基于地面共振试验的操纵面间隙非线性颤振分析方法  

A numerical method based on ground vibration test for flutter analysis of the control surface with freeplay nonlinearity

作　　者：陈文[1] 窦忠谦[1] 何俊 章俊杰[1] CHEN Wen;DOU Zhongqian;HE Jun;ZHANG Junjie(Shanghai Aircraft Design and Research Institute,Commercial Aircraft Corporation of China Ltd.,Shanghai 201210,China)

机构地区：[1]中国商飞上海飞机设计研究院,上海201210

出　　处：《振动与冲击》2020年第16期75-80,共6页Journal of Vibration and Shock

基　　金：国家自然科研基金项目(11002162)。

摘　　要：以某型民机带中心对称间隙的方向舵为研究对象。按动力相似准则设计了尾翼颤振风洞模型,通过地面共振试验获得不同操纵刚度和自由间隙组合情况下方向舵旋转模态的力频曲线,根据收敛的频率值获得有限元模型作动器单元的等效刚度,经动力学特性修正后的有限元模型进行了颤振分析。风洞试验后通过比较表明,计算结果与试验结果吻合:①颤振速度一致;②颤振频率的偏差不大于6.5%;③颤振型一致。由此可见,根据试验频率得到的等效操纵刚度是准确的,用来预测弹性操纵面的极限环振荡临界速度是可行的,可以作为民机适航符合性验证的一种手段。A rudder with central symmetric freeplay of a civil transport airplane was investigated.A tail flutter wind tunnel model was designed according to the dynamic similarity criterion.The force-frequency curves of rudder rotational modes in various combinations of control stiffness and freeplay were achieved by ground vibration test.The equivalent stiffness of actuator element of the finite element model was achieved according to the convergent frequencies.The flutter analysis was carried out based on the dynamical updating finite element model.The numerical results are in good agreement with the test data.①The calculated flutter speed is close to the test data.②The difference of flutter frequencies between simulation and test are less than 6.5%.③The flutter modes are the same between simulation and test.The validated equivalent control stiffness achieved by test frequencies can be used to predict the LCO critical velocity of elastic control surface.The method can also be proof of compliance for airworthiness standards.

关 键 词：地面共振试验 操纵面 间隙 非线性 颤振 适航验证 

分 类 号：TH212[机械工程—机械制造及自动化] TH213.3