跨声速机翼颤振现象计算与分析  

Calculation and Analysis of Transonic Wing Flutter

作　　者：盖京波[1] 高扬[1] 胡麒麟[1] 

机构地区：[1]哈尔滨工程大学航天与建筑工程学院,黑龙江哈尔滨150001

出　　处：《西安航空学院学报》2015年第5期17-19,共3页Journal of Xi’an Aeronautical Institute

基　　金：中央高校基本科研业务费专项基金(HEUCF130208)

摘　　要：机翼颤振是气动弹性的一个重要现象,并且是飞机结构破坏的一个主要原因。在跨声速阶段颤振临界速度呈现的"凹坑"现象,使得颤振最易在这一阶段发生。亚声速阶段利用偶极子网格法,超声速阶段利用ZONA51法,计算了AGARD 455.6机翼跨声速附近的颤振速度。总结其临界速度变化规律,符合跨声速阶段的"凹坑"现象。研究方法和所得结论具有普遍适用性,能够对跨声速机翼颤振速度做出较为简单方便但依旧精确的估算。Flutter is an important phenomenon of aeroelasticity ,also the main cause of airplane destruction . The pit that the flutter speed curve shows in transonic implies flutter is most likely to take place in tran‐sonic stage .In this paper ,double lattice method and ZONA51 method are adopted respectively in subsonic and supersonic ,which are used to compute the flutter speed in the range of transonic .The summarized flutter speed curve reveals the consistency with the phenomenon during the transonic stage . Research methods and conclusions are generally applicable ,and can be used to estimate transonic flutter speed more simply but still accurately .

关 键 词：跨声速 颤振 AGARD455.6机翼 颤振速度 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]