飞机T型尾翼跨音速颤振特性研究

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振动与冲击 ›› 2013, Vol. 32 ›› Issue (10) : 50-54.

论文

飞机T型尾翼跨音速颤振特性研究

杨飞1, 杨智春2

作者信息 +

A Research on Transonic Flutter Characteristic of Aircraft T-Tail

ANG Fei1 YANG Zhichun2

Author information +

文章历史 +

摘要

由于飞机T型尾翼的结构与气动布局特点，T型尾翼颤振计算不能套用常规尾翼的分析方法，而需要考虑平尾面内运动以及静升力等因素的影响。而跨音速空气压缩性效应和非定常气动力计算的不准确性，使得T型尾翼跨音速颤振计算更加困难，准确性较低。因此，需要采用试验为主计算为辅的方法来研究飞机T型尾翼跨音速颤振特性。针对某T型尾翼结构，用ZAERO软件等价片条势流跨音速颤振（ZTAIC）方法计算T型尾翼跨音速颤振特性，研究了马赫数、风洞气流密度和平尾迎角对T型尾翼颤振特性的影响。通过升力系数斜率空气压缩性修正计算方法和跨音速颤振模型风洞试验方法得到了飞机T型尾翼的跨音速颤振的凹坑曲线和空气压缩性特性，两种方法得到结果一致。

Abstract

The flutter calculation method to conventional aircraft tail wing can not be applied directly to T-tail flutter analysis due to its features in structural and aerodynamic configurations, and the effects of in-plane motion and steady aerodynamics of horizontal plane should be considered in T-tail flutter calculation. Because transonic compressibility and unsteady Transonic flow of T-tail is difficult, the transonic flutter of aircraft T-Tail calculation is more difficult and inaccurate. Transonic flutter of aircraft T-Tail calculation Method should give priority to transonic wind tunnel test and give secondary to calculation. For aircraft T-tail, the transonic flutter characteristic is also simulated using ZAERO soft ZTAIC and the effect of the Mach number, flow air density and stabilizer attack angle is investigated. The well known ‘Transonic Dip’ phenomenon and compressibility Characteristic has been captured for T-tail model using the present method in transonic wind tunnel and lift curve slope compressibility correct method. The results of the lift curve slope compressibility correct method agreed well with the transonic wind tunnel as T-tail model result.