颤振边界预测的系统稳定性分析方法  

Flutter boundary prediction research depending on system stability analysis methods

作　　者：李扬[1] 周丽[1] LI Yang;ZHOU Li(State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China)

机构地区：[1]南京航空航天大学机械结构力学及控制国家重点实验室,南京210016

出　　处：《航空动力学报》2018年第4期980-988,共9页Journal of Aerospace Power

基　　金：国家自然科学基金(51475228);江苏省普通高校研究生科研创新计划(CXZZ13_0146);机械结构力学及控制国家重点实验室(南京航空航天大学)开放课题资助(MCMS-0517K01);江苏高校优势学科建设工程资助

摘　　要：对颤振边界预测方法中的颤振裕度法与自回归滑动平均模型(ARMA)稳定性分析方法进行研究,采用数值仿真算例研究这两种方法受参数识别误差的影响,采用风洞颤振试验算例对比分析其预测颤振边界的有效性与准确性,结果表明:(1)颤振裕度法的判据受阻尼比识别误差的影响较小,相对于阻尼比识别误差更容易受频率识别误差的影响,ARMA稳定性分析方法的判据相对于颤振裕度法更易受阻尼比识别误差的影响,颤振裕度法比ARMA稳定性分析方法鲁棒性更高;(2)对于机翼弯扭耦合颤振,两方法的判据变化趋势相近,相差采样频率4次方的数量级,两者随着风速的增加具有平缓的下降趋势,有助于较早地预测颤振边界;(3)对于面内弯曲为主的颤振,ARMA稳定性分析方法比颤振裕度法适用性更好。A research was made on two flutter boundary prediction methods：flutter margin method and auto-regressive and moving average model（ARMA）stability analysis method.The influence of parameter identification errors on the accuracy of boundary prediction was analyzed through numerical simulation case.And the prediction effectiveness of these two methods was analyzed by two wind tunnel flutter tests.The results showed that：（1）the identified damping error had less influence on the criterion of flutter margin method than the identified frequency error,and ARMA stability analysis method was more sensitive to the identified damping error than flutter margin method contrastively,thus the flutter margin method had better robustness than ARMA stability analysis method.（2）For wing bending-torsion coupling flutter,these two criterions had approximate variation curves,which differed in order of magnitude approximating to the biquadrate of the sampling frequency,and good decreasing trends helpful to predict flutter boundary in advance were presented.（3）For in-plane bending flutter,ARMA stability analysis method may have betterapplicability than flutter margin method.

关 键 词：颤振 边界预测 风洞试验 误差分析 颤振裕度 稳定性分析 

分 类 号：V216.24[航空宇航科学与技术—航空宇航推进理论与工程]