on horizontal-stabilizer and oscillatory modality on T-tail flutter are analyzed. The special additive unsteady aerodynamic using in T-tail flutter is investigated especially, and it is been established that the analytic approach of unsteady aerodynamic and flutter for T-tail. In order to validate analytic method, the experimentation of reduced scale T-tail model was carried out in the low speed wind tunnel. According the result, the special aerodynamic of T-tail affects mainly the form of bend-torsion coupling of fin. The flutter speed descends with attack angle increasing of stabilizer, and it can improve the flutter speed by using the negative dihedral in design. According the theoretical analysis of test result, the mechanism of T-tail effect is explained and some suggestion is given for practical design.

关 键 词：气动弹性 T型尾翼 颤振 非定常气动力 上反角 定常升力 

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] V215.34