飞机T型尾翼跨音速颤振特性研究  

Transonic flutter characteristics of aircraft T-tail

作　　者：杨飞[1] 杨智春[2] 

机构地区：[1]中国商飞上海飞机设计研究院强度部,上海200232 [2]西北工业大学航空学院,西安710072

出　　处：《振动与冲击》2013年第10期50-54,共5页Journal of Vibration and Shock

基　　金：国家自然科学基金(11072198);高等学校学科引智计划(B07050)资助

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。Due to the features of T-tail in structural and aerodynamic configurations, the effects of in-plane motion and steady aerodynamics of horizontal plane, as well as the inaccuracy in the calculation of transonic compressibility and unsteady transonic flow, the transonic flutter calculation of aircraft T-tail is much more difficult. In the analysis of transonic flutter of aircraft T-tail priority should be given first to transonic wind tunnel test and then to calculation. For a certain type of aircraft T-tail, the transonic flutter characteristics were simulated by using the method of ZTAIC in software ZAERO and the effects of Mach number, flow air density and stabilizer attack angle were investigated. The well known 'transonic dip' phenomenon and compressibility characteristic of the T-tail model were captured based on the present method in transonic wind tunnel tests and at the same time calculated by using the method of lift curve slope compressibility correction. The results of these two methods are in good agreement.

关 键 词：跨音速 颤振 T型尾翼 风洞 试验 跨音速凹坑 压缩性 

分 类 号：V215.3[航空宇航科学与技术—航空宇航推进理论与工程]